JP6726776B2 - Cooling structure for split ring of gas turbine and gas turbine having the same - Google Patents

Description

The present invention relates to a gas turbine rotated by combustion gas.

Conventionally, a rotary shaft, a turbine rotor blade that extends radially outward with respect to the rotary shaft, a split ring that is provided radially outward from the turbine rotor blade, and a turbine vane that is axially adjacent to the split ring. A gas turbine equipped with is known. The turbine vane and the split ring are arranged apart from each other, and a cavity extending in the circumferential direction and the radial direction is formed between the turbine vane and the split ring. Seal air discharged from the turbine vanes is flown through this cavity to prevent backflow of combustion gas.

The gas turbine is formed radially outside and has a cooling flow passage formed inside the split body for allowing cooling air supplied from a turbine casing or a blade ring cavity surrounded by the turbine casing and a blade ring to flow therein. A split ring cooling structure that cools the split ring by flowing cooling air through the cooling flow path is provided (for example, Patent Documents 1 and 2). As the cooling air, it is general to use vehicle compartment air on the compressor outlet side or bleed air extracted from the compressor. In the split ring cooling structure described in Patent Document 1, a cooling flow path for flowing cooling air in the flow direction of the combustion gas is formed inside the split body. The cooling flow passage has an opening to which cooling air is supplied at the upstream end in the flow direction of the combustion gas. In addition, the split ring cooling structure described in Patent Document 1 further includes cooling passages that are opened toward ends in the rotation direction at both ends of the split body on the front side and the rear side in the rotation direction.

In the split ring cooling structure described in Patent Document 2, a cooling flow path for flowing cooling air in the circumferential direction (the front side and the rear side in the rotation direction of the rotating shaft) is formed inside the divided body. Further, in Patent Document 2, a cooling flow passage for flowing cooling air to the front side in the rotation direction of the rotary shaft and a cooling flow passage for flowing cooling air to the rear side in the direction opposite to the rotation direction of the rotation shaft are combusted. They are arranged alternately in the gas flow direction.

International publication 2011/024242 US Pat. No. 5,375,973

As shown in Patent Document 1 and Patent Document 2, it is possible to cool the end portions in the rotation direction of the divided body by providing the cooling flow paths for flowing the cooling air toward both ends in the rotation direction of the divided body. Here, as the split ring cooling structure, there is room for improvement even in the split ring cooling structures of Patent Documents 1 and 2. The split ring cooling structures of Patent Document 1 and Patent Document 2 are complicated in structure, and there is a limit to improvement of utilization efficiency of cooling air.

Therefore, it is an object of the present invention to provide a split ring cooling structure capable of efficiently supplying cooling air and reusing the cooling air to efficiently cool the split ring, and a gas turbine having the split ring cooling structure. ..

In order to solve the above-mentioned problems, the present invention provides a split ring cooling structure for cooling a split ring of a gas turbine having a plurality of ring-shaped split bodies arranged in the circumferential direction, which shields the split body from the main body. A cavity surrounded by a heat ring and a blade ring, a collision plate supported by the divided body and provided with a large number of holes, and arranged along the inner peripheral surface of the divided body in the circumferential direction within the main body of the divided body. , The front side or the rear side in the rotation direction of the divided body, which extends in one direction without folding back and is radially inward from the outer surface of the divided body body facing the cavity covered by the collision plate. And a cooling flow path through which cooling air flows, the cooling air flow path is disposed inside the cavity, one end of which is opened to the cavity, and the other end of which is opened to a side end portion on the front side or the rear side in the rotation direction of the split body, The cooling flow passage has a first cooling flow passage from which the cooling air is discharged from the rear side in the rotation direction toward the front side, and the cooling air is discharged from the front side in the rotation direction toward the rear side. One of the second cooling flow path and the second cooling flow path are included.

According to this configuration, the convection cooling of the main body of the divided body in which one of the first cooling flow passage and the second cooling flow passage is arranged, and the impingement cooling of the outer surface of the main body in the radial direction are performed. Has a double-acting cooling structure. Further, the cooling flow passage can be simultaneously processed from the flow passage inlet to the side end opening by bending in the circumferential direction in a single processing up to the end opening. Therefore, the cooling air is reused, and both ends in the rotation direction of the divided body can be efficiently cooled with a simple structure. Thereby, the cooling air is efficiently supplied, the amount of the cooling air is reduced, and the split ring can be efficiently cooled.

In the cooling flow passages, it is preferable that the cooling flow passages arranged on the downstream side in the combustion gas flow direction are arranged at an arrangement pitch smaller than that of the cooling flow passages arranged on the upstream side in the combustion gas flow direction. ..

According to this structure, since the cooling air is discharged from both front and rear end portions in the rotation direction, both end cooling is further strengthened.

In order to solve the above-mentioned problems, the present invention is a gas turbine, wherein the turbine rotor blade attached to a rotatable turbine shaft and a turbine rotor fixed so as to axially oppose the turbine rotor blade. A vane, the split ring surrounding the turbine rotor blade in the circumferential direction, the casing arranged on the outer periphery of the split ring and supporting the turbine vane, and the split ring cooling structure according to any one of the above. And.

With this configuration, the split ring can be efficiently cooled, and the amount of cooling air discharged to the flow path of the combustion gas can be reduced. As a result, the efficiency of the gas turbine can be increased.

According to the present invention, by providing the first cooling flow path and the second cooling flow path communicating with the cavity, the cooling air is reused, and both ends in the rotation direction of the divided body are efficiently cooled with a simple structure. can do. Thereby, the cooling air is efficiently supplied, the amount of the cooling air is reduced, and the split ring can be efficiently cooled.

FIG. 1 is a schematic configuration diagram of a gas turbine according to the first embodiment. FIG. 2 is a partial cross-sectional view around the turbine of the gas turbine according to the first embodiment. FIG. 3 is a partially enlarged view of the vicinity of the split ring of the gas turbine according to the first embodiment. FIG. 4 is a perspective view of a divided body of the divided ring according to the first embodiment. FIG. 5 is a sectional view of a divided body of the divided ring according to the first embodiment. FIG. 6 is a schematic cross-sectional view of the split ring according to the first embodiment as viewed from the radial direction, and is a cross-sectional view taken along the line AA of FIG. FIG. 7 is a schematic cross-sectional view of the split ring according to the first embodiment as viewed from the flow direction of the combustion gas, and is a cross-sectional view taken along the line BB of FIG. 6. FIG. 8 is a schematic cross-sectional view of a divided body according to a modified example of the first embodiment as seen from the radial direction. FIG. 9 is a schematic cross-sectional view of the split body according to the second embodiment as viewed from the radial direction. FIG. 10 is a cross-sectional view of the split body according to the second embodiment as seen from the flow direction of the combustion gas, and is a cross-sectional view taken along the line C-C of FIG. 9. FIG. 11 is a schematic cross-sectional view of the split body according to the third embodiment as viewed from the radial direction. FIG. 12 is a schematic cross-sectional view of the split body according to the fourth embodiment as viewed in the radial direction. FIG. 13 is a schematic cross-sectional view of the split body according to the fifth embodiment as viewed from the radial direction. FIG. 14 is a schematic cross-sectional view of the split body according to the sixth embodiment as viewed from the radial direction. FIG. 15 is a schematic cross-sectional view of the split body according to the seventh embodiment as viewed from the radial direction.

Hereinafter, the present invention will be described with reference to the accompanying drawings. The present invention is not limited to the following embodiments. Further, the constituent elements in the following embodiments include those that can be easily replaced by those skilled in the art, or those that are substantially the same.

As shown in FIG. 1, the gas turbine 1 according to the first embodiment includes a compressor 5, a combustor 6, and a turbine 7. Further, a turbine shaft 8 penetrates through the central portions of the compressor 5, the combustor 6, and the turbine 7. The compressor 5, the combustor 6, and the turbine 7 are arranged in parallel along the axial center CL of the turbine shaft 8 from the upstream side to the downstream side in the flow direction FG of air or combustion gas.

The compressor 5 compresses air into compressed air. The compressor 5 is provided with a plurality of stages of compressor vanes 13 and a plurality of stages of compressor rotor blades 14 in a compressor casing 12 having an air intake 11 for taking in air. A plurality of compressor vanes 13 of each stage are attached to the compressor casing 12 and are arranged side by side in the circumferential direction, and a plurality of compressor blades 14 of each stage are attached to the turbine shaft 8 and are arranged in parallel in the circumferential direction. There is. The plurality of stages of compressor vanes 13 and the plurality of stages of compressor blades 14 are alternately provided along the axial direction.

The combustor 6 supplies a fuel to the compressed air compressed by the compressor 5 to generate high-temperature and high-pressure combustion gas. The combustor 6 serves as a combustion cylinder, an inner cylinder 21 that mixes and burns compressed air and fuel, a tail cylinder 22 that guides combustion gas from the inner cylinder 21 to the turbine 7, and an outer circumference of the inner cylinder 21. The outer cylinder 23 guides the compressed air from the inner cylinder 21. The combustor 6 is arranged in the turbine casing 31, and a plurality of combustors 6 are arranged in the circumferential direction. The air compressed by the compressor is temporarily stored in the vehicle compartment 24 surrounded by the turbine casing and then supplied to the combustor.

The turbine 7 produces rotational power by the combustion gas generated in the combustor 6. The turbine 7 is provided with a plurality of stages of turbine stationary blades 32 and a plurality of stages of turbine moving blades 33 inside a turbine casing 31 that serves as an outer shell. The turbine vanes 32 of each stage are attached to the turbine casing 31 and are arranged in a plurality of annular shapes in the circumferential direction, and the turbine rotor blades 33 of each stage are formed of a disc-shaped disk centered on the axis CL of the turbine shaft 8. It is fixed to the outer circumference and is arranged in a plurality of annular shapes in the circumferential direction. The plurality of stages of turbine stationary blades 32 and the plurality of stages of turbine moving blades 33 are alternately provided along the axial direction.

An exhaust chamber 34 having therein a diffuser portion 54 continuous with the turbine 7 is provided on the downstream side of the turbine casing 31 in the axial direction (see FIG. 1 ). The turbine shaft 8 is provided rotatably around the shaft center CL, with the end portion on the compressor 5 side being supported by the bearing portion 37 and the end portion on the exhaust chamber 34 side being supported by the bearing portion 38. A drive shaft of a generator (not shown) is connected to the end of the turbine shaft 8 on the exhaust chamber 34 side.

Hereinafter, the turbine 7 will be specifically described with reference to FIG. 2. As shown in FIG. 2, the turbine vane 32 includes an outer shroud 51, an airfoil portion 53 extending radially inward from the outer shroud 51, and an inner shroud (illustrated in the figure) provided radially inward of the airfoil portion. Not) and are integrally formed. Further, the turbine stationary blade 32 is supported from the turbine casing 31 via a heat shield ring and a blade ring, and is a fixed side. The plural stages of turbine vanes 32 are, in order from the upstream side in the flow direction FG of the combustion gas, a first turbine vane 32a, a second turbine vane 32b, a third turbine vane 32c, and a fourth turbine vane. 32d and. The first turbine vane 32a is integrally formed by an outer shroud 51a, an airfoil portion 53a, and an inner shroud (not shown). The second turbine vane 32b is integrally formed by an outer shroud 51b, an airfoil portion 53b, and an inner shroud (not shown). The third turbine vane 32c is integrally formed by an outer shroud 51c, an airfoil portion 53c, and an inner shroud (not shown). The fourth turbine vane 32d is integrally formed by an outer shroud 51d, an airfoil portion 53d, and an inner shroud (not shown).

The plurality of stages of turbine rotor blades 33 are arranged inside in the radial direction so as to face the plurality of divided rings 52. The turbine rotor blades 33 of each stage are provided with a predetermined gap from each of the split rings 52, and are provided on the movable side. The plurality of stages of turbine rotor blades 33 include a first turbine rotor blade 33a, a second turbine rotor blade 33b, a third turbine rotor blade 33c, and a fourth turbine rotor blade in order from the upstream side in the combustion gas flow direction FG. And 33d. The first turbine rotor blade 33a is provided radially inside the first split ring 52a. Similarly, the second turbine rotor blade 33b, the third turbine rotor blade 33c, and the fourth turbine rotor blade 33d are provided radially inside the second split ring 52b, the third split ring 52c, and the fourth split ring 52d. There is.

Therefore, the plurality of stages of turbine vanes 32 and the plurality of stages of turbine rotor blades 33 are arranged in order from the upstream side in the flow direction FG of the combustion gas in the order of the first turbine stator blades 32a, the first turbine rotor blades 33a, and the second turbine rotor blades 33a. The blades 32b, the second turbine moving blades 33b, the third turbine stationary blades 32c, the third turbine moving blades 33c, the fourth turbine stationary blades 32d, and the fourth turbine moving blades 33d are arranged to face each other in the axial direction. Is provided.

As shown in FIG. 2, the turbine casing 31 has a blade ring 45 arranged inside the radial direction thereof and supported by the turbine casing 31. The blade ring 45 is formed in an annular shape around the turbine shaft 8, is divided into a plurality in the circumferential direction and the axial direction, and is supported by the turbine casing 31. In addition, the plurality of blade rings 45 include a first blade ring 45a, a second blade ring 45b, a third blade ring 45c, and a fourth blade ring in order from the upstream side of the flow direction (axial direction) FG of the combustion gas. 45d and. A heat shield ring 46 is arranged radially inside the blade ring 45, and the turbine vane 32 is supported from the blade ring 45 via the heat shield ring 46. The plurality of heat shield rings 46 include a first heat shield ring 46a, a second heat shield ring 46b, a third heat shield ring 46c, and a fourth heat shield ring 46c in order from the upstream side of the flow direction (axial direction) FG of the combustion gas. The heat shield ring 46d is included.

Inside the blade ring 45, a plurality of turbine stationary blades 32 and a plurality of divided rings 52 are provided adjacent to each other in the axial direction.

The plurality of turbine vanes 32 and the plurality of split rings 52 are arranged in order from the upstream side in the flow direction FG of the combustion gas from the first turbine vane 32a, the first split ring 52a, the second turbine vane 32b, and the second turbine vane 32b. The divided ring 52b, the third turbine vane 32c, the third divided ring 52c, the fourth turbine vane 32d, and the fourth divided ring 52d are arranged so as to face each other in the axial direction.

The first turbine vane 32a and the first split ring 52a are attached to the inside of the first blade ring 45a in the radial direction via the first heat shield ring 46a. Similarly, the second turbine vane 32b and the second split ring 52b are attached to the inner side in the radial direction of the second blade ring 45b via the second heat shield ring 46b, and the third turbine vane 32c and the third split ring are provided. The ring 52c is attached to the inside of the third blade ring 45c in the radial direction via the third heat shield ring 46c, and the fourth turbine vane 32d and the fourth split ring 52d are connected to each other via the fourth heat shield ring 46d. It is attached to the inside of the four-blade ring 45d in the radial direction.

The annular shroud formed between the outer shroud 51 of the plurality of turbine vanes 32 and the inner circumferential side of the plurality of split rings 52 and the inner shroud of the turbine vane 32 and the outer circumferential side of the platform of the turbine rotor blades 33. The flow path becomes the combustion gas flow path R1, and the combustion gas flows along the combustion gas flow path R1.

In the gas turbine 1 as described above, when the turbine shaft 8 is rotated, air is taken in from the air intake 11 of the compressor 5. Then, the taken-in air is compressed by passing through the plurality of stages of compressor vanes 13 and the plurality of stages of compressor rotor blades 14 to become high temperature/high pressure compressed air. Fuel is supplied from the combustor 6 to the compressed air, and high-temperature, high-pressure combustion gas is generated. The combustion gas passes through the turbine vanes 32 of multiple stages and the turbine blades 33 of multiple stages of the turbine 7, whereby the turbine shaft 8 is rotationally driven. As a result, the generator connected to the turbine shaft 8 generates power by being given rotational power. After that, the combustion gas after the turbine shaft 8 is rotationally driven is discharged from the diffuser portion 54 in the exhaust chamber 34 to the outside of the system.

Next, with reference to FIGS. 2 and 3, a split ring and a split ring cooling structure for cooling the split ring will be described. FIG. 3 is a partially enlarged view of the split ring of the gas turbine according to the first embodiment. Here, in FIG. 2, only the split ring cooling structure around the second split ring 52b is shown, but other split rings have the same structure. Hereinafter, the second split ring 52b will be described as the split ring 52 as a representative.

The cooling air supplied to the split ring cooling structure 60 is supplied from the blade ring cavity 41 surrounded by the turbine casing and the blade ring 45, as described in the background art. A supply opening 47 is formed in the blade ring 45. A first cavity 80 serving as a space is provided between the heat shield ring 46, the blade ring 45, and the split ring 52. The first cavity 80 is provided in a ring shape in the circumferential direction. The first cavity 80 communicates with the blade ring cavity 42 via the supply opening 47. Further, the split ring 52 is formed with a cooling flow path communicating with the first cavity 80.

The cooling air CA supplied to the blade ring cavity 41 of the split ring cooling structure 60 is supplied to the first cavity 80 via the supply opening 47. As the cooling air CA of the present embodiment, vehicle interior air on the compressor outlet side or bleed air extracted from the compressor is used. The cooling air CA supplied to the first cavity 80 is supplied to the split ring 52 and passes through a cooling flow path (details will be described later) arranged in the split ring to cool the split ring 52.

Next, the cooling passages of the split ring cooling structure 60 will be described in more detail by describing the structure of the split ring 52 with reference to FIGS. 4 to 7 in addition to FIG. 3. FIG. 4 is a perspective view of a divided body of the divided ring according to the first embodiment. FIG. 5 is a sectional view of a divided body of the divided ring according to the first embodiment. FIG. 6 is a schematic cross-sectional view of the split ring according to the first embodiment as viewed from the radial direction. FIG. 7 is a cross-sectional view of the split ring according to the first embodiment as seen from the flow direction of the combustion gas. Here, in the present embodiment, the rotation direction of the turbine shaft 8 (the rotation direction of the turbine rotor blade) is R, and the rotation direction R is a direction orthogonal to the axial direction of the rotation shaft.

The split ring 52 has a plurality of annular split bodies 100 arranged in the circumferential direction of the turbine shaft 8. The divided body 100 is arranged so that a certain gap is secured between the inner peripheral surface 111a of the divided body 100 and the tip of the turbine rotor blade 33. The split ring 52 is formed of, for example, a heat resistant nickel alloy or the like.

The split body 100 has a main body 112 and a hook 113. In addition, a collision plate 114 is provided between the hooks 113 of the split body 100. The main body 112 is a plate-shaped member in which a cooling flow path described later is provided. The main body 112 is a curved surface whose inner surface in the radial direction is curved along the rotation direction R. Further, the main body 112 is formed with a cooling flow path. The shape of the main body 112 will be described later.

The hooks 113 are integrally provided on the upstream and downstream ends of the combustion gas flow direction FG and on the radially outer surface of the main body 112. The hook 113 is attached to the heat shield ring 46. As a result, the divided body 100 is supported by the heat shield ring 46.

The collision plate 114 is arranged in the first cavity 80. Specifically, the collision plate 114 is arranged radially outside the main body 112 and spaced apart from the radially outer surface 112 a of the main body 112. Further, the collision plate 114 is arranged between the hooks 113 of the divided body 100 and fixed to the inner wall 112b of the hook 113 of the divided body 100, and the collision plate 114 forms a space on the outer side in the radial direction of the main body 112. It is blocking. Thereby, the main body 112, the collision plate 114, the hooks 113 arranged on the upstream side and the downstream side of the combustion gas flow direction FG, and the direction substantially orthogonal to the axial direction of the turbine shaft 8 (the rotation direction of the turbine shaft 8). The space surrounded by the side end portions provided on the upstream side and the downstream side of () becomes the cooling space 129.

The collision plate 114 has a large number of small holes 115 through which cooling air CA for cooling impingement passes. As a result, the cooling air CA supplied into the first cavity 80 passes through the small holes 115 and is discharged to the cooling space 129 when moving toward the main body 112. As a result, the cooling air CA is ejected from the small holes 115 and impingement-cools the surface 112a of the main body 112.

Next, a flow path for flowing the cooling air CA formed in the main body 112 will be described with reference to FIGS. 3 to 7. Here, in the divided body 100, the rear side in the rotation direction R is the rear side of the arrow (the side that first contacts the rotating blade), and the front side in the rotation direction R is the front side of the arrow (the rotating blade). And the side that touches the end).

The split body 100 has an opening 120, a second cavity 122, a first cooling flow channel (front side cooling flow channel) 123, and a second cooling flow channel (rear side cooling flow channel) 124 formed in a main body 112. Has been done. The opening 120 is formed on the first cavity 80 side of the main body 112, that is, on the radially outer surface, and connects the second cavity 122 and the first cavity 80 (cooling space 129). The opening 120 is formed near the center of the main body 112 in the rotation direction R.

The second cavity 122 is a closed space formed inside the main body 112 in which the flow direction FG of the combustion gas is the longitudinal direction, and as shown by the arrow, the upstream side in the flow direction of the cooling air communicates with the opening 120. The downstream side communicates with the first cooling flow passage 123 and the second cooling flow passage 124. The second cavity 122 is a space that connects the opening 120 to the first cooling flow path 123 and the second cooling flow path 124, and the opening 120, the first cooling flow path 123 and the second cooling flow path 124, Plays the role of a manifold that connects to each other.

The first cooling flow path 123 is formed in the first region 131 of the main body 112. The first region 131 is a region on the front side in the rotation direction R of the main body 112. In the first region 131, a plurality of first cooling flow channels 123 are pipe lines that extend in the rotation direction R and are formed inside the main body 112 in parallel to each other, and one end of the first cooling flow channels 123 is in the second cavity 122. The other end is opened to the front end surface of the main body 112 in the rotation direction R. That is, the first cooling flow path 123 communicates the second cavity 122 with the combustion gas flow path R1.

The second cooling flow path 124 is formed in the second region 132 of the main body 112. The second region 132 is a region on the rear side in the rotation direction R of the main body 112. Here, the front end of the second region 132 in the rotation direction R is rearward of the rear end of the first region 131 in the rotation direction R. That is, the second area 132 is an area that does not overlap with the first area 131. In the second region 132, a plurality of second cooling flow passages 124 are pipe passages extending in the rotation direction R and formed inside the main body 112 in parallel to each other, and one end of the second cooling flow passages 124 is formed in the second cavity 122. The other end is opened to the rear end surface of the main body 112 in the rotation direction R. That is, the second cooling flow passage 124 connects the second cavity 122 and the combustion gas flow passage R1.

Here, the first cooling flow channel 123 and the second cooling flow channel 124 can be formed by various methods. For example, it can be formed by using the curved electric discharge machining method described in Japanese Unexamined Patent Publication No. 2013-136140, which can move in the formed hole while bending the machining position. By using this method, it is possible to manufacture the divided body 100 by performing necessary processing such as cutting and electric discharge machining on the plate-shaped member.

A path through which the cooling air CA flows as described above is formed in the divided body 100. The cooling air CA, which is supplied to the cooling space 129 by the split ring cooling structure 60 and impingement-cools the surface 112a of the divided body, passes through the opening 120 and is supplied to the second cavity 122. The cooling air CA supplied to the second cavity 122 moves to the first cooling flow passage 123 and the second cooling flow passage 124 while moving in the second cavity 122 in the upstream direction or the downstream direction of the flow direction FG of the combustion gas. Inflow. The cooling air CA that has flowed into the first cooling flow path 123 flows from the rear side to the front side in the rotation direction R and is discharged to the combustion gas flow path R1 from the end portion on the front side in the rotation direction R of the split body 100. .. The cooling air CA that has flowed into the second cooling flow path 124 flows from the front side to the rear side in the rotation direction R and is discharged to the combustion gas flow path R1 from the rear end of the split body 100 in the rotation direction R. ..

The split ring cooling structure 60 of the present embodiment is configured as described above, and supplies the cooling air CA to the first cavity 80, and the cooling air CA is formed in the main body 112 of the split body 100. By passing the divided body 100, the divided body 100 can be suitably cooled.

Specifically, the divided body 100 is provided with a plurality of first cooling flow channels 123 extending in the rotation direction R in the first region 131, and the second cooling flow channels 124 extending in the rotation direction R in the second region 132. By providing a plurality of cooling air CA to the first cooling flow path 123 and the second cooling flow path 124, the cooling air CA can be circulated inside the divided body 100, and the divided body 100 is cooled appropriately. be able to. Furthermore, the first cooling flow path 123 and the second cooling flow path 124 are formed as paths extending in the rotation direction R, and the cooling air CA is discharged from the end portion in the rotation direction R, whereby the end in the rotation direction R of the divided body 100. The part can be convectively cooled by cooling air CA. Thereby, the divided body 100 and the end portion of the divided body 100 in the rotation direction R can be efficiently cooled. Furthermore, the split ring cooling structure 60 allows the same cooling air CA to cool the entire divided body 100 and then the end portion by passing the first cooling flow passage 123 and the second cooling flow passage 124. Therefore, the divided body 100 can be cooled efficiently by reusing the cooling air. Further, after the cooling air CA is supplied to the first cavity 80, the cooling air CA is supplied to the first cooling flow path 123 and the second cooling flow path 124, so that the same cooling air CA cools each component of the first cavity 80. Then, each part of the main body 112 is cooled. Thereby, the cooling air CA can be efficiently used. Since the cooling air CA can be efficiently used in this way, the amount of air used for cooling can be reduced.

Further, by providing the opening 120 and the second cavity 122 in the divided body 100, the amount of cooling air flowing into the second cavity 122 can be adjusted by changing the opening area of the opening 120. Therefore, the cooling air CA can be supplied to each cooling flow path in good balance. Further, in the above-described embodiment, since the radially outer surface of the divided body 100 can be efficiently cooled, the collision plate 114 is provided, but the collision plate 114 may not be provided.

FIG. 8 is a schematic configuration diagram of the split body of the first embodiment as viewed from the radial direction, and shows a modification in which the opening area of the opening 120 provided in the split body 100 is changed. In this modified example, the second cavity 120a is formed in a groove shape on the outer circumferential surface of the main body 112 in the radial direction, and a shield plate is not provided on the side facing the first cavity 80, and is opened outward in the radial direction. It is a structured structure. That is, as compared with the structure of the opening 120 shown in FIG. 6, the length of the opening 120 in the combustion gas flow direction FG is substantially the same as that of the first cavity 80 without changing the width of the opening in the rotation direction R. This is an expanded example. With such a structure, it is not necessary to form the second cavity as a closed space, and processing is easier than in the first embodiment.

Next, a gas turbine and a split ring cooling structure according to the second embodiment will be described with reference to FIGS. 9 and 10. FIG. 9 is a schematic cross-sectional view of the split body according to the third embodiment as viewed from the radial direction. FIG. 10 is a schematic cross-sectional view of the divided body according to the second embodiment as seen from the flow direction of the combustion gas, and is a cross-sectional view taken along the line AA of FIG. 9. The gas turbine and the split ring cooling structure according to the third embodiment are the same as those of the first embodiment except the structure of the divided body. Hereinafter, different points of the structure of the divided body will be mainly described, parts having the same structure will be denoted by the same reference numerals, and description thereof will be omitted.

A main body 112 of the divided body 100b has a first cooling flow passage 123a and a second cooling flow passage 124a. One end of the first cooling flow path 123a is connected to the radially outer surface 112a of the main body 112, that is, the opening 140 formed on the surface facing the first cavity 80, and the other end thereof is in the rotation direction. It is open to the front end face of R. As shown in FIG. 10, the first cooling flow path 123a is a curved pipe whose path on the rear side in the rotation direction R is directed toward the rear side toward the radially outer surface of the main body 112. One end of the second cooling flow path 124a is connected to the radially outer surface 112a of the main body 112, that is, the opening 141 formed on the surface facing the first cavity 80, and the other end thereof is in the rotation direction. It is open to the rear end face of R. As shown in FIG. 10, the second cooling flow path 124a is a curved pipe whose front side path in the rotation direction R is directed toward the front side toward the radially outer surface of the main body 112. Further, the first cooling flow passage 123a is formed in the first region 131, and the second cooling flow passage 124a is formed in the second region 132. Further, the first cooling flow channel 123a and the second cooling flow channel 124a, which are partially bent, can be formed by the curved electric discharge machining described above.

As described above, the divided body 100b does not have the second cavity, and even if the first cooling flow channel 123a and the second cooling flow channel 124a are in direct communication with the first cavity 80, the first cooling flow channel 123a, By the two cooling flow paths 124a, it is possible to preferably cool the radially inner surface of the divided body 100b, and also to appropriately cool both end portions in the rotation direction.

Next, a gas turbine and a split ring cooling structure according to the third embodiment will be described with reference to FIG. FIG. 11 is a schematic cross-sectional view of the split body according to the fourth embodiment as viewed from the radial direction. The gas turbine and the split ring cooling structure according to the third embodiment are the same as those of the first embodiment except the structure of the divided body. Hereinafter, different points of the structure of the divided body will be mainly described, parts having the same structure will be denoted by the same reference numerals, and description thereof will be omitted.

The split body 100c has an opening 120, a second cavity 122, a first cooling flow passage 123b, and a second cooling flow passage 124b formed in the main body 112.

The first cooling flow path 123b is formed in the first region 131 of the main body 112. In the first region 131, a plurality of first cooling flow passages 123b are pipe lines formed in the main body 112 in parallel with each other, extending in the rotation direction R, and one end of the first cooling flow passage 123b is formed in the second cavity 122. The other end is opened to the front end surface of the main body 112 in the rotation direction R. The interval between the first cooling flow passage 123b and the adjacent first cooling flow passage 123b is narrower on the downstream side than on the upstream side in the combustion gas flow direction FG. That is, in the divided body 100c, the first cooling flow passages 123b are arranged more densely on the downstream side than on the upstream side in the combustion gas flow direction FG.

The second cooling flow path 124b is formed in the second region 132 of the main body 112. In the second region 132, a plurality of second cooling flow passages 124b are pipe passages extending in the rotation direction R and formed inside the main body 112 in parallel to each other, and one end of the second cooling flow passages 124b is formed in the second cavity 122. The other end is opened to the rear end surface of the main body 112 in the rotation direction R. The second cooling flow passage 124b has a smaller gap between the adjacent second cooling flow passages 124b on the downstream side than on the upstream side in the combustion gas flow direction FG. That is, in the divided body 100c, the second cooling flow passages 124b are densely arranged on the downstream side of the upstream side in the combustion gas flow direction FG.

In the divided body 100c, by arranging the first cooling flow passages 123b and the second cooling flow passages 124b so that the number of cooling flow passages on the downstream side is smaller than that on the upstream side in the combustion gas flow direction FG, It is possible to more reliably cool the downstream side of the divided body 100c in the combustion gas flow direction FG. As a result, more cooling air CA can be circulated in the downstream side portion of the combustion gas flow direction FG that needs more cooling, and the divided body 100c can be cooled more efficiently.

Next, a gas turbine and a split ring cooling structure according to the fourth embodiment will be described with reference to FIG. FIG. 12 is a schematic cross-sectional view of the split body according to the fourth embodiment as viewed in the radial direction. The gas turbine and the split ring cooling structure according to the fourth embodiment are the same as those of the first embodiment except the structure of the split body. Hereinafter, different points of the structure of the divided body will be mainly described, parts having the same structure will be denoted by the same reference numerals, and description thereof will be omitted.

The divided body 100d has an opening 120, a second cavity 122, a first cooling flow passage 123c, and a second cooling flow passage 124c formed in the main body 112.

The first cooling flow path 123c is formed in the first region 131 of the main body 112. In the first region 131, a plurality of first cooling flow channels 123c are formed side by side in the combustion gas flow direction FG. One end of the first cooling flow path 123c is opened to the second cavity 122, and the other end is opened to the front end face of the main body 112 in the rotation direction R. The first cooling flow path 123c extends in the rotation direction R and has a parallel portion 150 formed inside the main body 112 in parallel with each other and an inclined portion 152 inclined with respect to the rotation direction R. The parallel part 150 is connected to the second cavity 122. The inclined portion 152 is connected to the parallel portion 150 and opens at an end portion (front end portion) in the rotation direction R. That is, the inclined portion 152 is formed on the front side in the rotation direction R of the main body 112. Further, the inclined portion 152 inclines toward the downstream side in the combustion gas flow direction FG as it goes toward the front side in the rotation direction R. In addition, the interval between the first cooling flow passage 123c and the adjacent first cooling flow passage 123c is narrower on the downstream side than on the upstream side in the combustion gas flow direction FG. That is, in the divided body 100d, the first cooling flow channels 123c are arranged more densely on the downstream side than on the upstream side in the flow direction FG of the combustion gas.

The second cooling flow path 124c is formed in the second region 132 of the main body 112. In the second region 132, a plurality of second cooling channels 124c are formed side by side in the combustion gas flow direction FG. One end of the second cooling flow path 124c is open to the second cavity 122, and the other end is open to the rear end surface of the main body 112 in the rotation direction R. The second cooling flow channel 123c extends in the rotation direction R and has a parallel portion 154 formed inside the main body 112 in parallel with each other and an inclined portion 156 inclined with respect to the rotation direction R. The parallel portion 154 is connected to the second cavity 122. The inclined portion 156 is connected to the parallel portion 154 and is open at an end portion (rear end portion) in the rotation direction R. That is, the inclined portion 156 is formed on the rear side in the rotation direction R of the main body 112. In addition, the inclined portion 156 is inclined toward the rear side in the rotation direction R toward the downstream side in the combustion gas flow direction FG. The second cooling flow passage 124c has a smaller gap between the adjacent second cooling flow passages 124c on the downstream side than on the upstream side in the flow direction FG of the combustion gas. In other words, in the divided body 100d, the second cooling flow passages 124c are densely arranged on the downstream side of the combustion gas in the flow direction FG.

The divided body 100d is provided with the inclined portions 152 and 156 on the side of the portions that are connected to the end faces of the first cooling flow passage 123c and the second cooling flow passage 124c in the rotation direction R, whereby both ends of the division body 100d in the rotation direction R are provided. It is possible to increase the length of the cooling flow passage in the section and increase the flow passage surface area. As a result, both ends of the divided body 100d in the rotation direction R can be appropriately cooled.

Next, a gas turbine and a split ring cooling structure according to the fifth embodiment will be described with reference to FIG. FIG. 13 is a schematic cross-sectional view of the split body according to the fifth embodiment as viewed from the radial direction. The gas turbine and the split ring cooling structure according to the fifth embodiment are the same as those of the first embodiment except the structure of the split body. Hereinafter, different points of the structure of the divided body will be mainly described, parts having the same structure will be denoted by the same reference numerals, and description thereof will be omitted.

The split body 100e has an opening 120, a second cavity 122, a first cooling passage 162, and a second cooling passage 164 formed in the main body 112.

The first cooling flow path 162 is formed in the first region 131 of the main body 112. In the first region 131, a plurality of first cooling flow paths 162 are formed side by side in the combustion gas flow direction FG. The first cooling flow passage 162 is a pipe passage that extends in the rotation direction R and is formed inside the main body 112 in parallel with each other. One end of the first cooling flow passage 162 is open to the second cavity 122, and the other end thereof is the main body 112. Has an opening on the front end face in the rotation direction R.

The second cooling channel 164 is formed in the second region 132 of the main body 112. In the second region 132, a plurality of second cooling flow paths 164 are formed side by side in the combustion gas flow direction FG. The second cooling flow passage 164 is a pipe passage that extends in the rotation direction R and is formed inside the main body 112 in parallel with each other. One end of the second cooling flow passage 164 opens into the second cavity 122 and the other end of the main body 112. Has an opening on the rear end face in the rotation direction R.

The divided body 100e is formed such that the number of the second cooling channels 164 is larger than the number of the first cooling channels 162. That is, in the divided body 100e, the arrangement density of the cooling passages is higher in the second cooling passages 164 than in the first cooling passages 162. As a result, in the divided body 100e, more cooling air CA is supplied to the second region 132 in which the first cooling flow path 164 is provided. This makes it possible to further cool the second region 132 in which the first cooling flow path 164 is provided. Therefore, the divided body 100e can accurately cool the rear end portion in the rotation direction R that is under more severe conditions than the front end portion in the rotation direction R. As a result, the cooling air CA can be accurately supplied to each part and can be efficiently cooled. This makes it possible to reliably cool the split ring 52 while reducing the amount of cooling air CA to be supplied.

Next, a gas turbine and a split ring cooling structure according to the sixth embodiment will be described with reference to FIG. FIG. 14 is a schematic cross-sectional view of the split body according to the sixth embodiment as viewed from the radial direction. The gas turbine and split ring cooling structure according to the sixth embodiment are the same as those of the first embodiment except for the structure of the divided body. Hereinafter, different points of the structure of the divided body will be mainly described, parts having the same structure will be denoted by the same reference numerals, and description thereof will be omitted.

The divided body 100f has an opening 170, a second cavity 172, a first cooling flow path 173, and a second cooling flow path 174 formed in the main body 112. The opening 170 of the divided body 100f and the second cavity 172 are formed on the rear side in the rotational direction with respect to the center line Cla that is parallel to the axis CL of the turbine shaft 8 and passes through the center of the main body 112 in the rotational direction R. As a result, since the formation positions of the opening 170 and the second cavity 172 are formed on the rear side of the center line CLa, the first cooling flow passage 173 is longer than the second cooling flow passage 174. There is. The connection relationship among the opening 170, the second cavity 172, the first cooling flow path 173, and the second cooling flow path 174 is that the opening 120 of the divided body 100, the second cavity 122, and the first cooling flow. It is similar to the path 123 and the second cooling flow path 124.

In the divided body 100f, the openings 170 and the second cavities 172 are formed on the rear side of the center line CLa, and the first cooling flow passage 173 is longer than the second cooling flow passage 174. The temperature of the cooling air CA reaching the rear end of the second cooling flow path 174 in the rotation direction R is lower than the temperature of the cooling air CA reaching the front end of the first cooling flow path 173 in the rotation direction. You can Therefore, the divided body 100f can accurately cool the rear end of the rotation direction R that is under more severe conditions than the front end of the rotation direction R. As a result, the cooling air CA can be accurately supplied to each part and can be efficiently cooled. This makes it possible to reliably cool the split ring while reducing the amount of cooling air CA to be supplied.

Next, a gas turbine and a split ring cooling structure according to the seventh embodiment will be described with reference to FIG. FIG. 15 is a schematic cross-sectional view of the split body according to the seventh embodiment as viewed from the radial direction. The gas turbine and the split ring cooling structure according to the seventh embodiment are the same as those of the first embodiment except for the structure of the split body. Hereinafter, different points of the structure of the divided body will be mainly described, parts having the same structure will be denoted by the same reference numerals, and description thereof will be omitted.

The divided body 100g has openings 180a and 180b, second cavities 182a and 182b, a first cooling flow path 183, and a second cooling flow path 184 formed in the main body 112. The first cooling flow passage 183 and the second cooling flow passage 184 are similar to the first cooling flow passage 123 and the second cooling flow passage 124.

The opening 180a is formed on the side of the main body 112 facing the first cavity 80, that is, on the radially outer surface, and communicates the second cavity 182a with the first cavity 80 (cooling space 129). The opening 180a is formed near the center of the main body 112 in the rotation direction R. The opening 180b is formed on the side of the main body 112 that faces the first cavity 80, that is, on the radially outer surface, and connects the second cavity 182b and the first cavity 80 (cooling space 129). The opening 180b is formed near the center of the main body 112 in the rotation direction R. Further, the opening 180b is arranged downstream of the opening 180a in the flow direction FG of the combustion gas.

The second cavities 182a and 182b are closed spaces that are formed inside the main body 112 and that are long in the flow direction of the combustion gas. The second cavities 182a and 182b are partitioned by the partition wall 186 into a second cavity 182a on the upstream side and a second cavity 182b on the downstream side in the flow direction of the combustion gas, and the second cavities 182a and 182b are not in communication with each other. .. One of the second cavities 182a and 182b communicates with the opening 180a or 180b, and the other communicates with the first cooling channel (front side cooling channel) 183 and the second cooling channel (rear side cooling channel) 184. ing.

In this way, the divided body 100g is provided with the second cavities 182a and 182b connected in series in the combustion gas flow direction FG. Accordingly, among the plurality of first cooling flow passages 183, the first cooling flow passage 183 formed on the upstream side of the combustion gas flow direction FG communicates with the second cavity 182a, and the combustion gas flow direction FG. The first cooling flow path 183 formed on the downstream side of the first communication path 183 communicates with the second cavity 182b. Among the plurality of second cooling flow paths 184, the second cooling flow path 184 formed on the upstream side in the combustion gas flow direction FG communicates with the second cavity 182a and is downstream in the combustion gas flow direction FG. The second cooling flow path 184 formed in the above communicates with the second cavity 182b.

As described above, the second cavity is not limited to one, and a plurality of second cavities may be provided. Further, the second cavity only needs to communicate with both the first cooling flow path 183 and the second cooling flow path 184, and the position in the flow direction FG of the combustion gas and the position in the rotation direction R are not particularly limited. Moreover, although the case where the second cavities 182a and 182b are connected in series in the flow direction of the combustion gas has been described, the two second cavities 182a and 182b may be separated from each other. That is, in each of the cavities 182a and 182b, the upstream side in the flow direction of the cooling air communicates with the openings 180a and 180b, and the downstream sides include the first cooling flow path (front side cooling flow path) 183 and the second cooling flow path. The positions of the second cavities 182a and 182b in the flow direction of the combustion gas and the positions in the rotation direction R may be different from each other as long as they communicate with the passage (rear side cooling passage) 184.

By dividing the second cavity into a plurality of pieces, the divided body 100g can change the opening area of each cavity and adjust the amount of cooling air flowing into each cavity. Therefore, the amount of the cooling air CA supplied to the cooling flow path at each position can be adjusted more finely.

DESCRIPTION OF SYMBOLS 1 Gas turbine 5 Compressor 6 Combustor 7 Turbine 8 Turbine shaft 11 Air intake 12 Compressor casing 13 Compressor stationary blade 14 Compressor moving blade 21 Inner cylinder 22 Tail cylinder 23 Outer cylinder 24 Cabin 31 Turbine casing 32 Turbine stationary blade 33 turbine blade 41 blade ring cavity 45 blade ring 46 heat shield ring 51 outer shroud 52 split ring 53 airfoil 60 split ring cooling structure 80 first cavity 100 split body 112 main body 113 hook 114 collision plate 115 small hole 120 opening 122 Second cavity 123 First cooling channel (front side cooling channel)
124 Second cooling flow path (rear side cooling flow path)
131 First Region 132 Second Region R1 Combustion Gas Flow Path CA Cooling Air

Claims (3)

A split ring cooling structure for cooling a split ring of a gas turbine having a plurality of annular split members arranged in the circumferential direction,
A cavity surrounded by the main body of the divided body, the heat shield ring, and the blade ring,
A collision plate supported by the divided body and provided with a large number of holes,
Arranged along the inner peripheral surface of the divided body in the circumferential direction within the main body of the divided body, the front side or the rear side in the rotation direction of the divided body, extending in one direction without folding back, The cavity covered by the collision plate is disposed inside the outer surface of the divided body which faces the cavity, one end opens to the cavity, and the other end is the front side or the rear side in the rotation direction of the divided body. A cooling flow path through which the cooling air opening at the side end of the side flows,
The cooling flow passage is a first cooling flow passage from which the cooling air is discharged from a rear side in the rotation direction toward a front side,
A second cooling flow path through which the cooling air is discharged from the front side toward the rear side in the rotation direction;
A split ring cooling structure that includes either one of the above. The cooling channels are arranged such that the cooling channels arranged on the downstream side in the combustion gas flow direction are arranged at an arrangement pitch smaller than that of the cooling channels arranged on the upstream side in the combustion gas flow direction. The split ring cooling structure described in. A turbine rotor blade attached to a rotatable turbine shaft,
A turbine stationary blade fixed so as to face the turbine moving blade in the axial direction,
The split ring surrounding the turbine rotor blade in the circumferential direction,
A cabin the disposed on the outer periphery of the split ring, and you support the turbine vane,
The split ring cooling structure according to claim 1 or 2,
Gas turbine having.

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