CN114412582A - Gas turbine shroud ring adjusting device and gas turbine - Google Patents
Gas turbine shroud ring adjusting device and gas turbine Download PDFInfo
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- CN114412582A CN114412582A CN202210112622.8A CN202210112622A CN114412582A CN 114412582 A CN114412582 A CN 114412582A CN 202210112622 A CN202210112622 A CN 202210112622A CN 114412582 A CN114412582 A CN 114412582A
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- gas turbine
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- support member
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- 238000005259 measurement Methods 0.000 claims description 19
- 230000004308 accommodation Effects 0.000 claims description 2
- 230000008602 contraction Effects 0.000 description 10
- 238000005299 abrasion Methods 0.000 description 4
- 239000010720 hydraulic oil Substances 0.000 description 3
- 239000000463 material Substances 0.000 description 2
- 238000012544 monitoring process Methods 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Turbines (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a gas turbine supporting ring adjusting device and a gas turbine, wherein the gas turbine supporting ring adjusting device comprises a first supporting piece, a second supporting piece and a driving piece, one end of the first supporting piece is suitable for being connected with the gas turbine, the second supporting piece is suitable for supporting the turbine supporting ring, the second supporting piece is sleeved on the first supporting piece, a preset gap is formed between the inner wall surface of the second supporting piece and the outer wall surface of the first supporting piece, the driving piece is connected with the second supporting piece, the driving piece is used for adjusting the size of the preset gap, the position of the turbine supporting ring can be adjusted under the condition that the gas turbine does not shut down, and the operation efficiency of the gas turbine is improved.
Description
Technical Field
The invention relates to the technical field of gas turbines, in particular to a turbine retaining ring adjusting device of a gas turbine and a gas turbine.
Background
In the stator structure of a gas turbine, the position of the turbine retaining ring needs to be adjusted to achieve the purpose that the turbine retaining ring is concentric with the rotor. In the related art, the position of the turbine retaining ring is adjusted by using the combined adjusting shim, however, the adjusting mode in the related art needs to frequently replace the shim to adjust the position of the turbine retaining ring, and the adjusting efficiency is low.
Disclosure of Invention
The present invention is based on the discovery and recognition by the inventors of the following facts and problems:
the related art discloses an adjusting device for a stationary blade carrier ring of a gas turbine, which comprises a shaft body and a sliding block, wherein the shaft body comprises a first shaft section and a second shaft section, the cross section of the first shaft section is a Lelo triangle, the first shaft section is provided with a first end and a second end, the second end of the first shaft section is connected with the first end of the second shaft section, and the sliding block is connected with the second end of the second shaft section. However, the inventors of the present application have found that the adjusting device in the related art requires the turbine to be stopped to adjust the position of the turbine shroud, and the adjusting efficiency is low.
The present invention is directed to solving, at least to some extent, one of the technical problems in the related art. Therefore, the embodiment of the invention provides a turbine supporting ring adjusting device, which can adjust the position of a turbine supporting ring under the condition that a gas turbine does not stop, and improve the operation efficiency of the gas turbine.
The embodiment of the invention also provides a gas turbine.
The turbine supporting ring adjusting device comprises a first supporting piece, wherein one end of the first supporting piece is suitable for being connected with a gas turbine; the second support piece is suitable for supporting the turbine support ring, the second support piece is sleeved on the first support piece and can extend and contract in the width direction of the first support piece, and a preset gap is formed between the inner wall surface of the second support piece and the outer wall surface of the first support piece; the driving piece is connected with the second supporting piece and used for adjusting the size of the preset gap.
The gas turbine supporting ring adjusting device provided by the embodiment of the invention can adjust the position of the turbine supporting ring under the condition that the gas turbine does not stop, so that the operation efficiency of the gas turbine is improved.
In some embodiments, the first support member includes a first section, a second section and a third section which are connected in sequence, the first section is suitable for being connected with the gas turbine, the second support member is sleeved on the third section, the second support member can extend and contract on the third section along the width direction of the first support member, the cross section of the first support member is smaller than that of the second section so as to form a first step surface, and the cross section of the second section is smaller than that of the first section so as to form a second step surface.
In some embodiments, the first support member is provided with a channel, the channel extends along the length direction of the first support member, and one end of the driving member is connected with the second support member through the channel.
In some embodiments, the gas turbine shroud adjustment apparatus further comprises a measurement member having one end extending through the gas turbine, the measurement member adapted to measure a clearance between the turbine shroud and a rotor of the gas turbine.
In some embodiments, the gas turbine shroud adjustment assembly further includes a controller coupled to the measurement member and the drive member, respectively, the controller controlling the extension and retraction of the second support member based on a clearance between the turbine shroud and the rotor of the gas turbine as measured by the measurement member.
The gas turbine comprises a cylinder body, wherein an accommodating cavity and a rotor are arranged in the cylinder body, and the rotor is arranged in the accommodating cavity; the turbine supporting ring is arranged in the accommodating cavity and sleeved on the rotor, and a preset gap is formed between the inner wall surface of the turbine supporting ring and the outer wall surface of the rotor; the adjusting device is the adjusting device for the turbine support ring, the first supporting piece is connected with the cylinder body, one end of the first supporting piece extends into the accommodating cavity, and the second supporting piece is connected with the turbine support ring.
According to the gas turbine provided by the embodiment of the invention, under the condition that the gas turbine operates, the position of the turbine retaining ring can be adjusted, and the operating efficiency of the gas turbine is improved.
In some embodiments, the turbine support ring of the gas turbine has a connecting portion, and the second support member is connected to the connecting portion.
In some embodiments, the connecting portion has a cavity therein, the second supporting member is disposed in the cavity, and at least a portion of the first supporting member extends into the cavity to connect with the second supporting member.
In some embodiments, the number of the adjusting devices is plural, the adjusting devices are arranged at intervals in the circumferential direction of the cylinder body, the number of the connecting portions is plural, and the connecting portions and the adjusting devices are in one-to-one correspondence.
In some embodiments, the cylinder block of the gas turbine is provided with a groove, and the first section is provided in the groove.
Drawings
FIG. 1 is a sectional view of a gas turbine according to an embodiment of the present invention.
FIG. 2 is a cross-sectional view of a gas turbine shroud adjustment assembly in accordance with an embodiment of the present invention and does not include a controller and a measurement component.
Reference numerals:
the first support 1, the first section 11, the second section 12, the third section 13, the channel 14,
the second support member 2, the first support portion 21, the second support portion 22,
a driving member 3, a connecting pipe 31, a measuring part 4, a controller 5,
the cylinder 6, the accommodating chamber 61, the recess 62,
the turbine holder ring 7, the connecting portion 71, the cavity 711,
and a rotor 8.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
The gas turbine supporting ring adjusting device comprises a first supporting piece 1, a second supporting piece 2 and a driving piece 3.
One end of the first support 1 is adapted to be connected to a gas turbine.
The second supporting member 2 is adapted to support the turbine support ring 7, the second supporting member 2 is sleeved on the first supporting member 1, and a predetermined gap (not shown) is formed between the inner wall surface of the second supporting member 2 and the outer wall surface of the first supporting member 1.
The driving member 3 is connected to the second supporting member 2, and the driving member 3 is used for adjusting the size of the predetermined gap.
For example, the second support 2 includes a first support 21 and a second support 22, the first support 21 and the second support 22 are arranged opposite to each other in the up-down direction, the first support 21 and the second support 22 have the same structure and size, a first preset gap (not shown) is formed between the lower end surface of the first support 21 and the upper end surface of the first support 1, a second preset gap (not shown) is formed between the upper end surface of the second support 22 and the lower end surface of the first support 1, and both the first preset gap and the second preset gap are adjustable.
Specifically, as shown in fig. 1 and 2, the right end of the first support 1 is connected to the outer wall surface of the gas turbine, for example, the right end of the first support 1 is detachably connected to the outer wall surface of the gas turbine.
The upper end of the first support portion 21 is connected to the turbine holder ring 7, and the lower end of the second support portion 22 is connected to the turbine holder ring 7. The driving part 3 is connected with the first supporting part 21 and the second supporting part 22, the driving part 3 can be arranged outside the gas turbine, and the driving part 3 adjusts the size of the first preset gap and the second preset gap by driving the first supporting part 21 and the second supporting part 22 to extend or contract, so as to drive the position of the turbine support ring 7 to change. For example, the first supporting portion 21 and the second supporting portion 22 may be hydraulic supporting rods, and accordingly, the driving member 3 may be a hydraulic controller or a hydraulic workstation, and the driving member 3 may adjust the extension or the contraction of the first supporting portion 21 and the second supporting portion 22 by adjusting the pressure of the hydraulic oil in the first supporting portion 21 and the second supporting portion 22, so as to adjust the size of the first preset gap and the second preset gap, and thus adjust the position of the turbine support ring 7, although the first supporting portion 21 and the second supporting portion 22 may also be other supporting rods of the prior art.
According to the gas turbine supporting ring adjusting device, the driving part 3 can adjust the extension or contraction of the first supporting part 21 and the second supporting part 22 by adjusting the pressure of hydraulic oil in the first supporting part 21 and the second supporting part 22, so that the size of the first preset gap and the size of the second preset gap are adjusted, the position of the turbine supporting ring 7 is adjusted, collision and abrasion between the turbine supporting ring 7 and the rotor 8 can be avoided, the position of the turbine supporting ring 7 can be adjusted on the premise that the gas turbine is not shut down, and therefore the operation efficiency of the gas turbine is improved.
In some embodiments, the first support member 1 includes a first section 11, a second section 12 and a third section 13 connected in sequence, the first section 11 is suitable for being connected with a gas turbine, the second support member 2 is sleeved on the third section 13, the second support member 2 is movable on the third section 13 along the width direction of the first support member 1, the cross section of the first support member 1 is that the cross section area of the third section 13 is smaller than that of the second section 12 to form a first step surface, and the cross section area of the second section 12 is smaller than that of the first section 11 to form a second step surface.
As shown in fig. 1 and 2, the first section 11 is detachably connected to the outer wall surface of the gas turbine, the left end of the first section 11 is connected to the right end of the second section 12, and the left end of the second section 12 is connected to the right end of the third section 13.
The second support member 2 is extendable or retractable in the width direction (up-down direction in fig. 2) of the first support member 1 at the third section 13.
As shown in fig. 1 and 2, the dimension of the third section 13 in the up-down direction is smaller than the dimension of the second section 12 in the up-down direction to form a first step surface, and the dimension of the first section 11 in the up-down direction is larger than the dimension of the second section 12 in the up-down direction to form a second step surface.
According to the turbine retaining ring adjusting device of the gas turbine, the first step surface is arranged, so that the first supporting piece 1 can be connected with the outer wall of the gas turbine more stably, and the adjusting device can adjust the position of the turbine retaining ring 7 more stably.
In some embodiments, the first support member 1 is provided with a channel 14, the channel 14 extends along the length direction of the first support member 1, and one end of the driving member 3 is connected to the second support member 2 through the channel 14.
Specifically, as shown in fig. 1 and 2, a channel 14 is provided in the first support member 1, the channel 14 extends in the left-right direction, the number of the channels 14 is two, the two channels 14 are independent of each other, the two channels 14 are respectively in one-to-one correspondence with the first support portion 21 and the second support portion 22, the left end of the channel 14 is communicated with the second support member 2, the right end of the channel 14 is communicated with the driving member 3, hydraulic oil or other pressure media is suitable for flowing through the channel 14, and the pressure media in the channel 14 can respectively enter the first support portion 21 and the second support portion 22 through the channel 14, so as to adjust the extension or contraction of the first support portion 21 and the second support portion 22, and further adjust the position of the turbine support ring 7.
It should be noted that the driving member 3 may further be provided with a connecting pipe 31, a left end of the driving member 3 is communicated with a right end of the connecting pipe 31, a left end of the connecting pipe 31 is communicated with a right end of the channel 14, the number of the connecting pipes 31 is two, and the two connecting pipes 31 are in one-to-one correspondence with the two channels 14.
According to the turbine supporting ring adjusting device, the driving part 3 supplies pressure medium to the second supporting part 2 through the channel 14, so that the expansion or contraction of the first supporting part 21 and the second supporting part 22 is adjusted, the position of the turbine supporting ring 7 is adjusted, collision between the turbine supporting ring 7 and the rotor 8 and abrasion between the turbine supporting ring 7 and the rotor 8 can be avoided, and the operation efficiency of the gas turbine is improved.
In some embodiments, the gas turbine shroud adjustment apparatus further includes a measurement component 4, one end of the measurement component 4 passing through the gas turbine, the measurement component 4 adapted to measure a clearance between the turbine shroud 7 and a rotor 8 of the gas turbine.
For example, the measuring component 4 may be a gap measuring instrument or other instrument that can measure the gap of an object.
As shown in fig. 1 and 2, the lower end of the measurement member 4 passes through the gas turbine, and the measurement member 4 is used to monitor the size of the gap between the turbine shroud 7 and the rotor 8 of the gas turbine. For example, the measuring unit 4 may measure the gap between the rotor 8 and the turbine retaining ring 7 in real time, and the driving unit 3 adjusts the pressure of the first supporting portion 21 and the second supporting portion 22 according to the gap between the rotor 8 and the turbine retaining ring 7 monitored by the measuring unit 4, so as to adjust the position of the turbine retaining ring 7, and thus adjust the gap between the turbine retaining ring 7 and the rotor 8. It will be appreciated that the measurement component 4 may also monitor in real time whether the clearance between the turbine retaining ring 7 and the rotor 8 is within a suitable range.
The gas turbine supporting ring adjusting device provided by the embodiment of the invention is provided with the measuring component 4, the size of the gap between the turbine supporting ring 7 and the rotor 8 can be monitored, the driving component 3 adjusts the pressure of the first supporting part 21 and the second supporting part 22 according to the monitoring data, so that the position of the turbine supporting ring 7 is adjusted, the automation degree of the gas turbine is improved, the size of the gap between the turbine supporting ring 7 and the rotor 8 can be monitored in real time on the premise of operation of the gas turbine, and the operation efficiency of the gas turbine is improved.
In some embodiments, the gas turbine shroud adjustment assembly further comprises a controller 5, the controller 5 being connected to the measurement member 4 and the drive member 3, respectively, the controller 5 controlling the extension and retraction of the second support member 2 based on the clearance between the turbine shroud 7 and the turbine rotor 8 as measured by the measurement member 4.
As shown in fig. 1 and 2, one end of the controller 5 is connected to the measuring part 4, and the other end of the controller 5 is connected to the driving part 3. For example, one end of the controller 5 is connected to the measuring unit 4 by a wire or wirelessly, and the other end of the controller 5 is connected to the driving unit 3 by a wire or wirelessly. When the gap between the turbine support ring 7 and the rotor 8 of the gas turbine measured by the measuring part 4 needs to be adjusted, the controller 5 controls the driving part 3 to adjust the expansion or contraction of the first support part 21 and the second support part 22. For example, when it is desired to move the turbine holder ring 7 upward, the first support portion 21 is contracted and the second support portion 22 is expanded.
For example, the controller 5 may further calculate a relative eccentric position between the turbine support ring 7 and the rotor 8 according to the data of the gap between the turbine support ring 7 and the rotor 8 measured by the measuring unit 4, obtain an adjustment amount of the turbine support ring 7, further obtain an expansion or contraction amount of the second support member 2, and then control the pressure of the pressure medium in the first support portion 21 and the second support portion 22 through the two passages 14, thereby adjusting the expansion or contraction of the first support portion 21 and the second support portion 22, further adjusting the position of the turbine support ring 7, and finally adjusting the size of the gap between the turbine support ring 7 and the rotor 8.
The gas turbine supporting ring adjusting device provided by the embodiment of the invention is provided with the controller 5, the adjusting quantity of the turbine supporting ring 7 can be calculated according to the clearance data obtained by measurement of the measuring part 4, the adjusting precision of the turbine supporting ring 7 is improved, and compared with manual calculation and manual repeated adjustment, the adjusting speed of the turbine supporting ring 7 is improved, so that the operation efficiency of the gas turbine is improved.
A gas turbine shroud retaining ring adjustment assembly of an embodiment of the present invention will now be described with reference to fig. 1 and 2.
The gas turbine shroud adjustment assembly includes a first support 1, a second support 2, a drive 3, a measurement member 4, and a controller 5.
As shown in fig. 1 and 2, the first section 11 of the first support 1 is detachably connected to the outer wall surface of the gas turbine. The first section 11 of the first support 1 may also be detachably connected to the outer wall surface of the gas turbine by means of fasteners (not shown), which may be detachable existing fasteners such as bolts, snaps, etc. The second support member 2 is fitted over the third section 13 of the first support member 1, the upper end of the first support portion 21 is connected to the turbine retaining ring 7, and the lower end of the second support portion 22 is connected to the turbine retaining ring 7. A first predetermined gap (not shown) is formed between the lower end surface of the first supporting portion 21 and the upper end surface of the third section 13, and a second predetermined gap (not shown) is formed between the upper end surface of the second supporting portion 22 and the lower end surface of the third section 13. The driving member 3 is disposed outside the gas turbine, and a left end of the driving member 3 is communicated with a right end of the connecting pipe 31, and a left end of the connecting pipe 31 is communicated with a right end of the passage 14. The driving member 3 supplies the pressure medium to the second support member 2 through the passage 14, and the pressure medium in the passage 14 can enter the first support portion 21 and the second support portion 22 through the passage 14, respectively, thereby adjusting the expansion or contraction of the first support portion 21 and the second support portion 22.
The lower end of the measuring part 4 penetrates through the gas turbine, the measuring part 4 is used for monitoring the size of a gap between a turbine supporting ring 7 and a rotor 8 of the gas turbine, one end of the controller 5 is connected with the measuring part 4, and the other end of the controller 5 is connected with the driving part 3.
The operation of the gas turbine shroud adjustment assembly of an embodiment of the present invention will now be described with reference to fig. 1 and 2.
The measuring component 4 measures the size of the gap between the rotor 8 and the turbine supporting ring 7, the controller 5 calculates the relative eccentric position between the turbine supporting ring 7 and the rotor 8 according to the data of the gap between the turbine supporting ring 7 and the rotor 8 measured by the measuring component 4, obtains the adjustment amount of the turbine supporting ring 7, further obtains the extension or contraction amount of the second supporting member 2, and then respectively controls the pressure of pressure media in the first supporting portion 21 and the second supporting portion 22 through the two channels 14, so that the extension or contraction of the first supporting portion 21 and the second supporting portion 22 is adjusted, further the position of the turbine supporting ring 7 is adjusted, and finally the size of the gap between the turbine supporting ring 7 and the rotor 8 is adjusted.
The gas turbine of the embodiment of the present invention includes a cylinder block 6, a rotor 8, a turbine retainer ring 7, and an adjusting device. The cylinder body 6 is internally provided with an accommodating cavity 61, the rotor 8 is arranged in the accommodating cavity 61, the turbine holding ring 7 is sleeved on the rotor 8, and a preset gap is formed between the inner wall surface of the turbine holding ring 7 and the outer wall surface of the rotor 8. The adjusting device is a turbine supporting ring adjusting device of any one of the gas turbines, the first supporting piece 1 is connected with the cylinder body 6, one end of the first supporting piece 1 extends into the accommodating cavity 61, and the second supporting piece 2 is connected with the turbine supporting ring 7.
Specifically, as shown in fig. 1, the cylinder 6 has a cylindrical shape, and the accommodation chamber 61 extends in the longitudinal direction of the cylinder 6. The first section 11 is detachably connected with the cylinder body 6, the right end of the first supporting piece 1 extends into the accommodating cavity 61, the second section 12 penetrates through the inner wall surface and the outer wall surface of the cylinder body 6, the second supporting piece 2 is sleeved on the third section 13, the first supporting part 21 and the second supporting part 22 are connected with the turbine supporting ring 7, the position of the turbine supporting ring 7 is adjusted by extending and contracting the first supporting part 21 and the second supporting part 22, and therefore the size of a gap between the inner wall surface of the turbine supporting ring 7 and the outer wall surface of the rotor 8 is adjusted.
The gas turbine provided by the embodiment of the invention is provided with the turbine retaining ring adjusting device, so that the size of the gap between the turbine retaining ring 7 and the rotor 8 can be adjusted in an automatic adjusting mode on the premise that the gas turbine does not shut down, collision and abrasion between the turbine retaining ring 7 and the rotor 8 are avoided, the automation degree of the gas turbine is improved, and the operation efficiency of the gas turbine is also improved.
In some embodiments, the turbine retaining ring 7 of the gas turbine has a connecting portion 71, and the second support member 2 is connected to the connecting portion 71.
As shown in fig. 1 and 2, the turbine support ring 7 is provided with a connecting portion 71, the upper end of the first support portion 21 and the lower end of the second support portion 22 are respectively connected to the connecting portion 71, and the first support portion 21 and the second support portion 22 extend or contract to move the connecting portion 71, and thus move the turbine support ring 7.
In the gas turbine of the embodiment of the invention, the turbine retaining ring 7 is provided with the connecting part 71, so that the connection between the turbine retaining ring 7 and the second supporting part 2 can be adjusted to have stability, the second supporting part 2 is prevented from loosening or falling off when the position of the turbine retaining ring 7 is adjusted, the collision and abrasion between the turbine retaining ring 7 and the rotor 8 can be avoided, and the operation efficiency of the gas turbine is improved.
In some embodiments, the connecting portion 71 has a cavity 711 therein, the second supporting member 2 is disposed in the cavity 711, and at least a portion of the first supporting member 1 extends into the cavity 711 and is connected to the second supporting member 2.
Specifically, as shown in fig. 1 and 2, one end of the cavity 711 facing the first support member 1 has an opening, as shown in fig. 2, a right end of the cavity 711 has an opening, a left end of the first support member 1 extends into the cavity 711, a left end surface of the first support member 1 has a gap with a bottom surface of the cavity 711, the second support member 2 is connected with a side wall surface of the cavity 711, that is, an upper end of the first support member 21 is connected with the side wall surface of the cavity 711, and a lower end of the second support member 22 is connected with the side wall surface of the cavity 711.
In the gas turbine according to the embodiment of the present invention, the connecting portion 71 has the cavity 711 therein, so that the stability of the connection between the connecting portion 71 and the second support member 2 can be increased.
In some embodiments, the number of the adjusting devices is plural, the plural adjusting devices are arranged at intervals in the circumferential direction of the cylinder 6, the number of the connecting portions 71 is plural, and the plural connecting portions 71 correspond to the plural adjusting devices one by one.
Specifically, as shown in fig. 1 and fig. 2, the plurality of adjusting devices are uniformly spaced in the circumferential direction of the cylinder block 6, the plurality of connecting portions 71 are uniformly spaced in the circumferential direction of the turbine retaining ring 7, and the plurality of connecting portions 71 correspond to the plurality of adjusting devices one to one, for example, the number of connecting portions 71 may be four, two adjacent connecting portions 71 are spaced at 90 ° in the circumferential direction of the turbine retaining ring 7, when the number of adjusting devices is four, two adjacent adjusting devices are spaced at 90 ° in the circumferential direction of the cylinder block 6, by providing the plurality of adjusting devices, it is possible to perform multi-directional position adjustment on the turbine retaining ring 7, for example, by providing four adjusting devices, it is possible to adjust the position of the turbine retaining ring 7 in four directions, up and down, left and right, and improve the adjustment efficiency and accuracy of the adjusting devices.
According to the gas turbine provided by the embodiment of the invention, the number of the adjusting devices is multiple, so that the efficiency and the precision of adjusting the position of the turbine retaining ring 7 can be improved, and the operation efficiency and the stability of the gas turbine are improved.
In some embodiments, the cylinder block 6 of the gas turbine is provided with a groove 62, and the first section 11 is provided within the groove 62.
Specifically, as shown in fig. 2, the cylinder 6 is provided with a groove 62, the first segment 11 is arranged in the groove 62, and the first segment 11 is connected with the groove 62. It should be noted that the number of the grooves 62 may also be multiple, and the grooves correspond to multiple adjusting devices one by one.
According to the gas turbine provided by the embodiment of the invention, the cylinder body 6 is provided with the groove 62, so that the stability of connection between the outer wall surface of the cylinder body 6 and the first section 11 can be improved.
In the description of the present invention, it is to be understood that the terms "central," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," "circumferential," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the invention and to simplify the description, and are not intended to indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and are therefore not to be considered limiting of the invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; may be mechanically coupled, may be electrically coupled or may be in communication with each other; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In the present invention, unless otherwise expressly stated or limited, the first feature "on" or "under" the second feature may be directly contacting the first and second features or indirectly contacting the first and second features through an intermediate. Also, a first feature "on," "over," and "above" a second feature may be directly or diagonally above the second feature, or may simply indicate that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature may be directly under or obliquely under the first feature, or may simply mean that the first feature is at a lesser elevation than the second feature.
In the present disclosure, the terms "one embodiment," "some embodiments," "an example," "a specific example," or "some examples" and the like mean that a specific feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present disclosure. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples and features of different embodiments or examples described in this specification can be combined and combined by one skilled in the art without contradiction.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art within the scope of the present invention.
Claims (10)
1. A gas turbine shroud adjustment assembly, comprising:
a first support member having one end adapted to be coupled to a gas turbine;
the second supporting piece is suitable for supporting the turbine supporting ring, can be expanded and contracted in the width direction of the first supporting piece, is sleeved on the first supporting piece, and has a preset gap between the inner wall surface of the second supporting piece and the outer wall surface of the first supporting piece;
the driving piece is connected with the second supporting piece and used for adjusting the size of the preset gap.
2. The gas turbine shroud ring adjusting device of claim 1, wherein said first support member includes a first section, a second section, and a third section connected in series, said first section being adapted to be connected to said gas turbine, said second support member being fitted over said third section, and said second support member being extendable and retractable in a width direction of said first support member over said third section,
in a cross section of the first support, a cross sectional area of the third section is smaller than a cross sectional area of the second section to form a first step surface, and a cross sectional area of the second section is smaller than a cross sectional area of the first section to form a second step surface.
3. The gas turbine shroud ring adjuster according to claim 2, wherein said first support member is provided with a passage extending along a length of said first support member, and one end of said drive member is connected to said second support member through said passage.
4. The gas turbine shroud ring adjustment assembly of claim 2 or 3, further comprising a measurement member having one end passing through said gas turbine, said measurement member adapted to measure a clearance between said shroud ring and a rotor of said gas turbine.
5. The gas turbine shroud ring adjustment assembly of claim 4, further comprising a controller coupled to said measurement member and said drive member, respectively, said controller controlling extension and retraction of said second support member based on a clearance between said turbine shroud ring and a rotor of said gas turbine as measured by said measurement member.
6. A gas turbine engine, comprising:
a cylinder body having an accommodation cavity therein;
the rotor is arranged in the accommodating cavity;
the turbine supporting ring is arranged in the accommodating cavity and sleeved on the rotor, and a preset gap is formed between the inner wall surface of the turbine supporting ring and the outer wall surface of the rotor;
the adjusting device is the turbine.
7. The gas turbine of claim 6, wherein said turbine retaining ring has a connecting portion, said second support member being connected to said connecting portion.
8. The gas turbine of claim 7, wherein said connecting portion has a cavity therein, said second support member is disposed in said cavity, and at least a portion of said first support member extends into said cavity and is connected to said second support member.
9. The gas turbine according to claim 7 or 8, wherein the number of the adjusting devices is plural, the plurality of adjusting devices are arranged at intervals in the circumferential direction of the cylinder block, the number of the connecting portions is plural, and the plurality of connecting portions correspond to the plurality of adjusting devices one by one.
10. A gas turbine according to claim 6, wherein said cylinder block is provided with a groove, said first section being provided in said groove.
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| CN114876640A (en) * | 2022-06-10 | 2022-08-09 | 中国联合重型燃气轮机技术有限公司 | Regulating device and gas turbine |
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| CN114412582B (en) | 2024-09-13 |
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