JP6169007B2 - Rotor blade and axial flow rotating machine - Google Patents

Description

  The present invention relates to a moving blade used in an axial-flow rotating machine and an axial-flow rotating machine including the same.

  For example, an axial compressor is known as a kind of axial flow rotating machine. In this axial flow rotary machine, fluid such as air is taken in and compressed by passing the moving blades provided in multiple rows on the rotating shaft and the stationary blades provided in the casing alternately with the moving blades. After that, the compressed fluid is discharged through the diffuser section.

  Patent Document 1 discloses a gas turbine provided with such an axial compressor. In the gas turbine, the turbine is driven by the combustion gas obtained by mixing and burning the compressed air from the axial flow compressor and the fuel, and the rotational power is taken out.

  By the way, in the diffuser section of the axial flow compressor, a diffuser channel is formed so that the channel cross-sectional area gradually increases toward the downstream side of the fluid flow, and the pressure is reduced by reducing the flow rate of the compressed fluid. Let me recover.

JP 2011-169172 A

  However, in the fluid flowing into the diffuser portion, a flow velocity distribution (pressure distribution) is generated in the radial direction of the rotating shaft due to the influence of shear between the inner surface of the casing and the fluid. For this reason, when the fluid flows through the diffuser flow path, the fluid tends to be peeled off from the inner surface of the diff user flow path, which may cause a loss.

  The present invention has been made in consideration of such circumstances, and provides a moving blade and an axial compressor that can reduce loss in the diffuser section and obtain sufficient pressure recovery performance. Objective.

In order to solve the above problems, the present invention employs the following means.
That is, the moving blade according to one aspect of the present invention includes a rotating shaft that extends in the direction of the axis and rotates around the axis, and supports the rotating shaft from the outer peripheral side so as to be relatively rotatable. A casing that defines a fluid flow path therebetween, and is provided on the downstream side of the casing and communicates with the flow path to form an annular shape centering on the axis, and the flow path cross-sectional area increases toward the downstream side A diffuser portion in which a diffuser flow path is defined, a stationary blade row protruding inward in the radial direction of the axis from the casing and provided in a plurality of rows in the direction of the axis, and a direction of the axis in the stationary blade row And a moving blade row that is provided in a plurality of rows adjacent to each other and compresses or pumps the fluid, and is located on the most downstream side of the fluid flow in the moving blade row Constitute the last blade row to be A plurality arranged the blades at intervals in the circumferential direction of the axis, as toward the hub side and the tip side than the central portion of the blade height direction can be compressed fluid to a higher pressure, each blade the flow direction of the fluid in the wings outlet in order to vary at the hub side and the tip side with respect to the central portion, the hub side and the tip side than turning angle in the center of the blade height direction at each blade Ru equipped with a blade portion is larger.

According to such a moving blade, the turning angle of the blade part in the moving blade of the final moving blade row, that is, the relative angle between the fluid flow direction with respect to the blade inlet and the fluid flow direction at the blade outlet is determined by the blade height. The hub side and the tip side are larger than the central portion in the vertical direction. For this reason, the flow direction of the fluid passing through the final moving blade row is largely changed on the hub side and the tip side. Therefore, the rotor blade performs more work on the fluid on the hub side and the tip side, and the amount of fluid compression (or pumping amount) increases at this position.
Here, if the turning angle of the moving blade is uniform in the blade height direction, the fluid flow velocity is slow on the hub side and tip side due to the influence of the shearing force between the fluid and the inner surface of the flow path of the casing. Become.
In this regard, by changing the turning angle of the moving blade in the blade height direction as described above, the flow velocity of the fluid near the inner surface of the flow path is increased, and the velocity of the fluid that has passed through the last moving blade row (total pressure) ) The distribution can be made more uniform in the blade height direction, that is, the radial direction of the axis, at the exit of the diffuser section. As a result, fluid separation in the diffuser channel can be suppressed.
Further, by suppressing the separation of the fluid as described above, the pressure can be stably recovered even if the dimension in the axial direction of the diffuser portion is shortened, and the friction loss of the fluid caused by the friction with the diffuser flow path can be reduced. Reduction is possible.
Further, by suppressing the separation of the fluid, it is possible to increase the ratio of the channel cross-sectional area between the inlet and the outlet of the diffuser channel, and the pressure recovery amount can be increased .
An axial-flow rotating machine according to another aspect of the present invention includes a moving blade row having the above-described moving blade, and a rotation that fixes the moving blade row, extends in the direction of the axis, and rotates about the axis. A shaft and a casing that supports the rotating shaft from the outer peripheral side so as to be relatively rotatable, and define a fluid flow path between the rotating shaft and the shaft, and are provided on the downstream side of the casing and communicate with the flow path A diffuser portion having an annular shape centering on the axis and having a diffuser flow path whose flow cross-sectional area increases toward the downstream side, and protruding radially inward of the axis from the casing, A stationary blade row having a plurality of rows adjacent to the moving blade row in the direction of the axis, and having stationary blades spaced apart from each other in the circumferential direction of the axis.
According to such an axial-flow rotating machine, the above-described moving blade is included in the final moving blade row, thereby increasing the flow velocity of the fluid in the vicinity of the inner surface of the flow path of the casing and passing through the final moving blade row. The velocity (total pressure) distribution of the fluid can be made uniform in the blade height direction, that is, the radial direction of the axis, at the outlet of the diffuser portion .
Further, the diffuser portion is an end portion on the downstream side of the final stationary blade row provided downstream of the upstream end portion of the final moving blade row and further downstream of the final moving blade row. It may be provided in the casing so that the diffuser channel extends from the upstream side.
As described above, because the turning angle of the moving blades of the final moving blade row is different in the blade height direction, the fluid whose total pressure is increased in the vicinity of the inner surface of the flow channel flows into the diffuser flow channel. Separation of fluid in the flow path is unlikely to occur. Therefore, even if the diffuser flow path is started from the downstream side of this position, including the position where the final moving blade row is provided, and from the upstream side of the final stationary blade row, loss is unlikely to occur. Therefore, by doing in this way, pressure recovery can be performed from an earlier stage while obtaining the fluid deceleration effect by the last stationary blade row. As a result, the dimension of the diffuser portion in the axial direction can be further shortened, and the flow passage cross-sectional area ratio between the inlet and the outlet of the diffuser flow passage can be further increased.

  Further, in the diffuser portion, a part of the inner surface of the diffuser channel may be formed by a part of the stationary blade in the final stationary blade row.

  In this way, a part of the vane forms the inner surface of the diffuser flow path, so that even if the diffuser flow path is expanded from the upstream side of the downstream end of the final stationary blade row, it expands toward the downstream side. Therefore, a part of the stationary blade (for example, shroud or the like) does not protrude from the inner surface of the diffuser flow path into the diffuser flow path. Therefore, the fluid can be circulated more smoothly in the diffuser flow path toward the downstream side, and the separation of the fluid can be further suppressed.

  Further, in the diffuser portion, the diffuser flow path includes a first region corresponding to a region in the direction of the axis where the final stationary blade row is provided, and a second region downstream of the first region, The second region is further divided into a third region on the downstream side of the second region, and the second region has a larger amount of enlargement of the channel cross-sectional area than the first region. The expansion amount of the channel cross-sectional area may be smaller in the three regions.

In this way, from the first region to the third region, that is, the diffuser flow path is directed to the downstream side, first, the diffuser channel expands small, then expands large, and then expands small. Therefore, when the fluid passes through the final stationary blade row, that is, when passing through the first region, the amount of fluid deceleration by the diffuser flow path can be reduced, so that the separation of the fluid in the final stationary blade row is suppressed. Can do. Thereafter, when passing through the second region, the amount of deceleration of the fluid can be increased by the diffuser flow path, and a sufficient pressure recovery amount can be obtained. Furthermore, although the boundary layer of the fluid develops in the third region on the most downstream side, the amount of deceleration of the fluid can be reduced, so that separation in the third region can be suppressed.
Here, the expansion amount of the channel cross-sectional area means an angle based on the axis of the diffuser channel in each region, that is, an opening angle.

  Further, in the diffuser portion, the diffuser flow path is divided into a first region corresponding to a region in the direction of the axis where the final stationary blade row is provided, and a second region downstream of the first region. The second region may be divided and the amount of enlargement of the channel cross-sectional area may be smaller than that of the first region.

  In this way, the diffuser flow path expands smaller in the second region than in the first region. In this case, by opening the diffuser channel from the first region, a large amount of deceleration can be obtained in the first region while suppressing fluid separation on the inner surface (end wall) of the diffuser channel downstream of the first region. Then, even if the boundary layer develops in the second region, the fluid can be decelerated without peeling.

  Further, in the diffuser portion, the flow passage cross-sectional area may be increased so that the radially inner inner surface of the diffuser flow passage is inclined outward in the radial direction toward the downstream side.

  Since the fluid flows into the diffuser channel with a component in the rotational direction of the rotating shaft, the fluid flows through the diffuser channel with the fluid approaching the radially inner surface side of the diffuser channel. Therefore, the diffuser flow path is formed along the flow direction of the fluid by enlarging the cross-sectional area of the diffuser flow path so as to incline radially outward. For this reason, the fluid can be circulated more smoothly in the diffuser flow path, and the effect of pressure recovery can be improved.

  Furthermore, in the diffuser portion, the flow passage cross-sectional area may be increased so that the inner surface of the diffuser flow passage on the inner side in the radial direction of the axis is inclined inward in the radial direction toward the downstream side.

  In this way, in the diffuser channel, the inner surface on the radially inner side and the inner surface on the radially inner side are inclined radially inward toward the downstream side, so that the diffuser channel can be expanded at a shorter distance and pressure recovery is possible. It becomes. Therefore, the length of the diffuser channel in the axial direction can be shortened, and the friction loss of the fluid can be reduced.

  Further, in the diffuser portion, the flow path cross-sectional area may be increased so that the inner surface of the diffuser flow path on the inner side in the radial direction of the axis is inclined toward the downstream side in the radial direction.

As described above, in the diffuser flow path, the radially inner surface and the radially inner surface are inclined radially outward toward the downstream side, so that, for example, the fluid compressed or pumped to the device disposed radially outside Can guide you.
An axial-flow rotating machine according to another aspect of the present invention includes a rotating shaft that extends in the direction of the axis and rotates around the axis, and the rotating shaft that supports the rotating shaft from the outer peripheral side so as to be relatively rotatable. A casing defining a fluid flow path between the casing and the casing. The casing is provided on the downstream side of the casing and communicates with the flow path to form an annular shape centering on the axis, and the flow path cross-sectional area toward the downstream side. A diffuser section in which a diffuser flow path is defined, a stationary blade row protruding inward in the radial direction of the axis from the casing and provided in a plurality of rows in the direction of the axis, and the axis in the stationary blade row And a moving blade row provided in a plurality of rows adjacent to each other in the direction of the fluid to compress or pump the fluid, and provided on an axial-flow rotating machine, the most downstream side of the fluid flow in the moving blade row The final blade row located at In particular, a moving blade provided with a plurality of blades arranged at intervals in the circumferential direction of the axis, each turning angle being larger on the hub side and tip side than the central portion in the blade height direction. A rotating blade row having a rotating blade that fixes the moving blade row, extends in the direction of the axis and rotates around the axis, and supports the rotating shaft from the outer peripheral side so as to be relatively rotatable, and the rotating shaft A casing defining a fluid flow path between the casing and the downstream side of the casing, communicating with the flow path, forming an annular shape centering on the axis, and having a flow path cross-sectional area toward the downstream side A diffuser portion in which an expanding diffuser channel is defined, and protrudes radially inward of the axis from the casing, and is provided in a plurality of rows adjacent to the moving blade row in the direction of the axis. Provided apart from each other in the circumferential direction of the axis. The diffuser portion is downstream of the upstream end of the final moving blade row and further downstream of the final moving blade row. The diffuser flow path is provided in the casing so as to extend from the upstream side to the downstream end of the stationary blade row, and the final stationary blade row is a first final stationary blade row and a first final stationary blade. The diffuser flow path extends from the upstream side of the downstream end of the second final stationary blade row. The second final stationary blade row is adjacent to the upstream side of the row.

  According to the above moving blade and the axial flow rotating machine, the flow loss of the fluid in the diffuser portion can be reduced because the turning angle of the blade portion of the moving blade is different in the blade height direction. Recovery performance can be obtained.

It is a longitudinal section containing the axis of the axial flow compressor concerning a first embodiment of the present invention. It is a longitudinal section containing the axis of the axial flow compressor concerning a first embodiment of the present invention, and is a figure expanding and showing the diffuser part circumference. It is a perspective view which shows the moving blade which comprises the last moving blade row | line | column of the axial flow compressor which concerns on 1st embodiment of this invention. It is sectional drawing orthogonal to the blade height direction of the moving blade which comprises the last moving blade row | line | column of the axial flow compressor which concerns on 1st embodiment of this invention, (a) shows the AA cross section of FIG. (B) shows the BB cross section of FIG. 3, (c) shows the CC cross section of FIG. It is a longitudinal cross-sectional view containing the axial line of the axial flow compressor which concerns on 2nd embodiment of this invention, Comprising: It is a figure which expands and shows a diffuser part periphery. It is a longitudinal cross-sectional view including the axis line of the axial flow compressor which concerns on the 1st modification of 2nd embodiment of this invention, Comprising: It is a figure which expands and shows a diffuser part periphery further. It is a longitudinal cross-sectional view containing the axis line of the axial flow compressor which concerns on the 2nd modification of 2nd embodiment of this invention, Comprising: It is a figure which expands and shows a diffuser part periphery further. It is a longitudinal cross-sectional view containing the axial line of the axial flow compressor which concerns on 3rd embodiment of this invention, Comprising: It is a figure which expands and shows a diffuser part periphery.

[First embodiment]
Hereinafter, an axial flow compressor 1 (axial flow rotary machine) according to a first embodiment of the present invention will be described with reference to the drawings.

  The axial flow compressor 1 takes in a gas G (fluid) such as air, compresses it, and discharges it. As shown in FIGS. 1 and 2, the axial flow compressor 1 includes a rotating shaft 2 that rotates about an axis O, a casing 3 that supports the rotating shaft 2, and a diffuser portion 4 provided in the casing 3. A stationary blade row 10 protruding from the casing 3 toward the rotating shaft 2 and a moving blade row 20 protruding from the rotating shaft 2 toward the casing 3 are provided.

  The rotating shaft 2 is a columnar member extending in the direction of the axis O.

  The casing 3 has a cylindrical shape that covers the rotary shaft 2 from the outer peripheral side. The casing 3 is provided with a bearing (not shown). The casing 3 supports the rotating shaft 2 via this bearing, so that the casing 3 and the rotating shaft 2 can rotate relative to each other. A space S is defined between the casing 3 and the rotating shaft 2.

  The casing 3 is formed with a gas G suction port 3 a that opens to the outside of the casing 3 on one side in the direction of the axis O (left side as viewed in FIG. 1) and communicates with the space S. The gas G is introduced into the space S from the suction port 3a and flows from one side in the direction of the axis O toward the other side. Hereinafter, one side in the direction of the axis O is the upstream side, and the other side is the downstream side.

  The stationary blade row 10 is fixed to the casing 3 and protrudes radially inward of the axis O from the casing 3 and is disposed in the space S, and is provided in a plurality of rows at intervals in the direction of the axis O.

Each stationary blade row 10 has a plurality of stationary blades 12 provided at intervals in the circumferential direction of the axis O.
Each stationary blade 12 includes a blade portion 13 whose cross section perpendicular to the radial direction forms a blade shape, an outer shroud 14 provided on the radially outer side of the blade portion 13, and an inner side provided on the radially inner side of the blade portion 13. And a shroud 15. The outer shroud 14 is fitted into the casing 3 and constitutes a part of the inner surface of the casing 3. By connecting the inner shrouds 15 of the stationary blades 12 adjacent to each other in the circumferential direction, an annular shape centering on the axis O is formed.

  In this embodiment, the outlet guide vane 11 (or the stationary blade 12) is provided on the most downstream side of the space S in the casing 3, but such an outlet guide vane 11 (or the stationary blade 12) is not necessarily provided. It does not have to be done.

  The rotor blade row 20 is fixed to the rotary shaft 2 and protrudes radially outward from the rotary shaft 2 in the radial direction of the axis O, and is disposed in the space S, and is provided in a plurality of rows at intervals in the direction of the axis O. . These moving blade rows 20 are provided between the stationary blade rows 10 adjacent to each other in the direction of the axis O to the stationary blade row 10.

  Here, on the most downstream side of the casing 3, the moving blade row 20 is not adjacent to the upstream side of the outlet guide vane 11, and two rows of stationary blade rows 10 are provided adjacent to each other in the direction of the axis O. . Here, among these two adjacent stationary blade rows 10, the outlet guide vane 11 is the first final stationary blade row 10 </ b> A, and the stationary blade row 10 provided on the upstream side of the outlet guide vane 11 is the second final stationary blade. Column 10B.

  A moving blade row 20 is provided adjacent to the upstream side of the second final stationary blade row 10B in the direction of the axis O. This moving blade row 20 is defined as a final moving blade row 20A.

As shown in FIGS. 3 and 4, the final moving blade row 20 </ b> A has a plurality of moving blades 22 that are provided at intervals in the circumferential direction of the axis O.
Each rotor blade 22 includes a blade portion 25 whose cross section perpendicular to the radial direction forms a blade shape, a platform 23 provided on the radially inner side of the blade portion 25, and a blade root 24 that protrudes radially inward from the platform 23. And.

  The moving blade 22 is fixed to the rotating shaft 2 by inserting a blade root 24 into the rotating shaft 2. The wing part 25 has a negative pressure surface 22 a facing the rear side in the rotation direction R of the rotary shaft 2 and a pressure surface 22 b facing the front side in the rotation direction R.

  In the space S of the casing 3, a gap formed between the stationary blades 12 and the moving blades 22 is a flow path C through which the gas G introduced from the suction port 3a flows. The gas G introduced into the flow path C is compressed by passing through the blade portion 25 of the moving blade 22 of each moving blade row 20 and turning the angle along the pressure surface 22 b of the moving blade 22.

The turning angle of the blade portion 25 of the moving blade 22 is larger on the hub side (inner side in the radial direction) and on the tip side (outer side in the radial direction) than in the blade height direction, that is, the central portion in the radial direction of the axis O. ing. Specifically, as shown in FIGS. 4A and 4C, on the hub side and the tip side, the flow direction of the fluid at the outlet of the wing portion 25 relative to the flow direction of the gas G at the inlet of the wing portion 25 The relative angle θ1 is steeper. On the other hand, as shown in FIG. 4B, the relative angle θ2 is a gentler angle at the center in the blade height direction.
The angles θ1 and θ2 preferably change smoothly from the center in the blade height direction toward the hub side and the tip side.

  The diffuser portion 4 is provided on the downstream side of the casing 3 and has a cylindrical shape with the axis O as the center. More specifically, the diffuser portion 4 has an inner cylinder formed around the axis O, and an outer cylinder 4b formed around the axis O and having a diameter larger than the diameter of the inner cylinder 4a. It has a double tubular shape.

  A rotating shaft 2 is disposed inside the inner cylinder 4a. An annular space defined between the inner cylinder 4a and the outer cylinder 4b is a diffuser channel DC communicating with the space S of the casing 3, that is, the channel C. The diffuser channel DC is defined such that the channel cross-sectional area increases toward the downstream side. Here, the channel cross-sectional area indicates the area of a cross section perpendicular to the axis O.

Then, the gas G compressed through the flow path C is discharged to the outside of the axial flow compressor 1 through the diffuser flow path DC.
The diffuser portion 4 may be provided integrally with the casing 3 or may be provided separately.

  In the present embodiment, the diffuser portion 4 is provided in the casing 3 such that the diffuser channel DC extends from the downstream side of the first final stationary blade row 10A.

  According to such an axial flow compressor 1, the turning angle θ1 of the blade portion 25 in the moving blade 22 of the final moving blade row 20A is larger on the hub side and the tip side than on the central portion in the blade height direction. ing. Therefore, the flow direction of the gas G passing through the final moving blade row 20A is diverted more on the hub side and the tip side. Therefore, the moving blade 22 performs more work on the fluid on the hub side and the tip side, so that the compression amount of the gas G increases at this position.

  Here, if the turning angle of the rotor blade 22 is uniform in the blade height direction, the gas G on the hub side and the tip side is affected by the shearing force between the gas G and the inner surface of the diffuser channel DC. The flow rate of is slow. In this respect, as described above, the turning angles θ1 and θ2 of the blade portion 25 of the moving blade 22 are different in the blade height direction, thereby increasing the flow velocity of the gas G in the vicinity of the inner surface of the diffuser flow channel DC, and the final moving blade. The distribution of the velocity (total pressure) of the gas G that has passed through the row 20A can be made uniform in the blade height direction, that is, the radial direction of the axis O at the outlet of the diffuser section 4. Therefore, separation of the gas G in the diffuser channel DC can be suppressed.

Here, in general, in order to improve the performance of pressure recovery in the diffuser section 4, it is necessary to increase the ratio of the channel cross-sectional area between the inlet and the outlet of the diffuser channel DC. Further, the diffuser channel DC is formed so as to enlarge the channel cross-sectional area while suppressing the opening angle of the channel C to a predetermined angle so that the gas G does not peel off.
The opening angle referred to here is an angle at which the radially inner surface of the diffuser channel DC that is the surface of the inner cylinder 4a is inclined with respect to the axis O, and the diffuser channel DC that is the surface of the outer cylinder 4b. The sum of the angle at which the radially outer surface is inclined in the radial direction with respect to the axis O is shown.

  Accordingly, if the turning angles θ1 and θ2 of the moving blade 22 are the same and the blade portion 25 has a uniform shape in the radial direction, the diffuser portion is maintained in order to maintain the pressure recovery function in the diffuser portion 4. The length dimension in the direction of the axis O of 4 becomes large. As a result, the distance at which the gas G contacts the inner surface of the diffuser channel DC becomes long, and the loss due to friction increases.

  In this respect, in the present embodiment, by uniforming the velocity distribution of the gas G in this way, the dimension of the diffuser portion 4 in the direction of the axis O can be shortened. Therefore, it is possible to reduce the friction loss of the gas G caused by the friction with the diffuser channel DC.

  In addition, since the velocity distribution of the gas G is made uniform, the ratio of the channel cross-sectional area between the inlet and the outlet of the diffuser channel DC can be increased, and the pressure recovery amount in the diffuser section 4 is increased. be able to. That is, for example, the opening angle of the diffuser channel DC can be set to 10 degrees or more.

[Second Embodiment]
The axial flow compressor 31 (axial flow rotary machine) according to the second embodiment of the present invention will be described below.
In addition, the same code | symbol is attached | subjected to the component similar to 1st embodiment, and detailed description is abbreviate | omitted.
As shown in FIG. 5, in the axial flow compressor 31, the diffuser portion 34 is located downstream from the final moving blade row 20A and from the upstream side of the downstream end of the second final stationary blade row 10B. It is provided in the casing 3 so that the diffuser channel DC1 extends. In the present embodiment, the diffuser channel DC1 extends from between the final moving blade row 20A and the second final stationary blade row 10B.

  Here, the downstream end of the second final stationary blade row 10B indicates the downstream end of the outer shroud 14 and the inner shroud 15 in the second final stationary blade row 10B.

  According to the axial flow compressor 31 of the present embodiment, the pressure recovery can be performed from an earlier stage while obtaining the gas G deceleration effect by the first final stationary blade row 10A and the second final stationary blade row 10B. As a result, it is possible to further reduce the dimension of the diffuser portion 34 in the direction of the axis O, and to further increase the flow path cross-sectional area ratio between the inlet and the outlet of the diffuser flow path DC1.

  Here, the total pressure is applied in the vicinity of the inner surface of the flow path C (which means the inner peripheral surfaces on both the inner side and the outer side in the radial direction) which becomes the end wall portion in the radial direction by the moving blades 22 of the final moving blade row 20A. Since the raised gas G flows into the diffuser channel DC1, separation of the gas G in the diffuser channel DC is less likely to occur. Therefore, even if it is diffuser flow path DC1 of this embodiment, pressure recovery is possible, reducing the loss of gas G. FIG.

  Here, in the present embodiment, as shown in FIGS. 6 and 7, the diffuser portion 34 is located downstream of the downstream end of the second final stationary blade row 10B, and the first final stationary blade row 40A. The diffuser flow path DC1 may be provided in the casing 3 so as to extend from the upstream side of the downstream end portion.

  The downstream end of the first final stationary blade row 40A indicates the downstream end of the outer shroud 44 in the first final stationary blade row 40A. Similarly, the downstream end of the second final stationary blade row 10B indicates the downstream end of the outer shroud 44 in the second final stationary blade row 10B.

  In this case, a part of the inner surface of the diffuser channel DC1 is formed by a part of the stationary blade 12 in the first final stationary blade row 40A, that is, the outer shroud 44. Specifically, in FIG. 6, the surface facing the radially inner side of the outer shroud 44 is inclined radially outward from the midway position in the axis O direction toward the downstream side, and the inner surface of the diffuser flow channel DC1. It has become a part of.

  In FIG. 7, the surface facing the radially inner side of the outer shroud 44 is inclined radially outward toward the downstream side over the entire region in the axis O direction, and becomes a part of the inner surface of the diffuser flow channel DC1. ing.

  As described above, the outer shroud 44 that is a part of the stationary blade 12 forms the inner surface of the diffuser flow channel DC1, so that the diffuser flow channel DC1 is moved from the upstream side to the downstream end of the first final stationary blade row 40A. Even if enlarged, the outer shroud 44 does not protrude from the inner surface of the diffuser flow channel DC1 that expands toward the downstream side (see FIG. 5).

  Therefore, the gas G can be more smoothly circulated toward the downstream side in the diffuser channel DC1, and the separation of the gas G can be further suppressed. In particular, by making the surface facing the radially inner side of the outer shroud 44 flush with the surface facing the radially inner side of the diffuser channel DC1, the effect of suppressing the separation of the gas G can be improved.

  Here, in the present embodiment, as shown in FIGS. 6 and 7, the surface facing the radially inner side of the outer shroud 14 in the second final stationary blade row 10B is inclined radially outward toward the downstream side. And you may become a part of inner surface of the diffuser flow path DC1.

[Third embodiment]
Hereinafter, the axial-flow compressor 51 which concerns on 2nd embodiment of this invention is demonstrated.
In addition, the same code | symbol is attached | subjected to the component similar to 1st embodiment and 2nd embodiment, and detailed description is abbreviate | omitted.

  As shown in FIG. 8, in the diffuser section 54 of the axial flow compressor 51, the diffuser flow path DC2 corresponds to a region in the axis O direction in which the first final stator blade row 10A and the second final stator blade row 10B are provided. It is divided into a first area A1, a second area A2 downstream from the first area A1, and a third area A3 further downstream from the second area A2.

  The second region A2 has a larger flow cross-sectional area than the first region A1, and the third region A3 has a smaller flow cross-sectional area than the second region A2. . Here, the expansion amount of the channel cross-sectional area means the opening angle of the diffuser channel DC2 in each region.

  In this way, from the first region A1 toward the third region A3, that is, the diffuser flow channel DC2 toward the downstream side, first, the diffuser channel DC2 expands small, then expands large, and then expands small. Therefore, when the gas G passes through the first final stationary blade row 10A and the second final stationary blade row 10B, that is, when the gas G passes through the first region A1, the amount of deceleration of the gas G by the diffuser channel DC can be reduced. . For this reason, it is possible to suppress the separation of the gas G in the first final stationary blade row 10A and the second final stationary blade row 10B.

  Thereafter, when the gas G passes through the second region A2, the amount of deceleration of the gas G can be increased by the diffuser channel DC2, and a sufficient pressure recovery amount can be obtained. Furthermore, although the boundary layer of the gas G is developed in the third region A3 on the most downstream side, since the amount of deceleration of the gas G can be reduced, the separation of the gas G can be suppressed. Therefore, pressure recovery can be effectively performed.

  Here, in the present embodiment, the diffuser channel DC2 may be divided into a first region A1 and a second region A2 on the downstream side of the first region A1. In this case, the amount of enlargement of the channel cross-sectional area may be smaller in the second region A2 than in the first region A1. In this case, by opening the diffuser flow channel DC2 from the first region A1, the first region is suppressed while preventing the gas G from being separated on the inner surface (end wall) in the diffuser flow channel DC2 downstream from the first region A1. Even if the amount of deceleration is increased at A1 and then the boundary layer develops in the second region A2, the gas G can be decelerated without separation.

Although the embodiment of the present invention has been described in detail above, some design changes can be made without departing from the technical idea of the present invention.
For example, in the diffuser section 4 (34, 54), the inner surface on the radially outer side of the axis O in the diffuser channel DC (DC1, DC2), that is, the inner surface of the outer cylinder 4b is inclined radially outward toward the downstream side. Thus, the flow path cross-sectional area may be enlarged. Here, since the gas G flows into the diffuser flow channel DC in a state having a component in the rotation direction R of the rotating shaft 2, the diffuser flow in a state where the gas G approaches the radially outer inner surface side of the diffuser flow channel DC. It will circulate through the road DC.

  Therefore, the diffuser channel DC is formed along the flow direction of the gas G by increasing the channel cross-sectional area of the diffuser channel DC so as to incline radially outward. For this reason, the gas G can be more smoothly circulated in the diffuser channel DC, and the effect of pressure recovery can be improved.

  Further, in the diffuser part 4 (34, 54), the inner surface in the radial direction of the axis O in the diffuser flow channel DC (DC1, DC2), that is, the inner surface of the inner cylinder 4a is inclined radially inward toward the downstream side. Thus, the flow path cross-sectional area may be enlarged. Thus, in the diffuser flow channel DC, the radially inner surface and the radially inner surface are inclined radially inward toward the downstream side, and the flow channel C expands radially on both sides, so that the distance is shorter. Pressure recovery. Therefore, the length of the diffuser channel DC in the direction of the axis O can be shortened, and the friction loss of the gas G in the diffuser channel DC can be reduced.

  Further, in the diffuser portion 4 (34, 54), the inner surface on the radially inner side of the axis O in the diffuser flow channel DC (DC1, DC2), that is, the outer surface of the inner cylinder 4a is inclined radially outward toward the downstream side. Thus, the flow path cross-sectional area may be enlarged. As described above, in the diffuser flow channel DC, the radially inner surface and the radially inner surface are inclined radially outward toward the downstream side, so that the gas G compressed into the device disposed radially outward is supplied. Can lead.

  For example, when the axial flow compressor 1 (31, 51) is applied to a gas turbine, the gas G is smoothly guided to the combustor disposed on the radially outer side of the diffuser portion 4 (34, 54). Is possible.

  Further, the diffuser channel DC may be formed so as to start from a position including the final moving blade row 20A, that is, an end portion on the upstream side of the final moving blade stage 20A.

  In the above-described embodiment, the axial flow compressor 1 (31, 51) has been described as an example of the axial flow rotary machine. However, another shaft such as an axial flow pump that pumps liquid instead of the gas G is described. The configuration of the above-described embodiment can be applied to a flow rotating machine.

  According to the above moving blades and the axial flow rotating machine, the flow angle of the blades of the moving blades is different in the direction of the blade height, so that the flow loss of the fluid in the diffuser can be reduced, and sufficient pressure recovery performance It is possible to obtain

DESCRIPTION OF SYMBOLS 1, 31, 51 ... Axial compressor (Axial rotary machine) 2 ... Rotary shaft 3 ... Casing 3a ... Suction port 4, 34, 54 ... Diffuser part 4a ... Inner cylinder 4b ... Outer cylinder 10 ... Stator blade row 10A , 40A ... first final stationary blade row 10B ... second final stationary blade row 11 ... outlet guide vane 12 ... stationary blade 13 ... blade portion 14, 44 ... outer shroud 15 ... inner shroud 20 ... moving blade row 20A ... final moving blade Row 22 ... Rotor blade 22a ... Negative pressure surface 22b ... Pressure surface 23 ... Platform 24 ... Blade root 25 ... Blade portion S ... Space G ... Gas O ... Axis DC, DC1, DC2 ... Diffuser flow path C ... Flow path A1 ... First Area A2 ... Second area A3 ... Third area

Claims (10)

A rotating shaft that extends in the direction of the axis and rotates about the axis; a casing that supports the rotating shaft from the outer peripheral side so as to be relatively rotatable and defines a fluid flow path between the rotating shaft; and A diffuser portion that is provided on the downstream side of the casing, communicates with the flow path, forms an annular shape centered on the axis, and defines a diffuser flow path that has a cross-sectional area that increases toward the downstream side; and A stationary blade row protruding inward in the radial direction of the axis from the casing and provided in a plurality of rows in the direction of the axis, and compression of the fluid provided in a plurality of rows adjacent to the stationary blade row in the direction of the axis Or provided in an axial-flow rotating machine including a moving blade row that performs pumping,
The final blade row that is located on the most downstream side of the flow of the fluid in the blade row, and a plurality of blades that are arranged at intervals in the circumferential direction of the axis ,
In order to compress the fluid to a higher pressure on the hub side and tip side than in the center portion in the blade height direction, the fluid flow direction at the blade portion outlet of each blade is set to the hub side and tip relative to the center portion. to vary the side, Ru with the wings is larger at the hub side and the tip side turning angle than the central portion of the blade height direction at each rotor blade rotor blade. A moving blade row having the moving blade according to claim 1;
  A rotating shaft that fixes the blade row, extends in the direction of the axis, and rotates about the axis;
  A casing that supports the rotation shaft from the outer peripheral side so as to be relatively rotatable, and defines a fluid flow path between the rotation shaft and
  A diffuser portion that is provided on the downstream side of the casing, communicates with the flow path, forms a ring centered on the axis, and defines a diffuser flow path that has a cross-sectional area that increases toward the downstream side; and
  A plurality of rows that protrude radially inward of the axis from the casing, are provided adjacent to the blade row in the direction of the axis, and are spaced apart from each other in the circumferential direction of the axis for each row. A stationary blade row having wings;
  An axial-flow rotating machine comprising: The diffuser portion is downstream of the upstream end portion of the final moving blade row, and more downstream than the downstream end portion of the final stationary blade row provided downstream of the final moving blade row. The axial flow rotary machine according to claim 2, wherein the casing is provided in the casing so that the diffuser flow path extends from an upstream side. The axial flow rotating machine according to claim 2 , wherein a part of the inner surface of the diffuser flow path is formed by a part of the stationary blade in the final stationary blade row in the diffuser portion. In the diffuser portion, the diffuser flow path includes a first region corresponding to a region in the axial direction in which the final stationary blade row is provided, a second region downstream of the first region, and the first region. Divided into a third region further downstream than the two regions,
Wherein the first region towards the second region than increases the expansion volume of the flow path cross-sectional area, the amount of increase is the channel cross-sectional area towards the second region the third region than smaller claim 2 To an axial-flow rotating machine according to any one of claims 1 to 4 . In the diffuser portion, the diffuser flow path is divided into a first region corresponding to a region in the direction of the axis where the final stationary blade row is provided, and a second region downstream of the first region. ,
The axial flow rotary machine according to any one of claims 2 to 4 , wherein the second region has a smaller amount of expansion of the flow path cross-sectional area than the first region. In the diffuser portion, any one of claims 2 to 6, the radially outer side of the inner surface of the axis of the diffuser flow path is enlarged flow path cross-sectional area to be inclined to the radially outward toward the downstream side An axial flow rotating machine as described in 1. The axial flow rotating machine according to claim 7 , wherein in the diffuser portion, the flow path cross-sectional area is increased so that the radially inner surface of the diffuser flow path is radially inwardly inclined toward the downstream side. . 8. The axial flow rotation according to claim 7 , wherein in the diffuser portion, the cross-sectional area of the flow path expands so that the inner surface of the diffuser flow path on the inner side in the radial direction of the axis inclines toward the downstream side in the radial direction. machine.   A rotating shaft that extends in the direction of the axis and rotates about the axis; a casing that supports the rotating shaft from the outer peripheral side so as to be relatively rotatable and defines a fluid flow path between the rotating shaft; and A diffuser portion that is provided on the downstream side of the casing, communicates with the flow path, forms an annular shape centered on the axis, and defines a diffuser flow path that has a cross-sectional area that increases toward the downstream side; and A stationary blade row protruding inward in the radial direction of the axis from the casing and provided in a plurality of rows in the direction of the axis, and compression of the fluid provided in a plurality of rows adjacent to the stationary blade row in the direction of the axis Or provided in an axial-flow rotating machine including a moving blade row that performs pumping,
  Among the blade rows, a final blade row located on the most downstream side of the fluid flow is constituted, and a plurality of blade blades are arranged at intervals in the circumferential direction of the axis, and each turning angle is a blade height. A moving blade row having a moving blade with a blade portion that is larger on the hub side and the tip side than the central portion of the direction;
  The rotating blade row is fixed, extends in the direction of the axis, rotates around the axis, and supports the rotation axis from the outer peripheral side so as to be relatively rotatable, and a fluid flow path between the rotation axis A casing that defines
  A diffuser portion that is provided on the downstream side of the casing, communicates with the flow path, forms a ring centered on the axis, and defines a diffuser flow path that has a cross-sectional area that increases toward the downstream side; and
  A plurality of rows that protrude radially inward of the axis from the casing, are provided adjacent to the blade row in the direction of the axis, and are spaced apart from each other in the circumferential direction of the axis for each row. A stationary blade row having wings;
  With
  The diffuser portion is downstream of the upstream end portion of the final moving blade row, and more downstream than the downstream end portion of the final stationary blade row provided downstream of the final moving blade row. It is provided in the casing so that the diffuser flow path extends from the upstream side,
  The final stator blade row includes a first final stator blade row and a second final stator blade row adjacent to the upstream side of the first final stator blade row, from the downstream end of the second final stator blade row. An axial flow rotary machine in which the diffuser flow path extends from the upstream side.

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