CN117569876A - Turbine straight blade grid type pre-rotation nozzle structure - Google Patents
Turbine straight blade grid type pre-rotation nozzle structure Download PDFInfo
- Publication number
- CN117569876A CN117569876A CN202311463121.5A CN202311463121A CN117569876A CN 117569876 A CN117569876 A CN 117569876A CN 202311463121 A CN202311463121 A CN 202311463121A CN 117569876 A CN117569876 A CN 117569876A
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- Prior art keywords
- nozzle
- ring
- straight blade
- inlet
- turbine
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- 238000001816 cooling Methods 0.000 claims description 15
- 238000007789 sealing Methods 0.000 claims description 5
- 238000003466 welding Methods 0.000 claims description 3
- 238000003754 machining Methods 0.000 claims description 2
- 238000009987 spinning Methods 0.000 abstract description 17
- 239000013585 weight reducing agent Substances 0.000 abstract description 5
- 230000001133 acceleration Effects 0.000 description 4
- 230000008602 contraction Effects 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- 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
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
-
- 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
- F01D9/047—Nozzle boxes
Abstract
The application provides a turbine straight blade cascade type pre-rotation nozzle structure, this pre-rotation nozzle structure includes: a nozzle inner ring, a nozzle outer ring and a straight blade grid; the inner ring and the outer ring of the nozzle are respectively fixed on the inner ring and the outer ring of the casing or the mounting seat, the inner wall surface of the inlet of the inner ring of the nozzle forms an inlet inner runner of the pre-spinning nozzle, and the inner wall surface of the inlet of the outer ring of the nozzle forms an inlet outer runner of the pre-spinning nozzle; the straight blade grids are arranged between the inner nozzle ring and the outer nozzle ring, are fixed on the inner nozzle ring in a row in the circumferential direction, and leave a gap between the straight blade grids and the outer nozzle ring. Compared with the prerotation nozzle in the prior art, the prerotation nozzle structure formed by the inner ring and the outer ring of the nozzle and the row of straight blade grids can lighten the weight of the prerotation nozzle to a certain extent, and the weight reduction design of the turbine part of the engine is realized.
Description
Technical Field
The application belongs to the field of aeroengines, and particularly relates to a turbine straight blade grid type pre-rotation nozzle structure.
Background
The main purpose of the turbine pre-spinning nozzle of the aeroengine is to accelerate air flow in a pre-spinning nozzle channel, form air flow with certain speed, pressure, angle and rotational flow ratio at an outlet, enter the inner cavity of a blade along a disk tenon structure, and achieve the purpose of cooling the turbine working blade.
With the development of aeroengines to high thrust-weight ratio, the required turbine front temperature is higher and higher, even reaches 2000K-2200K, the ultra-high temperature exceeds the bearing capacity of the blades, the pre-spinning nozzle is used as a structure for providing cooling air for the working blades, the difference of the outlet cold air characteristics of different pre-spinning nozzle structures is large, and the cold air condition entering the inner cavity of the turbine working blades is directly determined by the pre-spinning nozzle structure, so that the cooling effect of the working blades is greatly influenced.
Currently, most pre-swirl nozzles are of straight circular hole type (shown in fig. 1) or inclined hole type (shown in fig. 2).
For the straight round hole type nozzle formed by opening a plurality of straight round hole structures with the same size on the annular plate, the inlet of the nozzle is greatly deflected by airflow, the flow loss is large, the acceleration of the airflow in a channel is poor, the rotational flow of an outlet is low, the cooling effect of the nozzle on the working blade is not ideal, the structural weight of the nozzle is large, and the design of reducing the weight of an engine turbine is not facilitated.
As for the inclined hole type pre-rotation nozzle with an inlet adopting an expanded inclined hole and a contracted inclined hole structure, although partial flow loss is reduced compared with a straight round hole type, the airflow has great airflow deflection and flow resistance at the inlet of the nozzle, has great flow loss in a hole type channel with poor acceleration, has lower rotational flow of an outlet, is poor in mixing with rotating fluid, and is not beneficial to cooling of the working blades by cold air.
Disclosure of Invention
It is an object of the present application to provide a turbine cascade-type pre-rotation nozzle structure to solve or alleviate at least one of the problems of the background art.
The technical scheme of the application is as follows: a turbine cascade pre-rotation nozzle structure comprising: a nozzle inner ring, a nozzle outer ring and a straight blade grid;
the inner ring and the outer ring of the nozzle are respectively fixed on the inner ring and the outer ring of the casing or the mounting seat, the inner wall surface of the inlet of the inner ring of the nozzle forms an inlet inner runner of the pre-spinning nozzle, and the inner wall surface of the inlet of the outer ring of the nozzle forms an inlet outer runner of the pre-spinning nozzle;
the straight blade grids are arranged between the inner nozzle ring and the outer nozzle ring, are fixed on the inner nozzle ring in a row in the circumferential direction, and leave a gap between the straight blade grids and the outer nozzle ring.
In the preferred embodiment of the present application, the nozzle inner ring and the nozzle outer ring are fixedly connected with the inner ring and the outer ring of the casing or the mounting seat through connecting pieces.
In a preferred embodiment of the present application, the inner wall surface at the inlet of the inner ring of the nozzle is in a tapered structure, and the inner wall surface at the inlet of the outer ring of the nozzle is in a flat section structure, so that the inner inlet runner and the outer inlet runner form a tapered inlet channel structure of the pre-rotation nozzle.
In a preferred embodiment of the present application, the straight blade cascade is fixed to the nozzle inner ring by means of welding.
In the preferred embodiment of the present application, the straight blade cascade and the nozzle inner ring are obtained by adopting an integral machining mode.
In the preferred embodiment of the application, the straight blade cascade type pre-rotation nozzle is provided with a radial channel at the front end position matched with the straight blade cascade, and the radial channel penetrates through the inner nozzle ring, the straight blade cascade and the outer nozzle ring, so that another channel for cooling or sealing other structures of the turbine to circulate is formed.
In the preferred embodiment of the present application, the center coordinates and the radius of the front and rear edges of the straight blade cascade and the coordinates of the tangent points of the front and rear edges and the molded lines are as follows:
in a preferred embodiment of the present application, the profile coordinates of the straight blade cascade (13) are as follows:
compared with the prerotation nozzle in the prior art, the turbine straight blade cascade prerotation nozzle structure provided by the application has the following advantages:
1) The weight of the pre-spinning nozzle can be reduced to a certain extent by adopting a pre-spinning nozzle structure formed by the inner ring, the outer ring and a row of straight blade grids of the nozzle, so that the weight reduction design of the turbine part of the engine is realized;
2) The contraction channel formed by the air inlet inner flow channel and the air inlet outer flow channel can accelerate the cold air in the contraction channel of the inlet of the pre-spinning nozzle, accelerate the cold air again in the blade grid channel, improve the acceleration of the cold air in the nozzle, greatly reduce the flow loss of the cold air through the rectification function and good aerodynamic characteristics of the straight blade grid, improve the swirl ratio of the outlet cold air, greatly improve the aerodynamic performance of the pre-spinning nozzle, realize the good flow of the air flow in the nozzle, and provide higher-quality cooling air for the turbine working blades;
3) Through the front end of the straight blade grid of the pre-rotation nozzle is provided with a hole, other cold air can be supplied to other structures of the turbine for cooling or sealing through the inner cavities of the blades, the design of a cold air flow path is simplified, and the weight reduction design of the turbine can be further realized.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following description will briefly refer to the accompanying drawings. It will be apparent that the figures described below are only some embodiments of the present application.
Fig. 1 is a schematic view of a straight round hole type pre-rotation nozzle in the prior art.
FIG. 2 is a schematic diagram of a prior art inclined hole type pre-rotation nozzle.
Fig. 3 is a schematic view of a straight vane cascade type pre-rotation nozzle structure of the present application.
Fig. 4 is a schematic view of a straight blade cascade structure of the present application.
Detailed Description
In order to make the purposes, technical solutions and advantages of the implementation of the present application more clear, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application.
In order to improve the aerodynamic performance of the pre-rotation nozzle and reduce the structural weight of a turbine assembly, the application provides a turbine straight blade cascade type pre-rotation nozzle structure.
As shown in fig. 3, the turbine straight blade cascade type pre-rotation nozzle structure 10 provided in the present application includes: a nozzle inner ring 11, a nozzle outer ring 12 and a straight cascade 13.
The inner nozzle ring 11 is fixed on the inner ring of the casing or the mounting seat through a bolt connecting piece, and an inner wall surface of an inlet of the inner nozzle ring 11 forms an inlet inner runner 141 of the pre-rotation nozzle. The nozzle outer ring 12 is fixed on the casing or the mounting seat outer ring through a bolt connecting piece, and the inner wall surface of the inlet of the nozzle outer ring 12 forms a pre-rotation nozzle inlet outer runner 121.
In the preferred embodiment of the present application, the inner wall surface of the inlet of the inner nozzle ring 11 is in a tapered structure, and the inner wall surface of the inlet of the outer nozzle ring 12 is in a flat section structure, so that the inlet inner flow passage 141 and the inlet outer flow passage 121 can form a tapered inlet passage structure of the pre-rotation nozzle, which is beneficial to realizing the accelerated flow of the cold air and reducing the flow loss before entering the cascade passage.
The straight blade cascades 13 are provided between the nozzle inner ring 11 and the nozzle outer ring 12, and the number of the straight blade cascades 13 is set to 60 to 80, preferably about 70, in the circumferential direction. The straight cascades 13 are fixed to the nozzle inner ring 11 in a row. In some embodiments of the present application, the straight blade cascade 13 may be fixed to the nozzle inner ring 11 by welding, or the straight blade cascade 13 and the nozzle inner ring 11 may be integrally machined.
A certain gap is reserved between the straight blade grid 13 and the nozzle outer ring 12, the gap can be set to be about 0.1 mm-1 mm, and when the turbine runs in a hot state, the contact extrusion of the straight blade grid 13 and the nozzle outer ring 12 can be realized after the pre-rotation nozzle expands due to heating, so that the tip leakage loss is prevented.
The straight blade grid 13 in the pre-rotation nozzle has good rectifying effect and pneumatic performance, the flow of the nozzle can be accurately controlled through the width of the throat part, and the required outlet airflow angle can be accurately realized through the geometric angle of the blade outlet. The center coordinates of the front and rear edges of the straight blade grating of the pre-rotation nozzle, the radius and the coordinates of the tangent points of the front and rear edges and the molded lines are shown in the table 1, and the molded surface coordinates of the straight blade grating are shown in the table 2.
TABLE 1 center coordinates of front and rear edges of straight blade cascade, radius and coordinates of tangent points of front and rear edges and molded lines
| Parameter symbol | Parameter name | Straight blade grid base section of pre-rotation nozzle |
| C max | Maximum thickness (mm) | 3.5404 |
| b | Chord length (mm) | 28.6461 |
| X q | X coordinate of center of front edge (mm) | -13.5649 |
| Y q | Y coordinate of center of front edge (mm) | 23.5718 |
| r q | Radius of center of front edge (mm) | 1.2178 |
| X h | X coordinate of center of tail margin (mm) | 0.0005 |
| Y h | Y coordinate of center of tail margin (mm) | 0.0016 |
| r h | Radius of center of tail edge (mm) | 0.2500 |
| X qp | X coordinate (mm) of tangent point of leading edge and leaf basin molded line | -14.1344 |
| Y qp | Y coordinate (mm) of tangent point of leading edge and leaf basin molded line | 22.4953 |
| X qb | X coordinate (mm) of tangent point of front edge and blade back profile | -14.1531 |
| Y qb | Y coordinate (mm) of tangent point of front edge and back profile | 24.6381 |
| X hp | X coordinate (mm) of tangential point of tail edge and leaf basin molded line | -0.2351 |
| Y hp | Y coordinate (mm) of tangential point of tail edge and leaf basin molded line | -0.0850 |
| X hb | X coordinate (mm) of tangential point of tail edge and blade back profile | 0.2398 |
| Y hb | Y coordinate (mm) of tangential point of tail edge and blade back profile | 0.0705 |
TABLE 2 coordinates of straight blade grid profile of pre-rotation nozzle
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As shown in fig. 4, the straight-blade cascade pre-rotation nozzle is provided with a radial channel 14 at the front end position of the straight-blade cascade pre-rotation nozzle, which is adapted to the straight-blade cascade 13, and the radial channel 14 passes through the nozzle inner ring 11, the straight-blade cascade 13 and the nozzle outer ring 12, so that another channel for cooling or sealing other structures of the turbine to circulate is formed, the design of other cooling flow paths can be reduced, and the weight of the turbine is further reduced.
In use, cooling air flows from the inlet of the pre-rotation nozzle into the convergent inlet channel formed by the inlet inner runner 131 and the inlet outer runner 121, passes through the straight blade cascade 13 and then flows out of the pre-rotation nozzle. The straight blade grid type pre-rotation nozzle structure can greatly improve the outlet cold air swirl ratio, better control the flow characteristic of air flow at the nozzle, improve the pneumatic performance of the pre-rotation nozzle and provide higher-quality cooling air for the working blade.
Compared with the prerotation nozzle in the prior art, the turbine straight blade cascade prerotation nozzle structure provided by the application has the following advantages:
(1) The weight of the pre-spinning nozzle can be reduced to a certain extent by adopting a pre-spinning nozzle structure formed by the inner ring, the outer ring and a row of straight blade grids of the nozzle, so that the weight reduction design of the turbine part of the engine is realized;
(2) The contraction channel formed by the air inlet inner flow channel and the air inlet outer flow channel can accelerate the cold air in the contraction channel of the inlet of the pre-spinning nozzle, accelerate the cold air again in the blade grid channel, improve the acceleration of the cold air in the nozzle, greatly reduce the flow loss of the cold air through the rectification function and good aerodynamic characteristics of the straight blade grid, improve the swirl ratio of the outlet cold air, greatly improve the aerodynamic performance of the pre-spinning nozzle, realize the good flow of the air flow in the nozzle, and provide higher-quality cooling air for the turbine working blades;
(3) Through the front end of the straight blade grid of the pre-rotation nozzle is provided with a hole, other cold air can be supplied to other structures of the turbine for cooling or sealing through the inner cavities of the blades, the design of a cold air flow path is simplified, and the weight reduction design of the turbine can be further realized.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (8)
1. A turbine cascade pre-rotation nozzle structure, comprising: a nozzle inner ring (11), a nozzle outer ring (12) and a straight blade grid (13);
the inner ring (11) and the outer ring (12) of the nozzle are respectively fixed on the inner ring and the outer ring of the casing or the mounting seat, an inlet inner flow passage (141) of the pre-rotation nozzle is formed on the inner wall surface of the inlet of the inner ring (11), and an inlet outer flow passage (121) of the pre-rotation nozzle is formed on the inner wall surface of the inlet of the outer ring (12);
the straight blade grids (13) are arranged between the inner nozzle ring (11) and the outer nozzle ring (12), are circumferentially fixed on the inner nozzle ring (11) in a row, and leave a gap between the straight blade grids (13) and the outer nozzle ring (12).
2. The turbine straight blade cascade type pre-rotation nozzle structure as claimed in claim 1, wherein the nozzle inner ring (11) and the nozzle outer ring (12) are fixedly connected with the inner ring and the outer ring of the casing or the mounting seat through connecting pieces.
3. Turbine straight blade cascade type pre-rotation nozzle structure according to claim 1, characterized in that the inner wall surface of the inlet of the nozzle inner ring (11) is of a tapered structure, and the inner wall surface of the inlet of the nozzle outer ring (12) is of a straight section structure, so that the inlet inner runner (141) and the inlet outer runner (121) form a tapered inlet channel structure of the pre-rotation nozzle.
4. Turbine straight blade cascade type pre-rotation nozzle structure according to claim 1, characterized in that the straight blade cascade (13) is fixed to the nozzle inner ring (11) by means of welding.
5. Turbine straight blade cascade type pre-rotation nozzle structure according to claim 1, characterized in that the straight blade cascade (13) and the nozzle inner ring (11) are obtained by means of integral machining.
6. Turbine cascade pre-rotation nozzle structure according to claim 1, characterized in that the cascade pre-rotation nozzle is provided with radial channels (14) at the front end position adapted to the cascade (13), said radial channels (14) passing through the inner nozzle ring (11), the cascade (13) and the outer nozzle ring (12) so as to form a further cold air flow channel for cooling or sealing other structures of the turbine.
7. Turbine straight blade cascade type pre-rotation nozzle structure according to claim 1, characterized in that the center coordinates and radius of the front and rear edges and the line tangent point coordinates of the front and rear edges of the straight blade cascade (13) are as follows:
8. Turbine cascade pre-rotation nozzle structure according to claim 7, characterized in that the profile coordinates of the cascade (13) are as follows:
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311463121.5A CN117569876A (en) | 2023-11-06 | 2023-11-06 | Turbine straight blade grid type pre-rotation nozzle structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311463121.5A CN117569876A (en) | 2023-11-06 | 2023-11-06 | Turbine straight blade grid type pre-rotation nozzle structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117569876A true CN117569876A (en) | 2024-02-20 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311463121.5A Pending CN117569876A (en) | 2023-11-06 | 2023-11-06 | Turbine straight blade grid type pre-rotation nozzle structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117569876A (en) |
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2023
- 2023-11-06 CN CN202311463121.5A patent/CN117569876A/en active Pending
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