CN210289846U - Shrouded cooling turbine rotor blade leading edge cooling structure - Google Patents
Shrouded cooling turbine rotor blade leading edge cooling structure Download PDFInfo
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- CN210289846U CN210289846U CN201921181682.5U CN201921181682U CN210289846U CN 210289846 U CN210289846 U CN 210289846U CN 201921181682 U CN201921181682 U CN 201921181682U CN 210289846 U CN210289846 U CN 210289846U
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Abstract
The application belongs to the technical field of aeroengine turbine rotor blades, and particularly relates to a shrouded cooling structure for a leading edge of a cold turbine rotor blade. The method comprises the following steps: a blade and a leading edge cooling portion. The blade is provided with a blade shroud, a dust removal hole is formed in the blade shroud, a cooling channel is arranged on the front edge of the blade, one end of the cooling channel is communicated with the tenon, and the other end of the cooling channel is communicated with the dust removal hole of the blade shroud; the front edge cooling part is arranged at the front edge of the blade and comprises a first side wall and a second side wall, an impact cavity is arranged between the first side wall and the second side wall, an impact hole is formed in the first side wall and communicated with the cooling channel and the impact cavity, an air film hole is formed in the second side wall and communicated with the impact cavity and the outer portion of the blade. This application has improved blade cooling efficiency, and the blade temperature is more even, reduces thermal stress, improves intensity deposit and life.
Description
Technical Field
The application belongs to the technical field of aeroengine turbine rotor blades, and particularly relates to a shrouded cooling structure for a leading edge of a cold turbine rotor blade.
Background
With the increasing thrust demand of engines, the requirements on the performance of a turbine and the temperature in front of the turbine are gradually improved, and the turbine rotor blades operate at high speed in a high-temperature and high-pressure gas environment, so that the working environment is very severe. In order to improve the efficiency of the turbine, a high aspect ratio turbine rotor blade is often designed to be provided with a crown structure, so that the leakage of gas along the blade tip is reduced, and the rigidity and the high-cycle fatigue resistance of the blade are improved. For a new generation of engine, the temperature of the turbine inlet is greatly increased, and complex cooling measures are required to reduce the temperature of the blades so as to ensure the safe and reliable operation of the blades.
At present, the leading edge of the shrouded turbine rotor blade generally adopts a convection cooling mode, and a cooling channel is divided into a smooth channel or a channel with a rib and other forced convection cooling structures. The cooling mode cannot meet the requirement of the working environment of a new generation of engine with high turbine front temperature, the cooling effect is low, and the front edge of the blade can be ablated.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
It is an object of the present application to provide a shrouded cold turbine rotor blade leading edge cooling arrangement to address at least one problem of the prior art.
The technical scheme of the application is as follows:
a shrouded cold turbine rotor blade leading edge cooling structure comprising:
the blade is provided with a blade shroud, a dust removal hole is formed in the blade shroud, a cooling channel is arranged on the front edge of the blade, one end of the cooling channel is communicated with the tenon, and the other end of the cooling channel is communicated with the dust removal hole of the blade shroud;
the front edge cooling part is arranged at the front edge of the blade and comprises a first side wall and a second side wall, an impact cavity is arranged between the first side wall and the second side wall, an impact hole is formed in the first side wall and communicated with the cooling channel and the impact cavity, a film hole is formed in the second side wall and communicated with the impact cavity and the outer portion of the blade.
Optionally, the leading edge cooling portion is integrally formed with the blade.
Optionally, the shroud has a tip.
Optionally, a plurality of impact holes are formed in the first side wall along the height direction of the blade.
Optionally, a plurality of air film holes are formed in the second side wall along the height direction of the blade.
Optionally, four air film holes are formed in the second side wall along the same height direction of the blade.
Optionally, the axis of the film hole forms an angle with the second sidewall.
Optionally, included angles formed by the axes of the four air film holes arranged in the same height direction of the blade and the second side wall are all different.
Optionally, the impingement holes on the first sidewall and the film holes on the second sidewall proximate the tip shroud are each a predetermined distance from the tip shroud.
Utility model has the following beneficial technical effects:
the utility model provides a take the hat to have cold turbine rotor blade leading edge cooling structure, improved blade cooling efficiency, blade temperature is more even, can effectively reduce blade leading edge and leaf basin, the leaf back side difference in temperature, reduces thermal stress, improves intensity deposit and life.
Drawings
FIG. 1 is a schematic overall view of a shrouded cold turbine rotor blade leading edge cooling configuration according to an embodiment of the present application;
FIG. 2 is a schematic view of a leading edge of a shrouded cold turbine rotor blade leading edge cooling structure according to an embodiment of the present application;
FIG. 3 is a sectional view of a leading edge of a shrouded cold turbine rotor blade leading edge cooling structure according to an embodiment of the present application.
Wherein:
1-leaf tip cap; 2-a cooling channel; 3-an impact chamber; 4-impact holes; 5-air film hole; 6-dust removal hole.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The present application is described in further detail below with reference to fig. 1 to 3.
The application provides a shrouded cold turbine rotor blade leading edge cooling structure, includes: the cooling structure comprises a blade and a front edge cooling part arranged on the front edge of the blade.
Specifically, the blade is provided with a blade shroud 1, a dust removal hole 6 is formed in the blade shroud 1, a cooling channel 2 is arranged on the front edge of the blade, one end of the cooling channel 2 is communicated with the tenon, and the other end of the cooling channel 2 is communicated with the dust removal hole 6 of the blade shroud 1; the leading edge cooling part is arranged at the leading edge of the blade and comprises a first side wall and a second side wall, an impact cavity 3 is arranged between the first side wall and the second side wall, an impact hole 4 is formed in the first side wall, the impact hole 4 is communicated with the cooling channel 2 and the impact cavity 3, a gas film hole 5 is formed in the second side wall, and the gas film hole 5 is communicated with the impact cavity 3 and the blade. The shroud has cold turbine rotor blade leading edge cooling structure of this application, and cooling gas gets into cooling channel 2 from the tenon of blade, and partly cooling gas gets into impact chamber 3 by impingement hole 4, discharges through gas film hole 5 afterwards, and another part cooling gas is by dust removal hole 6 discharge shroud 1.
In one embodiment of the present application, the leading edge cooling portion is integrally formed with the blade.
In one embodiment of the present application, the shroud 1 has a blade tip.
In one embodiment of the present application, a plurality of impingement holes 4 are formed in the first sidewall of the leading edge cooling portion in the height direction of the blade. And a plurality of air film holes 5 are formed in the second side wall along the height direction of the blade. The second side wall may be provided with a plurality of film holes 5 along the same height direction of the blade. In this embodiment, four air film holes 5 are formed in the second sidewall along the same height direction of the blade. The axis of the film hole 5 forms an included angle with the second side wall. It can be understood that the axes of the four air film holes 5 opened in the same height direction of the blade form different included angles with the second side wall. It will be appreciated that the impingement holes 4 on the first sidewall and the film holes 5 on the second sidewall near one side of the tip shroud 1 are each at a predetermined distance from the tip shroud 1 that avoids the cooling flow path at the tip shroud 1 from interfering with the cooling flow path of the leading edge cooling section.
The utility model provides a take hat there is cold turbine rotor blade leading edge cooling structure, cooling gas is with higher speed when the shock hole 4 on the first lateral wall through leading edge cooling portion, the internal face that strikes the second lateral wall is stagnant, the gyration, form the impingement cooling district, the heat transfer in the reinforcing impact cavity 3, later by the 5 discharge blade leading edges in the gas film hole on the second lateral wall, it covers with wall with the gas isolation to form the gas film at the second lateral wall outer wall, and take away partial gas heat, thereby carry out thermal protection to the wall. The cooling gas passes through the dust removing holes 6 and then is mixed with other gas flows to cool the surface of the blade shroud 1.
Compared with the existing shrouded cold turbine rotor blade, the shrouded cold turbine rotor blade front edge cooling structure has the advantages that the temperature of the front edge of the blade is effectively reduced by over 100 ℃ under the same cooling gas supply condition, and the blade cooling efficiency is improved; compared with the existing structure, the structure has the advantages that the temperature of the blade is more uniform, the temperature difference between the front edge of the blade and the back side of the blade can be effectively reduced, the thermal stress is reduced, and the strength storage and the service life are improved. The structure is obvious in effect through calculation and analysis, and can be applied to a new generation of power low-pressure turbine blade.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within 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 (9)
1. A shrouded cold turbine rotor blade leading edge cooling structure comprising:
the blade is provided with a blade shroud (1), a dust removal hole (6) is formed in the blade shroud (1), a cooling channel (2) is arranged at the front edge of the blade, one end of the cooling channel (2) is communicated with the tenon, and the other end of the cooling channel is communicated with the dust removal hole (6) of the blade shroud (1);
the front edge cooling part is arranged at the front edge of the blade and comprises a first side wall and a second side wall, an impact cavity (3) is arranged between the first side wall and the second side wall, an impact hole (4) is formed in the first side wall, the impact hole (4) is communicated with the cooling channel (2) and the impact cavity (3), an air film hole (5) is formed in the second side wall, and the air film hole (5) is communicated with the impact cavity (3) and the outer portion of the blade.
2. The shrouded cold turbine rotor blade leading edge cooling structure of claim 1 wherein said leading edge cooling portion is integrally formed with said blade.
3. The shrouded cold turbine rotor blade leading edge cooling structure according to claim 1, wherein the shroud (1) has a blade tip.
4. The shrouded cold turbine rotor blade leading edge cooling structure of claim 1 wherein said first sidewall has a plurality of impingement holes (4) formed therein along the height of said blade.
5. The structure of claim 4, wherein the second sidewall has a plurality of film holes (5) formed along the height direction of the blade.
6. The structure for cooling the leading edge of the shrouded cold turbine rotor blade of claim 5 wherein the second sidewall has four film holes (5) formed therein along the same height of the blade.
7. The shrouded cold turbine rotor blade leading edge cooling structure according to claim 6 wherein the axis of the film hole (5) forms an angle with the second sidewall.
8. The structure for cooling the leading edge of the shrouded cold turbine rotor blade of claim 7 wherein the axes of the four film holes (5) formed in the same height direction of the blade form different angles with the second side wall.
9. The shrouded cold turbine rotor blade leading edge cooling structure according to claim 8, wherein the impingement holes (4) on the first sidewall and the film holes (5) on the second sidewall close to the shroud (1) are each at a predetermined distance from the shroud (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921181682.5U CN210289846U (en) | 2019-07-25 | 2019-07-25 | Shrouded cooling turbine rotor blade leading edge cooling structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921181682.5U CN210289846U (en) | 2019-07-25 | 2019-07-25 | Shrouded cooling turbine rotor blade leading edge cooling structure |
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| Publication Number | Publication Date |
|---|---|
| CN210289846U true CN210289846U (en) | 2020-04-10 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201921181682.5U Active CN210289846U (en) | 2019-07-25 | 2019-07-25 | Shrouded cooling turbine rotor blade leading edge cooling structure |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111485956A (en) * | 2020-04-24 | 2020-08-04 | 中国航发湖南动力机械研究所 | Turbine guide cooling blade |
| CN112228161A (en) * | 2020-10-16 | 2021-01-15 | 中国航发沈阳发动机研究所 | Blade and turbine thereof |
-
2019
- 2019-07-25 CN CN201921181682.5U patent/CN210289846U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111485956A (en) * | 2020-04-24 | 2020-08-04 | 中国航发湖南动力机械研究所 | Turbine guide cooling blade |
| CN112228161A (en) * | 2020-10-16 | 2021-01-15 | 中国航发沈阳发动机研究所 | Blade and turbine thereof |
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