CN113638777B - Turbine outer ring clamp, cooling structure of turbine outer ring, turbine and engine - Google Patents
Turbine outer ring clamp, cooling structure of turbine outer ring, turbine and engine Download PDFInfo
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- CN113638777B CN113638777B CN202111059346.5A CN202111059346A CN113638777B CN 113638777 B CN113638777 B CN 113638777B CN 202111059346 A CN202111059346 A CN 202111059346A CN 113638777 B CN113638777 B CN 113638777B
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- Prior art keywords
- outer ring
- turbine outer
- turbine
- shaped piece
- cooling
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Classifications
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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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/14—Casings modified therefor
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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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/26—Double casings; Measures against temperature strain in casings
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a turbine outer ring clamp, a cooling structure of a turbine outer ring, a turbine and an engine, wherein the turbine outer ring clamp comprises a top circle and a fulcrum; the fulcrum is arranged below the top circle; the turbine outer ring clamp is of an annular structure with a notch; the top circle is used for bearing the impact cooling of the cooling gas and splitting the cooling gas; the fulcrum is a locating point and is used for supporting the turbine outer ring clamp. The cooling structure of the turbine outer ring comprises a casing, the turbine outer ring, a turbine outer ring clamp and a sealing piece. The turbine includes a cooling structure for the turbine outer ring. The engine includes a turbine. According to the invention, the local impact reinforcement cooling mode is converted into a uniform convection cooling mode by arranging the turbine outer ring clamp; after the turbine outer ring clamp is added, the turbine outer ring is more fastened; the turbine outer ring clamp is provided with two fulcrums, so that the installation is more stable; the turbine outer ring clamp has the characteristics of easy assembly, self-fixing and the like, and other assembly processes are not required to be added.
Description
Technical Field
The invention belongs to the technical field of engines, and particularly relates to a turbine outer ring clamp, a cooling structure of a turbine outer ring, a turbine and an engine.
Background
Because the turbine outer ring is contacted with hot gas, the temperature of the part flushed by the gas is higher, the service life and reliability of the part are affected, and particularly the outer ring of the first-stage rotor are affected. The existing solution is to guide cooling air flow to cool the outer ring of the turbine, and reduce the temperature. Two air flows are led from the combustion chamber/the turbine outer ring, enter the turbine outer ring cavity through small holes on the casing, impact cooling is carried out on the inner surface of the turbine outer ring, then the cooling air flows respectively flow into the main flow channel through gaps between the front end face and the rear end face of the adjacent turbine outer ring, and the effect of sealing fuel gas is achieved.
Firstly, cooling gas directly impacts the inner surface of the turbine outer ring, because the impact residence point has good heat exchange effect, the temperature of an impact area can be very low, and the other side of the turbine outer ring is very high in gas scouring temperature, so that the local temperature gradient of the turbine outer ring is large, and the thermal stress is large, therefore, the strength and the service life of the turbine outer ring are reduced, meanwhile, the large thermal stress can also cause local abnormal deformation of the turbine outer ring, the effective control of blade tip gaps is influenced, and even the problems of local scraping, coating dropping and the like are caused.
Secondly, the existing scheme is easy to loosen after the turbine outer ring is assembled due to machining tolerance, assembly and other reasons, blade tip gaps under the condition of cold and hot states are not easy to control, turbine performance can be affected, and after the engine runs for a long time, the engine is easy to fall off due to deformation of related parts and other reasons, so that running safety is compromised.
Chinese patent 201921224140.1 discloses a turbine casing reinforced cooling structure, which strengthens convection heat exchange into impact heat exchange by arranging an annular plate in a cooling cavity, strengthens the cooling of the upper surface of an outer ring, can effectively improve the cooling effect of the outer ring and the turbine casing, and reduces the working temperature of the outer ring and the turbine casing. The problems of large local temperature gradient and large thermal stress of the upper surface and the lower surface of the outer ring are not solved. Therefore, there is a need to develop a novel cooling structure for the turbine outer ring, which solves the above-mentioned problems.
Disclosure of Invention
In order to solve the problems, the invention discloses a turbine outer ring clamp which is applied to a turbine casing, wherein the turbine outer ring clamp comprises a top circle and a fulcrum;
the fulcrum is arranged below the top circle;
the turbine outer ring clamp is of an annular structure with a notch;
the top circle is used for bearing the impact cooling of the cooling gas and splitting the cooling gas;
the fulcrum is a locating point and is used for supporting the turbine outer ring clamp.
Furthermore, the section of the turbine outer ring clamp is W-shaped.
Still further, the device also comprises a small hole;
the small holes are arranged on two sides of the top circle;
and the small holes are used for enabling the cooling air in the outer ring cavity to flow more uniformly.
Further, the cross-sectional shape of the small hole is circular, elliptical or polygonal.
Further, the thickness of the turbine outer ring clamp is 0.6-1.5 mm.
Further, the radius of the top circle is 0.8-2 mm.
A cooling structure for an outer ring of a turbine, comprising: the device comprises a casing, a turbine outer ring, the turbine outer ring clamp and a sealing piece;
the plurality of turbine outer rings are hung on the casing; the turbine outer ring clamp is arranged outside a plurality of turbine outer rings; the sealing piece covers the gap between the adjacent turbine outer rings.
Further, the casing comprises a first groove, a second groove, a third groove, a through hole, a gas through hole and a boss;
a first groove which is downwards opened is formed in one end of the casing, a second groove which is rightwards opened is formed close to the first groove, and a through hole is formed in the casing right above the second groove; a plurality of gas through holes are uniformly formed in the circumferential direction of the casing, and the gas through holes are right opposite to the top circle of the turbine outer ring clamp; the first surface of the other end of the casing is provided with a boss, and a third groove is arranged below the boss.
Still further, the turbine outer ring includes: the device comprises an arc-shaped piece, a first L-shaped piece and a second L-shaped piece;
the section of the outer ring of the turbine is inverted pi;
the first L-shaped piece and the second L-shaped piece are matched with the arc-shaped piece, one side of the first L-shaped piece and one side of the second L-shaped piece are parallel to the arc-shaped piece, and the other side of the first L-shaped piece and the other side of the second L-shaped piece are perpendicular to the arc-shaped piece; the horizontal edge of the first L-shaped piece exceeds the vertical line of the end point of the arc-shaped piece, and the horizontal edge of the second L-shaped piece does not exceed the vertical line of the end point of the arc-shaped piece; the first L-shaped piece is lower than the second L-shaped piece in height.
A turbine comprises the cooling structure of the turbine outer ring.
An engine comprising the turbine described above.
Compared with the prior art, the invention has the beneficial effects that:
1) The W-shaped turbine outer ring clamp is arranged, so that a local impact strengthening cooling mode is converted into a uniform convection cooling mode, and the temperature gradient and the thermal stress of the turbine outer ring are greatly reduced;
2) After the W-shaped turbine outer ring clamp is added, the turbine outer ring is more fastened, and the control of blade tip clearance can be effectively ensured;
3) The W-shaped turbine outer ring clamp is provided with two fulcrums, so that the installation is more stable, and the front and rear stress of the turbine outer ring is more uniform;
4) The W-shaped turbine outer ring clamp has the characteristics of easy assembly, self-fixing and the like, and other assembly processes are not required to be added.
Additional features and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. The objectives and other advantages of the invention may be realized and attained by the structure particularly pointed out in the written description and claims hereof as well as the appended drawings.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions of the prior art, the following description will briefly explain the drawings used in the embodiments or the description of the prior art, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 illustrates a schematic structural view of a cooling structure of a turbine outer ring in accordance with an embodiment of the present invention;
FIG. 2 illustrates a schematic structural view of a cooling structure of a turbine outer ring without a turbine outer ring band installed in accordance with an embodiment of the present invention;
FIG. 3 illustrates a schematic view of a turbine outer ring band in accordance with an embodiment of the present invention;
FIG. 4 illustrates a cross-sectional view of a turbine outer ring clamp according to an embodiment of the invention;
fig. 5 shows a small hole structure of a turbine outer ring band according to an embodiment of the present invention.
Reference numerals: 1. a casing; 11. a first groove; 12. a second groove; 13. a third groove; 14. a through hole; 15. a gas through hole; 16. a boss; 2. a turbine outer ring; 21. an arc-shaped member; 22. a first L-shaped member; 23. a second L-shaped member; 3. a turbine outer ring clamp; 31. a top circle; 32. a fulcrum; 33. a small hole; 4. and (5) sealing the piece.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments of the present invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
Fig. 1 shows a schematic structural view of a cooling structure of a turbine outer ring according to an embodiment of the present invention. As shown in fig. 1, the cooling structure of the turbine outer ring according to the present invention includes: the turbine outer ring clamping hoop 3 is arranged on the turbine outer ring clamp 4;
a plurality of turbine outer rings 2 are hung on the casing 1; the turbine outer ring clamp 3 is arranged outside a plurality of the turbine outer rings 2; the sealing piece 4 covers the gap between the adjacent turbine outer rings 2.
The casing 1 comprises a first groove 11, a second groove 12, a third groove 13, a through hole 14, a gas through hole 15 and a boss 16;
one end of the casing 1 is provided with a first groove 11 which is opened downwards, a second groove 12 which is opened rightward is arranged close to the first groove 11, a through hole 14 is formed in the casing 1 right above the second groove 12, a plurality of gas through holes 15 are uniformly formed in the circumference of the casing 1, the gas through holes 15 are opposite to a top circle 31 of the turbine outer ring clamp 3, a boss 16 is arranged on the first surface of the other end of the casing 1, and a third groove 13 is arranged below the boss 16.
The section of the turbine outer ring 2 is inverted pi-shaped and comprises an arc-shaped piece 21, a first L-shaped piece 22 and a second L-shaped piece 23; the first L-shaped piece 22 and the second L-shaped piece 23 are matched with the arc-shaped piece 21, one side of the first L-shaped piece 22 and one side of the second L-shaped piece 23 are parallel to the arc-shaped piece 21, and the other side of the first L-shaped piece 22 and the second L-shaped piece 23 are perpendicular to the arc-shaped piece 21. The horizontal edge of the first L-shaped member 22 extends beyond the perpendicular to the end of the arcuate member 21, and the horizontal edge of the second L-shaped member 23 does not extend beyond the perpendicular to the end of the arcuate member 21. The first L-shaped member 22 is lower in height than the second L-shaped member 23, and reverse installation errors can be prevented. The first L-shaped member 22 and the second L-shaped member 23 and the arc-shaped member 21 form grooves at both ends of the arc-shaped member 21, respectively. The bottom of the turbine outer ring 2 is provided with a high temperature coating. Preferably, the turbine outer ring 2 is of integrally formed construction.
The section of the sealing piece 4 is L-shaped and of a thin sheet structure, and the sealing piece is arranged in the opposite L-shaped grooves on the end faces of the two adjacent turbine outer rings 2 and is mainly used for covering gaps between the adjacent turbine outer rings 2 to play a role in sealing fuel gas. The L-shaped groove is slightly larger than the sealing piece in size and plays a role of fixing the mounting piece.
The horizontal edge of the first L-shaped piece 22 of the turbine outer ring 2 is inserted into the second groove 12 of the casing 1, the positioning block is inserted into the through hole 14 of the casing 1, and is abutted with the first L-shaped piece 22 of the turbine outer ring 2 for fixing the turbine outer ring 2. The turbine outer ring collar 3 is arranged outside the circumferentially arranged turbine outer ring 2. The fixing piece is inserted into the groove at the other end of the turbine outer ring 2, and is mounted on the third groove 13 through the positioning block.
As shown in fig. 2, the cooling structure of the turbine outer ring is not provided with the turbine outer ring clamp 3, after the cooling gas enters the outer ring cavity from the gas through hole 15, the inner surface of the turbine outer ring 2 is subjected to impact cooling, and then the cooling gas flows into the main runner through gaps between the front end face and the rear end face of the adjacent turbine outer ring 2. The inner surface of the turbine outer ring 2 is directly subjected to impact cooling, the impact stagnation point heat exchange effect is good, so that the temperature of an impact area is very low, and the other side of the turbine outer ring 2 is very high in gas flushing temperature, so that the local temperature gradient of the turbine outer ring 2 is large, and the thermal stress is large.
In order to further improve the cooling structure of the turbine outer ring, a turbine outer ring collar 3 is provided. As shown in fig. 1, after the turbine outer ring clamp 3 is installed, after the cooling gas enters the outer ring cavity from the gas through hole 15, the cooling gas first impinges on the top circle 31 area of the turbine outer ring clamp 3 and is divided into two cooling gases: a first flow of cooling gas flowing to the left and a second flow of cooling gas flowing to the right. In the process of flowing leftwards, the first cooling gas is divided into a third cooling gas and a fourth cooling gas, the third cooling gas flows upwards along the inner wall of the turbine outer ring clamp 3, the fourth cooling gas passes through small holes 33 on the turbine outer ring clamp 3 and flows obliquely upwards along a gap between the turbine outer ring clamp 3 and the turbine outer ring 2, and finally the third cooling gas and the fourth cooling gas are combined into one cooling gas. In the rightward flowing process of the second cooling gas, the second cooling gas is further divided into a fifth cooling gas and a sixth cooling gas, the fifth cooling gas flows upwards along the inner wall of the turbine outer ring clamp 3, the sixth cooling gas passes through the small holes 33 on the turbine outer ring clamp 3, flows obliquely upwards along the gap between the turbine outer ring clamp 3 and the turbine outer ring 2, and finally the fifth cooling gas and the sixth cooling gas are combined into one cooling gas. The turbine outer ring clamp 3 has the vortex effect on cooling gas, and finally cooling gas fills the outer ring cavity, so that the temperature of the whole outer ring cavity is effectively reduced, after the temperature of the inner surface of the turbine outer ring 2 is uniformly distributed through full heat exchange, two cooling gases respectively flow into the main runner from gaps between the front end surface and the rear end surface of the adjacent turbine outer ring 2, and meanwhile, the effect of sealing gas is achieved. The turbine outer ring clamp 3 has a turbulent flow effect, changes the flow mode of cooling gas, converts the local impact strengthening cooling mode into a uniform convection cooling mode, and can effectively reduce the temperature gradient and the thermal stress of the turbine outer ring 2 by the two flow modes on the premise of ensuring effective heat exchange.
Fig. 3 shows a schematic structural view of a turbine outer ring band according to an embodiment of the present invention, and fig. 4 shows a sectional view of a turbine outer ring band according to an embodiment of the present invention. As shown in fig. 3 and 4, the turbine outer ring collar 3 is applied to a turbine brake and comprises a top circle 31, a fulcrum 32 and a small hole 33;
the fulcrum 32 sets up in top circle 31 below, and top circle 31 is used for bearing the cooling gas impingement cooling to shunt the cooling gas, fulcrum 32 as the setpoint for support turbine outer loop clamp 3, fulcrum 32 hugs closely turbine outer loop 2 internal surface. A plurality of small holes 33 are provided on both sides of the top circle 31. The turbine outer ring clamp 3 is of an annular structure with a notch, and is convenient to install and replace. The turbine outer ring clamp 3 is arranged in the outer ring cavity.
As shown in FIG. 4, the cross section of the turbine outer ring clamp 3 is W-shaped, and the thickness is 0.6-1.5 mm. The radius of the top circle 31 is 0.8-2 mm.
In structure, two fulcrums 32 at one end of the turbine outer ring clamp 3 are clung to the inner surface of the turbine outer ring 2, and the turbine outer ring 2 of the whole circle circumferentially arranged is hooped inwards, so that the turbine outer ring 2 is fastened after being hung on the casing 1, and the effective control of blade tip gaps is ensured. In addition, the turbine outer ring clamp 3 is provided with two supporting points 32, so that the installation is more stable, and the front and rear stress of the turbine outer ring 2 is more uniform.
In order to make the flow of the cooling gas in the outer ring cavity more uniform, the turbine outer ring band 3 is provided with a plurality of small holes 33. The cross-sectional shape of the aperture 33 is circular, elliptical or polygonal. Polygons include triangles, rectangles, squares, etc. Preferably, the aperture 33 is circular in cross-sectional shape.
Fig. 5 shows a small hole structure of a turbine outer ring band according to an embodiment of the present invention. As shown in FIG. 5 (a), the present invention provides a preferred embodiment of the turbine outer ring band 3, the turbine outer ring band 3 having a thickness of 1.5mm and a radius of 2mm for the top circle 31. The turbine outer ring clamp 3 is provided with two rows of small holes 33, the cross section of the small holes 33 is circular, the parameters of the small holes 33 are 2 rows and 8 columns, and the aperture isAs shown in fig. 5 (b), in another design, the small holes 33 in the turbine outer ring band 3 may be provided as rounded rectangles.
The turbine comprises the cooling structure of the turbine outer ring, and the cooling structure is not repeated here.
An engine comprising the turbine described above.
According to the turbine outer ring clamp, the cooling structure of the turbine outer ring, the turbine and the engine, the W-shaped turbine outer ring clamp is arranged, so that a local impact strengthening cooling mode is converted into a uniform convection cooling mode, and the temperature gradient and the thermal stress of the turbine outer ring are greatly reduced; after the W-shaped turbine outer ring clamp is added, the turbine outer ring is more fastened, and the control of blade tip clearance can be effectively ensured; the W-shaped turbine outer ring clamp is provided with two fulcrums, so that the installation is more stable, and the front and rear stress of the turbine outer ring is more uniform; the W-shaped turbine outer ring clamp has the characteristics of easy assembly, self-fixing and the like, and other assembly processes are not required to be added.
In the description of the embodiments of the present invention, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", "horizontal", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present invention and simplify the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the invention.
Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first", "a second", etc. may explicitly or implicitly include one or more such feature. In the description of the invention, unless otherwise indicated, the meaning of "a plurality" is two or more.
The term "mounted" is to be understood broadly, and may be, for example, fixedly attached, detachably attached, or integrally attached; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the creation of the present invention can be understood by those of ordinary skill in the art in a specific case.
Although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present invention.
Claims (7)
1. The turbine outer ring clamp is applied to a turbine casing and is characterized in that the turbine outer ring clamp (3) comprises a top circle (31), a fulcrum (32) and a small hole (33);
the radius of the top circle (31) is 0.8-2 mm;
the fulcrum (32) is arranged below the top circle (31);
the small holes (33) are arranged on two sides of the top circle (31);
the turbine outer ring clamp (3) is of an annular structure with a notch, the section is W-shaped, and the thickness is 0.6-1.5 mm;
the top circle (31) is used for bearing the impact cooling of the cooling gas and splitting the cooling gas;
the fulcrum (32) is a positioning point and is used for supporting the turbine outer ring clamp (3);
and a plurality of small holes (33) for making the flow of the cooling gas in the outer ring cavity more uniform.
2. Turbine outer ring clamp according to claim 1, characterized in that the cross-sectional shape of the aperture (33) is circular, elliptical or polygonal.
3. A cooling structure of a turbine outer ring, comprising: a casing (1), a turbine outer ring (2), a turbine outer ring clamp (3) according to any one of claims 1-2, and a sealing piece (4);
a plurality of turbine outer rings (2) are hung on the casing (1); the turbine outer ring clamp (3) is arranged outside the plurality of turbine outer rings (2); the sealing piece (4) covers gaps between adjacent turbine outer rings (2).
4. A cooling structure of a turbine outer ring according to claim 3, characterized in that the casing (1) comprises a first groove (11), a second groove (12), a third groove (13), a through hole (14), a gas through hole (15) and a boss (16);
a first groove (11) which is downwards opened is formed in one end of the casing (1), a second groove (12) which is rightwards opened is formed close to the first groove (11), and a through hole (14) is formed in the casing (1) right above the second groove (12); a plurality of gas through holes (15) are uniformly formed in the circumferential direction of the casing (1), and the gas through holes (15) are opposite to a top circle (31) of the turbine outer ring clamp (3); a boss (16) is arranged on the first surface of the other end of the casing (1), and a third groove (13) is arranged below the boss (16).
5. A cooling structure of a turbine outer ring according to claim 3, characterized in that the turbine outer ring (2) comprises: an arc-shaped piece (21), a first L-shaped piece (22) and a second L-shaped piece (23);
the section of the turbine outer ring (2) is inverted pi-shaped;
the first L-shaped piece (22) and the second L-shaped piece (23) are matched with the arc-shaped piece (21), one side of the first L-shaped piece (22) and one side of the second L-shaped piece (23) are parallel to the arc-shaped piece (21), and the other side of the first L-shaped piece is perpendicular to the arc-shaped piece (21); the horizontal edge of the first L-shaped piece (22) exceeds the vertical line of the end point of the arc-shaped piece (21), and the horizontal edge of the second L-shaped piece (23) does not exceed the vertical line of the end point of the arc-shaped piece (21); the first L-shaped piece (22) is lower in height than the second L-shaped piece (23).
6. A turbine comprising the cooling structure of the turbine outer ring of any one of claims 3-5.
7. An engine comprising the turbine of claim 6.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111059346.5A CN113638777B (en) | 2021-09-10 | 2021-09-10 | Turbine outer ring clamp, cooling structure of turbine outer ring, turbine and engine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111059346.5A CN113638777B (en) | 2021-09-10 | 2021-09-10 | Turbine outer ring clamp, cooling structure of turbine outer ring, turbine and engine |
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| Publication Number | Publication Date |
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| CN113638777A CN113638777A (en) | 2021-11-12 |
| CN113638777B true CN113638777B (en) | 2023-09-15 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202111059346.5A Active CN113638777B (en) | 2021-09-10 | 2021-09-10 | Turbine outer ring clamp, cooling structure of turbine outer ring, turbine and engine |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115898559A (en) * | 2022-10-10 | 2023-04-04 | 杭州汽轮动力集团股份有限公司 | High-efficient turbine dish chamber air feed structure with prewhirl nozzle |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101173612A (en) * | 2006-10-30 | 2008-05-07 | 斯奈克玛 | Turbine fixing ring sector, turbine ring, turbine and turbomachine |
| JPWO2007099895A1 (en) * | 2006-03-02 | 2009-07-16 | 株式会社Ihi | Impingement cooling structure |
| FR2955890A1 (en) * | 2010-02-02 | 2011-08-05 | Snecma | Ring sector for use in ring of turbine in e.g. turbo-prop engine of airplane, has plate that is corrugated such that size of gap is increased and decreased successively, where perforations of plate are provided at level of gap |
| CN110847982A (en) * | 2019-11-04 | 2020-02-28 | 中国科学院工程热物理研究所 | Combined type cooling and sealing structure for outer ring of high-pressure turbine rotor |
-
2021
- 2021-09-10 CN CN202111059346.5A patent/CN113638777B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPWO2007099895A1 (en) * | 2006-03-02 | 2009-07-16 | 株式会社Ihi | Impingement cooling structure |
| CN101173612A (en) * | 2006-10-30 | 2008-05-07 | 斯奈克玛 | Turbine fixing ring sector, turbine ring, turbine and turbomachine |
| FR2955890A1 (en) * | 2010-02-02 | 2011-08-05 | Snecma | Ring sector for use in ring of turbine in e.g. turbo-prop engine of airplane, has plate that is corrugated such that size of gap is increased and decreased successively, where perforations of plate are provided at level of gap |
| CN110847982A (en) * | 2019-11-04 | 2020-02-28 | 中国科学院工程热物理研究所 | Combined type cooling and sealing structure for outer ring of high-pressure turbine rotor |
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