CN115405370A - Semi-elastic turbine outer ring structure - Google Patents
Semi-elastic turbine outer ring structure Download PDFInfo
- Publication number
- CN115405370A CN115405370A CN202211365079.9A CN202211365079A CN115405370A CN 115405370 A CN115405370 A CN 115405370A CN 202211365079 A CN202211365079 A CN 202211365079A CN 115405370 A CN115405370 A CN 115405370A
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- China
- Prior art keywords
- outer ring
- flexure strip
- casing
- connecting portion
- elastic
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
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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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gasket Seals (AREA)
Abstract
The application belongs to the field of design of aero-engines and gas turbines, and discloses a semi-elastic turbine outer ring structure which comprises a casing and an outer ring, wherein the casing and the outer ring are coaxially arranged; the casing is provided with a first connecting part, a second connecting part and a third connecting part, and an outer ring, a third elastic sheet and a fourth elastic sheet are arranged between the casing and the outer ring; through the connecting structure who sets up outer loop, third flexure strip and fourth flexure strip, form rigid connection structure between outer loop and the machine casket, form flexible connection structure between third flexure strip and fourth flexure strip and the machine casket to the outer loop is the theme, uses third flexure strip and fourth flexure strip as supplementary, forms the compound connection structure of rigid-flexible combination. The engine has the characteristics of stable fixation and high assembly precision of the rigid connection structure, has the characteristics of good assembly performance, good sealing performance, excellent cooling effect and good reliability of the elastic connection structure, and ensures the overall performance of the engine while having stable structure.
Description
Technical Field
The application belongs to the field of design of aero-engines and gas turbines, and particularly relates to a semi-elastic turbine outer ring structure.
Background
The turbine outer ring and the blade tip of the blade are matched to form a blade tip gap, the radial positioning of the outer ring is unreliable, the maintenance of the blade tip gap is influenced, the flow loss of the blade tip is increased due to the increase of the gap, and the collision and abrasion risks are caused due to the decrease of the gap; in addition, the outer ring mainly bears thermal shock of high-temperature gas of the main channel, the working condition is harsh, the surface temperature can reach more than 1000 ℃, and the surface temperature is higher and higher along with the rise of the temperature of the gas at the inlet of the turbine, so that the outer ring is one of components for limiting the service life of an engine.
There are two positioning ways for the conventional outer ring, one is rigid connection, see fig. 1, the first outer ring 1a is connected with the first casing 2a or the guide vane in a hook and lap joint manner; the other one is flexible connection, as shown in fig. 2, the second outer ring 1b is connected with the second casing 2b or the guide vane by a first elastic sheet 3 and a second elastic sheet 4 of a sheet metal part.
According to the figure 3, the rigid connection type outer ring is easy to deform after working, so that the secondary assembly difficulty is high, meanwhile, the deformed outer ring and the casing cannot be tightly attached, a large amount of cooling air is leaked in a working state, the cooling effect of the outer ring is seriously influenced, the ablation risk of the outer ring is increased, and meanwhile, the ineffective leakage of the cooling air also influences the overall performance of the engine.
The flexible connection type outer ring is difficult to reliably position and cannot stably keep the blade tip clearance, so that the performance loss of the turbine and the collision and abrasion risk are brought.
Therefore, how to achieve stable positioning while improving the repeated assembly is a problem to be solved.
Disclosure of Invention
The application aims to provide a semi-elastic turbine outer ring structure to solve or alleviate the problem that the assembling repeatability and stable positioning are difficult to realize simultaneously in the background art.
The technical scheme of the application is as follows: a semi-elastic turbine outer ring structure comprises a casing, wherein the casing is provided with a first connecting part, a second connecting part and a third connecting part, and further comprises an outer ring, a third elastic sheet and a fourth elastic sheet; the utility model discloses a flexible connection structure, including outer loop, first connecting portion and second connecting portion, outer loop one end and third connecting portion link to each other, form the flexure strip installation cavity between the other end and first connecting portion and the second connecting portion, correspond the setting inside and outside first connecting portion and the second connecting portion, the flexure strip installation cavity is all located to third flexure strip and fourth flexure strip, the third flexure strip is connected between first connecting portion and outer loop through predeformation, the fourth flexure strip is connected between second connecting portion and outer loop.
Preferably, the second connecting portion is an annular first protrusion arranged on the casing, the fourth elastic piece is of a comb tooth structure, and a comb tooth portion of the fourth elastic piece is radially matched with the first protrusion after being pre-deformed.
Preferably, an annular boss is arranged on the side wall of the outer ring, and the main body of the fourth elastic sheet is in clamping fit with the annular boss.
Preferably, the first connecting portion is an annular second protrusion coaxially arranged on the inner side of the casing, the third elastic sheet and the second protrusion are coaxially arranged, and the second protrusion is hermetically connected with a sealing sheet at a position corresponding to an interval of the third elastic sheet.
Preferably, the third connecting portion is an inner annular groove formed in the side wall of the casing, the cross section of the outer ring is L-shaped, and a hook is arranged on the side wall of the outer ring, which is far away from one end of the third elastic piece and one end of the fourth elastic piece, and the hook is coaxially connected to the inner annular groove.
The semi-elastic turbine outer ring structure comprises a casing and an outer ring, wherein the casing and the outer ring are coaxially arranged; the casing is provided with a first connecting part, a second connecting part and a third connecting part, and an outer ring, a third elastic sheet and a fourth elastic sheet are arranged between the casing and the outer ring; through the connecting structure who sets up outer loop, third flexure strip and fourth flexure strip, form rigid connection structure between outer loop and the machine casket, form flexible connection structure between third flexure strip and fourth flexure strip and the machine casket to the outer loop is the theme, uses third flexure strip and fourth flexure strip as supplementary, forms the compound connection structure of rigid-flexible combination. The engine has the characteristics of stable fixation and high assembly precision of the rigid connection structure, has the characteristics of good assembly performance, good sealing performance, excellent cooling effect and good reliability of the elastic connection structure, and ensures the overall performance of the engine while having stable structure.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
FIG. 1 is a schematic diagram of a rigid connection structure in the prior art;
FIG. 2 is a schematic diagram of a flexible connection structure in the prior art;
FIG. 3 is a structural diagram of deformation of an outer ring in the prior art;
FIG. 4 is a schematic view of the overall structure of the present application;
FIG. 5 is a schematic view of a fourth elastic sheet according to the present application;
fig. 6 is a schematic structural view of a third elastic sheet of the present application.
1. An outer ring; 2. a casing; 3. a first elastic sheet; 4. a second elastic sheet; 5. a third elastic sheet; 6. a fourth elastic sheet; 7. a first protrusion; 8. an annular boss; 9. a second protrusion; 10. hooking; 11. a sealing sheet; 1a, a first outer ring; 2a, a first casing; 1b, a second outer ring; 2b, a second casing.
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.
A semi-elastic turbine outer ring structure is shown in figure 4 and comprises a casing 2 and an outer ring 1, wherein the casing 2 and the outer ring 1 are coaxially arranged.
A first connecting part, a second connecting part and a third connecting part are arranged on the casing 2, and a third elastic sheet 5 and a fourth elastic sheet 6 are arranged between the casing 2 and the outer ring 1; the 1 one end of outer loop links to each other with the third connecting portion, forms the flexure strip installation cavity between the other end and first connecting portion and the second connecting portion, and the inside and outside correspondence setting of first connecting portion and second connecting portion, third flexure strip 5 and fourth flexure strip 6 all locate the flexure strip installation cavity, and fourth flexure strip 6 is connected between second connecting portion and outer loop 1 through predeformation, and third flexure strip 5 is connected between first connecting portion and outer loop 1.
Through the connection structure who sets up outer loop 1, third flexure strip 5 and fourth flexure strip 6, form rigid connection structure between outer loop 1 and the quick-witted casket 2, form flexible connection structure between third flexure strip 5 and fourth flexure strip 6 and the quick-witted casket 2 to outer loop 1 is the main part, uses third flexure strip 5 and fourth flexure strip 6 as supplementary, forms the compound connection structure of rigid-flexible combination. The engine has the characteristics of stable fixation and high assembly precision of the rigid connection structure, has the characteristics of good assembly performance, good sealing performance, excellent cooling effect and good reliability of the elastic connection structure, and ensures the overall performance of the engine while having stable structure.
Referring to fig. 5, preferably, the second connecting portion is an annular first protrusion 7 disposed on the casing 2, the fourth elastic sheet 6 is of a comb structure, and a comb portion of the fourth elastic sheet 6 is pre-deformed and then radially fits the first protrusion 7. The broach structure is convenient for the secondary assembly school type, changes and guarantees the assembly tightness, further improves its and the reliable laminating of quick-witted casket 2, simultaneously for guaranteeing assembly manufacturability, the broach structure is stable with the cooperation of first arch 7.
The fourth elastic sheet 6 is required to be provided with an assembly guide structure. The amount of elastic pre-deformation is required to be able to withstand the weight of the monolithic outer ring 1 while being determined in combination with the thermal deformation of the fitting therein.
Preferably, the side wall of the outer ring 1 is provided with an annular boss 8, and the main body part of the fourth elastic sheet 6 is in clamping fit with the annular boss 8, so that the fit is simple and stable.
With reference to fig. 6, preferably, the first connecting portion is an annular second protrusion 9 coaxially disposed inside the casing 2, the third elastic sheet 5 and the second protrusion 9 are coaxially disposed, and the second protrusion 9 is hermetically connected to a sealing sheet 11 at a position corresponding to an interval between the third elastic sheets 5. Because third flexure strip 5 is the sectional type along with outer ring 1, there is the clearance in circumference, consequently the piece 11 of obturating of design is used for the air conditioning between the flexure strip circumference of obturating, ensures performance and cooling effect of obturating.
Preferably, the third connecting portion is an inner annular groove formed in the side wall of the casing 2, the cross section of the outer ring 1 is L-shaped, a hook 10 is arranged on the side wall of one end of the outer ring 1, which is far away from the third elastic sheet 5 and the fourth elastic sheet 6, and the hook 10 is coaxially connected in the inner annular groove. The hook 10 is used for realizing radial lap joint with the inner ring groove, and the front end elastic positioning is matched for realizing radial stable positioning.
In addition, the positioning form of the outer ring 1 is also suitable for the positioning form of the casing 2-guide vane-outer ring 1, namely the third elastic sheet 5 can be matched with the upper edge plate of the guide vane to realize the positioning of the outer ring 1, and the elastic positioning form at the position can solve the problem of thermal deformation coordination between the casing 2 and the guide vane more easily.
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 (5)
1. A semi-elastic turbine outer ring structure comprises an outer ring (1) and a casing (2), and is characterized in that: the casing (2) is provided with a first connecting part, a second connecting part and a third connecting part, and a third elastic sheet (5) and a fourth elastic sheet (6) are arranged between the casing (2) and the outer ring (1); outer loop (1) one end links to each other with the third connecting portion, forms the flexure strip installation cavity between the other end and first connecting portion and the second connecting portion, correspond the setting in first connecting portion and the second connecting portion, flexure strip installation cavity is all located in third flexure strip (5) and fourth flexure strip (6), fourth flexure strip (6) are connected between second connecting portion and outer loop (1) through predeformation, third flexure strip (5) are connected between first connecting portion and outer loop (1).
2. The semi-elastomeric turbine outer ring structure of claim 1, wherein: the second connecting portion is an annular first bulge (7) arranged on the casing (2), the fourth elastic piece (6) is of a comb tooth structure, and the comb tooth portion of the fourth elastic piece (6) is in radial fit with the first bulge (7) after being pre-deformed.
3. The semi-elastomeric turbine outer ring structure of claim 2, wherein: the novel elastic piece is characterized in that an annular boss (8) is arranged on the side wall of the outer ring (1), and the main body part of the fourth elastic piece (6) is matched with the annular boss (8) in a clamping mode.
4. The semi-elastomeric turbine outer ring structure of claim 1, wherein: the first connecting portion is an annular second protrusion (9) coaxially arranged on the inner side of the casing (2), the third elastic piece (5) and the second protrusion (9) are coaxially arranged, and the second protrusion (9) is hermetically connected with a sealing piece (11) at an interval position corresponding to the third elastic piece (5).
5. A semi-resilient turbine outer ring structure according to claim 1, wherein: the third connecting portion are inner ring grooves formed in the side wall of the casing (2), the cross section of the outer ring (1) is L-shaped, a hook (10) is arranged on the side wall, far away from one end of the third elastic sheet (5) and one end of the fourth elastic sheet (6), of the outer ring (1), and the hook (10) is coaxially connected to the inner ring grooves.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211365079.9A CN115405370B (en) | 2022-11-03 | 2022-11-03 | Semi-elastic turbine outer ring structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211365079.9A CN115405370B (en) | 2022-11-03 | 2022-11-03 | Semi-elastic turbine outer ring structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115405370A true CN115405370A (en) | 2022-11-29 |
| CN115405370B CN115405370B (en) | 2023-03-10 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202211365079.9A Active CN115405370B (en) | 2022-11-03 | 2022-11-03 | Semi-elastic turbine outer ring structure |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020184888A1 (en) * | 2001-06-06 | 2002-12-12 | Snecma Moteurs | Connection for a two-part CMC chamber |
| US20050242522A1 (en) * | 2004-03-26 | 2005-11-03 | Snecma Moteurs | Seal between the inner and outer casings of a turbojet section |
| CN102224323A (en) * | 2008-11-21 | 2011-10-19 | 涡轮梅坎公司 | Positioning member for ring segment |
| US20140223920A1 (en) * | 2013-02-12 | 2014-08-14 | United Technologies Corporation | Consumable assembly mistake proofing tool for a gas turbine engine |
| CN209818122U (en) * | 2019-04-18 | 2019-12-20 | 中国航发沈阳发动机研究所 | Turbine outer ring fixing structure |
| CN113062781A (en) * | 2021-05-06 | 2021-07-02 | 中国航发湖南动力机械研究所 | Centering and positioning structure for CMC gas turbine outer ring |
| WO2021209707A1 (en) * | 2020-04-15 | 2021-10-21 | Safran Aircraft Engines | Turbine for a turbine engine |
| CN217681869U (en) * | 2022-09-27 | 2022-10-28 | 中国航发燃气轮机有限公司 | Light gas turbine high-pressure turbine guider connecting structure |
-
2022
- 2022-11-03 CN CN202211365079.9A patent/CN115405370B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020184888A1 (en) * | 2001-06-06 | 2002-12-12 | Snecma Moteurs | Connection for a two-part CMC chamber |
| US20050242522A1 (en) * | 2004-03-26 | 2005-11-03 | Snecma Moteurs | Seal between the inner and outer casings of a turbojet section |
| CN102224323A (en) * | 2008-11-21 | 2011-10-19 | 涡轮梅坎公司 | Positioning member for ring segment |
| US20140223920A1 (en) * | 2013-02-12 | 2014-08-14 | United Technologies Corporation | Consumable assembly mistake proofing tool for a gas turbine engine |
| CN209818122U (en) * | 2019-04-18 | 2019-12-20 | 中国航发沈阳发动机研究所 | Turbine outer ring fixing structure |
| WO2021209707A1 (en) * | 2020-04-15 | 2021-10-21 | Safran Aircraft Engines | Turbine for a turbine engine |
| CN113062781A (en) * | 2021-05-06 | 2021-07-02 | 中国航发湖南动力机械研究所 | Centering and positioning structure for CMC gas turbine outer ring |
| CN217681869U (en) * | 2022-09-27 | 2022-10-28 | 中国航发燃气轮机有限公司 | Light gas turbine high-pressure turbine guider connecting structure |
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| Publication number | Publication date |
|---|---|
| CN115405370B (en) | 2023-03-10 |
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Inventor after: Cui Inventor after: Cao Maoguo Inventor after: Liu Mei Inventor after: Yuan Chang Inventor after: Zhuo Wenjing Inventor after: Liu Yunlong Inventor after: Sun Guozhi Inventor after: Dong Yue Inventor before: Cui Gong Inventor before: Cao Maoguo Inventor before: Liu Mei Inventor before: Yuan Chang Inventor before: Zhuo Wenjing Inventor before: Liu Yunlong Inventor before: Sun Guozhi Inventor before: Dong Yue |