CN111288020A - Compressor stator blade linkage structure - Google Patents
Compressor stator blade linkage structure Download PDFInfo
- Publication number
- CN111288020A CN111288020A CN202010113668.2A CN202010113668A CN111288020A CN 111288020 A CN111288020 A CN 111288020A CN 202010113668 A CN202010113668 A CN 202010113668A CN 111288020 A CN111288020 A CN 111288020A
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- China
- Prior art keywords
- compressor stator
- compressor
- stator blade
- linkage structure
- hole
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/46—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/462—Fluid-guiding means, e.g. diffusers adjustable especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The application belongs to compressor stator blade linkage structure design field, concretely relates to compressor stator blade linkage structure, include: the annular compressor casing is provided with a plurality of mounting through holes distributed along the circumferential direction; a plurality of compressor stator blades arranged in an annular compressor casing; the upper journal of each compressor stator blade correspondingly penetrates through one mounting through hole; the linkage ring is sleeved on the annular compressor casing, and one side of the linkage ring is meshed with the upper journals of the stator blades of each compressor through insections; the linkage ring can rotate relative to the annular compressor casing to drive each compressor stator blade to synchronously rotate, so that the angle of each compressor stator blade is synchronously adjusted, each compressor stator blade of the compressor stator blade linkage structure is in toothed connection with the linkage ring, transmission is performed through the toothed line, and the linkage ring is efficient and reliable in transmission, relatively simple in structure and convenient to assemble.
Description
Technical Field
The application belongs to the field of design of a compressor stator blade linkage structure, and particularly relates to a compressor stator blade linkage structure.
Background
The angle of the stator blade is adjusted through a stator blade linkage structure on the gas compressor, at present, the stator blade linkage structure mainly comprises a linkage ring, a stator blade rocker arm, and correspondingly arranged locking screws, locking plates, gaskets, joint bearings, split pins, clamping rings and other parts, and is complex in structure, large in part number, heavy in weight, complex in assembly process, poor in economical efficiency, easy to wear and break in part of the parts, and capable of influencing the reliability of the stator blade linkage structure.
The present application has been made in view of the above-mentioned technical drawbacks.
Disclosure of Invention
The object of the present application is to provide a compressor stator vane linkage that overcomes or alleviates at least one of the technical disadvantages of the known prior art.
The technical scheme of the application is as follows:
a compressor stator vane linkage structure comprising:
the annular compressor casing is provided with a plurality of mounting through holes distributed along the circumferential direction;
a plurality of compressor stator blades arranged in an annular compressor casing; the upper journal of each compressor stator blade correspondingly penetrates through one mounting through hole;
the linkage ring is sleeved on the annular compressor casing, and one side of the linkage ring is meshed with the upper journals of the stator blades of each compressor through insections; the linkage ring can rotate relative to the annular compressor casing to drive each compressor stator blade to synchronously rotate, so that the angle of each compressor stator blade is synchronously adjusted.
According to at least one embodiment of the present application, further comprising:
and each bevel gear is correspondingly arranged on the end surface of one upper shaft neck and meshed with one side of the linkage ring through insections.
According to at least one embodiment of the present application, one side of each bevel gear has a connection hole;
the end surface of each upper journal is provided with a connecting boss; each connecting boss is correspondingly inserted into one connecting hole.
According to at least one embodiment of the present application, the side wall of each connection hole is provided with an anti-rotation through hole;
each connecting boss is provided with an anti-rotation hole;
further comprising:
and each anti-rotation pin correspondingly penetrates through one anti-rotation through hole and is inserted into the corresponding anti-rotation hole.
According to at least one embodiment of the present application, further comprising:
and each inner bushing is correspondingly sleeved on one upper shaft neck.
According to at least one embodiment of the present application, further comprising:
and each outer bushing is correspondingly arranged in one mounting through hole and positioned on the outer side of the corresponding inner bushing.
According to at least one embodiment of the present application, a limiting groove is formed between each outer bushing and the corresponding compressor stator blade;
the outer wall of each inner bushing is provided with a clamping edge, and each clamping edge is clamped into the corresponding limiting groove.
According to at least one embodiment of the application, each outer bushing inner wall is provided with a limiting protrusion, and a limiting groove is formed between the limiting protrusion and the corresponding compressor stator blade.
According to at least one embodiment of the present application, each outer liner outer wall has a connecting edge; each connecting edge is connected with the outer wall of the annular compressor casing.
Please have at least the following beneficial technical effects:
the compressor stator blade linkage structure has the advantages that the compressor stator blades synchronously rotate through the rotation of the linkage rings meshed with the upper journal insections, the synchronous adjustment of the angles of the compressor stator blades is realized, and the compressor stator blades of the compressor stator blade linkage structure are connected with the insections of the linkage rings and are driven through the insections, so that the transmission is efficient and reliable, the structure is relatively simple, and the assembly is convenient.
Drawings
FIG. 1 is a schematic diagram of a compressor stator vane linkage structure provided by an embodiment of the application;
wherein:
1-an annular compressor casing; 2-compressor stator blades; 3-a linkage ring; 4-bevel gear; 5-anti-rotation pin; 6-inner lining; 7-outer liner.
Detailed Description
In order to make the technical solutions and advantages of the present application clearer, the technical solutions of the present application will be further clearly and completely described in the following detailed description with reference to the accompanying drawings, and it should be understood that the specific embodiments described herein are only some of the embodiments of the present application, and are only used for explaining the present application, but not limiting the present application. It should be noted that, for convenience of description, only the parts related to the present application are shown in the drawings, other related parts may refer to general designs, and the embodiments and technical features in the embodiments in the present application may be combined with each other to obtain a new embodiment without conflict.
In addition, unless otherwise defined, technical or scientific terms used in the description of the present application shall have the ordinary meaning as understood by one of ordinary skill in the art to which the present application belongs. The terms "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", and the like used in the description of the present application, which indicate orientations, are used only to indicate relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and when the absolute position of the object to be described is changed, the relative positional relationships may be changed accordingly, and thus, should not be construed as limiting the present application. The use of "first," "second," "third," and the like in the description of the present application is for descriptive purposes only to distinguish between different components and is not to be construed as indicating or implying relative importance. The use of the terms "a," "an," or "the" and similar referents in the context of describing the application is not to be construed as an absolute limitation on the number, but rather as the presence of at least one. The use of the terms "comprising" or "including" and the like in the description of the present application is intended to indicate that the element or item preceding the term covers the element or item listed after the term and its equivalents, without excluding other elements or items.
Further, it is noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and the like are used in the description of the invention in a generic sense, e.g., connected as either a fixed connection or a removable connection or integrally connected; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected through the inside of two elements, and those skilled in the art can understand their specific meaning in this application according to the specific situation.
The present application is described in further detail below with reference to fig. 1.
A compressor stator vane linkage structure comprising:
the annular compressor casing 1 is provided with a plurality of mounting through holes distributed along the circumferential direction;
a plurality of compressor stator blades 2 are arranged in the annular compressor casing 2; the upper journal of each compressor stator blade 2 correspondingly penetrates through one mounting through hole;
the linkage ring 3 is sleeved on the annular compressor casing 1, and one side of the linkage ring is meshed with the upper journals of the compressor stator blades 2 through insections; the linkage ring 3 can rotate relative to the annular compressor casing 1 to drive each compressor stator blade 2 to rotate synchronously, and synchronous adjustment of the angle of each compressor stator blade 2 is achieved.
For the compressor stator blade linkage structure disclosed in the above embodiment, it can be understood by those skilled in the art that the compressor stator blades 2 are synchronously rotated by the rotation of the linkage ring 3 engaged with the upper journal insections, so as to realize the synchronous adjustment of the angles of the compressor stator blades 2, and it can be understood that the compressor stator blades 2 of the compressor stator blade linkage structure are connected with the insections of the linkage ring 3, and the transmission is performed by the insections, so that the transmission is efficient and reliable, and the structure is relatively simple and convenient to assemble.
In some optional embodiments, further comprising:
and each bevel gear 4 is correspondingly arranged on the end surface of one upper shaft neck and meshed with one side of the linkage ring 3 through insections.
For the compressor stator blade linkage structure disclosed in the above embodiment, it can be understood by those skilled in the art that the linkage ring 3 is connected with each compressor stator blade 2 through the bevel gear 4, and the linkage ring 3 is meshed with each bevel gear 4 through the insections, so that each bevel gear 4 can be synchronously driven to rotate, and each compressor stator blade 2 is synchronously rotated, thereby realizing synchronous adjustment of the angle of each compressor stator blade 2.
For the compressor stator blade linkage structure disclosed in the above embodiment, it can be further understood by those skilled in the art that, in order to change the direction of the torque, the torque of the link ring 3 is transmitted to each compressor stator blade 2, and the link ring 3 is connected with each compressor stator blade 2 through the bevel gear 4, so that the rotating shaft is changed from the engine shaft to the journal center of each compressor stator blade 2.
In some alternative embodiments, one side of each bevel gear 4 has a connection hole;
the end surface of each upper journal is provided with a connecting boss; each connecting boss is correspondingly inserted into one connecting hole and connected with the corresponding bevel gear.
In some alternative embodiments, the side wall of each connecting hole is provided with an anti-rotation through hole;
each connecting boss is provided with an anti-rotation hole;
further comprising:
and each anti-rotation pin 5 correspondingly penetrates through one anti-rotation through hole and is inserted into the corresponding anti-rotation hole so as to prevent the bevel gear 4 from loosening from the corresponding connecting boss and prevent the bevel gear 4 and the corresponding connecting boss from rotating relatively.
In some optional embodiments, further comprising:
and a plurality of inner bushings 6, wherein each inner bushing 6 is sleeved on one upper journal correspondingly so as to protect the upper journal from being worn.
In some optional embodiments, further comprising:
and a plurality of outer bushings 7, each outer bushing 7 being correspondingly disposed in one of the mounting through holes at an outer side of the corresponding inner bushing 6.
For the compressor stator blade linkage structure disclosed in the above embodiment, it can be understood by those skilled in the art that the inner bushing 6 is connected to the corresponding upper journal, and the outer bushing 7 is connected to the inner wall of the corresponding mounting through hole, so as to avoid the wear between the upper journal and the mounting through hole and protect the upper journal and the mounting through hole.
In some alternative embodiments, a limiting groove is formed between each outer bushing 7 and the corresponding compressor stator blade 2;
the outer wall of each inner bushing 6 is provided with a clamping edge, and each clamping edge is clamped into the corresponding limiting groove to prevent the inner bushing from falling off.
In some alternative embodiments, each outer bushing 7 has a limiting projection on its inner wall, which forms a limiting groove with the corresponding compressor stator blade 2.
In some alternative embodiments, each outer wall of the outer bush 7 has a connecting edge; each connecting edge is connected with the outer wall of the annular compressor casing 1.
The embodiments are described in a progressive manner in the specification, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
Having thus described the present application in connection with the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present application is not limited to those specific embodiments, and that equivalent modifications or substitutions of related technical features may be made by those skilled in the art without departing from the principle of the present application, and those modifications or substitutions will fall within the scope of the present application.
Claims (9)
1. The utility model provides a compressor stator blade linkage structure which characterized in that includes:
the annular compressor casing (1) is provided with a plurality of mounting through holes distributed along the circumferential direction;
a plurality of compressor stator blades (2) arranged in the annular compressor casing (2); the upper journal of each compressor stator blade (2) correspondingly penetrates through one mounting through hole;
the linkage ring (3) is sleeved on the annular compressor casing (1), and one side of the linkage ring is meshed with the upper journals of the compressor stator blades (2) through insections; the linkage ring (3) can rotate relative to the annular compressor casing (1) to drive each compressor stator blade (2) to synchronously rotate, and synchronous adjustment of the angle of each compressor stator blade (2) is realized.
2. The compressor stator vane linkage structure of claim 1,
further comprising:
and each bevel gear (4) is correspondingly arranged on the end face of one upper shaft neck and meshed with one side of the linkage ring (3) through insections.
3. The compressor stator vane linkage structure of claim 1,
one side of each bevel gear (4) is provided with a connecting hole;
the end face of each upper journal is provided with a connecting boss; each connecting boss is correspondingly inserted into one connecting hole.
4. The compressor stator vane linkage structure of claim 3,
the side wall of each connecting hole is provided with an anti-rotation through hole;
each connecting boss is provided with an anti-rotation hole;
further comprising:
and each anti-rotation pin (5) correspondingly penetrates through one anti-rotation through hole and is inserted into the corresponding anti-rotation hole.
5. The compressor stator vane linkage structure of claim 1,
further comprising:
a plurality of inner bushings (6), wherein each inner bushing (6) is sleeved on one upper shaft neck correspondingly.
6. The compressor stator vane linkage structure of claim 5,
further comprising:
and each outer bushing (7) is correspondingly arranged in one mounting through hole and is positioned outside the corresponding inner bushing (6).
7. The compressor stator vane linkage structure of claim 6,
a limiting groove is formed between each outer bushing (7) and the corresponding compressor stator blade (2);
the outer wall of each inner bushing (6) is provided with a clamping edge, and each clamping edge is clamped into a corresponding limiting groove.
8. The compressor stator vane linkage structure of claim 7,
the inner wall of each outer bushing (7) is provided with a limiting protrusion, and a limiting groove is formed between the limiting protrusion and the corresponding compressor stator blade (2).
9. The compressor stator vane linkage structure of claim 6,
the outer wall of each outer bushing (7) is provided with a connecting edge; each connecting edge is connected with the outer wall of the annular compressor casing (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010113668.2A CN111288020B (en) | 2020-02-24 | 2020-02-24 | Compressor stator blade linkage structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010113668.2A CN111288020B (en) | 2020-02-24 | 2020-02-24 | Compressor stator blade linkage structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111288020A true CN111288020A (en) | 2020-06-16 |
| CN111288020B CN111288020B (en) | 2021-05-28 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010113668.2A Active CN111288020B (en) | 2020-02-24 | 2020-02-24 | Compressor stator blade linkage structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111288020B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112476272A (en) * | 2020-11-17 | 2021-03-12 | 中国航发沈阳黎明航空发动机有限责任公司 | Fatigue performance assessment clamp structure for thin and thick adjustable blade of aero-engine |
| CN113202621A (en) * | 2021-06-14 | 2021-08-03 | 中国航发沈阳发动机研究所 | Stator blade rotation angle adjusting mechanism |
| CN113883090A (en) * | 2021-10-29 | 2022-01-04 | 中国航发沈阳发动机研究所 | Aero-engine stator blade rotation angle adjusting mechanism |
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| EP0909880A2 (en) * | 1997-10-14 | 1999-04-21 | General Electric Company | Turbine vane actuation system |
| JP2002115699A (en) * | 2000-08-31 | 2002-04-19 | General Electric Co <Ge> | Variable stationary blade assembly body |
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| US20050036885A1 (en) * | 2003-07-17 | 2005-02-17 | Snecma Moteurs | Guide system for the outer pivot of a variable stator vane, for a turbojet stator |
| CN103133423A (en) * | 2011-11-25 | 2013-06-05 | 中国航空工业集团公司沈阳发动机设计研究所 | Mandrel-type multi-stage adjustable blade joint debugging and actuating mechanism |
| CN204783125U (en) * | 2015-07-07 | 2015-11-18 | 中国航空工业集团公司沈阳发动机设计研究所 | Double metal bush |
| CN106089810A (en) * | 2016-06-21 | 2016-11-09 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of stator blade setting angle adjusting apparatus |
| CN106930965A (en) * | 2017-02-10 | 2017-07-07 | 中国航发沈阳发动机研究所 | A kind of Multi-angle corner size block |
| CN108953130A (en) * | 2018-07-10 | 2018-12-07 | 南京航空航天大学 | A kind of compressor stator blade fan-shaped section Quick Release housing device |
| CN208397006U (en) * | 2018-06-05 | 2019-01-18 | 中国航发沈阳发动机研究所 | A kind of stator blade regulating mechanism |
| CN109356671A (en) * | 2018-12-16 | 2019-02-19 | 中国航发沈阳发动机研究所 | A kind of adjustable stator blade angle adjusting mechanism |
-
2020
- 2020-02-24 CN CN202010113668.2A patent/CN111288020B/en active Active
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0909880A2 (en) * | 1997-10-14 | 1999-04-21 | General Electric Company | Turbine vane actuation system |
| JP2002115699A (en) * | 2000-08-31 | 2002-04-19 | General Electric Co <Ge> | Variable stationary blade assembly body |
| JP2004084572A (en) * | 2002-08-27 | 2004-03-18 | Mitsubishi Heavy Ind Ltd | Stationary blade structure of rotating machine |
| US20050036885A1 (en) * | 2003-07-17 | 2005-02-17 | Snecma Moteurs | Guide system for the outer pivot of a variable stator vane, for a turbojet stator |
| CN103133423A (en) * | 2011-11-25 | 2013-06-05 | 中国航空工业集团公司沈阳发动机设计研究所 | Mandrel-type multi-stage adjustable blade joint debugging and actuating mechanism |
| CN204783125U (en) * | 2015-07-07 | 2015-11-18 | 中国航空工业集团公司沈阳发动机设计研究所 | Double metal bush |
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| CN106930965A (en) * | 2017-02-10 | 2017-07-07 | 中国航发沈阳发动机研究所 | A kind of Multi-angle corner size block |
| CN208397006U (en) * | 2018-06-05 | 2019-01-18 | 中国航发沈阳发动机研究所 | A kind of stator blade regulating mechanism |
| CN108953130A (en) * | 2018-07-10 | 2018-12-07 | 南京航空航天大学 | A kind of compressor stator blade fan-shaped section Quick Release housing device |
| CN109356671A (en) * | 2018-12-16 | 2019-02-19 | 中国航发沈阳发动机研究所 | A kind of adjustable stator blade angle adjusting mechanism |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112476272A (en) * | 2020-11-17 | 2021-03-12 | 中国航发沈阳黎明航空发动机有限责任公司 | Fatigue performance assessment clamp structure for thin and thick adjustable blade of aero-engine |
| CN113202621A (en) * | 2021-06-14 | 2021-08-03 | 中国航发沈阳发动机研究所 | Stator blade rotation angle adjusting mechanism |
| CN113202621B (en) * | 2021-06-14 | 2022-04-01 | 中国航发沈阳发动机研究所 | Stator blade rotation angle adjusting mechanism |
| CN113883090A (en) * | 2021-10-29 | 2022-01-04 | 中国航发沈阳发动机研究所 | Aero-engine stator blade rotation angle adjusting mechanism |
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| Publication number | Publication date |
|---|---|
| CN111288020B (en) | 2021-05-28 |
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