CN112709716A - Compressor stator blade structure - Google Patents
Compressor stator blade structure Download PDFInfo
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- CN112709716A CN112709716A CN202011599817.7A CN202011599817A CN112709716A CN 112709716 A CN112709716 A CN 112709716A CN 202011599817 A CN202011599817 A CN 202011599817A CN 112709716 A CN112709716 A CN 112709716A
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- Prior art keywords
- arc
- stator blade
- section
- compressor
- compressor stator
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- 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
- F04D29/403—Casings; Connections of working fluid especially adapted for elastic fluid pumps
Abstract
The application belongs to compressor stator blade structural design field, concretely relates to compressor stator blade structure, include: the multiple sections of arc-shaped outer edge plates can be mutually spliced into an annular structure; the multiple sections of arc-shaped inner edge plates can be mutually spliced to form an annular structure; multiunit stator blade, every stator blade of group correspondence set up between one section arc outer fringe board, one section arc inner fringe board, wherein each stator blade's apex position integrated into one piece on the arc outer fringe board that corresponds, and blade root position integrated into one piece is on the arc inner fringe board that corresponds.
Description
Technical Field
The application belongs to the field of structural design of compressor stator blades, and particularly relates to a compressor stator blade structure.
Background
The stator blade has the outer flange plate in the welding of apex position mostly in the compressor to and have the inner flange plate in the welding of root position, assemble to compressor stator cartridge receiver in the draw-in groove of compressor stator cartridge receiver inner wall through with the outer flange plate, this kind of technical scheme has following defect:
1) the stator blade has more welding seams, so that stress concentration is easy to generate, and the stator blade structure is damaged;
2) the stator blades, the outer edge plate and the inner edge plate are welded at a high temperature, deformation is easy to occur, and the overall performance of the compressor is affected;
3) the requirement on the space of the outer edge plate and the space of the inner edge plate is high, enough axial dimension must be ensured to provide splicing welding space for the stator blade, and in the gas compressor needing gas entraining, the position of the edge plate is occupied for gas entraining, so that the mounting position of the stator blade is insufficient;
4) the stator blades and the corresponding outer edge plates and inner edge plates thereof are numerous, and the assembling process of the stator blades on the stator casing of the gas compressor is complicated and repeated.
The present application has been made in view of the above-mentioned technical drawbacks.
It should be noted that the above background disclosure is only for the purpose of assisting understanding of the inventive concept and technical solutions of the present invention, and does not necessarily belong to the prior art of the present patent application, and the above background disclosure should not be used for evaluating the novelty and inventive step of the present application without explicit evidence to suggest that the above content is already disclosed at the filing date of the present patent application.
Disclosure of Invention
The object of the present application is to provide a compressor stator vane arrangement 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 structure comprising:
the multiple sections of arc-shaped outer edge plates can be mutually spliced into an annular structure;
the multiple sections of arc-shaped inner edge plates can be mutually spliced to form an annular structure;
multiunit stator blade, every stator blade of group correspondence set up between one section arc outer fringe board, one section arc inner fringe board, wherein each stator blade's apex position integrated into one piece on the arc outer fringe board that corresponds, and blade root position integrated into one piece is on the arc inner fringe board that corresponds.
According to at least one embodiment of the application, in the compressor stator blade structure, the arc-shaped outer edge plates of the sections are coated with wear-resistant coatings.
According to at least one embodiment of the application, in the compressor stator blade structure, the adjacent arc-shaped outer edge plates in the annular structure can be spliced with each other to form inclined surface matching butt joint;
can be spliced mutually to form the matching butt joint of the inclined planes between the adjacent arc inner edge plates in the annular structure.
According to at least one embodiment of the application, in the compressor stator blade structure, the part of each stator blade in each group of stator blades, which protrudes out of the corresponding arc-shaped outer edge plate in the spanwise direction, is rounded.
According to at least one embodiment of the application, in the compressor stator blade structure, each stator blade in each group of stator blades is in rounded transition with the corresponding arc-shaped outer edge plate and the corresponding arc-shaped inner edge plate.
According to at least one embodiment of the application, in the compressor stator blade structure, the inner side of each section of the arc-shaped inner edge plate is provided with a sealing groove extending along the circumferential direction;
compressor stator blade structure still includes:
the multi-section honeycomb sealing sleeve is correspondingly arranged in one sealing groove.
According to at least one embodiment of the application, in the compressor stator blade structure, one end of each section of honeycomb sealing sleeve in the corresponding sealing groove is welded in an argon arc welding mode after being pressed and deformed.
Drawings
FIG. 1 is a partial schematic structural view of a compressor stator blade structure provided by an embodiment of the application;
FIG. 2 is a view in the direction A of FIG. 1;
FIG. 3 is a B-diagram of FIG. 1;
FIG. 4 is a partial schematic view of a compressor stator vane configuration provided by an embodiment of the present application;
wherein:
1-an arc-shaped outer edge plate; 2-arc inner edge plate; 3-stator blades; 4-a honeycomb sealing sleeve; 5-stop
Moving the strips; 6-stop block.
For the purpose of better illustrating the embodiments, certain features of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; further, the drawings are for illustrative purposes, and terms describing positional relationships are limited to illustrative illustrations only and are not to be construed as limiting the patent.
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 to 4.
A compressor stator vane structure comprising:
the multi-section arc-shaped outer edge plates 1 can be mutually spliced to form an annular structure;
the multi-section arc-shaped inner edge plates 2 can be mutually spliced to form an annular structure;
To the compressor stator blade structure disclosed in the above embodiment, a skilled person in the art can understand that each group of stator blades 3 is designed to be arranged between one section of arc-shaped outer edge plate 1 and one section of arc-shaped inner edge plate 2, wherein each stator blade 3 and the corresponding arc-shaped outer edge plate 1 and the corresponding arc-shaped inner edge plate 2 are integrally formed, and the whole structure is a fan-shaped structure.
For the compressor stator blade structure disclosed in the above embodiment, as can be understood by those skilled in the art, each stator blade 3 in each group of stator blades 3 is integrally formed with the corresponding arc-shaped outer edge plate 1 and the corresponding arc-shaped inner edge plate 2, so that a non-existent weld does not generate corresponding stress concentration, and is not easily damaged.
For the stator blade structure of the air compressor disclosed in the above embodiment, as can be understood by those skilled in the art, when the stator blade structure is processed, the arc-shaped outer edge plate 1, the arc-shaped inner edge plate 2 and the stator blade 3 thereof can be machined in a form of a whole ring, and then the arc-shaped outer edge plate, the arc-shaped inner edge plate 2 and the stator blade 3 thereof are cut and divided into a plurality of fan-shaped structures, so that the process does not involve welding, the arc-shaped outer edge plate 1 cannot be affected by high temperature to deform, the overall performance of the air compressor can be effectively ensured, and in addition, the arc-shaped outer edge plate 1 can have a larger containment degree for the stator blade 3, so that the installation position of the stator blade.
In some alternative embodiments, in the compressor stator blade structure, the arc-shaped outer edge plates 1 of the segments are coated with wear-resistant coatings, and particularly, the wear-resistant coatings can be coated only on the contact parts of the arc-shaped outer edge plates and the compressor stator casing to avoid abrasion.
In some optional embodiments, in the compressor stator blade structure, the adjacent arc-shaped outer edge plates 1 in the annular structure can be spliced with each other to form an inclined surface matching butt joint;
can splice each other for inclined plane cooperation butt joint between adjacent arc inner flange board 2 in the annular structure.
To the compressor stator blade structure disclosed in the above embodiment, a person skilled in the art can understand that the design can splice each other for inclined plane cooperation butt joint between adjacent arc outer flange plates 1 in the annular structure, and the design can splice each other for inclined plane cooperation butt joint between adjacent arc inner flange plates 2 in the annular structure, when will add out arc outer flange plates 1 with the form machine of whole ring promptly, arc inner flange plates 2 and its stator blade 3 cutting are cut apart into a plurality of fan-shaped structures, certain angle of cutting position slope, thereby can avoid cutting stator blade 3, with this avoid causing the damage to stator blade 3.
In some alternative embodiments, in the compressor stator blade structure, the portion of each stator blade 3 in each set of stator blades 3 protruding from the corresponding arc-shaped outer edge plate 1 along the spanwise direction is rounded.
For the compressor stator blade structure disclosed in the above embodiment, those skilled in the art can understand that the compressor stator blade structure has a larger accommodation degree for the size C in fig. 2, and by changing the size C, a larger range of the width of the ring groove bleed air groove can be realized, and the bleed air function is ensured.
In some alternative embodiments, in the compressor stator blade structure, each stator blade 3 in each set of stator blades 3 is in rounded transition with the corresponding arc-shaped outer edge plate 1 and the corresponding arc-shaped inner edge plate 2.
In some alternative embodiments, in the compressor stator blade structure, the inner side of each section of the arc-shaped inner edge plate 2 is provided with a sealing groove extending along the circumferential direction;
compressor stator blade structure still includes:
and a plurality of sections of honeycomb sealing sleeves 4 are correspondingly arranged in one sealing groove.
In some optional embodiments, in the above compressor stator blade structure, each section of the honeycomb sealing sleeve 4 is welded by argon arc welding after one end of the honeycomb sealing sleeve is pressed and deformed in the corresponding sealing groove, so as to realize positioning and stopping of each honeycomb sealing sleeve 4.
In some optional embodiments, the compressor stator casing is of a split structure, the arc-shaped outer edge plate 1 on one side of the split installation edge of the compressor stator casing is provided with a stop block 6, the arc-shaped outer edge plate 1 on the other side of the split installation edge of the compressor stator casing is provided with a stop groove, the compressor stator casing is provided with a stop strip 5, the stop strip 5 is clamped in the stop groove, in the working process of the compressor, the arc-shaped outer edge plate 1 provided with the stop block 6 generates a movement trend towards the arc-shaped outer edge plate 1 with the stop groove, and the stop block 6 and the stop strip 5 are matched to play a circumferential stop role.
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 (7)
1. A compressor stator vane structure, comprising:
the multi-section arc-shaped outer edge plates (1) can be mutually spliced into an annular structure;
the multi-section arc-shaped inner edge plates (2) can be mutually spliced to form an annular structure;
multiunit stator blade (3), every group stator blade (3) correspond one section arc outer fringe board (1), one section set up between arc inner fringe board (2), the apex position integrated into one piece of each stator blade (3) wherein on the arc outer fringe board (1) that corresponds, root position integrated into one piece is on the arc inner fringe board (2) that corresponds.
2. Compressor stator vane arrangement according to claim 1,
each section of arc-shaped outer edge plate (1) is sprayed with a wear-resistant coating.
3. Compressor stator vane arrangement according to claim 1,
can be mutually spliced into the inclined plane matching butt joint between adjacent arc-shaped outer edge plates (1) in an annular structure;
can splice each other for inclined plane cooperation butt joint between adjacent arc inner flange board (2) in the annular structure.
4. Compressor stator vane arrangement according to claim 1,
and rounding the parts of the stator blades (3) in each group of the stator blades (3) which protrude from the corresponding arc-shaped outer edge plate (1) along the spanwise direction of the stator blades.
5. Compressor stator vane arrangement according to claim 1,
and each stator blade (3) in each group of stator blades (3) is in radius transition with the corresponding arc-shaped outer edge plate (1) and the corresponding arc-shaped inner edge plate (2).
6. Compressor stator vane arrangement according to claim 1,
the inner side of each section of the arc-shaped inner edge plate (2) is provided with a sealing groove extending along the circumferential direction;
the compressor stator blade structure further comprises:
and each section of honeycomb sealing sleeve (4) is correspondingly arranged in one sealing groove.
7. Compressor stator vane arrangement according to claim 6,
and one end of each section of the honeycomb sealing sleeve (4) in the corresponding sealing groove is pressed and deformed and then is welded by argon arc welding.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011599817.7A CN112709716A (en) | 2020-12-29 | 2020-12-29 | Compressor stator blade structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011599817.7A CN112709716A (en) | 2020-12-29 | 2020-12-29 | Compressor stator blade structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112709716A true CN112709716A (en) | 2021-04-27 |
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ID=75546760
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011599817.7A Pending CN112709716A (en) | 2020-12-29 | 2020-12-29 | Compressor stator blade structure |
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| CN (1) | CN112709716A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113847276A (en) * | 2021-09-27 | 2021-12-28 | 中国航发沈阳发动机研究所 | Compressor stator blade and stator structure thereof |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH1061405A (en) * | 1996-08-22 | 1998-03-03 | Hitachi Ltd | Stationary blade of axial flow turbo machine |
| US20100158685A1 (en) * | 2008-12-22 | 2010-06-24 | Techspace Aero S.A | Guide Vane Architecture |
| CN103097668A (en) * | 2010-10-29 | 2013-05-08 | 三菱重工业株式会社 | Turbine and method for manufacturing turbine |
| US20130149136A1 (en) * | 2011-12-12 | 2013-06-13 | Tsuguhisa Tashima | Stationary blade cascade, assembling method of stationary blade cascade, and steam turbine |
| WO2016207942A1 (en) * | 2015-06-22 | 2016-12-29 | 三菱日立パワーシステムズ株式会社 | Stator-vane segment and axial-flow fluid machine provided with same |
| CN206000582U (en) * | 2016-08-02 | 2017-03-08 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of removable honeycomb ring structure |
| CN206889026U (en) * | 2017-06-30 | 2018-01-16 | 常州市三维技术成套设备有限公司 | A kind of steam turbine stator blade |
| CN111561480A (en) * | 2020-05-14 | 2020-08-21 | 中国航发沈阳发动机研究所 | Stator structure |
-
2020
- 2020-12-29 CN CN202011599817.7A patent/CN112709716A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH1061405A (en) * | 1996-08-22 | 1998-03-03 | Hitachi Ltd | Stationary blade of axial flow turbo machine |
| US20100158685A1 (en) * | 2008-12-22 | 2010-06-24 | Techspace Aero S.A | Guide Vane Architecture |
| CN103097668A (en) * | 2010-10-29 | 2013-05-08 | 三菱重工业株式会社 | Turbine and method for manufacturing turbine |
| US20130149136A1 (en) * | 2011-12-12 | 2013-06-13 | Tsuguhisa Tashima | Stationary blade cascade, assembling method of stationary blade cascade, and steam turbine |
| WO2016207942A1 (en) * | 2015-06-22 | 2016-12-29 | 三菱日立パワーシステムズ株式会社 | Stator-vane segment and axial-flow fluid machine provided with same |
| CN206000582U (en) * | 2016-08-02 | 2017-03-08 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of removable honeycomb ring structure |
| CN206889026U (en) * | 2017-06-30 | 2018-01-16 | 常州市三维技术成套设备有限公司 | A kind of steam turbine stator blade |
| CN111561480A (en) * | 2020-05-14 | 2020-08-21 | 中国航发沈阳发动机研究所 | Stator structure |
Non-Patent Citations (1)
| Title |
|---|
| 张启运 等: "《钎焊手册》", 30 November 1998, 机械工业出版社 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113847276A (en) * | 2021-09-27 | 2021-12-28 | 中国航发沈阳发动机研究所 | Compressor stator blade and stator structure thereof |
| CN113847276B (en) * | 2021-09-27 | 2023-09-05 | 中国航发沈阳发动机研究所 | Stator blade of air compressor and stator structure thereof |
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Application publication date: 20210427 |
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