CN112628206A - Air entraining structure of air compressor - Google Patents
Air entraining structure of air compressor Download PDFInfo
- Publication number
- CN112628206A CN112628206A CN202011469299.7A CN202011469299A CN112628206A CN 112628206 A CN112628206 A CN 112628206A CN 202011469299 A CN202011469299 A CN 202011469299A CN 112628206 A CN112628206 A CN 112628206A
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- China
- Prior art keywords
- stage
- casing
- bleed air
- air
- air guide
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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
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
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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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
- F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
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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
- F01D25/12—Cooling
-
- 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
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
- F04D29/324—Blades
-
- 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
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
A compressor bleed air arrangement comprising: 0-9 stage stator vanes; 1-10 stages of rotor blades; the front casing is coated with 0 th-6 th-stage stator blades and 1 st-6 th-stage rotor blades and is provided with a sixth-stage air guide hole; the middle casing wraps the 7 th-8 th-stage stator blade and the 7 th-8 th-stage rotor blade, a sixth-stage air-entraining passage is arranged between the middle casing and the front casing, and the outer wall of the middle casing is provided with a connecting edge; the inner ring is connected with the connecting edge, the outer ring is connected with the front casing, and a sixth-stage bleed air cavity communicated with the sixth-stage bleed air hole and the sixth-stage bleed air channel is formed; the rear casing is used for coating the 9 th-stage stator blade and the 9 th-10 th-stage rotor blade, and an eighth-stage air guide channel is formed between the rear casing and the middle casing; the extension casing is sleeved on the periphery of the rear casing, is connected with the outer ring of the connecting ring and is provided with an eighth-stage air guide hole; and the inner ring of the support ring is connected with the rear casing, the outer ring of the support ring is connected with the extension casing, and an eighth-stage air guide cavity communicated with the eighth-stage air guide hole and the eighth-stage air guide channel is formed.
Description
Technical Field
The application belongs to the technical field of air compressor air entraining design, and particularly relates to an air compressor air entraining structure.
Background
In an aircraft engine, air is required to be introduced from compressed air to cool high-temperature components and seal a fulcrum structure.
With the development of the technology, the requirement of the compressor for multi-stage air entraining is generated, and the multi-stage air entraining of the compressor is difficult to realize due to the limitation of the structure, the outline and the axial dimension space of the existing compressor.
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 purpose of the present application is to provide a compressor bleed air arrangement that overcomes or alleviates at least one of the technical deficiencies known to exist.
The technical scheme of the application is as follows:
a compressor bleed air arrangement comprising:
0-9 stage stator vanes;
1-10 stages of rotor blades and 0-9 stages of stator blades are distributed at intervals;
the front casing is coated with 0 th-6 th-stage stator blades and 1 st-6 th-stage rotor blades and is provided with a sixth-stage air guide hole;
the middle casing wraps the 7 th-8 th-stage stator blade and the 7 th-8 th-stage rotor blade, a sixth-stage air-entraining passage is arranged between the middle casing and the front casing, and the outer wall of the middle casing is provided with a connecting edge;
the inner ring is connected with the connecting edge, the outer ring is connected with the front casing, and a sixth-stage air guide cavity is formed between the outer ring and the front casing and between the outer ring and the middle casing; the sixth-stage bleed air cavity is communicated with the sixth-stage bleed air hole and the sixth-stage bleed air channel;
the rear casing is used for coating the 9 th-stage stator blade and the 9 th-10 th-stage rotor blade, and an eighth-stage air guide channel is formed between the rear casing and the middle casing;
the extension casing is sleeved on the periphery of the rear casing, is connected with the outer ring of the connecting ring and is provided with an eighth-stage air guide hole;
the inner ring of the support ring is connected with the rear casing, the outer ring of the support ring is connected with the extension casing, and an eighth-stage air guide cavity is formed among the support ring, the middle casing, the connecting ring, the rear casing and the extension casing; the eighth-stage air guide cavity is communicated with the eighth-stage air guide hole and the eighth-stage air guide channel.
According to at least one embodiment of the application, in the bleed air structure of the compressor, the front casing is a two-half split casing, wherein one half is integrally formed with part of the 0 th-5 th stage stator blades, and the other half is integrally formed with the other rest part of the 0 th-5 th stage stator blades.
According to at least one embodiment of the application, in the air compressor air entraining structure, the inner wall of the front casing is provided with a sixth-stage annular clamping groove; the blade tip of the 6 th stage stator blade is clamped in the sixth stage annular clamping groove.
According to at least one embodiment of the application, in the bleed air structure of the compressor, the intermediate casing is a two-half split casing, wherein one half is integrally formed with part of the 7 th stage stator blade, and the other half is integrally formed with the other remaining part of the 7 th stage stator blade.
According to at least one embodiment of the application, in the air compressor air entraining structure, the inner wall of the middle casing is provided with an eighth-stage annular clamping groove; and the blade tip of the 8 th stage stator blade is clamped in the eighth stage annular clamping groove.
According to at least one embodiment of the application, in the compressor bleed air structure, the connecting edge is located in the middle of the middle casing.
According to at least one embodiment of the application, in the bleed air structure of the compressor, the rear casing is a two-half split casing, wherein one half is integrally formed with part of the 9 th stage stator blade, and the other half is integrally formed with the rest of the 9 th stage stator blade.
According to at least one embodiment of the application, in the compressor bleed air structure, the extension casing is a two-half split casing.
According to at least one embodiment of the present application, the above compressor bleed air structure further includes:
and the inlet of the sixth-stage air guide pipe is communicated with the sixth-stage air guide hole.
According to at least one embodiment of the present application, the above compressor bleed air structure further includes:
and the inlet of the eighth stage bleed air pipe is communicated with the eighth stage bleed air hole.
Drawings
FIG. 1 is a schematic diagram of a compressor bleed air structure provided by an embodiment of the application;
FIG. 2 is a schematic diagram of a part of structure of a bleed air structure of a compressor provided by an embodiment of the application;
FIG. 3 is a schematic diagram of another part of the structure of a bleed air structure of the compressor provided by the embodiment of the application;
FIG. 4 is a schematic diagram of a partial structure of a bleed air structure of the compressor provided by the embodiment of the application;
wherein:
1-stator blade; 2-rotor blades; 3-front case; 4-an intermediate case; 5-connecting rings; 6-rear case; 7-extension case; 8-a support ring; 9-a sixth stage bleed air pipe; 10-tenth stage bleed air pipe;
0S-stage 0 stator vane; 1S-stage 1 stator blade; 2S-stage 2 stator vane; 3S-3 rd stage stator blade; 4S-stage 4 stator vane; 5S-stage 5 stator blade; 6S-stage 6 stator blade; 7S-stage 7 stator blade; 8S-stage 8 stator vane; 9S-stage 9 stator vane;
1R-stage 1 rotor blade; 2R-2 nd stage rotor blades; 3R-3 rd stage rotor blade; 4R-4 th stage rotor blade; 5R-5 th stage rotor blade; 6R-6 th stage rotor blade; 7R-7 th stage rotor blade; 8R-8 th stage rotor blade; 9R-9 th stage rotor blade; 10R-10 th stage rotor blade.
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 bleed air arrangement comprising:
0-9 stage stator vanes 1;
1-10 stages of rotor blades 2 are distributed at intervals with 0-9 stages of stator blades 1;
the front casing 3 is coated with 0 th-6 th-stage stator blades 1 and 1 st-6 th-stage rotor blades 2 and is provided with a sixth-stage air guide hole;
the middle casing 4 coats the 7 th-8 th-stage stator blade 1 and the 7 th-8 th-stage rotor blade 2, a sixth-stage air-entraining passage is arranged between the middle casing and the front casing 3, and the outer wall of the middle casing is provided with a connecting edge;
the inner ring is connected with the connecting edge, the outer ring is connected with the front casing 3, and a sixth-level air guide cavity is formed between the outer ring and the front casing 3 and between the outer ring and the middle casing 4; the sixth-stage bleed air cavity is communicated with the sixth-stage bleed air hole and the sixth-stage bleed air channel;
the rear casing 6 is used for coating the 9 th-stage stator blade 1 and the 9 th-10 th-stage rotor blade 2, and an eighth-stage air guide channel is arranged between the rear casing and the middle casing 4;
the extension casing 7 is sleeved on the periphery of the rear casing 6, is connected with the outer ring of the connecting ring 5 and is provided with an eighth-stage air guide hole;
the inner ring of the support ring 8 is connected with the rear casing 6, the outer ring of the support ring is connected with the extension casing 7, and an eighth-stage air guide cavity is formed among the support ring, the middle casing 4, the connecting ring 5, the rear casing 6 and the extension casing 7; the eighth-stage air guide cavity is communicated with the eighth-stage air guide hole and the eighth-stage air guide channel.
For the air entraining structure of the air compressor disclosed in the above embodiment, as can be understood by those skilled in the art, the air after the 6 th-stage stator blade 1 can be introduced into the sixth-stage air entraining cavity through the sixth-stage air entraining hole and then is introduced out through the sixth-stage air entraining hole, and the air after the 8 th-stage stator blade 1 can be introduced into the eighth-stage air entraining cavity through the eighth-stage air entraining hole and then is introduced out through the eighth-stage air entraining hole, so that the two-stage air entraining of the air compressor is realized, and the air entraining efficiency is high.
For the air compressor bleed air structure disclosed in the above embodiment, it can be understood by those skilled in the art that the structure of the components is compact, the structure of the air compressor is slightly changed, and the multistage air bleed of the air compressor can be realized under the condition of the limitation of the outline and the axial dimension space of the air compressor.
In some alternative embodiments, in the above-mentioned compressor bleed air structure, the front casing 3 is a two-half split casing, wherein one half is integrally formed with a part of the 0-5 th stage stator blades 1, and the other half is integrally formed with the other remaining part of the 0-5 th stage stator blades.
In some optional embodiments, in the above compressor bleed air structure, the inner wall of the front casing 3 has a sixth stage of annular clamping groove; the blade tip of the 6 th stage stator blade is clamped in the sixth stage annular clamping groove.
In some alternative embodiments, in the above-mentioned compressor bleed air structure, the intermediate casing 4 is a two-half split casing, wherein one half is integrally formed with a part of the 7 th stage stator blade 1, and the other half is integrally formed with the other remaining part of the 7 th stage stator blade 1.
In some optional embodiments, in the above compressor bleed air structure, the inner wall of the intermediate casing 4 has an eighth-stage annular clamping groove; and the blade tip of the 8 th stage stator blade is clamped in the eighth stage annular clamping groove.
In some optional embodiments, in the above-mentioned compressor bleed air structure, the connecting edge is located in the middle of the middle casing 3, and on one hand, the connecting edge can be used as a partition part of the sixth-stage bleed air cavity and the eighth-stage bleed air cavity, and on the other hand, a cantilever structure can be prevented from being formed on the middle casing 3, so that the stress is reasonable.
In some alternative embodiments, in the above-mentioned compressor bleed air structure, the outer wall of the intermediate casing 3 is provided with a reinforcing rib to increase the rigidity thereof.
In some alternative embodiments, in the above-mentioned compressor bleed air structure, the rear casing 6 is a two-half split casing, wherein one half is integrally formed with a part of the 9 th stage stator blade 1, and the other half is integrally formed with the remaining part of the 9 th stage stator blade 1.
For the air compressor air-entraining structure disclosed in the above embodiment, it can be understood by those skilled in the art that the front casing 3, the middle casing 4, and the rear casing 6 are designed to be two-half split structures and are integrally formed with the stator blade of the corresponding stage, so as to ensure the machining precision and facilitate the assembly.
In some alternative embodiments, the compressor bleed air structure described above, the extension casing 7 is a split casing in two halves to facilitate assembly.
In some optional embodiments, the compressor bleed air structure further includes:
and the inlet of the sixth-stage air-entraining pipe 9 is communicated with the sixth-stage air-entraining hole, and the outlet of the sixth-stage air-entraining pipe is extended to the high-temperature component or the fulcrum structure, so that the high-temperature component can be cooled or the fulcrum structure can be sealed.
In some optional embodiments, the compressor bleed air structure further includes:
eighth level bleed air pipe 10, entry and eighth level bleed air hole intercommunication, the export extends to high temperature component or fulcrum structure to can realize cooling the high temperature component or seal the fulcrum structure.
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 (10)
1. A compressor bleed air structure, comprising:
0-9 stage stator blades (1);
1-10 stages of rotor blades (2) and 0-9 stages of stator blades (1) are distributed at intervals;
the front casing (3) is coated with 0 th-6 th-stage stator blades (1) and 1 st-6 th-stage rotor blades (2) and is provided with a sixth-stage air guide hole;
the middle casing (4) coats the 7 th-8 th-stage stator blade (1) and the 7 th-8 th-stage rotor blade (2), a sixth-stage air-entraining passage is arranged between the middle casing and the front casing (3), and the outer wall of the middle casing is provided with a connecting edge;
the inner ring is connected with the connecting edge, the outer ring is connected with the front casing (3), and a sixth-stage air guide cavity is formed between the outer ring and the front casing (3) and between the outer ring and the middle casing (4); the sixth-stage bleed air cavity is communicated with the sixth-stage bleed air hole and the sixth-stage bleed air channel;
the rear casing (6) is used for coating the 9 th-stage stator blade (1) and the 9 th-10 th-stage rotor blade (2), and an eighth-stage air guide channel is arranged between the rear casing and the middle casing (4);
the extension casing (7) is sleeved on the periphery of the rear casing (6), is connected with the outer ring of the connecting ring (5), and is provided with an eighth-stage air guide hole;
the inner ring of the support ring (8) is connected with the rear casing (6), the outer ring of the support ring is connected with the extension casing (7), and an eighth-stage air guide cavity is formed among the support ring, the middle casing (4), the connecting ring (5), the rear casing (6) and the extension casing (7); the eighth-stage air guide cavity is communicated with the eighth-stage air guide hole and the eighth-stage air guide channel.
2. The compressor bleed air structure of claim 1,
the front casing (3) is a two-half split casing, wherein one half is integrally formed with part of the 0 th-5 th stage stator blades (1), and the other half is integrally formed with the other part of the 0 th-5 th stage stator blades.
3. The compressor bleed air structure of claim 2,
the inner wall of the front casing (3) is provided with a sixth-stage annular clamping groove; the blade tip of the 6 th stage stator blade is clamped in the sixth stage annular clamping groove.
4. The compressor bleed air structure of claim 1,
the middle casing (4) is a two-half split casing, wherein one half is integrally formed with part of the 7 th-stage stator blade (1), and the other half is integrally formed with the other rest part of the 7 th-stage stator blade (1).
5. The compressor bleed air structure of claim 4,
the inner wall of the middle casing (4) is provided with an eighth-stage annular clamping groove; and the blade tip of the 8 th stage stator blade is clamped in the eighth stage annular clamping groove.
6. The compressor bleed air structure of claim 4,
the connecting edge is positioned in the middle of the middle casing (3).
7. The compressor bleed air structure of claim 1,
the rear casing (6) is a two-half split casing, wherein one half is integrally formed with part of the 9 th-stage stator blade (1), and the other half is integrally formed with the rest part of the 9 th-stage stator blade (1).
8. The compressor bleed air structure of claim 1,
the extension casing (7) is a two-half split casing.
9. The compressor bleed air structure of claim 1,
further comprising:
and the inlet of the sixth-stage air guide pipe (9) is communicated with the sixth-stage air guide hole.
10. The compressor bleed air structure of claim 1,
further comprising:
and the inlet of the eighth stage bleed air pipe (10) is communicated with the eighth stage bleed air hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011469299.7A CN112628206A (en) | 2020-12-15 | 2020-12-15 | Air entraining structure of air compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011469299.7A CN112628206A (en) | 2020-12-15 | 2020-12-15 | Air entraining structure of air compressor |
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| Publication Number | Publication Date |
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| CN112628206A true CN112628206A (en) | 2021-04-09 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011469299.7A Pending CN112628206A (en) | 2020-12-15 | 2020-12-15 | Air entraining structure of air compressor |
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| CN (1) | CN112628206A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114233685A (en) * | 2021-12-21 | 2022-03-25 | 中国航发沈阳发动机研究所 | Four-stage compressor casing structure |
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| CN112065774A (en) * | 2020-09-15 | 2020-12-11 | 中国航发沈阳发动机研究所 | Cartridge receiver structure and rotor-stator structure thereof |
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| US20170175750A1 (en) * | 2015-12-22 | 2017-06-22 | General Electric Company | Method and system for varying tip clearance gap using an actuated shroud |
| CN106194846A (en) * | 2016-07-12 | 2016-12-07 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of double-layered case structure compressor and there is its aero-engine |
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