阅读说明：本技术 压气机引气结构 (Air-entraining structure of air compressor ) 是由 张新强 韩方军 张征 王�华 张鑫 于 2020-12-15 设计创作，主要内容包括：一种压气机引气结构,包括：0-9级静子叶片；1-10级转子叶片；前机匣,具有第六级引气孔；第七级机匣,与前机匣之间具有第六级引气道；第八级机匣,与第七级机匣对接；连接机匣,与第八级机匣对接,外壁具有连接边；延伸机匣,具有第八级引气孔,套设在连接边外周,内壁与连接边连接,与前机匣对接,与前机匣、第七级机匣、第八级机匣、连接机匣之间形成有与第六级引气孔、第六级引气道连通的第六级引气腔；第九级机匣,与连接机匣之间具有第八级引气道；后机匣,外壁具有支撑边；支撑边与延伸机匣连接；后机匣与连接机匣、延伸机匣、第九级机匣之间形成有与第八级引气孔、第八级引气道连通的第八级引气腔。(A compressor bleed air arrangement comprising: 0-9 stage stator vanes; 1-10 stages of rotor blades; the front casing is provided with a sixth-stage air guide hole; a sixth-stage air guide channel is arranged between the seventh-stage casing and the front casing; the eighth-stage casing is butted with the seventh-stage casing; the connecting casing is butted with the eighth-stage casing, and the outer wall of the connecting casing is provided with a connecting edge; the extension casing is provided with an eighth-stage air guide hole which is sleeved on the periphery of the connecting edge, the inner wall of the extension casing is connected with the connecting edge and is butted with the front casing, and a sixth-stage air guide cavity communicated with the sixth-stage air guide hole and the sixth-stage air guide channel is formed among the extension casing, the front casing, the seventh-stage casing, the eighth-stage casing and the connecting casing; the ninth-stage casing is connected with the casing, and an eighth-stage air guide channel is formed between the ninth-stage casing and the connecting casing; the outer wall of the rear casing is provided with a supporting edge; the supporting edge is connected with the extension casing; and an eighth-stage bleed air cavity communicated with the eighth-stage bleed air hole and the eighth-stage bleed air channel is formed among the rear casing, the connecting casing, the extending casing and the ninth-stage casing.)

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 seventh-stage casing (4) coats the 7 th-stage rotor blade (2), and a sixth-stage air guide channel is arranged between the seventh-stage casing (4) and the front casing (3);

the eighth-stage casing (5) is wrapped on the 7 th-stage stator blade (1) and the 8 th-stage rotor blade (2) and is butted with the seventh-stage casing (4);

the connecting casing (6) wraps the 8 th-stage stator blade (1) and is in butt joint with the eighth-stage casing (5), and the outer wall of the connecting casing is provided with a connecting edge;

the extension casing (7) is provided with an eighth-stage air guide hole which is sleeved on the periphery of the connecting edge, the inner wall of the extension casing is connected with the connecting edge and is butted with the front casing (3), and a sixth-stage air guide cavity is formed among the extension casing, the front casing (3), the seventh-stage casing (4), the eighth-stage casing (5) and the connecting casing (6); the sixth-stage bleed air cavity is communicated with the sixth-stage bleed air hole and the sixth-stage bleed air channel;

the ninth-stage casing (8) wraps the 8 th-stage rotor blade (2), and an eighth-stage air guide channel is arranged between the ninth-stage casing (8) and the connecting casing (6);

the rear casing (9) is used for coating the 9 th-stage stator blade (1) and the 10 th-stage rotor blade (2), and the outer wall of the rear casing is provided with a supporting edge; the supporting edge is connected with an extension casing (7); an eighth-stage air guide cavity is formed among the rear casing (9), the connecting casing (6), the extending casing (7) and the ninth-stage casing (8); 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,

a seventh-stage annular clamping groove is formed between one end, facing the eighth-stage casing (5), of the seventh-stage casing (4) and the eighth-stage casing (5); the blade tip of the 7 th stage stator blade (1) is clamped in the seventh stage annular clamping groove.

5. The compressor bleed air structure of claim 1,

an eighth-stage annular clamping groove is formed between one end, facing the connecting casing (6), of the eighth-stage casing (5) and the connecting casing (6); the blade tip of the 8 th stage stator blade (1) is clamped in the eighth stage annular clamping groove.

6. The compressor bleed air structure of claim 1,

the extension casing (7) is a two-half split casing.

7. The compressor bleed air structure of claim 1,

a ninth-stage annular clamping groove is formed between one end, facing the rear casing (9), of the ninth-stage casing (8) and the rear casing (9); the blade tip of the 9 th stage stator blade (1) is clamped in the ninth stage annular clamping groove.

8. The compressor bleed air structure of claim 1,

further comprising:

and the inlet of the sixth-stage air guide pipe (10) is communicated with the sixth-stage air guide hole.

9. The compressor bleed air structure of claim 1,

further comprising:

and the inlet of the eighth stage bleed air pipe (11) is communicated with the eighth stage bleed air hole.

10. The compressor bleed air structure of claim 1,

the part of the inner wall of the seventh-stage casing (4) facing the 7 th-stage rotor blade (2) is coated with a wear-resistant coating;

the part of the inner wall of the eighth-stage casing (5) facing the 8 th-stage rotor blade (2) is coated with a wear-resistant coating;

the part of the inner wall of the ninth-stage casing (8) facing the 9 th-stage rotor blade (2) is coated with a wear-resistant coating;

the part of the inner wall of the rear casing (9) facing the 10 th-stage rotor blade (2) is coated with a wear-resistant coating.

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 seventh-stage casing wraps the 7 th-stage rotor blade, and a sixth-stage air guide channel is arranged between the seventh-stage casing and the front casing;

the eighth-stage casing wraps the 7 th-stage stator blade and the 8 th-stage rotor blade and is in butt joint with the seventh-stage casing;

the connecting casing wraps the 8 th-stage stator blade and is butted with the eighth-stage casing, and the outer wall of the connecting casing is provided with a connecting edge;

the extension casing is provided with an eighth-stage air guide hole which is sleeved on the periphery of the connecting edge, the inner wall of the extension casing is connected with the connecting edge and is butted with the front casing, and a sixth-stage air guide cavity is formed among the extension casing, the front casing, the seventh-stage casing, the eighth-stage casing and the connecting casing; the sixth-stage bleed air cavity is communicated with the sixth-stage bleed air hole and the sixth-stage bleed air channel;

the ninth-stage casing wraps the 8 th-stage rotor blade, and an eighth-stage air guide channel is arranged between the ninth-stage casing and the connecting casing;

the rear casing is used for coating the 9 th-stage stator blade and the 10 th-stage rotor blade, and the outer wall of the rear casing is provided with a supporting edge; the supporting edge is connected with the extension casing; an eighth-stage air guide cavity is formed among the rear casing, the connecting casing, the extending casing and the ninth-stage 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, a seventh-stage annular clamping groove is formed between one end, facing the eighth-stage casing, of the seventh-stage casing and the eighth-stage casing; the blade tip of the 7 th stage stator blade is clamped in the seventh stage annular clamping groove.

According to at least one embodiment of the application, in the bleed structure of the compressor, an eighth-stage annular clamping groove is formed between one end, facing the connecting casing, of the eighth-stage casing and the connecting casing; 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 extension casing is a two-half split casing.

According to at least one embodiment of the application, in the bleed structure of the compressor, a ninth-stage annular clamping groove is formed between one end, facing the rear casing, of the ninth-stage casing and the rear casing; the blade tip of the 9 th stage stator blade is clamped in the ninth stage annular clamping groove.

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.

According to at least one embodiment of the application, in the air compressor bleed structure, a wear-resistant coating is coated on a part, facing the 7 th-stage rotor blade, of the inner wall of the seventh-stage casing;

the part of the inner wall of the eighth-stage casing, which is opposite to the 8 th-stage rotor blade, is coated with a wear-resistant coating;

the part of the inner wall of the ninth-stage casing, which is opposite to the 9 th-stage rotor blade, is coated with a wear-resistant coating;

and the part of the inner wall of the rear casing, which is opposite to the 10 th-stage rotor blade, is coated with a wear-resistant coating.

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 illustration of a seventh stage casing provided by an embodiment of the present application;

FIG. 3 is a schematic view of an eighth stage casing provided in embodiments of the present application;

FIG. 4 is a schematic view of a connecting case provided by an embodiment of the present application;

FIG. 5 is a schematic view of an extended case provided by an embodiment of the present application;

FIG. 6 is a schematic illustration of a ninth stage casing provided in accordance with an embodiment of the present application;

FIG. 7 is a schematic illustration of an aft case provided by an embodiment of the present application;

wherein:

1-stator blade; 2-rotor blades; 3-front case; 4-seventh stage case; 5-eighth stage case; 6-connecting a casing; 7-extension case; 8-ninth stage case; 9-rear case; 10-a sixth stage bleed air pipe; 11-an eighth stage bleed air pipe;

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 7.

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 seventh-stage casing 4 coats the 7 th-stage rotor blade 2 and is provided with a sixth-stage air guide channel with the front casing 3;

the eighth-stage casing 5 is wrapped with the 7 th-stage stator blade 1 and the 8 th-stage rotor blade 2 and is butted with the seventh-stage casing 4;

the connecting casing 6 wraps the 8 th-stage stator blade 1 and is in butt joint with the eighth-stage casing 5, and the outer wall of the connecting casing is provided with a connecting edge;

the extension casing 7 is provided with an eighth-stage air guide hole, is sleeved on the periphery of the connecting edge, is connected with the connecting edge at the inner wall, is butted with the front casing 3, and forms a sixth-stage air guide cavity among the front casing 3, the seventh-stage casing 4, the eighth-stage casing 5 and the connecting casing 6; the sixth-stage bleed air cavity is communicated with the sixth-stage bleed air hole and the sixth-stage bleed air channel;

the ninth-stage casing 8 covers the 8 th-stage rotor blade 2, and an eighth-stage air guide channel is arranged between the ninth-stage casing 8 and the connecting casing 6;

the rear casing 9 coats the 9 th-stage stator blade 1 and the 10 th-stage rotor blade 2, and the outer wall of the rear casing is provided with a supporting edge; the supporting edge is connected with the extension casing 7; an eighth-stage air guide cavity is formed among the rear casing 9, the connecting casing 6, the extension casing 7 and the ninth-stage casing 8; 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.

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 is designed to be a two-half split structure and is integrally formed with the corresponding 0-5 stage stator blade, so that the processing precision can be ensured, and the assembly is convenient.

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 optional embodiments, in the above compressor bleed air structure, a seventh-stage annular clamping groove is formed between one end of the seventh-stage casing 4 facing the eighth-stage casing 5 and the eighth-stage casing 5; the blade tip of the 7 th stage stator blade 1 is clamped in the seventh stage ring clamping groove.

In some alternative embodiments, in the above compressor bleed air structure, an eighth-stage annular clamping groove is formed between one end of the eighth-stage casing 5 facing the connecting casing 6 and the connecting casing 6; the blade tip of the 8 th stage stator blade 1 is clamped in the eighth stage ring clamping groove.

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, in the bleed air structure of the compressor, a ninth-stage annular clamping groove is formed between one end, facing the rear casing 9, of the ninth-stage casing 8 and the rear casing 9; the blade tip of the 9 th stage stator blade 1 is clamped in the ninth stage ring clamping groove.

For the air compressor air-entraining structure disclosed in the above embodiment, it can be understood by those skilled in the art that a seventh-stage ring-shaped clamping groove, an eighth-stage ring-shaped clamping groove, and a ninth-stage ring-shaped clamping groove are formed between the seventh-stage casing 4, the eighth-stage casing 5, the connecting casing 6, and the rear casing 9, so as to cooperate with the main 7 th-stage stator blade 1, the 8 th-stage stator blade 1, and the 9 th-stage stator blade 1, and can be conveniently stacked and assembled in the axial direction.

In some optional embodiments, the compressor bleed air structure further includes:

and an inlet of the sixth-stage bleed air pipe 10 is communicated with the sixth-stage bleed air hole, and an outlet of the sixth-stage bleed air pipe extends 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 11, entry and eighth level bleed air hole intercommunication, the export extends to high temperature component or fulcrum structure to can realize cooling high temperature component or carrying out the obturage to the fulcrum structure.

In some alternative embodiments, in the above-mentioned compressor bleed air structure, the portion of the inner wall of the seventh-stage casing 4, which faces the 7 th-stage rotor blade 2, is coated with a wear-resistant coating so as to avoid serious wear of the portion;

the part of the inner wall of the eighth-stage casing 5, which faces the 8 th-stage rotor blade 2, is coated with a wear-resistant coating so as to avoid serious abrasion of the part;

the part of the inner wall of the ninth-stage casing 8, which is opposite to the 9 th-stage rotor blade 2, is coated with a wear-resistant coating so as to avoid serious abrasion of the part;

the inner wall of the rear casing 9 facing the 10 th-stage rotor blade 2 is coated with a wear-resistant coating to avoid severe wear of the part.

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.