CN112324574A - Aeroengine, aeroengine's (air) intake valve and air intake structure - Google Patents
Aeroengine, aeroengine's (air) intake valve and air intake structure Download PDFInfo
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- CN112324574A CN112324574A CN202110000567.9A CN202110000567A CN112324574A CN 112324574 A CN112324574 A CN 112324574A CN 202110000567 A CN202110000567 A CN 202110000567A CN 112324574 A CN112324574 A CN 112324574A
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- Prior art keywords
- air inlet
- cavity
- rod
- oil
- aircraft engine
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/057—Control or regulation
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
- F02C7/222—Fuel flow conduits, e.g. manifolds
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/02—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the jet being intermittent, i.e. pulse-jet
- F02K7/06—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the jet being intermittent, i.e. pulse-jet with combustion chambers having valves
- F02K7/067—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the jet being intermittent, i.e. pulse-jet with combustion chambers having valves having aerodynamic valves
Abstract
The invention provides an aircraft engine, an inlet valve and an inlet structure of the aircraft engine, wherein the inlet valve comprises: the air inlet seat is provided with a cavity structure which comprises a far large cavity and a small cavity, the section sleeve, the elastic part and the limiting blocking plug are sequentially and mutually contacted and arranged in the large cavity, the air inlet rod comprises a large rod body and a small rod body, the small rod body penetrates through the small cavity to be connected with the section sleeve, the air inlet seat has the trend of reciprocating motion along the air inlet rod under the action of the elastic part, and the stroke of the reciprocating motion is limited between the step and the left end face of the section sleeve. The air inlet structure comprises an oil-gas mixing cavity formed by the pipe wall of the oil-gas mixing cavity and an inlet valve arranged in the oil-gas mixing cavity. The aircraft engine is provided with the aircraft engine air inlet structure. The invention can automatically control the opening of the air valve channel, thereby optimizing combustion and improving the performance of the engine, and has compact structure and low cost.
Description
Technical Field
The invention relates to the technical field of engines, in particular to an air inlet valve and an air inlet structure of an aircraft engine.
Background
An aero-engine (aero-engine) is a highly complex and precise thermal machine, is used as the heart of an airplane, is not only the power for flying the airplane, but also an important driving force for promoting the development of aviation industry, and each important change in human aviation history is inseparable from the technical progress of the aero-engine. The intake valve of the engine is a very important part of the engine and has a very great function. In the prior art, the spring sleeve is usually arranged on the outer wall of the valve rod and is of a split structure, and the lift of the intake valve cannot be adjusted in the working process of an engine, so that a mechanism which improves the performance of the engine, can change the opening time of the gas-oil valve and delay closing of the gas-oil valve can be generally installed on the engine.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides an aircraft engine, an inlet valve of the aircraft engine and an air inlet structure of the aircraft engine.
In order to achieve the purpose, the technical scheme adopted by the invention is as follows:
an inlet valve for an aircraft engine, comprising: the air inlet seat, the air inlet rod, the joint sleeve, the elastic piece and the limiting plugging plug are arranged on the air inlet seat; the air inlet seat is provided with a cavity structure which penetrates from the right end surface of the air inlet seat to extend to the left end surface; the cavity structure comprises a large cavity far away from the air inlet rod and a small cavity close to the air inlet rod, and a step is formed at the joint of the large cavity and the small cavity; the joint sleeve, the elastic piece and the limiting plugging plug are sequentially and mutually contacted and are arranged in the large cavity; the air inlet rod comprises a large rod body and a small rod body, and a step is formed at the joint of the large rod body and the small rod body; the small rod body penetrates through the small cavity to be connected with the joint sleeve; the air inlet seat has a tendency of reciprocating along the air inlet rod under the action of the elastic piece, and the reciprocating stroke of the air inlet seat is limited between the step and the left end face of the sleeve.
Optionally, the socket has a threaded hole; the air inlet rod is provided with a threaded rod extending outwards from one end of the small rod body; the threaded rod is in threaded connection in the threaded hole.
Optionally, the air inlet seat comprises: the skirt body is integrally formed at one end of the seat body; the skirt body is expanded outwards from one end of the seat body; the cavity structure extends from one end of the skirt body to the inside of the seat body and penetrates through the seat body.
Optionally, the skirt is formed with a cavity recessed inwardly from an end face of the skirt.
An aircraft engine air intake structure comprising: the oil-gas mixing cavity is formed by the pipe wall of the oil-gas mixing cavity; the air inlet valve is arranged in the oil-gas mixing cavity; the air inlet valve is the air inlet valve of any one of the aeroengine.
Optionally, the pipe wall of the oil-gas mixing cavity is provided with a mixed compressed gas input port communicated with the oil-gas mixing cavity; the air inlet rod is provided with a fuel oil channel arranged in the air inlet rod, and the fuel oil channel is communicated with the oil-gas mixing cavity through a fuel oil nozzle; the fuel nozzle is arranged on the small rod body.
Optionally, the number of the fuel nozzles is 2, and the fuel nozzles and the small rod body are symmetrically arranged around the small rod body.
Optionally, the skirt body has a first bevel structure; the pipe wall of the oil-gas mixing cavity is provided with a second inclined surface structure at the skirt body; the first inclined surface structure is matched with the second inclined surface structure, a channel for the oil-gas mixture to enter the engine combustion cavity is formed between the first inclined surface structure and the second inclined surface structure, and the channel can be closed or opened along with the detonation of the engine combustion cavity in a self-adaptive mode.
Optionally, a plurality of sliding support wing plates are further arranged on the outer side of the seat body; one end of each of the sliding support wings extends to a surface of the skirt.
An aircraft engine having an aircraft engine air intake structure as claimed in any preceding claim.
Compared with the prior art, the invention has the beneficial effects that:
according to the invention, the joint sleeve, the elastic piece and the limiting blocking plug are sequentially arranged in the cavity structure of the air inlet seat, and the threaded rod is in threaded connection with the threaded hole of the joint sleeve, so that the air inlet rod and the air inlet valve form an integral structure, and the air inlet rod has a compact structure and low cost. And the integral structure can automatically control the opening or closing of the gas throttle according to the pressure of the left end surface or the right end surface. When oil gas is input from the fuel oil channel and the mixed compressed gas input port, the pressure is larger than that of the elastic part under the condition of continuous oil gas transmission, the air inlet rod moves towards the right end and automatically compresses the elastic part, so that the air valve channel of the engine is automatically opened, and an oil gas mixture is input into the combustion cavity of the engine. When the engine is ignited and then reversely burns the intake valve, when the pressure generated by combustion is greater than the sum of two forces in the elastic part and the oil-gas mixing cavity, the skirt body can automatically compress the resultant force of the elastic part and the oil-gas mixture until the first inclined surface structure of the skirt body tightly presses the second inclined surface structure of the pipe wall of the oil-gas mixing cavity, so that the engine air throttle channel is closed, and the oil-gas mixture is sealed to flow to the engine combustion cavity. Therefore, the opening of the air throttle channel can be automatically controlled by the air inlet structure of the engine, so that combustion is optimized, and the performance of the engine is improved.
Drawings
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings needed to be used in the embodiments or technical descriptions will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present application, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic view showing the structure of an intake valve in the present invention.
Fig. 2 is a schematic structural view of an air intake structure in the present invention.
Reference numerals: 1. an air inlet seat; 10. a base body; 11. a sliding support wing plate; 12. a skirt body; 120. a first bevel structure; 13. a concave cavity; 1a, a large cavity; 1b, a small cavity; 1c, a step; 2. an air intake rod; 20. a large rod body; 21. a small rod body; 22. a threaded rod; 23. a fuel passage; 24. a fuel nozzle; 2c, a step; 3. sleeving; 30. a threaded hole; 4. an elastic member; 5. the plug is blocked in a limiting way; 100. an intake valve; 200. the oil-gas mixing cavity pipe wall; 201. a mixed compressed gas input port; 202. a second bevel structure; 203. a channel; 300. an engine combustion chamber.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
Example 1
As shown in fig. 1, the present embodiment provides an intake valve of an aircraft engine, the intake valve including: the air inlet device comprises an air inlet seat 1, an air inlet rod 2, a joint sleeve 3, an elastic piece 4 and a limiting plugging plug 5.
The air inlet seat 1 is provided with a cavity structure which penetrates from the right end face of the air inlet seat 1 and extends to the left end face. The cavity structure comprises a large cavity 1a far away from the air inlet rod 2 and a small cavity 1b close to the air inlet rod 2, and a step 1c is formed at the joint of the large cavity 1a and the small cavity 1 b. The joint sleeve 3, the elastic piece 4 and the limiting plugging plug 5 are sequentially and mutually contacted and are arranged in the large cavity 1 a. The elastic part 4 can adopt a spring, and is preferably a recoil spring; the limiting plugging plug 5 can adopt a plugging limiting screw.
The air inlet rod 2 comprises a large rod body 20 and a small rod body 21, and a step 2c is formed at the joint of the large rod body 20 and the small rod body 21. Step 1c with step 2c punishment do not is provided with the blotter, can effectively play the cushioning effect through the blotter, prolongs the life of this (air) intake valve.
The small rod body 21 penetrates through the small cavity 1b to be connected with the node sleeve 3. Specifically, the socket 3 has a threaded hole 30, and the air inlet rod 2 has a threaded rod 22 extending outward from one end of the small rod body 21, and the threaded rod 22 is screwed in the threaded hole 30.
Under the action of the elastic piece 4, the air inlet seat 1 has the tendency of reciprocating along the air inlet rod 2, and the reciprocating stroke of the air inlet seat 1 is limited between the step 2c and the left end surface of the sleeve 3. When the pressure applied to the air inlet seat 1 is greater than the pressure of the elastic element 4, the elastic element 4 is automatically compressed, so that the air inlet seat 1 automatically opens or closes the air throttle of the engine. Specifically, when the air inlet rod 2 is pressed from the left end face, the air inlet rod 2 moves towards the right end and compresses the elastic part 4 through the sleeve 3, so that the air inlet seat 1 moves towards the right end, and an air throttle of the engine is opened; when the air inlet seat 1 is pressed from the right end face, the limiting blocking plug 5 moves leftwards and compresses the elastic piece 4, so that the air inlet seat 1 moves leftwards, and an air throttle of an engine is closed.
Example 2
As shown in fig. 1, the present embodiment provides an intake valve of an aircraft engine, the intake valve including: the air inlet device comprises an air inlet seat 1, an air inlet rod 2, a joint sleeve 3, an elastic piece 4 and a limiting plugging plug 5.
The air inlet seat 1 is provided with a cavity structure which penetrates from the right end face of the air inlet seat 1 and extends to the left end face. The cavity structure comprises a large cavity 1a far away from the air inlet rod 2 and a small cavity 1b close to the air inlet rod 2, and a step 1c is formed at the joint of the large cavity 1a and the small cavity 1 b. The joint sleeve 3, the elastic piece 4 and the limiting plugging plug 5 are sequentially and mutually contacted and are arranged in the large cavity 1 a. The elastic part 4 can adopt a spring, and is preferably a recoil spring; the limiting plugging plug 5 can adopt a plugging limiting screw.
The air inlet rod 2 comprises a large rod body 20 and a small rod body 21, and a step 2c is formed at the joint of the large rod body 20 and the small rod body 21. Step 1c with step 2c punishment do not is provided with the blotter, can effectively play the cushioning effect through the blotter, prolongs the life of this (air) intake valve.
The small rod body 21 penetrates through the small cavity 1b to be connected with the node sleeve 3. Specifically, the socket 3 has a threaded hole 30, and the air inlet rod 2 has a threaded rod 22 extending outward from one end of the small rod body 21, and the threaded rod 22 is screwed in the threaded hole 30.
The air intake seat 1 includes: a body 10 and a skirt 12 integrally formed at one end of the body 10. The skirt 12 is expanded from one end of the body 10, and the cavity structure extends from one end of the skirt 12 to the inside of the body 10 and penetrates through the body 10. The skirt 12 is formed with a cavity 13 recessed inwardly from an end surface of the skirt 12. Specifically, the skirt 12 is expanded outward toward the right end of the seat 10, and the large cavity 1a and the small cavity 1b extend from the left end of the skirt 12 toward the inside of the seat 10 and penetrate through the seat 10 toward the left end. The cavity 13 is recessed inwardly from the right end face of the skirt 12.
Under the action of the elastic piece 4, the air inlet seat 1 has the tendency of reciprocating along the air inlet rod 2, and the reciprocating stroke of the air inlet seat 1 is limited between the step 2c and the left end surface of the sleeve 3. When the pressure applied to the air inlet seat 1 is greater than the pressure of the elastic element 4, the elastic element 4 is automatically compressed, so that the air inlet seat 1 automatically opens or closes the air throttle of the engine. Specifically, when the air inlet rod 2 is pressed from the left end face, the air inlet rod 2 moves towards the right end and compresses the elastic part 4 through the sleeve 3, so that the air inlet seat 1 moves towards the right end, and an air throttle of the engine is opened; when the air inlet seat 1 is pressed from the right end face, the limiting blocking plug 5 moves leftwards and compresses the elastic piece 4, so that the air inlet seat 1 moves leftwards, and an air throttle of an engine is closed.
Example 3
As shown in fig. 1 and 2, the present embodiment provides an air intake structure of an aircraft engine, including: the air inlet valve 100 and the air-gas mixing cavity formed by the air-gas mixing cavity pipe wall 200 are arranged in the air-gas mixing cavity, and the air inlet valve 100 is arranged in the air-gas mixing cavity.
The intake valve 100 includes: the air inlet device comprises an air inlet seat 1, an air inlet rod 2, a joint sleeve 3, an elastic piece 4 and a limiting plugging plug 5. The air inlet seat 1 is provided with a cavity structure which penetrates from the right end face of the air inlet seat 1 and extends to the left end face. The cavity structure comprises a large cavity 1a far away from the air inlet rod 2 and a small cavity 1b close to the air inlet rod 2, and a step 1c is formed at the joint of the large cavity 1a and the small cavity 1 b. The joint sleeve 3, the elastic piece 4 and the limiting plugging plug 5 are sequentially and mutually contacted and are arranged in the large cavity 1 a. The elastic part 4 can adopt a spring, and is preferably a recoil spring; the limiting plugging plug 5 can adopt a plugging limiting screw. The air inlet rod 2 comprises a large rod body 20 and a small rod body 21, and a step 2c is formed at the joint of the large rod body 20 and the small rod body 21. Step 1c with step 2c punishment do not is provided with the blotter, can effectively play the cushioning effect through the blotter, prolongs the life of this (air) intake valve. The small rod body 21 penetrates through the small cavity 1b to be connected with the node sleeve 3. Specifically, the socket 3 has a threaded hole 30, and the air inlet rod 2 has a threaded rod 22 extending outward from one end of the small rod body 21, and the threaded rod 22 is screwed in the threaded hole 30. The air intake seat 1 includes: a body 10 and a skirt 12 integrally formed at one end of the body 10. The skirt 12 is expanded from one end of the body 10, and the cavity structure extends from one end of the skirt 12 to the inside of the body 10 and penetrates through the body 10. The skirt 12 is formed with a cavity 13 recessed inwardly from an end surface of the skirt 12. Specifically, the skirt 12 is expanded outward toward the right end of the seat 10, and the large cavity 1a and the small cavity 1b extend from the left end of the skirt 12 toward the inside of the seat 10 and penetrate through the seat 10 toward the left end. The cavity 13 is recessed inwardly from the right end face of the skirt 12.
Under the action of the elastic piece 4, the air inlet seat 1 has the tendency of reciprocating along the air inlet rod 2, and the reciprocating stroke of the air inlet seat 1 is limited between the step 2c and the left end surface of the sleeve 3. When the pressure applied to the intake seat 1 is greater than the pressure applied to the elastic member 4, the elastic member 4 is automatically compressed, so that the intake valve 100 automatically opens or closes the passage 203. Specifically, when the air inlet rod 2 is pressed from the left end face, the air inlet rod 2 moves towards the right end and compresses the elastic part 4 through the sleeve 3, so that the air inlet seat 1 moves towards the right end, and the channel 203 is opened; when the air inlet seat 1 is pressed from the right end face, the limiting blocking plug 5 moves leftwards and compresses the elastic piece 4, so that the air inlet seat 1 moves leftwards, and the channel 203 is closed.
The oil-gas mixing cavity pipe wall 200 is provided with a mixed compressed gas input port 201 communicated with the oil-gas mixing cavity. The air inlet rod 2 is provided with a fuel oil channel 23 arranged inside the air inlet rod, the small rod body 21 is provided with a fuel oil nozzle 24, and the fuel oil channel 23 is communicated with the oil-gas mixing cavity through the fuel oil nozzle 24. The number of the fuel nozzles 24 is 2, and the fuel nozzles and the small rod body 21 are symmetrically arranged around the small rod body.
The skirt body 12 is provided with a first inclined surface structure 120, the oil-gas mixing cavity tube wall 200 is provided with a second inclined surface structure 202 at the position of the skirt body 12, the first inclined surface structure 120 is matched with the second inclined surface structure 202, a channel 203 for an oil-gas mixture to enter an engine combustion cavity is formed between the first inclined surface structure 120 and the second inclined surface structure 202, and the channel 203 can be closed or opened along with the detonation of the engine combustion cavity 300 in a self-adaptive manner. The outer side of the seat body 10 is further provided with a plurality of sliding support wing plates 11, and one end of each sliding support wing plate 11 extends to the surface of the skirt body 12. Preferably, the number of the sliding support wing plates 11 is 4, and the sliding support wing plates are symmetrically arranged around the base body 10. It will be appreciated that the skirt 12 is of butterfly configuration and the cavity 13 is located in a recess at the right end of the skirt 12.
The working principle is as follows: by simultaneously feeding oil and gas from the fuel oil passage 23 and the mixed compressed gas input port 201, the fuel oil is atomized and injected into the passage 203 of the engine combustion chamber through the fuel nozzle 24, and is mixed with the gas flow fed from the mixed compressed gas input port 201 in the passage 203. At this time, the fuel oil is continuously input into the oil-gas mixing cavity under the action of output pressure, the oil-gas mixture moves to the back of the skirt body 12 through the airflow between the sliding support wing plates 11, namely moves to the first inclined surface structure 120, and under the action of continuous pushing and pressing of the subsequent mixed oil and gas, the channel 203 is in an open state, namely the oil-gas mixture is input into the engine combustion cavity 300 through the channel 203 formed between the first inclined surface structure 120 and the second inclined surface structure 202. After the engine is ignited, blocking type combustion explosion can be instantly generated, reverse combustion is generated in the direction of the skirt body 12, the pressure generated by combustion of the engine combustion cavity 300 of the skirt body 12 is greater than the sum of two forces in the elastic part 4 and the oil-gas mixing cavity, the resultant force of the elastic part 4 and the oil-gas mixing cavity can be automatically compressed until the first inclined surface structure 120 of the skirt body 12 tightly presses the second inclined surface structure 202 of the pipe wall 200 of the oil-gas mixing cavity, so that the oil-gas mixture is pushed to flow to the engine combustion cavity 300 in a closed oil-gas mixing cavity, namely, the skirt body 12 moves towards the left end and compresses the elastic part 4, and the channel 203 is closed. Meanwhile, when the combustion pressure acting on the skirt 12 stops moving backward to generate a hard damping effect, reflected kinetic energy is generated instantaneously, and high-temperature and high-pressure gas in the engine combustion chamber 300 is pushed in a gas-phase piston mode to move towards the engine nozzle under the action of the reflected oscillation waves of the surface of the skirt 12.
Example 4
As shown in FIGS. 1-2, the invention provides an aircraft engine. The aircraft engine has an aircraft engine air intake structure as described in embodiment 3.
In the foregoing, only certain exemplary embodiments have been described briefly. As those skilled in the art will recognize, the described embodiments may be modified in various different ways, all without departing from the spirit or scope of the present invention. Accordingly, the drawings and description are to be regarded as illustrative in nature, and not as restrictive.
In the description of the present invention, it is to be understood that the terms "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "inner", "outer", "end", "side", and the like, indicate orientations or positional relationships that are based on the orientations or positional relationships shown in the drawings, or the orientations or positional relationships that the products of the present invention are conventionally placed in use, or the orientations or positional relationships that are conventionally understood by those skilled in the art, and are used only for the convenience of describing and simplifying the description, but do not indicate or imply that the referred devices or elements must have a specific orientation, be constructed in a specific orientation, and be operated, and thus should not be construed as limiting the present invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the embodiments of the present application, "a plurality" means two or more unless specifically defined otherwise.
The terms "mounted," "connected," "fixed," and the like are to be construed broadly and may, for example, be fixedly connected or detachably connected or integrated; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
Claims (10)
1. Aeroengine's (air) intake valve, including air inlet seat (1) and air inlet rod (2), its characterized in that:
the intake valve also comprises a joint sleeve (3), an elastic piece (4) and a limiting plugging plug (5);
the air inlet seat (1) is provided with a cavity structure which penetrates from the right end surface to the left end surface of the air inlet seat (1) and extends to the left end surface; the cavity structure comprises a large cavity (1 a) far away from the air inlet rod (2) and a small cavity (1 b) close to the air inlet rod (2), and a step (1 c) is formed at the joint of the large cavity (1 a) and the small cavity (1 b);
the joint sleeve (3), the elastic piece (4) and the limiting blocking plug (5) are sequentially and mutually contacted and are arranged in the large cavity (1 a);
the air inlet rod (2) comprises a large rod body (20) and a small rod body (21), and a step (2 c) is formed at the joint of the large rod body (20) and the small rod body (21);
the small rod body (21) penetrates through the small cavity (1 b) to be connected with the joint sleeve (3);
the air inlet seat (1) has a tendency of reciprocating along the air inlet rod (2) under the action of the elastic piece (4), and the stroke of reciprocating motion is limited between the step (2 c) and the left end face of the sleeve (3).
2. An air intake valve for an aircraft engine as claimed in claim 1, wherein:
the node sleeve (3) is provided with a threaded hole (30);
the air inlet rod (2) is provided with a threaded rod (22) extending outwards from one end of the small rod body (21);
the threaded rod (22) is screwed into the threaded bore (30).
3. An inlet valve for an aircraft engine according to claim 1 or 2, characterised in that the inlet seat (1) comprises:
a base body (10); and
a skirt body (12) integrally formed at one end of the seat body (10);
the skirt body (12) is expanded outwards from one end of the seat body (10);
the cavity structure extends from one end of the skirt body (12) to the interior of the seat body (10) and penetrates through the seat body (10).
4. An inlet valve for an aircraft engine according to claim 3, characterised in that the skirt (12) is formed with a cavity (13) recessed inwardly from an end face of the skirt (12).
5. Aeroengine air intake structure, its characterized in that includes:
the oil-gas mixing cavity is formed by an oil-gas mixing cavity pipe wall (200); and
an inlet valve (100) arranged in the oil-gas mixing cavity;
the inlet valve (100) is an inlet valve of an aircraft engine according to any of claims 1 to 4.
6. An aircraft engine air intake structure according to claim 5, wherein:
the pipe wall (200) of the oil-gas mixing cavity is provided with a mixed compressed gas input port (201) communicated with the oil-gas mixing cavity;
the air inlet rod (2) is provided with a fuel oil channel (23) arranged inside the air inlet rod, and the fuel oil channel (23) is communicated with the oil-gas mixing cavity through a fuel oil nozzle (24);
the fuel nozzle (24) is arranged on the small rod body (21).
7. An aircraft engine air intake structure according to claim 6, wherein the number of fuel jets (24) is 2, both symmetrically arranged around the small rod body (21).
8. An aircraft engine air intake structure according to claim 5 or 6, wherein:
the skirt (12) of the inlet valve of the aircraft engine has a first ramp structure (120);
the oil-gas mixing cavity pipe wall (200) is provided with a second inclined surface structure (202) at the skirt body (12);
the first inclined surface structure (120) is matched with the second inclined surface structure (202), a channel (203) for the oil-gas mixture to enter the engine combustion chamber is formed between the first inclined surface structure and the second inclined surface structure, and the channel (203) can be closed or opened along with the detonation of the engine combustion chamber (300) in a self-adaptive mode.
9. An aircraft engine air intake structure according to claim 8, wherein:
the outer side of the seat body (10) of the inlet valve of the aero-engine is also provided with a plurality of sliding support wing plates (11);
one end of each of the slide support wings (11) extends to the surface of the skirt (12).
10. An aircraft engine characterized by having the aircraft engine air intake structure of any one of claims 5 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110000567.9A CN112324574B (en) | 2021-01-04 | 2021-01-04 | Aeroengine, aeroengine's (air) intake valve and air intake structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110000567.9A CN112324574B (en) | 2021-01-04 | 2021-01-04 | Aeroengine, aeroengine's (air) intake valve and air intake structure |
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| CN112324574A true CN112324574A (en) | 2021-02-05 |
| CN112324574B CN112324574B (en) | 2021-04-06 |
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Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
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| GB548898A (en) * | 1941-07-08 | 1942-10-28 | Fairey Aviat Co Ltd | Improvements in or relating to the propulsion of aircraft and other vehicles |
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| CN112324574B (en) | 2021-04-06 |
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