CN112325333A - Aeroengine oil-gas mixing method and mixing cavity structure - Google Patents
Aeroengine oil-gas mixing method and mixing cavity structure Download PDFInfo
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- CN112325333A CN112325333A CN202110000560.7A CN202110000560A CN112325333A CN 112325333 A CN112325333 A CN 112325333A CN 202110000560 A CN202110000560 A CN 202110000560A CN 112325333 A CN112325333 A CN 112325333A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
Abstract
The invention provides an aeroengine oil-gas mixing method and a mixing cavity structure, wherein the oil-gas mixing method comprises the following steps: fuel is sprayed into the mixing cavity in a fan-shaped atomization mode in a preset plane to form an oil screen; leading the compressed gas to travel in the mixing cavity at a high speed along a preset direction; the included angle between the preset direction and the preset plane is minus 30 degrees minus plus 30 degrees. The oil-gas mixing cavity structure is used for realizing the oil-gas mixing method and comprises the following steps: the oil-gas mixing cavity is formed by a pipe wall of the oil-gas mixing cavity, and the pipe wall of the oil-gas mixing cavity is provided with a compressed gas input port communicated with the oil-gas mixing cavity and an inlet valve arranged in the oil-gas mixing cavity; fuel is sprayed into the oil-gas mixing cavity through the fuel channel through the fuel nozzle to form an oil screen; the compressed gas travels in the oil-gas mixing cavity along the direction defined by the pipe wall of the oil-gas mixing cavity. The invention has the function of reflecting high-temperature and high-pressure combustion airflow in the combustion cavity of the engine, and effectively improves the oil-gas mixing rate and the mixture ignition efficiency.
Description
Technical Field
The invention relates to the technical field of engines, in particular to an oil-gas mixing method and a mixing cavity 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 problems of insufficient and uneven mixing between fuel oil and compressed air still exist in the working process of the conventional aero-engine, so that the combustion efficiency of an oil-gas mixture is low and the oil-gas mixture cannot be efficiently combusted; even if the ignition is performed, unstable combustion may occur due to insufficient and uneven air-fuel mixture, resulting in a series of engine problems.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides an oil-gas mixing method and an oil-gas mixing cavity structure of an aero-engine.
In order to achieve the purpose, the technical scheme adopted by the invention is as follows:
an aircraft engine oil-gas mixing method, comprising: fuel is sprayed into the mixing cavity in a fan-shaped atomization mode in a preset plane to form an oil screen; leading the compressed gas to travel in the mixing cavity at a high speed along a preset direction; wherein, the included angle between the preset direction and the preset plane is minus 30 degrees.
Optionally, an included angle between the preset direction and the preset plane is 0 °.
The aeroengine oil-gas mixing cavity structure is used for realizing the mixing method and comprises the following steps: the oil-gas mixing cavity is formed by a pipe wall of the oil-gas mixing cavity, and the pipe wall of the oil-gas mixing cavity is provided with a compressed gas input port communicated with the oil-gas mixing cavity; the air inlet valve is arranged in the oil-gas mixing cavity and is provided with a fuel oil channel arranged in the air inlet valve; the fuel is sprayed into the oil-gas mixing cavity through the fuel channel through the fuel nozzle to form an oil screen; the compressed gas travels in the oil-gas mixing cavity along the direction defined by the pipe wall of the oil-gas mixing cavity.
Optionally, the intake valve comprises: the air inlet seat, the air inlet rod, the joint sleeve and the elastic piece limit and plug the plug; 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 fuel channel extends to the small rod body through the large rod body, and the fuel nozzle is arranged on the small rod body; the air inlet seat has a tendency of reciprocating along the air inlet rod under the action of the elastic piece, and the stroke of reciprocating motion of the air inlet seat is limited between the step and the left end face of the sleeve; when the air inlet seat reciprocates, the fuel nozzle is opened or closed along with the reciprocating motion of the air inlet seat.
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: a base body; and a skirt body 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.
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 of the inlet valve of the aircraft engine is provided with a first inclined surface 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, and a channel for the oil-gas mixture to enter the combustion chamber of the engine is formed between the first inclined surface structure and the second inclined surface structure; the channel can be closed or opened along with the reciprocating motion of the air inlet seat in a self-adaptive mode.
Optionally, a plurality of sliding support wing plates are further arranged on the outer side of the seat body of the inlet valve of the aero-engine; one end of each of the sliding support wings extends to a surface of the skirt.
Compared with the prior art, the invention has the beneficial effects that:
1. the fuel oil is sprayed into the oil-gas mixing cavity in a fan-shaped atomization mode through the fuel nozzle and is vertically intersected with the compressed gas input from the compressed gas input port, so that the phenomenon of gas oil pushing is formed. Therefore, the fuel oil pellets are changed from big to small under the punching and stretching action of the airflow and are mutually fused with gas molecules to form a mist oil and gas mixture. Effectively improves the mixing rate and is beneficial to improving the ignition rate. Meanwhile, the engine is continuously combusted, and reliable guarantee is provided.
2. According to the invention, through the channel formed between the first inclined surface structure of the skirt body and the second inclined surface structure of the pipe wall of the oil-gas mixing cavity, the inclined surface of the oil-gas mixture is led into the combustion cavity of the engine in a turbulent flow manner at all angles, so that the oil-gas mixture is forced to be fully mixed in the combustion cavity of the engine for the second time, the mixing rate is further improved, and the ignition efficiency of the mixture is improved.
3. The invention has the function of reflecting high-temperature and high-pressure combustion airflow in the combustion cavity of the engine. When high-temperature and high-pressure gas generated in the ignition combustion process of the engine forms a reverse combustion phenomenon, pressure can be generated on the skirt body, and the skirt body can automatically move towards the left end and compress the elastic part under the action of the pressure 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 as to seal the oil-gas mixture airflow in the oil-gas mixing cavity to enter the combustion cavity of the engine. The combustion pressure acting on the skirt body can instantly generate reflected kinetic energy when the skirt body stops retreating to generate a rigid damping effect, so that the inlet valve pushes high-temperature and high-pressure gas in a combustion cavity of the engine in a gas-phase piston mode to move towards an engine spray pipe.
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 of an oil-gas mixing chamber according to the present invention.
FIG. 2 is a schematic view showing the structure of an intake valve 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 first 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 second 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 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
The embodiment of the invention provides an air-fuel mixing method for an aircraft engine, which comprises the following steps:
fuel is sprayed into the mixing cavity in a fan-shaped atomization mode in a preset plane to form an oil screen;
leading the compressed gas to travel in the mixing cavity at a high speed along a preset direction;
the included angle between the preset direction and the preset plane is minus 30 degrees minus plus 30 degrees.
Preferably, the included angle between the preset direction and the preset plane is 0 °.
Example 2
As shown in fig. 1 and fig. 2, an embodiment of the present invention provides an air-fuel mixing chamber structure of an aircraft engine, configured to implement the air-fuel mixing method described in embodiment 1, where the air-fuel mixing chamber structure includes: an intake valve 100 and an air-fuel mixing chamber formed by an air-fuel mixing chamber wall 200. The oil-gas mixing cavity pipe wall 200 is provided with a compressed gas input port 201 communicated with the oil-gas mixing cavity. The intake valve 100 is disposed in the oil-gas mixing chamber, and the intake valve 100 has a fuel passage 23 disposed therein. The fuel oil is sprayed into the oil-gas mixing cavity through the fuel oil channel 23 through the fuel oil nozzle 24 to form an oil screen; the compressed gas travels within the mixing chamber in a direction defined by the mixing chamber wall 200. When the oil-gas mixing cavity is used, after oil and gas are input into the oil-gas mixing cavity, the fuel oil is sprayed into the oil-gas mixing cavity in a fan-shaped atomization mode through the fuel nozzle 24 to form an oil screen, and the oil screen is vertically intersected with compressed gas input into the oil-gas mixing cavity from the compressed gas input port 201, so that an air oil pushing phenomenon is formed, and the air oil is advanced at a highest speed along a preset direction.
Specifically, 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 first 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 second step 2c is formed at the joint of the large rod body 20 and the small rod body 21. First step 1c with second 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.
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 fuel channel 23 extends to the small rod body 21 through the large rod body 20, and the fuel nozzle 24 is arranged on the small rod body 21. 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. The angle between the flow direction of the compressed gas and the fuel passage 23 is-30 DEG minus-30 DEG, preferably 0 deg. 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.
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 second step 2c and the left end face of the sleeve 3. When the air inlet seat reciprocates, the fuel nozzle is opened or closed along with the reciprocating motion of the air inlet seat. 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 fuel nozzle 24 and the channel 203 are 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, the fuel nozzle 24 is closed, and the channel 203 is closed.
According to the method, the fuel is sprayed into the mixing cavity in a fan-shaped atomization mode in the preset plane to form the fuel screen; leading the compressed gas to travel in the mixing cavity at a high speed along a preset direction; the included angle between the preset direction and the preset plane is minus 30 degrees minus plus 30 degrees. Preferably, the included angle between the preset direction and the preset plane is 0 °.
The specific mixing method comprises the following steps: the fuel is injected into the oil-gas mixing cavity in a fan-shaped atomization mode through the fuel nozzle 24 to form an oil screen, and the oil screen is vertically intersected with the compressed gas input into the oil-gas mixing cavity from the compressed gas input port 201, so that the phenomenon of air pushing is formed. The compressed gas is limited by the structure of the oil-gas mixing cavity in the flow direction, namely, the compressed gas flows transversely after being input from the compressed gas input port 201, and the fuel oil flows vertically from the fuel oil nozzle 24, so that the fuel oil and the compressed gas are vertically crossed to form the phenomenon of gas oil pushing. At the moment, the fuel oil is continuously input into the oil-gas mixing cavity under the action of output pressure, and a stretching and penetrating atomization area is formed in pushing and pressing airflow, so that fuel oil granules are changed from big to small under the stamping and stretching action of the airflow and are mutually fused with gas molecules to form a mist oil-gas mixture, the mixing rate of the fuel oil granules basically reaches 96%, the ignition rate is improved, and meanwhile, the reliable guarantee is provided for continuous combustion of an engine. Meanwhile, a channel 203 for the oil-gas mixture to enter the engine combustion chamber is formed between the first inclined surface structure 120 and the second inclined surface structure 202, and the oil-gas mixture in the oil-gas mixing chamber is introduced into the combustion chamber in a disordered manner through the inclined surface channel 203, so that the oil-gas mixture is forced to be fully mixed for the second time in the engine combustion chamber 300, the mixing rate reaches more than 96%, and the ignition efficiency of the mixture is greatly improved.
By simultaneously feeding oil and gas from the fuel passage 23 and the compressed gas input port 201, the fuel 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 compressed gas input port 201 in the passage 203. In a dynamic pushing and mixing state, the airflow between the sliding support wing plates 11 moves to the back of the skirt body 12 at the highest speed, namely moves to the first inclined surface structure 120, and under the continuous pushing and pressing action of the subsequent mixed oil and gas, the channel 203 is in an open state, namely the oil-gas mixture is diffused and input into the engine combustion chamber 300 through the channel 203 formed between the first inclined surface structure 120 and the second inclined surface structure 202. Due to the butterfly-shaped structure of the skirt body 12, the oil-gas mixture is mixed for the second time in a cross turbulent flow state in the engine combustion chamber 300.
After the engine combustion chamber 300 flows towards the engine nozzle, the oil-gas mixture in the direction of the engine nozzle can be ignited by an igniter, so that blocking explosion is generated instantly, meanwhile, reverse combustion is generated towards the skirt body 12, top flow combustion is formed, the pressure in the engine combustion chamber 300 is rapidly increased, when the pressure generated by combustion in the engine combustion chamber 300 is greater than 26kg, the pressure generated by combustion in the skirt body 12 is greater than the sum of the two forces in the elastic part 4 and the oil-gas mixing chamber, the resultant force of the elastic part 4 and the oil-gas mixing chamber 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 chamber, so that the oil-gas mixture is pushed to flow towards the engine combustion chamber 300 in a closed oil-gas mixing chamber. That is, high-temperature and high-pressure gas generated in the ignition combustion process of the engine can form a reverse combustion phenomenon, dynamic pressure can be generated on the surface of the skirt body 12, the skirt body 12 is under the action of the dynamic pressure, when the dynamic pressure exceeds the sum of two forces in the elastic part 4 and the oil-gas mixing cavity, the skirt body 12 moves towards the left end and compresses the elastic part 4 until the first inclined surface structure 120 tightly presses the second inclined surface structure 202, so that the incoming flow of the oil-gas mixing cavity is sealed, the air flow of the oil-gas mixture is stopped to enter the engine combustion cavity 300, the channel 203 is closed, and the engine combustion cavity 300 is in a one-way sealed state. The combustion pressure acting on the skirt 12 instantaneously generates reflected kinetic energy when the skirt 12 stops retreating to generate a hard damping effect. In the continuous semi-closed combustion pressurization process, the high-temperature and high-pressure gas flow in the engine combustion cavity 300 pushes the high-temperature and high-pressure gas in the engine combustion cavity 300 to move towards the engine spray pipe in the form of a gas-phase piston under the action of the reflected oscillation waves of the surface of the skirt body 12. Therefore, the intake valve 100 has the function of reflecting high-temperature and high-pressure combustion airflow in the combustion chamber, and reflecting oscillation (7 times/s) gas-phase detonation waves are formed in the combustion chamber, so that the engine spray pipe generates a gas detonation effect, and the instant 520kg thrust efficiency can be achieved.
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. An aircraft engine oil-gas mixing method, characterized in that the method comprises:
fuel is sprayed into the mixing cavity in a fan-shaped atomization mode in a preset plane to form an oil screen;
leading the compressed gas to travel in the mixing cavity at a high speed along a preset direction;
wherein, the included angle between the preset direction and the preset plane is minus 30 degrees.
2. A method of mixing aircraft engine fuel and air according to claim 1, wherein the predetermined direction is at an angle of 0 ° to the predetermined plane.
3. An aircraft engine oil-gas mixing chamber structure for implementing the mixing method of claim 1 or 2, characterized by comprising:
the oil-gas mixing cavity is formed by an oil-gas mixing cavity pipe wall (200), and the oil-gas mixing cavity pipe wall (200) is provided with a compressed gas input port (201) communicated with the oil-gas mixing cavity; and
the air inlet valve (100) is arranged in the oil-gas mixing cavity, and the air inlet valve (100) is provided with a fuel oil channel (23) arranged in the air inlet valve;
the fuel oil is sprayed into the oil-gas mixing cavity through a fuel oil channel (23) through a fuel oil nozzle (24) to form an oil screen; the compressed gas travels in the gas-oil mixing cavity along a direction defined by a gas-oil mixing cavity tube wall (200).
4. An aircraft engine fuel-air mixing chamber structure according to claim 3, wherein:
the intake valve includes: the air inlet seat (1), the air inlet rod (2), the joint sleeve (3) and the elastic piece (4) limit the 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 first 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 second 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 fuel channel (23) extends to the small rod body (21) through the large rod body (20), and the fuel nozzle (24) is arranged on the small rod body (21);
the air inlet seat (1) has a tendency of reciprocating along the air inlet rod (2) under the action of an elastic piece (4), and the stroke of the reciprocating motion is limited between the second step (2 c) and the left end face of the sleeve (3); when the air inlet seat (1) reciprocates, the fuel nozzle (24) is opened or closed along with the reciprocating motion of the air inlet seat (1).
5. An aircraft engine fuel-air mixing chamber structure according to claim 4, 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).
6. An aircraft engine fuel-air mixing chamber structure according to claim 5, characterised in that the air intake 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).
7. The aeroengine fuel-air mixing chamber structure of claim 6, characterized in that said skirt (12) is formed with a cavity (13) recessed inwardly from an end face of said skirt (12).
8. An aeroengine fuel-air mixing chamber structure according to claim 4, characterized in that the number of said fuel nozzles (24) is 2, and they are symmetrically arranged around said small rod body (21).
9. An aircraft engine fuel-air mixing chamber structure according to claim 6, wherein:
the skirt (12) having 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), and a channel (203) for the oil-gas mixture to enter a combustion chamber of the engine is formed between the first inclined surface structure and the second inclined surface structure;
the channel (203) can be closed or opened along with the reciprocating motion of the air inlet seat (1) in a self-adaptive mode.
10. An aircraft engine fuel-air mixing chamber structure according to claim 9, wherein:
the outer side of the seat body (10) 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).
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