Aircraft engine tail nozzle
阅读说明:本技术 一种航空发动机尾喷管 (Aircraft engine tail nozzle ) 是由 孙涛 张家俊 于 2020-07-08 设计创作,主要内容包括:本发明涉及航空发动机技术领域,具体的说是一种航空发动机尾喷管,包括动力筒、滑动机构、驱动机构、调节结构和通风结构,动力筒的内部固定有压气机、燃烧室和涡轮,压气机、燃烧室和涡轮依次固定连接,涡轮远离压气机的一侧固定连接有锥形筒,通风结构固定套设在动力筒的外侧壁上,通过设置滑动机构和通风结构,能够对涡轮中的涡扇进行散热,解决了长期高温运行的涡轮扇叶使用寿命短容易出现损坏的问题,通过设置驱动机构和调节结构,能够扩大喷口的直径,使燃气在尾喷管中完全膨胀,能够使发动机在各种工作状态都获得良好的性能,通过设置动力筒和保护壳,当航空发动机碰撞到飞鸟时,保护壳能够保护航空发动机不会出现损坏。(The invention relates to the technical field of aero-engines, in particular to an aero-engine tail nozzle which comprises a power cylinder, a sliding mechanism, a driving mechanism, an adjusting structure and a ventilation structure, wherein an air compressor, a combustion chamber and a turbine are fixed inside the power cylinder, the air compressor, the combustion chamber and the turbine are sequentially and fixedly connected, a conical cylinder is fixedly connected to one side of the turbine far away from the air compressor, the ventilation structure is fixedly sleeved on the outer side wall of the power cylinder, through the arrangement of the sliding mechanism and the ventilation structure, the heat dissipation can be carried out on a turbofan in the turbine, the problem that long-term high-temperature operation turbine blades are short in service life and easy to damage is solved, through the arrangement of the driving mechanism and the adjusting structure, the diameter of a nozzle can be enlarged, so that gas is completely expanded in the tail nozzle, the engine can obtain good performance in various working states, and through, when the aircraft engine collides with the flying bird, the protective shell can protect the aircraft engine from being damaged.)
1. The aircraft engine tail nozzle is characterized by comprising a power cylinder (1), a sliding mechanism (2), a driving mechanism (3), an adjusting structure (4) and a ventilation structure (5), wherein a gas compressor (6), a combustion chamber (7) and a turbine (10) are fixed inside the power cylinder (1), the gas compressor (6), the combustion chamber (7) and the turbine (10) are sequentially and fixedly connected, a tapered cylinder (9) is fixedly connected to one side, away from the gas compressor (6), of the turbine (10), the ventilation structure (5) is fixedly sleeved on the outer side wall of the power cylinder (1), the turbine (10) is located on the inner side of the ventilation structure (5), the sliding mechanism (2) is fixedly connected to the outer side wall of the power cylinder (1), the driving mechanism (3) is fixedly connected to the outer side wall of the power cylinder (1), and the driving mechanism (3) and the sliding mechanism (2) are respectively located on two sides of the ventilation structure (5), the adjusting structure (4) is fixedly connected to one end of the power cylinder (1), and the adjusting structure (4) is located on one side, far away from the gas compressor (6), of the turbine (10).
2. The aircraft engine exhaust nozzle according to claim 1, characterized in that the sliding mechanism (2) comprises a push ring (21), a driving motor (26), a threaded cylinder (24) and a threaded rod (25), the push ring (21) is slidably sleeved on the outer side wall of the power cylinder (1), the threaded cylinder (24) is fixedly connected with the push ring (21), the threaded rod (25) is slidably connected inside the threaded cylinder (24), one end of the threaded rod (25) far away from the push ring (21) is fixedly connected with the output end of the driving motor (26) through a coupler, and the driving motor (26) is fixedly connected on the outer side wall of the power cylinder (1).
3. The aircraft engine jet nozzle according to claim 2, characterized in that two sliding blocks (23) are fixedly connected to the inner side wall of the push ring (21), a sliding groove (22) corresponding to the two sliding blocks (23) is formed in the outer side wall of the power cylinder (1), and the two sliding blocks (23) are both slidably connected to the inside of the sliding groove (22).
4. The aircraft engine exhaust nozzle according to claim 2, characterized in that the ventilation structure (5) comprises a ventilation ring (55), a ventilation hole (51) and a sealing plug (53), the ventilation ring (55) is fixedly sleeved on the outer side wall of the power cylinder (1), the ventilation hole (51) is provided with a plurality of ventilation holes (51), the ventilation holes (51) are uniformly formed in the side wall of the ventilation ring (55), the outer side wall of the power cylinder (1) is provided with a plurality of through holes (52) corresponding to the ventilation holes (51), the through holes (52) are communicated with the ventilation hole (51), the sealing plug (53) is provided with a plurality of sealing plugs (53) which are slidably connected inside the ventilation holes (51), and one ends of the sealing plugs (53) close to the push ring (21) are fixedly connected with the push ring (21).
5. The aircraft engine exhaust nozzle according to claim 1, characterized in that the driving mechanism (3) comprises a cylinder (31), a connecting ring (32) and a push rod (33), the connecting ring (32) is slidably sleeved on the outer side wall of the power cylinder (1), the cylinder (31) is fixedly connected on the outer side wall of the power cylinder (1), the output end of the cylinder (31) is fixedly connected with the connecting ring (32), the outer side wall of the connecting ring (32) is fixedly sleeved with a plurality of sliding sleeves (34), the push rod (33) is provided with a plurality of push rods (33), and the push rods (33) are all hinged to the sliding sleeves (34).
6. The aircraft engine exhaust nozzle according to claim 5, characterized in that the adjusting structure (4) comprises a sealing plate (41), a plurality of grooves (43) and a mounting ring (42), the mounting ring (42) is fixedly connected with one end of the power cylinder (1), the sealing plate (41) is located on one side of the turbine (10) far away from the compressor (6), the plurality of grooves (43) are formed, the plurality of grooves (43) are uniformly formed on the outer side wall of the mounting ring (42) far away from the power cylinder (1), the plurality of sealing plates (41) are provided, one ends of the plurality of sealing plates (41) close to the mounting ring (42) are hinged inside the grooves (43), one sides of the plurality of sealing plates (41) far away from each other are fixedly connected with connecting blocks (44), and the plurality of connecting blocks (44) are hinged with the push rod (33).
7. An aircraft engine jet nozzle according to claim 5, characterized in that the sealing plate (41) is arranged in an arc-shaped configuration, and the length of the side of the sealing plate (41) close to the mounting ring (42) is longer than the length of the side of the sealing plate (41) far from the mounting ring (42).
8. The aircraft engine exhaust nozzle according to claim 7, characterized in that a protective shell (8) is sleeved on the outer side wall of the power barrel (1), a plurality of support rods (81) are fixedly connected to the bottom end of the protective shell (8), the bottoms of the support rods (81) are fixedly connected to the power barrel (1), a notch (54) is formed in the outer side wall of the protective shell (8), the notch (54) is located on the outer side of the push ring (21), and the push ring (21) is in contact with the notch (54).
Technical Field
The invention relates to the technical field of aero-engines, in particular to an aero-engine tail nozzle.
Background
The aircraft engine is the 'heart' of the aircraft, is one of the components of the turbojet engine of the jet aircraft, carbon dioxide, sulfur dioxide and other incompletely combusted small-molecule hydrocarbon substances after fuel combustion of the aircraft are ejected through the tail nozzle, the aircraft is pushed by acting force generated during air ejection, the aircraft is divided into an adjustable tail gas pipe and an unadjustable tail gas pipe according to the size of the diameter of the nozzle, and the adjustable tail nozzle can ensure that the nozzle is enlarged in a stress application state. When a turbine engine in the prior aeroengine runs, a turbine fan blade running in a long-term high-temperature environment is short in service life and easy to damage, and in a convergent tail nozzle, gas cannot be fully expanded in the tail nozzle under the stress application state of the aeroengine, so that most of thrust can be lost.
Disclosure of Invention
The invention provides an aircraft engine tail nozzle which effectively solves the problems in the prior art.
In order to solve the technical problems, the invention provides the following technical scheme: the invention discloses an aircraft engine tail nozzle which comprises a power cylinder, a sliding mechanism, a driving mechanism, an adjusting structure and a ventilation structure, wherein a gas compressor, a combustion chamber and a turbine are fixed inside the power cylinder, the gas compressor, the combustion chamber and the turbine are sequentially and fixedly connected, a conical cylinder is fixedly connected to one side, away from the gas compressor, of the turbine, the ventilation structure is fixedly sleeved on the outer side wall of the power cylinder, the turbine is located on the inner side of the ventilation structure, the sliding mechanism is fixedly connected to the outer side wall of the power cylinder, the driving mechanism and the sliding mechanism are respectively located on two sides of the ventilation structure, the adjusting structure is fixedly connected to one end of the power cylinder, and the adjusting structure is located on one side, away.
Specifically, slide mechanism includes throw-out collar, driving motor, a screw thread section of thick bamboo and threaded rod, the throw-out collar slides and cup joints on the lateral wall of a power section of thick bamboo, a screw thread section of thick bamboo and throw-out collar fixed connection, threaded rod sliding connection is in the inside of a screw thread section of thick bamboo, the one end that the throw-out collar was kept away from to the threaded rod passes through shaft coupling fixed connection with driving motor's output, driving motor fixed connection is on the lateral wall of a power section of thick bamboo.
Specifically, the inside wall fixedly connected with two sliders of push ring, the corresponding spout with two sliders is seted up to the lateral wall of power section of thick bamboo, two equal sliding connection of slider is in the inside of spout.
Specifically, the ventilation structure includes ventilation ring, ventilation hole and shutoff stopper, the fixed cup joint of ventilation ring is on the lateral wall of a power section of thick bamboo, the ventilation hole is provided with a plurality ofly, and is a plurality of the ventilation hole is even set up on the lateral wall of ventilation ring, the lateral wall of a power section of thick bamboo set up with the corresponding through-hole in a plurality of ventilation holes, and is a plurality of the through-hole all is linked together with the ventilation hole, the shutoff stopper is provided with a plurality ofly, and is a plurality of the equal sliding connection of shutoff stopper is in the inside in ventilation hole, the shutoff stopper is close to the one end of throw-out collar.
Specifically, actuating mechanism includes cylinder, go-between and push rod, the go-between slides and cup joints on the lateral wall of a power section of thick bamboo, cylinder fixed connection is on the lateral wall of a power section of thick bamboo, the output and the go-between fixed connection of cylinder, a plurality of sliding sleeves have been cup jointed to the lateral wall of go-between fixedly, the push rod is provided with a plurality ofly, and is a plurality of the push rod all articulates with the sliding sleeve.
The adjustable gas compressor is characterized in that the adjusting structure comprises a sealing plate, a groove and a mounting ring, the mounting ring is fixedly connected with one end of the power cylinder, the sealing plate is located on one side, away from the gas compressor, of the turbine, the groove is formed in a plurality of and a plurality of grooves are uniformly formed in the outer side wall, away from the power cylinder, of the mounting ring, the sealing plate is provided with a plurality of sealing plates, one ends of the sealing plates, close to the mounting ring, are hinged to the grooves, and are a plurality of connecting blocks and a plurality of connecting blocks are fixedly connected to one sides, away from the sealing plates, and are hinged.
Specifically, the shrouding is the arc structure setting, the length that the shrouding is close to collar one side is longer than the shrouding keeps away from collar one side.
Specifically, the lateral wall cover of a power section of thick bamboo is equipped with the protective housing, a plurality of bracing pieces of bottom fixedly connected with of protective housing, it is a plurality of the bottom of bracing piece all with power section of thick bamboo fixed connection, the lateral wall of protective housing is seted up jaggedly, the breach is located the outside of throw-away collar, the throw-away collar contacts with the breach.
The invention has the following beneficial effects:
(1) according to the aero-engine tail nozzle, the sliding mechanism and the ventilation structure are arranged, the driving motor is started, the threaded barrel drives the push ring to slide, the push ring drives the sealing plug to be drawn out of the ventilation hole, after external air flow outside the protective shell enters the ventilation hole through the notch, the external air flow can be directly blown on the turbine through the through holes, heat dissipation can be conducted on a turbofan in the turbine, and the problem that the turbine fan blade which runs at high temperature for a long time is short in service life and prone to damage is solved.
(2) According to the jet pipe of the aircraft engine tail, the driving mechanism and the adjusting structure are arranged, when the aircraft engine is in a stress application state, the air cylinder is started, the connecting ring slides towards the direction away from the tail part of the power cylinder, the sealing plates are pulled by the connecting rods simultaneously, the sealing plates rotate towards the outer side of the power cylinder simultaneously, the sealing plates are separated from each other, the diameter of the nozzle can be enlarged, fuel gas is fully expanded in the jet pipe, and the engine can obtain good performance in various working states.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention and not to limit the invention. In the drawings:
FIG. 1 is a schematic external view of an aircraft engine jet nozzle provided in accordance with the present invention;
FIG. 2 is a schematic diagram of an internal structure of an aircraft engine jet nozzle provided by the invention;
FIG. 3 is a schematic diagram of a right-view structure of an aircraft engine jet nozzle provided by the invention:
FIG. 4 is an enlarged schematic view of portion A of an aircraft engine jet nozzle of the present invention shown in FIG. 1:
FIG. 5 is a schematic perspective view of a vent ring in an aircraft engine nozzle according to the present invention.
In the figure: 1. a power cylinder; 2. a sliding mechanism; 21. a push ring; 22. a chute; 23. a slider; 24. a threaded barrel; 25. a threaded rod; 26. a drive motor; 3. a drive mechanism; 31. a cylinder; 32. a connecting ring; 33. a push rod; 34. a sliding sleeve; 4. an adjustment structure; 41. closing the plate; 42. a mounting ring; 43. a groove; 44. connecting blocks; 5. a ventilation structure; 51. a vent hole; 52. a through hole; 53. sealing; 54. a notch; 55. a ventilation ring; 6. a compressor; 7. a combustion chamber; 8. a protective shell; 81. a support bar; 9. a tapered barrel; 10. a turbine.
Detailed Description
In order to make the technical means, the creation characteristics, the achievement purposes and the effects of the invention easy to understand, the invention is further described with the specific embodiments.
As shown in fig. 1-5, the invention relates to an aircraft engine exhaust nozzle, which comprises a
Specifically, slide mechanism 2 includes a
Specifically, the inner side wall of the
Specifically, the ventilation structure 5 includes a
Specifically, actuating mechanism 3 includes
It is specific, it includes shrouding 41,
Specifically, the closing
Specifically, the lateral wall cover of
Specifically, when the aircraft engine is in a stress application state, the
The foregoing illustrates and describes the principles, general features, and advantages of the present invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, and the embodiments and descriptions given above are only illustrative of the principles of the present invention, and various changes and modifications may be made without departing from the spirit and scope of the invention, which fall within the scope of the claims. The scope of the invention is defined by the appended claims and equivalents thereof.
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