阅读说明：本技术 航空发动机先进冷却结构用回流燃烧室结构 (Backflow combustion chamber structure for advanced cooling structure of aircraft engine ) 是由 杨卫华 于 2021-09-18 设计创作，主要内容包括：本发明提供航空发动机先进冷却结构用回流燃烧室结构,涉及发动机技术领域。该航空发动机先进冷却结构用回流燃烧室结构,包括外壳和内壳,所述内壳的内壁上固定设置有陶瓷膜,所述外壳和内壳之间固定设置有连接机构,所述连接机构的出气口处固定连接有净化装置,所述净化装置包括二号密封法兰和外管,所述二号密封法兰的一侧通过多个连接螺栓固定设置有一号密封法兰,所述一号密封法兰和二号密封法兰的内部均开设有加密槽,两个所述加密槽之间设置有四号密封圈,所述四号密封圈的内部固定套设有活性炭过滤板。本发明提供航空发动机先进冷却结构用回流燃烧室结构,该航空发动机先进冷却结构用回流燃烧室结构使用方便,绿色环保。(The invention provides a backflow combustion chamber structure for an advanced cooling structure of an aircraft engine, and relates to the technical field of engines. This advanced cooling structure of aeroengine is with backward flow combustion chamber structure, including shell and inner shell, the fixed ceramic membrane that is provided with on the inner wall of inner shell, the fixed coupling mechanism that is provided with between shell and the inner shell, coupling mechanism's gas outlet department fixedly connected with purifier, purifier includes No. two sealing flange and outer tube, one side of No. two sealing flange is provided with a sealing flange through a plurality of connecting bolt is fixed, No. one sealing flange and No. two sealing flange's inside has all been seted up the groove of densifying, two be provided with No. four sealing washers between the groove of densifying, the fixed cover in inside of No. four sealing washers is equipped with the active carbon filter. The invention provides a backflow combustion chamber structure for an advanced cooling structure of an aero-engine, which is convenient to use and environment-friendly.)

1. Advanced cooling structure of aeroengine is with reflow combustion chamber structure, including shell (1) and inner shell (5), its characterized in that: a ceramic membrane (6) is fixedly arranged on the inner wall of the inner shell (5), a connecting mechanism (28) is fixedly arranged between the outer shell (1) and the inner shell (5), and a purifying device (4) is fixedly connected at an air outlet of the connecting mechanism (28);

the purification device (4) comprises a second sealing flange (13) and an outer pipe (11), one side of the second sealing flange (13) is fixedly provided with a first sealing flange (8) through a plurality of connecting bolts (9), the interiors of the first sealing flange (8) and the second sealing flange (13) are respectively provided with an encryption groove (26), a fourth sealing ring (23) is arranged between the two encryption grooves (26), and an active carbon filter plate (22) is fixedly sleeved in the fourth sealing ring (23);

a connecting seat (12) is fixedly arranged at the center of one side, away from the first sealing flange (8), of the second sealing flange (13), a sealing groove (24) is formed in the center of one side, away from the second sealing flange (13), of the connecting seat (12), a threaded hole (25) is formed in the center of the inner wall of one side, close to the second sealing flange (13), of the sealing groove (24), a threaded pipe head (16) is sleeved on an internal thread of the threaded hole (25), and an adjusting pipe (10) is fixedly arranged at one end, away from the second sealing flange (13), of the threaded pipe head (16);

the utility model discloses a telescopic rod, including outer tube (11), spout (15), the inside of spout (15) is close to center department and has seted up spout (15), the inside of spout (15) leans on both sides department to slide respectively and is provided with No. two sealing washer (18) and No. three sealing washer (20), it is fixed between No. two sealing washer (18) and No. three sealing washer (20) to be provided with two telescopic links (21), two equal movable sleeve is equipped with spring (19) on the pole body of telescopic link (21).

2. The structure of a reflow combustion chamber for an advanced cooling structure of an aircraft engine according to claim 1, wherein: the one end that threaded tube head (16) was kept away from in control tube (10) is located the inside of outer tube (11), No. two sealing washer (18) movable sleeve establish on the pipe shaft of control tube (10), No. three sealing washer (20) fixed sleeve establish on the pipe shaft of control tube (10).

3. The structure of a reflow combustion chamber for an advanced cooling structure of an aircraft engine according to claim 1, wherein: an ignition device (2) and a fuel output device (3) are respectively and fixedly arranged between the outer shell (1) and the inner shell (5).

4. The structure of a reflow combustion chamber for an advanced cooling structure of an aircraft engine according to claim 1, wherein: an air inlet pipe (7) is fixedly arranged at an air inlet of the shell (1).

5. The structure of a reflow combustion chamber for an advanced cooling structure of an aircraft engine according to claim 1, wherein: the inner shell (5) is positioned inside the outer shell (1), and a combustion chamber (27) is arranged inside the inner shell (5).

6. The structure of a reflow combustion chamber for an advanced cooling structure of an aircraft engine according to claim 1, wherein: an air outlet pipe (14) is fixedly arranged at the center of one side, away from the second sealing flange (13), of the first sealing flange (8).

7. The structure of a reflow combustion chamber for an advanced cooling structure of an aircraft engine according to claim 1, wherein: a first sealing ring (17) is movably sleeved on the head body of the threaded pipe head (16) positioned in the sealing groove (24).

8. The structure of a reflow combustion chamber for an advanced cooling structure of an aircraft engine according to claim 1, wherein: the two telescopic rods (21) are parallel to each other.

Technical Field

The invention relates to the technical field of engines, in particular to a backflow combustion chamber structure for an advanced cooling structure of an aircraft engine.

Background

The reflux combustion chamber is widely applied to small aircraft engines, mainly comprises a flame tube, an inner ring channel, an outer ring channel, a large bent pipe and the like, has the unique structural characteristic that airflow is deflected twice by 180 degrees, has obvious advantages and disadvantages, and is commonly used for small turboshaft engines provided with centrifugal compressors.

The present invention discloses a cooling structure of flame tube in backflow combustion chamber of turboshaft reflux engine (CN 109990309A), which comprises a tube body, a bent tube formed by bending at one end of the tube body, a flame tube cooling cavity wrapping the tube body and the bent tube, and adjusts the distribution proportion of cooling airflow between the initial gas film plate and the inclined diverging holes of the outer arc wall and the vertical inclined diverging holes of the inner arc wall by changing the proportion of the total area of the opening (slot) of the initial gas film plate to the total area of the opening, the arrangement of the inclined diverging holes on the outer arc wall is characterized in that the front section distribution density is larger than the middle section density, the middle section density is smaller than the tail section density, and the tail section density is larger than the front section density, under the condition of not increasing cold air, the invention improves the cooling structure of the bending wall surface of the traditional flame tube, and reduces the temperature gradient of the flame tube in backflow combustion chamber, thereby reducing the thermal stress of the wall surface, the service life of the flame tube is prolonged, and the invention also provides the turboshaft engine backflow combustion chamber with the cooling structure. However, although the device is convenient to use, the discharged gas is directly discharged, so that the device is not environment-friendly and pollutes the environment.

Disclosure of Invention

Technical problem to be solved

Aiming at the defects of the prior art, the invention provides a backflow combustion chamber structure for an advanced cooling structure of an aircraft engine, and solves the problem that the backflow combustion chamber structure is not environment-friendly and pollutes the environment when being used.

(II) technical scheme

In order to achieve the purpose, the invention is realized by the following technical scheme: the backflow combustion chamber structure for the advanced cooling structure of the aircraft engine comprises an outer shell and an inner shell, wherein a ceramic membrane is fixedly arranged on the inner wall of the inner shell, a connecting mechanism is fixedly arranged between the outer shell and the inner shell, and a purifying device is fixedly connected at an air outlet of the connecting mechanism;

the purifying device comprises a second sealing flange and an outer pipe, wherein a first sealing flange is fixedly arranged on one side of the second sealing flange through a plurality of connecting bolts, encryption grooves are formed in the first sealing flange and the second sealing flange, a fourth sealing ring is arranged between the two encryption grooves, and an activated carbon filter plate is fixedly sleeved in the fourth sealing ring;

a connecting seat is fixedly arranged at the center of one side, away from the first sealing flange, of the second sealing flange, a sealing groove is formed in the center of one side, away from the second sealing flange, of the connecting seat, a threaded hole is formed in the center of the inner wall of one side, close to the second sealing flange, of the sealing groove, a threaded pipe head is sleeved in the threaded hole in a threaded manner, and an adjusting pipe is fixedly arranged at one end, away from the second sealing flange, of the threaded pipe head;

the utility model discloses a sealing device, including outer tube, the inside of outer tube is close to center department and has seted up the spout, the inside of spout leans on both sides department to slide respectively and is provided with No. two sealing washers and No. three sealing washers, the fixed two telescopic links that are provided with between No. two sealing washers and No. three sealing washers, two equal movable sleeve is equipped with the spring on the pole body of telescopic link.

Preferably, the one end that the screw thread tube head was kept away from to the regulating tube is located the inside of outer tube, No. two sealing washer movable sleeve establish on the pipe shaft of regulating tube, No. three sealing washer fixed sleeve establish on the pipe shaft of regulating tube.

Preferably, an ignition device and a fuel output device are fixedly arranged between the outer shell and the inner shell respectively.

Preferably, an air inlet pipe is fixedly arranged at the air inlet of the shell.

Preferably, the inner shell is located inside the outer shell, and a combustion chamber is arranged inside the inner shell.

Preferably, the center of one side of the first sealing flange, which is far away from the second sealing flange, is fixedly provided with an air outlet pipe.

Preferably, a first sealing ring is movably sleeved on the head body of the threaded pipe head positioned in the sealing groove.

Preferably, the two telescopic rods are parallel to each other.

The working principle is as follows: when the active carbon filter needs to be changed, the adjusting pipe is rotated, the adjusting pipe rotates to drive the threaded pipe head to rotate, so that the threaded pipe head leaves the threaded hole, then the sealing flange and the sealing flange are separated through dismounting the connecting bolt, then the sealing ring and the active carbon filter are taken out, then the sealing ring and the active carbon filter are updated, the reverse operation is reassembled, and the replacement can be completed.

(III) advantageous effects

The invention provides a backflow combustion chamber structure for an advanced cooling structure of an aircraft engine. The method has the following beneficial effects:

1. the invention provides a backflow combustion chamber structure for an advanced cooling structure of an aircraft engine, which can purify gas output after use through a purification mechanism when in use, so that the backflow combustion chamber structure is more environment-friendly when in use, and air pollution is avoided.

2. The invention provides a backflow combustion chamber structure for an advanced cooling structure of an aircraft engine, which can be used for dismounting a second sealing flange by rotating an adjusting pipe in the process that an outer pipe and other structures are fixed and difficult to dismount when in use, is simple to operate and is convenient for replacing an active carbon filter plate.

3. The invention provides a backflow combustion chamber structure for an advanced cooling structure of an aircraft engine, which can enable a second sealing ring to be constantly kept to be tightly attached to an outer pipe through the elasticity of a spring when in use, so that the backflow combustion chamber structure is higher in sealing property when in use.

4. The invention provides a backflow combustion chamber structure for an advanced cooling structure of an aircraft engine, which can enable the backflow combustion chamber structure to be more stable and durable through a ceramic membrane when in use, and enhances the use efficiency of fuel.

Drawings

FIG. 1 is a schematic partial front cross-sectional view of the present invention;

FIG. 2 is a schematic axial view of the purge mechanism of the present invention;

FIG. 3 is a schematic front cross-sectional view of the purification mechanism of the present invention;

FIG. 4 is a schematic side view of the regulator tube of the present invention;

FIG. 5 is a schematic side view of a cross-section of a number four seal ring of the present invention;

FIG. 6 is a schematic front sectional axial view of a second sealing flange according to the present invention.

Wherein, 1, a shell; 2. an ignition device; 3. a fuel output device; 4. a purification device; 5. an inner shell; 6. a ceramic membrane; 7. a gas stream inlet pipe; 8. a first sealing flange; 9. a connecting bolt; 10. an adjusting tube; 11. an outer tube; 12. a connecting seat; 13. a second sealing flange; 14. an air outlet pipe; 15. a chute; 16. a threaded tube head; 17. a first sealing ring; 18. a second sealing ring; 19. a spring; 20. a third sealing ring; 21. a telescopic rod; 22. an activated carbon filter plate; 23. a fourth sealing ring; 24. a sealing groove; 25. a threaded hole; 26. an encryption groove; 27. a combustion chamber; 28. and a connecting mechanism.

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.

Example (b):

as shown in fig. 1 to 6, an embodiment of the present invention provides a reflow combustion chamber structure for an advanced cooling structure of an aircraft engine, including an outer shell 1 and an inner shell 5, wherein a ceramic membrane 6 is fixedly disposed on an inner wall of the inner shell 5, the ceramic membrane 6 is used for enhancing stability, a connection mechanism 28 is fixedly disposed between the outer shell 1 and the inner shell 5, and a purification device 4 is fixedly connected to an air outlet of the connection mechanism 28.

Purifier 4 includes No. two sealing flange 13 and outer tube 11, one side of No. two sealing flange 13 is provided with sealing flange 8 No. one through a plurality of connecting bolt 9 are fixed, No. one sealing flange 8 and No. two sealing flange 13's inside has all been seted up and has been encrypted groove 26, it is used for strengthening the effect of leakproofness to encrypt groove 26, be provided with No. four sealing washer 23 between two encryption grooves 26, the inside fixed cover of No. four sealing washer 23 is equipped with activated carbon filter 22, activated carbon filter 22 is used for filtering the harmful gas who gives vent to anger.

No. two fixed connecting seats 12 that are provided with in one side center department that sealing flange 13 kept away from a sealing flange 8, sealing groove 24 has been seted up in one side center department that sealing flange 13 was kept away from to connecting seat 12, sealing groove 24 is close to No. two threaded hole 25 in one side inner wall center department of sealing flange 13, the inside thread cover of threaded hole 25 is equipped with threaded tube head 16, through threaded tube head 16 convenient connection and dismantlement, threaded tube head 16 keeps away from the fixed regulating pipe 10 that is provided with in one end of No. two sealing flange 13.

The inside of outer tube 11 is close to center department and has seted up spout 15, and the inside of spout 15 leans on both sides department to slide respectively and is provided with No. two sealing washers 18 and No. three sealing washer 20, and fixed being provided with two telescopic links 21 between No. two sealing washers 18 and No. three sealing washer 20, and the equal movable sleeve in pole body of two telescopic links 21 is equipped with spring 19, makes spring 19 more stable durable through telescopic link 21.

One end of the adjusting pipe 10 far away from the threaded pipe head 16 is positioned inside the outer pipe 11, the second sealing ring 18 is movably sleeved on the pipe body of the adjusting pipe 10, the third sealing ring 20 is fixedly sleeved on the pipe body of the adjusting pipe 10, the third sealing ring 20 is fixed, the second sealing ring 18 is conveniently pushed by the elastic force of the spring 19, an ignition device 2 and a fuel output device 3 are respectively and fixedly arranged between the outer shell 1 and the inner shell 5, the ignition device 2 is used for ignition, the fuel output device 3 is used for adding fuel, an air flow inlet pipe 7 is fixedly arranged at the air inlet of the outer shell 1, the inner shell 5 is positioned inside the outer shell 1, a combustion chamber 27 is arranged inside the inner shell 5, an air outlet pipe 14 is fixedly arranged at the center of one side of the first sealing flange 8 far away from the second sealing flange 13, a first sealing ring 17 is movably sleeved on the head body of the threaded pipe head 16 positioned inside the sealing groove 24, and the first sealing ring 17 plays a role in sealing enhancement, the two telescopic rods 21 are parallel to each other.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.