CN217029102U

CN217029102U - Frost prevention device suitable for aerospace engine precooler

Info

Publication number: CN217029102U
Application number: CN202122308017.1U
Authority: CN
Inventors: 杨萍; 王建磊; 张延超; 潘宁民; 李庆宇; 张澄宇; 曹阳; 李博; 任枫
Original assignee: Xi'an Jiasheng Zhizao Technology Co ltd
Current assignee: Xi'an Jiasheng Zhizao Technology Co ltd
Priority date: 2021-09-24
Filing date: 2021-09-24
Publication date: 2022-07-22
Anticipated expiration: 2031-09-24

Abstract

The utility model belongs to the technical field of an aeroengine precooler, and particularly relates to a frost prevention device suitable for the aeroengine precooler. According to the utility model, by starting the injection mechanism on the injection device, the pusher operates to generate thrust on the alcohol additive in the liquid storage tank, so that the alcohol additive is injected into the air inlet through the injection head to be mixed with air flow, and the condensation of frost can be effectively prevented; when the alcohol additives in the injection device are used up, the cleaning plate on the cleaning mechanism rotates under the action of air flow pushing, and ice and frost on the condensation pipe are automatically cleaned.

Description

Frost prevention device suitable for aerospace engine precooler

Technical Field

The utility model relates to the technical field of an aeroengine precooler, in particular to a frost prevention device suitable for an aerospace engine precooler.

Background

An aircraft engine is a highly complex and precise thermal machine and is used for providing power required by flying of an aircraft. The heart of the airplane is known as the 'industrial flower', which directly influences the performance, reliability and economy of the airplane and is an important embodiment of national science and technology, industry and national defense strength. A precooler of an aircraft engine is used for a device for precooling air entering the engine. The air compressor is arranged on the space shuttle engine and used for sucking outside air for compression and then reacting with fuel to release energy to push the engine to operate.

When the precooler precools air, the temperature in the air circulation channel of the precooler can be reduced to be below 0 ℃, so that the inner wall of the precooler is frosted, the channel is easily blocked, the precooling effect is reduced, and the frosted air is inconvenient to clean.

SUMMERY OF THE UTILITY MODEL

In order to solve the problems in the prior art, the utility model provides a frost prevention device suitable for an aerospace engine precooler, which has the characteristics of frost prevention and automatic cleaning.

In order to achieve the purpose, the utility model provides the following technical scheme: the frost prevention device comprises a precooler, an injection device and a cleaning mechanism, wherein the precooler is fixed on the outer side of an air compressor of the aerospace engine, the injection device is arranged on the inner side of the precooler, the bottom of the injection device is fixedly connected to the inner wall of the precooler, the cleaning mechanism is arranged on the outer side of the injection device, and the inner wall of the cleaning mechanism is clamped with the outer wall of the injection device.

The precooling device comprises a refrigerator and a precooling box, wherein the refrigerator is fixed on the outer side of the aerospace engine, the precooling box is fixedly arranged on the side wall of the refrigerator, and the precooling box is communicated with an air inlet of an air compressor of the aerospace engine.

The precooling box comprises a precooling box wall, an air inlet, an air outlet and a condensing tube, wherein the precooling box wall is fixed on the side wall of the refrigerating machine, one end of the precooling box wall is fixedly provided with the air inlet, the other end of the precooling box wall is fixedly provided with the air outlet, the air outlet is communicated with an air suction port of an air compressor of the aerospace engine, the inner wall of the precooling box wall is provided with the condensing tube, and two ends of the condensing tube are connected with the refrigerating machine.

As a preferable technical scheme of the anti-frost device suitable for the aerospace engine precooler, the spraying device comprises a spraying mechanism and a liquid storage tank, the spraying mechanism is located on one side of an air outlet, the spraying mechanism is fixed on the inner wall of the precooler tank, and the liquid storage tank is fixedly arranged on the outer side of one end of the spraying mechanism.

According to the preferable technical scheme of the frost prevention device suitable for the aerospace engine precooler, the injection mechanism comprises a fixed rod, a limiting rod and a pusher, the fixed rod is fixed on the inner wall of the precooling tank, the limiting rod is fixedly arranged on one side of the fixed rod, the pusher is arranged on the inner side of the limiting rod and fixed on the fixed rod, a liquid storage tank is arranged on the outer side of the limiting rod, the lower end of the liquid storage tank is fixed on the limiting rod, and one end of the pusher penetrates through the liquid storage tank.

According to the preferable technical scheme of the frost prevention device suitable for the aerospace engine precooler, the liquid storage tank comprises a liquid storage tank wall, a clamping ring and an injection head, the liquid storage tank wall is located on the inner side of the cleaning mechanism, the clamping ring is fixedly arranged on the outer wall of the liquid storage tank wall, the clamping ring and the cleaning mechanism are mutually clamped, and the injection head is fixedly arranged at one end of the liquid storage tank wall.

According to the preferable technical scheme of the frost prevention device suitable for the aerospace engine precooler, the cleaning mechanism comprises a sleeve, a clamping groove and a cleaning plate, the sleeve is sleeved on the outer side of the liquid storage tank and is located on the inner side of the wall of the precooling tank, the clamping groove is formed in the inner wall of the sleeve and is clamped with the clamping ring, and the cleaning plate is fixedly arranged on the outer wall of the sleeve.

Compared with the prior art, the utility model has the beneficial effects that:

1. in the using process, the jetting device is arranged, when the air compressor of the aerospace engine generates suction to air flow, and the air flow passes through the precooling box on the precooler, the pusher is enabled to operate to generate thrust to the alcohol additive in the liquid storage box by starting the jetting mechanism on the jetting device, so that the alcohol additive is jetted into the air inlet through the jetting head to be mixed with the air flow, and the condensation of frost can be effectively prevented.

2. When the cleaning mechanism is arranged in the using process of the utility model, when the alcohol additive in the injection device is used up or the temperature is too low to cause partial frost to be condensed on the wall of the precooling tank, the cleaning plate on the cleaning mechanism rotates under the pushing action of the air flow, and the frost on the condensing pipe is automatically cleaned.

Drawings

The accompanying drawings, which are included to provide a further understanding of the utility model and are incorporated in and constitute a part of this specification, illustrate embodiments of the utility model and together with the description serve to explain the principles of the utility model and not to limit the utility model. In the drawings:

FIG. 1 is a schematic view of the overall structure of the present invention;

FIG. 2 is a front view of the present invention;

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

FIG. 4 is a schematic cross-sectional view of a spraying device of the present invention;

FIG. 5 is a schematic cross-sectional view of a cleaning mechanism of the present invention.

In the figure: 1. a precooler; 11. a refrigerator; 12. a pre-cooling box; 121. precooling the wall of the tank; 122. an air inlet; 123. an air outlet; 124. a condenser tube; 2. an injection device; 21. an injection mechanism; 211. fixing the rod; 212. a limiting rod; 213. a pusher; 22. a liquid storage tank; 221. a tank wall; 222. a snap ring; 223. an injector head; 3. a cleaning mechanism; 31. a sleeve; 32. a card slot; 33. and (6) cleaning the plate.

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.

Examples

Referring to fig. 1-5, the present invention provides the following technical solutions: the utility model provides a frost prevention device suitable for aerospace engine precooler, includes precooler 1, injection apparatus 2 and clearance mechanism 3, and precooler 1 is fixed in the air compressor outside of aerospace engine, and the inboard of precooler 1 is equipped with injection apparatus 2, and injection apparatus 2's bottom fixed connection is on precooler 1's inner wall, and injection apparatus 2's the outside is equipped with clearance mechanism 3, and clearance mechanism 3's the inner wall blocks each other with injection apparatus 2's outer wall.

Referring to fig. 1, 2 and 3, specifically, the precooler 1 includes a refrigerator 11 and a precooling tank 12, the refrigerator 11 is fixed outside the space engine, the precooling tank 12 is fixed on the side wall of the refrigerator 11, and the precooling tank 12 is connected with an air inlet of an air compressor of the space engine in a through manner; the pre-cooling box 12 comprises a pre-cooling box wall 121, an air inlet 122, an air outlet 123 and a condensing tube 124, the pre-cooling box wall 121 is fixed on the side wall of the refrigerator 11, the air inlet 122 is fixed at one end of the pre-cooling box wall 121, the air outlet 123 is fixed at the other end of the pre-cooling box wall 121, the air outlet 123 is communicated with an air suction port of an air compressor of the space engine, the condensing tube 124 is arranged on the inner wall of the pre-cooling box wall 121, and two ends of the condensing tube 124 are connected with the refrigerator 11.

Referring to fig. 4 and 5, specifically, the spraying device 2 includes a spraying mechanism 21 and a liquid storage tank 22, the spraying mechanism 21 is located on one side of the air outlet 123, the spraying mechanism 21 is fixed on the inner wall of the pre-cooling tank wall 121, the liquid storage tank 22 is fixed on the outer side of one end of the spraying mechanism 21, and an alcohol additive for preventing airflow from frosting is placed in the liquid storage tank 22; the spraying mechanism 21 comprises a fixing rod 211, a limiting rod 212 and a pusher 213, the fixing rod 211 is fixed on the inner wall of the precooling tank wall 121, the limiting rod 212 is fixedly arranged on one side of the fixing rod 211, the pusher 213 is arranged on the inner side of the limiting rod 212, the pusher 213 is fixed on the fixing rod 211, the liquid storage tank 22 is arranged on the outer side of the limiting rod 212, the lower end of the liquid storage tank 22 is fixed on the limiting rod 212, and one end of the pusher 213 penetrates through the liquid storage tank 22; the liquid storage tank 22 comprises a liquid storage tank wall 221, a clamping ring 222 and an injection head 223, the liquid storage tank wall 221 is located on the inner side of the cleaning mechanism 3, the clamping ring 222 is fixedly arranged on the outer wall of the liquid storage tank wall 221, the clamping ring 222 and the cleaning mechanism 3 are mutually clamped, and the injection head 223 is fixedly arranged at one end of the liquid storage tank wall 221; the cleaning mechanism 3 comprises a sleeve 31, a clamping groove 32 and a cleaning plate 33, the sleeve 31 is sleeved outside the liquid storage tank 22, the sleeve 31 is located on the inner side of the precooling tank wall 121, the clamping groove 32 is formed in the inner wall of the sleeve 31, the clamping groove 32 is clamped with the clamping ring 222, the cleaning plate 33 is fixedly arranged on the outer wall of the sleeve 31, the frost prevention effect of the alcohol additive is very good, including but not limited to methanol, ethanol or n-propanol and the like, frost condensation can be effectively prevented, when an air compressor of the space engine generates suction force on air flow, and the air flow passes through the precooling tank 12 on the precooler 1, the jet mechanism 21 on the jet device 2 is started, so that the pusher 213 operates to generate thrust force on the alcohol additive in the liquid storage tank 22, the alcohol additive is jetted into the air inlet 122 through the jet head 223 to be mixed with the air flow, and condensation of the frost can be effectively prevented; when the alcohol additive in the spraying device 2 is used up or the temperature is too low, so that part of frost is condensed on the wall 121 of the precooling tank, the cleaning plate 33 on the cleaning mechanism 3 rotates under the pushing action of the air flow, and the frost on the condensation pipe 124 is automatically cleaned.

The utility model has the following use flow and working principle: when the utility model is used, firstly, the air outlet 123 on the precooler 1 is fixedly connected with the air suction inlet of the air compressor of the engine, then the alcohol additive is put into the liquid storage tank 22, then the refrigerating machine 11 on the precooler 1 is started, when the space engine runs, the air compressor is started to generate suction force, when the air flow passes through the precooler 12, the air flow with higher temperature is cooled by the condensing pipe 124, when the temperature is too low and frost is generated on the precooler wall 121, the pusher 213 on the injection mechanism 21 is started, so that the alcohol additive in the liquid storage tank 22 is sprayed to the air inlet 122 by the pusher 213 through the injection head 223, the alcohol additive is mixed with the air flow to effectively prevent the air flow from being precooled and condensed, when the air flow passes through the cleaning mechanism 3, the air flow pushes the cleaning plate 33, so that the sleeve 31 rotates on the outer side of the liquid storage tank 22 through the clamping groove 32, and the cleaning plate 33 cleans the condensing pipe 124, the situation that the precooling effect is affected by frost generated in the precooling tank wall 121 due to the fact that the alcohol additive is used up is prevented.

The embodiments of the present invention are preferred embodiments of the present invention, and the scope of the present invention is not limited by these embodiments, so: equivalent changes made according to the structure, shape and principle of the utility model shall be covered by the protection scope of the utility model.

Claims

1. The utility model provides a frost prevention device suitable for aerospace engine precooler, includes precooler (1), injection apparatus (2) and clearance mechanism (3), its characterized in that: the precooler (1) is fixed on the outer side of an air compressor of the space engine, the inner side of the precooler (1) is provided with an injection device (2), the bottom of the injection device (2) is fixedly connected to the inner wall of the precooler (1), the outer side of the injection device (2) is provided with a cleaning mechanism (3), and the inner wall of the cleaning mechanism (3) is clamped with the outer wall of the injection device (2) mutually.

2. The frost prevention device for an aerospace engine precooler as claimed in claim 1, wherein: the precooler (1) comprises a refrigerator (11) and a precooling box (12), the refrigerator (11) is fixed on the outer side of the space engine, the precooling box (12) is fixedly arranged on the side wall of the refrigerator (11), and the precooling box (12) is communicated with an air inlet of an air compressor of the space engine.

3. The frost prevention device suitable for an aerospace engine precooler as claimed in claim 2, wherein: precooling case (12) are including precooling tank wall (121), air intake (122), air exit (123) and condenser pipe (124), precooling tank wall (121) are fixed on the lateral wall of refrigerator (11), the fixed air intake (122) that is equipped with of one end of precooling tank wall (121), the fixed air exit (123) that is equipped with of the other end of precooling tank wall (121), air exit (123) and space engine's air compressor induction port through connection, be equipped with condenser pipe (124) on the inner wall of precooling tank wall (121), the both ends and the refrigerator (11) of condenser pipe (124) are connected.

4. The frost prevention device for an aerospace engine precooler as claimed in claim 1, wherein: injection apparatus (2) include injection mechanism (21) and liquid reserve tank (22), injection mechanism (21) are located one side of air exit (123), injection mechanism (21) are fixed on the inner wall of precooling tank wall (121), the fixed liquid reserve tank (22) that is equipped with in the one end outside of injection mechanism (21), placed the alcohol type additive that prevents the air current frosting in liquid reserve tank (22).

5. The frost prevention device for an aerospace engine precooler as claimed in claim 4, wherein: injection mechanism (21) includes dead lever (211), gag lever post (212) and impeller (213), dead lever (211) are fixed on the inner wall of precooling tank wall (121), one side of dead lever (211) is fixed and is equipped with gag lever post (212), the inboard of gag lever post (212) is equipped with impeller (213), impeller (213) are fixed on dead lever (211), the outside of gag lever post (212) is equipped with liquid reserve tank (22), the lower extreme of liquid reserve tank (22) is fixed on gag lever post (212), liquid reserve tank (22) is run through to the one end of impeller (213).

6. The frost prevention device for an aerospace engine precooler as claimed in claim 4, wherein: liquid reserve tank (22) are including liquid reserve tank wall (221), snap ring (222) and injection head (223), liquid reserve tank wall (221) are located clearance mechanism (3) inboard, fixed snap ring (222) that are equipped with on the outer wall of liquid reserve tank wall (221), snap ring (222) and clearance mechanism (3) block each other with, the fixed injection head (223) that are equipped with in one end of liquid reserve tank wall (221).

7. The frost prevention device suitable for an aerospace engine precooler as claimed in claim 1, wherein: clearance mechanism (3) are including sleeve (31), draw-in groove (32) and clearance board (33), sleeve (31) cup joint in the liquid reserve tank (22) outside, sleeve (31) are located the inboard of precooling tank wall (121), the inner wall of sleeve (31) is equipped with draw-in groove (32), draw-in groove (32) and snap ring (222) block, the fixed clearance board (33) that is equipped with of outer wall of sleeve (31).