Aircraft test post cooling mechanism

Abstract

The aircraft post-experiment cooling mechanism of the present invention belongs to the field of aircraft cooling technology, and includes a cooling device, a heat recovery device, and a circulating refrigeration device. The cooling device is suitable for supplying cooling energy to aircraft equipment to be cooled. The heat recovery device includes a heat transfer device, and the heat transfer device generates a thermal connection between the cooling device and a cabin exhaust system so as to transfer the waste heat generated by the cabin exhaust system of the cooling device to the cooling device. The present invention utilizes a heat recovery device to recover the output heat of the aircraft, and drives a circulating refrigeration device to provide a cold source for the equipment, thereby realizing the cooling of the equipment in the aircraft. Compared with traditional equipment cooling devices, the present invention has the characteristics of large cooling capacity, small volume, energy saving, reliability and safety, and can accurately control the vaporization process of liquid nitrogen, and maximizes the use of the latent heat of liquid nitrogen (i.e., the cold released when liquid nitrogen vaporizes into nitrogen) and the cold of low-temperature nitrogen to improve the cooling effect.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft cooling, in particular to an aircraft post-experiment cooling mechanism. Background Art

[0002] The thermal fatigue life of aircraft components is crucial to the flight safety of the aircraft and plays an important role in the life protection of pilots. With the substantial improvement of modern aircraft design indicators, the design of aircraft components adopts new materials, new structures and new processes, which brings thermal fatigue risks. An effective means to improve flight safety is to conduct sufficient and effective thermal fatigue test verification on aircraft components. During the flight, the aircraft will generate a lot of heat due to friction with the external atmosphere, so it is necessary to design thermal protection for the aircraft and conduct experimental treatment on the thermal protection design in order to achieve better protection effect. At present, there is little research on aircraft thermal protection at home and abroad, and the cooling effect of the equipment inside the aircraft is poor and the cooling efficiency is low. Summary of the invention

[0003] The purpose of the present invention is to provide an aircraft post-experiment cooling mechanism to solve the problems raised in the above background technology that there is currently little research on aircraft thermal protection at home and abroad, the cooling effect of in-flight equipment is poor, and the cooling efficiency is low.

[0004] The technical solution of the present invention is: it includes a cooling device, a heat recovery device, and a circulating refrigeration device, the cooling device is suitable for supplying cooling energy to the aircraft equipment to be cooled, the heat recovery device includes a heat transfer device, the heat transfer device creates a thermal connection between the cooling device and a cabin air extraction system so as to transfer the waste heat generated by the cabin air extraction system of the cooling device to the cooling device, the heat transfer device includes a heat transfer circuit channel, and a liquid heat transfer medium heated by the waste heat of the cooling device circulates in the heat transfer circuit channel, the heat transfer device is further suitable for transferring the waste heat generated by the heat-generating aircraft equipment to the cooling device, wherein the cooling device is used to supply cooling energy to the area where the heat-generating aircraft equipment generates heat.

[0005] Furthermore, the heat recovery device also includes a first liquid nitrogen storage tank and a heat exchanger. The first liquid nitrogen storage tank is connected to the cooling device through a first connecting pipe, and the heat transfer device transfers heat to the first liquid nitrogen storage tank.

[0006] Furthermore, a heat pipe accumulator is included. The first liquid nitrogen storage tank is connected to the heat pipe accumulator through a second connecting pipe. One side of the heat pipe accumulator is connected to a turbine. The heat pipe accumulator absorbs a large amount of heat and turns into steam. The steam enters the turbine to expand and do work. The steam enters the heat exchanger to condense and release heat as a low-pressure and low-temperature working fluid. The heat exchanger is a coil-shaped closed cavity made of copper tubes. The heat pipe accumulator is arranged at the heat output position of the heat transfer device.

[0007] Furthermore, a first flow valve is provided between the turbine and the heat exchanger.

[0008] Furthermore, a second nitrogen storage tank is included, and the second nitrogen storage tank is connected to the heat exchanger through a third connecting pipe, and a second flow valve is arranged on the third connecting pipe.

[0009] Furthermore, the second nitrogen storage tank is connected to a nitrogen nozzle via a fourth connecting pipe, a third flow valve is provided on the fourth connecting pipe, and the first connecting pipe, the second connecting pipe, the third connecting pipe and the fourth connecting pipe are all made of stainless steel.

[0010] Furthermore, a controller is installed on the second nitrogen storage tank, and a pressure sensor is installed on the second nitrogen storage tank. The controller is used to control the opening or closing of the first flow valve, the second flow valve and the third flow valve according to the signal of the pressure sensor, so that the heat exchanger and the nitrogen nozzle can achieve double cooling. The heat exchanger is arranged upstream of the airflow direction of the nitrogen nozzle.

[0011] Furthermore, the heat transfer loop channel has airflow, the heat transfer loop channel is configured to allow the airflow to circulate, and the heat transfer loop channel is provided with cooling holes, which are arranged upstream of the airflow direction of the liquid nitrogen dual cooling device.

[0012] Furthermore, the circulating refrigeration device includes a compressor, an exchanger, an expansion valve, and an evaporator located in the heat transfer circuit channel. A cooling pipe is provided at the bottom of the compressor. The compressor works under the drive of the turbine. The refrigerant becomes a high-temperature and high-pressure refrigerant after passing through the compressor and enters the exchanger for condensation, becoming a high-pressure and low-temperature refrigerant liquid. Then, it enters the evaporator after passing through the expansion valve to absorb heat. The refrigerant enters the compressor again, and the cooling gas is discharged from the heat transfer circuit channel through the cooling pipe to complete the refrigeration cycle. The exchanger is a working fluid / fuel heat exchanger.

[0013] Furthermore, a circulation fan is also provided in the heat transfer circuit channel, and the gas exhausted from the cooling pipe passes through the circulation fan and circulates in the heat transfer circuit channel.

[0014] The present invention provides an aircraft post-experiment cooling mechanism through improvement, which has the following improvements and advantages compared with the prior art:

[0015] The invention utilizes a heat recovery device to recover the output heat of the aircraft and drives a circulating refrigeration device to provide a cold source for the equipment, thereby realizing cooling of the equipment inside the aircraft. Compared with a traditional equipment cooling device, the invention has the characteristics of large refrigeration capacity, small volume, energy saving, reliability and safety, and can accurately control the vaporization process of liquid nitrogen, thereby maximally utilizing the latent heat of liquid nitrogen (i.e., the cold released when liquid nitrogen vaporizes into nitrogen gas) and the cold of low-temperature nitrogen gas to improve the cooling effect. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The present invention will be further explained below in conjunction with the accompanying drawings and Examples:

[0017] Figure 1 This is a schematic diagram of the cooling mechanism structure after the aircraft experiment of the present invention;

[0018] Explanation of the reference numerals: 1. heat transfer device; 2. first liquid nitrogen storage tank; 3. heat pipe accumulator; 4. turbine; 5. heat exchanger; 6. second nitrogen storage tank; 7. nitrogen nozzle; 8. controller; 9. pressure sensor; 10. heat transfer circuit channel; 12. compressor; 13. exchanger; 14. expansion valve; 15. evaporator; 16. cooling pipe; 17. circulating fan; 18. first flow valve; 19. second flow valve; 20. third flow valve. DETAILED DESCRIPTION

[0019] The present invention will be described in detail below in conjunction with the accompanying drawings, and the technical solutions in the embodiments of the present invention will be clearly and completely described. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0020] The present invention provides an aircraft post-experiment cooling mechanism through improvement, as shown in the figure, including a cooling device, a heat recovery device, and a circulating refrigeration device. The cooling device is suitable for supplying cooling energy to the aircraft equipment to be cooled. The heat recovery device includes a heat transfer device 1. The heat transfer device 1 creates a thermal connection between the cooling device and the cabin air extraction system so as to transfer the waste heat generated by the cabin air extraction system of the cooling device to the cooling device. The heat transfer device 1 includes a heat transfer circuit channel 10. The liquid heat transfer medium heated by the waste heat of the cooling device circulates in the heat transfer circuit channel 10. The heat transfer device 1 is further suitable for transferring the waste heat generated by the heat-generating aircraft equipment to the cooling device, wherein the cooling device is used to supply cooling energy to the area where the heat-generating aircraft equipment generates heat.

[0021] The heat recovery device also includes a first liquid nitrogen storage tank 2 and a heat exchanger 5 . The first liquid nitrogen storage tank 2 is connected to the cooling device through a first connecting pipe, and the heat transfer device 1 transfers heat to the first liquid nitrogen storage tank 2 .

[0022] The heat pipe accumulator 3 is also included. The first liquid nitrogen storage tank 2 is connected to the heat pipe accumulator 3 through a second connecting pipe. One side of the heat pipe accumulator 3 is connected to a turbine 4. The heat pipe accumulator 3 absorbs a large amount of heat and turns into steam. The steam enters the turbine 4 to expand and do work. The steam enters the heat exchanger 5 to condense and release heat after becoming a low-pressure and low-temperature working fluid. The heat exchanger 5 is a coil-shaped closed cavity made of copper tubes. The heat pipe accumulator 3 is arranged at the heat output position of the heat transfer device 1.

[0023] A first flow valve 18 is provided between the turbine 4 and the heat exchanger 5 .

[0024] The second nitrogen storage tank 6 is also included. The second nitrogen storage tank 6 is connected to the heat exchanger 5 through a third connecting pipe. A second flow valve 19 is provided on the third connecting pipe.

[0025] The second nitrogen storage tank 6 is connected to the nitrogen nozzle 7 via a fourth connecting pipe, a third flow valve 20 is provided on the fourth connecting pipe, and the first connecting pipe, the second connecting pipe, the third connecting pipe and the fourth connecting pipe are all made of stainless steel.

[0026] A controller 8, model S7-300, is installed on the second nitrogen storage tank 6. A pressure sensor 9, model LLBLS-I, is installed on the second nitrogen storage tank 6. The controller 8 is used to control the opening or closing of the first flow valve 18, the second flow valve 19 and the third flow valve 20 according to the signal of the pressure sensor 9, so that the heat exchanger 5 and the nitrogen nozzle 7 can achieve double cooling. The heat exchanger 5 is arranged upstream of the airflow direction of the nitrogen nozzle 7. The controller 8 controls the opening or closing of the first flow valve 18, the second flow valve 19 and the third flow valve 20 according to the signal of the pressure sensor 9, so that the heat exchanger 5 and the nitrogen nozzle 7 can achieve double cooling. In the aircraft test, the heat exchanger 5 and the nitrogen nozzle 7 of the liquid nitrogen double cooling device are arranged in the heat transfer circuit channel 10. There is airflow in the heat transfer circuit channel 10. The heat transfer circuit channel 10 is an annular closed duct that can circulate the airflow. The heat transfer circuit channel 10 is driven to circulate the airflow by arranging a circulating fan 17.

[0027] There is airflow in the heat transfer loop channel 10, and the heat transfer loop channel 10 is configured to allow the airflow to circulate, and a cooling through hole is provided in the heat transfer loop channel 10. The cooling through hole is provided upstream of the airflow direction of the liquid nitrogen dual cooling device.

[0028] The circulating refrigeration device includes a compressor 12, an exchanger 13, an expansion valve 14, and an evaporator 15 located in a heat transfer loop channel 10. A cooling pipe 16 is provided at the bottom of the compressor 12. The compressor 12 works under the drive of the turbine 4. The refrigerant becomes a high-temperature and high-pressure refrigerant after passing through the compressor 12 and enters the exchanger 13 for condensation to become a high-pressure and low-temperature refrigerant liquid. Then, it enters the evaporator 15 after passing through the expansion valve 14 to absorb heat. The refrigerant enters the compressor 12 again, and the cooling gas is discharged from the heat transfer loop channel 10 through the cooling pipe 16 to complete the refrigeration cycle. The exchanger 13 is a working fluid / fuel heat exchanger 13.

[0029] A circulation fan 17 is also provided in the heat transfer circuit channel 10 , and the gas exhausted from the cooling pipe 16 passes through the circulation fan 17 and circulates in the heat transfer circuit channel 10 .

[0030] Working principle: The cooling device is suitable for supplying cooling energy to the aircraft equipment to be cooled. The heat transfer device 1 creates a thermal connection between the cooling device and the cabin exhaust system so as to transfer the waste heat generated by the cabin exhaust system of the cooling device to the cooling device. The liquid heat transfer medium heated by the waste heat of the cooling device circulates in the heat transfer circuit channel 10, and transfers the heat to the first liquid nitrogen storage tank 2 through the heat transfer device 1. The first liquid nitrogen storage tank 2 transfers the heat to the heat pipe accumulator 3. The heat pipe accumulator 3 absorbs a large amount of heat and becomes steam, which enters the turbine 4. The liquid nitrogen expands and does work, and then enters the heat exchanger 5 to condense and release heat as a low-pressure and low-temperature working fluid. At the same time, the controller 8 controls the first flow valve 18 to open, so that the liquid nitrogen enters the heat exchanger 5 located in the heat transfer loop channel 10. The liquid nitrogen vaporizes in the heat exchanger 5 and turns from liquid nitrogen to low-temperature nitrogen gas. The vaporization process generates a large amount of cold energy, which reduces the temperature of the heat exchanger 5. The heat exchanger 5 is placed in the heat transfer loop channel 10. The airflow in the heat transfer loop channel 10 flows through the outer surface of the heat exchanger 5, absorbs cold energy from the heat exchanger 5, and the airflow temperature is reduced. The low-temperature nitrogen in the heat exchanger 5 The gas enters the second nitrogen storage tank 6 through the second connecting pipe of the heat exchanger 5 channel. The computer detects the pressure in the second nitrogen storage tank 6 through the pressure sensor 9, and can monitor the vaporization process of the liquid nitrogen. When the liquid nitrogen is completely vaporized, the pressure value in the second nitrogen storage tank 6 reaches the highest peak. The computer controls the second flow valve 19 to open, and the low-temperature nitrogen is discharged into the heat transfer loop channel 10, and mixed with the airflow in the heat transfer loop channel 10 to reduce the airflow temperature again. The gas in the heat transfer loop channel 10 passes through the compressor 12. The compressor 12 works under the drive of the turbine 4. The refrigerant becomes high-temperature and high-pressure refrigerant after passing through the compressor 12 and enters the exchanger 13 to condense and become a high-pressure and low-temperature refrigerant liquid. After passing through the expansion valve 14, it enters the evaporator 15 to absorb heat. The refrigerant enters the compressor 12 again, and the cooling gas is discharged into the heat transfer loop channel 10 through the cooling pipe 16 to complete the refrigeration cycle. The gas discharged from the cooling pipe 16 passes through the circulating fan 17 and circulates in the heat transfer loop channel 10. The circulating fan 17 ensures that the cold air circulates in the heat transfer loop channel 10 to achieve the cooling effect and improve the cooling efficiency.

[0031] The above description of the disclosed embodiments enables one skilled in the art to implement or use the present invention. Various modifications to these embodiments will be apparent to one skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention will not be limited to the embodiments shown herein, but rather to the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. Aircraft cooling mechanism after experiment, Features: The invention comprises a cooling device, a heat recovery device and a circulating refrigeration device, wherein the cooling device is used to supply cooling energy to aircraft equipment to be cooled, the heat recovery device comprises a heat transfer device (1), the heat transfer device (1) creates a thermal connection between the cooling device and a cabin air extraction system so as to transfer waste heat generated by the cabin air extraction system to the cooling device, and the heat recovery device comprises a heat transfer circuit channel (10), in which a liquid heat transfer medium heated by waste heat circulates; The mechanism further comprises a first liquid nitrogen storage tank (2) and a heat exchanger (5); the first liquid nitrogen storage tank (2) is connected to the heat transfer device via a first connecting pipe, and the heat transfer device (1) transfers heat to the first liquid nitrogen storage tank (2); The mechanism further comprises a heat pipe accumulator (3), the first liquid nitrogen storage tank (2) is connected to the heat pipe accumulator (3) via a second connecting pipe, one side of the heat pipe accumulator (3) is connected to a turbine (4), the liquid nitrogen in the heat pipe accumulator (3) absorbs a large amount of heat and turns into steam, enters the turbine (4) to expand and do work, and the low-pressure and low-temperature working fluid enters the heat exchanger (5) to condense and release heat, the heat exchanger (5) is a coil-shaped closed cavity made of copper tubes, and the heat pipe accumulator (3) is arranged at the heat output position of the heat transfer device (1); A first flow valve (18) is provided between the turbine (4) and the heat exchanger (5); The mechanism further comprises a second nitrogen storage tank (6), the second nitrogen storage tank (6) being connected to the heat exchanger (5) via a third connecting pipe, and a second flow valve (19) being arranged on the third connecting pipe; The second nitrogen storage tank (6) is connected to a nitrogen nozzle (7) via a fourth connecting pipe, and a third flow valve (20) is provided on the fourth connecting pipe; A controller (8) is installed on the second nitrogen storage tank (6), and a pressure sensor (9) is installed on the second nitrogen storage tank (6). The controller (8) is used to control the opening or closing of the first flow valve (18), the second flow valve (19) and the third flow valve (20) according to a signal from the pressure sensor (9), so that the heat exchanger (5) and the nitrogen nozzle (7) can achieve double cooling. The heat exchanger (5) is arranged upstream of the airflow direction of the nitrogen nozzle (7); The circulating refrigeration device comprises a compressor (12), an exchanger (13), an expansion valve (14) and an evaporator (15) located in the heat transfer circuit channel (10).

2. The aircraft post-experiment cooling mechanism according to claim 1, Features: The first communicating pipe, the second communicating pipe, the third communicating pipe and the fourth communicating pipe are all made of stainless steel.

3. The aircraft post-experiment cooling mechanism according to claim 1, Features: The heat transfer circuit channel (10) has an airflow in it, the heat transfer circuit channel (10) is configured to enable the airflow to circulate, and the heat transfer circuit channel (10) is provided with cooling through holes.

4. The aircraft post-experiment cooling mechanism according to claim 1, Features: A cooling pipe (16) is provided at the bottom of the compressor (12). The compressor (12) works under the drive of the turbine (4). The refrigerant becomes high-temperature and high-pressure refrigerant after passing through the compressor (12) and enters the exchanger (13) for condensation to become high-pressure and low-temperature refrigerant liquid. The refrigerant then enters the evaporator (15) for heat absorption after passing through the expansion valve (14). The refrigerant enters the compressor (12) again, and the cooling gas is discharged from the heat transfer circuit channel (10) through the cooling pipe (16) to complete the refrigeration cycle. The exchanger (13) is a working fluid / fuel heat exchanger.

5. The aircraft post-experiment cooling mechanism according to claim 4, Features: A circulation fan (17) is also provided in the heat transfer circuit channel (10), and the gas discharged from the cooling pipe (16) passes through the circulation fan (17) and circulates in the heat transfer circuit channel (10).

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