A high-altitude performance test device for an aero-engine oil-gas heat exchanger

Abstract

An aero-engine oil-gas heat exchanger high-altitude performance test device, comprising a test cabin, an oil system, and an air system; the oil system comprises an oil tank, an oil supply pump, and an oil heater; the oil tank is connected with the oil supply pump at an oil outlet, the oil supply pump is connected with the oil heater, and the oil heater is connected with the test cabin at an oil inlet; the test cabin is connected with the oil tank at an oil return port through a pipeline; the air system comprises an air dryer, a turbine expander, a mixing tank, and a vacuum pump; the air dryer is connected with a gas source at an air inlet, the air dryer is connected with the turbine expander at an air outlet, the turbine expander is connected with the mixing tank through a second one-way valve, and the mixing tank is connected with the test cabin at an air inlet through a pipeline; the test cabin is connected with a radiator at an air outlet, and the vacuum pump is connected with the outlet end of the radiator.

Description

Technical Field

[0001] This invention relates to the field of aero-engine testing technology, and in particular to a high-altitude performance testing device for aero-engine oil-gas heat exchangers, which is suitable for testing the heat dissipation performance and flow resistance characteristics of aero-engine accessory oil-gas heat exchangers. Background Technology

[0002] When an engine operates at high altitudes, the fuel flow is extremely low due to the low airflow. Conventional engine designs cannot effectively cool the lubricating oil solely through fuel cooling; an oil-gas heat exchanger is necessary to further reduce the lubricating oil temperature. Currently, due to the lack of experimental methods, analysis relies solely on theoretical calculations. However, in the low Reynolds number environment at high altitudes, theoretical calculations have significant errors and cannot accurately assess the performance of the oil-gas heat exchanger. Therefore, high-altitude simulation tests are needed to analyze and evaluate its performance.

[0003] With the development of the aviation industry and the engine industry, oil-gas heat exchangers are increasingly used in aircraft and engines for cooling and heat dissipation of the engine's lubrication system. The heat dissipation performance and flow resistance characteristics of oil-gas heat exchangers under different altitudes and intake conditions are necessary design inputs when designing aircraft and engine-related systems. Currently, the evaluation of the heat dissipation performance and flow resistance characteristics of oil-gas heat exchangers in design and manufacturing mainly relies on software calculations and ground-based heat dissipation performance tests, and cannot evaluate their heat dissipation performance and flow resistance characteristics under mid-to-high altitude operating environments. This is especially true for oil-gas heat exchangers used in high-altitude, long-endurance engines, where the air temperature and pressure are low, and the air density is thin, causing changes in the heat dissipation performance, particularly the flow resistance, compared to ground conditions. Due to the lack of test rigs, experimental research on the heat dissipation performance and flow resistance characteristics of oil-gas heat exchangers under high-altitude conditions can only be conducted on high-altitude test platforms along with the engine, which carries significant development risks. Summary of the Invention

[0004] The main objective of this invention is to provide a high-altitude performance testing device for an aero-engine oil-gas heat exchanger, aiming to solve the aforementioned technical problems.

[0005] To achieve the above objectives, the present invention proposes a high-altitude performance test device for an aero-engine oil-gas heat exchanger, comprising: a test chamber, a lubricating oil system, and an air system;

[0006] The lubricating oil system includes an oil tank, an oil supply pump, and an oil heater; the oil outlet of the oil tank is connected to the oil supply pump, the oil supply pump is connected to the oil heater, and the oil outlet of the oil heater is connected to the oil inlet of the test chamber; the oil outlet of the test chamber is connected to the oil return port of the oil tank through a pipeline.

[0007] The air system includes an air dryer, a turbo expander, a mixing chamber, and a vacuum pump; the air inlet of the air dryer is connected to the air supply source, the air outlet of the air dryer is connected to the turbo expander, the turbo expander is connected to the mixing chamber after passing through a second one-way valve, and the mixing chamber is connected to the air inlet of the test chamber through a pipeline.

[0008] The air outlet of the test chamber is connected to a radiator, and the vacuum pump is connected to the outlet end of the radiator. After the air from the test chamber is cooled by the radiator, it is extracted by the vacuum pump and discharged into the atmosphere.

[0009] Preferably, the lubricating oil system further includes a pressure regulating valve and a lubricating oil flow meter; the lubricating oil flow meter is connected in series after the pressure regulating valve; and both the pressure regulating valve and the lubricating oil flow meter are installed on the connecting pipeline between the oil outlet of the test chamber and the oil return port of the lubricating oil tank; there are two pressure regulating valves, namely a lubricating oil pressure fine adjustment valve and a lubricating oil pressure coarse adjustment valve, which are connected in parallel; there are two lubricating oil flow meters, namely a first lubricating oil flow meter and a second lubricating oil flow meter, which are connected in parallel.

[0010] Preferably, the lubricating oil system further includes a third check valve, a safety valve, and a lubricating oil flow regulating valve; the inlet ends of the safety valve and the lubricating oil flow regulating valve are both connected to the outlet pipe of the lubricating oil heater; the third check valve is connected in series after the lubricating oil flow meter; the outlet ends of the third check valve, the safety valve, and the lubricating oil flow regulating valve are connected to the return port of the lubricating oil tank through pipelines; there are two lubricating oil flow regulating valves, namely a lubricating oil flow coarse adjustment valve and a lubricating oil flow fine adjustment valve; the lubricating oil flow coarse adjustment valve and the lubricating oil flow fine adjustment valve are arranged in parallel.

[0011] Preferably, an inlet valve is provided at the oil inlet of the test chamber and an outlet valve is provided at the oil outlet; the pipeline between the pressure regulating valve and the outlet valve, and the pipeline between the inlet valve and the lubricating oil heater are connected by a connecting pipe, and a manual valve h is provided on the connecting pipe.

[0012] Preferably, an air flow meter and an air flow regulating valve are connected in series on the pipeline between the mixing tank and the air inlet of the test chamber; the number of air flow meters is three, namely a first air flow meter, a second air flow meter and a third air flow meter, which are connected in parallel; the number of air flow regulating valves is three, namely a first air flow regulating valve, a second air flow regulating valve and a third air flow regulating valve, which are connected in parallel, with the first air flow regulating valve being a fine-tuning valve and the second and third air flow regulating valves being coarse-tuning valves.

[0013] Preferably, there are three radiators, namely a first radiator, a second radiator and a third radiator, which are arranged in parallel and are all water-cooled radiators; there are two vacuum pumps, namely a first vacuum pump and a second vacuum pump, both of which are installed on the pipeline after the radiators.

[0014] Preferably, the outlet of the radiator is connected to the pipeline between the air dryer and the turbine expander via an auxiliary air pipeline, and an auxiliary air control valve and a manual valve a are connected in series on the auxiliary air pipeline.

[0015] Preferably, an air inlet bypass is provided between the air outlet pipe of the air dryer and the mixing box. A bypass air flow regulating valve, a bypass air three-way regulating valve, and a fourth radiator are connected in series in the air inlet bypass. A manual valve b is connected to the bypass air three-way regulating valve. The outlet end of the manual valve b and the outlet end of the fourth radiator are connected together to the mixing box. The fourth radiator is a water-cooled radiator.

[0016] Preferably, a turbine expander precooling air regulating valve and a first check valve are connected to the turbine expander. The outlets of the turbine expander precooling air regulating valve and the first check valve are combined and then connected to the mixing tank via the turbine expander outlet regulating valve. The outlets of the turbine expander precooling air regulating valve and the first check valve are also connected to a silencer.

[0017] Preferably, the air outlet pipe of the air dryer is also connected to two air bearings of the turbine expander, and a turbine expander air bearing supply valve A and a turbine expander air bearing supply valve B are installed on the pipe. The turbine expander air bearing supply valve B is used to control one of the air bearings, and the turbine expander air bearing supply valve A controls both air bearings at the same time.

[0018] Due to the adoption of the above technical solution, the beneficial effects of the present invention are as follows:

[0019] The high-altitude performance testing apparatus for aero-engine oil-gas heat exchangers provided by this invention connects a lubricating oil system, an air system, and a test chamber. The lubricating oil system simulates the lubricating oil supply pressure, flow rate, and temperature under high-altitude conditions for the test chamber. The air system, including an air dryer, a turbine expander, and an air mixing chamber, provides the test chamber with the air inlet pressure and temperature requirements simulating high-altitude conditions. A vacuum pump and a regulating valve at the front of the test chamber simulate the air inlet pressure and flow rate requirements under high-altitude conditions. This testing apparatus enables experimental research on the heat dissipation performance and flow resistance characteristics of oil-gas heat exchangers under high-altitude conditions.

[0020] This invention can simulate the heat exchange conditions of an oil-gas heat exchanger at high altitude and low Reynolds number, and evaluate the heat dissipation performance and flow resistance characteristics of the radiator. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort.

[0022] Figure 1 This is a schematic diagram of the high-altitude performance testing device for an aero-engine oil-gas heat exchanger provided by the present invention.

[0023] Explanation of icon numbers:

[0024] 1. Silencer; 2. Air dryer; 3. Air dryer control valve A; 4. Turbine expander inlet regulating valve; 5. Air dryer control valve B; 6. Turbine expander precooling air regulating valve; 7. First check valve; 8. Turbine expander; 9. Second check valve; 10. Turbine expander outlet regulating valve; 11. Manual valve a; 12. Auxiliary air control valve; 13. Bypass air flow coarse adjustment valve; 14. Bypass air flow fine adjustment valve; 15. Turbine expander air bearing supply valve A; 16. Turbine expander air bearing supply valve B; 17. Bypass air three-way regulating valve; 18. Mixing box; 19. Manual valve b; 20. Fourth radiator; 21. First water supply valve; 22. Manual valve c; 23. Manual valve d; 24. Manual valve e; 25. First air flow meter; 26. Second air flow meter; 27. Third air flow meter. Flow meter; 28. First air flow regulating valve; 29. ​​Second air flow regulating valve; 30. Third air flow regulating valve; 31. Test chamber; 32. First vacuum pump; 33. Second vacuum pump; 34. First radiator; 35. Second radiator; 36. Third radiator; 37. Second water supply valve; 38. Oil tank; 39. Manual valve f; 40. Oil supply pump; 41. Manual valve g; 42. Oil heater; 43. Safety valve; 44. Oil flow coarse adjustment valve; 45. Oil flow fine adjustment valve; 46. Inlet valve; 47. Manual valve h; 48. Outlet valve; 49. Oil pressure fine adjustment valve; 50. Oil pressure coarse adjustment valve; 51. First oil flow meter; 52. Second oil flow meter; 53. Manual valve i; 54. Manual valve j; 55. Third check valve; 56. Manual valve k; 57. Connecting pipe. Detailed Implementation

[0025] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0026] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present invention are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indication will also change accordingly.

[0027] Furthermore, the use of terms such as "first" and "second" in this invention is for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of that feature. Additionally, the technical solutions of the various embodiments can be combined with each other, but only on the basis of being achievable by those skilled in the art. When the combination of technical solutions is contradictory or impossible to implement, such a combination of technical solutions should be considered non-existent and not within the scope of protection claimed by this invention.

[0028] Combination Figure 1 The image shows a specific embodiment of a high-altitude performance testing device for an aero-engine oil-gas heat exchanger provided by the present invention. The testing device includes: a test chamber 31, a lubricating oil system, and an air system.

[0029] The lubricating oil system includes an oil tank 38, an oil supply pump 40, and an oil heater 42. The oil outlet of the oil tank 38 is connected to the oil supply pump 40, the oil supply pump 40 is connected to the oil heater 42, and the oil outlet of the oil heater 42 is connected to the oil inlet of the test chamber 31. The oil outlet of the test chamber 31 is connected to the oil return port of the oil tank 38 through a pipeline. A manual valve k56 is installed at the oil return port of the oil tank 38, a manual valve f39 is installed between the oil supply pump 40 and the oil tank, and a manual valve g41 is installed between the oil supply pump 40 and the oil heater.

[0030] The air system includes an air dryer 2, a turbo expander 8, a mixing chamber 18, and a vacuum pump. The air inlet of the air dryer 2 is connected to an air supply source, and the air outlet of the air dryer 2 is connected to the turbo expander 8. The turbo expander 8 is connected to the mixing chamber 18 after passing through a second one-way valve 9. The mixing chamber 18 is connected to the air inlet of the test chamber 31 through a pipeline. An air dryer control valve A3 and an air dryer control valve B5 are respectively installed on the air inlet and outlet sides of the air dryer 2. A turbo expander inlet regulating valve 4 is installed between the air dryer 2 and the turbo expander.

[0031] The air outlet of the test chamber 31 is connected to a radiator, and the vacuum pump is connected to the outlet of the radiator. After the air from the test chamber 31 is cooled by the radiator, it is extracted by the vacuum pump and discharged into the atmosphere. The outlet of the radiator is connected to the pipeline between the air dryer 2 and the turbine expander 8 through an auxiliary air pipeline. An auxiliary air control valve 12 and a manual valve a11 are connected in series on the auxiliary air pipeline. When the air temperature measuring point before the vacuum pump alarms due to over-temperature, the auxiliary air control valve 12 is opened to mix the inlet air with the high-temperature air for cooling.

[0032] Combination Figure 1 As shown, the lubricating oil system also includes a pressure regulating valve and a lubricating oil flow meter; the lubricating oil flow meter is connected in series after the pressure regulating valve; and both the pressure regulating valve and the lubricating oil flow meter are installed on the connecting pipeline between the oil outlet of the test chamber 31 and the oil return port of the lubricating oil tank 38.

[0033] Specifically, the inlet pressure range of the lubricating oil system is 0.1MPa~1MPa, with an accuracy requirement of ±0.25%FS. To meet the control accuracy requirements across the entire range, there are two pressure regulating valves: a lubricating oil pressure fine adjustment valve 49 and a lubricating oil pressure coarse adjustment valve 50. The valve diameter of the lubricating oil pressure fine adjustment valve 49 is DN25, and the valve diameter of the lubricating oil pressure coarse adjustment valve 50 is DN50. The lubricating oil pressure fine adjustment valve 49 and the lubricating oil pressure coarse adjustment valve 50 are connected in parallel.

[0034] To meet the accuracy requirements for measuring lubricating oil flow rate across its full range, two lubricating oil flow meters are installed: a first lubricating oil flow meter 51 and a second lubricating oil flow meter 52 connected in parallel. The range of the first lubricating oil flow meter 51 is 0–12 L / min, and the range of the second lubricating oil flow meter 52 is 0–100 L / min. A manual valve i53 is connected in series on the outlet side of the first lubricating oil flow meter 51, and a manual valve j54 is connected in series on the outlet side of the second lubricating oil flow meter 52. By selecting different flow meters for testing according to the flow conditions, the problem of insufficient accuracy of large-range flow meters under low-temperature conditions can be solved.

[0035] In this embodiment, the lubricating oil system further includes a third check valve 55, a safety valve 43, and a lubricating oil flow regulating valve; the inlet ends of the safety valve 43 and the lubricating oil flow regulating valve are both connected to the outlet pipeline of the lubricating oil heater 42; the third check valve 55 is connected in series after the lubricating oil flow meter; the outlet ends of the third check valve 55, the safety valve 43, and the lubricating oil flow regulating valve are connected to the return port of the lubricating oil tank 38 after being collected by pipelines;

[0036] In this embodiment, the flow rate of the lubricating oil system ranges from 2 L / min to 100 L / min, with an accuracy requirement of ±0.5% FS. To meet the control accuracy requirement across the entire range, two lubricating oil flow regulating valves are installed: a coarse flow regulating valve 44 and a fine flow regulating valve 45. These two valves are connected in parallel. The valve diameter of the coarse flow regulating valve 44 is DN50, and the valve diameter of the fine flow regulating valve 45 is DN25.

[0037] Combination Figure 1 As shown, an inlet valve 46 is installed at the oil inlet of the test chamber 31, and an outlet valve 48 is installed at the oil outlet. The pipeline between the pressure regulating valve and the outlet valve 48, and the pipeline between the inlet valve 46 and the lubricating oil heater 42 are connected by a connecting pipe 57, and a manual valve h47 is installed on the connecting pipe 57.

[0038] In this embodiment, an air flow meter and an air flow regulating valve are connected in series on the pipeline between the mixing tank 18 and the air inlet of the test chamber 31. There are three air flow meters: a first air flow meter 25, a second air flow meter 26, and a third air flow meter 27, connected in parallel. The range of the first air flow meter 25 is 0–0.1 kg / s, the range of the second air flow meter 26 is 0–0.35 kg / s, and the range of the third air flow meter 27 is 0–1 kg / s. A manual valve c22 is connected in series before the first air flow meter 25, a manual valve d23 is connected in series before the second air flow meter 26, and a manual valve e24 is connected in series before the third air flow meter 27. Using three air flow meters can meet the flow measurement accuracy requirements under different flow rates.

[0039] The system comprises three air flow regulating valves: a first air flow regulating valve 28, a second air flow regulating valve 29, and a third air flow regulating valve 30, all connected in parallel. The first air flow regulating valve 28 is a fine-tuning valve with a nominal diameter of DN32; the second air flow regulating valve 29 and the third air flow regulating valve 30 are coarse-tuning valves, with the second air flow regulating valve 29 having a nominal diameter of DN80 and the third air flow regulating valve 30 having a nominal diameter of DN100. Using three air flow regulating valves can meet the flow control accuracy requirements under different flow rates.

[0040] In this embodiment, in order to improve the heat dissipation effect, there are three radiators, namely the first radiator 34, the second radiator 35 and the third radiator 36, which are connected in parallel and are all water-cooled radiators. Without changing the pipe diameter, the extreme cooling requirements under the maximum air flow condition can be met. The first radiator 34, the second radiator 35 and the third radiator 36 use the same water supply pipeline and are controlled by the second water supply valve 37.

[0041] There are two vacuum pumps, namely the first vacuum pump 32 and the second vacuum pump 33, both of which are installed on the pipeline after the radiator. Both vacuum pumps are screw vacuum pumps, which can meet the requirements of the maximum pumping conditions.

[0042] An air inlet bypass is provided between the air outlet pipe of the air dryer 2 and the mixing tank 18. A bypass air flow regulating valve, a bypass air three-way regulating valve 17, and a fourth radiator 20 are connected in series on this bypass. A manual valve b19 is connected to the bypass air three-way regulating valve 17. The outlet of the manual valve b19 and the outlet of the fourth radiator 20 converge and are connected to the mixing tank 18. The fourth radiator 20 is a water-cooled radiator, and a first water supply valve 21 is provided on its water supply pipe. The bypass air three-way regulating valve 17 can divide the bypass air into two categories: one flows through the fourth radiator 20, and the other does not flow through the radiator. The two air streams converge at the end via a three-way valve. By controlling the opening of the bypass air three-way regulating valve 17, the flow rate of the two air streams can be adjusted to meet the bypass air temperature requirements.

[0043] A turbine expander precooling air regulating valve 6 and a first one-way valve 7 are connected to the turbine expander 8. The outlets of the turbine expander precooling air regulating valve 6 and the first one-way valve 7 are combined and then connected to the mixing tank 18 via the turbine expander outlet regulating valve 10. The outlets of the turbine expander precooling air regulating valve 6 and the first one-way valve 7 are also connected to the silencer 1, which can discharge excess gas that has not entered the turbine expander 8 to the atmosphere and prevent the air pipeline from being pressurized or overpressurized.

[0044] The air outlet pipe of the air dryer 2 is also connected to two air bearings of the turbine expander 8, and a turbine expander air bearing supply valve A15 and a turbine expander air bearing supply valve B16 are installed on the pipe. The turbine expander air bearing supply valve B16 is used to control one of the air bearings, and the turbine expander air bearing supply valve A15 controls both air bearings at the same time.

[0045] The high-altitude performance testing device for aero-engine oil-gas heat exchangers provided by this invention is used for testing. The testing method can be implemented through the following testing steps, the specific steps of which are as follows:

[0046] Step 1, Preparations before the experiment:

[0047] a) Install the oil-gas heat exchanger inside the test chamber 31;

[0048] b) Add the test lubricating oil into the lubricating oil tank 38.

[0049] Step 2, lubrication system preparation:

[0050] a) Open the manual valves f39, g41, h47, and k56 of the lubricating oil system; close the inlet valve 46 and outlet valve 48 of the test chamber 31; adjust the lubricating oil flow coarse adjustment valve 44 and lubricating oil flow fine adjustment valve 45 to the fully open state, and close the lubricating oil pressure fine adjustment valve 49 and lubricating oil pressure coarse adjustment valve 50. Select and open the manual valves i53 and j54 after the first lubricating oil flow meter 51 and the second lubricating oil flow meter 52 according to the test lubricating oil flow requirements. If manual valve i53 is opened, manual valve j54 must be closed, and vice versa.

[0051] b) Start the lubricating oil supply pump 40 and the lubricating oil heater 42 to heat the lubricating oil to the required test temperature.

[0052] c) Open inlet valve 46 and outlet valve 48, and close manual valve h47.

[0053] d) Slowly open the lubricating oil pressure coarse adjustment valve 50 and gradually close the lubricating oil flow coarse adjustment valve 44 to coarsely adjust the lubricating oil flow and pressure. When the pressure and flow are adjusted to be close to the target value, adjust the lubricating oil pressure fine adjustment valve 49 and the lubricating oil flow fine adjustment valve 45 to finely adjust until the test lubricating oil flow and pressure meet the test requirements.

[0054] e) During the test, safety valve 43 ensures that the pressure in front of the test chamber will not exceed the limit, and the third check valve 55 ensures that the lubricating oil flow direction of the flow meter is correct.

[0055] Step 3, Air System Preparation:

[0056] a) Open the air dryer control valve A3, air dryer control valve B5, manual valve a11, turbine expander air bearing supply valve A15, turbine expander air bearing supply valve B16, and manual valve b19 of the air system; open the first water supply valve 21 and the second water supply valve 37 of the fourth radiator 20, the first radiator 34, the second radiator 35, and the third radiator 36; adjust the turbine expander outlet regulating valve 10, the bypass air flow coarse adjustment valve 13, and the bypass air flow fine adjustment valve 14 to the fully open state; adjust the bypass air three-way regulating valve 17 to the fully open state, and the bypass air passes through the fourth radiator 20; adjust the turbine expander inlet regulating valve 4, the turbine expander precooling air regulating valve 6, the first air flow regulating valve 28, the second air flow regulating valve 29, and the third air flow regulating valve 30 to the closed state. Select manual valves c22, d23, and e24 after opening the first air flow meter 25, the second air flow meter 26, and the third air flow meter 27, according to the test air flow requirements. If manual valve c22 is opened, manual valves d23 and e24 must be closed, and vice versa.

[0057] b) The gas source station supplies air, which enters the bypass pipeline, mixing box 18, and turbine expander outlet regulating valve 10 through the air dryer 2, and is finally discharged from the silencer 1.

[0058] c) Gradually open the turbine expander inlet regulating valve 4, and slowly adjust the opening of the turbine expander outlet regulating valve 10 and the bypass air flow fine adjustment valve 14 so that the pressure difference between the turbine expander inlet and outlet reaches the required level.

[0059] d) Gradually open the precooling air regulating valve 6 of the turbine expander to reduce the outlet air temperature of the turbine expander.

[0060] e) Adjust the bypass air flow coarse adjustment valve 13 to finely adjust the bypass air flow, and adjust the bypass air three-way adjustment valve 17 to finely adjust the bypass air temperature. The bypass ambient temperature air and the main low temperature air are mixed in the mixing box 18 so that the temperature of the mixed test air meets the test requirements.

[0061] f) Set the target air pressure value after the test chamber 31, and start the first vacuum pump 32 and the second vacuum pump 33.

[0062] g) Gradually open the second air flow regulating valve 29 and the third air flow regulating valve 30 in front of the test chamber 31 to coarsely adjust the air flow, and then finely adjust the air flow through the first air flow regulating valve 28 so that the test flow and pressure meet the test requirements.

[0063] h) The first check valve 7 and the second check valve 9 ensure the correct airflow direction at the outlet of the turbine expander 8. If the outlet air temperature after the test chamber 31 is too high during the test, the auxiliary air control valve 12 can be opened quickly to reduce the air temperature before the first vacuum pump 32 and the second vacuum pump 33, thus ensuring the safety of the vacuum pumps.

[0064] The fourth step is to measure the experimental parameters.

[0065] The testing system measures parameters such as air pressure, temperature, flow rate, and lubricating oil pressure, temperature, and flow rate at the inlet and outlet of the oil-gas heat exchanger. Based on the inlet and outlet parameters, it calculates the heat dissipation performance and flow resistance characteristics of the oil-gas heat exchanger.

[0066] The above description is merely a preferred embodiment of the present invention and does not limit the patent scope of the present invention. Any equivalent structural transformations made using the contents of the present invention's specification and drawings under the inventive concept of the present invention, or direct / indirect applications in other related technical fields, are included within the patent protection scope of the present invention.

Claims

1. A high-altitude performance testing device for an aero-engine oil-gas heat exchanger, characterized in that, include: Test chamber (31), lubricating oil system, and air system; The lubricating oil system includes an oil tank (38), an oil supply pump (40), and an oil heater (42); the oil outlet of the oil tank (38) is connected to the oil supply pump (40), the oil supply pump (40) is connected to the oil heater (42), the oil outlet of the oil heater (42) is connected to the oil inlet of the test chamber (31); the oil outlet of the test chamber (31) is connected to the oil return port of the oil tank (38) through a pipeline; The air system includes an air dryer (2), a turbo expander (8), a mixing chamber (18), and a vacuum pump; the air inlet of the air dryer (2) is connected to the air supply source, the air outlet of the air dryer (2) is connected to the turbo expander (8), the turbo expander (8) is connected to the mixing chamber (18) after passing through the second one-way valve (9), and the mixing chamber (18) is connected to the air inlet of the test chamber (31) through a pipeline; The air outlet of the test chamber (31) is connected to a radiator, and the vacuum pump is connected to the outlet end of the radiator; The lubricating oil system also includes a pressure regulating valve and a lubricating oil flow meter; the lubricating oil flow meter is connected in series after the pressure regulating valve; and both the pressure regulating valve and the lubricating oil flow meter are installed on the connecting pipeline between the oil outlet of the test chamber (31) and the oil return port of the lubricating oil tank (38); There are two pressure regulating valves, namely a lubricating oil pressure fine adjustment valve (49) and a lubricating oil pressure coarse adjustment valve (50), which are arranged in parallel. There are two lubricating oil flow meters, namely the first lubricating oil flow meter (51) and the second lubricating oil flow meter (52) connected in parallel.

2. The high-altitude performance testing device for aero-engine oil-gas heat exchangers as described in claim 1, characterized in that: The lubricating oil system also includes a third check valve (55), a safety valve (43), and a lubricating oil flow regulating valve; the inlet of the safety valve (43) and the lubricating oil flow regulating valve are both connected to the outlet pipeline of the lubricating oil heater (42); the third check valve (55) is connected in series after the lubricating oil flow meter; the outlets of the third check valve (55), the safety valve (43), and the lubricating oil flow regulating valve are connected to the return port of the lubricating oil tank (38) after being collected by pipelines; There are two oil flow regulating valves, namely an oil flow coarse regulating valve (44) and an oil flow fine regulating valve (45); the oil flow coarse regulating valve (44) and the oil flow fine regulating valve (45) are arranged in parallel.

3. The high-altitude performance testing device for aero-engine oil-gas heat exchangers as described in claim 1, characterized in that: An inlet valve (46) is provided at the oil inlet of the test chamber (31), and an outlet valve (48) is provided at the oil outlet. The pipeline between the pressure regulating valve and the outlet valve (48), and the pipeline between the inlet valve (46) and the lubricating oil heater (42) are connected by a connecting pipe (57), and a manual valve h (47) is provided on the connecting pipe (57).

4. The high-altitude performance testing device for aero-engine oil-gas heat exchangers as described in claim 1, characterized in that: An air flow meter and an air flow regulating valve are connected in series on the pipeline between the air inlet of the mixing tank (18) and the test chamber (31); The number of air flow meters is three, namely the first air flow meter (25), the second air flow meter (26) and the third air flow meter (27), which are connected in parallel; The number of air flow regulating valves is three, namely the first air flow regulating valve (28), the second air flow regulating valve (29) and the third air flow regulating valve (30), which are arranged in parallel. The first air flow regulating valve (28) is a fine-tuning valve, and the second air flow regulating valve (29) and the third air flow regulating valve (30) are coarse-tuning valves.

5. The high-altitude performance testing device for an aero-engine oil-gas heat exchanger as described in claim 1, characterized in that: The number of radiators is three, namely the first radiator (34), the second radiator (35) and the third radiator (36), which are connected in parallel and are all water-cooled radiators; The number of vacuum pumps is two, namely a first vacuum pump (32) and a second vacuum pump (33), both of which are installed on the pipeline after the radiator.

6. The high-altitude performance testing device for an aero-engine oil-gas heat exchanger as described in claim 1, characterized in that: The outlet of the radiator is connected to the pipeline between the air dryer (2) and the turbine expander (8) through an auxiliary air pipeline. An auxiliary air control valve (12) and a manual valve a (11) are connected in series on the auxiliary air pipeline.

7. The high-altitude performance testing device for an aero-engine oil-gas heat exchanger as described in claim 1, characterized in that: An air inlet bypass is provided between the air outlet pipe of the air dryer (2) and the mixing box (18). A bypass air flow regulating valve, a bypass air three-way regulating valve (17), and a fourth radiator (20) are connected in series in the bypass air inlet bypass. A manual valve b (19) is connected to the bypass air three-way regulating valve (17). The outlet end of the manual valve b (19) and the outlet end of the fourth radiator (20) are connected together to the mixing box (18). The fourth radiator (20) is a water-cooled radiator.

8. The high-altitude performance testing device for an aero-engine oil-gas heat exchanger as described in claim 1, characterized in that: A turbine expander precooling air regulating valve (6) and a first check valve (7) are connected to the turbine expander (8). The outlet ends of the turbine expander precooling air regulating valve (6) and the first check valve (7) are connected to the mixing tank (18) through the turbine expander outlet regulating valve (10). The outlet ends of the turbine expander precooling air regulating valve (6) and the first check valve (7) are also connected to the silencer (1).

9. The high-altitude performance testing device for an aero-engine oil-gas heat exchanger as described in claim 1, characterized in that: The air outlet pipe of the air dryer (2) is also connected to two air bearings of the turbine expander (8), and a turbine expander air bearing supply valve A (15) and a turbine expander air bearing supply valve B (16) are installed on the pipeline. The turbine expander air bearing supply valve B (16) is used to control one of the air bearings, and the turbine expander air bearing supply valve A (15) controls both air bearings at the same time.

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