CN116499752A - Aeroengine oil gas heat exchanger high altitude performance test device - Google Patents
Aeroengine oil gas heat exchanger high altitude performance test device Download PDFInfo
- Publication number
- CN116499752A CN116499752A CN202310563203.0A CN202310563203A CN116499752A CN 116499752 A CN116499752 A CN 116499752A CN 202310563203 A CN202310563203 A CN 202310563203A CN 116499752 A CN116499752 A CN 116499752A
- Authority
- CN
- China
- Prior art keywords
- air
- valve
- lubricating oil
- oil
- regulating valve
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000011056 performance test Methods 0.000 title claims abstract description 21
- 239000010687 lubricating oil Substances 0.000 claims abstract description 120
- 239000003921 oil Substances 0.000 claims abstract description 99
- 238000012360 testing method Methods 0.000 claims abstract description 71
- 238000002156 mixing Methods 0.000 claims abstract description 28
- 230000001105 regulatory effect Effects 0.000 claims description 148
- 230000001276 controlling effect Effects 0.000 claims description 6
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 8
- 238000001816 cooling Methods 0.000 description 7
- 230000005855 radiation Effects 0.000 description 6
- 230000017525 heat dissipation Effects 0.000 description 4
- 238000013461 design Methods 0.000 description 3
- 238000004364 calculation method Methods 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 239000000314 lubricant Substances 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000002360 preparation method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008094 contradictory effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000006185 dispersion Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000005086 pumping Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The high-altitude performance test device for the aeroengine oil-gas heat exchanger comprises a test cabin, an lubricating oil system and an air system; the lubricating oil system comprises a lubricating oil tank, a lubricating oil supply pump and a lubricating oil warmer; an oil outlet of the lubricating oil tank is connected with a lubricating oil supply pump, the lubricating oil supply pump is connected with a lubricating oil warmer, and an oil outlet of the lubricating oil warmer is connected with an oil inlet of the test cabin; the oil outlet of the test cabin is connected to the oil return port of the lubricating oil tank through a pipeline; the air system comprises an air dryer, a turbine expander, a blending tank and a vacuum pump; the air inlet of the air dryer is connected with an air supply source, the air outlet of the air dryer is connected with the turbine expander, the turbine expander is connected with the mixing box after passing through the second one-way valve, and the mixing box is connected to the air inlet of the test cabin through a pipeline; the air outlet of the test cabin is connected with a radiator, and the vacuum pump is connected with the outlet end of the radiator.
Description
Technical Field
The invention relates to the technical field of aeroengine tests, in particular to a high-altitude performance test device for an aeroengine oil-gas heat exchanger, which is suitable for testing the heat dispersion and flow resistance characteristics of an aeroengine accessory oil-gas heat exchanger.
Background
When the engine works at high altitude, the fuel flow is very small because of small air flow, and the required cooling effect can not be achieved by simply cooling the lubricating oil by the fuel according to the design of the conventional engine, and an oil-gas heat exchanger is required to be added to further reduce the lubricating oil temperature. At present, no test means can only analyze the oil gas heat exchanger by means of theoretical calculation, but under the high-altitude low-Reynolds number environment, the theoretical calculation error is larger, and the performance of the oil gas heat exchanger cannot be truly evaluated, so that the performance of the oil gas heat exchanger needs to be analyzed and evaluated through a high-altitude simulation test.
With the development of aviation industry and engine industry, the oil-gas heat exchanger is increasingly used on aircrafts and engines to cool and dissipate heat of lubricating oil systems of the engines and the like. The heat dissipation performance and the flow resistance characteristics of the oil-gas heat exchanger under different air inlet conditions with different heights are design inputs required in the process of designing related systems of an airplane and an engine. In the design and manufacture of the current oil-gas heat exchanger, the assessment of the heat radiation performance and the flow resistance characteristic mainly depends on software calculation and a ground heat radiation performance test, but the assessment of the heat radiation performance and the flow resistance characteristic in a middle-high working environment cannot be carried out. In particular to an engine oil-gas heat exchanger applied to high altitude long endurance, the air temperature and pressure in the high altitude state are low, the air density is thin, the heat dissipation performance of the oil-gas heat exchanger, particularly the flow resistance, is changed, and the difference exists compared with the ground. Because the test bed is not provided, the heat radiation performance and the flow resistance characteristic of the oil gas heat exchanger under the high-altitude condition are subjected to test study, and the oil gas heat exchanger can only be tested on the high-altitude table together with the engine, so that a large development risk is required to be born.
Disclosure of Invention
The invention mainly aims to provide a high-altitude performance test device for an aeroengine oil-gas heat exchanger, and aims to solve the technical problems.
In order to achieve the above purpose, the invention provides an aeroengine oil-gas heat exchanger high altitude performance test device, comprising: test cabin, lubricating oil system, and air system;
the lubricating oil system comprises a lubricating oil tank, a lubricating oil supply pump and a lubricating oil warmer; an oil outlet of the lubricating oil tank is connected with a lubricating oil supply pump, the lubricating oil supply pump is connected with a lubricating oil warmer, and an oil outlet of the lubricating oil warmer is connected with an oil inlet of the test cabin; the oil outlet of the test cabin is connected to the oil return port of the lubricating oil tank through a pipeline;
the air system comprises an air dryer, a turbine expander, a blending tank and a vacuum pump; the air inlet of the air dryer is connected with an air supply source, the air outlet of the air dryer is connected with the turbine expander, the turbine expander is connected with the mixing box after passing through the second one-way valve, and the mixing box is connected to the air inlet of the test cabin through a pipeline;
the air outlet of the test cabin is connected with a radiator, and the vacuum pump is connected with the outlet end of the radiator; and cooling the outlet air of the test cabin by a radiator, and pumping out the air by a vacuum pump to exhaust the air to the atmosphere.
Preferably, the lubricating oil system further comprises a pressure regulating valve and a lubricating oil flowmeter; the lubricating oil flowmeter is connected in series behind the pressure regulating valve; the pressure regulating valve and the lubricating oil flowmeter are arranged on a connecting pipeline between the oil outlet of the test cabin and the oil return port of the lubricating oil tank; the number of the pressure regulating valves is two, namely a lubricating oil pressure fine regulating valve and a lubricating oil pressure rough regulating valve, and the lubricating oil pressure fine regulating valve and the lubricating oil pressure rough regulating valve are arranged in parallel; the number of the lubricating oil flow meters is two, and the first lubricating oil flow meter and the second lubricating oil flow meter are respectively arranged in parallel.
Preferably, the lubricating oil system further comprises a third one-way valve, a safety valve and a lubricating oil flow regulating valve; the oil inlet ends of the safety valve and the lubricating oil flow regulating valve are connected to the oil outlet pipeline of the lubricating oil warmer; the third one-way valve is connected in series behind the lubricating oil flowmeter; the oil outlet ends of the third one-way valve, the safety valve and the lubricating oil flow regulating valve are connected to an oil return port of the lubricating oil tank after being converged through pipelines; the number of the oil flow regulating valves is two, and the oil flow regulating valves are respectively an oil flow rough regulating valve and an oil flow fine regulating valve; the rough-regulation valve of the lubricating oil flow and the fine-regulation valve of the lubricating oil flow are connected in parallel.
Preferably, an inlet valve is arranged at the position of an oil inlet of the test cabin, and an outlet valve is arranged at the position of an oil outlet; the pipeline between the pressure regulating valve and the outlet valve, and the pipeline between the inlet valve and the lubricating oil warmer are communicated through a connecting pipe, and a manual valve h is arranged on the connecting pipe.
Preferably, an air flow meter and an air flow regulating valve are arranged in series on a pipeline between the blending box and the air inlet of the test cabin; the number of the air flow meters is three, namely a first air flow meter, a second air flow meter and a third air flow meter, which are arranged in parallel; the number of the 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 arranged in parallel, wherein the first air flow regulating valve is a fine regulating valve, and the second air flow regulating valve and the third air flow regulating valve are coarse regulating valves.
Preferably, the number of the radiators is three, namely a first radiator, a second radiator and a third radiator, which are arranged in parallel, and the three radiators are all water-cooled radiators; the number of the vacuum pumps is two, namely a first vacuum pump and a second vacuum pump, and the two vacuum pumps are arranged on a pipeline behind the radiator.
Preferably, the outlet of the radiator is connected to a pipeline between the air dryer and the turbo expander through an auxiliary air pipeline, and an auxiliary air control valve and a manual valve a are sequentially and serially arranged on the auxiliary air pipeline.
Preferably, an air inlet bypass is arranged between the air outlet pipeline of the air dryer and the blending tank, and a bypass air flow regulating valve, a bypass air three-way regulating valve and a fourth radiator are sequentially arranged in series on the air inlet bypass; a manual valve b is connected to the bypass air three-way regulating valve, and the outlet end of the manual valve b and the outlet end of the fourth radiator are connected to the blending tank together after being converged; the fourth radiator is a water-cooled radiator.
Preferably, the pre-cooling air regulating valve of the turbine expander and the first one-way valve are connected and arranged on the turbine expander, and the outlet ends of the pre-cooling air regulating valve of the turbine expander and the first one-way valve are connected to the blending box together through the outlet regulating valve of the turbine expander after being collected; the outlet ends of the precooling air regulating valve and the first one-way valve of the turbine expander are connected to the muffler after being collected.
Preferably, the air outlet pipe of the air dryer is further connected with two air bearing of the turbine expander, and a turbine expander air bearing air supply valve A and a turbine expander air bearing air supply valve B are arranged on the pipeline, wherein the turbine expander air bearing air supply valve B is used for controlling one air bearing, and the turbine expander air bearing air supply valve A simultaneously controls the two air bearing.
Due to the adoption of the technical scheme, the invention has the following beneficial effects:
according to the high-altitude performance test device for the aeroengine oil-gas heat exchanger, the lubricating oil system and the air system are connected with the test cabin, the lubricating oil system simulates lubricating oil supply pressure, flow and temperature of the test cabin in a high-altitude state, the air dryer, the turbine expander and the air blending box in the air system provide air inlet pressure and temperature requirements of the test cabin in the simulated high-altitude state, and the vacuum pump and the front regulating valve of the test cabin simulate air inlet pressure and flow requirements of the test cabin in the high-altitude state. The test device is used for realizing test research on the heat radiation performance and the flow resistance characteristic of the oil-gas heat exchanger under the high altitude condition.
According to the invention, the heat exchange working condition of the oil-gas heat exchanger under the high altitude and low Reynolds number can be simulated, and the heat radiation performance and the flow resistance characteristic of the radiator can be evaluated.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to the structures shown in these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of an aeroengine oil-gas heat exchanger high-altitude performance test device provided by the invention.
Reference numerals illustrate:
1. a muffler; 2. an air dryer; 3. an air dryer control valve a; 4. an air inlet regulating valve of the turbine expander; 5. an air dryer control valve B; 6. precooling air regulating valve of turbine expander; 7. a first one-way valve; 8. a turbine expander; 9. a second one-way valve; 10. an outlet regulating valve of the turbine expander; 11. a manual valve a; 12. an auxiliary air control valve; 13. a bypass air flow rough adjustment valve; 14. a bypass air flow fine tuning valve; 15. an air bearing air supply valve A of the turbine expander; 16. an air bearing air supply valve B of the turbine expander; 17. a bypass air three-way regulating valve; 18. a blending tank; 19. a manual valve b; 20. a fourth radiator; 21. a first water supply valve; 22. a manual valve c; 23. a manual valve d; 24. a manual valve e; 25. a first air flow meter; 26. a second air flow meter; 27. a third air flow meter; 28. a first air flow rate regulating valve; 29. a second air flow rate regulating valve; 30. a third air flow rate regulating valve; 31. a test cabin; 32. a first vacuum pump; 33. a second vacuum pump; 34. a first heat sink; 35. a second heat sink; 36. a third heat sink; 37. a second water supply valve; 38. a lubricating oil tank; 39. a manual valve f; 40. a lubricating oil supply pump; 41. a manual valve g; 42. a lubricating oil warmer; 43. a safety valve; 44. a rough lubricant flow valve; 45. a fine adjustment valve for the flow rate of lubricating oil; 46. an inlet valve; 47. a manual valve h; 48. an outlet valve; 49. a lubricating oil pressure fine-tuning valve; 50. a rough lubricant pressure regulating valve; 51. a first oil flow meter; 52. a second oil flow meter; 53. a manual valve i; 54. a manual valve j; 55. a third one-way valve; 56. a manual valve k; 57. and (5) connecting pipes.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are only some, but not all embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
It should be noted that all directional indicators (such as up, down, left, right, front, and rear … …) in the embodiments of the present invention are merely used to explain the relative positional relationship, movement, etc. between the components in a particular posture (as shown in the drawings), and if the particular posture is changed, the directional indicator is changed accordingly.
Furthermore, the description of "first," "second," etc. in this disclosure is for descriptive purposes only and is not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In addition, the technical solutions of the embodiments may be combined with each other, but it is necessary to base that the technical solutions can be realized by those skilled in the art, and when the technical solutions are contradictory or cannot be realized, the combination of the technical solutions should be considered to be absent and not within the scope of protection claimed in the present invention.
Referring to fig. 1, a specific embodiment of an aeroengine oil-gas heat exchanger high-altitude performance test device provided by the invention is shown, where the test device includes: test chamber 31, lubricating oil system, and air system;
the oil system includes an oil tank 38, an oil feed pump 40, and an oil warmer 42; an oil outlet of the lubricating oil tank 38 is connected with a lubricating oil supply pump 40, the lubricating oil supply pump 40 is connected with a lubricating oil warmer 42, and an oil outlet of the lubricating oil warmer 42 is connected with an oil inlet of the test cabin 31; the oil outlet of the test cabin 31 is connected to the oil return port of the lubricating oil tank 38 through a pipeline; a manual valve k56 is provided at the oil return port position of the lubricating oil tank 38, and a manual valve f39 is provided between the lubricating oil supply pump 40 and the lubricating oil tank; a manual valve g41 is provided between the oil feed pump 40 and the oil warmer.
The air system comprises an air dryer 2, a turbine expander 8, a blending tank 18 and a vacuum pump; the air inlet of the air dryer 2 is connected with an air supply source, the air outlet of the air dryer 2 is connected with the turbine expander 8, the turbine expander 8 is connected with the blending box 18 after passing through the second one-way valve 9, and the blending box 18 is connected to the air inlet of the test cabin 31 through a pipeline; an air dryer control valve A3 and an air dryer control valve B5 are respectively arranged on the air inlet side and the air outlet side of the air dryer 2; a turbine expander air inlet regulating valve 4 is arranged between the air dryer 2 and the turbine expander;
the air outlet of the test cabin 31 is connected with a radiator, and the vacuum pump is connected with the outlet end of the radiator; after the outlet air of the test chamber 31 is cooled by the radiator, the air is pumped out by a vacuum pump and discharged to the atmosphere. The outlet of the radiator is connected to a 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 sequentially and serially arranged on the auxiliary air pipeline, and when the overtemperature of an air temperature measuring point before a vacuum pump alarms, the auxiliary air control valve 12 is opened to mix inlet air with high-temperature air for cooling.
As shown in connection with fig. 1, the oil system further comprises a pressure regulating valve and an oil flow meter; the lubricating oil flowmeter is connected in series behind the pressure regulating valve; the pressure regulating valve and the lubricating oil flowmeter are arranged on a connecting pipeline between the oil outlet of the test cabin 31 and the oil return port of the lubricating oil tank 38;
specifically, the inlet pressure range of the lubricating oil system is 0.1 MPa-1 MPa, the precision requirement is +/-0.25% F.S, the control precision requirement is met in the whole range, the number of the pressure regulating valves is two, namely a lubricating oil pressure fine regulating valve 49 and a lubricating oil pressure rough regulating valve 50, the valve diameter DN25 of the lubricating oil pressure fine regulating valve 49 and the valve diameter DN50 of the lubricating oil pressure rough regulating valve 50 are respectively arranged, and the lubricating oil pressure fine regulating valve 49 and the lubricating oil pressure rough regulating valve 50 are arranged in parallel;
in order to meet the measurement accuracy requirement of the lubricating oil flow in the whole range, two lubricating oil flow meters are arranged, namely a first lubricating oil flow meter 51 and a second lubricating oil flow meter 52 are respectively connected in parallel; the range of the first lubricating oil flowmeter 51 is 0-12L/mm, and the range of the second lubricating oil flowmeter 52 is 0-100L/mm. A manual valve i53 is connected in series to the outlet side of the first oil flow meter 51, and a manual valve j54 is connected in series to the outlet side of the second oil flow meter 52. Different flow meters are selected for testing according to flow working conditions, and the problem that the accuracy of the wide-range flow meter under low working conditions is not met can be solved.
In the present embodiment, the oil system further includes a third check valve 55, a relief valve 43, and an oil flow rate adjustment valve; the safety valve 43 and the oil inlet end of the oil flow regulating valve are both connected to the oil outlet pipeline of the oil heater 42; the third check valve 55 is connected in series after the oil flow meter; the oil outlet ends of the third one-way valve 55, the safety valve 43 and the lubricating oil flow regulating valve are connected to an oil return port of the lubricating oil tank 38 after being collected through pipelines;
in the embodiment, the flow range of the lubricating oil system is 2L/min-100L/min, the precision requirement is +/-0.5 percent F.S, the control precision requirement is met in the whole range, two lubricating oil flow regulating valves are arranged, namely a lubricating oil flow rough regulating valve 44 and a lubricating oil flow fine regulating valve 45; the rough oil flow regulating valve 44 and the fine oil flow regulating valve 45 are arranged in parallel. Valve path DN50 of rough valve 44; the oil flow fine-adjusts the valve path DN25 of the valve 45.
As shown in fig. 1, an inlet valve 46 is arranged at the oil inlet position of the test chamber 31, and an outlet valve 48 is arranged at the oil outlet position; the line between the pressure regulating valve and the outlet valve 48 and the line between the inlet valve 46 and the oil warmer 42 are connected by a connecting pipe 57, and a manual valve h47 is provided on the connecting pipe 57.
In the present embodiment, an air flow meter and an air flow rate regulating valve are provided in series on the piping between the blending tank 18 and the air inlet of the test chamber 31; the number of the air flow meters is three, namely a first air flow meter 25, a second air flow meter 26 and a third air flow meter 27, which are arranged in parallel; the range of the first air flow meter 25 is 0 to 0.1kg/s, the range of the second air flow meter 26 is 0 to 0.35kg/s, and the range of the third air flow meter 27 is 0 to 1kg/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. And the three air flowmeters are adopted, so that the flow measurement precision requirements under different flows can be met.
The number of the air flow regulating valves is three, namely a first air flow regulating valve 28, a second air flow regulating valve 29 and a third air flow regulating valve 30, which are arranged in parallel, wherein the first air flow regulating valve 28 is a fine regulating valve, and the valve diameter DN32 is a valve diameter; the second air flow rate adjustment valve 29 and the third air flow rate adjustment valve 30 are rough adjustment valves, the valve path DN80 of the second air flow rate adjustment valve 29, and the valve path DN100 of the third air flow rate adjustment valve 30. And three air flow regulating valves are adopted, so that the flow control precision requirements under different flows can be met.
In this embodiment, in order to improve the heat dissipation effect, the number of the three heat sinks is three, namely, the first heat sink 34, the second heat sink 35 and the third heat sink 36, which are arranged in parallel, and the three heat sinks are all water-cooled heat sinks, so that the requirement of limiting cooling working conditions under the maximum flow of air can be met under the condition of not changing the pipe diameter; the first radiator 34, the second radiator 35 and the third radiator 36 use the same water supply line and are controlled by a second water supply valve 37.
The number of the vacuum pumps is two, namely a first vacuum pump 32 and a second vacuum pump 33, which are both arranged on a pipeline behind the radiator, and the two vacuum pumps are screw type vacuum pumps, so that the maximum air exhaust working condition requirement can be met.
An air inlet bypass is arranged between the air outlet pipeline of the air dryer 2 and the blending tank 18, and a bypass air flow regulating valve, a bypass air three-way regulating valve 17 and a fourth radiator 20 are sequentially and serially arranged on the air inlet bypass; a manual valve b19 is connected to the bypass air three-way regulating valve 17, and the outlet end of the manual valve b19 and the outlet end of the fourth radiator 20 are connected to the blending tank 18 together after being gathered; the fourth radiator 20 is a water-cooled radiator, and a water supply pipe thereof is provided with a first water supply valve 21. The bypass air three-way regulating valve 17 can divide bypass air into two types, one of the two types passes through the fourth radiator 20, the other type does not pass through the radiator, and the two types of air are converged at the back through a three-way, so that the flow of the two types of air can be regulated by controlling the opening of the bypass air three-way regulating valve 17, and the requirement of regulating the temperature of the bypass air is met.
The turbine expander 8 is connected with a turbine expander precooling air regulating valve 6 and a first one-way valve 7, and the outlet ends of the turbine expander precooling air regulating valve 6 and the first one-way valve 7 are connected to a blending box 18 together through a turbine expander outlet regulating valve 10 after being converged; the precooling air regulating valve 6 of the turbo expander and the outlet end of the first one-way valve 7 are connected to the muffler 1 after being gathered, so that redundant gas which does not enter the turbo expander 8 to work can be discharged to the atmosphere, and the pressure of an air pipeline is prevented from being suppressed and the pressure of the air pipeline is prevented from being excessively increased.
The air outlet pipe of the air dryer 2 is also connected with two air bearing of the turbine expander 8, and a turbine expander air bearing air supply valve A15 and a turbine expander air bearing air supply valve B16 are arranged on the pipeline, the turbine expander air bearing air supply valve B16 is used for controlling one air bearing, and the turbine expander air bearing air supply valve A15 is used for controlling the two air bearing simultaneously.
The aeroengine oil-gas heat exchanger high-altitude performance test device provided by the invention is used for testing, and the test method can be realized through the following test steps:
first, preparation before test:
a) The oil-gas heat exchanger is arranged in the test cabin 31;
b) The test oil is filled into the oil tank 38.
Secondly, preparing an oiling system:
a) Opening a manual valve f39, a manual valve g41, a manual valve h47 and a manual valve k56 of the lubricating oil system; closing the inlet valve 46 and the outlet valve 48 of the test chamber 31; the rough oil flow regulating valve 44 and the fine oil flow regulating valve 45 are set to the fully opened state, and the fine oil pressure regulating valve 49 and the rough oil pressure regulating valve 50 are closed. The manual valve i53 and the manual valve j54 after the first and second oil flow meters 51 and 52 are opened are selected according to the requirements of the test oil flow, for example, the manual valve i53 is opened, the manual valve j54 is closed, and vice versa.
b) The oil feed pump 40 is started, and the oil warmer 42 is started to warm the oil temperature to the test demand temperature.
c) The inlet valve 46 and the outlet valve 48 are opened, and the manual valve h47 is closed.
d) The rough oil pressure regulating valve 50 is slowly opened, the rough oil flow regulating valve 44 is gradually closed to roughly regulate the oil flow and the pressure, and the fine oil pressure regulating valve 49 and the fine oil flow regulating valve 45 are regulated again when the pressure and the flow are regulated to be close to the target values, until the test oil flow and the test oil pressure meet the test requirements.
e) The safety valve 43 ensures that the pressure in front of the test chamber does not exceed the limit during the test, and the third one-way valve 55 ensures that the flow direction of the lubricating oil of the flowmeter is correct.
Third, air system preparation:
a) Opening an air dryer control valve A3, an air dryer control valve B5, a manual valve a11, a turbine expander air bearing air supply valve A15, a turbine expander air bearing air supply valve B16 and a manual valve B19 of the air system; 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 are opened; regulating the turbine expander outlet regulating valve 10, the bypass air flow rough regulating valve 13 and the bypass air flow fine regulating valve 14 to a full-open state; the bypass air three-way regulating valve 17 is regulated to a full-open state, and the bypass air passes through the fourth radiator 20; the turbo-expander intake air regulating valve 4, the turbo-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 are set to the closed state. The manual valves c22, d23 and e24 after the first, second and third air flow meters 25, 26 and 27 are selectively opened according to the test air flow requirement, for example, the manual valves c22 are opened, the manual valves d23 and e24 are closed, and vice versa.
b) The air source station supplies air, and the air enters a bypass pipeline, a blending box 18 and a turbine expander outlet regulating valve 10 through the air dryer 2, and finally is discharged from the muffler 1.
c) The inlet regulating valve 4 of the turboexpander is gradually opened, and the opening degrees of the outlet regulating valve 10 and the bypass air flow fine regulating valve 14 of the turboexpander are slowly regulated, so that the inlet and outlet pressure difference of the turboexpander reaches the use requirement.
d) The precooling air regulating valve 6 of the turboexpander is gradually opened, and the temperature of the air at the outlet of the turboexpander is reduced.
e) The bypass air flow rough regulating valve 13 is regulated to finely regulate the bypass air flow, the bypass air three-way regulating valve 17 is regulated to finely regulate the bypass air temperature, and the bypass normal-temperature air and the main-way low-temperature air are mixed in the mixing box 18, so that the mixed test air temperature meets the test requirement.
f) The first vacuum pump 32 and the second vacuum pump 33 are started by setting the target air pressure value after the test chamber 31.
g) The second air flow regulating valve 29 and the third air flow regulating valve 30 before the test cabin 31 are opened step by step to carry out rough air flow, and then the air flow is finely regulated through the first air flow regulating valve 28, so that the test flow and the pressure meet the test requirements.
h) The first check valve 7 and the second check valve 9 ensure that the outlet air of the turbine expander 8 flows correctly, for example, the outlet air temperature after the test cabin 31 is too high in the test process, and the auxiliary air control valve 12 is opened quickly, so that the air temperature before the first vacuum pump 32 and the second vacuum pump 33 can be reduced, and the safety of the vacuum pumps is ensured.
And fourthly, testing parameters.
The testing system is used for measuring parameters such as air pressure, temperature and flow of an inlet and an outlet of the oil-gas heat exchanger, lubricating oil pressure, temperature and flow, and calculating the heat dissipation performance and flow resistance of the oil-gas heat exchanger according to the inlet and outlet parameters.
The foregoing description is only of the preferred embodiments of the present invention, and is not intended to limit the scope of the invention, but rather, the equivalent structural changes made by the description of the present invention and the accompanying drawings or the direct/indirect application in other related technical fields are included in the scope of the invention.
Claims (10)
1. High altitude performance test device of aeroengine oil gas heat exchanger, characterized by, include: the test cabin (31), the lubricating oil system and the air system;
the lubricating oil system comprises a lubricating oil tank (38), a lubricating oil supply pump (40) and a lubricating oil heater (42); an oil outlet of the lubricating oil tank (38) is connected with a lubricating oil supply pump (40), the lubricating oil supply pump (40) is connected with a lubricating oil warmer (42), and an oil outlet of the lubricating oil warmer (42) is connected with an oil inlet of the test cabin (31); an oil outlet of the test cabin (31) is connected to an oil return port of an oil tank (38) through a pipeline;
the air system comprises an air dryer (2), a turbine expander (8), a blending tank (18) and a vacuum pump; the air inlet of the air dryer (2) is connected with an air supply source, the air outlet of the air dryer (2) is connected with the turbine expander (8), the turbine expander (8) is connected with the mixing box (18) after passing through the second one-way valve (9), and the mixing box (18) is connected to the air inlet of the test cabin (31) through a pipeline;
the air outlet of the test cabin (31) is connected with a radiator, and the vacuum pump is connected with the outlet end of the radiator.
2. The aeroengine oil-gas heat exchanger high altitude performance test apparatus of claim 1, wherein: the lubricating oil system also comprises a pressure regulating valve and a lubricating oil flowmeter; the lubricating oil flowmeter is connected in series behind the pressure regulating valve; the pressure regulating valve and the lubricating oil flowmeter are arranged on a connecting pipeline between an oil outlet of the test cabin (31) and an oil return port of the lubricating oil tank (38);
the number of the pressure regulating valves is two, namely a lubricating oil pressure fine regulating valve (49) and a lubricating oil pressure rough regulating valve (50), and the lubricating oil pressure fine regulating valve (49) and the lubricating oil pressure rough regulating valve (50) are arranged in parallel;
the number of the lubricating oil flow meters is two, and the first lubricating oil flow meter (51) and the second lubricating oil flow meter (52) are respectively arranged in parallel.
3. The aeroengine oil-gas heat exchanger high altitude performance test apparatus of claim 2, wherein: the lubricating oil system also comprises a third one-way valve (55), a safety valve (43) and a lubricating oil flow regulating valve; the oil inlet ends of the safety valve (43) and the lubricating oil flow regulating valve are connected to the oil outlet pipeline of the lubricating oil heater (42); the third one-way valve (55) is connected in series after the lubricating oil flowmeter; the oil outlet ends of the third one-way valve (55), the safety valve (43) and the lubricating oil flow regulating valve are connected to an oil return port of the lubricating oil tank (38) after being converged through pipelines;
the number of the oil flow regulating valves is two, namely an oil flow rough regulating valve (44) and an oil flow fine regulating valve (45); the rough-regulation valve (44) and the fine-regulation valve (45) are connected in parallel.
4. The aeroengine oil-gas heat exchanger high altitude performance test apparatus of claim 2, wherein: an inlet valve (46) is arranged at the oil inlet position of the test cabin (31), and an outlet valve (48) is arranged at the oil outlet position; the pipeline between the pressure regulating valve and the outlet valve (48) and the pipeline between the inlet valve (46) and the lubricating oil warmer (42) are communicated through a connecting pipe (57), and a manual valve h (47) is arranged on the connecting pipe (57).
5. The aeroengine oil-gas heat exchanger high altitude performance test apparatus of claim 1, wherein: an air flow meter and an air flow regulating valve are arranged on a pipeline between the blending box (18) and the air inlet of the test cabin (31) in series;
the number of the air flow meters is three, namely a first air flow meter (25), a second air flow meter (26) and a third air flow meter (27), and the three air flow meters are arranged in parallel;
the number of the air flow regulating valves is three, namely a first air flow regulating valve (28), a second air flow regulating valve (29) and a third air flow regulating valve (30), the three air flow regulating valves are arranged in parallel, the first air flow regulating valve (28) is a fine regulating valve, and the second air flow regulating valve (29) and the third air flow regulating valve (30) are coarse regulating valves.
6. The aeroengine oil-gas heat exchanger high altitude performance test apparatus of claim 1, wherein:
the number of the radiators is three, namely a first radiator (34), a second radiator (35) and a third radiator (36), which are arranged in parallel, and the three radiators are all water-cooled radiators;
the number of the vacuum pumps is two, namely a first vacuum pump (32) and a second vacuum pump (33), and the two vacuum pumps are arranged on a pipeline behind the radiator.
7. The aeroengine oil-gas heat exchanger high altitude performance test apparatus of claim 1, wherein: the outlet of the radiator is connected to a pipeline between the air dryer (2) and the turbine expander (8) through an auxiliary air pipeline, and an auxiliary air control valve (12) and a manual valve a (11) are sequentially and serially arranged on the auxiliary air pipeline.
8. The aeroengine oil-gas heat exchanger high altitude performance test apparatus of claim 1, wherein: an air inlet bypass is arranged between an air outlet pipeline of the air dryer (2) and the blending box (18), and a bypass air flow regulating valve, a bypass air three-way regulating valve (17) and a fourth radiator (20) are sequentially and serially arranged in the air inlet bypass; a manual valve b (19) is connected to the bypass air three-way regulating valve (17), and the outlet end of the manual valve b (19) and the outlet end of the fourth radiator (20) are connected to the blending tank (18) together after being converged; the fourth radiator (20) is a water-cooled radiator.
9. The aeroengine oil-gas heat exchanger high altitude performance test apparatus of claim 1, wherein: the turbine expander (8) is connected with a turbine expander precooling air regulating valve (6) and a first one-way valve (7), and the outlet ends of the turbine expander precooling air regulating valve (6) and the first one-way valve (7) are converged and then are connected to the blending box (18) through a turbine expander outlet regulating valve (10); the outlet ends of the precooling air regulating valve (6) and the first one-way valve (7) of the turbine expander are connected to the muffler (1) after being converged.
10. The aeroengine oil-gas heat exchanger high altitude performance test apparatus of claim 1, wherein: the air outlet pipe of the air dryer (2) is further connected with two air bearing of the turbine expander (8), a turbine expander air bearing air supply valve A (15) and a turbine expander air bearing air supply valve B (16) are arranged on the pipeline, the turbine expander air bearing air supply valve B (16) is used for controlling one air bearing, and the turbine expander air bearing air supply valve A (15) is used for controlling the two air bearing simultaneously.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310563203.0A CN116499752A (en) | 2023-05-18 | 2023-05-18 | Aeroengine oil gas heat exchanger high altitude performance test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310563203.0A CN116499752A (en) | 2023-05-18 | 2023-05-18 | Aeroengine oil gas heat exchanger high altitude performance test device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116499752A true CN116499752A (en) | 2023-07-28 |
Family
ID=87326675
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310563203.0A Pending CN116499752A (en) | 2023-05-18 | 2023-05-18 | Aeroengine oil gas heat exchanger high altitude performance test device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116499752A (en) |
-
2023
- 2023-05-18 CN CN202310563203.0A patent/CN116499752A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN113063597B (en) | System and method for testing attitude characteristic of lubricating oil tank | |
| CN104360702A (en) | System for dynamically testing aviation thermal power and method for dynamically controlling temperature and pressure environments | |
| Lüddecke et al. | On wide mapping of a mixed flow turbine with regard to compressor heat flows during turbocharger testing | |
| CN107290166B (en) | Test system and test method for simulating rapid change of fluid temperature and/or pressure | |
| Serrano et al. | Methodology to characterize heat transfer phenomena in small automotive turbochargers: experiments and modelling based analysis | |
| Serrano et al. | Experimental study of the turbine inlet gas temperature influence on turbocharger performance | |
| CN116499752A (en) | Aeroengine oil gas heat exchanger high altitude performance test device | |
| CN105806873B (en) | The cold effect experimental rigs of expansion ratios such as combustion engine turbine blade cooling | |
| Cormerais et al. | Heat transfers characterisations in a turbocharger: Experiments and correlations | |
| CN213515916U (en) | Loop flow calibrating device | |
| CN114441180B (en) | Low-temperature endurance test system and test method | |
| Grannan et al. | Small Turbojet Altitude Test Facility with Two Stage Turbocharger Inlet Air Cooling | |
| CN104596757B (en) | Variable geometry turbine supercharger nozzle ring flow calibration method and experimental rig | |
| CN112484822A (en) | Loop flow calibrating device | |
| Ambrogi et al. | The effect of off-design operation on the thermal performance of propylene-glycol and ethylene-glycol engine coolants | |
| RU105990U1 (en) | INSTALLATION FOR VERIFICATION OF GAS METERS | |
| Mataczynski et al. | Characterization of small-scale turbochargers for unmanned aerial systems | |
| Mikkelsen et al. | An Equation Set for ASME Nozzle Discharge and Thrust Coefficients | |
| Wang et al. | The Sensitivity Study of a Mechanical Loss Model in Turbocharger System | |
| CN115524130A (en) | Method for determining real-time heat release of air cooler in external bypass of engine | |
| McAssey Jr et al. | Convective heat transfer of binary mixtures under flow boiling conditions | |
| CN114486108B (en) | Method for evaluating leakage area of nacelle of aircraft engine | |
| CN114216684A (en) | Test system for testing plateau low-pressure transient performance of engine | |
| CN116296330A (en) | Turbine blade molded surface single-exhaust film cooling hole flow coefficient measuring method and application thereof | |
| Ballani et al. | 3D CFD Simulation of Hydraulic Test of an Engine Coolant System |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |