CN117889014B - Engine test system in vacuum environment - Google Patents
Engine test system in vacuum environment Download PDFInfo
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- CN117889014B CN117889014B CN202410303166.4A CN202410303166A CN117889014B CN 117889014 B CN117889014 B CN 117889014B CN 202410303166 A CN202410303166 A CN 202410303166A CN 117889014 B CN117889014 B CN 117889014B
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- 238000012360 testing method Methods 0.000 title claims abstract description 94
- 238000001816 cooling Methods 0.000 claims abstract description 54
- 238000000605 extraction Methods 0.000 claims abstract description 35
- 230000000087 stabilizing effect Effects 0.000 claims abstract description 5
- 239000012530 fluid Substances 0.000 claims description 28
- 238000009792 diffusion process Methods 0.000 claims description 13
- 230000000694 effects Effects 0.000 claims description 8
- 230000001105 regulatory effect Effects 0.000 claims description 8
- 239000002826 coolant Substances 0.000 claims description 7
- 239000000155 melt Substances 0.000 claims description 4
- 238000004891 communication Methods 0.000 claims description 3
- 230000002093 peripheral effect Effects 0.000 claims description 3
- 230000001603 reducing effect Effects 0.000 claims description 3
- 238000005086 pumping Methods 0.000 description 14
- 238000013016 damping Methods 0.000 description 4
- 230000010349 pulsation Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 239000007789 gas Substances 0.000 description 3
- 238000004088 simulation Methods 0.000 description 3
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000002708 enhancing effect Effects 0.000 description 2
- 230000010354 integration Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 238000000429 assembly Methods 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 239000000110 cooling liquid Substances 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 229910052757 nitrogen Inorganic materials 0.000 description 1
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Abstract
The invention provides a vacuum environment engine test system, which comprises a test cabin; a vacuum switch valve; the front end of the diffuser is connected with the ejector connecting port through a vacuum switch valve; a cooling device; the air extraction device is connected with the air outlet of the cooling device through a first air extraction pipeline, and the air extraction port is also connected with the vacuum air outlet through a second air extraction pipeline; and the buffer device is arranged on the first air extraction pipeline and/or the second air extraction pipeline and is used for stabilizing the pressure in the vacuum environment engine test system. Therefore, the buffer device is arranged to effectively improve the stability of the pressure in the vacuum environment engine test system when the tested engine is started, so that the system can more truly simulate the high vacuum environment of space, and the accuracy of data acquisition is improved.
Description
Technical Field
The invention relates to a simulation test system of a rocket engine in a vacuum environment, in particular to a vacuum environment engine test system.
Background
With the development of science and technology, space exploration is also becoming deeper and deeper.
The rocket engine designed by the engineer needs to be tested on the ground, and only through strict tests, the engine which can be used efficiently and safely can be applied to the spacecraft. At this time, an environment capable of simulating a high vacuum degree in the space needs to be created on the ground, and a vacuum environment engine test system is generated. The vacuum environment engine test system comprises a test cabin capable of forming a vacuum environment, and the engine can work in the test cabin in an ignition mode to simulate the condition that the engine ignites and works in space.
However, it is known that after the engine is ignited, the pressure in the test chamber will change obviously, and even if the vacuum pumping system works continuously, it is difficult to reduce the fluctuation of the pressure in the test chamber, so that the working condition of the engine in space cannot be fully restored on the ground, and the conditions of inaccurate data acquisition, low data reliability and the like are caused, so that a simulation test system is needed to solve the problems.
Disclosure of Invention
In order to at least partially solve the problems of the prior art, the present invention provides a vacuum environment engine test system comprising: the test cabin comprises a vacuum exhaust port and an ejector connecting port, the test cabin is used for arranging a tested engine in the test cabin, and the ejector connecting port is used for being connected with a nozzle of the tested engine; the vacuum switch valve is opened when the tested engine works; the diffusion device comprises a diffuser front end, a waiting pipe part and a diffuser rear end which are sequentially connected, wherein the diffuser front end is connected with an ejector connection port through a vacuum switch valve, the diffusion device is used for improving the flow velocity of fluid when the fluid passes through the waiting pipe part, and a pressure difference is formed between the diffuser front end and the diffuser rear end; the cooling device comprises an air inlet and an air outlet, the air inlet is connected with the rear end of the diffuser, and the cooling device is used for reducing the temperature of fluid; the air extraction device is connected with the air outlet of the cooling device through a first air extraction pipeline, and the air extraction port is also connected with the vacuum air outlet through a second air extraction pipeline; and the buffer device is arranged on the first air extraction pipeline and/or the second air extraction pipeline and is used for stabilizing the pressure in the vacuum environment engine test system.
The buffer device has a volume of 0.5-1 times the volume of the test chamber.
The buffer device comprises a first buffer tank, wherein the first buffer tank is arranged on the first exhaust pipe and is close to the air outlet of the cooling device.
Illustratively, the buffer device includes a second buffer tank disposed on the second extraction line and proximate to the vacuum exhaust port of the test chamber.
The buffer device has a buffer inlet and a buffer outlet, and is connected to the suction line in which it is located via the buffer inlet and the buffer outlet.
Illustratively, the cooling device has a fluid passageway in fluid communication with the air inlet and the air outlet for causing fluid entering the cooling device to tend to a steady flow condition to enhance the cooling effect of the cooling device on fluid passing therethrough.
Illustratively, the vacuum switch valve includes a shutoff rupture disk that melts and breaks upon ignition of the subject engine and communicates the test chamber with the diffusion device.
The vacuum environment engine test system further includes a condensing device provided on the first extraction line, the condensing device being configured to condense the gas exhausted from the cooling device.
Illustratively, the first air extraction pipeline and the second air extraction pipeline are further provided with regulating valves, and the regulating valves are used for regulating the opening amount according to the pressures of the front end and the rear end of the vacuum switch valve.
The vacuum environment engine test system further comprises a cold source with a cooling medium, wherein a cooling sleeve is arranged on the peripheral wall of the diffusion device and communicated with the cold source, so that the cooling medium cools the diffusion device.
Because the pressure in the system can be changed sharply when the tested engine is started by ignition and the low-pressure environment in high air cannot be simulated stably, the pressure fluctuation in the system can be reduced by arranging the buffer device, so that the tested engine can work for a long time in a stable pressure environment. In the prior art, in order to stabilize the pressure in the system, the pumping flow rate of the pumping device is generally increased, but the power and the volume of the pumping device are also increased, which is not beneficial to use, and even if the pumping flow rate of the pumping device is increased, the pressure pulsation of the pumping device during operation is difficult to reduce. Therefore, the buffer device is arranged to effectively improve the stability of the pressure in the vacuum environment engine test system when the tested engine is started, so that the system can more truly simulate the high vacuum environment of space, and the accuracy of data acquisition is improved. In addition, the buffer device is arranged, the volume of the test cabin can be increased to stabilize the pressure in the test cabin, the buffer device can be flexibly arranged on any exhaust pipeline, the use is flexible, the space is reasonably planned, and the integration level of the vacuum environment engine test system is effectively improved.
In the summary, a series of concepts in a simplified form are introduced, which will be further described in detail in the detailed description section. This summary is not intended to identify key features or essential features of the claimed subject matter, nor is it intended to be used as an aid in determining the scope of the claimed subject matter.
Advantages and features of the invention are described in detail below with reference to the accompanying drawings.
Drawings
The following drawings are included to provide an understanding of the invention and are incorporated in and constitute a part of this specification. Embodiments of the present invention and their description are shown in the drawings to explain the principles of the invention. In the drawings of which there are shown,
FIG. 1 is a schematic diagram of a vacuum environment engine test system according to an exemplary embodiment of the present invention;
FIG. 2 is a perspective view of an exemplary embodiment of the cooling device of FIG. 1;
FIG. 3 is a schematic diagram of a vacuum environment engine test system according to another exemplary embodiment of the present invention; and
FIG. 4 is a schematic diagram of a vacuum environment engine test system according to yet another exemplary embodiment of the present invention.
Wherein the above figures include the following reference numerals:
10. A test cabin; 20. a diffusion device; 21. a cooling jacket; 30. a cooling device; 31. a fluid channel; 40. an air extracting device; 50. a buffer device; 51. a first buffer tank; 52. a second buffer tank; 61. a first bleed line; 62. a second bleed line; 70. a condensing device; 80. a vacuum switch valve; 90. a regulating valve; 100. and a cold source.
Detailed Description
In the following description, numerous details are provided to provide a thorough understanding of the invention. However, it will be understood by those skilled in the art that the following description illustrates preferred embodiments of the invention by way of example only and that the invention may be practiced without one or more of these details. Furthermore, some technical features that are known in the art have not been described in detail in order to avoid obscuring the invention.
According to one aspect of the present invention, a vacuum environment engine test system is provided that may be used to simulate a vacuum environment to perform simulation experiments on rocket engines operating in a vacuum environment.
As shown in fig. 1, the vacuum environment engine test system may include a test chamber 10, a vacuum switching valve 80, a diffuser 20, a cooling device 30, an air extraction device 40, and a buffer device 50.
Test chamber 10 may have a cavity of any shape that can be pressurized. The cavity can be used for accommodating a tested engine and equipment related to a test, such as a test bench, signal acquisition equipment, a connecting pipeline and the like. In some embodiments, the test chamber 10 may have a cover that can be opened and closed to facilitate operation of the user within the chamber 10. In addition, the test chamber 10 may also have a plurality of sealed chamber-penetrating passages for connecting pipes, cables, signal lines, etc. inside and outside the test chamber. The test chamber 10 may also have an observation window for a user to observe from outside, although an image acquisition device may also be provided in the test chamber 10. Test chamber 10 may include vacuum vents and injector connection ports. The vacuum exhaust port can be used for exhausting, and the injector connecting port can be connected with the nozzle of the tested engine.
The vacuum switching valve 80 may comprise any valve configuration that can be opened when the subject engine is operating. In some embodiments, the vacuum switching valve 80 may be an electric valve, a pneumatic valve, a burst valve, or the like.
The diffuser 20 has a diffuser front end, a candidate pipe portion, and a diffuser rear end that are connected in sequence. The diffuser front end may be connected to the injector connection port through a vacuum switching valve 80. The diffuser 20 may be used to increase the fluid flow rate as it passes through the venturi section and create a pressure differential between the front and rear ends of the diffuser. The diffuser 20 may include any diffuser that may be present or may occur in the future. In some embodiments, the throat is provided with a constriction or nozzle between the inlet and outlet, which, due to its geometry, can change the velocity of the fluid as it passes through the constriction or nozzle, thereby creating a pressure differential between the inlet and outlet that facilitates a smoother flow of fluid from the front end of the diffuser to the rear end of the diffuser, thereby maintaining the low pressure condition within the front end of the diffuser, i.e., the test chamber 10.
The cooling device 30 may comprise any cooling device that may be present or may occur in the future, such as an air cooling device or a water cooling device. The cooling device may include an air inlet and an air outlet, and the air inlet may be coupled to the rear end of the diffuser. The cooling device 30 may be used to cool down the fluid entering it, avoiding damage to the vacuum environment engine test system by high temperature fluids.
The air extraction device 40 has an air extraction opening and an air exhaust opening, and the air extraction opening can be connected with the air outlet of the cooling device 30 through a first air extraction pipeline 61. The extraction port may also be connected to a vacuum exhaust port of the test chamber 10 via a second extraction line 62. The suction device 40 may comprise any configuration of vacuum pump, such as a dry screw vacuum pump, a Roots pump, a steam jet pump, or the like. By connecting the first suction line 61 and the second suction line 62, the suction device 40 can rapidly reduce the pressure in the test chamber 10, the diffuser 20, the cooling device 30, and the connecting lines to simulate a high vacuum environment in space.
The buffer means may be provided on one or more of the first suction line 61 and the second suction line 62. The damping means may comprise a damping tank, a damping chamber or a damping piston or the like. The buffer device can stabilize the pressure in the vacuum environment engine test system.
The workflow of the vacuum environment engine test system will be further described below. Before testing, the user may close the vacuum switching valve 80, install the test engine into the test chamber 10, and connect the nozzle of the test engine with the injector connection port. The evacuation device 40 is turned on to evacuate the test chamber 10, the diffuser 20, the cooling device 30, the buffer device 50, the first evacuation line 61, and the second evacuation line 62. In some embodiments, the pressures at the front and rear ends of the vacuum switching valve 80 may be equal or have a pressure difference. When the system reaches the required vacuum degree, the state is maintained, the tested engine is started by ignition, the vacuum switch valve 80 is opened, the air flow and tail flame sprayed by the tested engine enter the diffusion device 20, the flow speed is accelerated when the air flow passes through the diffusion device 20, and the pressure difference is formed between the front end and the rear end of the diffusion device 20, so that the low-pressure environment in the test cabin 10 is maintained. The cooling device 30 can rapidly cool the high temperature air flow to protect the system from the high temperature air flow.
Since the pressure in the system changes sharply when the engine to be tested is started by ignition, and the low-pressure environment in the high air cannot be stably simulated, the pressure fluctuation in the system can be reduced by providing the buffer device 50, so that the engine to be tested can work for a long time in a stable pressure environment. In the prior art, in order to stabilize the pressure in the system, the pumping flow rate of the pumping device 40 is generally increased, but the power and volume of the pumping device 40 are also increased, which is disadvantageous in use, and even if the pumping flow rate of the pumping device 40 is increased, it is difficult to reduce the pressure pulsation of the pumping device 40 during operation. Therefore, the buffer device 50 can effectively improve the stability of the pressure in the vacuum environment engine test system when the tested engine is started, so that the system can more truly simulate the high vacuum environment of space, and the accuracy of data acquisition is improved. In addition, the buffer device 50 is arranged, the increase of the volume of the test cabin 10 for stabilizing the pressure in the test cabin 10 can be avoided, the buffer device 50 can be flexibly arranged on any exhaust pipeline, the use is flexible, the space is reasonably planned, and the integration level of the vacuum environment engine test system is effectively improved.
Preferably, the volume of the buffer device 50 may be 0.5-1 times the volume of the test chamber 10. The volume of the vacuum environment engine test system can ensure the pressure stability in the vacuum environment engine test system, and the volume in the vacuum environment is not oversized, so that the power of the air extractor 40 is reduced. The volume ratio of the buffer device 50 to the test chamber 10 is a preferred value. Of course, it will be appreciated that the volume of the cushioning device 50 may be larger as desired in order to better enhance the pressure stabilizing effect.
Illustratively, the buffer device 50 may include a first buffer tank 51. The first buffer tank 51 may be disposed on the first suction line 61 near the air outlet of the cooling device 30. The first buffer tank 51 can provide a buffer space for the system at the rear end of the vacuum switch valve 80, so that if a large amount of fluid is discharged, if the air extractor 40 cannot timely discharge the large amount of fluid, the first buffer tank 51 can perform a temporary storage function, and maintain the pressure difference between the front end and the rear end of the diffuser 20, so that the air flow sprayed out by the tested engine smoothly flows, thereby maintaining the low pressure environment in the test chamber 10. It will of course be appreciated that the first buffer vessel 51 also reduces pressure pulsations generated in the first suction line 61 during operation of the suction device 40, further enhancing the system, and in particular the pressure stability in the test chamber 10.
Illustratively, the buffer device 50 may include a second buffer tank 52. The second buffer tank 52 may be disposed on the second bleed line 62 proximate to the vacuum vent of the test chamber 10. The second buffer tank 52 can provide buffer space for the system in front of the vacuum switch valve 80, so that when a large amount of fluid is accumulated in the system in front of the vacuum switch valve 80 and cannot be discharged through the vacuum switch valve 80 as soon as possible, buffer space can be provided for the system in front of the vacuum switch valve 80, and the rate of pressure rise in the test chamber 10 is reduced, thereby maintaining a low pressure environment in the test chamber 10. It will of course be appreciated that the second buffer tank 52 also reduces pressure pulsations during operation of the suction device 40, further enhancing the system, and in particular the pressure stability within the test chamber 10.
For example, the buffer device 50 may have a buffer inlet and a buffer outlet. The buffer device 50 can be connected with the air suction pipeline where the buffer device is located through the buffer inlet and the buffer outlet. That is, the inlet and outlet of the buffer device 50 are independently arranged, so that the speed of the air flow entering and exiting the buffer device 50 can be effectively improved, and the buffer effect of the buffer device is improved. Of course, it is understood that the damper 50 may also have multiple damper inlets or multiple damper outlets to provide a more unobstructed flow of air into and out of the damper 50.
Illustratively, as shown in FIG. 2, the cooling device 30 may have a fluid passage 31 that multiplexes the air inlet and the air outlet. The fluid passage 31 may be used to stabilize the fluid entering the cooling device 30 to enhance the cooling effect of the cooling device 30 on the fluid passing therethrough. This is because the air flow injected by the test engine is turbulent, which is disadvantageous for cooling. When the air flow sprayed by the tested engine passes through the fluid channel 31, the air flow can tend to be in a steady flow state, and the cooling effect is effectively improved. In addition, the multi-channel fluid channel 31 is arranged in the cooling device 30, so that the contact area between the air flow and the inner surface of the cooling device 30 can be increased, and the cooling effect of the cooling device 30 can be improved.
Illustratively, the vacuum switch valve 80 may include a shutoff rupture disk. The plugging rupture disk melts and breaks when the engine under test ignites and communicates the test chamber 10 with the diffusion device 20. In some embodiments, the blocking rupture disk may be made of a flammable rubber mat that may block the cavities at both ends of the vacuum interrupter valve 80 from communicating with each other until the engine ignites. When the engine ignites, the shutoff rupture disk melts and breaks, thereby rapidly switching on both ends of the vacuum interrupter valve 80. The vacuum switch valve 80 is a plugging rupture disk, so that the opening speed of the vacuum switch valve can be increased, and the accuracy of the acquisition parameters of the tested engine is improved.
For example, as shown in FIG. 3, the vacuum environment engine test system may also include a condensing device 70. The condensing means 70 may be provided on the first suction line 61. The condensing means 70 may be used to condense the gas discharged from the cooling means 30. On the one hand, the condensing device 70 can liquefy the discharged gas, so that the pressure in the pipeline where the condensing device is positioned is reduced, and the condensing device is matched with the air extractor 40, so that the pressure reducing effect is improved; on the other hand, in some embodiments, the air extractor 40 is provided with a low-temperature vacuum pump, and the air passing through the condensing device 70 is more beneficial to the vacuum effect of the low-temperature vacuum pump due to lower temperature, so that the vacuum-pumping speed is greatly improved, and the operation cost of the system is reduced.
Illustratively, the first and second bleed lines 61, 62 may also have a regulator valve 90 disposed thereon. The regulating valve 90 may be used to regulate the opening amount according to the pressures at the front and rear ends of the vacuum switching valve 80. In some embodiments, the regulator valve 90 may include a manual valve, a solenoid valve, a pneumatic valve, or the like. Preferably, the regulator valve 90 may be a proportional valve to facilitate accurate regulation of the pressure in front of and behind the vacuum switching valve 80.
Illustratively, as shown in FIG. 4, the vacuum environment engine test system may further include a cold source 100 having a cooling medium. A cooling jacket 21 may be provided on the outer peripheral wall of the diffuser 20. The cooling jacket 21 may be in communication with the cold source 100 such that the cooling medium cools the diffuser 20. By providing the heat sink 100, the high temperature damage of the tail flame to the diffuser 20 after the engine is ignited can be reduced, and the jet air flow can be cooled at the diffuser 20, and the cooling effect can be improved by matching with the cooling device 30. In some embodiments, the cooling source 100 may also be cooled by the cooling device 30. The cooling medium may include water, cooling liquid, liquid nitrogen, or the like.
In the description of the present invention, it should be understood that the azimuth or positional relationships indicated by the azimuth terms such as "front", "rear", "upper", "lower", "left", "right", "transverse", "vertical", "horizontal", and "top", "bottom", etc., are generally based on the azimuth or positional relationships shown in the drawings, merely for convenience of describing the present invention and simplifying the description, and these azimuth terms do not indicate and imply that the apparatus or elements referred to must have a specific azimuth or be constructed and operated in a specific azimuth, without limiting the scope of protection of the present invention; the orientation terms "inner" and "outer" refer to the inner and outer relative to the outline of the components themselves.
For ease of description, regional relative terms, such as "over … …," "over … …," "on the upper surface of … …," "over," and the like, may be used herein to describe regional positional relationships of one or more components or features to other components or features shown in the figures. It will be understood that the relative terms of regions include not only the orientation of the components illustrated in the figures, but also different orientations in use or operation. For example, if the element in the figures is turned over entirely, elements "over" or "on" other elements or features would then be included in cases where the element is "under" or "beneath" the other elements or features. Thus, the exemplary term "above … …" may include both orientations "above … …" and "below … …". Moreover, these components or features may also be positioned at other different angles (e.g., rotated 90 degrees or other angles), and all such cases are intended to be encompassed herein.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of exemplary embodiments according to the present application. As used herein, the singular is also intended to include the plural unless the context clearly indicates otherwise, and furthermore, it is to be understood that the terms "comprises" and/or "comprising" when used in this specification are taken to specify the presence of stated features, steps, operations, components, assemblies, and/or combinations thereof.
It should be noted that the terms "first," "second," and the like in the description and the claims of the present application and the above figures are used for distinguishing between similar objects and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used may be interchanged where appropriate such that embodiments of the application described herein may be implemented in sequences other than those illustrated or otherwise described herein.
The present invention has been illustrated by the above-described embodiments, but it should be understood that the above-described embodiments are for purposes of illustration and description only and are not intended to limit the invention to the embodiments described. In addition, it will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, and that many variations and modifications are possible in light of the teachings of the invention, which variations and modifications are within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (8)
1. A vacuum environment engine test system, the vacuum environment engine test system comprising:
the test cabin comprises a vacuum exhaust port and an ejector connecting port, wherein the test cabin is used for arranging a tested engine in the test cabin, and the ejector connecting port is used for being connected with a nozzle of the tested engine;
the vacuum switch valve is opened when the tested engine works;
The diffuser device comprises a diffuser front end, a venturi part and a diffuser rear end which are sequentially connected, wherein the diffuser front end is connected with the ejector connecting port through the vacuum switching valve, and the diffuser device is used for improving the flow rate of fluid when the fluid passes through the venturi part and forming pressure difference between the diffuser front end and the diffuser rear end; the vacuum environment engine test system further comprises a cold source with a cooling medium, wherein a cooling sleeve is arranged on the peripheral wall of the diffusion device and communicated with the cold source so that the cooling medium cools the diffusion device;
The cooling device comprises an air inlet and an air outlet, the air inlet is connected with the rear end of the diffuser, and the cooling device is used for reducing the temperature of fluid;
The air extraction opening of the air extraction device is connected with the air outlet of the cooling device through a first air extraction pipeline, and the air extraction opening is also connected with the vacuum air outlet through a second air extraction pipeline;
The buffer device is arranged on the first air extraction pipeline and the second air extraction pipeline and is used for stabilizing the pressure in the vacuum environment engine test system; and
And the condensing device is arranged on the first extraction pipeline and is used for condensing the gas exhausted from the cooling device.
2. The vacuum environment engine test system of claim 1, wherein the buffer means has a volume of 0.5-1 times the test chamber volume.
3. The vacuum environment engine test system of claim 1, wherein the buffer means comprises a first buffer tank disposed on the first extraction line proximate the air outlet of the cooling means.
4. The vacuum environment engine testing system of claim 1, wherein the buffer device comprises a second buffer tank disposed on the second extraction line proximate the vacuum exhaust port of the test chamber.
5. The vacuum environment engine test system of claim 1, wherein the buffer device has a buffer inlet and a buffer outlet, the buffer device being connected to the bleed line through the buffer inlet and the buffer outlet.
6. The vacuum environment engine test system of claim 1, wherein said cooling device has a fluid passage in multiplexing communication with said air inlet and said air outlet for bringing fluid entering said cooling device to a steady flow condition to enhance the cooling effect of said cooling device on fluid passing therethrough.
7. The vacuum environment engine test system of claim 1, wherein the vacuum switching valve includes a shutoff rupture disk that melts and breaks upon ignition of the subject engine and communicates the test chamber with the diffusion device.
8. The vacuum environment engine test system of claim 1, wherein the first extraction pipeline and the second extraction pipeline are further provided with regulating valves, and the regulating valves are used for regulating opening amounts according to pressures at front and rear ends of the vacuum switch valve.
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