Test system for conducting ground and high-altitude tests

Abstract

The present invention discloses a test system for conducting ground and high-altitude tests, comprising: a soundproof tower and a test workshop arranged on the ground, and an air intake circuit, an adjustment circuit, a test circuit, a ground exhaust circuit and a vacuum exhaust circuit arranged in the test workshop. The air intake end of the air intake circuit is connected to a gas supply device. The adjustment circuit and the test circuit are arranged in parallel, and their air intake ends are respectively communicated with the air intake circuit. An air turbine starter is connected in the test circuit, and a vacuum test chamber is slidably arranged to cover the air turbine starter. The ground exhaust circuit and the vacuum exhaust circuit are arranged in parallel, and their air intake ends are respectively connected to the adjustment circuit and the test circuit. The exhaust ends of the ground exhaust circuit and the vacuum exhaust circuit are respectively connected to the soundproof tower. The system of the present invention can conduct conventional tests and high-altitude tests simultaneously, thereby saving test costs and test sites, having high test efficiency, and creating conditions for conducting high-altitude tests on the ground state of the air turbine starter.

Description

Technical Field

[0001] The present invention relates to the field of air turbine starter test devices, and in particular, to a test system for carrying out ground and high-altitude tests. Background Art

[0002] Currently, the air turbine starter test items mainly include power measurement, main engine start, main engine false start, etc. During the test, the air turbine starter is installed on the test bench. When the intake valve is opened, air with a certain temperature and pressure enters the air turbine starter to impact the turbine and do work, and the air after doing work is discharged into the test workshop. As Figure 1 shown, the existing test scheme simulates the exhaust of the starter to the ground atmospheric environment, and the exhaust environment pressure is 1 atmospheric pressure.

[0003] In the existing technical scheme, the test equipment cannot simulate the exhaust of the air turbine starter to a vacuum environment, that is, the high-altitude test of the air turbine starter cannot be carried out. Summary of the Invention

[0004] The present invention provides a test system for carrying out ground and high-altitude tests to solve the technical problem that the existing test equipment cannot simulate the exhaust of the air turbine starter to a vacuum environment, that is, the high-altitude test of the air turbine starter cannot be carried out.

[0005] The technical solution adopted by the present invention is as follows:

[0006] A test system for carrying out ground and high-altitude tests includes: a silencing tower and a test workshop arranged on the ground, and an intake circuit, a regulating circuit, a test circuit, a ground exhaust circuit and a vacuum exhaust circuit arranged in the test workshop; the intake end of the intake circuit is connected to a gas supply device for supplying test gas; the regulating circuit and the test circuit are arranged in parallel, and the intake ends of both are respectively communicated with the exhaust end of the intake circuit. An air turbine starter to be tested is connected in the test circuit, and a vacuum test chamber is slidably arranged to cover the air turbine starter to form a vacuum test environment; the ground exhaust circuit and the vacuum exhaust circuit are arranged in parallel, and the intake ends of both are respectively connected to the exhaust ends of the regulating circuit and the test circuit. The exhaust ends of both the ground exhaust circuit and the vacuum exhaust circuit extend out of the test workshop and are then connected to the silencing tower, and the vacuum exhaust circuit is used to adjust the exhaust pressure of the vacuum test chamber.

[0007] Further, the intake circuit includes a gas input pipe for conveying test gas, a regulating branch pipe, a gas supply valve, a quick shut-off valve, a flowmeter, a first regulating valve, and an electric heater that are sequentially connected to the gas input pipe along the gas input direction, and a second regulating valve; the intake end of the gas input pipe is connected to a gas supply device, and its opposite exhaust end is respectively connected to the intake ends of the regulating circuit and the test circuit; the intake end of the regulating branch pipe is connected to the gas input pipe between the gas supply valve and the quick shut-off valve, and its opposite exhaust end extends out of the test plant and is connected to a silencing tower.

[0008] Further, the regulating circuit includes a regulating pipe, an exhaust valve and a third regulating valve that are sequentially connected to the regulating pipe along the gas flow direction, and the intake end of the regulating pipe is connected to the exhaust end of the intake circuit; the test circuit includes an intake pipeline assembly, an output connecting pipe, and an intake valve connected to the intake pipeline assembly. The intake end of the intake pipeline assembly is connected to the exhaust end of the intake circuit, and its opposite exhaust end is connected to an air turbine starter. The two ends of the output connecting pipe are respectively connected to the vacuum test chamber and the exhaust end of the regulating pipe.

[0009] Further, the ground exhaust circuit includes a ground exhaust pipe and a first switch valve connected to the ground exhaust pipe; the intake end of the ground exhaust pipe is connected to the output connecting pipe, and its opposite exhaust end extends out of the test plant and is connected to a silencing tower.

[0010] Further, the vacuum exhaust circuit includes a vacuum exhaust pipe, a second switch valve, a heat exchanger, and a vacuum pump that are sequentially connected to the vacuum exhaust pipe along the gas discharge direction; the intake end of the vacuum exhaust pipe is connected to the output connecting pipe, and its opposite exhaust end extends out of the test plant and communicates with a silencing tower.

[0011] Further, the vacuum test chamber includes a hollow chamber provided in a hollow manner for forming a vacuum test environment. The air turbine starter is fixedly installed in the hollow chamber. The hollow chamber is also communicated with a vacuum pumping and pressure regulating system for pumping the hollow chamber to a vacuum and regulating the vacuum pressure in the hollow chamber; a through-hole is provided on the wall surface of the hollow chamber, and an intake pipeline assembly is hermetically installed in the through-hole. The intake end of the intake pipeline assembly communicates with the exhaust end of the intake circuit, and its opposite exhaust end communicates with the intake casing of the air turbine starter in the hollow chamber; the intake pipeline assembly is used to supply the test gas supplied by the gas supply device to the air turbine starter, and at the same time reduce the thermal stress on the intake pipeline through its own structural setting to avoid damaging the air turbine starter.

[0012] Further, the intake pipeline assembly includes a bellows axially telescoped to absorb thermal expansion and an intake pipeline for conveying test gas; one end of the bellows is fixed to the hollow chamber outside the periphery of the through-hole, and its opposite end is fixedly connected to the intake pipeline; the intake end of the intake pipeline communicates with the intake circuit, and its opposite exhaust end axially penetrates the bellows and the through-hole and then communicates with the intake casing of the air turbine starter.

[0013] Furthermore, the bellows includes a bellows body telescopically arranged along the axial direction, and flange connection discs connected to opposite ends of the bellows body; the intake pipeline includes a mating flange disc that cooperates and fixes with the flange connection disc at the cantilever end of the bellows body, and an intake pipe for conveying test gas. The intake pipe axially penetrates the mating flange disc and the bellows, and is detachably fixed to the mating flange disc.

[0014] Furthermore, the hollow cabin includes a cabin body that is hollowly arranged to form a vacuum test environment, and a cover for installing an air turbine starter; the cabin body is slidably supported on the guide rail platform, and the first end of the cabin body is open, and a penetration port is provided on the opposite second end; the cover is fixedly supported on the installation platform or the ground of the test bench, and is used to connect to the open end of the cabin body to close the cabin body.

[0015] Furthermore, the vacuum test chamber 3 further includes a cold blowing pipeline connected to the cover. The cold blowing pipeline is used to blow cooling gas to the air turbine starter to reduce the body temperature of the air turbine starter, thereby shortening the time interval between two starts.

[0016] The present invention has the following beneficial effects:

[0017] The test system of the present invention for carrying out ground and high-altitude tests can not only carry out conventional (ground) air turbine starter tests, but also carry out high-altitude tests of air turbine starters, simulating the exhaust of air turbine starters into a vacuum environment. Thus, a set of test systems has the functions of carrying out both conventional tests and high-altitude tests, saving test costs and test sites, and the test operation is simple, the test efficiency is high, creating conditions for carrying out high-altitude tests on air turbine starters in the ground state.

[0018] In addition to the purposes, features and advantages described above, the present invention has other purposes, features and advantages. The following will refer to the drawings for a further detailed description of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The drawings forming a part of this application are used to provide a further understanding of the present invention. The schematic embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation to the present invention. In the drawings:

[0020] Figure 1 is a schematic diagram of an existing air turbine starter test scheme;

[0021] Figure 2 is a schematic diagram of the test system for carrying out ground and high-altitude tests according to the preferred embodiment of the present invention;

[0022] Figure 3 is Figure 2 the schematic diagram of the spatial structure of the vacuum test chamber in

[0023] Figure 4 is Figure 3 a top view structural schematic diagram of

[0024] Figure 5 is Figure 3 a sectional front view structural schematic diagram of

[0025] Figure 6 is Figure 3 a spatial structural schematic diagram of the cold air distribution pipe in

[0026] Figure 7 is Figure 3 a front view structural schematic diagram of the mating flange in

[0027] Figure 8 is Figure 7 a sectional view structural schematic diagram in the A-A direction of

[0028] Figure 9 is Figure 3 a front view structural schematic diagram of the intake pipe in

[0029] Figure 10 is Figure 9 a sectional view structural schematic diagram in the B-B direction of

[0030] Legend Explanation

[0031] 1. Silencing tower; 2. Test workshop; 3. Vacuum test chamber; 10. Hollow chamber; 101. Through-cabin opening; 102. Threading hole; 11. Cabin body; 12. Cover; 13. Observation window; 20. Air turbine starter; 31. Air extraction port; 32. Ventilation port; 40. Intake pipeline assembly; 41. Bellows; 42. Intake pipeline; 421. Mating flange; 4211. Internal thread hole; 4212. Kidney-shaped hole; 422. Intake pipe; 4220. Threaded boss; 50. Guide rail platform; 60. Cold blowing pipeline; 61. Cold air connection pipe; 62. Cold air distribution pipe; 620. Air outlet hole; 7. Intake circuit; 71. Gas input pipe; 72. Regulation branch pipe; 73. Supply valve; 74. Quick shut-off valve; 75. Flowmeter; 76. First regulating valve; 77. Electric heater; 78. Second regulating valve; 8. Regulation circuit; 81. Regulation pipe; 82. Exhaust valve; 83. Third regulating valve; 9. Test circuit; 91. Output connecting pipe; 92. Intake valve; 93. Dynamometer; 15. Ground exhaust circuit; 151. Ground exhaust pipe; 152. First switching valve; 16. Vacuum exhaust circuit; 161. Vacuum exhaust pipe; 162. Second switching valve; 163. Heat exchanger; 164. Vacuum pump. Detailed Implementation Modes

[0032] The following will describe the embodiments of the present invention in detail with reference to the accompanying drawings. However, the present invention can be implemented in many different ways defined and covered by the following.

[0033] Referring to Figure 2 , a preferred embodiment of the present invention provides a test system for conducting ground and high-altitude tests, including: a soundproof tower 1 and a test workshop 2 arranged on the ground, and an intake air circuit 7, a regulating circuit 8, a test circuit 9, a ground exhaust circuit 15 and a vacuum exhaust circuit 16 arranged in the test workshop 2. The intake end of the intake air circuit 7 is connected to a gas supply device for supplying test gas. The regulating circuit 8 and the test circuit 9 are arranged in parallel, and the intake ends of both are respectively communicated with the exhaust end of the intake air circuit 7. In the test circuit 9, an air turbine starter to be tested is connected, and a vacuum test chamber 3 is slidably arranged to cover the air turbine starter to form a vacuum test environment. The ground exhaust circuit 15 and the vacuum exhaust circuit 16 are arranged in parallel, and the intake ends of both are respectively connected to the exhaust ends of the regulating circuit 8 and the test circuit 9. The exhaust ends of both the ground exhaust circuit 15 and the vacuum exhaust circuit 16 extend out of the test workshop 2 and are then connected to the soundproof tower 1. The vacuum exhaust circuit 16 is used to adjust the exhaust pressure of the vacuum test chamber 3.

[0034] As Figure 2 shown, when conducting a conventional (ground) test, the ground exhaust circuit 15 is opened, the vacuum exhaust circuit 16 is closed, and the vacuum test chamber 3 is moved away to expose the air turbine starter 20 to the atmospheric environment; before the test, the test circuit 9 is closed and the regulating circuit 8 is opened. The compressed air supplied by the gas supply device is discharged to the soundproof tower 1 through the intake air circuit 7, the regulating circuit 8 and the ground exhaust circuit 15. During the test, the temperature and pressure of the compressed air are adjusted to the required intake parameters through the intake air circuit 7, and then the test circuit 9 is opened and the regulating circuit 8 is closed. The compressed air enters the air turbine starter 20 through the test circuit 9 to impact the turbine to do work, and the air after doing work is discharged into the test workshop 2, thereby realizing the exhaust of the air turbine starter 20 to the ground atmospheric environment. When conducting a high-altitude test, before the test, the ground exhaust circuit 15 is closed, the vacuum exhaust circuit 16 is opened, the vacuum test chamber 3 is sealed, and at the same time the regulating circuit 8 is opened and the test circuit 9 is closed. The compressed air supplied by the gas supply device expands into negative-pressure air with a certain degree of vacuum after passing through the intake air circuit 7 and the regulating circuit 8, and the negative-pressure air is then discharged to the soundproof tower through the vacuum exhaust circuit 16; during the test, the temperature and pressure of the compressed air are adjusted to the required intake parameters through the intake air circuit 7, and the pressure in the vacuum test chamber 3 is adjusted to the required exhaust pressure through the vacuum exhaust circuit 16. Then the test circuit 9 is opened and the regulating circuit 8 is closed. The compressed air enters the air turbine starter 20 through the test circuit 9 to impact the turbine to do work, and the air after doing work is discharged into the vacuum test chamber 3. The air in the vacuum test chamber 3 is sucked away by the vacuum exhaust circuit 16 and discharged into the soundproof tower 1.

[0035] The test system of the present invention is used for carrying out ground and high-altitude tests. It can not only carry out conventional (ground) air turbine starter tests, but also carry out high-altitude tests of air turbine starters, simulating the exhaust of air turbine starters into a vacuum environment. Thus, a set of test systems has the functions of carrying out both conventional tests and high-altitude tests, saving test costs and test sites. Moreover, the test operation is simple, the test efficiency is high, creating conditions for carrying out high-altitude tests on air turbine starters in the ground state.

[0036] Optionally, as Figure 2 shown, the intake circuit 7 includes a gas input pipe 71 for conveying test gas, a regulating branch pipe 72, a supply valve 73, a quick shut-off valve 74, a flowmeter 75, a first regulating valve 76, an electric heater 77, and a second regulating valve 78 that are sequentially connected to the gas input pipe 71 along the gas input direction. The intake end of the gas input pipe 71 is connected to a gas supply device, and its opposite exhaust end is respectively connected to the intake ends of the regulating circuit 8 and the test circuit 9. The intake end of the regulating branch pipe 72 is connected to the gas input pipe 71 between the supply valve 73 and the quick shut-off valve 74, and its opposite exhaust end extends out of the test workshop 2 and is connected to the silencer tower 1. In this optional solution, the supply valve 73 serves as a switching valve for controlling the on-off of the intake circuit 7; the quick shut-off valve 74 also serves as a switching valve for quickly cutting off the intake circuit 7 when problems occur in the system, playing a safety protection role; the first regulating valve 76 and the second regulating valve 78 cooperate to regulate the supply pressure of the intake circuit 7.

[0037] Optionally, as Figure 2 shown, the regulating circuit 8 includes a regulating pipe 81, an exhaust valve 82 and a third regulating valve 83 that are sequentially connected to the regulating pipe 81 along the gas flow direction. The intake end of the regulating pipe 81 is connected to the exhaust end of the intake circuit 7. The test circuit 9 includes an intake pipe assembly 40, an output connection pipe 91, and an intake valve 92 connected to the intake pipe assembly. The intake end of the intake pipe assembly is connected to the exhaust end of the intake circuit 7, and its opposite exhaust end is connected to the air turbine starter. Both ends of the output connection pipe 91 are respectively connected to the vacuum test chamber 3 and the exhaust end of the regulating pipe 81. In this optional solution, the exhaust valve 82 is used as a switching valve for controlling the on-off of the regulating circuit 8; the third regulating valve 83 is used to simulate the pressure drop when air passes through the air turbine starter 20, thereby improving the accuracy of regulating the intake pressure, temperature and flow in the circuit before the test in the regulating circuit 8; the intake valve 92 also serves as a switching valve for controlling the on-off of the test circuit 9. When the test circuit 9 is closed and the regulating circuit 8 is opened, it is used to regulate the supply pressure, flow and temperature in the whole circuit before the ground conventional test or the vacuum test, so that when the regulating circuit 8 is closed and the test circuit 9 is opened later, the formal air turbine starter test can be carried out. In this optional solution, as Figure 2 shown, the test circuit 9 further includes a dynamometer 93 connected to the air turbine starter 20.

[0038] Optionally, as Figure 2 shown, the ground exhaust circuit 15 includes a ground exhaust pipe 151 and a first switching valve 152 connected in the ground exhaust pipe 151. The intake end of the ground exhaust pipe 151 is connected to the output connection pipe 91, and its opposite exhaust end extends out of the test workshop 2 and is connected to the silencing tower 1. When the first switching valve 152 is opened, the whole system is used for a conventional ground test.

[0039] Optionally, as Figure 2 shown, the vacuum exhaust circuit 16 includes a vacuum exhaust pipe 161 and a second switching valve 162, a heat exchanger 163 and a vacuum pump 164 connected in sequence to the vacuum exhaust pipe 161 along the gas discharge direction. The intake end of the vacuum exhaust pipe 161 is connected to the output connection pipe 91, and its opposite exhaust end extends out of the test workshop 2 and communicates with the silencing tower 1. In this optional solution, the heat exchanger 163 is also externally connected to a cooling circuit for cooling the gas in the vacuum exhaust circuit 16, thereby reducing the power required by the vacuum pump 164. Thus, a vacuum pump 164 with a smaller power can be selected to reduce the test cost. When the second switching valve 162 is opened, the whole system is used for a vacuum test.

[0040] Specifically, when conducting a conventional (ground) test, the first switching valve 152 is opened, the second switching valve 162 is closed, and the vacuum test chamber 3 is moved away to expose the air turbine starter 20 to the atmospheric environment. Before the test, the intake valve 92 is closed and the exhaust valve 82 is opened. The compressed air supplied by the air supply device sequentially passes through the gas input pipe 71, the exhaust valve 82, the third regulating valve 83 and the first switching valve 152 and is discharged to the silencing tower 1. During the test, the temperature and pressure of the compressed air are adjusted to the required intake parameters through the intake circuit 7, and then the intake valve 92 is opened and the exhaust valve 82 is closed. The compressed air enters the air turbine starter 20 through the intake valve 92 to impact the turbine to do work, and the air after doing work is discharged into the test workshop 2, thereby realizing the exhaust of the air turbine starter 20 to the ground atmospheric environment. When conducting a high-altitude test, before the test, the first switching valve 152 is closed, the second switching valve 162 is opened, the vacuum test chamber 3 is sealed, and at the same time the exhaust valve 82 is opened and the intake valve 92 is closed. The compressed air supplied by the air supply device expands into negative-pressure air with a certain degree of vacuum after passing through the intake circuit 7, the exhaust valve 82 and the third regulating valve 83, and the negative-pressure air then passes through the second switching valve 162, the heat exchanger 163 and the vacuum pump 164 and is discharged to the silencing tower. During the test, the temperature and pressure of the compressed air are adjusted to the required intake parameters through the intake circuit 7, and the pressure in the vacuum test chamber 3 is adjusted to the required exhaust pressure through the vacuum exhaust circuit 16. Then the intake valve 92 is opened and the exhaust valve 82 is closed. The compressed air enters the air turbine starter 20 through the intake valve 92 to impact the turbine to do work, and the air after doing work is discharged into the vacuum test chamber 3. The air in the vacuum test chamber 3 is sucked away by the vacuum pump 164 and discharged to the silencing tower 1.

[0041] Optionally, as Figures 3 - 5 shown, the vacuum test chamber 3 includes: a hollow chamber 10 that is hollowly arranged to form a vacuum test environment, an air turbine starter 20 fixedly installed in the hollow chamber 10, and the hollow chamber 10 is also connected to a vacuum pumping and pressure regulating system for pumping the hollow chamber 10 into a vacuum and regulating the vacuum pressure inside the hollow chamber 10. A through-hole 101 penetrating the wall surface is formed on the wall surface of the hollow chamber 10, and an intake pipe assembly 40 is hermetically installed in the through-hole 101. The intake end of the intake pipe assembly 40 is connected to the exhaust end of the intake circuit 7, and its opposite exhaust end is connected to the intake casing of the air turbine starter 20 inside the hollow chamber 10. The intake pipe assembly 40 is used to supply the test gas supplied by the gas supply device into the air turbine starter 20, and at the same time reduce the thermal stress on the intake pipe through its own structural arrangement to avoid damage to the air turbine starter 20.

[0042] In the prior art, the air turbine starter is mainly used to drive the combustion engine rotor of the main engine to achieve false start, cold operation and start of the main engine. The existing test items of the air turbine starter mainly include power measurement, main engine start, main engine false start, etc. The existing test scheme is that air enters the air turbine starter to impact the turbine to do work, and the air after doing work is discharged into the test workshop, simulating the exhaust of the starter to the ground atmospheric environment, and the pressure of the exhaust environment is 1 atmospheric pressure. And the present invention proposes a vacuum test chamber 3. Before the test, the air turbine starter 20 is installed in the hollow chamber 10, and the intake pipe assembly 40 passes through the hollow chamber 10 and is connected to the intake casing of the air turbine starter 20. During the test, the air pressure inside the hollow chamber 10 is controlled by the vacuum pumping and pressure regulating system to achieve the simulation of the air turbine starter exhausting to the vacuum environment; during the test, the high-temperature compressed air enters the air turbine starter 20 through the intake pipe assembly 40, and the temperature decreases after the air turbine starter 20 does work, and the exhaust is discharged into the hollow chamber 10.

[0043] In the present invention, during the test of the air turbine starter 20, the exhaust gas is directly discharged into the hollow cabin 10. Therefore, the thermal expansion amounts between the intake pipe assembly 40 and the air turbine starter 20, and between the intake pipe assembly 40 and the hollow cabin 10 are different. A relative displacement occurs at the penetration opening 101 between the intake pipe assembly 40 and the cabin body of the hollow cabin 10. Without corresponding structural design, the intake pipe assembly 40 with a larger thermal expansion amount will directly apply thermal stress to the cabin body, and the cabin body will react the thermal stress on the intake pipe assembly 40 and the air turbine starter 20, resulting in the deformation of the casing of the air turbine starter 20. However, through the structural arrangement of the intake pipe assembly 40 in the present invention, the thermal stress on the intake pipe is greatly reduced, and further the deformation amount of the casing of the air turbine starter 20 is reduced to avoid damage to the air turbine starter 20. Thus, the present invention realizes the ground simulation of the exhaust of the air turbine starter into a vacuum environment, creates conditions for the high-altitude test of the air turbine starter in the ground state, and at the same time effectively solves the sealing problem at the penetration of the intake pipe assembly 40 through the hollow cabin and the thermal stress problem caused by different temperatures of the cabin body and the intake pipe assembly.

[0044] Optionally, as Figure 4 and Figure 5 shown, the intake pipe assembly 40 includes a bellows 41 that is axially telescopic to absorb thermal expansion, and an intake pipe 42 for conveying test gas. One end of the bellows 41 is fixed to the hollow cabin 10 on the outer periphery of the penetration opening 101, and the opposite end thereof is fixedly connected to the intake pipe 42. The intake end of the intake pipe 42 communicates with the intake circuit 7, and the opposite exhaust end axially penetrates through the bellows 41 and the penetration opening 101 and then communicates with the intake casing of the air turbine starter 20. During the test, high-temperature compressed air is input into the air turbine starter 20 through the intake pipe 42. After the air turbine starter 20 works, the temperature decreases, and the exhaust gas is discharged into the hollow cabin 10, resulting in different thermal expansion amounts between the intake pipe 42 and the air turbine starter 20, and between the intake pipe 42 and the cabin body. A relative displacement occurs at the penetration opening 101 between the intake pipe 42 and the cabin body. Without corresponding structural arrangement, the intake pipe 42 with a larger thermal expansion amount will directly apply thermal stress to the cabin body, and the cabin body will react the thermal stress on the intake pipe 42 and the air turbine starter 20, causing the deformation of the casing of the air turbine starter; after installing the bellows 41 made of metal material, the bellows 41 is stretched, and the thermal expansion amount difference between the intake pipe 42 and the cabin body is absorbed by the bellows 41, and the corresponding thermal stress is transformed into a very small tensile force of the bellows, thereby reducing the deformation amount of the casing of the air turbine starter.

[0045] In this optional solution, as Figure 5As shown, the bellows 41 includes a bellows body telescopically arranged along the axial direction, and flange connection plates connected to opposite ends of the bellows body. The intake pipeline 42 includes a mating flange plate 421 that cooperates and fixes with the flange connection plate at the cantilever end of the bellows body, and an intake pipe 422 for conveying test gas. The intake pipe 422 axially penetrates the mating flange plate 421 and the bellows 41, and is detachably fixed to the mating flange plate 421. In this alternative solution, one end of the metal bellows is connected to the cabin body in the form of a flange, and the other end is connected to the intake pipe 422 through a flange and the mating flange plate 421. In the conventional connection of the bellows, different pipelines are connected to both ends of the bellows, and the fluid flows through the bellows. However, the present invention proposes a new connection method, that is, one end of the bellows is connected to the cabin body through a flange, and the other end is connected to the intake pipe 422 through a flange and the mating flange plate 421, so that the intake pipe 422 can pass through the bellows 41, and the fluid flows in the intake pipeline without flowing through the bellows 41, improving the stability of the fluid flow and ensuring the uniformity of the inlet air of the air turbine starter 20.

[0046] In a specific embodiment of this alternative solution, as Figure 7 and Figure 8 shown, the mating flange plate 421 is in a disc shape, with an internally threaded hole 4211 penetrating the disc surface machined at its center, and waist-shaped holes 4212 arranged in sequence along the circumferential direction and penetrating the disc surface machined on its outer periphery, and the waist-shaped holes 4212 extend along the circumferential line. The waist-shaped holes 4212 facilitate the connection of the mating flange plate 421 and the bellows 41 by bolts. As Figure 9 and Figure 10 shown, the intake end of the intake pipe 422 is connected to the gas supply device, and its opposite exhaust end is connected to the intake casing of the air turbine starter 20. And an externally convex annular threaded boss 4220 is provided on the outer circle of the middle part of the intake pipe 422. External threads are machined on the outer circle surface of the threaded boss 4220. The intake pipe 422 is detachably fixed to the mating flange plate 421 through the threaded connection between the threaded boss 4220 and the internally threaded hole 4211. In the present invention, this kind of mating connection method between the intake pipe 422 and the mating flange plate 421 realizes reducing the thermal stress of the intake pipeline and reducing air leakage, and at the same time effectively avoids the direct connection of the metal bellows into the intake pipeline, improving the stability and uniformity of the air intake of the air turbine starter.

[0047] Optionally, as Figure 5As shown in the figure, the hollow chamber 10 includes a chamber body 11 that is hollowly arranged to form a vacuum test environment, and a cover 12 for installing the air turbine starter 20. The chamber body 11 is slidably supported on the guide rail platform 50, and the first end of the chamber body 11 is open, and a through-chamber opening 101 is provided at the opposite second end; the chamber body 11 is in a movable form and can be driven by manpower, an electric motor, a hydraulic mechanism, etc. to move linearly on the guide rail platform 50. The cover 12 is fixedly supported on the installation platform of the test stand or the ground and is used to connect with the open end of the chamber body 11 to close the chamber body 11. The cover 12 serves as the cover plate of the hollow chamber 10 and also serves as the installation bench for the air turbine starter 20. During the test, the air turbine starter is installed on the cover. This structural setting of the hollow chamber 10 facilitates the separate processing of the chamber body 11 and the cover 12 on the one hand, reducing the processing difficulty, and on the other hand, facilitating the movement of the chamber body 11 and its positioning after being connected and fixed to the cover 12 after movement.

[0048] Optionally, as Figure 5 shown, the vacuum pumping and pressure regulating system includes an air extraction port 31 and an air vent 32 penetrating the wall surface of the chamber body 11, a vacuum pump 164 connected to the air extraction port 31 for pumping vacuum, a regulating valve, and a controller connected to the air vent 32. The vacuum pump 164 and the regulating valve are respectively connected to the controller to cooperate to regulate the vacuum pressure in the chamber body 11. For example, when the pressure in the chamber body 11 is too low, the controller controls the opening of the regulating valve to increase, thereby increasing the amount of external gas entering the chamber body 11 through the air vent 32; when the pressure in the chamber body 11 is too high, the controller controls the opening of the regulating valve to decrease, thereby reducing the amount of external gas entering the chamber body 11 through the air vent 32. In the present invention, the vacuum pump 164 is provided with a pressure detector for detecting the pressure in the chamber body 11. The pressure detector sends the pressure value in the chamber body 11 to the controller in real time, and the controller adjusts the opening of the regulating valve or the suction force of the vacuum pump 164 according to the difference between the received pressure value and the set pressure value.

[0049] Optionally, as Figure 5 shown, the vacuum test chamber 3 further includes a cold blowing pipeline 60 connected to the cover 12. The cold blowing pipeline 60 is used to blow cooling gas to the air turbine starter 20 to reduce the body temperature of the air turbine starter 20, thereby shortening the time interval between two starts, accelerating the cooling and temperature reduction of the air turbine starter 20 after the start is completed, and thus improving the test efficiency.

[0050] In this optional solution, as Figure 5As shown in the figure, the cold air blowing pipeline 60 includes a cold air connection pipe 61 fixedly arranged in the cover 12 and a cold air distribution pipe 62 connected to the inner side surface of the cover 12. The cold air distribution pipe 62 is located inside the cabin body 11 and is communicated with the cold air connection pipe 61. The cold air connection pipe 61 is connected to a cold air supply device for supplying cooling air or is communicated with the atmosphere, and a switch valve for controlling its on-off and a flow regulating valve for regulating the flow rate are provided in the pipeline of the cold air connection pipe 61. In this alternative solution, by arranging the cold air blowing pipeline 60 on the cover 12, normal temperature air or cooling air can be blown to the air turbine starter 20 through the cold air blowing pipeline 60 between two starts of the air turbine starter 20, so as to reduce the temperature of the air turbine starter 20 body and shorten the time interval between two starts, thereby improving the test efficiency.

[0051] In the first specific embodiment of this alternative solution, as Figure 6 shown, the cold air distribution pipe 62 is a hollow annular pipe arranged in a ring shape, and air outlet holes 620 for the cooling air to spray outwards are opened on the inner ring surface of the annular pipe. The air turbine starter 20 is located in the inner hole of the annular pipe, and the structure of the cold air distribution pipe 62 is simple. Alternatively, in the second specific embodiment of this alternative solution, not shown in the figure, the cold air distribution pipe 62 is a cylindrical tube arranged in a hollow and cylindrical shape, and an annular cavity extending axially and in a ring shape is provided in the wall surface of the cylindrical tube. The annular cavity is communicated with the cold air connection pipe 61, and air outlet holes 620 for the cooling air to spray outwards are opened on the inner wall surface of the cylindrical tube, and one end of the air turbine starter 20 in the axial direction is installed in the inner hole of the cylindrical tube.

[0052] Optionally, as Figure 3 and Figure 5 shown, through holes for the measurement lines of vibration, temperature and pressure, and the lubricating oil pipes to pass through are further opened on the cover 12. An observation window 13 for external personnel to observe the situation inside the cabin and a wire passing hole 102 for the camera cable to pass through are further provided on the cabin body 11. Rubber layers are coated outside the measurement lines, the lubricating oil pipes and the cables. In this alternative solution, the observation window 13 facilitates the test personnel to observe the situation of the air turbine starter 20; a camera can be installed in the hollow cabin 10 through the camera cable, and the situation inside the cabin is displayed on the display device of the monitoring system; after rubber layers are coated outside the measurement lines, the lubricating oil pipes and the cables, they pass through the cover 12 and the cabin body 11, or a conversion joint is provided on the cover 12 and the cabin body 11 to reduce air leakage.

[0053] The above are only the preferred embodiments of the present invention and are not used to limit the present invention. For those skilled in the art, the present invention can have various changes and modifications. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A test system for conducting ground and high-altitude tests, characterized in that, Including: A silencing tower (1) and a test workshop (2) arranged on the ground, and an intake air circuit (7), a regulating circuit (8), a test circuit (9), a ground exhaust circuit (15) and a vacuum exhaust circuit (16) arranged in the test workshop (2). Switches for controlling the on / off of the circuits are respectively provided in the regulating circuit (8), the test circuit (9), the ground exhaust circuit (15) and the vacuum exhaust circuit (16); The intake end of the intake air circuit (7) is connected to a gas supply device for supplying test gas; The regulating circuit (8) and the test circuit (9) are arranged in parallel, and the intake ends of both are respectively communicated with the exhaust end of the intake air circuit (7). An air turbine starter to be tested is connected in the test circuit (9), and a vacuum test chamber (3) is slidably arranged to cover the air turbine starter to form a vacuum test environment; The ground exhaust circuit (15) and the vacuum exhaust circuit (16) are arranged in parallel, and the intake ends of both are respectively connected to the exhaust ends of the regulating circuit (8) and the test circuit (9). The exhaust ends of both the ground exhaust circuit (15) and the vacuum exhaust circuit (16) extend out of the test workshop (2) and are then connected to the silencing tower (1). The vacuum exhaust circuit (16) is used to adjust the exhaust pressure of the vacuum test chamber (3); The regulating circuit (8) includes a regulating pipe (81), an exhaust valve (82) and a third regulating valve (83) which are successively connected in the regulating pipe (81) along the gas flow direction. The intake end of the regulating pipe (81) is connected to the exhaust end of the intake air circuit (7). The test circuit (9) includes an intake pipe assembly, an output connecting pipe (91), and an intake valve (92) connected in the intake pipe assembly. The intake end of the intake pipe assembly is connected to the exhaust end of the intake air circuit (7), and its opposite exhaust end is connected to the air turbine starter. The two ends of the output connecting pipe (91) are respectively connected to the exhaust end of the vacuum test chamber (3) and the regulating pipe (81), and the output connecting pipe (91) is also connected to the intake end of the vacuum exhaust circuit (16).

2. The test system for conducting ground and high-altitude tests according to claim 1, wherein The intake air circuit (7) includes a gas input pipe (71) for transporting test gas, a regulating branch pipe (72), a gas supply valve (73), a quick shut-off valve (74), a flow meter (75), a first regulating valve (76), an electric heater (77), and a second regulating valve (78) which are successively connected in the gas input pipe (71) along the gas input direction; The intake end of the gas input pipe (71) is connected to the gas supply device, and its opposite exhaust end is respectively connected to the intake ends of the regulating circuit (8) and the test circuit (9); The intake end of the regulating branch pipe (72) is connected to the gas input pipe (71) between the gas supply valve (73) and the quick shut-off valve (74), and its opposite exhaust end extends out of the test workshop (2) and is then connected to the silencing tower (1).

3. The test system for conducting ground and high-altitude tests according to claim 1, wherein The ground exhaust circuit (15) includes a ground exhaust pipe (151), and a first switching valve (152) connected in the ground exhaust pipe (151); The air inlet end of the ground exhaust pipe (151) is connected to the output connecting pipe (91), and the opposite exhaust end thereof extends out of the test plant (2) and is connected to the muffler tower (1).

4. The test system for conducting ground and high-altitude tests according to claim 1, characterized in that: The vacuum exhaust circuit (16) comprises a vacuum exhaust pipe (161), and a second switch valve (162), a heat exchanger (163), and a vacuum pump (164) which are sequentially connected to the vacuum exhaust pipe (161) along a gas exhaust direction; The air inlet end of the vacuum exhaust pipe (161) is connected to the output connecting pipe (91), and the exhaust end opposite thereto extends out of the test plant (2) and is connected to the muffler tower (1).

5. The test system for conducting ground and high-altitude tests according to claim 1, characterized in that: The vacuum test chamber (3) comprises a hollow chamber (10) for forming a vacuum test environment, an air turbine starter (20) is fixedly installed in the hollow chamber (10), and the hollow chamber (10) is also connected to a vacuum and air pressure adjustment system for evacuating the hollow chamber (10) and adjusting the vacuum pressure in the hollow chamber (10); A hatch opening (101) penetrating the wall of the hollow cabin (10) is provided, and an air intake pipeline assembly (40) is sealed and installed in the hatch opening (101). The air intake end of the air intake pipeline assembly (40) is connected to the exhaust end of the air intake circuit (7), and the exhaust end opposite thereto is connected to the air intake casing of the air turbine starter (20) in the hollow cabin (10); The air intake pipeline assembly (40) is used to supply the test gas supplied by the air supply device to the air turbine starter (20), and at the same time, the thermal stress on the air intake pipeline is reduced through its own structural setting to avoid damage to the air turbine starter (20).

6. The test system for conducting ground and high-altitude tests according to claim 5, characterized in that: The air intake pipeline assembly (40) comprises a bellows (41) which is arranged to be telescopic in the axial direction to absorb thermal expansion, and an air intake pipeline (42) for conveying test gas; One end of the bellows (41) is fixed to the hollow chamber (10) at the periphery of the hatch opening (101), and the other end thereof is fixedly connected to the air intake pipeline (42); The intake end of the intake pipeline (42) is connected to the intake circuit (7), and the exhaust end opposite thereto is axially penetrated through a bellows (41) and a hatch (101) and then connected to an intake casing of an air turbine starter (20).

7. The test system for conducting ground and high-altitude tests according to claim 6, characterized in that: The bellows (41) comprises a bellows body which is telescopically arranged along the axial direction, and flange connection plates connected to opposite ends of the bellows body; The air intake pipeline (42) comprises a matching flange (421) that is fixedly matched with the flange connection plate at the cantilever end of the bellows body, and an air intake pipe (422) for conveying the test gas. The air intake pipe (422) is axially penetrated by the matching flange (421) and the bellows (41), and is detachably fixed to the matching flange (421).

8. The test system for conducting ground and high-altitude tests according to claim 5, characterized in that: The hollow cabin (10) includes a cabin body (11) that is hollowly arranged to form a vacuum test environment, and a cover (12) for installing an air turbine starter (20); The cabin body (11) is slidably supported on the guide rail platform (50), and the first end of the cabin body (11) is open, and a through-cabin opening (101) is provided at the opposite second end; The cover (12) is fixedly supported on the installation platform of the test bench or on the ground, and is used to be connected to the open end of the cabin body (11) to close the cabin body (11).

9. The test system for carrying out ground and high-altitude tests according to claim 8, characterized in that, The vacuum test cabin (3) further includes a cold blowing pipeline (60) connected to the cover (12), and the cold blowing pipeline (60) is used to blow cooling gas to the air turbine starter (20) to reduce the body temperature of the air turbine starter (20), thereby shortening the time interval between two starts.

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