Air Turbine Starter Vacuum Test Chamber

Abstract

The present invention discloses a vacuum test chamber for an air turbine starter, comprising: a hollow chamber, and a vacuum pumping and pressure regulating system is also connected to the hollow chamber for pumping the hollow chamber into a vacuum and regulating the vacuum pressure inside the hollow chamber. A through-hole is formed in the wall surface of the hollow chamber, and an air inlet pipeline assembly is hermetically installed in the through-hole. The air inlet end of the air inlet pipeline assembly is connected to an external gas supply device for supplying high-temperature and high-pressure test gas, and its opposite exhaust end is connected to the air inlet casing of the air turbine starter inside the hollow chamber. The air inlet pipeline assembly is used for supplying the test gas supplied by the gas supply device to the air turbine starter, and at the same time reducing the thermal stress on the air inlet pipeline through its own structural arrangement, so as to avoid damaging the air turbine starter. In the present invention, through the structural arrangement of the air inlet pipeline assembly, the thermal stress on the air inlet pipeline is greatly reduced, and further the deformation amount of the casing of the air turbine starter is reduced, so as to avoid damaging 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 an air turbine starter vacuum test chamber. 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 pressure of the exhaust environment is 1 atmospheric pressure.

[0003] (1) When designing the test chamber of the air turbine starter test bench with reference to the design of the engine whole vehicle test bench, there is a risk of more air leakage and greater thermal stress when the air supply pipeline passes through the test chamber;

[0004] (2) When designing the test chamber of the air turbine starter test bench with reference to the design of the engine whole vehicle test bench, the exhaust after the air turbine starter starts causes a relatively high temperature in the test chamber, which in turn leads to a relatively slow cooling rate of the air turbine starter body, a relatively long time interval between two consecutive starts of the air turbine starter, and affects the test efficiency. Summary of the Invention

[0005] The present invention provides an air turbine starter vacuum test chamber to solve the technical problem of "there is a risk of more air leakage and greater thermal stress when the air supply pipeline passes through the test chamber" existing when designing the test chamber of the air turbine starter test bench with reference to the design of the engine whole vehicle test bench.

[0006] The technical solution adopted by the present invention is as follows:

[0007] An air turbine starter vacuum test chamber includes: a hollow chamber provided in a hollow manner for forming a vacuum test environment, an air turbine starter to be tested is fixedly installed in the hollow chamber, and the hollow chamber is also connected with a vacuum pumping and pressure regulating system for pumping the hollow chamber into a vacuum and regulating the vacuum pressure in the hollow chamber; a through-hole penetrating the wall surface is opened on the wall surface of the hollow chamber, and an air inlet pipeline assembly is hermetically installed in the through-hole. The air inlet end of the air inlet pipeline assembly is connected to an external air supply device for supplying high-temperature and high-pressure test gas, and its opposite exhaust end is connected to the air inlet casing of the air turbine starter in the hollow chamber; the air inlet pipeline assembly is used to supply the test gas supplied by the air supply device into the air turbine starter, and at the same time reduce the thermal stress on the air inlet pipeline through its own structural setting to avoid damage to the air turbine starter.

[0008] Furthermore, the air intake pipe assembly includes a bellows that is axially telescopically arranged to absorb thermal expansion, and an air intake pipe for conveying test gas; one end of the bellows is fixed to a hollow cabin on the outer periphery of the hatch, and the other opposite end is fixedly connected to the air intake pipe; the air intake end of the air intake pipe is connected to the air supply device, and the opposite exhaust end is axially penetrated by the bellows and connected to the air intake casing of the air turbine starter after passing through the hatch.

[0009] Furthermore, the bellows includes a bellows body that is axially telescopically arranged, and flange connecting plates connected to the opposite ends of the bellows body; the air intake pipeline includes a matching flange that is fixed to the flange connecting plate at the cantilever end of the bellows body, and an air intake pipe for conveying test gas, the air intake pipe is axially penetrated by the matching flange and the bellows, and is detachably fixed to the matching flange.

[0010] Furthermore, the matching flange is disc-shaped, with an internal threaded hole penetrating the disc surface at its center, and waist-shaped holes arranged in sequence along the circumferential direction and penetrating the disc surface at its outer periphery, and the waist-shaped holes extend along the circumference; the intake end of the intake pipe is connected to the air supply device, and the opposite exhaust end is connected to the intake casing of the air turbine starter, and an outwardly convex annular threaded boss is provided on the outer circle of the middle part of the intake pipe, and an external thread is processed on the outer circle surface of the threaded boss, and the intake pipe is detachably fixed to the matching flange through a threaded connection between the threaded boss and the internal threaded hole.

[0011] Furthermore, the hollow cabin includes a hollow cabin body for forming a vacuum test environment, and a cover for installing an air turbine starter; the cabin body is slidably supported on a guide rail platform, and the first end of the cabin body is open, and a hatch opening is provided on the opposite second end; the cover is fixedly supported on the mounting platform or the ground of the test bench, and is used to be connected to the open end of the cabin body to close the cabin body.

[0012] Furthermore, the vacuum extraction and air pressure reduction system includes an exhaust port and an air vent arranged through the wall of the cabin, a vacuum extraction device connected to the exhaust port for vacuum extraction, a regulating valve connected to the air vent, and a controller; the vacuum extraction device and the regulating valve are respectively connected to the controller to cooperate with each other to adjust the vacuum pressure in the cabin.

[0013] Furthermore, the air turbine starter vacuum test chamber also includes a cold blow pipeline connected to the cover, and the cold blow pipeline is used to blow cooling air to the air turbine starter to reduce the body temperature of the air turbine starter, thereby shortening the time interval between two starts.

[0014] Furthermore, the cold blow pipeline includes a cold air connecting pipe fixedly arranged in the cover, and a cold air distribution pipe connected to the inner side of the cover; the cold air distribution pipe is located in the cabin and connected to the cold air connecting pipe; the cold air connecting pipe is connected to a cold air supply device for supplying cooling air, or is connected to the atmosphere, and a switch valve for controlling its on and off and a flow regulating valve for adjusting the flow rate are provided in the pipeline of the cold air connecting pipe.

[0015] Further, the cold air distribution pipe is a hollow annular pipe arranged in a ring shape. Air outlet holes for the cooling air to spray outwards are formed on the inner ring surface of the annular pipe, and the air turbine starter is located in the inner hole of the annular pipe; alternatively, the cold air distribution pipe is a cylindrical tube that is hollow and arranged in a cylindrical shape. An annular cavity extending axially and in a ring shape is provided inside the wall surface of the cylindrical tube. The annular cavity is communicated with the cold air connection pipe, and air outlet holes for the cooling air to spray outwards are formed on the inner wall surface of the cylindrical tube, and one end of the air turbine starter in the axial direction is installed in the axial hole of the cylindrical tube.

[0016] Further, through holes for the measurement lines of vibration, temperature and pressure, and the lubricating oil pipe to pass through respectively are further formed on the cover; an observation window for external personnel to observe the situation inside the cabin, and a wire passing hole for the camera cable to pass through are further provided on the cabin body; rubber layers are coated outside the measurement lines, the lubricating oil pipe and the cable.

[0017] The present invention has the following beneficial effects:

[0018] In the present invention, the exhaust gas during the test of the air turbine starter is directly discharged into the hollow cabin, so the thermal expansion amounts between the intake pipe assembly and the air turbine starter, and between the intake pipe assembly and the hollow cabin are different. Relative displacement occurs at the penetration port between the intake pipe assembly and the hollow cabin body. If no corresponding structural design is carried out, the intake pipe assembly with a larger thermal expansion amount will directly act the thermal stress on the cabin body, and the cabin body will react the thermal stress on the intake pipe assembly and the air turbine starter, thereby causing deformation of the casing of the air turbine starter. However, through the structural setting of the intake pipe assembly 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 is reduced to avoid damage to the air turbine starter. Thus, the present invention realizes the ground simulation of the air turbine starter exhausting into a vacuum environment, creates conditions for the air turbine starter to carry out high-altitude tests in the ground state, and at the same time effectively solves the sealing problem at the penetration of the air supply pipe assembly through the hollow cabin and the thermal stress problem caused by different temperatures of the cabin body and the intake pipe assembly.

[0019] In addition to the purposes, features and advantages described above, the present invention has other purposes, features and advantages. The present invention will be further described in detail below with reference to the drawings. Description of the Drawings

[0020] The drawings constituting 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:

[0021] Figure 1 is a schematic diagram of an existing air turbine starter test scheme;

[0022] Figure 2 It is a schematic diagram of the spatial structure of the air turbine starter vacuum test chamber according to a preferred embodiment of the present invention;

[0023] Figure 3 is Figure 2 a top view structural schematic diagram;

[0024] Figure 4 is Figure 2 a sectional front view structural schematic diagram;

[0025] Figure 5 is Figure 2 a schematic diagram of the spatial structure of the cold air distribution pipe in

[0026] Figure 6 is Figure 2 a front view structural schematic diagram of the mating flange in

[0027] Figure 7 is Figure 6 a sectional view along the A-A direction of

[0028] Figure 8 is Figure 2 a front view structural schematic diagram of the intake pipe in

[0029] Figure 9 is Figure 8 a sectional view along the B-B direction of

[0030] Legend Explanation

[0031] 10. Hollow cabin; 101. Through-cabin opening; 102. Thread-passing hole; 11. Cabin body; 12. Cover; 13. Observation window; 20. Air turbine starter; 31. Air extraction port; 32. Ventilation port; 40. Intake pipe 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 air blowing pipeline; 61. Cold air connection pipe; 62. Cold air distribution pipe; 620. Air outlet hole. Specific Embodiments

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

[0033] Refer to Figures 2 - 4, a preferred embodiment of the present invention provides an air turbine starter vacuum test chamber, comprising: a hollow chamber 10 provided in a hollow manner for forming a vacuum test environment, an air turbine starter 20 to be tested is 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 in 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 an external gas supply device for supplying high-temperature and high-pressure test gas, and its opposite exhaust end is connected to the intake casing of the air turbine starter 20 in 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 damaging the air turbine starter 20.

[0034] In the prior art, the air turbine starter is mainly used to drive the combustion engine rotor of the main engine to realize the 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 an air turbine starter vacuum test chamber. 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 in the hollow chamber 10 is controlled by the vacuum pumping and pressure regulating system to realize simulating the exhaust of the air turbine starter to the vacuum environment; during the test, 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.

[0035] 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 between the intake pipe assembly 40 and the cabin body of the hollow cabin 10 at the penetration opening 101. 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 air turbine starter discharging exhaust gas into a vacuum environment, creating conditions for carrying out high-altitude tests on the air turbine starter in the ground state. At the same time, it effectively solves the sealing problem of the supply pipe assembly 40 passing through the hollow cabin and the thermal stress problem caused by different temperatures of the cabin body and the intake pipe assembly.

[0036] Optionally, as Figure 3 and Figure 4 shown, the intake pipe assembly 40 includes a bellows 41 axially telescoped 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 its opposite end is fixedly connected to the intake pipe 42. The intake end of the intake pipe 42 communicates with the gas supply device, and its 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 between the intake pipe 42 and the cabin body at the penetration opening 101. 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. 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.

[0037] In this alternative solution, as Figure 4As shown in the figure, the corrugated pipe 41 includes a corrugated pipe body telescopically arranged along the axial direction, and flange connection discs connected to opposite ends of the corrugated pipe body. The intake pipeline 42 includes a mating flange disc 421 that is fixedly fitted with the flange connection disc at the cantilever end of the corrugated pipe body, and an intake pipe 422 for conveying test gas. The intake pipe 422 axially penetrates through the mating flange disc 421 and the corrugated pipe 41, and is detachably fixed to the mating flange disc 421. In this alternative solution, one end of the metal corrugated pipe 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 disc 421. In the conventional connection of the corrugated pipe, different pipelines are connected to both ends of the corrugated pipe, and the fluid flows through the corrugated pipe. However, the present invention proposes a new connection method, that is, one end of the corrugated pipe 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 disc 421, so that the intake pipe 422 can pass through the corrugated pipe 41, and the fluid flows in the intake pipeline without flowing through the corrugated pipe 41, improving the stability of fluid flow and ensuring the uniformity of the inlet air of the air turbine starter 20.

[0038] In a specific embodiment of this alternative solution, as Figure 6 and Figure 7 shown, the mating flange disc 421 is in a disc shape, and a through-hole internal thread hole 4211 is machined at its center, and waist-shaped holes 4212 that are arranged in sequence along the circumferential direction and penetrate the disc surface are machined on its outer circumference, and the waist-shaped holes 4212 extend along the circumferential line. The waist-shaped holes 4212 facilitate the connection of the mating flange disc 421 and the corrugated pipe 41 by bolts. As Figure 8 and Figure 9 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. An externally convex annular thread boss 4220 is provided on the outer circumference of the middle part of the intake pipe 422, and an external thread is machined on the outer circumferential surface of the thread boss 4220. The intake pipe 422 is detachably fixed to the mating flange disc 421 through the threaded connection between the thread boss 4220 and the internal thread hole 4211. In the present invention, this kind of mating connection method between the intake pipe 422 and the mating flange disc 421 realizes the reduction of the thermal stress of the intake pipeline and the reduction of air leakage, and at the same time effectively avoids the direct connection of the metal corrugated pipe into the intake pipeline, improving the stability and uniformity of the intake of the air turbine starter.

[0039] Optionally, as Figure 4As 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 penetration port 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 to 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 arrangement 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 moved and connected and fixed to the cover 12.

[0040] Optionally, as Figure 4 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 pumping device communicating with the air extraction port 31 for pumping vacuum, a regulating valve communicating with the air vent 32, and a controller. The vacuum pumping device and the regulating valve are respectively connected to the controller to cooperate to regulate the vacuum pressure inside the chamber body 11. For example, when the pressure inside 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 inside 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 pumping device is provided with a pressure detector for detecting the pressure inside the chamber body 11. The pressure detector sends the pressure value inside the chamber body 11 to the controller in real time, and the controller adjusts the opening of the regulating valve or the pumping force of the vacuum pumping device according to the difference between the received pressure value and the set pressure value.

[0041] Optionally, as Figure 4 shown, the air turbine starter vacuum test chamber further includes a cold blowing pipeline 60 connected to the cover 12. The cold blowing pipeline 60 is used to blow cooling air 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 ends, and thus improving the test efficiency.

[0042] In this optional solution, as Figure 4As 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 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.

[0043] In the first specific embodiment of this alternative solution, as Figure 5 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 formed 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 barrel arranged in a hollow and cylindrical shape, and an annular cavity extending axially and in a ring shape is arranged inside the wall surface of the cylindrical barrel. 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 formed on the inner wall surface of the cylindrical barrel, and one end of the air turbine starter 20 in the axial direction is installed in the axial hole of the cylindrical barrel.

[0044] Optionally, as Figure 2 and Figure 4 shown, through holes for the measurement lines of vibration, temperature and pressure, and lubricating oil pipes to pass through respectively are further formed 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, lubricating oil pipes and cables. In this alternative solution, the observation window 13 is convenient for 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, lubricating oil pipes and cables, they pass through the cover 12 and the cabin body 11, or a conversion joint is arranged on the cover 12 and the cabin body 11 to reduce air leakage.

[0045] 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, various changes and modifications can be made to the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. An air turbine starter vacuum test chamber, characterized in that Comprising: A hollow chamber (10) which is hollowly arranged for forming a vacuum test environment, and an air turbine starter (20) to be tested is fixedly installed in the hollow chamber (10). The hollow chamber (10) is also connected with 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-hull opening (101) penetrating the wall surface is formed on the wall surface of the hollow chamber (10), and an intake pipeline assembly (40) is hermetically installed in the through-hull opening (101). The intake pipeline assembly (40) includes a corrugated pipe (41) which is axially telescopic to absorb thermal expansion, and an intake pipeline (42) for conveying test gas; one end of the corrugated pipe (41) is fixed to the hollow chamber (10) outside the periphery of the through-hull opening (101), and the opposite end thereof is fixedly connected to the intake pipeline (42); the intake end of the intake pipeline (42) is communicated with an externally provided gas supply device for supplying high-temperature and high-pressure test gas, and the opposite exhaust end thereof axially penetrates through the corrugated pipe (41) and the through-hull opening (101) and then is communicated with the intake casing of the air turbine starter (20) inside the hollow chamber (10); The intake pipeline assembly (40) is used for supplying the test gas supplied by the gas supply device into the air turbine starter (20), and at the same time reducing the thermal stress on the intake pipeline through its own structural arrangement to avoid damaging the air turbine starter (20); The corrugated pipe (41) includes a corrugated pipe body which is axially telescopic, and flange connection discs connected to opposite ends of the corrugated pipe body; the intake pipeline (42) includes a mating flange disc (421) which is fixedly fitted with the flange connection disc at the cantilever end of the corrugated pipe body, and an intake pipe (422) for conveying test gas. The intake pipe (422) axially penetrates through the mating flange disc (421) and the corrugated pipe (41), and is detachably fixed to the mating flange disc (421).

2. The air turbine starter vacuum test chamber according to claim 1, wherein The mating flange disc (421) is disc-shaped, a through-hole internal thread hole (4211) is machined at the center of the disc surface, waist-shaped holes (4212) which are sequentially arranged along the circumferential direction and penetrate the disc surface are machined on the outer periphery thereof, and the waist-shaped holes (4212) extend along the circumferential line; The intake end of the intake pipe (422) is communicated with the gas supply device, the opposite exhaust end thereof is communicated with the intake casing of the air turbine starter (20), and an externally convex annular thread boss (4220) is arranged on the outer circle of the middle part of the intake pipe (422). External threads are machined on the outer circle surface of the thread boss (4220), and the intake pipe (422) is detachably fixed to the mating flange disc (421) through the threaded connection between the thread boss (4220) and the internal thread hole (4211).

3. The air turbine starter vacuum test chamber according to claim 1, wherein The hollow chamber (10) includes a chamber body (11) which is hollowly arranged for forming a vacuum test environment, and a cover (12) for installing the air turbine starter (20); The chamber body (11) is slidably supported on a guide rail platform (50), and the first end of the chamber body (11) is open, and a through-hull opening (101) is arranged at the opposite second end; The cover (12) is fixedly supported on the installation platform or the ground of the test stand and is used to connect with the open end of the cabin body (11) to seal the cabin body (11).

4. The air turbine starter vacuum test chamber according to claim 3, wherein The vacuum pumping and pressure regulating system includes an air extraction port (31) and an air vent (32) arranged through the wall of the cabin body (11), a vacuum pumping device connected to the air extraction port (31) for pumping vacuum, a regulating valve connected to the air vent (32), and a controller; The vacuum pumping device and the regulating valve are respectively connected to the controller to cooperate to adjust the vacuum pressure in the cabin body (11).

5. The air turbine starter vacuum test chamber according to claim 3, wherein The air turbine starter vacuum test chamber further includes a cold blowing pipeline (60) connected to the cover (12). The cold blowing pipeline (60) is used to blow cooling air 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.

6. The air turbine starter vacuum test chamber according to claim 5, wherein The cold blowing pipeline (60) includes a cold air connecting 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 connected to the cold air connecting pipe (61); The cold air connecting pipe (61) is connected to a cold air supply device for supplying cooling air or is connected to 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 connecting pipe (61).

7. The air turbine starter vacuum test chamber according to claim 6, wherein The cold air distribution pipe (62) is a hollow and annular pipe, and air outlet holes (620) for the cooling air to spray outwards are provided on the inner ring surface of the annular pipe. The air turbine starter (20) is located in the inner hole of the annular pipe; or The cold air distribution pipe (62) is a hollow and cylindrical column. An annular cavity extending axially and annularly is provided in the wall surface of the cylindrical column. The annular cavity is connected to the cold air connecting pipe (61), and air outlet holes (620) for the cooling air to spray outwards are provided on the inner wall surface of the cylindrical column. One end of the air turbine starter (20) in the axial direction is installed in the axial hole of the cylindrical column.

8. The air turbine starter vacuum test chamber according to claim 3, wherein Through holes for the measurement lines of vibration, temperature and pressure, and the lubricating oil pipe to pass through are further provided 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 pipe and the cable.

Images