Multifunctional air intake device for high-altitude environmental testing of turboprop engines

Abstract

The present invention relates to the technical field of engine testing, and discloses a multifunctional air intake device for high-altitude environmental testing of a turboprop engine, which is suitable for use with an air supply system, a turboprop engine, and an exhaust air extraction system, and comprises: an air transmission pipeline having a first interface and a second interface, the first interface being connected to the air supply system; one end of a pipeline adapter assembly being connected to the second interface; the other end being connected to the air intake of the turboprop engine; and the exhaust of the turboprop engine being connected to the exhaust air extraction system. The present invention can simulate atmospheric environments of different temperatures, different altitudes, and different Mach numbers by selecting different pipeline adapter assemblies, so as to fully test the overall performance of the turboprop engine under environmental conditions of different temperatures, different altitudes, and different Mach numbers and the influence of the turboprop engine air intake structure on the internal flow of the engine.

Description

Technical Field

[0001] The invention relates to the technical field of engine testing, and in particular to a multifunctional air intake device for high-altitude environmental testing of a turboprop engine. Background Art

[0002] In order to better understand the working conditions and performance characteristics of turboprop engines in high-altitude environments, high-altitude simulation test equipment is usually set up on the ground to test the performance of turboprop engines in high-altitude environments.

[0003] Since the current high-altitude simulation test devices can usually only carry out one type of test project, the direct-connected high-altitude simulation test device can only simulate and study the internal flow of the turboprop engine, and assess the steady-state and transient working performance of the turboprop engine. The overflow-type high-altitude simulation test device can not only simulate and study the internal flow of the engine, but also simulate and study the influence of the external flow of the turboprop engine on the operation of the turboprop engine. For example, the overflow-type high-altitude test with the engine inlet installed can also study the influence of the engine inlet structure on the intake and working performance of the turboprop engine. Therefore, if you want to more comprehensively test the performance of the turboprop engine in a high-altitude environment, you usually need to place the turboprop engine in different high-altitude simulation test devices in turn. In this way, not only the initial investment cost is greatly increased, but also the test cycle is extended. Summary of the invention

[0004] In view of this, the present invention provides a multifunctional air intake device for high-altitude environmental testing of turboprop engines to solve the problems of high initial investment cost and long test cycle for high-altitude environmental testing of turboprop engines.

[0005] The present invention provides a multifunctional air intake device for high-altitude environmental testing of a turboprop engine, which is suitable for use with an air supply system, a turboprop engine and an exhaust air extraction system, and comprises:

[0006] A gas pipeline having a first interface and a second interface, wherein the first interface is connected to a gas supply system;

[0007] A pipeline adapter assembly, one end of which is connected to the second interface; the other end of which is connected to the air inlet of the turboprop engine; and the exhaust port of the turboprop engine is connected to the exhaust extraction system.

[0008] Beneficial effects: The present invention can simulate atmospheric environmental conditions of different temperatures (e.g., any temperature in the range of -54 to 71°C), different altitudes (e.g., any altitude in the range of 0 to 8000m), and different Mach numbers (e.g., any value in the range of 0 to 0.7 Mach numbers) by selecting different pipeline adapter components and combining the air supply system with the exhaust air extraction system, so as to fully test the overall performance of the turboprop engine under environmental conditions of different temperatures, different altitudes, and different Mach numbers and the influence of the turboprop engine inlet duct structure on the internal flow of the engine. In addition, the present invention can realize the rapid adjustment of the engine high-altitude simulation test items and the environmental icing test items by replacing the pipeline adapter components, so that not only the initial investment cost of the test can be reduced, but also the test cycle can be shortened.

[0009] In an optional embodiment, the pipe adapter assembly includes an air inlet duct, one end of which is connected to the air inlet of the turboprop engine, and a gap is left between the other end and the second interface.

[0010] Beneficial effect: By leaving a gap between the air inlet and the second interface, the present invention can allow a portion of the airflow in the air pipeline to flow through the external structure of the turboprop engine, so that an overflow high-altitude simulation test can be performed on the turboprop engine.

[0011] In an optional embodiment, the pipe adapter assembly further includes a mist generating device, which is disposed on the second interface and communicated with the second interface, and a gap is left between the mist generating device and the air inlet duct and the mist generating device is communicated with the air inlet duct.

[0012] Beneficial effect: By arranging a mist generating device between the second interface and the air inlet and leaving a gap between the mist generating device and the air inlet, the present invention can allow a part of the airflow in the gas pipeline to flow through the external structure of the turboprop engine and simulate the icing condition of the turboprop engine in a high-altitude environment, so that the turboprop engine can be subjected to an overflow environment icing test.

[0013] In an optional embodiment, a mesh cover is provided on the air inlet duct.

[0014] Beneficial effect: The present invention prevents impurities in the air from entering the interior of the turboprop engine along with the airflow and causing damage to the structure of the turboprop engine by arranging a mesh cover on the air inlet.

[0015] In an optional embodiment, the pipeline adapter assembly also includes a first air supply duct and a mist generating device, the mist generating device is arranged on the second interface and is connected to the second interface, and the mist generating device is connected to the air inlet of the turboprop engine through the first air supply duct.

[0016] Beneficial effect: The present invention connects the second interface and the first gas duct through a cloud generating device, which can collect all the airflow in the gas duct into the interior of the turboprop engine, simulating the intake icing condition of the turboprop engine in a high-altitude environment, so that a direct-connected intake icing test can be performed on the turboprop engine.

[0017] In an optional embodiment, the pipeline adapter assembly also includes a first gas duct and a second gas duct, the second gas duct is arranged on the second interface and is connected to the second interface, and the second gas duct is connected to the air intake of the turboprop engine through the first gas duct.

[0018] Beneficial effect: The present invention connects the second interface and the first gas duct via the second gas duct, and can collect all the airflow in the gas duct into the interior of the turboprop engine, so that the turboprop engine can be subjected to a direct-connected high-altitude environmental test.

[0019] In an optional embodiment, along the direction from the second interface to the turboprop engine, the size of the air inlet end of the first air duct increases from large to small, and the size of the air outlet end of the first air duct increases from small to large.

[0020] Beneficial effects: The present invention sets the size of the air inlet end of the first air delivery duct from large to small, which is beneficial to collect the airflow flowing out of the second interface on the one hand, avoiding the loss and fluctuation of the airflow; on the other hand, it can rectify the collected airflow, thereby ensuring that the airflow can flow into the air inlet of the turboprop engine evenly and stably. In addition, the present invention sets the size of the air outlet end of the first air delivery duct from small to large, which can improve the dynamic characteristics of the airflow, reduce eddies and turbulence, and make the airflow enter the turboprop engine more smoothly.

[0021] In an optional embodiment, the cross-sectional shape of the air inlet end of the first air duct is circular, and the cross-sectional shape of the air outlet end of the first air duct is a special shape that matches the cross-sectional shape of the air inlet of the turboprop engine.

[0022] Beneficial effects: The present invention sets the cross-sectional shape of the air inlet end of the first air delivery conduit to be circular, which, compared with other shapes, can make the airflow flow more stably on the one hand; on the other hand, it can simplify the manufacturing process and reduce the production cost. In addition, the present invention sets the cross-sectional shape of the air outlet end of the first air delivery conduit to be a special shape, which can guide the flow of airflow, reduce the resistance of airflow flow, and ensure the uniformity of airflow at the engine inlet.

[0023] In an optional embodiment, along the direction from the gas pipeline to the turboprop engine, the size of the first interface increases from small to large.

[0024] Beneficial effect: The present invention sets the size of the first interface from small to large, which is conducive to collecting the airflow flowing out of the intake system and avoiding fluctuations in the airflow; the collected airflow is rectified to ensure that the airflow can flow out from the second interface evenly and stably.

[0025] In an optional embodiment, the pipeline adapter assembly is detachably connected to the gas pipeline or the air inlet of the turboprop engine.

[0026] Beneficial effects: The present invention detachably connects the pipeline adapter assembly to the gas pipeline or the air inlet of the turboprop engine, which can improve the efficiency of installation and disassembly of the pipeline adapter assembly and shorten the test cycle. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0028] Figure 1 A schematic diagram of the structure of a multifunctional air intake device for a high-altitude environmental test of a turboprop engine according to an embodiment of the present invention;

[0029] Figure 2 A schematic structural diagram of another multifunctional air intake device for a turboprop engine high-altitude environmental test according to an embodiment of the present invention;

[0030] Figure 3 The present invention is a schematic structural diagram of another multifunctional air intake device for high-altitude environmental testing of a turboprop engine according to an embodiment of the present invention.

[0031] Description of reference numerals:

[0032] 1. Air supply system; 2. Gas pipeline; 201. First interface; 202. Second interface; 3. Pipeline adapter assembly; 301. Air inlet; 3011. Mesh cover; 302. Cloud generating device; 303. First gas duct; 304. Second gas duct; 4. Turboprop engine; 401. Air inlet; 5. Exhaust extraction system. DETAILED DESCRIPTION

[0033] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present invention.

[0034] In view of the problem that the initial investment cost of high altitude simulation test of an engine is high and the test cycle is long, the present invention provides an engine high altitude environment test device.

[0035] Combine the following Figures 1 to 3 , describing an embodiment of the present invention.

[0036] According to an embodiment of the present invention, a multifunctional air intake device for high-altitude environmental testing of a turboprop engine is provided, which is suitable for use with an air supply system 1, a turboprop engine 4 and an exhaust air extraction system 5, and includes: an air supply pipeline 2 and a pipeline adapter assembly 3.

[0037] Specifically, the gas pipeline 2 has a first interface 201 and a second interface 202, the first interface 201 is connected to the gas supply system 1; one end of the pipeline adapter assembly 3 is connected to the second interface; the other end is connected to the air intake 401 of the turboprop engine 4; the exhaust port of the turboprop engine 4 is connected to the exhaust air extraction system 5.

[0038] The embodiment of the present invention can simulate atmospheric environmental conditions of different temperatures (e.g., any temperature in the range of -54 to 71°C), different altitudes (e.g., any altitude in the range of 0 to 8000m), and different Mach numbers (e.g., any value in the range of 0 to 0.7 Mach numbers) by selecting different pipeline adapter components 3 and combining the air supply system 1 with the exhaust air extraction system 5, so as to fully test the overall performance of the turboprop engine 4 under environmental conditions of different temperatures, different altitudes, and different Mach numbers and the influence of the inlet structure of the turboprop engine 4 on the internal flow of the engine. In addition, the embodiment of the present invention can realize the rapid adjustment of the engine high-altitude simulation test items and the environmental icing test items by replacing the pipeline adapter component 3, so that not only the initial investment cost of the test can be reduced, but also the test cycle can be shortened.

[0039] It should be noted that the air supply system 1 of this embodiment includes a rectifying device (such as a rectifying net, a guide baffle) and a temperature regulating device. Among them, the rectifying device can rectify the outflowing air, so that the air supply system 1 can provide a uniform and stable airflow for the turboprop engine 4, thereby improving the accuracy of the test data. In addition, the temperature of the airflow of the intake system can be changed by the temperature regulating device (-54 to 71°C), simulating the intake temperature of the turboprop engine 4 at different altitudes.

[0040] According to one embodiment of the present invention, the pipeline adapter assembly 3 includes an air inlet 301, one end of which is connected to the air inlet 401 of the turboprop engine 4, and a gap is left between the other end and the second interface 202. By leaving a gap between the air inlet 301 and the second interface 202, the embodiment of the present invention allows a portion of the air flow in the gas pipeline 2 to flow through the external structure of the turboprop engine 4, so that the turboprop engine 4 can be subjected to an overflow high-altitude simulation test.

[0041] It should be noted that in order to ensure that the air entering the air inlet 401 of the engine through the air inlet 301 can meet the basic requirements for the operation of the engine, the air inlet 301 can be set at a position substantially flush with the second interface 202 .

[0042] According to one embodiment of the present invention, the pipeline adapter assembly 3 also includes a mist generating device 302, which is arranged on the second interface 202 and connected to the second interface 202, and a gap is left between the mist generating device 302 and the air inlet 301 and is connected to the air inlet 301.

[0043] The embodiment of the present invention arranges a mist generating device 302 between the second interface 202 and the air inlet 301 and leaves a gap between the mist generating device 302 and the air inlet 301, so that a part of the airflow in the gas pipeline 2 can flow through the external structure of the turboprop engine 4, and at the same time simulates the icing condition of the turboprop engine 4 in a high-altitude environment, so that the turboprop engine 4 can be subjected to an overflow environment icing test.

[0044] According to an embodiment of the present invention, a mesh cover 3011 is provided on the air inlet 301. The embodiment of the present invention prevents impurities in the air from entering the interior of the turboprop engine 4 along with the airflow and causing damage to the structure of the turboprop engine 4 by providing the mesh cover 3011 on the air inlet 301.

[0045] According to an embodiment of the present invention, the pipeline adapter assembly 3 further includes a first gas delivery conduit 303 and a mist generating device 302, the mist generating device 302 is disposed on the second interface 202 and communicated with the second interface 202, and the mist generating device 302 is connected to the air inlet 401 of the turboprop engine 4 through the first gas delivery conduit 303. The embodiment of the present invention connects the second interface 202 and the first gas delivery conduit 303 through the mist generating device 302, and can collect all the airflow in the gas delivery pipeline 2 to the inside of the turboprop engine 4, simulating the intake icing condition of the turboprop engine 4 in a high-altitude environment, so that the turboprop engine 4 can be subjected to a direct-connection intake icing test.

[0046] According to one embodiment of the present invention, the pipeline adapter assembly 3 further includes a first gas delivery conduit 303 and a second gas delivery conduit 304, the second gas delivery conduit 304 is disposed on the second interface 202 and communicated with the second interface 202, and the second gas delivery conduit 304 is connected to the air inlet 401 of the turboprop engine 4 through the first gas delivery conduit 303. The embodiment of the present invention connects the second interface 202 and the first gas delivery conduit 303 through the second gas delivery conduit 304, and can collect all the airflow in the gas delivery pipeline 2 into the interior of the turboprop engine 4, so that the turboprop engine 4 can be subjected to a direct-connection high-altitude environmental test.

[0047] It can be understood that the multifunctional air intake device for high-altitude environmental testing of a turboprop engine 4 of the present invention realizes the integration of various engine high-altitude environmental testing by changing the pipe adapter assembly 3 between the gas pipeline 2 and the air inlet 401 of the turboprop engine 4, thereby alleviating the pressure of severe shortage of engine testing resources and promoting the universal construction of multifunctional high-altitude environmental testing equipment.

[0048] Furthermore, in order to improve the efficiency of installation and disassembly of the pipeline adapter assembly 3 and shorten the test cycle, the two ends of the cloud generating device 302 and the two ends of the second gas duct 304 can be set to the same installation structure. In this way, not only can the disassembly and replacement operations be performed faster, that is, the test items can be switched faster and the time consumed by the test can be shortened, but also parts can be shared to reduce production costs.

[0049] According to one embodiment of the present invention, along the direction from the second interface 202 to the turboprop engine 4, the size of the air inlet end of the first air delivery duct 303 is from large to small, and the size of the air outlet end of the first air delivery duct 303 is from small to large. In the embodiment of the present invention, the size of the air inlet end of the first air delivery duct 303 is set from large to small, which is conducive to collecting the airflow flowing out of the second interface 202 on the one hand, avoiding the loss and fluctuation of the airflow; on the other hand, the collected airflow can be rectified, thereby ensuring that the airflow can flow into the air inlet 401 of the turboprop engine 4 evenly and stably. In addition, in the embodiment of the present invention, the size of the air outlet end of the first air delivery duct 303 is set from small to large, which can improve the dynamic characteristics of the airflow, reduce eddies and turbulence, and make the airflow enter the turboprop engine 4 more smoothly.

[0050] It should be noted that when looking at the outlet end of the first gas duct 303 from the front, the outline is slightly enlarged, but when looking at the outlet end of the first gas duct 303 from a top view, the outline does not change significantly, so the size of the outlet end of the first gas duct 303 changes from small to slightly larger.

[0051] According to one embodiment of the present invention, the cross-sectional shape of the air inlet end of the first air duct 303 is circular, and the cross-sectional shape of the air outlet end of the first air duct 303 is a special shape matching the cross-sectional shape of the air inlet 401 of the turboprop engine 4.

[0052] The embodiment of the present invention sets the cross-sectional shape of the air inlet end of the first air delivery conduit 303 to be circular, which, compared with other shapes, can make the airflow flow more stably on the one hand; on the other hand, it can simplify the manufacturing process and reduce the production cost. In addition, the embodiment of the present invention sets the cross-sectional shape of the air outlet end of the first air delivery conduit 303 to be a special shape, which can guide the flow of airflow, reduce the resistance of airflow flow, and ensure the uniformity of airflow at the engine inlet.

[0053] According to an embodiment of the present invention, the size of the first interface 201 increases from small to large along the direction from the gas pipeline 2 to the turboprop engine 4. The embodiment of the present invention sets the size of the first interface 201 from small to large, which is conducive to collecting the airflow out of the intake system and avoiding airflow fluctuations; the collected airflow is rectified to ensure that the airflow can flow out from the second interface 202 evenly and stably.

[0054] According to one embodiment of the present invention, the pipeline adapter assembly 3 is detachably connected to the gas pipeline 2 or the air inlet 401 of the turboprop engine 4. In the embodiment of the present invention, the pipeline adapter assembly 3 is detachably connected to the gas pipeline 2 or the air inlet 401 of the turboprop engine 4, which can improve the efficiency of installation and removal of the pipeline adapter assembly 3 and shorten the test cycle.

[0055] Although the embodiments of the present invention have been described in conjunction with the accompanying drawings, those skilled in the art may make various modifications and variations without departing from the spirit and scope of the present invention, and such modifications and variations are all within the scope defined by the appended claims.

Claims

1. A multifunctional air intake device for a turboprop engine high-altitude environmental test, suitable for use with an air supply system (1), a turboprop engine (4) and an exhaust air extraction system (5), characterized in that: include: A gas transmission pipeline (2) having a first interface (201) and a second interface (202), wherein the first interface (201) is connected to the gas supply system (1); A pipeline adapter assembly (3), one end of which is connected to the second interface (202); the other end of which is connected to the air inlet (401) of the turboprop engine (4); and the exhaust port of the turboprop engine (4) is connected to the exhaust extraction system (5); The pipeline adapter assembly (3) comprises an air inlet (301) and a mist generating device (302); one end of the air inlet (301) is connected to an air inlet (401) of a turboprop engine (4), and a gap is left between the other end and the second interface (202); the mist generating device (302) is arranged on the second interface (202) and is in communication with the second interface (202); a gap is left between the mist generating device (302) and the air inlet (301), and the mist generating device (302) is in communication with the air inlet (301); The pipeline adapter assembly (3) further comprises a first air delivery conduit (303) and a mist generating device (302); the mist generating device (302) is arranged on the second interface (202) and is in communication with the second interface (202); the mist generating device (302) is connected to an air inlet (401) of the turboprop engine (4) via the first air delivery conduit (303); The pipeline adapter assembly (3) further comprises a first gas delivery conduit (303) and a second gas delivery conduit (304), wherein the second gas delivery conduit (304) is arranged on the second interface (202) and communicates with the second interface (202), and the second gas delivery conduit (304) is connected to the air inlet (401) of the turboprop engine (4) via the first gas delivery conduit (303); The multifunctional air intake device for high-altitude environmental testing of a turboprop engine realizes the integration of multiple engine high-altitude environmental tests by changing the pipeline adapter assembly (3) between the air delivery pipeline (2) and the air intake (401) of the turboprop engine (4).

2. The multifunctional air intake device for high-altitude environmental testing of a turboprop engine according to claim 1, characterized in that: The air inlet (301) is provided with a mesh cover (3011).

3. The multifunctional air intake device for high-altitude environmental testing of a turboprop engine according to claim 1, characterized in that: Along the direction from the second interface (202) to the turboprop engine (4), the size of the air inlet end of the first air delivery duct (303) increases from large to small, and the size of the air outlet end of the first air delivery duct (303) increases from small to large.

4. The multifunctional air intake device for high-altitude environmental testing of a turboprop engine according to claim 1, characterized in that: The cross-sectional shape of the air inlet end of the first air delivery duct (303) is circular, and the cross-sectional shape of the air outlet end of the first air delivery duct (303) is a special shape that matches the cross-sectional shape of the air inlet (401) of the turboprop engine (4).

5. The multifunctional air intake device for high altitude environment test of turboprop engine according to claim 1 or 2, characterized in that: Along the direction from the gas transmission pipeline (2) to the turboprop engine (4), the size of the first interface (201) increases from small to large.

6. The multifunctional air intake device for high-altitude environmental testing of a turboprop engine according to claim 1 or 2, characterized in that: The pipeline adapter assembly (3) is detachably connected to the gas pipeline (2) or the air inlet (401) of the turboprop engine (4).

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