High-speed lateral gas jet test device and test method

Abstract

The present application belongs to the technical field of high-speed wind tunnel test, and discloses a high-speed transverse gas jet test device and test method. The test device comprises a test model located in the test section of a high-speed wind tunnel, the inner cavity of the test model is sequentially fixed with a balance and a support rod from front to back, the rear section of the balance is sleeved with a heat insulation sleeve, a gas generator is installed on the support rod, and the rear section of the support rod is connected with a high-speed wind tunnel support mechanism. The test device further comprises a fuel storage tank and an air storage tank which are placed outside the high-speed wind tunnel and provide fuel and air for the gas generator, and an ignition controller of the gas generator. The test method establishes a safety interlocking test timing, ensures the reliability and safety of the high-speed transverse gas jet test, provides a stable time of the hot jet of 10s order, a stable chamber pressure, non-toxic and harmless gas, can simulate the specific impulse, temperature, specific heat ratio and secondary combustion effect of the real high-speed aircraft jet gas, and has engineering practical value.

Description

Technical Field

[0001] This invention belongs to the field of high-speed wind tunnel testing technology, specifically relating to a high-speed transverse gas jet test device and test method. Background Technology

[0002] High maneuverability and rapid response capability are important indicators for high-speed aircraft. High-speed aircraft use jet propulsion or a combination of jet propulsion and aerodynamic rudders for maneuver control during tracking, homing, and terminal maneuvers. This allows them to engage targets with high maneuverability and perform large maneuvers at low speeds and high altitudes.

[0003] The lateral jet interference effect of high-speed aircraft has a significant impact on their aerodynamic characteristics, requiring in-depth research through ground-based wind tunnel testing to provide a basis for the overall design and control system design of high-speed aircraft. Lateral jet interference wind tunnel tests mainly employ either cold or hot jets. Cold jets simulate the exhaust flow of a real high-speed aircraft by ejecting cold air. Cold jets offer good repeatability, are non-toxic, and relatively inexpensive, and can achieve satisfactory results while maintaining consistent jet pressure ratio and initial expansion angle, making them widely used in wind tunnel testing. However, cold jets struggle to simulate the specific impulse, temperature, specific heat ratio, and secondary combustion effects of exhaust gases from real high-speed aircraft. Therefore, using hot jets for lateral jet testing of high-speed aircraft is gradually becoming a development trend. Hot jets use the exhaust flow generated by a micro solid rocket motor as the test jet medium to replicate the working state of a real engine. However, hot jets suffer from problems such as short engine stabilization time (on the order of 100 ms), unstable chamber pressure, and toxic exhaust gases.

[0004] In order to simulate the lateral jet interference effect of high-speed aircraft as realistically as possible while ensuring experimental safety, it is urgent to develop a high-speed lateral gas jet test device and test method. Summary of the Invention

[0005] One technical problem to be solved by the present invention is to provide a high-speed transverse gas jet test device, and another technical problem to be solved is to provide a high-speed transverse gas jet test method, so as to overcome the defects of the prior art.

[0006] The high-speed transverse gas jet test device of the present invention includes a test model located in the high-speed wind tunnel test section. The inner cavity of the test model is fixed with a balance and a support rod from front to back. The rear section of the balance is fitted with a heat insulation sleeve. A gas generator is installed on the support rod. The rear section of the support rod is connected to the high-speed wind tunnel support mechanism. It also includes a fuel tank and an air tank placed outside the high-speed wind tunnel to provide fuel for the gas generator, as well as an ignition controller for the gas generator, which controls ignition through an ignition timing controller.

[0007] Furthermore, the main body of the gas generator is a ring, and the ring is provided with two annular cavities, the inner annular cavity being the first part of the cooling water flow channel; a nozzle is provided on the ring at a position corresponding to the jet outlet of the transverse jet, the nozzle is connected to the outer annular cavity, the central axis of the nozzle coincides with the corresponding diameter of the ring, and a second part of the cooling water flow channel is provided on the nozzle; the relative arrangement of the injector and the nozzle; The main body of the injector is a tube; the inner cavity of the front section of the tube is the combustion chamber, which is connected to the outer annular cavity. A third cooling water channel is provided around the combustion chamber. The combustion chamber is connected to the ignition nozzle, which is externally connected to an ignition timing controller. A nozzle is provided on the central axis of the rear section of the tube. An air manifold is provided on the tube corresponding to the middle section of the nozzle. The air manifold is connected to an air connector, which is externally connected to an air tank. A fuel manifold is provided on the tube corresponding to the rear section of the nozzle. The fuel manifold is connected to a fuel connector, which is externally connected to a fuel tank. Each part of the cooling water flow channel is connected to the corresponding cooling water connector, and the cooling water connector is connected to high-pressure cooling water; the pressure range of the high-pressure cooling water is 2.0Mpa~5.0Mpa.

[0008] Furthermore, the fuel storage tank and gas storage tank are part of a fuel supply system, which also includes a shut-off valve and an orifice plate. The gas storage tank increases the air pressure, and the shut-off valve and orifice plate control the fuel flow. The fuel stored in the fuel storage tank is alcohol.

[0009] Furthermore, the ignition timing controller ignites the fuel and air mixture by controlling the fuel injection time and ignition time, generating high-temperature and high-pressure gas.

[0010] Furthermore, all components of the gas generator except the nozzle are made of GH3625 high-temperature alloy material, integrally formed by 3D printing additive manufacturing, and then the mating surfaces are machined. In addition, according to the combustion parameter requirements, corresponding cooling water connectors are set at different positions of the cooling water flow channel. Combustion parameters include the specific impulse, temperature, specific heat ratio, and secondary combustion effect of the jet gas.

[0011] Furthermore, the nozzle of the gas generator is installed via a thread.

[0012] Furthermore, the nozzle is a Laval nozzle.

[0013] Furthermore, the connecting pipe for the fuel connector is a DN4mm pipe, and the connecting pipe for the air connector is a DN10mm pipe.

[0014] The high-speed transverse gas jet test method of the present invention includes the following steps: S10. Start the high-speed wind tunnel. The wind tunnel nozzles eject high-speed airflow, forming a stable high-speed flow field in the high-speed wind tunnel test section. S20. Open the water cooling system of the high-speed wind tunnel and inject cooling water into each cooling water channel through the corresponding cooling water connector to avoid structural ablation during the high-speed transverse gas jet test. S30. The ignition timing controller opens the valves in sequence, and the fuel supply system supplies air to the gas generator. After 0.5 seconds, fuel is supplied. After the fuel is sprayed out through the nozzle, it mixes with air in the injector and is then injected into the combustion chamber. It is ignited by the ignition nozzle in the combustion chamber. After successful ignition, the ignition nozzle is closed. S40. The gas generator enters the designed working state. Air and fuel are uniformly mixed and stably burned in the combustion chamber to form high-temperature and high-pressure gas. After being accelerated by the nozzle, the high-temperature and high-speed gas is ejected to obtain a transverse hot jet, and a transverse thrust is formed through the thrust surface. S50. After the balance test is completed, the gas generator is shut off, the fuel supply is turned off, the transverse hot jet is extinguished, the air supply is continued for 5 seconds, and then the air supply is turned off to purge the fuel pipeline and the combustion chamber cavity of residual fuel. After 60.2 seconds, the water cooling system of the high-speed wind tunnel is shut down; S70. High-speed wind tunnel shutdown.

[0015] The high-speed transverse gas jet test device of the present invention places a miniaturized gas generator inside the test model. Due to the large number of internal components and complex pipelines in the test model, the main body of the gas generator is a ring, and the main body of the injector is a pipe. Fuel, air and cooling water pipelines are designed inside the ring and the pipe, and the corresponding external fuel, air and cooling water pipelines are all enclosed inside the test model. At the same time, a space is reserved in the center of the ring for the support rod to pass through, so that the front part of the support rod can be connected to the balance and the rear part of the support rod can be connected to the high-speed wind tunnel support mechanism.

[0016] The high-speed transverse gas jet test method of this invention controls the fuel-air ratio through an ignition timing controller. Simultaneously, for reliability and safety, it is essential to ensure that air enters the combustion chamber first, and that the fuel is ignited by the ignition nozzle simultaneously with its injection into the combustion chamber. To prevent residual fuel in the combustion chamber from causing potential deflagration in subsequent tests, residual fuel must be removed after the thermal jetting process. Furthermore, safety interlocks must be incorporated into the ignition timing during the high-speed transverse gas jet test.

[0017] The high-speed transverse gas jet test device and test method of the present invention provide a thermal jet stabilization time on the order of 10 seconds, stable stagnation chamber pressure, and non-toxic and harmless gas. Under the premise of ensuring test safety, it can realize the simulation of the specific impulse, temperature, specific heat ratio and secondary combustion effect of the real high-speed aircraft jet gas in a high-speed wind tunnel for a long time, which has practical engineering value. Attached Figure Description

[0018] The accompanying drawings are for illustrative purposes only and are not intended to limit the scope of this disclosure. It is obvious that the drawings described below are merely some embodiments of this disclosure, and those skilled in the art can obtain other drawings based on these drawings without any inventive effort. Furthermore, the same reference numerals denote the same parts throughout the drawings.

[0019] Figure 1 This is a schematic diagram of the high-speed transverse gas jet test device of the present invention; Figure 2 This is an assembly schematic diagram of the high-speed transverse gas jet test device of the present invention; Figure 3 This is a schematic diagram of the gas generator in the high-speed transverse gas jet test device of the present invention; Figure 4 This is a cross-sectional view of the gas generator in the high-speed transverse gas jet test device of the present invention; Figure 5 This is a timing diagram of the test flow of the high-speed transverse gas jet test method of the present invention.

[0020] In the diagram: 1. Wind tunnel nozzle; 2. Test model; 3. Balance; 4. Gas generator; 5. Heat insulation jacket; 6. Fuel storage tank; 7. Ignition controller; 8. Gas storage tank; 9. Support rod; 401. Ignition nozzle; 402. Injector; 403. Cooling water connector; 404. Air connector; 405. Fuel connector; 406. Nozzle; 407. Combustion chamber; 408. Cooling water flow channel; 409. Air manifold; 410. Nozzle; 411. Fuel manifold. Detailed Implementation

[0021] The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0022] Example: Figure 1 , Figure 2 As shown, the high-speed transverse gas jet test device of this embodiment includes a test model 2 located in the high-speed wind tunnel test section. The inner cavity of the test model 2 is fixed with a balance 3 and a support rod 10 from front to back. The rear section of the balance 3 is fitted with a heat insulation sleeve 5. A gas generator 4 is installed on the support rod 10. The rear section of the support rod 10 is connected to the high-speed wind tunnel support mechanism. It also includes a fuel tank 6 placed outside the high-speed wind tunnel to provide fuel for the gas generator 4 and an air tank 8 to provide air, as well as an ignition controller 7 for the gas generator 4, which achieves ignition control through an ignition timing controller 9.

[0023] Furthermore, such as Figure 3 , Figure 4 As shown, the main body of the gas generator 4 is an annular body, and the annular body is provided with two annular cavities, inner and outer. The inner annular cavity is the first part of the cooling water channel 408. A nozzle 406 is provided on the annular body at a position corresponding to the outlet of the transverse jet. The nozzle 406 is connected to the outer annular cavity. The central axis of the nozzle 406 coincides with the corresponding diameter of the annular body. A second part of the cooling water channel 408 is provided on the nozzle 406. The injector 402 is arranged opposite to the nozzle 406. The main body of the injector 402 is a tube; the inner cavity of the front section of the tube is a combustion chamber 407, which is connected to the outer annular cavity. A third cooling water channel 408 is provided around the combustion chamber 407. The combustion chamber 407 is connected to an ignition nozzle 401, which is externally connected to an ignition timing controller 9. A nozzle 410 is provided on the central axis of the rear section of the tube. An air collection chamber 409 is provided on the tube corresponding to the middle section of the nozzle 410. The air collection chamber 409 is connected to an air connector 404, which is externally connected to an air tank 8. A fuel collection chamber 411 is provided on the tube corresponding to the rear section of the nozzle 410. The fuel collection chamber 411 is connected to a fuel connector 405, which is externally connected to a fuel tank 6. Each cooling water flow channel 408 is connected to a corresponding cooling water connector 403, and the cooling water connector 403 is connected to high-pressure cooling water; the pressure range of the high-pressure cooling water is 2.0Mpa~5.0Mpa.

[0024] Furthermore, the fuel storage tank 6 and the gas storage tank 8 are part of a fuel supply system, which also includes a shut-off valve and an orifice plate. The gas storage tank 8 increases the air pressure, and the shut-off valve and orifice plate control the fuel flow. The fuel stored in the fuel storage tank 6 is alcohol.

[0025] Furthermore, the ignition timing controller 9 ignites the fuel and air mixture by controlling the fuel injection time and ignition time, generating high-temperature and high-pressure gas.

[0026] Furthermore, all components of the gas generator 4 except for the nozzle 410 are made of GH3625 high-temperature alloy material, integrally formed by 3D printing additive manufacturing, and then the mating surfaces are machined. In addition, according to the combustion parameter requirements, corresponding cooling water connectors 403 are set at different positions of the cooling water flow channel 408. Combustion parameters include the specific impulse, temperature, specific heat ratio, and secondary combustion effect of the jet gas.

[0027] Furthermore, the nozzle 410 of the gas generator 4 is installed by thread.

[0028] Furthermore, the nozzle 406 is a Laval nozzle.

[0029] Furthermore, the connecting pipe of the fuel connector 405 is a DN4mm pipe, and the connecting pipe of the air connector 404 is a DN10mm pipe.

[0030] like Figure 5 As shown, the high-speed transverse gas jet test method of this embodiment includes the following steps: S10. Start the high-speed wind tunnel. The wind tunnel nozzle 1 ejects high-speed airflow, forming a stable high-speed flow field in the high-speed wind tunnel test section. S20. Open the water cooling system of the high-speed wind tunnel and inject cooling water into each cooling water channel 408 through the corresponding cooling water connector 403 to avoid structural ablation during the high-speed transverse gas jet test. S30. The ignition timing controller 9 opens the valve according to the timing sequence, and the fuel supply system supplies air to the gas generator 4. After 0.5s, fuel is supplied. After the fuel is sprayed out through the nozzle 410, it mixes with air in the injector 402 and is then sprayed into the combustion chamber cavity 407. It is ignited by the ignition nozzle 401 in the combustion chamber cavity 407. After successful ignition, the ignition nozzle 401 is closed. S40. The gas generator 4 enters the design working state. Air and fuel are uniformly mixed and stably burned in the combustion chamber 407 to form high-temperature and high-pressure gas. After being accelerated by the nozzle 406, the high-temperature and high-speed gas is ejected to obtain a transverse hot jet, and a transverse thrust is formed through the thrust surface. S50. After the balance 3 test is completed, the gas generator 4 is shut off, the fuel supply is turned off, the transverse hot jet is extinguished, the air supply continues for 5 seconds, and then the air supply is turned off to purge the fuel pipeline and the combustion chamber cavity 407 of the residual fuel. After 60.2 seconds, the water cooling system of the high-speed wind tunnel is shut down; S70. High-speed wind tunnel shutdown.

[0031] Although the embodiments of the present invention have been disclosed above, they are not limited to the applications listed in the specification and embodiments. For those skilled in the art, all features disclosed in the present invention, or all steps in all methods or processes disclosed, except for mutually exclusive features and / or steps, can be combined in any way without departing from the principles of the present invention. The present invention is not limited to the specific details and illustrations shown and described herein.

Claims

1. A high-speed transverse gas jet test device, characterized in that, The high-speed transverse gas jet test device includes a test model (2) located in the high-speed wind tunnel test section. The inner cavity of the test model (2) is fixed with a balance (3) and a support rod (10) from front to back. The rear section of the balance (3) is fitted with a heat insulation sleeve (5). A gas generator (4) is installed on the support rod (10). The rear section of the support rod (10) is connected to the high-speed wind tunnel support mechanism. It also includes a fuel tank (6) placed outside the high-speed wind tunnel to provide fuel for the gas generator (4) and an air tank (8) to provide air, as well as an ignition controller (7) for the gas generator (4), which implements ignition control through an ignition timing controller (9).

2. The high-speed transverse gas jet test device according to claim 1, characterized in that, The main body of the gas generator (4) is a ring body, and there are two annular cavities inside the ring body. The inner annular cavity is the first part of the cooling water channel (408). A nozzle (406) is provided on the ring body at the position corresponding to the outlet of the transverse jet. The nozzle (406) is connected to the outer annular cavity. The central axis of the nozzle (406) coincides with the diameter of the ring body. A second part of the cooling water channel (408) is provided on the nozzle (406). The injector (402) is arranged relative to the nozzle (406). The main body of the injector (402) is a tube; the inner cavity of the front section of the tube is a combustion chamber cavity (407), which is connected to the outer annular cavity. A third cooling water channel (408) is provided on the combustion chamber cavity (407) surrounding the combustion chamber cavity (407). The combustion chamber cavity (407) is connected to the ignition nozzle (401), which is externally connected to the ignition timing controller (9). A central axis of the rear section of the tube is provided with A nozzle (410) is provided; an air collection chamber (409) is provided on the pipe body corresponding to the middle section of the nozzle (410), the air collection chamber (409) is connected to an air connector (404), and the air connector (404) is connected to an external air storage tank (8); a fuel collection chamber (411) is provided on the pipe body corresponding to the rear section of the nozzle (410), the fuel collection chamber (411) is connected to a fuel connector (405), and the fuel connector (405) is connected to an external fuel storage tank (6). Each cooling water flow channel (408) is connected to a corresponding cooling water connector (403), and the cooling water connector (403) is connected to high-pressure cooling water; the pressure range of the high-pressure cooling water is 2.0Mpa~5.0Mpa.

3. The high-speed transverse gas jet test device according to claim 2, characterized in that, The fuel storage tank (6) and the gas storage tank (8) are part of the fuel supply system. The fuel supply system also includes a shut-off valve and an orifice plate. The air pressure is increased by the gas storage tank (8), and the fuel flow is controlled by the shut-off valve and the orifice plate. The fuel stored in the fuel storage tank (6) is alcohol.

4. The high-speed transverse gas jet test device according to claim 2, characterized in that, The ignition timing controller (9) controls the fuel injection time and ignition time to ignite the fuel and air mixture and generate high-temperature and high-pressure gas.

5. The high-speed transverse gas jet test device according to claim 2, characterized in that, All components of the gas generator (4) except the nozzle (410) are made of GH3625 high temperature alloy material, integrally formed by 3D printing additive manufacturing, and then the mating surfaces are processed. According to the combustion parameter requirements, corresponding cooling water connectors (403) are set at different positions in the cooling water channel (408). Combustion parameters include the specific impulse, temperature, specific heat ratio, and secondary combustion effect of the jet gas.

6. The high-speed transverse gas jet test device according to claim 2, characterized in that, The nozzle (410) of the gas generator (4) is installed by thread.

7. The high-speed transverse gas jet test device according to claim 2, characterized in that, The nozzle (406) is a Laval nozzle.

8. The high-speed transverse gas jet test device according to claim 2, characterized in that, The connecting pipe of the fuel connector (405) is a DN4mm pipe, and the connecting pipe of the air connector (404) is a DN10mm pipe.

9. A method for testing high-speed transverse gas jets, used in any one of the high-speed transverse gas jet testing apparatuses described in claims 2 to 8, characterized in that, The high-speed transverse gas jet test method establishes a safety interlock test sequence, including the following steps: S10. Start the high-speed wind tunnel. The wind tunnel nozzle (1) ejects high-speed airflow, forming a stable high-speed flow field in the high-speed wind tunnel test section. S20. Open the water cooling system of the high-speed wind tunnel and inject cooling water into each cooling water channel (408) through the corresponding cooling water connector (403) to avoid structural ablation during the high-speed transverse gas jet test; S30. The ignition timing controller (9) opens the valve according to the timing sequence, and the fuel supply system supplies air to the gas generator (4). After 0.5s, fuel is supplied. After the fuel is sprayed out through the nozzle (410), it mixes with air in the injector (402) and is then sprayed into the combustion chamber cavity (407). It is ignited by the ignition nozzle (401) in the combustion chamber cavity (407). After successful ignition, the ignition nozzle (401) is closed. S40. The gas generator (4) enters the designed working state. Air and fuel are uniformly mixed and stably burned in the combustion chamber cavity (407) to form high temperature and high pressure gas. After being accelerated by the nozzle (406), the high temperature and high speed gas is ejected to obtain a transverse hot jet, and a transverse thrust is formed through the thrust surface. S50. After the balance (3) test is completed, the gas generator (4) is shut off, the fuel supply is turned off, the transverse hot jet is extinguished, and the air supply is continued for 5 seconds before the air supply is turned off again to blow out the residual fuel in the fuel pipeline and combustion chamber cavity (407); After 60.2 seconds, the water cooling system of the high-speed wind tunnel is shut down; S70. High-speed wind tunnel shutdown.

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