Aircraft engine wake flow re-suction wind tunnel test device and test method

Abstract

The invention discloses an aircraft engine wake flow re-suction wind tunnel test device and test method, and belongs to the technical field of wind tunnel tests. According to the invention, the problem that the engine wake flow re-suction in the take-off and landing process of the aircraft cannot be effectively obtained by the existing wind tunnel test method is solved. An airplane model arranged in a thermal jet direct-current wind tunnel is connected with a rapid lifting support, a high-pressure gas source is connected with a high-temperature gas generating device, the high-temperature gas generating device and an air inlet channel suction device communicate with the airplane model through temperature-resistant and pressure-resistant flexible pipelines, the rapid lifting support is bound with the temperature-resistant and pressure-resistant flexible pipelines, and the high-temperature gas generating device and the air inlet channel suction device are connected with the rapid lifting support. The measurement and control system is arranged on the outer side of the thermal jet flow direct flow wind tunnel and connected with the airplane model, the thermal jet flow direct flow wind tunnel, the hot air suction floor, the rapid lifting support, the high-pressure air source and the high-temperature air generation device. According to the aircraft engine wake flow re-suction wind tunnel test device and method, system division is reasonable, and high practicability is achieved.

Description

Technical Field

[0001] The present invention belongs to the technical field of wind tunnel tests, and particularly relates to an aircraft engine wake re-ingestion wind tunnel test device and a test method. Background Art

[0002] When an aircraft takes off, the high-temperature wake can be ejected onto the deflector or the ground to generate a reaction force, effectively shortening the takeoff run distance and improving the takeoff and landing performance. However, during takeoff and landing, its inlet will inhale the wake that is ejected from the tail nozzle and then returns after hitting the ground, causing an increase in temperature distortion and pressure distortion at the outlet of the inlet, which may lead to engine surging or flameout, affecting the working stability and life of the engine, and even endangering the flight safety of the aircraft. The wind tunnel test of the inlet is an important research means for evaluating the distortion characteristics of the aircraft inlet. At present, the system for aircraft wind tunnel tests can only achieve cold jet simulation and does not consider the dynamic movement process of the aircraft model. The data obtained by this simulation method deviates greatly from the actual situation, which is not conducive to the evaluation of the inlet / engine compatibility of the aircraft.

[0003] Therefore, the present application proposes an aircraft engine wake re-ingestion wind tunnel test device and a test method to solve the above problems. Summary of the Invention

[0004] The research and development purpose of the present invention is to solve the problem that the existing wind tunnel test method cannot effectively obtain the engine wake re-ingestion during the takeoff and landing process of the aircraft. A brief overview of the present invention is given below to provide a basic understanding of certain aspects of the present invention. It should be understood that this overview is not an exhaustive overview of the present invention. It is not intended to identify the key or important parts of the present invention, nor is it intended to limit the scope of the present invention.

[0005] Technical Solution of the Present Invention Solution 1: An aircraft engine wake re-ingestion wind tunnel test device, including a hot jet DC wind tunnel, a hot gas suction floor, a quick lift support, a high-pressure gas source, a high-temperature gas generation device, an inlet suction device, a temperature and pressure resistant flexible pipeline, and a measurement and control system. An aircraft model is arranged in the hot jet DC wind tunnel, and the aircraft model is connected to the quick lift support. The hot gas suction floor is arranged below the aircraft model. The high-pressure gas source, the high-temperature gas generation device, and the inlet suction device are arranged outside the hot jet DC wind tunnel. The high-pressure gas source is connected to the high-temperature gas generation device through a normal temperature supply pipeline. The high-temperature gas generation device and the inlet suction device are respectively connected to the aircraft model through the temperature and pressure resistant flexible pipeline. The quick lift support binds the temperature and pressure resistant flexible pipeline. The measurement and control system is arranged outside the hot jet DC wind tunnel, and the measurement and control system is respectively connected to the aircraft model, the hot jet DC wind tunnel, the hot gas suction floor, the quick lift support, the high-pressure gas source, and the high-temperature gas generation device.

[0006] Furthermore, the hot gas suction floor includes a high-temperature resistant floor body, a sliding door, a slide rail, and a suction pipeline. The high-temperature resistant floor body is installed in the direct-current hot jet wind tunnel. The upper surface of the high-temperature resistant floor body is covered with a high-temperature resistant heat insulation layer. One end of the suction pipeline is installed on the high-temperature resistant floor body, and the other end of the suction pipeline is arranged outside the direct-current hot jet wind tunnel. An ejector is arranged in the suction pipeline. A sliding door is installed on the high-temperature resistant floor body. The sliding door is slidably installed on the high-temperature resistant floor body through the slide rail. The sliding door is arranged at the outlet of the suction pipeline and is arranged below the aircraft model.

[0007] Furthermore, one end of the quick lifting support is connected to the aircraft model through a three-degree-of-freedom mechanism. An elevating electric cylinder is installed at the other end of the quick lifting support. The elevating electric cylinder is connected to the upper wall plate of the direct-current hot jet wind tunnel to realize the height control and quick lifting of the aircraft model.

[0008] Furthermore, an engine nozzle and an air inlet are installed on the aircraft model. The engine nozzle is connected to the high-temperature gas generating device through a temperature and pressure resistant flexible pipeline. The air inlet is connected to the air inlet suction device through a temperature and pressure resistant flexible pipeline. The air inlet and the engine nozzle are not connected to each other.

[0009] Solution 2: A method for testing the re-ingestion of an aircraft engine wake in a wind tunnel. This method is realized relying on the aircraft engine wake re-ingestion wind tunnel test device described in Solution 1 and includes the following steps: Step 1: The quick lifting support is connected to the aircraft model through a three-degree-of-freedom mechanism, adjusts the attitude angle, and drives the aircraft model to lift and lower at a specified rate. The adjustable range of the pitch angle is -10° to 30°, the adjustable range of the sideslip angle is -90° to 90°, the adjustable range of the roll angle is -45° to 45°, and the adjustable range of the height is 1 to 15 times the diameter of the tail nozzle outlet. The ratio of the aircraft model to the real aircraft is 1:10. The lifting and lowering rate meets the simulation of the takeoff and landing process of the real aircraft, that is: ; In the formula, is the real-time rate of the aircraft model, is the real-time rate of the takeoff and landing process of the real aircraft, is the scale ratio of the aircraft model; Step 2: The high-pressure air source provides air source to the high-temperature gas generating device through the normal-temperature supply pipeline. The temperature range of the gas generated by the high-temperature gas generating device is 400K to 1200K, and the pressure range of the generated gas is 1 atm to 4 atm; Step 3: The wind speed in the direct-current hot jet wind tunnel is 5 m / s to 50 m / s. The high-temperature gas generating device inputs the generated high-temperature gas into the direct-current hot jet wind tunnel through a temperature and pressure resistant flexible pipeline to simulate the engine hot jet. Step 4: In the hot jet flow regulation stage, the measurement and control system controls the opening of the draw valve, and the ejector works. The hot waste gas is discharged outside the hot jet flow direct current wind tunnel through the suction pipeline. The suction flow rate is more than 1.5 times the waste gas flow rate. After the hot jet flow regulation is completed, the draw valve quickly closes within 1 s under the drive of the motor through the slide rail, forming a complete high-temperature resistant floor body structure to simulate the influence of ground effect and hot jet flow on the aircraft.

[0010] The present invention has the following beneficial effects: 1. The aircraft engine wake re-inhalation wind tunnel test device of the present invention realizes the design of the engine wake re-inhalation system within the limited space of the wind tunnel. The system is clearly and reasonably divided, has high practicability, and can meet the requirements of the engine wake re-inhalation test.

[0011] 2. The aircraft engine wake re-inhalation wind tunnel test device of the present invention is compatible with aircraft tests of types such as single nozzle, multi-nozzle, and combined cold and hot nozzles, and has stronger practicability; by using the temperature-resistant and pressure-resistant flexible pipeline scheme, while providing high-temperature and high-pressure gas and vacuum pumping for the aircraft model, the attitude and lifting of the model are realized.

[0012] 3. The aircraft engine wake re-inhalation wind tunnel test device of the present invention aims at the hot gas problem in the wind tunnel. By processing a draw valve on the high-temperature resistant floor body and cooperating with the suction of the suction pipeline, the influence of hot gas on the test environment is reduced. Description of the Drawings

[0013] Figure 1 is a schematic diagram of an aircraft engine wake re-inhalation wind tunnel test device; Figure 2 is a schematic diagram of an aircraft model; Figure 3 is a schematic diagram of a hot gas suction floor; Figure 4 is a schematic diagram of a quick lift support.

[0014] In the figure: 1 - aircraft model, 2 - hot jet flow direct current wind tunnel, 3 - hot gas suction floor, 4 - quick lift support, 5 - high-pressure gas source, 6 - high-temperature gas generating device, 7 - intake duct suction device, 8 - normal temperature supply pipeline, 9 - temperature-resistant and pressure-resistant flexible pipeline, 10 - measurement and control system, 11 - engine nozzle, 12 - intake duct, 13 - high-temperature resistant floor body, 14 - draw valve, 15 - slide rail, 16 - suction pipeline, 17 - ejector, 18 - three-degree-of-freedom mechanism, 19 - lift electric cylinder. Specific Embodiments

[0015] To make the objectives, technical solutions and advantages of the present invention clearer and more understandable, the present invention will be described below through specific embodiments shown in the accompanying drawings. However, it should be understood that these descriptions are only exemplary and are not intended to limit the scope of the present invention. In addition, in the following description, the descriptions of well-known structures and technologies are omitted to avoid unnecessarily confusing the concepts of the present invention.

[0016] The connections mentioned in the present invention are divided into fixed connections and detachable connections. The fixed connections (i.e., non-detachable connections) include but are not limited to conventional fixed connection methods such as hemming connection, rivet connection, bonding connection, and welding connection. The detachable connections include but are not limited to conventional disassembly methods such as screw connection, snap connection, pin connection, and hinge connection. When the specific connection method is not clearly defined, it is defaulted that at least one connection method can always be found among the existing connection methods to achieve this function, and those skilled in the art can select it according to their needs. For example: welding connection is selected for the fixed connection, and hinge connection is selected for the detachable connection.

[0017] Example 1, in combination with Figures 1-4 To illustrate this embodiment, a wind tunnel test device for re-inhaling the wake of an aircraft engine in this embodiment includes a hot jet DC wind tunnel 2, a hot gas suction floor 3, a quick lift support 4, a high-pressure gas source 5, a high-temperature gas generation device 6, an intake duct suction device 7, a temperature and pressure resistant flexible pipeline 9, and a measurement and control system 10. An aircraft model 1 is arranged in the hot jet DC wind tunnel 2. The aircraft model 1 is connected to the quick lift support 4. A hot gas suction floor 3 is arranged below the aircraft model 1. The high-pressure gas source 5, the high-temperature gas generation device 6, and the intake duct suction device 7 are arranged outside the hot jet DC wind tunnel 2. The high-pressure gas source 5 is connected to the high-temperature gas generation device 6 through a normal temperature gas supply pipeline 8. The high-temperature gas generation device 6 and the intake duct suction device 7 are respectively connected to the aircraft model 1 through the temperature and pressure resistant flexible pipeline 9. The measurement and control system 10 is arranged outside the hot jet DC wind tunnel 2. The measurement and control system 10 is respectively connected to the aircraft model 1, the hot jet DC wind tunnel 2, the hot gas suction floor 3, the quick lift support 4, the high-pressure gas source 5, and the high-temperature gas generation device 6. The measurement and control system 10 is used for wind speed control, hot gas suction control, support angle and lift control, gas supply control, intake duct air extraction control, and high-temperature gas control, and at the same time measures parameters such as the temperature and pressure of the model and the spatial flow field.

[0018] The span of the aircraft model 1 is 1 m, the fuselage length is 1 m, it includes 2 hot jet nozzles and pipelines, with a pressure resistance of 1 Mpa and a temperature resistance greater than 1000 K. The adapters of the engine nozzle 11 and the intake duct 12 on the aircraft model 1 are 90° reduced-diameter elbows. Temperature and pressure sensors are arranged inside the pipeline to monitor the air flow. The pipeline is wrapped with a high-temperature resistant heat insulation layer to prevent heat loss and reduce the influence on the surface temperature of the aircraft model 1; The test section of the thermal jet direct current wind tunnel 2 is 4.5m wide, 3.5m high and 8m long, all of which are larger than twice the length of the aircraft model 1 and the fuselage length. There are multiple slots on the wall of the thermal jet direct current wind tunnel 2 leading to the outside environment to prevent heat accumulation in the thermal jet direct current wind tunnel 2. There are multiple temperature sensors arranged in the thermal jet direct current wind tunnel 2 to monitor the environment in the wind tunnel.

[0019] The high temperature resistant floor body 13 of the hot air suction floor 3 is prevented from being covered with a high temperature resistant heat insulation layer, and a pull-out valve 14 is installed on the high temperature resistant floor body 13. The pull-out valve 14 is slidably arranged on the high temperature resistant floor body 13 through a slide rail 15. The size of the pull-out valve 14 is 1m*1m, and the height of the high temperature resistant floor body 13 from the aircraft model 1 is about 1.25m, which is greater than the half wingspan length of the aircraft model 1. In the thermal jet adjustment stage, the pull-out valve 14 is opened, and the ejector 17 in the exhaust pipe 16 below the pull-out valve 14 works, and the hot exhaust gas is discharged from the hot jet direct current wind tunnel 2 through the exhaust pipe 16, and the suction flow rate is greater than 1.5 times the exhaust flow rate. After the hot jet adjustment is completed, the pull-out valve 14 is quickly closed within 1s through the slide rail 15 under the drive of the motor. The pull-out valve 14 is arranged below the aircraft model 1 to form a complete high temperature resistant floor body 13 structure, simulating the aircraft being affected by ground effect and thermal jet.

[0020] The rapid lifting support 4 is connected to the back of the aircraft model 1 through a three-degree-of-freedom mechanism 18. The three-degree-of-freedom mechanism 18 is a ball head structure. After the aircraft model 1 adjusts its posture, it is locked by screws to adjust the posture angle and drive the aircraft model 1 to rise and fall at a specified rate. Through the three-degree-of-freedom mechanism 18, the pitch angle can be adjusted in the range of -10° to 30°, the sideslip angle can be adjusted in the range of -90° to 90°, the roll angle can be adjusted in the range of -45° to 45°, and the height can be adjusted in the range of 0.01m to 2m from the floor. The model ratio is 1:10, and the maximum lifting speed of the real aircraft is 10m / s. The support lifting speed is required to be greater than 1m / s to meet the simulation of the take-off and landing process of the real aircraft. The rapid lifting support 4 can be bound to the temperature-resistant and pressure-resistant flexible pipeline 9 to connect the high-temperature gas generation device 6 and the air intake suction device 7 to the aircraft model 1.

[0021] The high-pressure gas source 5 can provide room-temperature air with a pressure of 10Mpa, which is transported to the high-temperature gas generating device 6 through the room-temperature gas supply pipeline 8 and adjusted by the pressure-stabilizing valve, flow regulating valve, etc. The heating method of the high-temperature gas generating device 6 is electric heating. By adjusting the electric power and the gas supply pressure, a high-temperature gas with a temperature of 1000K can be generated. It is transported to the aircraft model 1 through the temperature-resistant and pressure-resistant flexible pipeline 9 wrapped with a thermal insulation layer. The outer surface temperature of the thermal insulation layer is less than 330K, which is used to simulate the engine thermal jet.

[0022] Embodiment 2, combined Figures 1-4This embodiment describes a method for a wind tunnel test of aircraft engine wake re - ingestion, which includes the following steps: Step 1: The quick - lift support 4 is connected to the aircraft model 1 through a three - degree - of - freedom mechanism 18. Adjust the attitude angle and drive the aircraft model 1 to lift and lower at a specified rate. The adjustable range of the pitch angle is - 10° to 30°, the adjustable range of the sideslip angle is - 90° to 90°, the adjustable range of the roll angle is - 45° to 45°, and the adjustable range of the height is 1 to 15 times the diameter of the tail - nozzle outlet. The ratio of the aircraft model 1 to the real aircraft is 1:10. The lift - and - lower rate satisfies the simulation of the real aircraft's take - off and landing process, that is: ; In the formula, is the real - time rate of the aircraft model 1, is the real - time rate of the real aircraft's take - off and landing process, is the scale ratio of the aircraft model 1; Step 2: The high - pressure gas source 5 provides gas source to the high - temperature gas generation device 6 through a normal - temperature gas supply pipeline 8. The temperature range of the gas generated by the high - temperature gas generation device 6 is 400K to 1200K, and the pressure range of the generated gas is 1atm to 4atm; Step 3: The wind speed in the hot - jet DC wind tunnel 2 is 5m / s to 50m / s. The high - temperature gas generation device 6 inputs the generated high - temperature gas into the hot - jet DC wind tunnel 2 through a temperature - and - pressure - resistant flexible pipeline 9 to simulate the engine hot jet; Step 4: In the hot - jet adjustment stage, the measurement and control system 10 controls the opening of the draw valve 14, and the ejector 17 works. The hot waste is discharged outside the hot - jet DC wind tunnel 2 through the suction pipeline 16, and the suction flow rate is more than 1.5 times the waste gas flow rate. After the hot - jet adjustment is completed, the draw valve 14 quickly closes within 1s under the drive of the motor through the slide rail 15 to form a complete structure of the high - temperature - resistant floor body 13, simulating the influence of the aircraft by ground effect and hot jet.

[0023] This embodiment is only an exemplary illustration of the present invention and does not limit its protection scope. Those skilled in the art can also make partial changes to it. As long as it does not exceed the spirit of the present invention, it is within the protection scope of the present invention.

Claims

1. An aircraft engine wake re - inhalation wind tunnel test device, characterized in that: It includes a hot jet direct current wind tunnel (2), a hot gas suction floor (3), a quick lift support (4), a high-pressure air source (5), a high-temperature gas generating device (6), an intake duct suction device (7), a temperature and pressure resistant flexible pipeline (9), and a measurement and control system (10). An aircraft model (1) is arranged inside the hot jet direct current wind tunnel (2). The aircraft model (1) is connected to the quick lift support (4). The hot gas suction floor (3) is arranged below the aircraft model (1). The high-pressure air source (5), the high-temperature gas generating device (6), and the intake duct suction device (7) are arranged outside the hot jet direct current wind tunnel (2). The high-pressure air source (5) is connected to the high-temperature gas generating device (6) through a normal temperature supply pipeline (8). The high-temperature gas generating device (6) and the intake duct suction device (7) are respectively connected to the aircraft model (1) through the temperature and pressure resistant flexible pipeline (9). The quick lift support (4) binds the temperature and pressure resistant flexible pipeline (9). The measurement and control system (10) is arranged outside the hot jet direct current wind tunnel (2). The measurement and control system (10) is respectively connected to the aircraft model (1), the hot jet direct current wind tunnel (2), the hot gas suction floor (3), the quick lift support (4), the high-pressure air source (5), and the high-temperature gas generating device (6).

2. The aircraft engine wake re - inhalation wind tunnel test device according to claim 1, characterized in that: The hot gas suction floor (3) includes a high-temperature resistant floor body (13), a sliding door (14), a slide rail (15), and a suction pipeline (16). The high-temperature resistant floor body (13) is installed inside the hot jet direct current wind tunnel (2). The upper surface of the high-temperature resistant floor body (13) is covered with a high-temperature resistant heat insulation layer. One end of the suction pipeline (16) is installed on the high-temperature resistant floor body (13). The other end of the suction pipeline (16) is arranged outside the hot jet direct current wind tunnel (2). An ejector (17) is arranged inside the suction pipeline (16). The sliding door (14) is installed on the high-temperature resistant floor body (13). The sliding door (14) is slidably installed on the high-temperature resistant floor body (13) through the slide rail (15). The sliding door (14) is arranged at the outlet of the suction pipeline (16). The sliding door (14) is arranged below the aircraft model (1).

3. The aircraft engine wake re - inhalation wind tunnel test device according to claim 2, characterized in that: One end of the quick lift support (4) is connected to the aircraft model (1) through a three-degree-of-freedom mechanism (18). The other end of the quick lift support (4) is installed with a lifting electric cylinder (19). The lifting electric cylinder (19) is connected to the upper wall plate of the hot jet direct current wind tunnel (2) to realize the height control and quick lift of the aircraft model (1).

4. The aircraft engine wake re - inhalation wind tunnel test device according to claim 3, characterized in that: An engine nozzle (11) and an intake duct (12) are installed on the aircraft model (1). The engine nozzle (11) is connected to the high-temperature gas generating device (6) through the temperature and pressure resistant flexible pipeline (9). The intake duct (12) is connected to the intake duct suction device (7) through the temperature and pressure resistant flexible pipeline (9). The intake duct (12) and the engine nozzle (11) are not connected to each other.

5. An aircraft engine wake re - inhalation wind tunnel test method, which is realized relying on the aircraft engine wake re - inhalation wind tunnel test device according to claim 4, characterized in that, It includes the following steps: Step 1: The quick lift support (4) is connected to the aircraft model (1) through a three-degree-of-freedom mechanism (18), adjusts the attitude angle and drives the aircraft model (1) to lift and lower at a specified rate. The adjustable range of the pitch angle is -10° to 30°, the adjustable range of the sideslip angle is -90° to 90°, the adjustable range of the roll angle is -45° to 45°, and the adjustable range of the height is 1 to 15 times the diameter of the nozzle exit. The ratio of the aircraft model (1) to the real aircraft is 1:

10. The lift and lower rate meets the simulation of the takeoff and landing process of the real aircraft, that is: ； In the formula, is the real-time speed of the aircraft model (1), is the real-time speed during the takeoff and landing process of the real aircraft, is the scale ratio of the aircraft model (1); Step 2: The high-pressure gas source (5) provides gas source to the high-temperature gas generating device (6) through the normal-temperature gas supply pipeline (8). The temperature range of the gas generated by the high-temperature gas generating device (6) is 400K to 1200K, and the pressure range of the generated gas is 1atm to 4atm; Step 3: The wind speed in the hot jet DC wind tunnel (2) is 5m / s to 50m / s. The high-temperature gas generating device (6) inputs the generated high-temperature gas into the hot jet DC wind tunnel (2) through the temperature-resistant and pressure-resistant flexible pipeline (9) to simulate the engine hot jet; Step 4: In the hot jet adjustment stage, the measurement and control system (10) controls the pull valve (14) to open, and the ejector (17) works. The hot waste is discharged outside the hot jet DC wind tunnel (2) through the suction pipeline (16). The suction flow rate is more than 1.5 times the waste gas flow rate. After the hot jet adjustment is completed, the pull valve (14) quickly closes within 1s under the drive of the motor through the slide rail (15) to form a complete high-temperature resistant floor body (13) structure to simulate the influence of the aircraft by ground effect and hot jet.

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