An aircraft engine wake re-ingestion wind tunnel test device and test method

Abstract

An aircraft engine wake re-ingestion wind tunnel test device and test method belong to the technical field of wind tunnel tests. The present invention solves the problem that the existing wind tunnel test methods cannot effectively obtain the engine wake re-ingestion during the takeoff and landing process of an aircraft. In the hot jet direct current wind tunnel of the present invention, an aircraft model is connected to a fast lifting support. A high-pressure air source is connected to a high-temperature gas generating device. The high-temperature gas generating device and the intake duct suction device are respectively connected to the aircraft model through temperature and pressure resistant flexible pipelines. The fast lifting support binds the temperature and pressure resistant flexible pipelines. The measurement and control system is arranged outside the hot jet direct current wind tunnel. The measurement and control system is respectively connected to the aircraft model, the hot jet direct current wind tunnel, the hot gas suction floor, the fast lifting support, the high-pressure air source and the high-temperature gas generating device. The aircraft engine wake re-ingestion wind tunnel test device and test method of the present invention have a reasonable system division and high practicability.

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 intake will suck in the wake that is ejected from the tailpipe and returns after hitting the ground, causing an increase in the temperature distortion and pressure distortion at the outlet of the intake, 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 intake wind tunnel test is an important research method for evaluating the distortion characteristics of aircraft intakes. Currently, the systems used for aircraft wind tunnel tests can only achieve cold jet simulation and do 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:

[0006] Solution 1: An aircraft engine wake re-ingestion wind tunnel test device, comprising a hot jet direct current wind tunnel, a hot gas suction floor, a quick lift support, a high-pressure gas source, a high-temperature gas generating device, an intake suction device, a temperature and pressure resistant flexible pipeline, and a measurement and control system. An aircraft model is arranged in the hot jet direct current wind tunnel. 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 generating device, and the intake suction device are arranged outside the hot jet direct current wind tunnel. The high-pressure gas source is connected to the high-temperature gas generating device through a normal temperature gas supply pipeline. The high-temperature gas generating device and the intake 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 direct current wind tunnel. The measurement and control system is respectively connected to the aircraft model, the hot jet direct current wind tunnel, the hot gas suction floor, the quick lift support, the high-pressure gas source, and the high-temperature gas generating device.

[0007] Further, the hot air suction floor includes a high-temperature resistant floor body, a sliding door, a slide rail, and an exhaust pipe. 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 exhaust pipe is installed on the high-temperature resistant floor body, and the other end of the exhaust pipe is arranged outside the direct-current hot jet wind tunnel. An ejector is arranged in the exhaust pipe. 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 exhaust pipe and is arranged below the aircraft model.

[0008] Further, one end of the fast 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 fast 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 fast lifting of the aircraft model.

[0009] Further, 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.

[0010] Solution 2: A test method for re-inhaling the wake of an aircraft engine in a wind tunnel. This method is realized relying on the test device for re-inhaling the wake of an aircraft engine in a wind tunnel described in Solution 1, and includes the following steps:

[0011] Step 1: The fast 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 outlet diameter of the tail nozzle. 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:

[0012] ;

[0013] 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;

[0014] Step 2: The high-pressure gas source provides gas source to the high-temperature gas generating device through the normal-temperature gas 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 1atm to 4atm;

[0015] Step 3: The wind speed in the hot jet DC wind tunnel is 5 m / s to 50 m / s. The high-temperature gas generating device inputs the generated high-temperature gas into the hot jet DC wind tunnel through a temperature-resistant and pressure-resistant flexible pipeline to simulate the engine hot jet.

[0016] Step 4: In the hot jet adjustment stage, the measurement and control system controls the draw valve to open, and the ejector works. The hot waste is discharged outside the hot jet DC wind tunnel through the extraction pipeline. The extraction flow rate is more than 1.5 times the waste gas flow rate. After the hot jet adjustment is completed, the draw valve quickly closes within 1 s under the drive of the motor through the slide rail to form a complete high-temperature resistant floor body structure, simulating the influence of ground effect and hot jet on the aircraft.

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

[0018] 1. An aircraft engine wake re-ingestion wind tunnel test device of the present invention realizes the design of the engine wake re-ingestion system within the limited space of the wind tunnel. The system is clearly and reasonably divided, has high practicability, and can meet the test requirements of engine wake re-ingestion.

[0019] 2. An aircraft engine wake re-ingestion wind tunnel test device of the present invention is compatible with aircraft tests of types such as single nozzle, multi-nozzle, and combined hot and cold nozzles, and has stronger practicability; 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, it realizes the change of the model attitude and lifting.

[0020] 3. An aircraft engine wake re-ingestion 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 extraction pipeline for air extraction, the influence of hot gas on the test environment is reduced. Description of the Drawings

[0021] Figure 1 is a schematic diagram of an aircraft engine wake re-ingestion wind tunnel test device;

[0022] Figure 2 is a schematic diagram of an aircraft model;

[0023] Figure 3 is a schematic diagram of a hot gas suction removal floor;

[0024] Figure 4 is a schematic diagram of a quick lifting support.

[0025] In the figure: 1 - aircraft model, 2 - hot jet 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 - inlet duct suction device, 8 - normal temperature gas supply pipeline, 9 - temperature and pressure resistant flexible pipeline, 10 - measurement and control system, 11 - engine nozzle, 12 - inlet duct, 13 - high-temperature resistant floor body, 14 - pull-out valve, 15 - slide rail, 16 - suction pipeline, 17 - ejector, 18 - three-degree-of-freedom mechanism, 19 - lift electric cylinder. Specific embodiments

[0026] To make the objectives, technical solutions and advantages of the present invention clearer, the present invention will be described below through specific embodiments shown in the drawings. However, it should be understood that these descriptions are merely exemplary and are not intended to limit the scope of the present invention. In addition, in the following description, descriptions of well-known structures and technologies are omitted to avoid unnecessarily confusing the concepts of the present invention.

[0027] 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, etc. The detachable connections include, but are not limited to, conventional disassembly methods such as threaded connection, snap connection, pin connection and hinge connection, etc. 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 according to their needs. For example: welding connection is selected for fixed connection, and hinge connection is selected for detachable connection.

[0028] Example 1, in combination with Figures 1-4Description of this embodiment, a kind of aircraft engine wake re - inhalation wind tunnel test device of this embodiment, includes a hot jet DC wind tunnel 2, a hot gas suction floor 3, a fast - lifting 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 in the hot jet DC wind tunnel 2. The aircraft model 1 is connected to the fast - lifting 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 DC wind tunnel 2. The high - pressure air source 5 is connected to the high - temperature gas generating device 6 through a normal - temperature gas 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 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 fast - lifting support 4, the high - pressure air source 5 and the high - temperature gas generating device 6. The measurement and control system 10 is used for wind speed control, hot gas suction control, support angle and lifting control, air supply control, intake duct air extraction control, 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.

[0029] 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 adapter of the engine nozzle 11 and the intake duct 12 on the aircraft model 1 is a 90° variable - diameter elbow. Temperature and pressure sensors are arranged inside the pipeline for monitoring the air flow. The pipeline is wrapped with a high - temperature - resistant heat - insulating layer to prevent heat loss and reduce the influence on the surface temperature of the aircraft model 1;

[0030] The test section of the hot jet DC wind tunnel 2 is 4.5 m wide, 3.5 m high and 8 m long, all of which are more than twice the span and fuselage length of the aircraft model 1. There are multiple slots on the wall of the hot jet DC wind tunnel 2 leading to the external environment to prevent heat accumulation in the hot jet DC wind tunnel 2. Multiple temperature sensors are arranged inside the hot jet DC wind tunnel 2 for monitoring the environment inside the wind tunnel.

[0031] On the high-temperature resistant floor body 13 of the hot gas suction floor 3, a high-temperature resistant heat insulation layer is avoided being covered. 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. The height between the high-temperature resistant floor body 13 and the aircraft model 1 is about 1.25m, which is greater than half of the wingspan length of the aircraft model 1. During the hot jet flow regulation stage, the pull-out valve 14 is opened, and the ejector 17 in the suction pipeline 16 below the pull-out valve 14 works to discharge the hot exhaust gas outside the hot jet flow direct current wind tunnel 2 through the suction pipeline 16. The suction flow rate is more than 1.5 times the exhaust gas flow rate. After the hot jet flow regulation is completed, the pull-out valve 14 is quickly closed within 1s under the drive of a motor through the slide rail 15. The pull-out valve 14 is arranged below the aircraft model 1 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 flow.

[0032] The quick 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 attitude, it is locked by screws, and the attitude angle can be adjusted and the aircraft model 1 can be driven to lift at a specified rate. Through the three-degree-of-freedom mechanism 18, 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 0.01m to 2m from the floor. The model scale is 1:10, and the maximum lifting speed of the real aircraft is 10m / s. It is required that the support lifting rate is greater than 1m / s to meet the simulation of the takeoff and landing process of the real aircraft. The quick lifting support 4 can be bound with a temperature-resistant and pressure-resistant flexible pipeline 9 to connect the high-temperature gas generating device 6 and the intake duct suction device 7 to the aircraft model 1.

[0033] The high-pressure air source 5 can provide normal temperature air with a pressure of 10Mpa. Through the normal temperature supply pipeline 8, after being regulated by a pressure stabilizing valve, a flow regulating valve, etc., it is transported into the high-temperature gas generating device 6. The heating method of the high-temperature gas generating device 6 is electric heating. By adjusting the electric power and the supply air pressure, high-temperature gas with a temperature of 1000K can be generated and transported to the aircraft model 1 through the temperature-resistant and pressure-resistant flexible pipeline 9 wrapped with a heat insulation layer. The outer surface temperature of the heat insulation layer is less than 330K, which is used to simulate the engine hot jet flow.

[0034] Example 2, combined with Figures 1-4 To illustrate this embodiment, a method for an aircraft engine wake re-inhalation wind tunnel test in this embodiment includes the following steps:

[0035] Step 1: The quick lift support 4 is connected to the aircraft model 1 through the 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, and the lift and lower rate meets the simulation of the takeoff and landing process of the real aircraft, that is:

[0036] ;

[0037] In the formula, is the real-time rate of the aircraft model 1, is the real-time rate of the takeoff and landing process of the real aircraft, is the scale ratio of the aircraft model 1;

[0038] Step 2: The high-pressure gas source 5 provides gas source into 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;

[0039] 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 for simulating the engine hot jet;

[0040] Step 4: In the hot jet adjustment stage, the measurement and control system 10 controls the draw 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, 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 high-temperature resistant floor body 13 structure, simulating the influence of the aircraft by ground effect and hot jet.

[0041] 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 they do not exceed the spirit essence of the present invention, and they are within the protection scope of the present invention.

Claims

1. An aircraft engine wake re-ingestion wind tunnel test device, characterized in that: It includes a hot jet DC 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 inlet 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 DC 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 inlet duct suction device (7) are arranged outside the hot jet DC 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 inlet 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 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 air source (5), and the high-temperature gas generating device (6); The hot gas suction floor (3) includes a high-temperature resistant floor body (13), a draw valve (14), a slide rail (15), and a suction pipeline (16). The high-temperature resistant floor body (13) is installed inside the hot jet DC 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 DC wind tunnel (2). An ejector (17) is arranged inside the suction pipeline (16). A draw valve (14) is installed on the high-temperature resistant floor body (13). The draw valve (14) is slidably installed on the high-temperature resistant floor body (13) through the slide rail (15). The draw valve (14) is arranged at the outlet of the suction pipeline (16). The draw valve (14) is arranged below the aircraft model (1).

2. The aircraft engine wake re-ingestion wind tunnel test device according to claim 1, 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 DC wind tunnel (2) to realize the height control and quick lift of the aircraft model (1).

3. The aircraft engine wake re-ingestion wind tunnel test device according to claim 2, characterized in that: An engine nozzle (11) and an inlet duct (12) are installed on the aircraft model (1). The engine nozzle (11) is connected to the high-temperature gas generating device (6) through a temperature and pressure resistant flexible pipeline (9). The inlet duct (12) is connected to the inlet duct suction device (7) through a temperature and pressure resistant flexible pipeline (9). The inlet duct (12) and the engine nozzle (11) are not connected to each other.

4. A method for wind tunnel test of aircraft engine wake re - ingestion, which is realized based on the aircraft engine wake re - ingestion wind tunnel test device described in claim 3, is 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 exhaust nozzle outlet. The ratio of the aircraft model (1) to the real aircraft is 1:10, and the lift and lower rate satisfies the simulation of the takeoff and landing process of the real aircraft, that is: ； Wherein, 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 into 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 opening of the pull valve (14), and the ejector (17) works. The hot waste is discharged outside the hot jet DC wind tunnel (2) through the exhaust 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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