Propeller inlet integrated high-speed wind tunnel test equipment and test method

Abstract

The present invention belongs to the field of aviation aerodynamics, specifically relating to a high-speed wind tunnel test apparatus and method for integrated propeller inlet testing. The apparatus includes a propeller and drive system, an inlet model and support system, an inlet flow simulation system, and a data acquisition and processing system. The method comprises the following steps: Step 1: Installing the model, propeller rotor and drive system, flowmeter, and ejector duct; Step 2: Starting the drive motor and controlling the drive motor's power; Step 3: Controlling the rotating measurement rake with an integrated five-hole probe to perform rotational acquisition at a given rotation angle step; Step 4: After the acquisition is complete, first turning off the vacuum ejector and shutting down the wind tunnel. Based on a high-speed wind tunnel, the present invention can simulate the effects of propeller slipstream on inlet performance under subsonic (Ma ≥ 0.3) inflow conditions in the wind tunnel, with the aircraft at a certain attitude and inlet flow rate, and establish process standards for high-speed wind tunnel testing of inlets under the influence of propeller slipstream.

Description

Technical Field

[0001] The present invention belongs to the technical field of aviation aerodynamics, and in particular relates to a propeller inlet integrated high-speed wind tunnel test device and a test method. Background Art

[0002] For turboprop engines, the propeller is usually placed before the engine inlet, i.e., a pull-in propeller. The engine needs to draw air from the propeller slipstream, which makes the internal flow field of the inlet very complex. This not only affects the inlet performance but also may produce large swirl distortion. High-speed inlet wind tunnel testing, as one of the means of evaluating inlet performance, can provide test data support for inlet design. However, existing technologies only have low-speed wind tunnel testing technology for integrated propeller inlets. At the same time, existing inlet wind tunnel tests do not evaluate the swirl conditions at the inlet outlet. There is a lack of test equipment and test methods specifically for high-speed wind tunnel testing of inlets under the influence of propeller slipstream, which makes it impossible to provide more comprehensive test data support for turboprop aircraft inlet design and optimization. Summary of the Invention

[0003] The purpose of the present invention is to provide a propeller inlet integrated high-speed wind tunnel test device and test method to solve the problem in the prior art that there is no special test equipment and test process standard for evaluating the swirl condition at the inlet outlet and studying the mutual influence between the propeller slipstream and the inlet at high Mach numbers.

[0004] The technical solutions adopted in the present invention are as follows:

[0005] Option 1:

[0006] A propeller-inlet integrated high-speed wind tunnel test device, comprising a propeller and drive system, an inlet model and support system, an inlet flow simulation system, and a data acquisition and processing system;

[0007] The propeller and drive system include blades, propeller hub and spinner cap, reducer, drive motor, motor line, encoder line and control cabinet; the inlet duct model and support system include horizontal support plate, measurement section, inlet duct model, wind tunnel support; the inlet duct flow simulation system includes vacuum tank, vacuum injection pipeline, flow meter and wind tunnel injection pipeline; the data acquisition and processing system includes pressure acquisition system and data processing computer;

[0008] The front end of the horizontal support plate is placed in the wind tunnel, and the rear end of the horizontal support plate passes through the wind tunnel and is connected to the wind tunnel support; a drive motor is provided on the horizontal support plate, the output end of the drive motor is connected to the input end of the reducer, the output end of the reducer is connected to the blade through the propeller hub and the propeller cap, and the input end of the drive motor is connected to the control cabinet placed outside the wind tunnel through the motor line and the encoder line;

[0009] The front end of the wind tunnel ejection pipeline is placed in the wind tunnel and connected to the air inlet model through the measuring section. The air inlet model is hoisted under the horizontal support plate through the connecting hoist. The rear end of the encoder line passes through the wind tunnel and is connected to the flow meter, vacuum ejection pipeline, and vacuum tank in sequence.

[0010] A rotating measuring rake with an integrated five-hole probe is built into the measuring section. The pressure measuring hose led out of the rotating measuring rake of the five-hole probe is connected to a pressure acquisition system, and the pressure acquisition system is connected to a data processing computer.

[0011] Furthermore, openings are provided on both sides of the front end of the horizontal support plate, which is fixedly connected to the wind tunnel via two tension lines.

[0012] Furthermore, the connecting hoist is a connecting hoist ring, and the lower part of the horizontal support plate is hoisted and connected to the wind tunnel injection pipeline and the air inlet duct model respectively through two connecting hoist rings.

[0013] Option 2:

[0014] A propeller inlet integrated high-speed wind tunnel test method is implemented using the propeller inlet integrated high-speed wind tunnel test equipment described in Scheme 1, comprising the following steps:

[0015] Step 1: Start the drive motor, control the power of the drive motor through the control cabinet, increase the speed of the propeller rotor to half of the test speed, and wait until the speed of the propeller rotor is stable;

[0016] Step 2: Start the vacuum ejection to simulate the flow field in the inlet duct. After the flow field in the inlet duct stabilizes, open the wind tunnel to achieve a subsonic flow condition of Ma ≥ 0.3 to simulate the flight speed of the aircraft. When the wind tunnel flow field stabilizes, adjust the power of the drive motor to continue to increase the speed of the propeller rotor to the test speed. At the same time, control the flow meter to adjust the inlet flow to reach the flow required for the test state.

[0017] Step 3: After the flow field in the inlet duct stabilizes again, the rotating measurement rake of the integrated five-hole probe is controlled to perform rotational acquisition at a given rotation angle step to obtain the swirl angle on the entire inlet duct outlet cross section. The average swirl intensity at the inlet duct outlet is obtained through data processing;

[0018] Step 4: After the acquisition is completed, turn off the vacuum injection and stop the wind tunnel. After the vacuum injection and wind tunnel stop, reduce the power of the drive motor to gradually reduce the speed of the propeller rotor until it stops rotating. The test is over.

[0019] Beneficial effect: Compared with the existing technology, the beneficial effect of the present invention is that: based on a high-speed wind tunnel, the present application can simulate the influence of propeller slipstream on the inlet performance under the conditions of subsonic (Ma≥0.3) in the wind tunnel and the aircraft at a certain attitude and inlet flow, and formulate the process standard for high-speed wind tunnel testing of the inlet under the influence of propeller slipstream. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a schematic diagram of a test equipment for a high-speed wind tunnel test of an air inlet under the influence of propeller slipstream according to the present invention.

[0021] In the figure: 1. Vacuum tank, 2. Vacuum injection pipeline, 3. Flowmeter, 4. Control cabinet, 5. Wind tunnel injection pipeline, 6. Horizontal support plate, 7. Measuring section, 8. Connecting ring, 9. Inlet duct model, 10. Blade, 11. Propeller hub and spinner cap, 12. Wind tunnel, 13. Wind tunnel support, 14. Motor cable, 15. Encoder cable, 16. Drive motor, 17. Tension wire, 18. Reducer. DETAILED DESCRIPTION

[0022] To make the purpose and technical solutions of the embodiments of the present invention more clear, the technical solutions of the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings of the embodiments of the present invention. Based on the described embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0023] Example 1

[0024] A propeller-inlet integrated high-speed wind tunnel test device, comprising a propeller and drive system, an inlet model and support system, an inlet flow simulation system, and a data acquisition and processing system;

[0025] The propeller and drive system includes blades 10, a propeller hub and spinner cap 11, a reducer 18, a drive motor 16, a motor line 14, an encoder line 15, and a control cabinet 4; the inlet duct model and support system includes a horizontal support plate 6, a measuring section 7, an inlet duct model 9, and a wind tunnel support 13; the inlet duct flow simulation system includes a vacuum tank 1, a vacuum injection pipeline 2, a flowmeter 3, and a wind tunnel injection pipeline 5; the data acquisition and processing system includes a pressure acquisition system and a data processing computer;

[0026] The front end of the horizontal support plate 6 is placed in the wind tunnel 12, and the rear end of the horizontal support plate 6 passes through the wind tunnel 12 and is connected to the wind tunnel support 13; a drive motor 16 is provided on the horizontal support plate 6, and the output end of the drive motor 16 is connected to the input end of the reducer 18, and the output end of the reducer 18 is connected to the blade 10 through the propeller hub and the propeller cap 11, and the input end of the drive motor 16 is connected to the control cabinet 4 placed outside the wind tunnel 12 through the motor line 14 and the encoder line 15;

[0027] The front end of the wind tunnel injection pipe 5 is placed in the wind tunnel 12 and connected to the air intake model 9 through the measuring section 7. The air intake model 9 is hoisted below the horizontal support plate 6 through a connecting hanger. The rear end of the encoder line 15 passes through the wind tunnel 12 and is connected to the flow meter 3, the vacuum injection pipe 2, and the vacuum tank 1 in sequence.

[0028] The measuring section 7 is built with a rotating measuring rake integrated with a five-hole probe. The pressure measuring hose led out of the rotating measuring rake of the five-hole probe is connected to a pressure acquisition system, and the pressure acquisition system is connected to a data processing computer.

[0029] Furthermore, openings are provided on both sides of the front end of the horizontal support plate 6 , which is fixedly connected to the wind tunnel 12 via two tensioning lines 17 .

[0030] Furthermore, the connecting hoist is a connecting hoist ring 8, and the lower part of the horizontal support plate 6 is hoisted and connected to the wind tunnel injection pipeline 5 and the air inlet duct model 9 respectively through two connecting hoist rings 8.

[0031] Example 2

[0032] A propeller inlet integrated high-speed wind tunnel test method is implemented using the propeller inlet integrated high-speed wind tunnel test equipment described in Example 1, comprising the following steps:

[0033] Step 1: Start the drive motor 16, control the power of the drive motor 16 through the control cabinet 4, increase the speed of the propeller rotor to half of the test speed, and wait until the speed of the propeller rotor is stable;

[0034] Step 2: Start the vacuum ejection to simulate the flow field in the inlet duct. After the flow field in the inlet duct stabilizes, the wind tunnel is opened to achieve a subsonic flow condition of Ma ≥ 0.3 to simulate the flight speed of the aircraft. When the flow field in the wind tunnel 12 stabilizes, adjust the power of the drive motor 16 to continue to increase the speed of the propeller rotor to the test speed. At the same time, control the flow meter 3 to adjust the inlet flow to reach the flow rate required for the test state.

[0035] Step 3: After the flow field in the inlet duct stabilizes again, the rotating measurement rake of the integrated five-hole probe is controlled to perform rotational acquisition at a given rotation angle step to obtain the swirl angle on the entire inlet duct outlet cross section. The average swirl intensity at the inlet duct outlet is obtained through data processing;

[0036] Step 4: After the acquisition is completed, turn off the vacuum injection and stop the wind tunnel. After the vacuum injection and wind tunnel stop, reduce the power of the drive motor to gradually reduce the speed of the propeller rotor until it stops rotating. The test is over.

[0037] The above is merely an embodiment of the present invention, and its description is relatively specific and detailed, but it should not be understood as limiting the scope of the present invention. It should be pointed out that those skilled in the art can make a number of modifications and improvements without departing from the concept of the present invention, and these modifications and improvements are all within the scope of protection of the present invention.

Claims

1. A propeller inlet integrated high-speed wind tunnel test equipment, characterized by: Including propeller and drive system, air inlet model and support system, air inlet flow simulation system, data acquisition and processing system; The propeller and drive system include blades (10), a propeller hub and a propeller cap (11), a speed reducer (18), a drive motor (16), a motor line (14), an encoder line (15) and a control cabinet (4); the air inlet model and support system include a horizontal support plate (6), a measuring section (7), an air inlet model (9), and a wind tunnel support (13); the air inlet flow simulation system includes a vacuum tank (1), a vacuum injection pipeline (2), a flow meter (3) and a wind tunnel injection pipeline (5); the data acquisition and processing system includes a pressure acquisition system and a data processing computer; The front end of the horizontal support plate (6) is placed in the wind tunnel (12), and the rear end of the horizontal support plate (6) passes through the wind tunnel (12) and is connected to the wind tunnel support (13); a driving motor (16) is provided on the horizontal support plate (6), the output end of the driving motor (16) is connected to the input end of the reducer (18), the output end of the reducer (18) is connected to the blade (10) through the propeller hub and the propeller cap (11), and the input end of the driving motor (16) is connected to the control cabinet (4) placed outside the wind tunnel (12) through the motor line (14) and the encoder line (15); The front end of the wind tunnel ejection pipeline (5) is placed in the wind tunnel (12) and is connected to the air inlet model (9) through the measuring section (7). The air inlet model (9) is hoisted below the horizontal support plate (6) through the connecting hoist. The rear end of the encoder line (15) passes through the wind tunnel (12) and is connected to the flow meter (3), the vacuum ejection pipeline (2), and the vacuum tank (1) in sequence. The measuring section (7) is built with a rotating measuring rake integrated with a five-hole probe, and the pressure measuring hose led out of the rotating measuring rake of the five-hole probe is connected to the pressure acquisition system, and the pressure acquisition system is connected to the data processing computer.

2. The propeller inlet integrated high-speed wind tunnel test equipment according to claim 1, characterized in that: Openings are provided on both sides of the front end of the horizontal support plate (6), which is fixedly connected to the wind tunnel (12) via two tensioning wires (17).

3. The propeller inlet integrated high-speed wind tunnel test equipment according to claim 2, characterized in that: The connecting hoist is a connecting hoist ring (8), and the lower portion of the horizontal support plate (6) is hoisted and connected to the wind tunnel ejection pipeline (5) and the air inlet duct model (9) respectively through two connecting hoist rings (8).

4. A propeller inlet integrated high-speed wind tunnel test method, implemented using the propeller inlet integrated high-speed wind tunnel test equipment according to any one of claims 1 to 3, characterized in that: The following steps are involved: Step 1: Start the drive motor (16), control the power of the drive motor (16) through the control cabinet (4), increase the speed of the propeller rotor to half of the test speed, and wait until the speed of the propeller rotor is stable; Step 2: Start the vacuum ejection to simulate the flow field of the pipe in the air inlet duct. After the flow field in the air inlet duct is stable, the wind tunnel is opened to achieve the subsonic flow condition of Ma≥0.3 to simulate the flight speed of the aircraft. When the flow field in the wind tunnel (12) is stable, adjust the power of the drive motor (16) to continue to increase the speed of the propeller rotor to the test speed. At the same time, control the flow meter (3) to adjust the air inlet flow to reach the flow required for the test state. Step 3: After the flow field in the inlet duct stabilizes again, the rotating measurement rake of the integrated five-hole probe is controlled to perform rotational acquisition at a given rotation angle step to obtain the swirl angle on the entire inlet duct outlet cross section. The average swirl intensity at the inlet duct outlet is obtained through data processing; Step 4: After the acquisition is completed, turn off the vacuum injection and stop the wind tunnel. After the vacuum injection and wind tunnel stop, reduce the power of the drive motor to gradually reduce the speed of the propeller rotor until it stops rotating. The test is over.

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