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

Abstract

The invention belongs to the technical field of aviation aerodynamic force, and particularly relates to propeller and air inlet integrated high-speed wind tunnel test equipment and a test method. The equipment comprises a propeller and driving system, an air inlet duct model and supporting system, an air inlet duct flow simulation system and a data acquisition and processing system. The method comprises the steps of 1, installing a model, a propeller rotor, a driving system, a flow meter, an injection pipeline and the like; 2, a driving motor is started, and the power of the driving motor is controlled; step 3, controlling the rotary measuring rake integrated with the five-hole probe to perform rotary acquisition of a given rotation angle step length; 4, after collection is completed, vacuum injection is firstly closed, and wind in the wind tunnel is stopped. On the basis of the high-speed wind tunnel, the influence of the propeller slip flow on the performance of the air inlet channel under the conditions of subsonic velocity (Ma > = 0.3) incoming flow in the wind tunnel and certain attitude and air inlet channel flow of an aircraft can be simulated, and the flow standard of the air inlet channel high-speed wind tunnel test under the influence of the propeller slip flow is formulated.

Description

Technical Field

[0001] The present invention belongs to the technical field of aeronautical aerodynamics, and particularly relates to an integrated propeller-inlet high-speed wind tunnel test device and test method. Background Technique

[0002] For turboprop engines, the vast majority have a propeller in front of the engine inlet, that is, a tractor propeller. The engine needs to suck air from the propeller slipstream area, which makes the internal flow field of the inlet very complex. While affecting the performance of the inlet, it may also generate relatively large swirl distortion. And the high-speed wind tunnel test of the inlet, as one of the means for evaluating the performance of the inlet, can provide experimental data support for the design of the inlet. However, in the existing technologies, there is only the integrated low-speed wind tunnel test technology of the propeller-inlet, and at the same time, in the existing inlet wind tunnel tests, the swirl condition at the outlet of the inlet is not evaluated. There is a lack of a test device and test method specifically for the high-speed wind tunnel test of the inlet under the influence of the propeller slipstream, and it is impossible to provide relatively comprehensive experimental data support for the design and optimization of the inlet of turboprop aircraft. Summary of the Invention

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

[0004] The technical solution adopted by the present invention is as follows: Solution 1: An integrated propeller-inlet high-speed wind tunnel test device, including a propeller and drive system, an inlet model and support system, an inlet flow simulation system, and a data acquisition and processing system; The propeller and drive system includes propeller blades, a propeller hub and cap, a speed reducer, a drive motor, motor wires, encoder wires, and a control cabinet; the inlet model and support system includes a horizontal support plate, a measurement section, an inlet model, and a wind tunnel support; the inlet flow simulation system includes a vacuum tank, a vacuum ejector pipeline, a flowmeter, and a wind tunnel ejector pipeline; the data acquisition and processing system includes a pressure acquisition system and a data processing computer; The front end of the horizontal support plate is placed inside 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 arranged on the horizontal support plate, the output end of the drive motor is connected to the input end of the speed reducer, and the output end of the speed reducer is connected to the propeller blades through the propeller hub and cap. The input end of the drive motor is connected to the control cabinet placed outside the wind tunnel through the motor wires and encoder wires; The front end of the wind tunnel ejector pipeline is placed inside the wind tunnel and is connected to the inlet duct model through the measurement section. The inlet duct model is hoisted below the horizontal support plate by a connecting sling; the rear end of the encoder wire passes through the wind tunnel and is successively connected to a flowmeter, a vacuum ejector pipeline, and a vacuum tank. A rotating measuring rake integrated with a five-hole probe is built into the measurement section. The pressure measuring hose led out by 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.

[0005] Furthermore, openings are provided on both sides of the front end of the horizontal support plate and are fixedly connected to the wind tunnel through two wire ropes.

[0006] Furthermore, the connecting sling is a connecting eyebolt, and the lower part of the horizontal support plate is hoisted and connected to the wind tunnel ejector pipeline and the inlet duct model respectively through two connecting eyebolts.

[0007] Solution Two: A method for a high-speed wind tunnel test of a propeller-inlet duct integrated system is realized by using the high-speed wind tunnel test equipment for a propeller-inlet duct integrated system described in Solution One, and includes the following steps: Step 1: Start the driving motor, control the power of the driving motor through the control cabinet, increase the rotational speed of the propeller rotor to half of the test rotational speed, and wait for the rotational speed of the propeller rotor to stabilize. Step 2: Turn on the vacuum ejector to simulate the flow field in the inlet duct. After the flow field in the inlet duct is stable, start the wind tunnel to reach the subsonic flow condition of Ma≥0.3 to simulate the flight speed of the aircraft. When the wind tunnel flow field is stable, adjust the power of the driving motor, continue to increase the rotational speed of the propeller rotor to the test rotational speed, and at the same time control the flowmeter to adjust the inlet duct flow rate to the flow rate required for the test state. Step 3: Again, after the flow field in the inlet duct is stable, control the rotating measuring rake of the integrated five-hole probe to perform rotational acquisition with a given rotational angle step size, obtain the swirl angle on the entire outlet section of the inlet duct, and obtain the surface-averaged swirl intensity at the outlet of the inlet duct through data processing. Step 4: After the acquisition is completed, turn off the vacuum ejector and stop the wind tunnel. After the vacuum ejector and the wind tunnel stop, reduce the power of the driving motor to gradually decrease the rotational speed of the propeller rotor until it stops rotating, and the test ends.

[0008] Beneficial Effects: Compared with the prior art, the beneficial effects of the present invention are as follows: Based on a high-speed wind tunnel, the present application can simulate the influence of the propeller slipstream on the performance of the inlet duct under the subsonic (Ma≥0.3) flow condition in the wind tunnel, at a certain attitude of the aircraft and a certain inlet duct flow rate, and formulate a process standard for a high-speed wind tunnel test of the inlet duct under the influence of the propeller slipstream. Description of the Drawings

[0009] Figure 1It is a schematic diagram of the test equipment for the high-speed wind tunnel test of the intake duct under the influence of the propeller slipstream of the present invention.

[0010] In the figure: 1. Vacuum tank, 2. Vacuum ejector pipeline, 3. Flowmeter, 4. Control cabinet, 5. Wind tunnel ejector pipeline, 6. Horizontal support plate, 7. Measurement section, 8. Connection sling, 9. Intake duct model, 10. Propeller blade, 11. Propeller hub and cap, 12. Wind tunnel, 13. Wind tunnel support, 14. Motor wire, 15. Encoder wire, 16. Driving motor, 17. Taut wire, 18. Reducer. Detailed implementation manners

[0011] To make the objectives and technical solutions of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Based on the described embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the scope of protection of the present invention.

[0012] Embodiment 1 A propeller-intake duct integrated high-speed wind tunnel test equipment includes a propeller and drive system, an intake duct model and support system, an intake duct flow simulation system, and a data acquisition and processing system; The propeller and drive system includes a propeller blade 10, a propeller hub and cap 11, a reducer 18, a driving motor 16, a motor wire 14, an encoder wire 15, and a control cabinet 4; the intake duct model and support system includes a horizontal support plate 6, a measurement section 7, an intake duct model 9, and a wind tunnel support 13; the intake duct flow simulation system includes a vacuum tank 1, a vacuum ejector pipeline 2, a flowmeter 3, and a wind tunnel ejector 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 inside 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 arranged 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 propeller blade 10 through the propeller hub and 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 wire 14 and the encoder wire 15; The front end of the wind tunnel ejector pipeline 5 is placed inside the wind tunnel 12 and is connected to the intake duct model 9 through the measurement section 7, and the intake duct model 9 is hoisted below the horizontal support plate 6 through a connection sling; the rear end of the encoder wire 15 passes through the wind tunnel 12 and is sequentially connected to the flowmeter 3, the vacuum ejector pipeline 2, and the vacuum tank 1; A rotating measuring rake with an integrated five-hole probe is built into the measurement section 7. The pressure measuring hose led out by 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.

[0013] Furthermore, openings are provided on both sides of the front end of the horizontal support plate 6 and are fixedly connected to the wind tunnel 12 through two wire ropes 17.

[0014] Furthermore, the connecting sling is a connecting eyebolt 8. The lower part of the horizontal support plate 6 is respectively hoisted and connected to the wind tunnel ejector pipeline 5 and the intake duct model 9 through two connecting eyebolts 8.

[0015] Embodiment 2 A method for high-speed wind tunnel test of a propeller-intake duct integration is realized by using the high-speed wind tunnel test equipment for propeller-intake duct integration described in Embodiment 1, and includes the following steps: Step 1: Start the driving motor 16, control the power of the driving motor 16 through the control cabinet 4, increase the rotational speed of the propeller rotor to half of the test rotational speed, and wait for the rotational speed of the propeller rotor to stabilize. Step 2: Turn on the vacuum ejector to simulate the flow field in the intake duct. After the flow field in the intake duct is stable, start the wind tunnel to reach the subsonic flow condition of Ma≥0.3 to simulate the flight speed of the aircraft. When the flow field of the wind tunnel 12 is stable, adjust the power of the driving motor 16 to continue increasing the rotational speed of the propeller rotor to the test rotational speed, and at the same time control the flowmeter 3 to adjust the intake duct flow rate to make it reach the flow rate required for the test state. Step 3: Again, after the flow field in the intake duct is stable, control the rotating measuring rake of the integrated five-hole probe to perform rotational acquisition with a given rotational angle step length, obtain the swirl angle on the entire outlet section of the intake duct, and obtain the area-averaged swirl intensity at the outlet of the intake duct through data processing. Step 4: After the acquisition is completed, turn off the vacuum ejector and stop the wind tunnel. After the vacuum ejector and the wind tunnel stop, reduce the power of the driving motor to gradually reduce the rotational speed of the propeller rotor until it stops rotating, and the test ends.

[0016] The above are only the embodiments of the present invention. The description is relatively specific and detailed, but it should not be construed as a limitation to the scope of the patent of the present invention. It should be noted that for those of ordinary skill in the art, without departing from the concept of the present invention, several deformations and improvements can still be made, and these all belong to the protection scope of the present invention.

Claims

1. An integrated high-speed wind tunnel test equipment for a propeller air intake, characterized in that: It includes a propeller and drive system, an inlet duct model and support system, an inlet duct flow simulation system, and a data acquisition and processing system; The propeller and drive system includes blades (10), a propeller hub and cap (11), a speed reducer (18), a drive motor (16), motor wires (14), encoder wires (15), and a control cabinet (4); the inlet duct model and support system includes a horizontal support plate (6), a measurement 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 ejector pipeline (2), a flowmeter (3), and a wind tunnel ejector 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 inside 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), the output end of the drive motor (16) is connected to the input end of the speed reducer (18), and the output end of the speed reducer (18) is connected to the blades (10) through the propeller hub and cap (11). The input end of the drive motor (16) is connected to the control cabinet (4) placed outside the wind tunnel (12) through the motor wires (14) and encoder wires (15); The front end of the wind tunnel ejector pipeline (5) is placed inside the wind tunnel (12), and is connected to the inlet duct model (9) through the measurement section (7). The inlet duct model (9) is hoisted below the horizontal support plate (6) through a connecting sling; the rear end of the encoder wire (15) passes through the wind tunnel (12) and is sequentially connected to the flowmeter (3), the vacuum ejector pipeline (2), and the vacuum tank (1); A rotating measurement rake integrated with a five-hole probe is built into the measurement section (7). The pressure measurement hose led out by the rotating measurement 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 integrated high-speed wind tunnel test equipment for a propeller air intake duct according to claim 1, characterized in that: Openings are provided on both sides of the front end of the horizontal support plate (6), and are fixedly connected to the wind tunnel (12) through two tension wires (17).

3. The integrated high-speed wind tunnel test equipment for a propeller air intake duct according to claim 2, characterized in that: The connecting sling is a connecting eyebolt (8). The lower part of the horizontal support plate (6) is hoisted and connected to the wind tunnel ejector pipeline (5) and the inlet duct model (9) respectively through two connecting eyebolts (8).

4. A method for high-speed wind tunnel test of integrated propeller inlet duct is realized by using the integrated high-speed wind tunnel test equipment of propeller inlet duct described in any one of claims 1-3, and is characterized in that It includes the following steps: Step 1, start the drive motor (16), control the power of the drive motor (16) through the control cabinet (4), increase the rotational speed of the propeller rotor to half of the test rotational speed, and wait for the rotational speed of the propeller rotor to stabilize; Step 2, turn on the vacuum ejector to simulate the flow field in the inlet duct. After the flow field in the inlet duct is stable, the wind tunnel is turned on to reach the subsonic incoming 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), continue to increase the rotational speed of the propeller rotor to the test rotational speed, and at the same time control the flowmeter (3) to adjust the inlet duct flow rate to make it reach the flow rate required for the test state; Step 3: After the flow field in the intake duct stabilizes again, control the rotating measurement rake of the integrated five-hole probe to perform rotational acquisition with a given rotational angle step, obtain the swirl angle on the entire outlet section of the intake duct, and obtain the area-averaged swirl intensity at the outlet of the intake duct through data processing. Step 4: After the acquisition is completed, turn off the vacuum ejector and stop the wind tunnel. After the vacuum ejector and the wind tunnel stop, reduce the power of the drive motor to gradually decrease the rotational speed of the propeller rotor until it stops rotating, and the test ends.

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