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A full-scale propeller blade icing wind tunnel test method

A technology of wind tunnel test and propeller, which is applied in the field of wind tunnel test, can solve problems such as inability to calibrate, and achieve the effect of a reliable positioning method

Active Publication Date: 2021-08-06
LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

For the 1:1 size propeller, it is installed and tested in the wind tunnel, because the shape of the propeller has a certain degree of distortion, it is impossible to accurately calibrate the angular position of different sections by conventional measurement means, because the existing wind There is no relevant project work in the hole test, so it is necessary to design a reasonable and effective test method to facilitate the development of the propeller blade safety assessment test.

Method used

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  • A full-scale propeller blade icing wind tunnel test method
  • A full-scale propeller blade icing wind tunnel test method
  • A full-scale propeller blade icing wind tunnel test method

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0045] In a certain test, the tested section needs to be tested at 26°.

[0046] Firstly, the preset angle value of the section is obtained from the design model of the propeller blade to be 17°, and then the blade is rotated to make the chord line of the truncated section parallel to the laser line. Use 26° to subtract 17° to get an angle of 9°, and then rotate 9° through the turntable to get the final test angle.

[0047] Then start the motor to adjust the wind speed to the test wind speed (such as 120m / s), then start the refrigeration system, adjust the temperature to the test temperature (such as -15°C), and adjust the number of nozzles used in the spray system (such as 1000) and water vapor Pressure (such as 0.2MPa, 0.18MPa), adjust the cloud parameter water droplet diameter and liquid water content to the test requirements (such as 20μm, 0.5g / m 3 ). Then open the solenoid valve in front of the nozzle, start spraying, and the test begins.

Embodiment 2

[0049] In a certain test, the tested section needs to be tested at 30°.

[0050] Firstly, the preset angle value of the section is obtained from the design model of the propeller blade -21°, and then the blade is turned to make the chord line of the truncated section parallel to the laser line.

[0051] Subtract -21° from 30° to obtain an angle of 51°, and then rotate the turntable by 51°, which is the final test angle.

[0052] Then start the motor to adjust the wind speed to the test wind speed (such as 180m / s), then start the refrigeration system, adjust the temperature to the test temperature (such as -25°C), and adjust the number of nozzles used in the spray system (such as 1000) and water vapor Pressure (such as 0.2MPa, 0.15MPa), adjust the cloud parameter water droplet diameter and liquid water content to the test requirements (such as 20μm, 0.5g / m3). Then open the solenoid valve in front of the nozzle, start spraying, and the test begins.

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Abstract

The invention discloses a full-scale propeller blade icing wind tunnel test method. First, the tip of the full-size blade is truncated in the length direction to fit the size of the wind tunnel, and then the blade is installed vertically on the wind tunnel turntable and the chord line on the truncated section is adjusted parallel to the horizontal line of the wind tunnel to determine The installation angle of the blade, and then deduct the initial angle between the section chord line and the blade angle chord line according to the test requirements to obtain the actual rotation angle of the blade. The invention provides a feasible method for the full-scale propeller icing wind tunnel test, and also solves the current problem that the full-scale propeller blades cannot be positioned in the wind tunnel. If the angle cannot be determined, relevant tests cannot be carried out .

Description

technical field [0001] The invention relates to the field of wind tunnel tests, in particular to a full-scale propeller blade icing wind tunnel test method. Background technique [0002] According to the requirements of Part 33 of my country's Civil Aviation Regulations "Aircraft Engine Airworthiness Standards" (CCAR-33), under the continuous maximum or intermittent maximum icing state specified in Appendix C of Part 25 of China's Civil Aviation Regulations, the engine is in its entire During operation within the flight power range, there should be no icing on engine parts that would affect engine operation or cause serious loss of power or thrust. Therefore, in the process of aero-engine type certification, the icing wind tunnel test has become a necessary compliance method to verify whether the engine meets the requirements of the icing clause in CCAR-33. [0003] As an important part of a turboprop engine, the propeller must carry out an icing wind tunnel test to verify w...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64F5/60
CPCB64F5/60
Inventor 赖庆仁郭龙杨升科吕波孙冬宁
Owner LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT