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Rotatory test temperature measuring equipment of aircraft engine rotor part

A technology of aero-engine and rotation test, applied in the direction of measuring devices, electric devices, thermometer parts, etc., can solve the problems of cylinder drive mechanism failure, poor reliability of cylinder drive, failure, etc., to achieve convenient installation position and drive reliability high effect

Active Publication Date: 2011-11-09
AECC AVIATION POWER CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The disadvantages of this temperature measuring device are: first, the reliability of the cylinder drive is poor
Since the temperature measurement device is located in a vacuum environment, the cylinder drive mechanism is prone to failure or failure due to leakage
Second, the opening distance of the double-arm scissor lever mechanism is limited, which cannot meet the temperature measurement needs of the rotor assembly with a large axial size
Third, its position must be fixed, it is difficult to adjust the installation position flexibly according to needs, and there are limitations in temperature measurement

Method used

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  • Rotatory test temperature measuring equipment of aircraft engine rotor part
  • Rotatory test temperature measuring equipment of aircraft engine rotor part
  • Rotatory test temperature measuring equipment of aircraft engine rotor part

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Embodiment Construction

[0008] The present invention will be described in further detail below. see figure 2 , aero-engine rotor component rotation test temperature measuring device, including base plate 1, lever bracket 8 and thermocouple assembly, the base of lever bracket 8 is fixed on base plate 1 by lever bracket fixing screw 10, and there is a horizontal lever bracket on lever bracket 8 Shaft hole, lever shaft 9 is arranged in this lever bracket shaft hole.

[0009] The thermocouple assembly consists of a thermocouple holder 13, a set screw 14 and a thermocouple 15. The thermocouple 15 is passed through the thermocouple mounting hole of the thermocouple holder 13, and the set screw 14 locks the thermocouple 15.

[0010] It is characterized in that there is a single-arm lever mechanism composed of an electromagnet drive mechanism, a connecting rod hinge shaft 6, a lever 7, a thermocouple assembly mounting plate 11 and a connecting screw 12. There is a horizontal lever shaft hole in the middle...

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Abstract

The invention belongs to an aircraft engine testing technology and relates to an improvement of rotatory test temperature measuring equipment of an aircraft engine rotor part. The temperature measuring equipment comprises a baseplate (1), a lever bracket (8) and a thermocouple assembly, and is characterized by being provided with a single-arm lever mechanism formed by an electromagnet driving mechanism, a connecting bar hinge shaft (6), a lever (7), a thermocouple assembly mounting plate (11) and a connecting screw (12), wherein the electromagnet driving mechanism comprises an electromagnet mounting base (2), an electromagnet (4) and a connecting bar (5). The temperature measuring equipment has high driving reliability, and can meet the need for measuring the temperature of a rotor assembly with larger axial dimension. The installation position of the temperature measuring equipment can be adjusted freely according to the testing needs.

Description

technical field [0001] The invention belongs to the testing technology of aero-engine, and relates to the improvement of a temperature-measuring device for the rotation test of the rotor part of the aero-engine. Background technique [0002] When aero-engine rotor components such as single disc parts or rotor assemblies are subjected to thermal rotation tests, temperature measurement is a technical difficulty due to the high-speed rotation of the tested components. At present, the structure of a thermocouple temperature measuring device can be found in figure 1 , it consists of a base plate 1, a lever bracket 8, a thermocouple assembly, a cylinder drive mechanism 16 and a double-arm scissor lever mechanism installed on the lever bracket 8. The piston of the cylinder driving mechanism 16 is connected with the left end of the double-arm scissor lever mechanism through a connector 18, and the right end of the double-arm scissor lever mechanism is connected with a thermocouple ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01K1/14G01K7/02
Inventor 杨鑫严萍张兴良王华旭
Owner AECC AVIATION POWER CO LTD
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