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Method for measuring distortion degree of blade profile in rotating state of engine rotor blades

A technology of rotating state and rotor blades, which is applied in the direction of engine components, machines/engines, mechanical equipment, etc., and can solve the problems of undisclosed measurement of rotor blade rotating state blade shape, measurement difficulties, etc.

Active Publication Date: 2019-08-13
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Although the measurement technology of the blade shape in the static state is quite mature, it is very difficult to measure due to the high-speed rotation of the rotor blade and the limited space during its operation.
So far, there is no published technique for measuring rotor blade rotational state airfoil

Method used

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  • Method for measuring distortion degree of blade profile in rotating state of engine rotor blades
  • Method for measuring distortion degree of blade profile in rotating state of engine rotor blades
  • Method for measuring distortion degree of blade profile in rotating state of engine rotor blades

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0077] Embodiment 1: A method for measuring the degree of distortion of an engine rotor blade in a rotating state,

[0078] (1) Calibration steps of the laser sensor before measurement.

[0079] (2) Install the laser tip timing sensor: when the blade is in a static state, install the laser tip timing sensor distributed along the axial direction at the highest part of the casing corresponding to the blade. The axial distance set by the laser tip timing sensor is: 10% of the chord length of the parietal blade; said laser tip timing sensors are at least three, and one of them must include a laser tip timing sensor located at 50%; and keep the laser tip timing sensor in a horizontal state, It is used to ensure that the sensing end of the laser tip timing sensor is parallel to the blade top, and to determine the distance from the sensing end of the laser tip timing sensor to the rotation center of the blade hub; figure 1 , the installation schematic diagram of the measuring device...

Embodiment 2

[0132] Embodiment 2 is the same as Embodiment 1, except that there are three laser blade tip timing sensors, which must include a laser blade tip timing sensor set at 50%;

[0133] In the step (1), three laser tip timing sensors distributed along the axial direction are installed at the top of the casing corresponding to the blade, that is, the attached Image 6 , the axial distances set by the laser tip timing sensor correspond to the 25%, 50%, and 75% chord lengths of the blade tip respectively. After step (3), four point coordinates of the front and rear edges of the blade can be obtained, as attached Figure 7 shown. attached Figure 8 Shown are the tip clearance values ​​measured by the laser tip timing sensor at 50% of the chord length. The signals received by the laser blade tip timing sensors placed at 25% and 75% of the chord length of the blade tip are respectively: the first signal and the second signal, as attached Figure 9 ;

[0134] at ΔT 1 During the period ...

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PUM

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Abstract

The invention relates to the technical field of gas turbines, in particular to an engine blade profile real-time monitoring method for monitoring distortion degree of blade profile during hot and coldconversion. The method for measuring the distortion degree of a blade profile in a rotating state of engine rotor blades mainly comprises steps of mounting a laser blade tip timing sensor, measuringthe distortion degree through the laser blade tip timing sensor when the blades rotate at a fixed rotation speed and calculating the blade profile. A cycle is formed through obtained blade tip geometric parameters of one blade, multiple cycles are formed in this way, the blade tip geometric parameters of the multiple blades are obtained, thus, blade tip blade profile geometry of each rotor blade of an engine is monitored in real time, and real-time monitoring of the fidelity of the blade profile design during hot and cold conversion is achieved.

Description

technical field [0001] The invention relates to the technical field of gas turbines, in particular to a method for real-time monitoring of the distortion degree of an engine blade profile during heat-to-cool conversion. Background technique [0002] Rotor blades are an indispensable part of turbomachinery to achieve heat-power conversion. In aero-engines and gas turbines, the rotor blades rotate at thousands or even tens of thousands of speeds, and the linear speed of the blade tip is as high as 500 m / s, which bears a large centrifugal force and also bears a high aerodynamic load. Under the action of strong centrifugal force and aerodynamic load, the blade will produce significant deformation. In the design of turbomachinery blades, the designed blade corresponds to the blade under the centrifugal force and aerodynamic load at the design speed, which is called the hot blade type; the blade has no centrifugal force and aerodynamic load during manufacturing, and its blade typ...

Claims

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Application Information

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IPC IPC(8): F01D21/00G06F17/50
CPCF01D21/003F05D2240/30G06F30/17G06F30/20
Inventor 王丁喜时瑞超何智霖
Owner NORTHWESTERN POLYTECHNICAL UNIV