CN-116085056-B - Method for prolonging service life of turbine disk

CN116085056BCN 116085056 BCN116085056 BCN 116085056BCN-116085056-B

Abstract

A method for prolonging the service life of a turbine disk relates to the technical field of turbine disks of aeroengines. The method comprises the steps of heating a first area of a turbine disc, heating a second area of the turbine disc, obtaining a first real-time temperature of the first area and a second real-time temperature of the second area, stopping heating the first area if the first real-time temperature reaches a first temperature threshold corresponding to the first area, stopping heating the second area if the second real-time temperature reaches a second temperature threshold corresponding to the second area, and enabling the first temperature threshold and the second temperature threshold to be different. The controllable elastoplastic deformation of the turbine disc is caused by heating different areas of the turbine disc at different temperatures, and the tip of the crack can be passivated, so that the damage tolerance is improved, the fatigue life of the center hole of the turbine disc is prolonged, and the aim of remarkably prolonging the working life of the turbine disc is fulfilled.

Inventors

ZENG WEIHU
ZHOU XIAOMING
WANG XUQING
FENG YEFEI
ZOU JINWEN
LUO XUEJUN

Assignees

中国航发北京航空材料研究院

Dates

Publication Date: 20260512
Application Date: 20230210

Claims (6)

1. A method of improving the operational life of a turbine disk, the turbine disk having a plurality of distinct regions, the distinct regions including at least a first region and a second region, the turbine disk surface being profiled with speckle, the method comprising: Heating the first region and the second region with a temperature gradient respectively; acquiring a first real-time temperature of the first area and a second real-time temperature of the second area; if the first real-time temperature reaches a first temperature threshold corresponding to the first region, stopping heating the first region; If the second real-time temperature reaches a second temperature threshold corresponding to the second region, stopping heating the second region, wherein the first temperature threshold is different from the second temperature threshold; Insulating the first region by the first temperature threshold value, and insulating the second region by the second temperature threshold value; rotating the turbine disk after stopping heating and maintaining the first region and stopping heating and maintaining the second region; determining the strain condition of an inner hole area of a disk center of the turbine disk according to the displacement condition of the speckles when the turbine disk rotates; And when the strain condition of the inner hole area of the disk center of the turbine disk reaches a preset strain threshold, decelerating the turbine disk until the duration after maintaining deceleration reaches a preset time threshold, and controlling the turbine disk to stop rotating, wherein the preset strain threshold is a plastic strain threshold which is determined according to a material low-cycle fatigue test and is used for introducing target residual compressive stress into the inner hole area.
2. The method of claim 1, wherein the first zone is provided with a first thermocouple and the second zone is provided with a second thermocouple, and wherein the heating the first zone and the second zone with a temperature gradient, respectively, comprises: And heating the first region and the second region with a temperature gradient by respectively supplying power to the first thermocouple and the second thermocouple.
3. The method of claim 2, wherein a ratio of heating power of the first thermocouple to the second thermocouple is a ratio of the first temperature threshold to the second temperature threshold.
4. The method of claim 1, wherein the displacement of the speckle as the turbine wheel rotates is obtained by: And shooting the turbine disc during rotation through a high-speed camera, and acquiring the displacement condition of the speckles during rotation of the turbine disc.
5. The method of claim 1, wherein the method of making the speckle comprises: And spraying a matte paint and a developer on the surface of the turbine disk by using a speckle spraying device so as to manufacture a speckle pattern layer.
6. The method of claim 1, wherein the determining of the strain condition of the inner bore region of the hub of the turbine disk comprises: based on TEMA software, a strain condition of an inner hole region of a hub of the turbine disk is determined.

Description

Method for prolonging service life of turbine disk Technical Field The application relates to the technical field of turbine disks of aeroengines, in particular to a method for prolonging the service life of a turbine disk. Background The turbine disk of the aeroengine is a core component of a modern aircraft engine, and is pushed by high-temperature fuel gas in a combustion chamber of the engine, so that the heat energy of the fuel gas is converted into mechanical energy, and the engine is driven to operate. However, the turbine disk rotates at a high speed during operation, and thus the turbine disk generates a large centrifugal load, and the centrifugal load generated by the rotation requires the turbine disk itself to carry. According to the elastoplasticity theory, centrifugal load is larger and larger along the radial direction from the outer edge of the turbine disk to the inner edge, namely, the load born by an inner hole area closer to the center of the turbine disk is larger, so that the inner hole is easy to be a weak point of fatigue fracture of the turbine disk, and the failure of the turbine disk of an engine in the working process is usually the fatigue fracture of the inner hole area of the center of the disk. Therefore, how to increase the service life of the inner hole area of the disk center of the turbine disk of the engine is a technical problem to be solved. Disclosure of Invention The application provides a method for prolonging the service life of a turbine disk, which can prolong the fatigue life of an inner hole area of a turbine disk core of an engine. The application discloses the following technical scheme: In a first aspect, the present application discloses a method of improving the operational life of a turbine disk having a plurality of distinct regions including at least a first region and a second region, the method comprising: heating a first region of the turbine disk and heating a second region of the turbine disk; acquiring a first real-time temperature of the first area and a second real-time temperature of the second area; if the first real-time temperature reaches a first temperature threshold corresponding to the first region, stopping heating the first region; and stopping heating the second region if the second real-time temperature reaches a second temperature threshold corresponding to the second region, wherein the first temperature threshold is different from the second temperature threshold. Optionally, the first region is provided with a first thermocouple, the second region is provided with a second thermocouple, and the heating the first region of the turbine disk comprises: Heating a first region of the turbine disk by powering the first thermocouple; The heating of the second region of the turbine disk includes: and heating a second region of the turbine disk by supplying power to the second thermocouple. Optionally, the ratio of the heating power of the first thermocouple to the second thermocouple is the ratio of the first temperature threshold to the second temperature threshold. Optionally, the method further comprises: And carrying out heat preservation on the first area by the first temperature threshold value, and carrying out heat preservation on the second area by the second temperature threshold value. Optionally, the turbine disk surface is painted with speckles, the method further comprising: rotating the turbine disk; acquiring the displacement of the speckles when the turbine rotates; and obtaining the strain condition of the inner hole area of the disk center of the turbine disk according to the displacement of the speckles. Optionally, the acquiring the displacement of the speckle when the turbine wheel rotates includes: And acquiring displacement of the speckles when the turbine disc rotates by shooting the turbine disc through a high-speed camera. Optionally, the method further comprises: And if the strain condition of the inner hole area of the disk center of the turbine disk reaches a preset strain threshold, the turbine disk is decelerated until the turbine disk stops rotating. Optionally, the method for manufacturing the speckles comprises the following steps: And spraying a matte paint and a developer on the surface of the turbine disk by using a speckle spraying device so as to manufacture a speckle pattern layer. Optionally, the acquiring the strain condition of the inner hole area of the hub of the turbine disk includes: and acquiring the strain condition of an inner hole area of a disk center of the turbine disk based on TEMA software. Optionally, before said decelerating said turbine disc, said method further comprises: Maintaining the rotation speed of the turbine disc, and enabling the time for maintaining the rotation speed of the turbine disc to reach a preset time threshold. Compared with the prior art, the application has the following beneficial effects: The application provides a method for prolonging the service life