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System and method for testing high-temperature mechanical properties of micro samples of complex-configuration turbine blades

A technology of turbine blades and high temperature mechanics, which is applied in scientific instruments, strength characteristics, and the use of stable tension/pressure to test the strength of materials, etc., to achieve the effect of simple and convenient operation and strong versatility

Pending Publication Date: 2020-09-22
BEIHANG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, the above method can only be applied to solid or thick-walled turbine blades

Method used

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  • System and method for testing high-temperature mechanical properties of micro samples of complex-configuration turbine blades
  • System and method for testing high-temperature mechanical properties of micro samples of complex-configuration turbine blades
  • System and method for testing high-temperature mechanical properties of micro samples of complex-configuration turbine blades

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Embodiment Construction

[0044] In order to make the object, technical solution and advantages of the present invention clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention.

[0045]The present invention provides a system and method for testing the high temperature mechanical properties of tiny samples of turbine blades with complex configurations. The specific implementation of the present invention will be described below by taking the sampling of turbine blades of a certain type of aircraft engine and the high temperature tensile and fatigue tests of sampled samples as examples. To elaborate:

[0046] refer to figure 1 In the sampling process, the geometric characteristics of the turbine blades of this type of aero-engine are analyzed first by taking the turbine blad...

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Abstract

The invention belongs to the field of aero-engine turbine blade technology and material mechanical property testing and particularly relates to a complex-configuration turbine blade micro sample high-temperature mechanical property test system and method. The system comprises a material tensile testing machine, a clamp, a load control system and a temperature control system, wherein the load control system comprises a load control computer, a load sensor and a displacement sensor, the temperature control system comprises a box-type resistance heating furnace, a thermocouple and a temperature control box, a turbine blade tiny sample is arranged on a clamp, and the clamp is clamped on a material tensile testing machine. The system is advantaged in that strength evaluation of a turbine bladein service and after repair is achieved, and the system is further suitable for turbine blades with solid and few cooling channels, and a sampling method and a designed special clamp have very high universality.

Description

technical field [0001] The invention belongs to the field of aero-engine turbine blade technology and material mechanical performance testing, in particular to a system and method for testing the high-temperature mechanical properties of tiny samples of turbine blades with complex configurations, and is especially suitable for testing the tiny samples of turbine blades with complex geometric configurations at room temperature and temperature Mechanical properties test at high temperature. Background technique [0002] Aeroengine turbine blades have been in high-speed, high-temperature and gas-corrosion environments for a long time, so changes in the mechanical properties of the blades and materials are inevitable. The change of high-temperature mechanical properties of the blade directly affects the safe service, propulsion performance and maintenance cost of the complete engine. [0003] Turbine blades are expensive, and the easy abandonment of damaged turbine blades makes...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01N3/18G01N3/06G01N3/04
CPCG01N3/04G01N3/06G01N3/18G01N2203/0017G01N2203/0071G01N2203/0073G01N2203/0226G01N2203/06
Inventor 石多奇杨晓光范永升谭龙施祎
Owner BEIHANG UNIV
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