High-temperature large-load test fixture and test method for turbine blade joggle joint structure

Abstract

The invention relates to a high-temperature large-load test fixture and test method for a turbine blade joggle joint structure, which can be used for test loading of thermal mechanical fatigue, creep-fatigue, low-cycle fatigue, creep and the like of the turbine blade joggle joint structure. The upper end and the lower end of the fixture are respectively connected with a fatigue testing machine through a clamping component, and the clamping components are connected with a turbine blade upper fixture and a turbine blade lower fixture through dovetail-shaped joggle joint structures; the turbine blade upper fixture is mainly composed of two components, a cold water channel is formed in the turbine blade upper fixture, a turbine blade is installed in an inner cavity formed by the two components, and the installation and positioning of the turbine blade and the blade upper fixture and the transmission of an axial load are achieved through a pair of inclined planes of the root extending section; the lower fixture is made of a high-temperature alloy material and is matched with a turbine blade tenon through a longitudinal tree-shaped mortise, and the blade joggle joint structure can be heated by using an induction heating coil. According to the invention, stable clamping of the turbine blade is realized, and the test requirements of applying a temperature load ranging from room temperature to 500 DEG C and a mechanical load from 0N to 150kN to the joggle joint structure can be met.

Description

Technical field [0001] The invention belongs to the field of turbine blade tenon joint structure testing, and particularly relates to a high temperature and large load test fixture and test method for a turbine blade tenon joint structure, which can perform high temperature and large load fatigue on the turbine blade tenon joint structure under laboratory conditions Load environment simulation, based on this, can perform composite fatigue tests such as turbine blade thermomechanical fatigue, test the life of the turbine blade tenon structure, and provide guarantee for the safe and reliable operation of the gas turbine engine. It belongs to the field of gas turbine engine technology. Background technique [0002] The turbine blades of a gas turbine engine work in extreme environments of high temperature, high pressure, and high speed. Under such a complex load environment, the mortise joint structure is prone to fatigue failure. Turbine blades are one of the core components of gas...

AI Technical Summary

Problems solved by technology

[0008] The technical problem to be solved by the present invention is to overcome the deficiencies of the prior art, provide a high-temperature and large-load test fixture and test method for the tenon joint structure of the turbine blade, and overcome the high temperature of 500°C and the pressure of 150 kN applied to the tenon joint structure of the turb

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