Integrated clamp for dovetail tenon turbine blade vibration fatigue test and test method

Abstract

The invention discloses an integrated clamp for a dovetail tenon turbine blade vibration fatigue test and a test method. The integrated clamp comprises an integrated clamp body dovetail tenon turbine blade, wherein one end of the integrated clamp body dovetail tenon turbine blade is provided with a groove clamp port dovetail tenon turbine blade, an outer side surface of the groove clamp port dovetail tenon turbine blade is provided with a groove which is identical to a dovetail tenon in shape and can accommodate the dovetail tenon, and the top portion of the integrated clamp body dovetail tenon turbine blade is provided with an adjusting fastening bolt. The integrated clamp is advantaged in that the blade is prevented from breaking at an R portion of a throat portion of the tenon, the test can be smoothly accomplished, a test target is realized, the quantity of test parts is reduced, and test cost is reduced.

Description

technical field [0001] The invention belongs to the technical field of aero-engine blade testing, and relates to a vibration fatigue test fixture and a testing method for an engine dovetail-shaped tenon turbine blade. Background technique [0002] The turbine blades of the engine have the highest working temperature, the most complex stress, and the most severe environment on the engine. The number of blades is large, the shape is complex, the processing is difficult, and the yield is low. Most of them are made of high-temperature alloys, and the cost of the blades is high. , is one of the core parts of the engine. The fatigue performance of turbine blades directly affects the life and reliability of the engine. The fir tree tenon is the most widely used on the turbine blade of the engine, and the dovetail tenon turbine blade (see figure 1 ) are relatively rare. In order to evaluate the fatigue reserve of dovetail tenon turbine blades, verify the rationality of its proces...

AI Technical Summary

Problems solved by technology

[0003] Referring to the dovetail-shaped tenon fatigue test fixture of the previous compressor blades, the jaw-type fixture and the rear top-type fixture were designed, but because the thickness of the turbine blade body is much larger than that of the compressor blade, the size of the tenon of the turbine blade is compared with the blade body of the assessment part. Relatively small (tenon length 18mm, thickness 6.7mm)

When the two kinds of fixtures commonly used for compressor blades are used for the test, stress concentration occurs at the throat of the tenon of the blade, and the blade breaks from the R of the throat of the tenon, and the blade body cannot be assessed, resulting in the failure of the test

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