Moderate thrust aero-engine testing switching device

Abstract

The invention provides a moderate thrust aero-engine testing switching device comprising a pedestal, air inlet openings, an inner sealing ring, an upper cover disc, and a pressing plate. The pedestal in the shape of a ring, and is provided with an annular-shaped concave groove. The inner sealing ring is disposed on the inner side top part of the annular-shaped concave groove of the pedestal, and the upper cover disc is disposed on the outer side top part of the annular-shaped concave groove of the pedestal. The outer side surface of the pedestal is provided with more than twenty air inlet openings facing the outer side horizontally, and the air inlet openings are disposed uniformly along the circumference of the pedestal. The position of the pressing plate in the annular-shaped concave groove is fixedly disposed on the bottom surface of the upper cover disc by the bolt. The moderate thrust aero-engine testing switching device is advantageous in that the test of the air flow between the high pressure turbine disc and low pressure turbine disc is simple and convenient, the assembly and the disassembly are easy, and the connection with the device of the test board is convenient; the flow measurement is accurate, and the flowing of the air flow is good.

Description

technical field [0001] The invention relates to a test adapter device for a medium-thrust aero-engine. Background technique [0002] In the medium thrust aeroengine test, it is necessary to conduct an air flow test between the high and low pressure turbine disks. During the test, it is necessary to control the cold air flow path, reduce the working temperature of the turbine blades, meet the cooling requirements of the working blades, and ensure an appropriate clearance between the rotor and the rotor. , to meet the air system seal, there is no suitable device in the prior art to directly complete the test, and it needs to use other devices to perform the test in multiple steps, which is very troublesome and easy to make mistakes. Contents of the invention [0003] In order to solve the above-mentioned technical problems, the present invention provides a medium-thrust aero-engine test adapter device, which through a reasonable structure ensures that the airflow test betwee...

AI Technical Summary

Problems solved by technology

[0002] In the medium thrust aeroengine test, it is necessary to conduct an air flow test between the high and low pressure turbine discs. During the test, it is necessary to control the cold air flow path, reduce the working temperature of the turbine blades, meet the cooling requirements of the working blades, and ensure an appropriate clearance between the rotor and the rotor. , to meet the tightness of the air system, there is no suitable device in the prior art that can directly complete the test, and it needs to use other devices to carry out the test in multiple steps, which is very cumbersome and error-prone

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