Axial expansion self-compensating device for aero-engine turbine part tester

Abstract

The invention belongs to the field of mechanical design, and particularly relates to an axial expansion self-compensating device for an annular runner steering part under high-temperature and high-pressure conditions. The axial expansion self-compensating device for the annular runner steering part under the high-temperature and high-pressure conditions comprises an inner steering shell section and an outer steering shell section, wherein the inner steering shell section and the outer steering shell section are both of an annular structure; one end of the inner steering shell section and one end of the outer steering shell section are connected with a connecting turbine test piece; and the other end of the inner steering shell section and the other end of the outer steering shell section are connected with an exhaust volute or an air inlet volute, wherein annular grooves are formed in the outer sides of the connecting positions of one ends of the inner steering shell section and the outer steering shell section and the connecting turbine test piece, annular sealing rings are arranged in the annular grooves, outer pressing rings are arranged on the outer sides of the inner steeringshell section and the outer steering shell section, the outer pressing rings are connected with the inner steering shell section and the outer steering shell section through bolts, and the inner steering shell section and the outer steering shell section are respectively connected with the turbine test piece in a sealing manner by extruding the sealing rings through the outer pressing rings. According to the axial expansion self-compensating device for the annular runner steering part under the high-temperature and high-pressure conditions, an expansion joint is not used, so that the axial length is shorter, and the application environment of the device is greatly widened.

Description

technical field [0001] The invention belongs to the field of mechanical design, and in particular relates to a self-compensating device for axial expansion of an annular flow path steering component under high temperature and high pressure conditions. Background technique [0002] In the application and test of aero-engines, gas turbines, flue gas turbines and related industries, sometimes it is necessary to divert the passage of high-temperature and high-pressure fluid. To ensure the safe operation of the channel under various working conditions. Contents of the invention [0003] Purpose of the invention: [0004] Provides an axial expansion self-compensating device for aero-engine turbine component testers, which solves the defects of limited application scenarios, low flexibility, and cumbersome installation and disassembly caused by the common structure of high-temperature and high-pressure steering components, and at the same time improves the service life and reduc...

AI Technical Summary

Problems solved by technology

[0004] Provides an axial expansion self-compensating device for aero-engine turbine component testers, which solves the defects of limited application scenarios, low flexibility, and cumbersome installation and disassembly caused by the common structure of high-temperature and high-pressure steering components, and at the same time improves the service life and reduces Design, processing, and maintenance costs, providing steering components capable of expansion self-compensation for high-temperature, high-pressure fluids in various industries

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