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A Turbine Tip Clearance Adjustment Device for Simulated Turbine Performance Test

A technology for turbine performance and testing, used in safety devices, machines/engines, leak prevention, etc., to save cycle and cost

Active Publication Date: 2022-07-15
AECC SHENYANG ENGINE RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The purpose of this application is to provide a turbine blade tip clearance adjustable device for simulated turbine performance tests to solve at least one problem in the prior art

Method used

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  • A Turbine Tip Clearance Adjustment Device for Simulated Turbine Performance Test
  • A Turbine Tip Clearance Adjustment Device for Simulated Turbine Performance Test

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Embodiment Construction

[0028] In order to make the implementation purpose, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. Throughout the drawings, the same or similar reference numbers refer to the same or similar elements or elements having the same or similar functions. The described embodiments are some, but not all, of the embodiments of the present application. The embodiments described below with reference to the accompanying drawings are exemplary, and are intended to be used to explain the present application, but should not be construed as a limitation to the present application. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative work fall within the protection scope of the present ap...

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Abstract

The application belongs to the field of aero-engine turbine blades, and in particular relates to a turbine blade tip clearance adjustment device for a simulated turbine performance test. Including: outer ring, casing, connecting rod, compression spring and adjusting nut. The outer ring includes a plurality of sector segments, and the non-flow channel side of each sector segment is provided with a first mounting seat; the casing is sleeved on the outer side of the outer ring, the casing is provided with a second mounting seat, and the second mounting seat is on the second mounting seat. A through hole is opened, and an external thread is arranged on the second mounting seat; one end of the connecting rod is provided with a first positioning block, and the other end is threadedly connected to the first mounting seat through the through hole on the second mounting seat; the compression spring sleeve Set on the connecting rod, one end of the compression spring abuts the first positioning block of the connecting rod, and the other end abuts the second mounting seat; The mounting seat is threadedly connected, and the radial height of the outer ring is changed by adjusting the length of the screw thread of the adjusting nut and the second mounting seat.

Description

technical field [0001] The application belongs to the field of aero-engine turbine blades, and in particular relates to a turbine blade tip clearance adjustment device for a simulated turbine performance test. Background technique [0002] The simulated state turbine performance test is a test project to verify the aero-engine turbine aerodynamic performance under simulated state (lower temperature and pressure conditions). Because the turbine tip clearance (that is, the radial clearance between the turbine rotor blade tip and the stator flow channel) is an important factor affecting the turbine aerodynamic performance, in order to more comprehensively grasp the influence degree and law of the turbine tip clearance on the turbine aerodynamic performance , the simulated state turbine performance test sometimes needs to carry out variable clearance test, that is, to measure the turbine aerodynamic performance under different blade tip clearance conditions. [0003] At present...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D11/00F01D21/00F01D25/00F01D25/28
CPCF01D21/00F01D21/003F01D11/001F01D25/00F01D25/285
Inventor 陈浩傅依顺
Owner AECC SHENYANG ENGINE RES INST