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Suddenly-applied high-energy foundation excitation test bed for laboratory and test method

A laboratory and test bench technology, applied in the field of gas turbine engines, to achieve the effect of convenient regularity research and precise application

Active Publication Date: 2021-01-12
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In the current existing technology, there is no suitable technical solution that can accurately test this kind of sudden high-energy foundation excitation

Method used

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  • Suddenly-applied high-energy foundation excitation test bed for laboratory and test method
  • Suddenly-applied high-energy foundation excitation test bed for laboratory and test method
  • Suddenly-applied high-energy foundation excitation test bed for laboratory and test method

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Embodiment Construction

[0035] A bidirectional excitation tester for a squeeze film damper capable of measuring inlet oil pressure and inlet oil temperature proposed by the present invention will be described below with reference to the accompanying drawings.

[0036] The preferred implementation of the device and method of the present invention will be further fully and detailedly described below in conjunction with the accompanying drawings.

[0037] Apparently, the described embodiments are only some of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0038] The invention discloses a laboratory-used sudden increase high-energy foundation excitation test bench, such as figure 1 , including a simulated engine to be tested 1, a mounting bracket 2, a mounting bracket 3, a drive mot...

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Abstract

The invention discloses a suddenly-applied high-energy foundation excitation test bed for a laboratory. The suddenly-applied high-energy foundation excitation test bed comprises an air cannon, a base,a test bed top borne on the base, a simulation engine installed on the test bed top and a driving motor. The base is connected with the test bed top through a plate-shaped spring or a common multidirectional spring; when the air cannon and the plate-shaped spring are installed on the side face of the test bed, a suddenly-applied lateral high-energy foundation excitation test bed is formed and canbe used for simulating the action working condition of suddenly-applied lateral high-energy foundation excitation when the marine gas turbine is subjected to near-field / far-field explosion; and whenthe air cannon system and the plate-shaped spring are installed in the axial direction of the test bed, the suddenly-applied axial high-energy foundation excitation test bed is formed, and can be usedfor simulating the action working condition of sudden-applied axial high-energy foundation excitation on the aviation gas turbine during arrested deck-landing.

Description

technical field [0001] The invention relates to the field of gas turbine engines, in particular to a test bench and a test method for a gas turbine engine complete machine or a rotor component subjected to sudden high-energy foundation excitation. Background technique [0002] Taking carrier-based aircraft and aircraft carriers as examples, under service conditions, aviation gas turbine engines may encounter blocked landings, and marine gas turbines may encounter near-field / far-field explosions. The sudden high-energy load formed in the engine structure under the above-mentioned harsh working conditions acts on the engine in the form of high-density impact energy, which may cause the deterioration of the dynamic characteristics of the engine / rotor components and damage to key structures, endangering the safety of the engine structure, serious affect its safety. [0003] According to the characteristics of the load, the research on the dynamic response of the gas turbine eng...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M7/06G01M15/14
CPCG01M7/06G01M15/14
Inventor 韩佳奇于飞陈伟赵振华刘璐璐罗刚
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS