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A high-temperature test method for an afterburner ignition nozzle of an aero-engine

An aero-engine and high-temperature test technology, which is applied in the direction of engine ignition, engine components, machines/engines, etc., can solve the problems of afterburner ignition nozzles not working, breaking, etc.

Active Publication Date: 2022-03-29
SHAANXI AVIATION ELECTRICAL
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

When the nozzle works at high temperature again, it will generate a certain tensile stress on the center electrode assembly again. With the extension of the working time, the tensile stress will accumulate and the weak part (welding part) of the center electrode assembly will break, which will cause the afterburner ignition nozzle to not work.

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  • A high-temperature test method for an afterburner ignition nozzle of an aero-engine

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Embodiment Construction

[0023] In order to make the objectives, technical solutions and advantages of the implementation of the application clearer, the technical solutions in the implementation modes of the application will be described in more detail below with reference to the drawings in the implementation modes of the application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the present application. The embodiments described below by referring to the figures are exemplary and are intended to explain the present application, and should not be construed as limiting the present application. Based on the implementation manners in this application, all other implementation manners obtained by persons of ordinary skill in the art without creative efforts fall within the scope of protection of this application. Embodiments of the pr...

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Abstract

The application provides a high-temperature test method for a booster ignition nozzle of an aero-engine, comprising: assembling the booster ignition nozzle with an ignition cable and an ignition device to form an ignition system and fixing them; Set a first high-frequency induction coil at the end, and set a second high-frequency induction coil at the root of the booster ignition nozzle, and both the first high-frequency induction coil and the second high-frequency induction coil are connected to the high-frequency induction heating test Equipment; control the heating of the first high-frequency induction coil to 940°C-960°C, control the heating of the second high-frequency induction coil to 740°C-760°C; turn on the power supply of the ignition system, work according to the electric nozzle for 3 minutes, rest 10 minutes is a cycle, perform 100 cycles; check whether the core rod inside the electric mouth is bent or broken. This application conducts engine high-temperature work simulation tests on the improved part of the modified afterburner ignition nozzle to ensure that it can meet the actual working needs of the aero-engine.

Description

technical field [0001] The invention belongs to the technical field of ignition device tests, and in particular relates to a high-temperature test method for an afterburner ignition nozzle of an aero-engine. Background technique [0002] The demand for high temperature in the afterburner ignition nozzle agreement includes two aspects: [0003] (1) The discharge end of the nozzle should be able to withstand a high temperature of 1100°C; [0004] (2) The maximum long-term working temperature of the nozzle: 180°C; the maximum short-term working temperature: 215°C; [0005] When designing the discharge end of the nozzle, the outer casing and central electrode of the discharge end are made of GH3044 superalloy, which can withstand a high temperature of 1400°C. The internal semiconductor block and ceramic parts are also heat-resistant materials, which can meet the high temperature requirement of 1100°C in the agreement. The afterburner ignition nozzle is subjected to a high-temp...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02P17/00
CPCF02P17/00
Inventor 张宁李星星曹秀梅
Owner SHAANXI AVIATION ELECTRICAL