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Pressurization visual combustion test device of combustor of gas turbine

A technology of gas turbine and combustion test, applied in the direction of measuring device, engine test, machine/structural component test, etc., to achieve the effect of cheap material, good perspective and simple processing technology

Active Publication Date: 2014-02-19
HARBIN TURBINE +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] In order to solve the problem that there is no experimental device specially used for gas turbine combustor test, the present invention further proposes a gas turbine combustor pressurized and visualized combustion test device

Method used

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  • Pressurization visual combustion test device of combustor of gas turbine
  • Pressurization visual combustion test device of combustor of gas turbine
  • Pressurization visual combustion test device of combustor of gas turbine

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Experimental program
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specific Embodiment approach 1

[0007] Specific implementation mode one: combine figure 1 , figure 2 with image 3 To illustrate this embodiment, the gas turbine combustor pressurized visual combustion test device described in this embodiment includes a single nozzle installation flange cover 1, a pressure-bearing casing 2, an elastic bracket assembly 3, a quartz glass flame tube 4, and a telescopic igniter 5. The high temperature measurement section 6 and the explosion-proof mechanism 7, the pressure casing 2 is set horizontally, the single nozzle installation flange cover 1 is installed on the end face of one end of the pressure casing 2, the pressure casing 2 is connected with the high temperature measurement section 6, The explosion-proof mechanism 7 is installed on the explosion-proof clamping flange 2-1 on the lower surface of the pressure-bearing casing 2, the elastic bracket assembly 3 is inserted in the pressure-bearing casing 2, and the glass flame tube 4 is adapted to be inserted into the elasti...

specific Embodiment approach 2

[0009] Specific implementation mode two: combination figure 1 with image 3 Describe this embodiment, the gas turbine combustor pressurized visual combustion test device described in this embodiment is respectively provided with a viewing window 2-3 on the upper surface and two sides of the pressure casing 2, and the upper surface of the pressure casing 2 is Three rows of temperature and pressure measuring points 2-4 are arranged at equal intervals on the upper surface, and two secondary diluent interface flanges 2-5 are respectively arranged on the upper surface and the lower surface of the pressure-bearing casing 2.

[0010] In this embodiment, after the compressed air enters from the inlet flange on the pressure-bearing casing 2, the air state parameters at the inlet of the tester are measured through the temperature and pressure measuring points 2-4, and then the four secondary diluent interface flanges 2-5 are downstream The compressed air is mixed with the secondary dil...

specific Embodiment approach 3

[0012] Specific Embodiment 3: This embodiment is described in conjunction with 1. Each viewing window 2-3 of the gas turbine combustor pressurized visual combustion test device in this embodiment is a viewing window 2-3 made of synthetic adaptive glass.

[0013] The technical effect of this embodiment is: so set, the peep window 2-3 can not only pass through the far ultraviolet spectrum, but also can pass through the visible light and near-infrared spectrum, can work at a temperature above 950°C for a long time, and realize it at a temperature above 1200°C Working at the maximum cycle, the three peep windows 2-3 are used in conjunction with each other, so that the combustion flame in the quartz glass flame tube 4 can be observed by the experimenter with the naked eye, and can cooperate with the combustion optical measurement system to measure the flame in the quartz glass flame tube 4 form and structure. Other components and connections are the same as those in the second embo...

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Abstract

The invention relates to a pressurization visual combustion test device, in particular to a pressurization visual combustion test device of a combustor of a gas turbine. The pressurization visual combustion test device of the combustor of the gas turbine aims to solve the problem that no test device special for testing the combustor of the gas turbine exists in the prior art. According to the pressurization visual combustion test device, a pressure-bearing casing is horizontally arranged, a single-nozzle installation flange cover is installed at the end face of one end of the pressure-bearing casing, the pressure-bearing casing is connected with a high-temperature measurement section, an anti-explosion mechanism is installed on an anti-explosion clamping flange at the lower surface of the pressure-bearing casing, an elastic carrier assembly is inserted in the pressure-bearing casing, a quartz glass flame tube is inserted in the elastic carrier assembly, a telescopic igniter is connected with an igniter flange at the lower surface of the pressure-bearing casing, the upper end of the telescopic igniter is connected with the quartz glass flame tube, and an air inlet flange is arranged on the upper surface of the pressure-bearing casing. The pressurization visual combustion test device of the combustor of the gas turbine is used in the field of gas turbines.

Description

technical field [0001] The invention relates to a pressurized and visualized combustion test device, in particular to a pressurized and visualized combustion test device for a combustion chamber of a gas turbine. Background technique [0002] At present, the working pressure of engineering combustion equipment such as gas turbine combustors is generally 0.4-3MPa, and the inlet air temperature is 200-500°C. The flow and combustion process inside the combustor are significantly different from those under atmospheric pressure. The technical development of gas turbine combustors And the design needs to be carried out under actual working conditions. However, it is very difficult to measure the flame shape and structure under the pressurized condition of the existing gas turbine combustor, and there is no special device for the test of the gas turbine combustor. Contents of the invention [0003] In order to solve the problem that there is no experimental device specially used ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M15/02
Inventor 冯永志张宏涛翁振宇王辉王岳赵俊明林铁王思远陈洪港卜一凡张文军张春梅吕智强于宗明吴鑫楠
Owner HARBIN TURBINE
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