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Fuel nozzle, combustion chamber, gas turbine engine and method for preventing coking of fuel

A technology of fuel nozzles and oil passages, applied in combustion methods, gas turbine devices, combustion chambers, etc., can solve the problems of increasing the operating cost of gas turbine engines and short maintenance periods, and achieve reduced coking risks, reduced operating costs, and strong reliability Effect

Pending Publication Date: 2022-06-07
AECC COMML AIRCRAFT ENGINE CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, due to the heating effect of the purge gas on the nozzle when the nozzle is running, there is a risk of coking of the fuel nozzle, which makes the maintenance cycle shorter and increases the operating cost of the gas turbine engine

Method used

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  • Fuel nozzle, combustion chamber, gas turbine engine and method for preventing coking of fuel
  • Fuel nozzle, combustion chamber, gas turbine engine and method for preventing coking of fuel
  • Fuel nozzle, combustion chamber, gas turbine engine and method for preventing coking of fuel

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Embodiment Construction

[0037] The present invention will be further described below with reference to specific embodiments and accompanying drawings. More details are set forth in the following description to facilitate a full understanding of the present invention, but it is obvious that the present invention can be implemented in many other ways that are different from those described herein. Those skilled in the art can make similar promotion and deduction according to the actual application situation without violating the connotation of the present invention, so the content of this specific embodiment should not limit the protection scope of the present invention.

[0038] In addition, it is to be understood that references such as "one embodiment," "an embodiment," and / or "some embodiments" mean a certain feature, structure, or characteristic associated with at least one embodiment of the present application. Therefore, it should be emphasized and noted that two or more references to "an embodim...

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PUM

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Abstract

The invention relates to a fuel nozzle, a combustion chamber, a gas turbine engine and a method for preventing fuel coking. Wherein the fuel nozzle comprises an oil way; a memory alloy part is arranged on the hole wall of the purging hole, so that the flow area of the purging hole is variable; through the air outlet hole, purging air entering from the purging hole flows out after passing through the oil path; wherein the fuel nozzle has a running state and a stopping state; in the stop state, the memory alloy part is of a first structure, and the circulation area of the purging hole is the maximum value; and in the running state, the memory alloy part is of a second structure, and the circulation area of the purging hole is the minimum value.

Description

technical field [0001] The invention relates to a fuel nozzle, a combustion chamber, a gas turbine engine and a method for preventing fuel coking. Background technique [0002] With the development of high-performance, high-pressure ratio aero-engines, the demand for using fuel as coolant to cool engine devices has grown rapidly, causing the fuel temperature to rise by 100 to 140 °C before the fuel enters the fuel nozzle; The inlet air temperature of the combustion chamber is also further increased, and the inlet air temperature of the combustion chamber of the first-stage engine with a thrust-weight ratio of 10 reaches more than 800K, which makes the oil temperature in the fuel nozzle and the wall temperature of the oil pipe continue to increase, causing the nozzle The internal fuel is seriously deposited and coked, attached to the inner wall. In severe cases, the nozzle will be partially blocked and the formation of the spray cone will be blocked, resulting in a sharp dete...

Claims

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Application Information

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IPC IPC(8): F23R3/28F23R3/42F02C3/04F02C7/22
CPCF23R3/283F23R3/42F02C7/22F02C3/04F23R2900/03043Y02T50/60
Inventor 吴雪松于博文曹伟
Owner AECC COMML AIRCRAFT ENGINE CO LTD
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