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Fuel nozzle, combustor, gas turbine, and method of preventing fuel coking in fuel nozzle

A fuel nozzle and combustion chamber technology is applied in the fields of fuel nozzles, gas turbines, and the prevention of fuel coking in fuel nozzles and combustion chambers. Increased fuel pressure and reduced fuel pump pressure requirements

Active Publication Date: 2022-02-01
AECC COMML AIRCRAFT ENGINE CO LTD
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0007] However, if only the technical means of cooling or heat insulation are used, the inventor has found in practice that fuel coking is an irreversible process. As long as there is fuel oil inside the nozzle, coking will inevitably occur during long-term work
In addition, it is necessary to design a relatively complex cooling structure, which is difficult to design and manufacture, and causes a large loss of fuel pressure

Method used

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  • Fuel nozzle, combustor, gas turbine, and method of preventing fuel coking in fuel nozzle
  • Fuel nozzle, combustor, gas turbine, and method of preventing fuel coking in fuel nozzle
  • Fuel nozzle, combustor, gas turbine, and method of preventing fuel coking in fuel nozzle

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Embodiment Construction

[0037] The present invention will be further described below in conjunction with specific embodiment and accompanying drawing, set forth more details in the following description so as to fully understand the present invention, but the present invention can obviously be implemented in many other ways different from this description, Those skilled in the art can make similar promotions and deductions based on actual application situations 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] A variety of different implementations or examples for implementing the described subject technical solutions are disclosed below. In order to simplify the disclosure, the following describes the specific examples of each component and arrangement, of course, these are only examples, not limiting the protection scope of the present invention. For example, the description...

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Abstract

The invention relates to a fuel nozzle, a combustion chamber, a gas turbine and a method for preventing fuel coking in the fuel nozzle. The fuel nozzle includes an inlet, a nozzle, and a fuel delivery channel between the inlet and the nozzle, and the fuel is delivered to the nozzle of the fuel nozzle through the inlet and the fuel delivery channel in sequence, and the inlet is used for The fuel oil input from the external oil circuit into the fuel nozzle is input into the oil delivery channel, the inlet part includes an oil inlet port, and a first distributing valve located downstream of the oil inlet port, including an oil inlet chamber, and an oil return port. chamber, and a plunger arranged in the oil inlet chamber.

Description

technical field [0001] The invention relates to a fuel nozzle, a combustion chamber, a gas turbine and a method for preventing fuel coking in the fuel nozzle. Background technique [0002] With the development of high-performance and high-pressure ratio aero-engines, the temperature of the fuel before entering the fuel nozzle rises to 100-140°C; at the same time, as the engine pressure ratio continues to increase to improve cycle efficiency, the temperature of the air at the inlet of the combustion chamber is also further improved. The air temperature at the inlet of the combustor of the first-stage engine with a thrust-to-weight ratio of 10 is higher than 800K, so that the temperature of the oil in the fuel nozzle and the temperature of the oil pipe wall continue to increase, causing serious deposition and coking of the fuel in the nozzle, which is attached to the inner wall. Partial blockage of the nozzle prevents the formation of the spray cone, resulting in a sharp deter...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F23R3/28F02C7/22
CPCF23R3/28F02C7/22
Inventor 鄂亚佳徐仲方
Owner AECC COMML AIRCRAFT ENGINE CO LTD
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