Integral fuel jet radial swirler pre-mixing preevaporated low pollution combustion-chamber

A fuel injection and swirler technology, which is applied in the combustion chamber, continuous combustion chamber, combustion method, etc., can solve the problems of reducing the fuel injection point, reducing the axial length of the combustion chamber head structure, etc., so as to reduce the length , Wide and stable working range with low effect

Inactive Publication Date: 2008-10-15
BEIHANG UNIV
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Problems solved by technology

[0005] The technical problem to be solved by the present invention is: to overcome the deficiencies of the above-mentioned prior art, adopt the integrated fuel injection/radial swirler scheme, through the fuel injection method in the radial swirler blade channel and the radial swirler The oil-air mixture in

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  • Integral fuel jet radial swirler pre-mixing preevaporated low pollution combustion-chamber

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[0032] The present invention will be described in detail below with reference to the drawings and specific embodiments.

[0033] figure 1 It is a schematic diagram of an engine 10. The engine 10 includes a low-pressure compressor 11, a high-pressure compressor 12, a combustion chamber 13, a high-pressure turbine 14 and a low-pressure turbine 15. When the engine 10 is working, the air is compressed by the low-pressure compressor 11, and then enters the high-pressure compressor 12. The high-pressure air enters the combustion chamber 13 and burns. The fuel injection system injects oil into the high-pressure airflow, and the combustion chamber 13 is fully and effectively After combustion, high-temperature and high-pressure gas is formed after combustion, which enters the high-pressure turbine 14 and the low-pressure turbine 15, thereby driving the turbine to perform work. figure 2 It is a schematic diagram of the combustion chamber 13, and the combustion chamber has a single-ring c...

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Abstract

The invention discloses a combustion cavity for an integral fuel oil ejecting radial hydrocyclone with functions of premixing, pre-evaporation and low pollution. The combustion cavity has a single ring cavity structure, and consists of a combustion cavity head and a flame tube, wherein the combustion cavity head comprises a precombustion stage positioned at the center and a main combustion stage positioned at the peripheral. The main combustion stage comprises a direct jet type air atomizer spray nozzle and a main combustion stage radial hydrocyclone. The jetting of the main combustion stage fuel oil and the main combustion stage radial hydrocyclone are integrated. The main combustion stage fuel oil ejected by the direct jet type air atomizer spray nozzle enters into a main combustion stage radial hydrocyclone vane channel of a main combustion stage radial hydrocyclone vane, and the fuel oil is mixed with the rotary flow air of the main combustion stage radial hydrocyclone. A premixed oil-gas mixture enters into a combustion zone through a main combustion stage mixing cavity to be combusted. The combustion mode can effectively reduce pollutant emission in the combustion cavity and reduce the length of the combustion cavity. The combustion cavity is mainly used for an aerial engine combustion cavity, and also can be used for the combustion cavities of industrial gas turbines and ship gas turbines so as to reduce the pollutant discharged into atmosphere.

Description

technical field [0001] The invention relates to a low-pollution emission combustion chamber, in particular to an integrated fuel injection radial swirler premixing pre-evaporation low-pollution combustion chamber. Background technique [0002] The main development trend of aero-engine combustors is low-pollution combustion. Aeroengine combustors must meet increasingly stringent aeroengine pollution emission standards. The currently adopted CAEP4 (Committee on Aviation Environmental Protection) standard has very strict requirements, especially for NOx pollution emission requirements, while the CAEP6 standard that will be adopted after 2008 is even more stringent. The pollution emission requirements of industrial gas turbines reach single digits—one ten-thousandth concentration emission requirements. [0003] In general, aeroengine pollutants can be divided into two categories: nitrogen oxides (NOx) due to high flame temperatures; carbon monoxide and unburned hydrocarbons (C...

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Application Information

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IPC IPC(8): F23R3/58F23R3/20
Inventor 彭云晖许全宏张驰林宇震刘高恩
Owner BEIHANG UNIV
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