Radial swirler turning zone liquid and mist injection premixing and prevapourising low pollution burning chamber

A combustion chamber and swirler technology, which is applied in the field of aero-engine combustion chambers, can solve the problems of reducing the distance of fuel injection points, reducing the axial length of the combustion chamber head structure, and achieving the effect of reducing the length

Inactive Publication Date: 2008-10-01
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, to overcome the deficiencies of the above-mentioned prior art, to use the fuel liquid mist injection in the turning area behind the radial swirler, and to use the oil and gas spraying before the fuel enters the turn...

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  • Radial swirler turning zone liquid and mist injection premixing and prevapourising low pollution burning chamber
  • Radial swirler turning zone liquid and mist injection premixing and prevapourising low pollution burning chamber
  • Radial swirler turning zone liquid and mist injection premixing and prevapourising low pollution burning chamber

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Embodiment Construction

[0030] The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0031] figure 1 It is a schematic diagram of an engine 10 , and 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 for combustion. Combustion, high-temperature and high-pressure gas is formed after combustion, and enters the high-pressure turbine 14 and the low-pressure turbine 15, thereby driving the turbines to do work. figure 2 It is a schematic diagram of the combustion chamber 13 of the engine, and the combustion chamber is a single-ring cavity structure. image 3 is an enlarged view of zone 3 in the combustion chamber 13, and is...

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Abstract

Disclosed is a radial swirler turning area direct injection premixing pre-evaporation firebox, wherein the firebox composed of a burner head and a flame tube is a single ring structure. The burner head includes a preburning level in the center and a main burning level at the outer ring; Using the direct injection project in the back turning area of the main burning level radial swirler, first the main burning level fuel is premixed with the air, then the main burning level fuel forms the premixing pre-evaporation gas-oil mixture to enter the burning area for burning under the action of the swirling gas of the main burning lever radial swirler, wherein the burning way can effectively reduce the discharge of the pollutants in the burning chamber, meanwhile, the direct injection in the back turning area and the turning flow for the main burning level radial swirler of the main burning level fuel can reduce the length of the burning chamber; the invention is mainly used in the airmortor firebox, also can be used in the firebox of the industrial gas turbine and the ship gas turbine.

Description

technical field [0001] The invention relates to an aero-engine combustion chamber technology, in particular to a liquid mist injection premixed pre-evaporation low-pollution combustion chamber in the turning area of ​​a radial swirler. Background technique [0002] The main development trend of aero-engine combustion is low-pollution combustion, and aero-engine combustors must meet increasingly stringent aero-engine 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 a...

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Application Information

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IPC IPC(8): F23R3/58F23R3/40
Inventor 林宇震彭云晖许全宏张驰刘高恩
Owner BEIHANG UNIV
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