Combustion chamber based on RQL principle and aircraft engine with same

Abstract

The invention discloses a combustion chamber based on the RQL principle and an aircraft engine with the same. The combustion chamber based on the RQL principle comprises a combustion chamber casing and a double-layer flame cylinder arranged in the combustion chamber casing, the inner cavity of the double-layer flame cylinder forms a fuel rich combustion zone, the double-layer flame cylinder comprises a flame cylinder head, a flame cylinder outer wall, a flame cylinder inner wall and a swirler, and a high-pressure turbine guide vane component forming a quenching mixing zone and lean combustion zones is arranged between the double-layer flame cylinder and the combustion chamber casing; the double-layer flame cylinder and the high-pressure turbine guide vane component are connected integrally, and the high-pressure turbine guide vane component and the combustion chamber casing are connected integrally; the quenching mixing zone is arranged at the connection of the high-pressure turbine guide vane component and double-layer flame cylinder; the high-pressure turbine guide vane component comprises high-pressure turbine guide vanes, guide vane passages are formed between adjacent high-pressure turbine guide vanes, and the lean combustion zones are formed in the guide vane passages. The high-pressure turbine guide vane component is prevented from ablation through cold gas flowing through the guide vanes.

Description

technical field [0001] The invention relates to the field of aero-engines, in particular to a combustion chamber based on the RQL principle. In addition, the present invention also relates to an aeroengine comprising the above-mentioned combustion chamber based on the RQL principle. Background technique [0002] The main development direction of aero-engine combustor technology is low pollution and economy. In addition to meeting the increasingly stringent aero-engine pollution emission standards (the current CAEP6 standard), the aero-engine combustor must also meet economic requirements, namely lighter weight and lower fuel consumption. Often these two requirements conflict with each other, often at the expense of the structural simplicity of the combustion chamber in order to achieve the goal of low pollution emissions. Most low-pollution combustors, such as axial and radial staged combustors, LPP (Lean Premixed Prevaporized) combustors, and LDI (Lean Direct Injection) c...

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Problems solved by technology

[0005] The purpose of the present invention is to provide a combustor based on the RQL principle and an aeroengine with the combustor to solve the problem that the existing combustor structure still has a relatively large length of the flame tube, which causes the increase of the length and weight of the engine, and the outlet temperature field Technical issues where the distribution cannot be effectively controlled

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