Combustion chamber structure

Abstract

The invention provides a combustion chamber structure. The combustion chamber structure structurally comprises a truncated cone (1), a diffuser (2), a flame tube (3), a guide ring (4) and a lobe mixer(5), wherein the diffuser (2) is arranged outside the truncated cone (1) in a sleeving manner and comprises an inner profile surface (21) and an outer profile surface (22); the flame tube (3) is connected with the tail end of the outer profile surface (22); the guide ring (4) is arranged in the diffuser (2), high-temperature fuel gas is introduced into space between the guide ring (4) and the inner profile surface (21), and pure air is introduced into space between the guide ring (4) and the outer profile surface (22); multiple double-lobe structures (51) are uniformly distributed in the circumferential direction of the lobe mixer (5), each double-lobe structure (51) comprises two lobes with different radial heights and widths and is arranged in the diffuser (2), the front end is connected with the tail end of the guide ring (4), the rear end is flush with the tail end of the truncated cone (1), the lobe mixer (5) is used for mixing the high-temperature fuel gas and pure air, a streamwise vortex (6) is formed in the flame tube (3) behind the lobe mixer (5), and therefore, the high-temperature fuel gas stably combusts in the streamwise vortex (6). Mixing uniformity and flame stability are improved.

Description

technical field [0001] The invention relates to the field of power plant combustion, in particular to a combustion chamber structure. Background technique [0002] The ratio of the external flow rate to the internal flow rate of the turbojet engine with a wide speed range and high thrust-to-weight ratio is increased from a small bypass ratio of 1 to a large bypass ratio of more than 20. The range of airflow parameters at the inlet of the afterburner increases, and the non-uniformity increases, which brings great challenges to the mixing design of the airflow and the combustion organization. Under complex high-speed, multi-duct air intake conditions, the mixing uniformity of the airflow is the primary problem faced in the design. [0003] Under high flow conditions, special devices must be used in the combustion chamber to stabilize the flame. In related technologies, for example, a swirl structure is used to stabilize the flame, or a flame stabilizer with a blunt body stru...

AI Technical Summary

Problems solved by technology

Under the condition of high-speed incoming flow, the friction loss between the air flow and the wall of the cylinder increases significantly. The use of the traditional full-cone structure will lead to an increase in the structural length of the combustion chamber and an increase in friction loss. In the related art, the large groove width stabilizer structure It is difficult to meet the requirements of the new generation afterburner for flow resistance and flame stability

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