Three-stage stratified combustion high temperature rise combustion chamber structure

Abstract

The invention relates to a three-stage stratified combustion high temperature rise combustion chamber structure which is applied to an aircraft engine high in thrust-weight ratio. An oil-gas mixing device at the head of a combustion chamber is divided into a precombustion stage and a main combustion stage. Precombustion stage fuel oil enters a precombustion area through a center direct jet nozzle and a precombustion stage pre-film nozzle to form a solid atomizer cone, and the stability of precombustion stage flame is improved. The main combustion stage injects fuel oil through two rows of fuel oil injection holes, the inner-layer fuel oil injection hole injects the fuel oil into a swirler air channel inside the main combustion stage, the outer-layer fuel oil injection hole injects the fuel oil into a swirler air channel outside the main combustion stage, and thus two combustion areas, that is, the inner-layer main combustion area and the outer-layer main combustion area are formed in the main combustion stage. The oil-gas ratio of the inner-layer main combustion area is larger than that of the outer-layer main combustion area, so that the inner-layer main combustion area is ignited by the precombustion stage flame more easily, and a stabilizing effect is further achieved on the outer-layer main combustion area by the inner-layer main combustion area. Step-by-step stable combustion is achieved among the three combustion areas, and hence the combustion stability of the head of the high temperature rise combustion chamber is jointly improved.

Description

technical field [0001] The invention relates to the field of high thrust-to-weight ratio aero-engines, in particular to a combustion chamber structure which adopts air and fuel three-stage stratified combustion technology to improve the combustion stability of the head of a high-temperature rise combustion chamber. Background technique [0002] At present, aero-engine combustors are mainly developing in two directions. One is a low-pollution combustor, which is mainly used in civil aero-engines, with high combustion efficiency and low pollutant emissions (mainly nitrogen oxides and carbon monoxide) as its main technical features. , and its typical representatives are the TAPS combustor applied to the GEnx engine and the TAPS II combustor applied to the GE9x engine. The TAPS and TAPS II combustion chambers adopt the concept of staged and partitioned combustion. Most of the fuel is injected into the main combustion stage to achieve premixed and partially premixed combustion, t...

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Problems solved by technology

[0005] Aiming at the shortcomings and deficiencies of the prior art, the technical problem to be solved by the present invention is: for the existing high-temperature-rising combustor using the two-stage layered and partitioned combustion technology, the head air flow rate is relatively large, and the pre-combustion flame is difficult to control. The main combustion stage flame is effective and stable, which severely limits the robustness of the high-temperature rise combustor under different combustion load conditions. The present invention further refines the main combustion stage and The stratified combustion organization of the pre-combustion stage proposes that the flame of the main combustion stage is further divided into two layers, the pre-combustion stage adopts a combination nozzle of the center direct injection nozzle and the pre-film nozzle, and the overall structure of the high-temperature rise combustion chamber is a three-stage stratified combustion. So as to solve the combustion stability problem of the high-temperature rising combustion chamber adopting the layered and partitioned combustion technology

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