Aero-engine combustor with variable-cross-section step-shaped multiple-inclined-hole cooling structure used

Abstract

The invention discloses an aero-engine combustor with a variable-cross-section step-shaped multiple-inclined-hole cooling structure used. The aero-engine combustor comprises a combustor casing, a calotte, a cyclone, a connecting section, a splash plate, a flame tube inner ring wall and a flame tube outer ring wall. According to technical scheme, the flame tube inner ring wall and the flame tube outer ring wall are both straight walls, and multiple variable-cross-section step-shaped inclined holes are formed in the flame tube inner ring wall and the flame tube outer ring wall. The combustor with the cooling structure used can effectively reinforce impingement cooling in a wall surface, effective thermal insulation and cooling can be formed on the wall surface of the aero-engine combustor, meanwhile, consumption of cooling gas is reduced, tissue gas consumption is increased, and temperature rising of the combustor is quickened. The aero-engine combustor is simple in structure and easy to implement and has good engineering application value.

Description

technical field [0001] The invention relates to the field of aero-engines, in particular to an aero-engine combustion chamber adopting a step-shaped multi-slant hole cooling structure with variable cross-section. Background technique [0002] With the continuous improvement of aero-engine performance indicators, the requirements for the performance of the flame tube are becoming increasingly stringent. At present, the cooling of the flame tube is facing two major difficulties: (1) With the continuous increase of the outlet temperature of the combustion chamber, under the condition of a certain oil-gas ratio Next, the amount of tissue combustion air gradually increases. In addition, in order to ensure that the temperature distribution at the outlet of the combustion chamber meets the design requirements, the proper amount of mixed air cannot be reduced. When the air intake at the head is constant, this leads to a decrease in the amount of air available for cooling. If the tr...

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Problems solved by technology

(2) The total supercharging ratio of aero-engines is gradually increased, and the total supercharging ratio of high thrust-to-weight ratio aero-engines will reach 35-40, or even higher. At this time, the air temperature at the compressor outlet will reach about 1000K, that is to say, the cooling flame The temperature of the inlet air of the combustion chamber on the cylinder wall will gradually rise with the increase of the aero-engine boost ratio, therefore, the cooling capacity of the inlet air of the combustion chamber as a coolant is gradually decreasing

[0008] The impact cooling method with multiple oblique holes has higher cooling efficiency and consumes less cooling air. However, it adopts a floating wall structure, which makes the structure complex and further increases the processing difficulty. In addition, the floating wall structure is a double-layer structure, which increases the weight. Detrimental effect on engine weight

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