Optimization method for flame tube of combustion chamber of gas turbine impacting cooling system
A technology of gas turbine and cooling system, which is applied in the direction of gas turbine device, engine cooling, turbine/propulsion device cooling, etc., and can solve problems such as difficulty in optimizing impact structure
Active Publication Date: 2020-02-28
DONGFANG TURBINE CO LTD
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Problems solved by technology
[0003] The present invention aims to provide a method for optimizing the impingement cooling system of the combustor flame tube of a gas turbine to solve the problem that it is difficult to optimize the existing impingement structure when the cooling design cannot meet the wall temperature requirements
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[0038] This embodiment provides a method for optimizing the impingement cooling system of the combustion chamber flame cylinder of a gas turbine. When the wall temperature of the flame cylinder is overheated, the combustion chamber structure is optimized through the following steps:
[0039] 1) Initial measurement: measure the wall temperature of the original combustion chamber, and obtain the temperature value T at each row of cooling holes on the wall surface i , and calculate the value of the impinging jet depth ratio Y% corresponding to each row of cooling holes through formula (1) and formula (2):
[0040]
[0041]
[0042] Among them: Y max is the maximum jet depth, d j is the effective diameter of the cooling hole, ρ j is the jet air density, U j is the jet air velocity, ρ g is the mainstream air density, U g is the mainstream air velocity, m g is the mainstream air mass flow rate, m j is the jet air mass flow rate, H is the impact height, Y% is the impact ...
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The invention relates to the field of optimization of flame tube of a combustion chamber of a gas turbine impacting cooling system, aims to solve the problem that an existing impacting structure is difficult to optimize when the cooling design cannot meet the wall temperature requirement, and provides an optimization method for flame tube of the combustion chamber of the gas turbine impacting cooling system. The optimization method comprises the following steps that 1), initial measurement is carried out, specifically, the wall temperature measurement is carried out on the original combustionchamber to obtain a temperature value Ti corresponding to each row of cooling holes of the wall surface, and a value of the depth ratio Y% of an impact jet flow corresponding to each row of the cooling holes is calculated through an equation; and 2), structural optimization is carried out, specifically, aiming at parts where the measured temperature values Ti are larger than or equal to limit temperature values Tm, namely, reasonable parts of the wall temperature, each row of the cooling holes is subjected to the structural optimization, so that new calculated Y% values under the optimized structure are greater than or equal to the Y% values corresponding to the parts where the measured temperature values in the step 1) are equal to the limit temperature values Tm. The optimization methodhas the beneficial effects that the existing impacting structure can be scientifically and effectively evaluated and optimized.
Description
technical field [0001] The invention relates to the field of optimization of the impingement cooling system of the combustion chamber flame cylinder, in particular to an optimization method for the impingement cooling system of the combustion chamber flame cylinder of the gas turbine. Background technique [0002] Impingement jet cooling is widely used in the flame tube cooling of gas turbine combustors because of its high heat transfer coefficient, no direct contact with high-temperature gas, and low probability of CO quenching on the wall. For the designed cooling system, the test is the best means to test the cooling effect. However, when the cooling design cannot meet the wall temperature requirements, it becomes very difficult to optimize the existing impact structure, and the empirical formula method or CFD simulation method is usually used to adjust the key value H / d j (The ratio of the impact height to the diameter of the cooling hole) to obtain a better cooling eff...
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IPC IPC(8): F02C7/12F02C7/18F02C7/00
CPCF02C7/00F02C7/12F02C7/18
Inventor 冯珍珍田晓晶凤云仙杨安建张渊刘维兵黄毅
Owner DONGFANG TURBINE CO LTD