An optimization method for the impingement cooling system of the combustion chamber flame tube of a gas turbine
A gas turbine and cooling system technology, which is applied in the direction of gas turbine devices, engine cooling, turbine/propulsion device cooling, etc., and can solve problems such as the difficulty of optimizing the impact structure
Active Publication Date: 2021-09-21
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 flame tube of the original combustion chamber, and obtain the temperature value T at each row of cooling holes on the wall of the flame tube 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 impa...
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The invention relates to the field of optimization of the impingement cooling system of the combustion chamber flame tube of a gas turbine, and aims to solve the problem that it is difficult to optimize the existing impingement structure when the cooling design cannot meet the wall temperature requirements. A method for optimizing the impingement cooling system of a gas turbine combustion chamber flame tube is provided, including 1) initial measurement: the wall temperature of the original combustion chamber is measured, and the temperature values T corresponding to each row of cooling holes on the wall surface are respectively obtained i , and calculate the value of the impact jet depth ratio Y% corresponding to each row of cooling holes through the formula; 2) structure optimization: for the measured temperature value T i ≥Limit temperature value T m Structural optimization of each row of cooling holes at the place where the wall temperature is unreasonable, so that the new Y% value calculated under the optimized structure is greater than or equal to the temperature measured in step 1) and is equal to the limit temperature value T m at the corresponding Y% value. The beneficial effect of the invention is that the existing shock structure can be evaluated and optimized scientifically and effectively.
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