A gas turbine guide inner ring impingement cooling structure, gas turbine
A technology of gas turbine and cooling structure, which is applied in the cooling of turbine/propulsion device, cooling of engine, machine/engine, etc. It can solve the problems of reducing the overall performance of the engine, improve the cooling effect, facilitate impingement cooling, and improve cooling efficiency Effect
Active Publication Date: 2021-03-09
INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI
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Problems solved by technology
In order to ensure the safe operation of the engine in the past, it usually achieves sealing and effective cooling by increasing the amount of cooling air, but increasing the amount of cooling air will inevitably reduce the overall performance of the engine
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[0026] Below in conjunction with embodiment the present invention is described in further detail, and following example is explanation of the present invention and the present invention is not limited to following example.
[0027] like figure 1 , 2 As shown, the structure for the impingement cooling of the inner ring of the gas turbine guide of the present invention includes the impingement cooling box plate 1 , the gas turbine guide 2 and the outlet wall surface 3 of the combustion chamber. The upstream of the impingement cooling box plate 1 is provided with a flange 101, which can be fixed on the outlet 301 of the combustion chamber by welding, or overlapped by interference fit. When the interference fit is used, it is necessary to ensure that the matching flange 101 and the outlet wall of the combustion chamber have a certain flatness requirement, as well as a parallelism requirement for the cooperation between the two, so as to prevent cold air from leaking there. A mou...
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The invention relates to an impact cooling structure for a gas turbine guider inner ring. The impact cooling structure comprises an impact cooling box plate, a gas turbine guider and a combustion chamber outlet wall surface, wherein the combustion chamber outlet wall surface is in lap joint with the inner ring gas side wall surface of the gas turbine guider, and a seam is formed in a lap joint part; the impact cooling box plate, the combustion chamber outlet wall surface and the guider inner ring wall surface are enclosed to form a cold gas chamber; an impact cooling lug boss is arranged on the cold gas side wall surface of the guider inner ring; a plurality of rows of impact cold gas holes are distributed in the cylindrical surface of the impact cooling box plate; high-pressure cold gas impacts and cools the lug boss on the guider inner ring through an impact cooling hole, and then flows out through a seam, so that a cooling gas film is formed on the gas side wall surface of the guider inner ring, and therefore, efficient cooling on the guider inner ring is achieved, and the high-temperature gas erosion risk is prevented. While popularized and used in a modern gas turbine, the impact cooling structure has a positive effect on performance and reliability of the engine.
Description
technical field [0001] The invention relates to the field of high-temperature parts of gas turbine turbines, and more specifically relates to an impingement cooling structure for the inner ring of the guider of the gas turbine, which can realize efficient cooling of the inner ring of the guider of the turbine, reduce thermal stress, and improve the service life and reliability of the engine. sex. Background technique [0002] In order to improve the performance of the gas turbine, the temperature before the high pressure turbine is continuously increased. The turbine inlet gas temperature of advanced aviation turbofan engines has reached 1800K-2050K, far exceeding the allowable temperature of existing superalloys. In order to ensure the safe operation of the high-pressure turbine, effective cooling must be implemented to reduce the metal wall temperature of the high-pressure turbine guide. [0003] Usually, there is a gap between the combustion chamber of an aero-engine an...
Claims
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IPC IPC(8): F01D25/12F02C7/18
CPCF01D25/12F02C7/18
Inventor 徐庆宗杜强柳光刘军王沛高金海杨晓洁胡嘉麟刘红蕊
Owner INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI