Cooling structure suitable for high-pressure turbine of gas turbine

A cooling structure, high-pressure turbine technology, applied in mechanical equipment, engine components, machines/engines, etc., can solve problems such as difficulty in outflow from the pressure surface of the channel, uneven pressure distribution at the outlet of the slot, and cooling of the pressure surface of the leakage channel.
CN109424367AActive Publication Date: 2019-03-05AECC COMML AIRCRAFT ENGINE CO LTD
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Patent Information

Authority / Receiving Office
CN · China
Current Assignee / Owner
AECC COMML AIRCRAFT ENGINE CO LTD
Publication Date
2019-03-05

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Abstract

The invention discloses a cooling structure suitable for a high-pressure turbine of a gas turbine. Through the cooling structure, outflow of cold gas along a groove slit can be more uniform, backward-flowing invasion of gas is prevented, and additionally, cooling heat-exchange of the positions, close to the pressure face sides, of the front edges of the end walls is also enhanced. The cooling structure comprises barrier ribs arranged on the positions, close to the force suction face sides of turbine blades, of the front end faces of the blade end walls, and a plurality of gas film holes formedin the positions, close to the pressure face sides of the turbine blades, of the front end faces of the blade end walls, wherein the gas film holes are connected with cooling cavities in the back faces of the blade end walls in a through hole form, P is the pitch of the turbine blades, 0%P serves as the front edge side position of the pressure face of the axially corresponding turbine blade on the front end face, 100%P serves as the front edge side positions of the force suction faces of the opposite adjacent turbine blades, the barrier ribs are circumferentially distributed within the 50-100%P range on the front end face, and the gas film holes are circumferentially distributed within the 0-50%P range on the front end face.
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Description

technical field

[0001] The invention relates to a cooling structure for the blade end wall of a gas turbine high pressure turbine. Background technique

[0002] With the continuous development of modern gas turbine technology, in order to improve the efficiency of the engine, the inlet temperature of the high-pressure turbine of the gas turbine is also increasing. At present, the inlet temperature of the high-pressure turbine of the advanced engine is between 1700-1850K, far exceeding the melting point of the metal. In order to protect the high-pressure turbine blades and prolong their life, various cooling methods are required to cool the turbine blades.

[0003] For turbine blade cooling, it is divided into blade surface cooling and blade edge cooling according to the cooling position. The blade edge area refers to the area where the flow and heat transfer of the turbine blade's end wall, leading edge, trailing edge and blade tip are complex, especially the flow, heat tra...

Claims

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