Gas turbine gas compressor cooling system
The invention discloses a gas turbine gas compressor cooling system comprising a cooling pipeline and a conveying device. The cooling pipeline communicates with a conveying pipeline, is located in a vertical face of an engine shaft and corresponds to an engine high-pressure gas compressor stator in...
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| creator | QIU HUIZHUANG ZOU TONGXUAN TU GAOXING LUO BINGLIANG GU CHAO WANG YUN LI MAOYUAN |
| description | The invention discloses a gas turbine gas compressor cooling system comprising a cooling pipeline and a conveying device. The cooling pipeline communicates with a conveying pipeline, is located in a vertical face of an engine shaft and corresponds to an engine high-pressure gas compressor stator in position. The cooling pipeline comprises an annular coolant conveying pipeline, a radial coolant conveying pipe and a stationary blade. The stationary blade is installed between a hub of a gas turbine and a case. A hollow stationary blade inner cavity is arranged in the stationary blade. The blade back and blade abdomen of the stationary blade are provided with seepage holes communicating with the stationary blade inner cavity. The stationary blade inner cavity communicates with the annular coolant conveying pipeline through the radial coolant conveying pipe. Through simple pipeline design, effective cooling of gas flow of the medium-high-pressure gas compressor is achieved, and meanwhile, the weight of the cooling |
| format | Patent |
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The cooling pipeline communicates with a conveying pipeline, is located in a vertical face of an engine shaft and corresponds to an engine high-pressure gas compressor stator in position. The cooling pipeline comprises an annular coolant conveying pipeline, a radial coolant conveying pipe and a stationary blade. The stationary blade is installed between a hub of a gas turbine and a case. A hollow stationary blade inner cavity is arranged in the stationary blade. The blade back and blade abdomen of the stationary blade are provided with seepage holes communicating with the stationary blade inner cavity. The stationary blade inner cavity communicates with the annular coolant conveying pipeline through the radial coolant conveying pipe. 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| language | chi ; eng |
| recordid | cdi_epo_espacenet_CN110878714A |
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| subjects | AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS |
| title | Gas turbine gas compressor cooling system |
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