IMPINGEMENT COOLED BUCKET SHROUD, TURBINE ROTOR INCORPORATING THE SAME, AND COOLING METHOD
PROBLEM TO BE SOLVED: To provide a novel method of cooling tip shrouds of a turbine bucket. SOLUTION: Localized directional impingement cooling is used to reduce the metal temperatures on highly stressed regions of the tip shrouds 120, 220, 420. One or more airfoil cooling passages are provided in a...
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| creator | BENJAMIN EDWARD DURELL BRITTINGHAM ROBERT ALAN ARNESS BRIAN PETER |
| description | PROBLEM TO BE SOLVED: To provide a novel method of cooling tip shrouds of a turbine bucket. SOLUTION: Localized directional impingement cooling is used to reduce the metal temperatures on highly stressed regions of the tip shrouds 120, 220, 420. One or more airfoil cooling passages are provided in an airfoil portion of the turbine bucket, and one or more cooling chambers 130, 142, 230, 242, 342, 430 are provided in the shroud. Cooling air from one or more airfoil cooling passages hits the wall faces of one or more cooling chambers through one or more impingement holes 132, 232, 432, and the used impingement cooling air is exhausted from one or more outlet openings 136, 138, 140, 236, 240 of the cooling chambers. COPYRIGHT: (C)2008,JPO&INPIT |
| format | Patent |
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SOLUTION: Localized directional impingement cooling is used to reduce the metal temperatures on highly stressed regions of the tip shrouds 120, 220, 420. One or more airfoil cooling passages are provided in an airfoil portion of the turbine bucket, and one or more cooling chambers 130, 142, 230, 242, 342, 430 are provided in the shroud. Cooling air from one or more airfoil cooling passages hits the wall faces of one or more cooling chambers through one or more impingement holes 132, 232, 432, and the used impingement cooling air is exhausted from one or more outlet openings 136, 138, 140, 236, 240 of the cooling chambers. 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SOLUTION: Localized directional impingement cooling is used to reduce the metal temperatures on highly stressed regions of the tip shrouds 120, 220, 420. One or more airfoil cooling passages are provided in an airfoil portion of the turbine bucket, and one or more cooling chambers 130, 142, 230, 242, 342, 430 are provided in the shroud. Cooling air from one or more airfoil cooling passages hits the wall faces of one or more cooling chambers through one or more impingement holes 132, 232, 432, and the used impingement cooling air is exhausted from one or more outlet openings 136, 138, 140, 236, 240 of the cooling chambers. 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SOLUTION: Localized directional impingement cooling is used to reduce the metal temperatures on highly stressed regions of the tip shrouds 120, 220, 420. One or more airfoil cooling passages are provided in an airfoil portion of the turbine bucket, and one or more cooling chambers 130, 142, 230, 242, 342, 430 are provided in the shroud. Cooling air from one or more airfoil cooling passages hits the wall faces of one or more cooling chambers through one or more impingement holes 132, 232, 432, and the used impingement cooling air is exhausted from one or more outlet openings 136, 138, 140, 236, 240 of the cooling chambers. COPYRIGHT: (C)2008,JPO&INPIT</abstract><oa>free_for_read</oa></addata></record> |
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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 | IMPINGEMENT COOLED BUCKET SHROUD, TURBINE ROTOR INCORPORATING THE SAME, AND COOLING METHOD |
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