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...

Ausführliche Beschreibung

Gespeichert in:

Bibliographische Detailangaben
Hauptverfasser:	BENJAMIN EDWARD DURELL, BRITTINGHAM ROBERT ALAN, ARNESS BRIAN PETER
Format:	Patent
Sprache:	eng
Schlagworte:	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
Online-Zugang:	Volltext bestellen
Tags:	Tag hinzufügen Keine Tags, Fügen Sie den ersten Tag hinzu!

Beschreibung
Zusammenfassung:	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