Patent ID: 6290464
Filing Date: 2001-09-18
Classification: F01D,F05B,F05D,Y02T

Abstract:
A turbine blade for use in a rotor assembly in an axial flow, high-pressure turbine in a turbomachine, said turbine blade comprising:a blade root and a blade portion extending from said blade root,said blade portion having a gas-wetted surface and at least one cooling air duct internally formed therein, said at least one cooling air duct issuing at the gas-wetted surface of said blade portion,said blade root having a cooling air chamber internally formed therein and configured to provide cooling air to said at least one cooling air duct, said blade root further having a cooling air passage internally formed therein, said integrated cooling air passage branching off from said cooling air chamber and issuing at an outlet port at a downstream, back surface of said blade root, said cooling air passage being configured to provide a substantially continuous passage for cooling air to pass from said cooling air chamber and to exit from said blade root at said downstream, back surface of said blade root, said cooling air passage further being configured to deflect the cooling air which it carries in a circumferential direction with respect to a turbine rotor assembly in which said turbine blade is to be installed.