US 2011/0217179 A1 · TURBINE AIRFOIL FILLET COOLING SYSTEM

Abstract

A cooling system for the fillet of a turbine blade is provided. The blade includes an airfoil transitioning to a platform having a flow path surface. The transition region is defined by a fillet. A cooling passage is formed in the platform and extends about at least a portion of the periphery of the airfoil. The cooling passage is located proximate to the flow path surface and is substantially aligned with at least a portion of the fillet. Coolant is delivered to the passage by a supply hole, which can reduce the temperature in the fillet region. As a result, thermal gradients in the fillet region can be minimized, which can reduce thermal stresses. An exhaust hole extends between the passage and the flow path surface of the platform. Thus, coolant discharged from the exhaust holes enters the flow path of the turbine.

Claims19

Dependent claims

An airfoil fillet cooling system for a turbine component comprising:

an airfoil;
an end wall having a flow path surface, the airfoil transitioning to the end wall in a region defined by a fillet;
at least one cooling passage formed in the end wall and extending about at least a portion of the airfoil, the at least one cooling passage being located proximate to the flow path surface and substantially aligned with at least a portion of the fillet;
at least one supply hole extending through the turbine component and between the passage and a coolant source so as to permit fluid communication therebetween;
and
at least one exhaust hole extending through the turbine component and between the passage and the exterior of the turbine component so as to permit fluid communication therebetween.

3 more elements

Dependencies are inferred from the claim text.

Turbine airfoil fillet cooling system

Life of this patent

Turbine airfoil fillet cooling system

Life of this patent

Abstract

Claims19