TURBINE BLADE AND GAS TURBINE

• US 20100247290A1
• Filed: 03/26/2009
• Published: 09/30/2010
• Est. Priority Date: 03/26/2009
• Status: Active Grant

• Current Assignee: Mitsubishi Power Limited (Mitsubishi Heavy Industries, Ltd.)
• Original Assignee: Mitsubishi Heavy Industries, Ltd.
• Inventors: ICHIRYU, Taku, HADA, Satoshi
• Granted Patent: US 8,182,203 B2
• Time in Patent Office: Days
• US Class Current: 415/115
• CPC Class Codes: F01D 5/189 the insert having a tubular cross-section, e.g. airfoil shape
• CPC Class Codes: F05D 2240/122 related to the trailing edge of a stator vane
• CPC Class Codes: F05D 2240/304 related to the trailing edge of a rotor blade
• CPC Class Codes: F05D 2260/201 by impingement of a fluid
• CPC Class Codes: F05D 2260/22141 using fins or ribs

Abstract

A turbine blade and a gas turbine are provided in which the velocity of cooling fluid at the inlet of a pin fin region is improved so that the cooling performance at the trailing edge of the turbine blade can be improved. It includes an airfoil; a supply channel extending through the interior of the airfoil in the span direction, through which cooling fluid flows; a pin fin channel extending from the supply channel along the center line of the airfoil toward the trailing edge of the airfoil and opening at the trailing edge to the exterior of the airfoil; a plurality of gap pin fins projecting from a pair of opposing inner walls that constitute the pin fin channel at a region at the supply channel side of the pin fin channel and forming a gap therebetween extending in the span direction; pin fins connecting the pair of opposing inner walls at a region at the trailing edge side of the pin fin channel; and an insertion portion disposed in the gap to decrease the area of the channel of the cooling fluid at the region at the supply channel side of the pin fin channel.

Claims

1. A turbine blade comprising:

an airfoil;

a supply channel extending through the interior of the airfoil in the span direction, through which cooling fluid flows;

a pin fin channel extending from the supply channel along the center line of the airfoil toward the trailing edge of the airfoil and opening at the trailing edge to the exterior of the airfoil;

a plurality of gap pin fins projecting from a pair of opposing inner walls that constitute the pin fin channel at a region at the supply channel side of the pin fin channel and forming a gap therebetween extending in the span direction;

pin fins connecting the pair of opposing inner walls at a region at the trailing edge side of the pin fin channel; and

an insertion portion disposed in the gap to decrease the area of the channel of the cooling fluid at the region at the supply channel side of the pin fin channel.

2. The turbine blade according to claim 1, wherein the cross-sectional area of the insertion portion decreases from the supply channel toward the trailing edge.

3. The turbine blade according to claim 1, wherein the ends of the gap pin fins and the insertion portion are in contact.

4. A gas turbine comprising the turbine blade according to claim 1.