Cooled blade for a gas turbine

Patent metadata

Field	Value
Publication number	US-9382804-B2
Application number	US-201313933548-A
Country	US
Kind code	B2
Filing date	Jul 2, 2013
Priority date	Jul 2, 2012
Publication date	Jul 5, 2016
Grant date	Jul 5, 2016

Abstract

A cooled blade is disclosed for a gas turbine that includes a radially extending aerofoil with a leading edge, a trailing edge, a suction side and a pressure side, and wherein a lip overhang is provided on the suction side of the trailing edge The blade also includes a plurality of radial internal flow channels connected via flow bends to form a multi-pass serpentine for a coolant flow, whereby a trailing edge ejection region is provided for cooling the trailing edge, the trailing edge ejection region comprising a trailing edge passage of the multi-pass serpentine running essentially parallel to the trailing edge and being connected over its entire length with a pressure side bleed. An optimized cooling is achieved by also determining the cooling flow from the trailing edge passage to the pressure side bleed by means of a staggered field of pins.

First claim

What is claimed is:

1. A cooled blade for a gas turbine, said cooled blade comprising:
a radially extending aerofoil with a leading edge, a trailing edge, a suction side and a pressure side, and wherein a lip overhang is provided on the suction side of the trailing edge, a plurality of radial internal flow channels connected via flow bends to form a multi-pass serpentine for a coolant flow, a trailing edge ejection region is provided for cooling said trailing edge, said trailing edge ejection region comprising a trailing edge passage of said multi-pass serpentine running parallel to said trailing edge and being connected over its entire length with a pressure side bleed, wherein the cooling flow from the trailing edge passage to the pressure side bleed is also determined by a staggered field of pins, provided between said pressure side bleed and said trailing edge passage, wherein the lateral dimension of said pins increasing in a chordwise flow direction; and
wherein in a hub and tip regions of said blade, a local hub and tip pin field with an increased number of pins is provided in order to meet the local flow, heat transfer and manufacturing criteria and at least within the local hub and tip pin field the pins are arranged in straight rows, which are inclined with respect to an axial direction by a predetermined angle.

2. The cooled blade according to claim 1 , wherein the pins have a circular cross section with a predetermined diameter (d) and a predetermined height (h), and the height to diameter ratio h/d for each pin ranges from 0.5 to 2.0.

3. The cooled blade according to claim 1 , wherein the pins of said pin field have a predetermined axial and radial spacing (s x , s y ), and the axial and radial spacing to pin diameter ratios s x /d and s x /y vary from 1.5 to 4.0.

4. The cooled blade according to claim 1 , wherein the coolant flows through a bend to enter said trailing edge passage, and the shape of the bend is designed to minimize the aerodynamic losses.

5. The cooled blade according to claim 4 , wherein the cross-area of the bend is contracting along the flow direction.

6. The cooled blade according to claim 5 , wherein the cross-area of said bend has an area of contraction ranging from 5% to 15%.

7. The cooled blade according to claim 1 , wherein the cross-area of the trailing edge passage converges in a radial direction by a factor ranging from 20 to 30.

8. The cooled blade according to claim 1 wherein said trailing-edge passage is lined with turbulators on both the pressure and the suction sides to increase the flow turbulence and to improve the heat transfer.

9. The cooled blade according to claim 8 , wherein said turbulators are arranged in the flow direction with a predetermined pitch (P) and have a predetermined turbulator height (e), and that the turbulator height to pitch ratio e/P ranges from 0.05 to 0.15.

10. The cooled blade according to claim 1 , wherein said lip overhang has a predetermined length (L), said pressure side bleed has a predetermined slot width(s), and the length of the lip overhang to the pressure side slot width ratio L/s ranges from 7 to 15.

Assignees

• Alstom Technology Ltd
• Gen Electric Technology Gmbh

Inventors

• Saxer-Felici Helen Marie
• Naik Shailendra
• Schnieder Martin

Classifications

• F05D2240/303

  related to the leading edge of a rotor blade · CPC title

• F05D2250/185

  serpentine-like · CPC title

• F05D2260/2212

  by creating turbulence · CPC title

• F05D2260/22141

  using fins or ribs · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title