Turbine blade

Patent metadata

Field	Value
Publication number	US-9771806-B2
Application number	US-201414287623-A
Country	US
Kind code	B2
Filing date	May 27, 2014
Priority date	Nov 30, 2011
Publication date	Sep 26, 2017
Grant date	Sep 26, 2017

Abstract

A turbine blade has hollowness, and is provided with a back-side wall of which a portion of the inner wall surface is exposed at the rear edge portion, with cooling air flown along the inner wall surface at the exposed region; and a recess provided in the inner wall surface at the exposed region. The contour of the recess ( 5 ) viewed from the normal direction of the inner wall surface of the back-side wall is set to a shape that is symmetrical centered on a reference axis (L) that intersects the flow direction of cooling air, and that broadens along the reference axis (L).

First claim

The invention claimed is:

1. A turbine blade having hollowness, comprising a front-side wall in which a blowout port is provided at the rear edge portion; a back-side wall of which a portion of the inner wall surface is exposed from the blowout port, with cooling air flowing along the inner wall surface at the exposed region; and a first recess provided in the inner wall surface of the back-side wall at the exposed region,
wherein the contour of the first recess, viewed from the normal direction of the inner wall surface of the back-side wall, is set to a shape that is symmetrical centered on a reference axis that intersects the flow direction of cooling air at 45 degrees with respect to the flow direction of cooling air, and that broadens along the reference axis,
the first recess is further provided in a partial region of the inner wall surface of the back-side wall that faces the front-side wall and is continuous with the exposed region,
a second recess having the same shape as the first recess is further provided in a region that is a partial region of the inner wall surface of the front-side wall, and that faces the partial region of the inner wall surface of the back-side wall in which the first recess is provided, and
perpendicular cross-sectional shapes of the first recess and the second recess include respective circular arcs with a depth equivalent to 0.3 multiplied by a diameter of a respective circle including a respective circular arc of the respective circular arcs.

2. The turbine blade according to claim 1 , wherein the shape of the first recess in a perpendicular cross-section of the inner wall surface of the back-side wall passing along the reference axis comprises a linear-shaped region heading from a blade leading edge side end to the deepest portion of the first recess arranged nearer the blade trailing edge, and an arc-shaped region that connects the deepest portion and the blade trailing edge side end.

3. The turbine blade according to claim 1 , wherein a plurality of the first recesses are provided in the back-side wall, with the reference axis of each first recess having the same orientation.

4. The turbine blade according to claim 1 , wherein a bottom of the first recess in the partial region of the inner wall surface of the back-side wall is completely located in the back-side wall and a bottom of the second recess in the partial region of the inner wall surface of the front-side wall is completely located in the front-side wall.

5. The turbine blade according to claim 1 , wherein the shape of the second recess in a perpendicular cross-section of the inner wall surface of the front-side wall passing along the reference axis comprises a linear-shaped region heading from a blade leading edge side end to the deepest portion of the second recess arranged nearer the blade trailing edge, and an arc-shaped region that connects the deepest portion and the blade trailing edge side end.

6. The turbine blade according to claim 1 , wherein a plurality of the second recesses are provided in the front-side wall, with the reference axis of each second recess having the same orientation.

Assignees

• Ihi Corp
• The Soc Of Japanese Aerospace Companies

Inventors

• Okita Yoji
• Murata Akira

Classifications

• F05D2240/304

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

• F01D5/186 Primary

  Film cooling (F01D5/187 takes precedence) · CPC title

• F05D2260/2214

  by increasing the heat transfer surface · CPC title

• F05D2240/122

  related to the trailing edge of a stator vane · CPC title

• F05D2240/31

  with roughened surfaces · CPC title