Gas turbine engine

• US 9,657,575 B2
• Filed: 11/12/2013
• Issued: 05/23/2017
• Est. Priority Date: 05/13/2011
• Status: Active Grant

• Current Assignee: IHI Corporation
• Original Assignee: IHI Corporation
• Inventors: Okita, Yoji
• Primary Examiner(s): Anderson, Gregory
• Assistant Examiner(s): Adjagbe, Maxime
• Application Number:
  US14/077,460
• Publication Number:
  US 20140286773A1
• Time in Patent Office: 1,288 Days
• CPC Class Codes: F01D 5/08 Heating, heat-insulating or cooling means specially adapted for radial flow machines or engines F01D5/04
• CPC Class Codes: F01D 5/143 Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
• CPC Class Codes: F01D 5/145 Means for influencing boundary layers or secondary circulations for compressors F04D29/68
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F05D 2240/121 related to the leading edge of a stator vane
• CPC Class Codes: F05D 2240/81 Cooled platforms
• CPC Class Codes: F05D 2250/611 undulated
• CPC Class Codes: F05D 2260/202 by film cooling
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

The gas turbine engine (S1) includes: turbine blades (7b); and a cooling air supply unit (11) to supply cooling air to the turbine blades (7b). A flow path surface (31) is formed so as to be positioned in an upstream side of the turbine blades (7b) and so as to be connected to a base surface (32) in which the turbine blades (7b) are provided. The flow path surface (31) includes: depression portions (31a) depressed relative to the base surface (32), each depression portion (31a) including at least an area overlapping with a front end (7b1) of each turbine blade (7b), when viewed from a direction of the turbine axis (L); and protrusion portions (31b) protruding relative to the base surface (32), each protrusion portion (31b) being at least part of each area positioned between front ends (7b1) of the turbine blades (7b), when viewed from the above direction.

Claims

1. A gas turbine engine comprising:

a turbine blade cascade formed by annularly arranging turbine blades around a turbine axis;

a cooling air supply unit to supply cooling air to the turbine blades;

a base surface which is a surface without depression portions or protrusion portions and on which at least a trailing half of each turbine blade in a chord length direction of the turbine blade is provided, the trailing half being a portion of the turbine blade from a middle position, which is between a leading edge and a trailing edge of the turbine blade, to the trailing edge of the turbine blade; and

a flow path surface formed so as to be positioned in an upstream side of the turbine blade cascade and so as to be connected to the base surface,

wherein the flow path surface includes;

depression portions depressed relative to the base surface, each depression portion including at least an area overlapping with the leading edge of each of the turbine blades, when viewed from a direction of the turbine axis; and

protrusion portions protruding relative to the base surface, each protrusion portion being at least part of each area positioned between the leading edges of the turbine blades, when viewed from the direction of the turbine axis.

2. The gas turbine engine according to claim 1, wherein

a depression area formed by the depression portion and the base surface viewed from the direction of the turbine axis, and a protrusion area formed by the protrusion portion and the base surface viewed from the direction of the turbine axis are set equal to each other.

3. The gas turbine engine according to claim 1, wherein

the turbine blades are turbine stator blades.

4. The gas turbine engine according to claim 2, wherein

the turbine blades are turbine stator blades.

5. The gas turbine engine according to claim 1, wherein a width of each of the depression portions in a circumferential direction around the turbine axis is greater than a width of each of the protrusion portions in the circumferential direction.

6. The gas turbine engine according to claim 1, wherein the depression portions and the protrusion portions are provided in the flow path surface of an outer end wall.