Crimped insert for improved turbine vane internal cooling

Patent metadata

Field	Value
Publication number	US-9879554-B2
Application number	US-201514593998-A
Country	US
Kind code	B2
Filing date	Jan 9, 2015
Priority date	Jan 9, 2015
Publication date	Jan 30, 2018
Grant date	Jan 30, 2018

Abstract

An insert tube of a turbine vane is disclosed. The insert tube includes a pressure side wall, a suction side wall opposite and spaced apart from the pressure side wall, a leading edge, and a trailing edge opposite the leading edge. The insert tube includes a plurality of cooling channels spaced along the pressure side wall. The insert tube includes an indented portion located between the trailing edge and the pressure side wall.

First claim

What is claimed is:

1. An insert tube of a turbine vane, the insert tube comprising:
a pressure side wall;
a suction side wall opposite and spaced apart from the pressure side wall;
a leading edge formed between the pressure side wall and the suction side wall at a first end of the insert tube;
a trailing edge formed between the pressure side wall and the suction side wall at a second end of the insert tube, the second end of the insert tube being located opposite the first end of the insert tube,
the pressure side wall, the suction side wall, the leading edge, and the trailing edge at least partly defining an internal volume of the insert tube;
and
an indented portion extending between the trailing edge and the pressure side wall, the indented portion including
a curved wall adjoining the pressure side wall and extending towards the suction side wall, and
a flat wall adjoining the curved wall and the trailing edge,

the pressure side wall defining a plurality of pressure side impingement apertures spaced along and extending through the pressure side wall,
the leading edge defining a plurality of leading edge impingement apertures spaced along and extending through the leading edge,
wherein the indented portion has an overall height that extends along the trailing edge, and that is defined entirely between an upper mounting section and a lower mounting section of the insert tube
the insert tube has an overall height that extends along the trailing edge.

2. The insert tube of claim 1 , wherein the curved wall extends towards the trailing edge along a radius.

3. The insert tube of claim 1 , wherein the insert tube includes an overall length, and the indented portion includes a width about 5 to 80 percent of the overall length of the insert tube.

4. The insert tube of claim 3 , wherein the trailing edge includes a diameter measured from one end of suction side wall to one end of pressure side wall, and the indented portion includes a depth that is about 20 to 80 percent of the trailing edge diameter.

5. The insert tube of claim 4 , wherein the width of the indented portion is about 4 mm, and the depth of the indented portion is about 1 mm.

6. The insert tube of claim 1 , wherein the plurality of pressure side impingement apertures propagate in a row parallel to the trailing edge.

7. The insert tube of claim 6 , wherein the plurality of pressure side impingement apertures are spaced about 4 mm from the trailing edge.

8. The insert tube of claim 1 , wherein the plurality of leading edge impingement apertures propagate in a row along the leading edge.

9. A nozzle segment for a nozzle ring of a gas turbine engine, the nozzle segment comprising:
an outer endwall;
an inner endwall;
an airfoil extending between the outer endwall and the inner endwall, the airfoil including
a leading edge extending from the outer endwall to the inner endwall,
a trailing edge extending from the outer endwall to the inner endwall distal to the leading edge,
a pressure side wall extending from the leading edge to the trailing edge,
a suction side wall extending from the leading edge to the trailing edge,
a plurality of pressure side film cooling apertures spaced along the pressure side wall,
a plurality of suction side film cooling apertures spaced along the suction side wall, and
a cavity extending from the leading edge a certain distance towards the trailing edge in one direction, and extending from the pressure side wall to the suction side wall in a perpendicular direction, the cavity including an inner wall;

an insert tube disposed within the cavity of the airfoil, the insert tube including
a pressure side wall,
a suction side wall opposite and spaced apart from the pressure side wall,
a leading edge formed between the pressure side wall and the suction side wall at a first end of the insert tube, and
a trailing edge formed between the pressure side wall and the suction side wall at a second end of the insert tube , the second end of the insert tube being located opposite the first end of the insert tube,
the pressure side wall, the suction side wall, the leading edge, and the trailing edge at least partly defining an internal volume of the insert tube; and
an indented portion located between the trailing edge and the pressure side wall, the indented portion including
a curved wall adjoining the pressure side wall and extending towards the suction side wall, and
a flat wall adjoining the curved wall and the trailing edge,

the pressure side wall defining a plurality of pressure side impingement apertures spaced along and extending through the pressure side wall,
the leading edge defining a plurality of leading edge impingement apertures spaced along and extending through the leading edge,
the inner wall of the cavity and indented portion having a clearance there between,
wherein the indented portion has an overall height that extends along the trailing edge, and that is defined entirely between an upper mounting section and a lower mounting section of the insert tube
the insert tube has an overall height that extends along the trailing edge.

10. The nozzle segment of claim 9 , wherein the clearance is formed between the indented portion and an edge of the inner wall located near the center of the airfoil.

11. The nozzle segment of claim 9 , wherein the clearance provides an open region between the indented portion and the inner wall of the cavity.

12. The nozzle segment of claim 9 , wherein the plurality of pressure side film cooling apertures propagate in a row parallel to the trailing edge.

13. The nozzle segment of claim 12 , wherein the plurality of pressure side film cooling apertures are spaced from trailing edge about 10% to 70% of a total length from the leading edge to the trailing edge.

14. The nozzle segment of claim 9 , wherein the plurality of suction side film cooling apertures propagate in a row parallel to the leading edge.

15. A insert tube for assembly in a cavity of a turbine vane, the insert tube comprising:
a pressure side wall;
a suction side wall opposite and spaced apart from the pressure side wall;
a leading edge formed between the pressure side wall and the suction side wall at a first end of the insert tube;
a trailing edge formed between the pressure side wall and the suction side wall at a second end of the insert tube, the second end of the insert tube being located opposite the first end of the insert tube,
the pressure side wall, the suction side wall, the leading edge, and the trailing edge at least partly defining an internal volume of the insert tube; and
an indented portion located between the trailing edge and the pressure side wall, the indented portion including
a first wall adjoining the pressure side wall and extending towards the suction side wall, and
a second wall adjoining the first wall and the trailing edge,

the pressure side wall defining a plurality of pressure side impingement apertures spaced along and extending through the pressure side wall,
the leading edge defining a plurality of leading edge impingement apertures spaced along and extending through the leading edge,
the indented portion being configured to be spaced apart from a wall of the cavity,
wherein the indented portion has an overall height that extends along the trailing edge, and that is defined entirely between an upper mounting section and a lower mounting section of the insert tube
the insert tube has an overall height that extends along the trailing edge.

16. The insert tube of claim 15 , wherein the indented portion is formed by c

Assignees

• Solar Turbines Inc

Inventors

• Kim Yong Weon
• Lin Tsuhon
• Carullo Jeffrey Stephen

Classifications

• F01D5/189 Primary

  the insert having a tubular cross-section, e.g. airfoil shape · CPC title

• F01D9/047 Primary

  Nozzle boxes · CPC title

• F01D9/02

  Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} · CPC title