System and method for integrating sections of a turbine

Patent metadata

Field	Value
Publication number	US-9284853-B2
Application number	US-201113277972-A
Country	US
Kind code	B2
Filing date	Oct 20, 2011
Priority date	Oct 20, 2011
Publication date	Mar 15, 2016
Grant date	Mar 15, 2016

Abstract

A system and method for integrating sections of a turbine are provided. In one system, a turbine includes a last stage bucket section with a first annular outer wall that is angled with respect to a centerline of the turbine at a first angle average. The turbine also includes a diffuser section having a second annular outer wall that is angled with respect to the centerline of the turbine at a second angle average for improving radial swirl. The first angle average is greater than the second angle average.

First claim

The invention claimed is:

1. A system, comprising:
a gas turbine, comprising:
a last stage bucket section having a first annular outer wall that is angled with respect to a centerline of the gas turbine at a first angle average; and
an axial diffuser section disposed immediately downstream of the last stage bucket section, the axial diffuser section having a second annular outer wall that is angled with respect to the centerline of the gas turbine at a second angle average for improving radial swirl,
wherein the first angle average is approximately 20-30 degrees, the second angle average is approximately 12-20 degrees, the first angle average is approximately 2-15 degrees greater than the second angle average, the last stage bucket section and the axial diffuser section couple to one another at a transition point, and a first angle of the last stage bucket section with respect to the centerline is greater than a second angle of the axial diffuser section with respect to the centerline at the transition point.

2. The system of claim 1 , wherein the first angle average is greater than the second angle average by approximately 6.75 degrees.

3. The system of claim 1 , wherein the first angle average is approximately 25 degrees.

4. The system of claim 1 , wherein the second angle average is approximately 19 degrees.

5. The system of claim 1 , wherein the second angle average is substantially constant.

6. A system, comprising:
a gas turbine having an outer wall transition from a last stage bucket outer wall directly to an axial diffuser section outer wall, wherein the last stage bucket outer wall is angled away from a centerline of the gas turbine at a first angle that is approximately 2-15 degrees greater than a second angle at which the axial diffuser section outer wall is angled away from the centerline of the gas turbine at the outer wall transition, wherein the first angle is approximately 20-30 degrees, and the second angle is approximately 12-20 degrees.

7. The system of claim 6 , wherein the first angle is greater than the second angle by approximately 6.75 degrees.

8. The system of claim 6 , wherein the first angle is approximately 22 degrees, and the second angle is approximately 17 degrees.

9. A method, comprising:
providing a last stage bucket section of a gas turbine that is outwardly angled with respect to an axial centerline of the last stage bucket section from a first axial end of the last stage bucket section to a second axial end of the last stage bucket section at a substantially constant first angle;
providing an axial diffuser section of the gas turbine that is outwardly angled with respect to an axial centerline of the axial diffuser section at a first axial end of the axial diffuser section at a second angle;
providing the last stage bucket section that is outwardly angled at the substantially constant first angle of approximately 20-30 degrees, and the axial diffuser section that is outwardly angled at the second angle of approximately 12-20 degrees; and
attaching the second axial end of the last stage bucket section to the first axial end of the axial diffuser section at a transition point, wherein the first angle is approximately 2-15 degrees greater than the second angle at the transition point.

10. The method of claim 9 , comprising providing the last stage bucket section that is outwardly angled at the substantially constant first angle of approximately 22 degrees, and providing the axial diffuser section that is outwardly angled at the second angle of approximately 17 degrees.

Assignees

• Nanda Deepesh Dinesh
• Siden Gunnar Leif
• Bielek Craig Allen
• Gen Electric

Inventors

• Nanda Deepesh Dinesh
• Siden Gunnar Leif
• Bielek Craig Allen

Classifications

• F01D25/30 Primary

  Exhaust heads, chambers, or the like · CPC title

• F05D2250/324

  divergent · CPC title

• F05D2220/3215

  the last stage of the turbine · CPC title

• F05D2220/31

  in steam turbines · CPC title