Turbine combustor transition piece having dilution holes

• US 20050204741A1
• Filed: 03/17/2004
• Published: 09/22/2005
• Est. Priority Date: 03/17/2004
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Simons, Derrick Walter, Romoser, Carey Edward, Gupta, Aja Kumar
• Granted Patent: US 7,373,772 B2
• Time in Patent Office: Days
• US Class Current: 60/752
• CPC Class Codes: F01D 9/023 Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
• CPC Class Codes: F05D 2270/082 with as little NOx as possible

Abstract

A transition piece body, having an inlet end for receiving combustion products from a turbine combustor and an outlet end for flowing the gaseous products into a first stage nozzle, has dilution holes in zones respectively adjacent the transition piece body inlet and outlet ends. The volume of dilution air flowing into the gas stream is substantially equal at the inlet and outlet ends of the transition piece. The locations and sizes of the openings are given in the respective X, Y, Z coordinates and hole diameters in Table I. The X and Y coordinates lie in the circular plane of the transition body at its inlet end and the Z coordinates extend in the direction of gas flow from the origin.

Claims

1. A combustion system component for location between a turbine combustor and a first stage turbine airfoil, comprising:

a transition piece including a body defining a flowpath and having a generally circular inlet end for receiving combustion products from the combustor and a generally rectilinear outlet end for flowing the combustor products into the first stage nozzle;

said body defining between said inlet end and said outlet end an enclosure for confining the flow of combustion products between said ends;

a plurality of dilution holes formed in said transition piece body in a first zone adjacent said inlet end and in a second zone adjacent said outlet end for flowing dilution air into the transition piece body;

said dilution holes being sized such that substantial equal quantities of the dilution air flow into the flowpath in said zones, respectively.

2. A system according to claim 1 wherein said plurality of holes in said first and second zones are unequal in number to one another.

3. A system according to claim 1 wherein said first zone includes three holes and said second zone includes four holes.

4. A system according to claim 1 wherein said holes are located in said transition piece body in accordance with the hole numbers ) through >

and X, Y, Z coordinates set forth in Table I wherein the X, Y, Z coordinates have an origin at the center of the circular inlet end with the Z coordinates extending from the origin in a downstream flow direction toward the outlet end, said holes lying along said transition piece body in an envelope within one inch in any direction along the surface of the transition piece body from the locations of the holes determined by said X, Y, Z coordinates.

5. A system according to claim 1 wherein said holes in said transition piece body in said first zone are circular and have equal diameters.

6. A system according to claim 1 wherein said holes in said transition piece body in said second zone are four in number, with at least a pair of said four holes being circular and equal in diameter.

7. A system according to claim 6 wherein said holes in said transition piece body in said first zone are three in number with each hole being circular and equal in diameter to other holes in said first zone.

8. A system according to claim 1 wherein said holes have a total area of about 7.10 square inches.

9. A combustion system component for location between a turbine combustor and a first stage turbine nozzle, comprising:

a transition piece including a body defining a flowpath and having a generally circular inlet end for receiving combustion products from the combustor and a generally rectilinear outlet end for flowing the combustor products into the first stage nozzle;

said body defining between said inlet end and said outlet end an enclosure for confining the flow of combustion products between said ends; and

a plurality of dilution holes formed in said body, said holes being located in said transition piece body in accordance with the hole numbers ) through > and

X, Y, Z coordinates set forth in Table I wherein the X, Y, Z coordinates have an origin at the center of the circular inlet end with the Z coordinates extending from the origin in a downstream flow direction toward the outlet end, said holes lying along said transition piece body in an envelope within one inch in any direction along the surface of the transition piece body from the locations of the holes determined by said X, Y, Z coordinates.

10. A system according to claim 9 wherein said holes in said transition piece body in said first zone are circular and have equal diameters.

11. A system according to claim 9 wherein said holes in said transition piece body in said second zone are four in number, with at least a pair of said four holes being circular and equal in diameter.

12. A system according to claim 11 wherein said holes in said transition piece body in said first zone are three in number with each hole being circular and equal in diameter to other holes in said first zone.

13. A system according to claim 12 wherein said holes have a total area of about 7.10 square inches.