Nozzle having an orifice plug for a gas turbomachine

Patent metadata

Field	Value
Publication number	US-9546600-B2
Application number	US-201414457505-A
Country	US
Kind code	B2
Filing date	Aug 12, 2014
Priority date	Aug 12, 2014
Publication date	Jan 17, 2017
Grant date	Jan 17, 2017

Abstract

A gas turbomachine nozzle includes a base portion having a first fluid inlet and a second fluid inlet, and an outlet portion having one or more outlets. A connection section fluidically connects the base portion and the outlet portion. An orifice plug is arranged in the base portion at the second fluid inlet. The orifice plug includes one or more openings fluidically connecting the second fluid inlet and the connection section.

First claim

What is claimed is:

1. A nozzle for a gas turbine engine, comprising:
a base portion including a first axial end of the nozzle;
an outlet portion including a second axial end of the nozzle, wherein the second axial end is the axially opposite end of the nozzle relative to the first axial end;
a connection section extending from the base portion to the outlet portion, wherein the connection section couples the base portion to the outlet portion;
a first passage having a first inlet at the first axial end and a first passage outlet at the second axial end; and
a second passage radially outward of the first passage, wherein the second passage is a fuel passage, the second passage having a second inlet at the first axial end, a second outlet at the second axial end, an aperture located in the base portion radially outward of the second inlet, and a base portion opening located in the base portion radially inward of the second inlet, wherein the first passage and the second passage extend through the base portion, the outlet portion, and the connection section;
an orifice plug comprising:
a plug section;
a base section defining one or more base section openings extending therethrough; and
an intermediate section located between the plug section and the base section, wherein the intermediate section couples the base section to the plug section, wherein the plug section is positioned in the aperture and the base section is positioned in the base portion opening.

2. The nozzle of claim 1 , wherein the base portion comprises a base surface, and wherein the first inlet and the second inlet are defined by the base surface.

3. The nozzle of claim 1 , wherein the plug section occludes the aperture.

4. The nozzle of claim 1 , wherein the base section and the plug section comprise a first diameter and the intermediate section comprises a second diameter, and wherein the second diameter is smaller than the first diameter.

5. A gas turbine engine, comprising:
a compressor portion;
a turbine portion; and
a combustor assembly comprising one or more nozzles, the one or more nozzles comprising:
a base portion including a first axial end of the nozzle;
an outlet portion including a second axial end of the nozzle, wherein the second axial end is the axially opposite end of the nozzle relative to the first axial end;
a connection section extending from the base portion to the outlet portion, wherein the connection section couples the base portion to the outlet portion;
a first passage having a first inlet at the first axial end and a first passage outlet at the second axial end; and
a second passage radially outward of the first passage, wherein the second passage is a fuel passage, the second passage having a second inlet at the first axial end, a second outlet at the second axial end, an aperture located in the base portion radially outward of the second inlet, and a base portion opening located in the base portion radially inward of the second inlet, wherein the first passage and the second passage extend through the base portion, the outlet portion, and the connection section;
an orifice plug comprising:
a plug section;
a base section defining a plurality of base section openings extending therethrough; and
an intermediate section located between the plug section and the base section, wherein the intermediate section couples the base section to the plug section, wherein the plug section is positioned in the aperture and the base section is positioned in the base portion opening.

6. The gas turbine engine of claim 5 , wherein the base portion comprises a base surface, and wherein the first inlet and the second inlet are defined by the base surface.

7. The gas turbine engine of claim 5 , wherein the plug section occludes the aperture.

8. The gas turbine engine of claim 5 , wherein the base section and the plug section comprise a first diameter and the intermediate section comprises a second diameter, and wherein the second diameter is smaller than the first diameter.

9. A gas turbine engine system, comprising:
a compressor portion;
a turbine portion;
an inlet system;
a load coupled to the compressor portion or the turbine portion;
a combustor assembly comprising one or more nozzles, the one or more nozzles comprising:
a base portion including a first axial end of the nozzle;
an outlet portion including a second axial end of the nozzle, wherein the second axial end is the axially opposite end of the nozzle relative to the first axial end;
a connection section extending from the base portion to the outlet portion, wherein the connection section couples the base portion to the outlet portion;
a first passage having a first inlet at the first axial end and a first passage outlet at the second axial end; and
a second passage radially outward of the first passage, wherein the second passage is a fuel passage, the second passage having a second inlet at the first axial end, a second outlet at the second axial end, an aperture located in the base portion radially outward of the second inlet, and a base portion opening located in the base portion radially inward of the second inlet, wherein the first passage and the second passage extend through the base portion, the outlet portion, and the connection section;
an orifice plug comprising:
a plug section;
a base section defining a plurality of base section openings extending therethrough; and
an intermediate section located between the plug section and the base section, wherein the intermediate section couples the base section to the plug section, wherein the plug section is positioned in the aperture and the base section is positioned in the base portion opening.

10. The gas turbine engine system of claim 9 , wherein the base portion comprises a base surface, and wherein the first inlet and the second inlet are defined by the base surface.

11. The gas turbine engine system of claim 9 , wherein the plug section occludes the aperture.

12. The gas turbine engine system of claim 9 , wherein the base section and the plug section comprise a first diameter and the intermediate section comprises a second diameter, and wherein the second diameter is smaller than the first diameter.

Assignees

• Gen Electric

Inventors

• Cihlar David William
• Hu Zhaoli
• Melton Patrick Benedict
• Woodlock Kevin

Classifications

• F23R3/14

  by using swirl vanes · CPC title

• F02C7/22 Primary

  Fuel supply systems · CPC title

• F23R3/343

  Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion (ignition in gas-turbine plants F02C7/264; pilot flame igniters F23Q9/00) · CPC title

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• F23R3/28 Primary

  characterised by the fuel supply (burners F23D) · CPC title