Integrated fuel nozzle connection

Patent metadata

Field	Value
Publication number	US-2019017444-A1
Application number	US-201715649853-A
Country	US
Kind code	A1
Filing date	Jul 14, 2017
Priority date	Jul 14, 2017
Publication date	Jan 17, 2019
Grant date	—

Abstract

A gas turbine includes a compressor, a turbine, and a combustor disposed downstream from the compressor and upstream from the turbine. The combustor includes an end cover. The combustor also includes a flange. The flange includes an internal fluid passage defined within the flange and the flange is coupled to an internal face of the end cover. A fuel port is integrally joined with the flange. The fuel port extends through the end cover between the flange and an inlet positioned outside of the end cover. The inlet of the fuel port is in fluid communication with the internal fluid passage of the flange.

First claim

What is claimed is:

1 . A gas turbine, comprising:
a compressor; a turbine; a combustor disposed downstream from the compressor and upstream from the turbine, the combustor comprising:
an end cover;
a flange comprising an internal fluid passage defined within the flange, the flange coupled to an internal face of the end cover; and
a fuel port integrally joined with the flange, the fuel port extending through the end cover between the flange and an inlet positioned outside of the end cover, the inlet of the fuel port in fluid communication with the internal fluid passage of the flange.

2 . The gas turbine of claim 1 , wherein the flange extends between a first side and a second side opposing the first side, the first side of the flange abutting the internal face of the end cover, and further comprising a fluid conduit extending between the second side of the flange and a fuel nozzle.

3 . The gas turbine of claim 2 , wherein the fuel port extends between the inlet and the first side of the flange.

4 . The gas turbine of claim 1 , further comprising a filter positioned within the fuel port such that the inlet of the fuel port is in fluid communication with the internal fluid passage of the flange via the filter.

5 . The gas turbine of claim 1 , further comprising an orifice fitting coupled to an inlet of the internal fluid passage of the flange such that the inlet of the fuel port is in fluid communication with the internal fluid passage of the flange via the orifice fitting.

6 . The gas turbine of claim 5 , further comprising a filter upstream of the orifice fitting such that the inlet of the fuel port is in fluid communication with the internal fluid passage of the flange via the filter and the orifice fitting.

7 . The gas turbine of claim 5 , further comprising a filter integrally joined with the orifice fitting, the filter positioned within the fuel port upstream of the orifice fitting such that the inlet of the fuel port is in fluid communication with the internal fluid passage of the flange via the filter and the orifice fitting.

8 . The gas turbine of claim 1 , wherein the fuel port passes through a bore of the end cover, and further comprising a seal groove surrounding the bore of the end cover.

9 . The gas turbine of claim 1 , wherein the fuel port is offset from the bore of the end cover such that an annular passage is defined between the fuel port and the bore of the end cover.

10 . The gas turbine of claim 1 , wherein the flange comprises a thermal shield, the internal fluid passage of the flange at least partially defined in the thermal shield.

11 . A combustor for a turbomachine, the combustor comprising:
an end cover; a flange comprising an internal fluid passage defined within the flange, the flange coupled to an internal side of the end cover; and a fuel port integrally joined with the flange, the fuel port extending through the end cover between the flange and an inlet positioned outside of the end cover, the inlet of the fuel port in fluid communication with the internal fluid passage of the flange.

12 . The combustor of claim 11 , wherein the flange extends between a first side and a second side opposing the first side, the first side of the flange abutting the end cover, and further comprising a fluid conduit extending between the second side of the flange and a fuel nozzle.

13 . The combustor of claim 12 , wherein the fuel port extends between the inlet and the first side of the flange.

14 . The combustor of claim 11 , further comprising a filter positioned within the fuel port such that the inlet of the fuel port is in fluid communication with the internal fluid passage of the flange via the filter.

15 . The combustor of claim 11 , further comprising an orifice fitting coupled to an inlet of the internal fluid passage of the flange such that the inlet of the fuel port is in fluid communication with the internal fluid passage of the flange via the orifice fitting.

16 . The combustor of claim 15 , further comprising a filter upstream of the orifice fitting such that the inlet of the fuel port is in fluid communication with the internal fluid passage of the flange via the filter and the orifice fitting.

17 . The combustor of claim 15 , further comprising a filter integrally joined with the orifice fitting, the filter positioned within the fuel port upstream of the orifice fitting such that the inlet of the fuel port is in fluid communication with the internal fluid passage of the flange via the filter and the orifice fitting.

18 . The combustor of claim 11 , wherein the fuel port passes through a bore of the end cover, and further comprising a seal groove surrounding the bore of the end cover.

19 . The combustor of claim 11 , wherein the fuel port is offset from the bore of the end cover such that an annular passage is defined between the fuel port and the bore of the end cover.

20 . The combustor of claim 11 , wherein the flange comprises a thermal shield, the internal fluid passage of the flange at least partially defined in the thermal shield.

Assignees

• Gen Electric

Inventors

• Annamalai Subramanian
• Stoia Lucas John
• Bobba Mohan Krishna

Classifications

• F23K2300/202

  Filtering · CPC title

• F23R3/283

  Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances · CPC title

• F23R2900/00005

  Preventing fatigue failures or reducing mechanical stress in gas turbine components · CPC title

• F23K5/14 Primary

  Details thereof · CPC title

• F02C7/057

  Control or regulation (conjointly with fuel supply control F02C9/50, with nozzle area control F02K1/16) · CPC title