Cooling of liquid fuel cartridge in gas turbine combustor head end

Patent metadata

Field	Value
Publication number	US-10655858-B2
Application number	US-201715625061-A
Country	US
Kind code	B2
Filing date	Jun 16, 2017
Priority date	Jun 16, 2017
Publication date	May 19, 2020
Grant date	May 19, 2020

Abstract

The present disclosure provides assemblies for cooling a liquid fuel cartridge unit within a combustor head end. In one embodiment, the cooling is accomplished passively as air from the head end air plenum is directed into a cooling channel radially outward of a liquid fuel delivery conduit. In another embodiment, the cooling of the liquid fuel cartridge unit is accomplished actively as air is directed through a first air flow conduit radially inward of the liquid fuel delivery conduit and then redirected through a second air flow conduit radially outward of the liquid fuel delivery conduit.

First claim

What is claimed is:

1. A combustor head end comprising:
an end cover;
a cap axially spaced from the end cover;
a sleeve extending axially between the end cover and the cap, thereby defining a head end air plenum;
a center bundled tube fuel nozzle disposed along a longitudinal axis of the combustor head end, the center bundled tube fuel nozzle comprising an upstream plate, an aft plate, a shroud extending axially between the upstream plate and the aft plate to define a fuel plenum, a plurality of premixing tubes extending through the fuel plenum and the cap, such that outlets of the plurality of premixing tubes are downstream of the cap;
a mounting flange attached to a hot side of the end cover, the mounting flange defining at least one air flow passage in flow communication with the head end air plenum; and
a liquid fuel cartridge extending through the mounting flange, the liquid fuel cartridge comprising a nozzle tip extending downstream of the cap, a liquid fuel delivery conduit in flow communication with the nozzle tip, and a cooling channel in flow communication with the nozzle tip;
wherein air from the head end air plenum flows through the at least one air flow passage in the mounting flange into the cooling channel and exits through at least one cooling hole in the nozzle tip.

2. The combustor head end of claim 1 , wherein the at least one air flow passage in the mounting flange comprises a plurality of apertures circumferentially spaced about the mounting flange.

3. The combustor head end of claim 1 , wherein the liquid fuel cartridge further comprises a cartridge mounting flange, the cartridge mounting flange being mounted to a cold side of the end cover.

4. The combustor head end of claim 1 , wherein the liquid fuel cartridge comprises a first tube surrounded by a second tube, the first tube being the liquid fuel delivery conduit, the liquid fuel delivery conduit being in flow communication with a liquid fuel supply.

5. The combustor head end of claim 4 , wherein the second tube defines, at an upstream end thereof, at least one port in flow communication with the air from the head end plenum, via the at least one air flow passage in the mounting flange.

6. The combustor head end of claim 1 , wherein the nozzle tip comprises a plurality of fuel injection ports configured to direct the liquid fuel in a predominantly radial direction relative to a longitudinal axis of the liquid fuel cartridge.

7. The combustor head end of claim 1 , wherein the liquid fuel cartridge extends coaxially through the center bundled tube fuel nozzle, the nozzle tip of the liquid fuel cartridge projecting axially downstream of the outlets of the plurality of premixing tubes.

8. The combustor head end of claim 1 , further comprising a plurality of outer bundled tube fuel nozzles circumferentially surrounding the center bundled tube fuel nozzle.

Assignees

• Gen Electric

Inventors

• Bailey Donald Mark
• Stoia Lucas John
• Purcell Timothy James

Classifications

• F23R3/286

  having fuel-air premixing devices (F23R3/30 takes precedence) · 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

• F23R3/04

  Air inlet arrangements · CPC title

• F23R3/34

  Feeding into different combustion zones · CPC title

• F23R3/36

  Supply of different fuels · CPC title