Combustor with two stage primary fuel tube with concentric members and flow regulating

Patent · 01 January 1999

OSTI ID:872661

Parker, David Marchant ^[1]; Whidden, Graydon Lane ^[2]; Zolyomi, Wendel ^[3]

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1. Oviedo, FL
2. Orlando, FL
3. Lawrenceville, GA

A combustor for a gas turbine having a centrally located fuel nozzle and inner, middle and outer concentric cylindrical liners, the inner liner enclosing a primary combustion zone. The combustor has an air inlet that forms two passages for pre-mixing primary fuel and air to be supplied to the primary combustion zone. Each of the pre-mixing passages has a circumferential array of swirl vanes. A plurality of primary fuel tube assemblies extend through both pre-mixing passages, with each primary fuel tube assembly located between a pair of swirl vanes. Each primary fuel tube assembly is comprised of two tubular members. The first member supplies fuel to the first pre-mixing passage, while the second member, which extends through the first member, supplies fuel to the second pre-mixing passage. An annular fuel manifold is divided into first and second chambers by a circumferentially extending baffle. The proximal end of the first member is attached to the manifold itself while the proximal end of the second member is attached to the baffle. The distal end of the first member is attached directly to the second member at around its mid-point. The inlets of the first and second members are in flow communication with the first and second manifold chambers, respectively. Control valves separately regulate the flow of fuel to the two chambers and, therefore, to the two members of the fuel tube assemblies, thereby allowing the flow of fuel to the first and second pre-mixing passages to be separately controlled.

• Research Organization: Westinghouse Electric Corp
• DOE Contract Number: FC21-95MC32267
• Assignee: Siemens Westinghouse Power Corporation (Orlando, FL)
• Patent Number(s): US 5983642
• OSTI ID: 872661
• Country of Publication: United States
• Language: English

Related Subjects

/60/239/431/
air
air inlet
allowing
annular
annular fuel
array
assemblies
assembly
attached
baffle
centrally
centrally located
chambers
circumferential
circumferentially
combustion
combustion zone
combustor
communication
comprised
concentric
concentric cylindrical
control
control valve
control valves
controlled
cylindrical
cylindrical liner
directly
distal
divided
enclosing
extend
extending
extends
flow
flow communication
forms
fuel
fuel nozzle
fuel tube
gas
gas turbine
inlet
inlets
inner
inner liner
liner
liners
located
manifold
mid-point
middle
nozzle
outer
outer concentric
pair
passage
passages
plurality
pre-mixing
pre-mixing passage
pre-mixing passages
pre-mixing primary
primary
primary combustion
primary fuel
proximal
regulate
regulating
respectively
separately
separately controlled
stage
stage primary
supplied
supplies
swirl
tube
tube assemblies
tube assembly
tubular
turbine
valves
vanes
zone