Combustor with two stage primary fuel tube with concentric members and flow regulating
- Oviedo, FL
- Orlando, FL
- 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., Pittsburgh, PA (United States)
- 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
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Related Subjects
stage
primary
fuel
tube
concentric
flow
regulating
gas
turbine
centrally
located
nozzle
inner
middle
outer
cylindrical
liners
liner
enclosing
combustion
zone
air
inlet
forms
passages
pre-mixing
supplied
circumferential
array
swirl
vanes
plurality
assemblies
extend
assembly
pair
comprised
tubular
supplies
passage
extends
annular
manifold
divided
chambers
circumferentially
extending
baffle
proximal
attached
distal
directly
mid-point
inlets
communication
respectively
control
valves
separately
regulate
allowing
controlled
centrally located
concentric cylindrical
tube assemblies
fuel nozzle
control valves
pre-mixing passages
fuel tube
primary combustion
inner liner
combustion zone
gas turbine
air inlet
control valve
flow communication
annular fuel
tube assembly
primary fuel
separately controlled
outer concentric
pre-mixing passage
stage primary
pre-mixing primary
cylindrical liner
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