Sectoral combustor for burning low-BTU fuel gas

Patent · Tue Jan 01 00:00:00 EST 1980

OSTI ID:863732

Vogt, Robert L ^[1]

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1. Schenectady, NY

A high-temperature combustor for burning low-BTU coal gas in a gas turbine is disclosed. The combustor includes several separately removable combustion chambers each having an annular sectoral cross section and a double-walled construction permitting separation of stresses due to pressure forces and stresses due to thermal effects. Arrangements are described for air-cooling each combustion chamber using countercurrent convective cooling flow between an outer shell wall and an inner liner wall and using film cooling flow through liner panel grooves and along the inner liner wall surface, and for admitting all coolant flow to the gas path within the inner liner wall. Also described are systems for supplying coal gas, combustion air, and dilution air to the combustion zone, and a liquid fuel nozzle for use during low-load operation. The disclosed combustor is fully air-cooled, requires no transition section to interface with a turbine nozzle, and is operable at firing temperatures of up to 3000.degree. F. or within approximately 300.degree. F. of the adiabatic stoichiometric limit of the coal gas used as fuel.

• Research Organization: General Electric Co., Boston, MA (United States)
• DOE Contract Number: EX-76-C-01-1806
• Assignee: General Electric Company (Schenectady, NY)
• Patent Number(s): US 4236378
• OSTI ID: 863732
• Country of Publication: United States
• Language: English

Related Subjects

sectoral
combustor
burning
low-btu
fuel
gas
high-temperature
coal
turbine
disclosed
separately
removable
combustion
chambers
annular
section
double-walled
construction
permitting
separation
stresses
due
pressure
forces
thermal
effects
arrangements
described
air-cooling
chamber
countercurrent
convective
cooling
flow
outer
shell
wall
inner
liner
film
panel
grooves
surface
admitting
coolant
path
systems
supplying
air
dilution
zone
liquid
nozzle
low-load
operation
air-cooled
requires
transition
interface
operable
firing
temperatures
3000
degree
approximately
300
adiabatic
stoichiometric
limit
burning low-btu
pressure forces
fuel nozzle
low-btu coal
wall surface
turbine nozzle
inner liner
outer shell
fuel gas
combustion zone
combustion chamber
gas turbine
coolant flow
combustion air
liquid fuel
coal gas
transition section
sectoral combustor
shell wall
thermal effects
combustion chambers
stresses due
cooling flow
convective cooling
gas path
low-btu fuel
high-temperature combustor
btu coal
btu fuel
/60/