초록 ▼

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

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°F. or within approximately 300°F. of the adiabatic stoichiometric limit of the coal gas used as fuel.

대표청구항 ▼

A combustion chamber operable to burn low-BTU fuel gas in a gas turbine comprising: an outer shell wall of corrugated construction; a liner wall comprising a plurality of liner panels each having an upstream end supported in overlapping relationship with the downstream end of an adjacent liner panel

A combustion chamber operable to burn low-BTU fuel gas in a gas turbine comprising: an outer shell wall of corrugated construction; a liner wall comprising a plurality of liner panels each having an upstream end supported in overlapping relationship with the downstream end of an adjacent liner panel, said liner wall housed coaxially within said shell wall and having an outer surface and an inner surface, said shell wall and said liner wall each having a cross section of a shape substantially equal to an annular sector of said gas turbine; said liner wall defining internally thereof a combustion zone and further defining between said liner wall and said shell wall a coolant channel for the flow of air in countercurrent relationship to flow in said combustion zone for cooling said liner wall outer surface; liner attachment means for supporting said liner wall from said shell wall said liner attachment means including a plurality of panel supports comprising an elongated rib or bulb rigidly attached to said inner wall and aligned approximately parallel to the direction of the countercurrent coolant flow in said coolant channel; air supply means for introducing combustion air to said combustion zone; and fuel supply means for introducing fuel gas and liquid fuel to said combustion zone.