초록 ▼

A generally annular combustor system has a chamber with an annular chamber portion and a plurality of can-like chamber portions protruding from the annular chamber portion. An external fuel/air premixer is associated with each can chamber portion to provide a mixture with a desired (generally lean)

A generally annular combustor system has a chamber with an annular chamber portion and a plurality of can-like chamber portions protruding from the annular chamber portion. An external fuel/air premixer is associated with each can chamber portion to provide a mixture with a desired (generally lean) fuel/air ratio tangentially through the can sidewall. A first portion of the total compressed air flows to the premixers, a second portion enters the combustion chamber through ports which, for can chamber volumes sufficient for complete combustion, can be located in the can chamber portion proximate the connection between the can portion and the annular portion. The premixer associated with each can chamber portion preferably includes a venturi and a fuel nozzle for spraying liquid fuel or gas into the venturi inlet to provide a fully premixed fuel/air mixture. An auxiliary fuel nozzle can be positioned in the annular portion for selectively supplying fuel for reheat of the combustion gases, using the dilution air, to maintain combustor outlet temperature. The annular chamber portion advantageously can be nested between the compressor and turbine components of large axial flow-type gas turbines in retrofit applications.

대표청구항 ▼

A combustor for combusting fuel and compressed air to produce combustion gases, for use in a gas turbine having a compressor and a turbine mounted spaced apart on a common shaft, the combustor comprising: a chamber having an annular chamber portion with an axis, a radially outer surface, and an exit

A combustor for combusting fuel and compressed air to produce combustion gases, for use in a gas turbine having a compressor and a turbine mounted spaced apart on a common shaft, the combustor comprising: a chamber having an annular chamber portion with an axis, a radially outer surface, and an exit for delivery of combustion gases, and at least one can chamber portion protruding from said radially outer surface and flow connected to said annual chamber portion, and a fuel/air inlet for admitting the fuel and the compressed air for combustion into said can chamber portion, and a fuel/air premixer cooperating with said fuel/air inlet, wherein said premixer delivers the fuel/air mixture along a direction substantially tangential to said can chamber portion axis, wherein said annual chamber portion is configured radially to surround the shaft and axially to nest between the compressor and the turbine.