Solid fuel combustion system for gas turbine engine

In a gas turbine engine including

• an engine case having a compressed air plenum therein,
• a compressor rotatable about an axis of said engine case and discharging compressed air into said compressed air plenum, and
• a turbine rotatable as a unit with said compressor and including a circumferential turbine blade stage in an annular gas flow path of said engine case,
• a solid fuel, pressurized fluidized bed combustion system comprising:
• a first conduit means connected to said engine case for transferring therefrom a first fraction of compressor discharge,
• a second conduit means connected to said engine case for transferring therefrom a second fraction of compressor discharge,
• a carbonizer means outside of said engine case connected to a supply of coal and to said first conduit means operative to produce from partial combustion of said coal in said first fraction of compressor discharge a continuous stream of low Btu combustible fuel gas and a residue of combustible solid char,
• a pressurized fluidized bed means outside of said engine case receiving said char from said carbonizer means and connected to said second conduit means operative to produce from further combustion of said char in said second fraction of compressor discharge a continuous stream of vitiated air at a temperature not exceeding the slagging temperature of said char,
• a topping combustor means inside said engine case in said compressed air plenum including in serial connection a rich zone and a quench zone and a lean zone,
• a third conduit means between said pressurized fluidized bed means and said rich zone for introducing said continuous stream of vitiated air into said rich zone,
• a fourth conduit means between said topping combustor means and said rich zone for introducing said continuous stream of low Btu combustible fuel gas into said rich zone for partial combustion in said said continuous stream of vitiated air at an equivalence ratio exceeding 1.0 to produce a continuous stream of ultra-low Btu combustible gas at a temperature above the slagging temperature of said char,
• quench air inlet means in said topping combustor for introducing compressed air from said compressed air plenum into said quench zone to quench said continuous stream of ultra-low Btu combustible gas and to support complete combustion of said ultra-low BTU fuel gas in said lean zone at an equivalence ratio of less than 1.0 whereby the temperature of said continuous stream of vitiated air is increased to above the slagging temperature of said char, and
• transition tube means for transferring said higher temperature vitiated air from said lean zone to said annular gas flow path of said engine.