Catalytic combustion system

A catalytic combustion system, comprising:

• a gas turbine engine including a compressor, a turbine, and a recuperator;
• an annular pre-burner/pre-mixer to receive heated compressed air from said gas turbine engine recuperator, said annular pre-burner/pre-mixer including near a closed end thereof a plurality of primary tangential air-fuel venturis each having a fuel injector, and a plurality of secondary tangential air dilution holes downstream from said plurality of primary tangential air-fuel venturis;
• an annular catalyst canister axially in-line with said annular pre-burner/pre-mixer and including a plurality of microlith catalyst elements;
• and
• an annular transition section connecting said annular pre-burner/pre-mixer to said annular catalyst canister, the inner diameter of said annular transition section including a plurality of tertiary air dilution holes,
• said annular pre-burner/pre-mixer to supply combustion products to said annular catalyst canister during system startup and a vaporized fuel-air mixture to said annular catalyst canister during catalytic system operation when said catalyst canister supplies combustion products to said turbine of said gas turbine engine.

A catalytic combustion system, comprising:

• a gas turbine engine including a compressor and a turbine on a common shaft, and a recuperator heating the incoming air from said compressor with exhaust gases from said turbine, said turbine including a turbine exhaust tube;
• an inner liner disposed around said turbine exhaust tube;
• an annular catalyst canister formed around the turbine end of said inner liner, said catalyst canister including a plurality of microlith catalyst elements;
• an annular pre-burner/pre-mixer formed around the other end of said inner liner to receive heated compressed air from said recuperator, said annular pre-burner/pre-mixer having a smaller outer diameter than said annular catalyst canister and including near a closed end thereof a plurality of primary tangential air-fuel venturis each having a fuel injector, a plurality of secondary tangential air dilution holes downstream from said plurality of primary tangential air-fuel venturis, and an ignitor at the closed end thereof;
• and
• an annular transition section formed around the central portion of said inner liner to join said annular pre-burner/pre-mixer with said annular catalyst canister, the inner liner of said annular transition section including a plurality of tertiary radial air dilution holes,
• said annular pre-burner/pre-mixer to supply combustion products to said annular catalyst canister during system startup and a vaporized fuel-air mixture to said annular catalyst canister during catalytic system operation when said catalyst canister supplies combustion products to said turbine of said gas turbine engine.