Catalytic combustion system

Claim 2

A catalytic combustion system for a recuperated gas turbine engine, comprising: an annular catalyst canister including a plurality of catalyst elements; an annular pre-burner/pre-mixer axially in line with said annular catalyst canister 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, 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; 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.

Claim 3

The catalytic combustion system of claim 1 and in addition, means operably associated with said fuel injectors to pulse off the flow of fuel to quench the combustion flame in said annular pre-burner/pre-mixer once the light-off temperature of the catalyst elements is reached.

Claim 4

The catalytic combustion system of claim 1 wherein said annular pre-burner/pre-mixer has a smaller outer diameter than said annular catalyst canister.

Claim 5

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.

Claim 6

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.

Claim 7

The catalytic combustion system of claim 4 and in addition, means operably associated with said fuel injectors to pulse off the flow of fuel to quench the combustion flame in said annular pre-burner/pre-mixer once the light-off temperature of the catalyst elements is reached.

Claim 8

The catalytic combustion system of claim 4 wherein said annular catalyst canister has an outer diameter greater than said annular pre-burner/pre-mixer.

Claim 9

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.

Claim 10

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.

Claim 11

The catalytic combustion system of claim 7 wherein said gas turbine engine recuperator is disposed around said turbine and compressor and said annular catalyst canister, said transition section and said annular pre-burner/pre-mixer, and the heated compressed air from said gas turbine recuperator passes over the annular catalyst canister, said annular transition section and said annular pre-burner/pre-mixer before being directed between said inner liner and said turbine exhaust tube.

Claim 12

The catalytic combustion system of claim 8 wherein approximately three percent of the heated compressed air from said recuperator is provided to said secondary tangential air dilution holes, approximately seven percent is provided to said primary tangential air-fuel venturis, and the remainder is provided to said tertiary air dilution holes.

Claim 13

The catalytic combustion system of claim 7 wherein said fuel injectors include means to pulse off the flow of fuel to quench the combustion flame in said annular pre- burner/pre-mixer once the light-off temperature of the catalyst elements is reached.

Claim 14

The catalytic combustion system of claim 7 wherein said means to pulse off the flow of fuel comprises a fuel control valve activated by a thermocouple disposed between said gas turbine recuperator and said annular catalytic canister.

Claim 15

The catalytic combustion system of claim 7 wherein said plurality of primary tangential air-fuel venturis is three.

Claim 16

The catalytic combustion system of claim 7 wherein said plurality of secondary tangential air dilution holes is six.

Claim 17

The catalytic combustion system of claim 7 wherein said plurality of tertiary radial air dilution holes is over one hundred.

Claim 18

The catalytic combustion system of claim 14 wherein said plurality of tertiary radial air dilution holes are in a plurality of rows.

Claim 19

The catalytic combustion system of claim 14 wherein said plurality of rows is four.

Claim 20

The catalytic combustion system of claim 7 wherein said plurality of primary tangential air-fuel venturis is three, said plurality of secondary tangential air dilution holes is six, and said plurality of tertiary radial air dilution holes is over one hundred in four rows.

Claim 21

The catalytic combustion system of claim 7 wherein said plurality of microlith catalyst elements is over one hundred and slidably supported within said catalyst canister amongst a plurality of support disks and held in place in said catalyst canister by support spokes at an end of said catalyst canister.