초록 ▼

A catalytic combustor (34) for a gas turbine engine (30). A fuel-air mixture (50) is reacted on a catalytic surface (54) of a catalytic heat exchanger module (36) to partially combust the fuel (48) to form heat energy. The fuel-air mixture is formed using compressed air (44) that has been pre-heated

A catalytic combustor (34) for a gas turbine engine (30). A fuel-air mixture (50) is reacted on a catalytic surface (54) of a catalytic heat exchanger module (36) to partially combust the fuel (48) to form heat energy. The fuel-air mixture is formed using compressed air (44) that has been pre-heated to above a reaction-initiation temperature in a non-catalytic cooling passage (46) of the catalytic heat exchanger module (36). Because the non-catalytic cooling passages (46) provide the necessary pre-heating of the combustion air, no separate pre-heat burner is required. Fuel (48) is added to the pre-heated air (44) downstream of the non-catalytic cooling passage (46) and upstream of the catalytic surface (54), thereby eliminating the possibility of flashback of flame into the cooling passages (46). Both can-type (60) and annular (80) combustors utilizing such a combustion system are described.

대표청구항 ▼

1. A combustor comprising: a heat exchanger module having a first passage defined by a non-catalytic material and a second passage defined by a catalytic material in a heat exchange relationship with the non-catalytic material; and a fuel injection apparatus disposed in a flow of combustion air

1. A combustor comprising: a heat exchanger module having a first passage defined by a non-catalytic material and a second passage defined by a catalytic material in a heat exchange relationship with the non-catalytic material; and a fuel injection apparatus disposed in a flow of combustion air downstream of the first passage and upstream of the second passage. 2. The combustor of claim 1, further comprising a means for directing the combustion air in sequence through the non-catalytic passage, the fuel injection apparatus and the catalytic passage. 3. The combustor of claim 1, wherein the non-catalytic passage and the catalytic passage are oriented in a cross-flow configuration through the heat exchanger module. 4. A gas turbine comprising: a compressor for providing a flow of air; a combustor for combusting a flow of fuel in the flow of air to produce a flow of combustion gas; and a turbine for extracting energy from the flow of combustion gas; wherein the combustor further comprises: a catalyst module having a catalytic surface and a non-catalytic surface in heat exchange relationship there between; a fuel delivery apparatus; and a flow directing arrangement for directing the flow of air in sequence from the non-catalytic surface to the fuel delivery apparatus to the catalytic surface. 5. The gas turbine of claim 4, wherein the combustor further comprises a plurality of said catalyst modules arranged in an annular pattern around an inlet to an annular combustion chamber, and a plurality of pilot burners disposed in an annular pattern alternately spaced between respective ones of the plurality of catalyst modules. 6. A method of combusting a fuel comprising: providing a catalyst device having a catalytic surface in heat exchange relationship with a non-catalytic surface; directing fuel-free air over the non-catalytic surface to remove heat energy from the catalyst device and to pre-heat the fuel-free air; adding a combustible fuel to the pre-heated fuel-free air to form a pre-heated fuel-air mixture; and directing the pre-heated fuel-air mixture over the catalytic surface to initiate combustion at least a first portion of the fuel. 7. The method of claim 6, wherein at least a second portion of the fuel is combusted in a combustion chamber downstream of the catalyst device, and further comprising: providing a pilot burner having an outlet to the combustion chamber; and directing a second fuel-air mixture through the pilot burner to produce a pilot flame in the combustion chamber for stabilizing the combustion of the at least a second portion of the fuel in the combustion chamber. 8. The method of claim 6, wherein the combustible fuel is a first type of fuel, and further comprising: supplying a second type of combustible fuel to the pre-heated fuel-free air until a predetermined temperature is achieved in the pre-heated fuel-free air; and terminating the supply of the second type of fuel after the predetermined temperature is achieved. 9. The method of claim 8, wherein the second type of combustible fuel comprises one of the group of hydrogen and propane.