Abstract: A combustor for a gas turbine engine is disclosed which is able to operate with high combustion efficiency, and low nitrous oxide emissions during gas turbine operations. The combustor consists of a can-type configuration which combusts fuel premixed with air and delivers the hot gases to a turbine. Fuel is premixed with air and is delivered to the combustor with a high degree of swirl motion. This swirling mixture of reactants is conveyed through a flowpath that expands; the mixture reacts, and establishes a central recirculation zone. An imperforate trapped vortex cavity is disposed proximal to the swirler apparatus which provides for a second reaction zone. Fresh fuel/air reactants are exchanged with burned products in the trapped vortex and a pilot flame is established in the trapped cavity. The imperforate trapped cavity is not supplied with either fuel or air, but is cooled on a backside of the cavity with a flow of cooling air.

Abstract: A combustor for a gas turbine engine is disclosed which is able to operate with high combustion efficiency, and low nitrous oxide emissions during gas turbine operations. The combustor consists of a can-type configuration which combusts fuel premixed with air and delivers the hot gases to a turbine. Fuel is premixed with air and is delivered to the combustor with a high degree of swirl motion. This swirling mixture of reactants is conveyed through a flowpath that expands; the mixture reacts, and establishes a central recirculation zone. An imperforate trapped vortex cavity is disposed proximal to the swirler apparatus which provides for a second reaction zone. Fresh fuel/air reactants are exchanged with burned products in the trapped vortex and a pilot flame is established in the trapped cavity. The imperforate trapped cavity is not supplied with either fuel or air, but is cooled on a backside of the cavity with a flow of cooling air.

Abstract: A fuel-conditioning skid for an engine. The fuel-conditioning skid includes an inlet that is connectable to a source to receive a flow of fuel containing undesirable compounds. An outlet is connectable to the engine to deliver a flow of fuel that is substantially free of undesirable compounds. An inlet cleaner is in fluid communication with the inlet and is operable to remove a portion of the undesirable compounds. A compressor is in fluid communication with the inlet cleaner to receive the flow of fuel at a first pressure and discharge the flow of fuel at a second pressure. The second pressure is greater than the first pressure. A purifier is in fluid communication with the inlet cleaner to receive the flow of fuel. The purifier is operable to remove substantially all of the remaining undesirable compounds from the flow of fuel.

Abstract: A method for forming a carbon deposit inhibiting thermal barrier coating for an internal element or component of a gas turbine engine. Such coating includes a layer of thermal barrier material coated onto the surface of an engine component that will be exposed to the flow of burning engine gases. Such coating further includes a layer of carbon deposit inhibiting material coated on top of the layer of thermal barrier material.

Abstract: A carbon deposit inhibiting thermal barrier coating for an internal element or component in a gas turbine engine. Such coating includes a layer of thermal barrier material coated onto the surface of an engine component that will be exposed to the flow of burning engine gases. Such coating further includes a layer of carbon deposit inhibiting material coated on top of the layer of thermal barrier material.

Abstract: A carbon deposit inhibiting thermal barrier coating for an internal element or component in a gas turbine engine. Such coating includes a layer of thermal barrier material coated onto the surface of an engine component that will be exposed to the flow of burning engine gases. Such coating further includes a layer of carbon deposit inhibiting material coated on top of the layer of thermal barrier material.

Abstract: A carbon deposit inhibiting thermal barrier coating for an internal element or component in a gas turbine engine. Such coating includes a layer of thermal barrier material coated onto the surface of an engine component that will be exposed to the flow of burning engine gases. Such coating further includes a layer of carbon deposit inhibiting material coated on top of the layer of thermal barrier material.