Abstract: A power generating apparatus including a gas turbine engine combusting a fuel in air to produce shaft power and producing a flow of exhaust gases including oxides of nitrogen (NOx), carbon monoxide (CO) and hydrocarbons (HC). An emissions treatment apparatus includes in the exhaust gas flowpath a CO oxidation catalyst disposed at a location with an exhaust gas temperature for which the CO oxidation catalyst advantageously limits NO2 production. The emissions treatment apparatus further includes an ammonia injection apparatus, a mixing section, and a selective catalytic reduction element disposed downsteam of the ammonia injection apparatus and adapted for reduction of NOx.

Abstract: An embodiment of the present invention provides a method and system of operating a combustion system that has Lean direct injection (LDI) functionality. The method and system provides a passive cooling system for an injector of the LDI system. The method and system may also provide a means to direct the flow of the fluid exiting the injector of the LDI system.

Abstract: A method of regulating the Wobbe number of a multi-composition gas fuel supplied to one or more combustors of a gas turbine includes: (a) providing a control system for regulating fuel and air flow to the one or more combustors; and (b) reforming a fraction of the gas fuel upstream of the one or more combustors to form hydrogen and carbon monoxide to be supplied to the one or more combustors with a remaining fraction of the fuel; wherein the fraction of fuel reformed is adjusted to maintain the Wobbe number of the fuel supplied to the one or more combustors within a predetermined range.

Abstract: The present application provides a gas turbine engine system. The gas turbine engine system may include a gas turbine engine producing a flow of combustion gases, an emissions reduction system in communication with the gas turbine engine, a flow of ammonia to be injected into the flow of combustion gases, and a source of compressed gas to vaporize the flow of ammonia.

Abstract: A nozzle for a gas turbine combustor includes a first radially outer tube defining a first passage having an inlet and an outlet, the inlet adapted to supply air to a reaction zone of the combustor. A center body is located within the first radially outer tube, the center body including a second radially intermediate tube for supplying fuel to the reaction zone and a third radially inner tube for supplying air to the reaction zone. The second intermediate tube has a first outlet end closed by a first end wall that is formed with a plurality of substantially parallel, axially-oriented air outlet passages for the additional air in the third radially inner tube, each air outlet passage having a respective plurality of associated fuel outlet passages in the first end wall for the fuel in the second radially intermediate tube.

Abstract: The present invention is directed to a lean direct injection (LDI) combustion system for a gas turbine using a shell and tube heat exchanger concept to construct a shell and tube lean direct injector (“LDI”) for the combustion system. One side of the LDI injector, either the shell side or the tube side, carries an oxidizer, such as air, to the combustor, while the other side of the LDI injector carries fuel to the combustor. Straight or angled holes drilled in an end plate of the combustor allow the fuel to enter the combustor and mix with air being injected into the combustor.

Abstract: A method of regulating the Wobbe number of a multi-composition gas fuel supplied to one or more combustors of a gas turbine includes: (a) providing a control system for regulating fuel and air flow to the one or more combustors; and (b) reforming a fraction of the gas fuel upstream of the one or more combustors to form hydrogen and carbon monoxide to be supplied to the one or more combustors with a remaining fraction of the fuel; wherein the fraction of fuel reformed is adjusted to maintain the Wobbe number of the fuel supplied to the one or more combustors within a predetermined range.

Abstract: A method of regulating the Wobbe number of a multi-composition gas fuel supplied to one or more combustors of a gas turbine comprising: (a) providing a control system for regulating fuel and air flow to the one or more combustors; and (b) reforming a fraction of the gas fuel upstream of the one or more combustors to form hydrogen and carbon monoxide to be supplied to the one or more combustors with a remaining fraction of the fuel; wherein the fraction of fuel reformed is adjusted to maintain the Wobbe number of the fuel supplied to the one or more combustors within a predetermined range.

Abstract: A method for assembling a gas turbine engine includes providing at least one combustor assembly defining a combustion chamber. At least one fuel nozzle is positioned at a forward end of the combustion chamber. The at least one fuel nozzle is configured to inject a premixed fuel/air mixture into the combustion chamber. A catalytic material is applied to at least a portion of the at least one fuel nozzle.

Abstract: A method of operating a turbine engine includes providing at least one combustor having a chamber defined therein. The assembly includes at least one combustor wall defining the chamber and a first fluid passage defining a first fluid inlet within the wall. The first fluid passage is coupled in flow communication with the chamber and is configured to inject a first fluid stream. The assembly further includes at least one second fluid passage defining at least one second fluid inlet within the wall. The second fluid inlet is adjacent to the first fluid inlet and is coupled in flow communication with the chamber. The method also includes injecting the first fluid stream and injecting the second fluid stream into the chamber at an oblique angle with respect to the first fluid stream, thereby intersecting and mixing the second fluid stream with the first fluid stream.

Abstract: An embodiment of the present invention provides a method and system of operating a combustion system that has Lean direct injection (LDI) functionality. The method and system provides a passive cooling system for an injector of the LDI system. The method and system may also provide a means to direct the flow of the fluid exiting the injector of the LDI system.

Abstract: A power generating apparatus including a gas turbine engine combusting a fuel in air to produce shaft power and producing a flow of exhaust gases including oxides of nitrogen (NOx), carbon monoxide (CO) and hydrocarbons (HC). An emissions treatment apparatus includes in the exhaust gas flowpath a CO oxidation catalyst disposed at a location with an exhaust gas temperature for which the CO oxidation catalyst advantageously limits NO2 production. The emissions treatment apparatus further includes an ammonia injection apparatus, a mixing section, and a selective catalytic reduction element disposed downsteam of the ammonia injection apparatus and adapted for reduction of NOx.

Abstract: A nozzle for a gas turbine combustor includes a first radially outer tube defining a first passage having an inlet and an outlet, the inlet adapted to supply air to a reaction zone of the combustor. A center body is located within the first radially outer tube, the center body including a second radially intermediate tube for supplying fuel to the reaction zone and a third radially inner tube for supplying air to the reaction zone. The second intermediate tube has a first outlet end closed by a first end wall that is formed with a plurality of substantially parallel, axially-oriented air outlet passages for the additional air in the third radially inner tube, each air outlet passage having a respective plurality of associated fuel outlet passages in the first end wall for the fuel in the second radially intermediate tube.

Abstract: The present invention is directed to a lean direct injection (LDI) combustion system for a gas turbine using a shell and tube heat exchanger concept to construct a shell and tube lean direct injector (“LDI”) for the combustion system. One side of the LDI injector, either the shell side or the tube side, carries an oxidizer, such as air, to the combustor, while the other side of the LDI injector carries fuel to the combustor. Straight or angled holes drilled in an end plate of the combustor allow the fuel to enter the combustor and mix with air being injected into the combustor.

Abstract: A method for assembling a gas turbine engine includes providing at least one combustor assembly defining a combustion chamber. At least one fuel nozzle is positioned at a forward end of the combustion chamber. The at least one fuel nozzle is configured to inject a premixed fuel/air mixture into the combustion chamber. A catalytic material is applied to at least a portion of the at least one fuel nozzle.

Abstract: A method of regulating the Wobbe number of a multi-composition gas fuel supplied to one or more combustors of a gas turbine comprising: (a) providing a control system for regulating fuel and air flow to the one or more combustors; and (b) reforming a fraction of the gas fuel upstream of the one or more combustors to form hydrogen and carbon monoxide to be supplied to the one or more combustors with a remaining fraction of the fuel; wherein the fraction of fuel reformed is adjusted to maintain the Wobbe number of the fuel supplied to the one or more combustors within a predetermined range.

Abstract: A method of operating a turbine engine includes providing at least one combustor having a chamber defined therein. The assembly includes at least one combustor wall defining the chamber and a first fluid passage defining a first fluid inlet within the wall. The first fluid passage is coupled in flow communication with the chamber and is configured to inject a first fluid stream. The assembly further includes at least one second fluid passage defining at least one second fluid inlet within the wall. The second fluid inlet is adjacent to the first fluid inlet and is coupled in flow communication with the chamber. The method also includes injecting the first fluid stream and injecting the second fluid stream into the chamber at an oblique angle with respect to the first fluid stream, thereby intersecting and mixing the second fluid stream with the first fluid stream.

Abstract: A structure is disclosed that will quench a flame front during a flashback event in a gas turbine while simultaneously providing a mixing function during normal operations. The device disclosed consists of two monoliths one upstream of the other. In the basic embodiment of the invention the downstream monolith acts as a mixer while the combination of the upstream monolith and the downstream monolith act as the flashback arrestor. Other embodiments of the device also allow the downstream monolith to be a flameholder.

Abstract: Flashback of flames in premixed combustion systems is avoided by passing premixed fuel and air prior to combustion through a series of two or more nonaligned multi-channel monolith attached in series. The device is useful as a pre-ignition inhibitor, a detonation wave inhibitor and a flashback arrestor protector.

Abstract: Flashback of flames in premixed combustion systems is avoided by passing premixed fuel and air prior to combustion through a series of two or more close coupled nonaligned multi-channel monoliths.