Abstract: A fuel cell unit that includes a support structure having a plurality of flow channels and an active layer membrane coupled with the support structure, the active layer membrane comprising at least one electrode layer. Each flow channel of the plurality of flow channels is configured to direct one of air and fuel across at least one electrode layer of an active layer membrane to create electric current. Each flow channel of the plurality of flow channels includes at least one enhancement feature that is configured to disrupt a formation of a boundary layer near a surface of the active layer membrane where reactions occur. The plurality of flow channels can be positioned in a zig-zag configuration to allow for an increase in power density of the fuel cell unit.

Abstract: A gas turbine engine with a compressor section, a turbine section, and a combustion section located downstream from the compressor section and upstream from the turbine section, the combustion section including a dome inlet, a combustor outlet fluidly coupled to the turbine section, a liner and a dome assembly together at least partially defining a combustion chamber extending between the dome inlet and the combustor outlet, a fuel system fluidly coupled to the combustion section, the fuel system comprising a fuel supply, a primary fuel line fluidly coupling the fuel supply to the combustion section, and a reformer fluidly coupled to the fuel supply.

Abstract: A gas turbine engine with a compressor section, a turbine section, and a combustion section located downstream from the compressor section and upstream from the turbine section, the combustion section including a dome inlet, a combustor outlet fluidly coupled to the turbine section, a liner and a dome assembly together at least partially defining a combustion chamber extending between the dome inlet and the combustor outlet, a fuel system fluidly coupled to the combustion section, the fuel system comprising a fuel supply, a primary fuel line fluidly coupling the fuel supply to the combustion section, and a reformer fluidly coupled to the fuel supply.

Abstract: A gas turbine engine with a compressor section, a turbine section, and a combustion section located downstream from the compressor section and upstream from the turbine section, the combustion section including: a dome inlet, a combustor outlet fluidly coupled to the turbine section, a liner and a dome assembly together at least partially defining a combustion chamber extending between the dome inlet and the combustor outlet, a primary fuel injector fluidly coupled to the dome inlet, and a second fuel injector fluidly coupled to the combustion chamber.

Abstract: An engine assembly includes a combustor, a fuel cell stack fluidly connected to the combustor, the fuel cell stack being configured (i) to generate power using fuel and air directed into the fuel cell stack and (ii) to direct fuel and air exhaust from the fuel cell stack into the combustor, a compressor fluidly connected upstream of (i) the combustor and (ii) the fuel cell stack, the compressor being configured to generate compressed air to direct into the fuel cell stack, a turbine disposed downstream from the combustor, the turbine having a turbine inlet temperature, and a controller that is configured to control a power allocation between the fuel cell stack and the turbine based upon the turbine inlet temperature of the turbine. The combustor is configured to combust the fuel and air exhaust from the fuel cell stack into one or more gaseous combustion products that power the turbine.

Abstract: An engine assembly includes a combustor, a fuel cell stack integrated with the combustor, the fuel cell stack configured (i) to direct fuel and air exhaust from the fuel cell stack into the combustor and (ii) to generate electrical energy, a catalytic partial oxidation convertor that is fluidly connected to the fuel cell stack, the catalytic partial oxidation convertor being configured to optimize a hydrogen content of a fuel stream to be directed into the fuel cell stack, and one or more subsystems electrically connected with the fuel cell stack, the one or more subsystems being configured to receive the electrical energy generated by the fuel cell stack. The combustor is configured to combust the fuel and air exhaust from the fuel cell stack into one or more gaseous combustion products that drive a downstream turbine.

Abstract: An engine assembly includes a combustor, a fuel cell stack integrated with the combustor, and a pre-burner system fluidly connected to the fuel cell stack. The fuel cell stack is configured to direct fuel and air exhaust from the fuel cell stack into the combustor. The pre-burner system is configured to control a temperature of an air flow directed into the fuel cell stack. The combustor is configured to combust the fuel and air exhaust from the fuel cell stack into one or more gaseous combustion products that drive a downstream turbine. The engine assembly can further include a catalytic partial oxidation convertor that is fluidly connected to the fuel cell stack. The catalytic partial oxidation convertor is configured to develop a hydrogen rich fuel stream to be directed into the fuel cell stack.

Abstract: A fuel mixer configured to provide a fuel-air mixture to a combustor of an engine. The fuel mixer may include a mixer body having a mixer outer wall, a center body, an annular passageway defined between the mixer outer wall and the center body, and a fuel tube assembly placed circumferentially about the mixer body. The fuel tube assembly may include at least one fuel channel for injecting a fuel flow into the annular passageway. The fuel tube assembly may be configured to cool a boundary layer flow present in the annular passageway. The fuel tube assembly may be configured to cool the mixer outer wall, the center body, or both the mixer outer wall and the center body. Heat from the mixer outer wall, the center body, or both the mixer outer wall and the center body, may pass to the fuel flow in the fuel tube assembly.

Abstract: A fuel cell unit that includes a support structure having a plurality of flow channels and an active layer membrane coupled with the support structure, the active layer membrane comprising at least one electrode layer. Each flow channel of the plurality of flow channels is configured to direct one of air and fuel across at least one electrode layer of an active layer membrane to create electric current. Each flow channel of the plurality of flow channels includes at least one enhancement feature that is configured to disrupt a formation of a boundary layer near a surface of the active layer membrane where reactions occur. The plurality of flow channels can be positioned in a zig-zag configuration to allow for an increase in power density of the fuel cell unit.

Abstract: An airfoil for a turbomachinery rotor includes: a body having a first density, the body defining a pressure side and a suction side, the pressure side and suction side intersecting at a leading edge and a trailing edge; and a mass positioned within the body and having a second density, wherein the second density is greater than the first density, wherein the mass is offset from a center of gravity of the body in at least one axis.

Abstract: An airfoil for a turbomachinery rotor includes: a body having a first density, the body defining a pressure side and a suction side, the pressure side and suction side intersecting at a leading edge and a trailing edge; and a mass positioned within the body and having a second density, wherein the second density is greater than the first density, wherein the mass is offset from a center of gravity of the body in at least one axis.

Abstract: A gas turbine engine includes a compressor rotor assembly including a first rotor, a combustor configured to operate with a fuel/air mixture equivalence ratio less than one, and a water injection assembly. The water injection assembly includes a water delivery system including a first plurality of spray nozzles to supply water upstream from the first rotor. The water being supplied to the first rotor is atomized with the first plurality of spray nozzles prior to being supplied to the engine to lower the emissions generated by the combustor.

Abstract: A gas turbine engine includes a compressor rotor assembly including a first rotor, a combustor configured to operate with a fuel/air mixture equivalence ratio less than one, and a water injection assembly. The water injection assembly includes a water delivery system including a first plurality of spray nozzles to supply water upstream from the first rotor. The water being supplied to the first rotor is atomized with the first plurality of spray nozzles prior to being supplied to the engine to lower the emissions generated by the combustor.

Abstract: A fuel nozzle for a gas turbine engine has a spray tip and a housing coaxially disposed around the spray tip. Bi-directional axial movement of the spray tip relative to the housing is constrained by first and second rows of tabs formed on one of the housing and the spray tip and a third row of tabs formed on the other one of the housing and the spray tip. The third row of tabs is disposed between the first and second rows to constrain spray tip motion in either axial direction.

Abstract: A gas turbine engine includes a compressor rotor assembly including a first rotor, a combustor configured to operate with a fuel/air mixture equivalence ratio less than one, and a water injection assembly. The water injection assembly includes a water delivery system including a first plurality of spray nozzles to supply water upstream from the first rotor. The water being supplied to the first rotor is atomized with the first plurality of spray nozzles prior to being supplied to the engine to lower the emissions generated by the combustor.

Abstract: An apparatus for premixing fuel and air prior to combustion in a gas turbine engine, including: a linear mixing duct having a circular cross-section defined by a wall; a centerbody located along a central axis of the mixing duct and extending substantially the full length of the mixing duct, the centerbody having a plurality of orifices therein to inject fuel into the mixing duct with an axial velocity component; a fuel supply in flow communication with the centerbody orifices; an outer annular swirler located adjacent an upstream end of the mixing duct and including a plurality of circumferentially spaced vanes oriented so as to swirl air flowing therethrough in a first direction; an inner annular swirler located adjacent the mixing duct upstream end and including a plurality of circumferentially spaced vanes, the vanes having an outer radial portion having a leading edge and a trailing edge oriented so as to swirl air flowing therethrough in a second direction opposite the first swirl direction by the outer

Abstract: A gas turbine engine that includes a 2/3 stage intercooled booster compressor is described. In one embodiment, the engine includes a low pressure turbine and a booster compressor rotatable on a low pressure shaft. The engine further includes a high pressure compressor, a high pressure combustor, and a high pressure turbine rotatable on a high pressure (HP) shaft and forming the core engine. A low pressure combustor is located at the outlet of the high pressure turbine and a power turbine. The booster compressor includes first and second stage compressors, and air flow from the first stage compressor is supplied to a first intercooler, and air flow from the second stage compressor is supplied to a second intercooler. Airflow from the first intercooler is supplied to the inlet of the second stage compressor, and airflow from the second intercooler is split between being provided to the inlet of the high pressure compressor and a recuperator.

Abstract: A dual fuel mixer is disclosed as including a mixing duct having an upstream end, a downstream end, and a centerline axis therethrough, where the mixing duct has a circular cross-section defined by a wall. A shroud surrounds the upstream end of the mixing duct and contains therein a gas manifold in flow communication with a gas fuel supply and control. A set of inner and outer annular counter-rotating swirlers are located adjacent the upstream end of the mixing duct for imparting swirl to an air stream. The outer annular swirler includes hollow vanes with internal cavities which are in flow communication with the gas manifold, the outer swirler vanes also having a plurality of gas fuel passages therethrough in flow communication with the internal cavities to inject gas fuel into the air stream. A hub is provided for separating the inner and outer annular swirlers to allow independent rotation thereof.

Abstract: An apparatus for premixing fuel and air prior to combustion in a gas turbine engine is disclosed as including a linear mixing duct having a circular cross-section defined by a wall. A gas fuel manifold is positioned adjacent the upstream end of the mixing duct and is in flow communication with a gas fuel supply and control means. An outer annular swirler is oriented radially to the mixing duct and positioned adjacent the upstream end of the mixing duct to impart swirl to an air stream entering the outer annular swirler. The outer annular swirler includes hollow vanes with internal cavities which are in flow communication with the gas manifold, the outer swirler vanes also having a plurality of gas fuel passages therethrough in flow communication with the internal cavities to inject gas fuel into the radially-oriented air stream.

Abstract: An air fuel mixer is disclosed having a mixing duct, a shroud surrounding the upstream end of the mixing duct in which a fuel manifold is provided in flow communication with a fuel supply and control means, a set of inner and outer counter-rotating swirlers adjacent the upstream end of the mixing duct for imparting swirl to an air stream, a hub separating the inner and outer annular swirlers to allow independent rotation of the air stream, and a centerbody located axially along and substantially the full length of the mixing duct. In order to inject one type of fuel into the mixing duct, fuel is supplied to the outer annular swirlers which include hollow vanes with internal cavities, wherein the internal cavities of the outer swirler vanes are in fluid communication with the fuel manifold in the shroud. The outer swirler vanes further include a plurality of fuel passages therethrough in flow communication with the internal cavities.