Abstract: The present disclosure relates to a processes and systems for producing fuels from biomass with high carbon conversion efficiency. The processes and systems described herein provide a highly efficient process for producing hydrocarbons from biomass with very low Green House Gas (GHG) emissions using a specific combination of components, process flows, and recycle streams. The processes and systems described herein provide a carbon conversion efficiency greater than 95% with little to no GHG in the flue gas due to the novel arrangement of components and utilizes renewable energy to provide energy to some components. The system reuses water and carbon dioxide produced in the process flows and recycles naphtha and tail gas streams to other units in the system for additional conversion to syngas to produce hydrocarbon-based fuels.

Abstract: The present disclosure relates to a processes and systems for producing fuels from biomass with high carbon conversion efficiency. The processes and systems described herein provide a highly efficient process for producing hydrocarbons from biomass with very low Green House Gas (GHG) emissions using a specific combination of components, process flows, and recycle streams. The processes and systems described herein provide a carbon conversion efficiency greater than 95% with little to no GHG in the flue gas due to the novel arrangement of components and utilizes renewable energy to provide energy to some components. The system reuses water and carbon dioxide produced in the process flows and recycles naphtha and tail gas streams to other units in the system for additional conversion to syngas to produce hydrocarbon-based fuels.

Abstract: A method enables a gas turbine engine positioned within a module to be operated. The engine includes an inlet and an exhaust, and the module includes an inlet area, an exhaust area, and an engine area extending therebetween and housing the engine. The exhaust area includes an exhaust duct and an outlet. The engine is operated such that inlet air is routed through the module inlet and into the engine inlet, wherein exhaust gases are discharged through the module exhaust duct and substantially perpendicularly from the gas turbine engine. The exhaust gases are discharged from the module outlet in a direction that is at least ninety degrees offset from exhaust gases flowing within the exhaust duct. Cooling fluid is discharged from the module engine area through a cooling system exhaust, such that the discharged fluid flows through the cooling system exhaust and around the module exhaust area.

Abstract: A method enables a gas turbine engine positioned within a module to be operated. The engine includes an inlet and an exhaust, and the module includes an inlet area, an exhaust area, and an engine area extending therebetween and housing the engine. The exhaust area includes an exhaust duct and an outlet. The engine is operated such that inlet air is routed through the module inlet and into the engine inlet, wherein exhaust gases are discharged through the module exhaust duct and substantially perpendicularly from the gas turbine engine. The exhaust gases are discharged from the module outlet in a direction that is at least ninety degrees offset from exhaust gases flowing within the exhaust duct. Cooling fluid is discharged from the module engine area through a cooling system exhaust, such that the discharged fluid flows through the cooling system exhaust and around the module exhaust area.

Abstract: A gas turbine engine including in-line intercooling wherein compressor intercooling is achieved without removing the compressor main flow airstream from the compressor flowpath is described. In an exemplary embodiment, a gas turbine engine suitable for use in connection with in-line intercooling includes a low pressure compressor, a high pressure compressor, and a combustor. The engine also includes a high pressure turbine, a low pressure turbine, and a power turbine. For intercooling, fins are located in an exterior surface of the compressor struts in the compressor flowpath between the outlet of the low pressure compressor and the inlet of the high pressure compressor. Coolant flowpaths are provided in the compressor struts, and such flowpaths are in flow communication with a heat exchanger. In operation, air flows through the low pressure compressor, and compressed air is supplied from the low pressure compressor to the high pressure compressor.

Abstract: A gas turbine engine including in-line intercooling wherein compressor intercooling is achieved without removing the compressor main flow airstream from the compressor flowpath is described. In an exemplary embodiment, a gas turbine engine suitable for use in connection with in-line intercooling includes a low pressure compressor, a high pressure compressor, and a combustor. The engine also includes a high pressure turbine, a low pressure turbine, and a power turbine. For intercooling, fins are located in an exterior surface of the compressor struts in the compressor flowpath between the outlet of the low pressure compressor and the inlet of the high pressure compressor. Coolant flowpaths are provided in the compressor struts, and such flowpaths are in flow communication with a heat exchanger. In operation, air flows through the low pressure compressor, and compressed air is supplied from the low pressure compressor to the high pressure compressor.

Abstract: A gas turbine engine including in-line intercooling wherein compressor intercooling is achieved without removing the compressor main flow airstream from the compressor flowpath is described. In an exemplary embodiment, a gas turbine engine suitable for use in connection with in-line intercooling includes a low pressure compressor, a high pressure compressor, and a combustor. The engine also includes a high pressure turbine, a low pressure turbine, and a power turbine. For intercooling, fins are located in an exterior surface of the compressor struts in the compressor flowpath between the outlet of the low pressure compressor and the inlet of the high pressure compressor. Coolant flowpaths are provided in the compressor struts, and such flowpaths are in flow communication with a heat exchanger. In operation, air flows through the low pressure compressor, and compressed air is supplied from the low pressure compressor to the high pressure compressor.

Abstract: Gas turbine engines working on an inverted Brayton cycle (IBC) which provides increased power output at a same fuel flow as is currently used in some other known cycles (e.g., air bottoming cycle) are described. In one embodiment, the engine includes a compressor coupled by a first shaft to a high pressure turbine. A combustor is located in the flow intermediate the compressor and high pressure turbine. A free wheeling power turbine is located downstream of the high pressure turbine, and the power turbine is coupled to a load by a second shaft. The flow from the power turbine is supplied, e.g., via ducts, to an axial turbine coupled to an axial compressor by a third shaft. A heat exchanger is located in the flow intermediate the axial turbine and axial compressor. In operation, the working fluid (e.g., air) is compressed by the compressor, and the compressed air is injected into the combustor which heats the air causing it to expand.

Abstract: A gas turbine engine including in-line intercooling wherein compressor intercooling is achieved without removing the compressor main flow airstream from the compressor flowpath is described. In an exemplary embodiment, a gas turbine engine suitable for use in connection with in-line intercooling includes a low pressure compressor, a high pressure compressor, and a combustor. The engine also includes a high pressure turbine, a low pressure turbine, and a power turbine. For intercooling, fins are located in an exterior surface of the compressor struts in the compressor flowpath between the outlet of the low pressure compressor and the inlet of the high pressure compressor. Coolant flowpaths are provided in the compressor struts, and such flowpaths are in flow communication with a heat exchanger. In operation, air flows through the low pressure compressor, and compressed air is supplied from the low pressure compressor to the high pressure compressor.

Abstract: A gas turbine engine including in-line intercooling wherein compressor intercooling is achieved without removing the compressor main flow airstream from the compressor flowpath is described. In an exemplary embodiment, a gas turbine engine suitable for use in connection with in-line intercooling includes a low pressure compressor, a high pressure compressor, and a combustor. The engine also includes a high pressure turbine, a low pressure turbine, and a power turbine. For intercooling, fins are located in an exterior surface of the compressor struts in the compressor flowpath between the outlet of the low pressure compressor and the inlet of the high pressure compressor. Coolant flowpaths are provided in the compressor struts, and such flowpaths are in flow communication with a heat exchanger. In operation, air flows through the low pressure compressor, and compressed air is supplied from the low pressure compressor to the high pressure compressor.

Abstract: Gas turbine engines working on an inverted Brayton cycle (IBC) which provides increased power output at a same fuel flow as is currently used in some other known cycles (e.g., air bottoming cycle) are described. In one embodiment, the engine includes a compressor coupled by a first shaft to a high pressure turbine. A combustor is located in the flow intermediate the compressor and high pressure turbine. A free wheeling power turbine is located downstream of the high pressure turbine, and the power turbine is coupled to a load by a second shaft. The flow from the power turbine is supplied, e.g., via ducts, to an axial turbine coupled to an axial compressor by a third shaft. A heat exchanger is located in the flow intermediate the axial turbine and axial compressor. In operation, the working fluid (e.g., air) is compressed by the compressor, and the compressed air is injected into the combustor which heats the air causing it to expand.

Abstract: A system for cooling hot section components of a gas turbine engine. The cooling system includes a plurality of compressors, or compression train, and an intercooler disposed between each adjacent pair of compressors so as to achieve the desired pressure and temperature of the cooling air at reduced shaft power requirements. The first stage of compression may be provided by the booster, or low pressure compressor, of the engine, with the first intercooler receiving all of the air discharging from the booster. After exiting the first intercooler, a first portion of the booster discharge air is routed to the engine high pressure compressor and a second portion is routed to an inlet of the second compressor of the cooling air compression train. The compressed, cooled air exiting the last, downstream one of the compressors is used for cooling at least a first hot section component of the engine.

Abstract: A gas turbine engine that includes a steam driven variable speed 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. The output of the low pressure compressor is supplied to an intercooler, and the output of the intercooler is supplied to the high pressure compressor. The engine further includes a power turbine downstream of the high pressure turbine, and the power turbine is coupled to a generator by a shaft. The output exhaust of the power turbine is supplied to an exhaust heat boiler, and steam output by the boiler is supplied to, and drives, the low pressure turbine. Steam from the boiler may also be supplied to the high pressure combustor and to the power turbine.

Abstract: A cospander for extending the high efficiency range of a turbine engine is described. A cospander, in one aspect, is a turbomachinery device including at least one stage wherein stator vane and rotor blade rows are continuously variable to an extent that each stage can be operated in compression, expansion, or null modes depending on the blade and vane angles at any specific operating point. Such a device placed ahead or within a typical compressor has the effect of reducing, increasing, or maintaining the through flow of the primary working fluid. Such flow variation control can be used to achieve the desired overall turbomachinery thermal efficiency improvements over a wider operating range than is otherwise possible. In one specific embodiment, for example, the cospander includes a variable stator vane and a variable pitch rotor blade in series flow relationship.

Abstract: A system for cooling hot section components of a gas turbine engine. The cooling system includes a plurality of compressors, or compression train, and an intercooler disposed between each adjacent pair of compressors so as to achieve the desired pressure and temperature of the cooling air at reduced shaft power requirements. The first stage of compression may be provided by the booster, or low pressure compressor, of the engine, with the first intercooler receiving all of the air discharging from the booster. After exiting the first intercooler, a first portion of the booster discharge air is routed to the engine high pressure compressor and a second portion is routed to an inlet of the second compressor of the cooling air compression train. The compressed, cooled air exiting the last, downstream one of the compressors is used for cooling at least a first hot section component of the engine.

Abstract: A combustor dome assembly having a venturi and an auxiliary wall concentric with the venturi to provide an annular passage for channeling or directing a high velocity air jet from a swirler to a combustion chamber associated with a downstream end of the venturi, thereby facilitating the atomization of a film of water flowing along an inner surface of the venturi and out of the downstream end. In an alternative embodiment, a deflector is used (instead of the auxiliary wall) to direct the air flow towards the downstream end. The downstream end of the venturi may have a curved edge to permit the film of water flowing along an inner surface of the venturi to turn substantially perpendicular to the air flowing past the downstream end of the venturi which further enhances atomization of water. The venturi may also comprise a flange which is positioned in operative relationship with the downstream end for increasing the turbulence at the downstream end.

Abstract: A powerplant comprising a compressor for producing a downstream fluid flow, a combustor downstream of the compressor, a turbine downstream of the combustor, a power turbine downstream and adjacent the turbine, and a duct region which receives at least a portion of the fluid output of the power turbine. A reformer is positioned downstream and is coupled to the duct region and the reformer has a fuel outlet which is coupled to the combustor.

Abstract: An improved cooling system for a gas turbine is disclosed. A plurality of V-shaped notch weirs are utilized to meter a coolant liquid from a pool of coolant into a plurality of platform and air foil coolant channels formed in the buckets of the turbine. The V-shaped notch weirs serve to desensitize the flow of coolant into the individual platform and air foil coolant channels to design tolerances and non-uniform flow distribution.