Abstract: A thermodynamic cycle is disclosed and has a working fluid circuit that converts thermal energy into mechanical energy on hot days. A pump circulates a working fluid to a heat exchanger that heats the working fluid. The heated working fluid is then expanded in a power turbine. The expanded working fluid is then cooled and condensed using one or more compressors interposing at least two intercooling components. The intercooling components cool and condense the working fluid with a cooling medium derived at ambient temperature, where the ambient temperature is above the critical temperature of the working fluid.

Abstract: Embodiments of the invention generally provide a heat engine system, a mass management system (MMS), and a method for regulating pressure in the heat engine system while generating electricity. In one embodiment, the MMS contains a tank fluidly coupled to a pump, a turbine, a heat exchanger, an offload terminal, and a working fluid contained in the tank at a storage pressure. The working fluid may be at a system pressure proximal an outlet of the heat exchanger, at a low-side pressure proximal a pump inlet, and at a high-side pressure proximal a pump outlet. The MMS contains a controller communicably coupled to a valve between the tank and the heat exchanger outlet, a valve between the tank and the pump inlet, a valve between the tank and the pump outlet, and a valve between the tank and the offload terminal.

Abstract: A combustor swirl cup includes coaxial inner and outer swirlers separated by a tubular centerbody. The centerbody includes a bypass inlet surrounding the inner swirler and diverges aft along a perforate inner nozzle to terminate at an annular flameholder. An impingement ring is spaced forward from the flameholder in flow communication with the bypass inlet for receiving cooling air therefrom to impingement cool the flameholder.

Abstract: Solar energy conversion systems and methods use solar collectors and working fluid management systems to provide both efficient and safe operation under a wide range of operating conditions. In one embodiment, a solar collector and at least one fluid accumulator preferably with an integral heat exchanger, and at least two mass flow regulator valves enable working fluid flow into and out of the fluid accumulator.

Abstract: Waste heat energy conversion cycles, systems and devices use multiple waste heat exchangers arranged in series in a waste heat stream, and multiple thermodynamic cycles run in parallel with the waste heat exchangers in order to maximize thermal energy extraction from the waste heat stream by a working fluid. The parallel cycles operate in different temperature ranges with a lower temperature work output used to drive a working fluid pump. A working fluid mass management system is integrated into or connected to the cycles.

Abstract: Various thermodynamic power-generating cycles are disclosed. A turbopump arranged in the cycles is started and ramped-up using a starter pump arranged in parallel with the main pump of the turbopump. Once the turbopump is able to self-sustain, a series of valves may be manipulated to deactivate the starter pump and direct additional working fluid to a power turbine for generating electrical power.

Abstract: A system for converting thermal energy to work. The system includes a working fluid circuit, and a precooler configured to receive the working fluid. The system also includes a compression stages and intercoolers. At least one of the precooler and the intercoolers is configured to receive a heat transfer medium from a high temperature ambient environment. The system also includes heat exchangers coupled to a source of heat and being configured to receive the working fluid. The system also includes turbines coupled to one or more of the heat exchangers and configured to receive heated working fluid therefrom. The system further includes recuperators fluidly coupled to the turbines, the precooler, the compressor, and at least one of the heat exchangers. The recuperators transfer heat from the working fluid downstream from the turbines, to the working fluid upstream from at least one of the heat exchangers.

Abstract: Systems and methods for recovering energy from waste heat are provided. The system includes a waste heat exchanger coupled to a source of waste heat to heat a first flow of a working fluid. The system also includes a first expansion device that receives the first flow from the waste heat exchanger and expands it to rotate a shaft. The system further includes a first recuperator coupled to the first expansion device and to receive the first flow therefrom and to transfer heat from the first flow to a second flow of the working fluid. The system also includes a second expansion device that receives the second flow from the first recuperator, and a second recuperator fluidly coupled to the second expansion device to receive the second flow therefrom and transfer heat from the second flow to a combined flow of the first and second flows.

Abstract: The present invention generally relates to a system that enables one to both: (i) address various thermal management issues (e.g., inlet air cooling) in gas turbines, gas turbine engines, industrial process equipment and/or internal combustion engines; and (ii) yield a supercritical fluid-based heat engine. In one embodiment, the present invention utilizes at least one working fluid selected from ammonia, carbon dioxide, nitrogen, or other suitable working fluid medium. In another embodiment, the present invention utilizes carbon dioxide or ammonia as a working fluid to achieve a system that enables one to address inlet cooling issues in a gas turbine, internal combustion engine or other industrial application while also yielding a supercritical fluid based heat engine as a second cycle using the waste heat from the gas turbine and/or internal combustion engine to create a combined power cycle.

Abstract: The present invention generally relates to a system that enables one to address various thermal management issues in advanced gas turbine engines. In one embodiment, the present invention relates to a method to extract heat from an air stream, utilize a significant fraction for on-board power generation, and reject a small quantity of heat to the fuel stream safely at, for example, a lower temperature. In another embodiment, the present invention relates to a method to extract heat from an air stream, utilize a significant fraction for on-board power generation, and reject a small quantity of heat to the fuel stream safely at, for example, a lower temperature with no potential air/fuel contact is disclosed.

Abstract: Various thermodynamic power-generating cycles employ a mass management system to regulate the pressure and amount of working fluid circulating throughout the working fluid circuits. The mass management systems may have a mass control tank fluidly coupled to the working fluid circuit at one or more strategically-located tie-in points. A heat exchanger coil may be used in conjunction with the mass control tank to regulate the temperature of the fluid within the mass control tank, and thereby determine whether working fluid is either extracted from or injected into the working fluid circuit. Regulating the pressure and amount of working fluid in the working fluid circuit helps selectively increase or decrease the suction pressure of the pump, which can increase system efficiency.

Abstract: A method for operating a gas turbine engine including a compressor and a combustor is provided. The method comprises channeling between about 0% to about 8% of the total airflow discharged from a compressor towards a pilot swirler coupled within the burner, wherein the burner includes a main swirler and an annular centerbody extending between the pilot and main swirlers, injecting a portion of the total fuel flow supplied to the burner through a plurality of apertures defined in a hollow pilot centerbody coupled within the pilot swirler, channeling the remaining airflow discharged from the compressor towards the main swirler, and injecting the remaining fuel flow supplied to the burner through at least one main swirler vane coupled within the main swirler, such that the portion of fuel is pre-mixed with a portion of the total airflow.

Abstract: A combustor swirl cup includes coaxial inner and outer swirlers separated by a tubular centerbody. The centerbody includes a bypass inlet surrounding the inner swirler and diverges aft along a perforate inner nozzle to terminate at an annular flameholder. An impingement ring is spaced forward from the flameholder in flow communication with the bypass inlet for receiving cooling air therefrom to impingement cool the flameholder.

Abstract: A method for operating a combustion system is provided. The method includes coupling the main swirler to the pilot swirler such that the main swirler substantially circumscribes the pilot swirler, supplying fuel to a first fuel circuit defined in the main swirler, and inducing swirling to the supplied fuel via a first set of swirler vanes positioned within the main swirler. The method also includes supplying fuel to a second fuel circuit defined in the main swirler, inducing swirling to the supplied fuel via a second set of swirler vanes positioned within the main swirler, each of the second set of swirler vanes comprising at least one second fuel passage defined therein, and coupling a shroud in flow communication to at least one of the first set of swirler vanes and the second set of swirler vanes, the shroud comprising at least one third fuel passage defined therein.

Abstract: A gas turbine engine combustor includes an annulus with one or more circular rows of burners and a means for providing a number of equiangular spaced apart flame temperature nonuniformities around the annulus during engine operation. The number of the flame temperature nonuniformities being equal to a circumferential acoustic mode to be attenuated in the combustor (i.e three, five, or seven). Fuel lines and/or water lines in supply communication with the burners and metering orifices in a portion of the fuel lines and/or the water lines may be used to produce the flame temperature nonuniformities. The annulus of the burners may have an equal number of equiangular spaced apart first and second arcuate segments of the burners and a means for operating the burners in the first segments and operating the burners in the second segments at different first and second flame temperatures respectively.

Abstract: A gas turbine engine fuel nozzle includes an axis of symmetry extending therethrough, the nozzle body including a first passage extending coaxially therethrough, a second passage, and a third passage, the second passage circumscribing the first passage, the third passage formed radially outward of the second passage, and a nozzle tip coupled to the nozzle body, the nozzle tip including at least one primary discharge opening in flow communication with the first passage, at least one secondary discharge opening in flow communication with the second passage, and at least one tertiary discharge opening in flow communication with the third passage.

Abstract: A method of operating a gas turbine engine is provided. The method includes discharging pilot fuel into a combustion chamber from a nozzle through at least one pilot fuel outlet defined in a tip of the nozzle, discharging steam from the nozzle through a plurality of steam outlets that are spaced circumferentially about the plurality of pilot fuel outlets, and discharging primary fuel from the nozzle through a plurality of primary fuel outlets that are circumferentially aligned with the plurality of steam outlets. To facilitate mixing the primary fuel with the steam, the primary fuel is discharged from the nozzle tip at an oblique angle with respect to a centerline extending through the nozzle tip.

Abstract: Disclosed here are integrated methods and systems for producing fuel from biomass. The methods and systems pertain to gasifying a feed derived from biomass fermentate separation residue, such as corn-based distiller's grains, and producing a liquid transportation fuel component, such as aviation turbine fuel, from the gasified feed in a hydrocarbon synthesis reactor. At least a portion of the waste heat from the hydrocarbon synthesis reactor is supplied to a thermal process for liquefying, fermenting or distilling a biomass, or to a thermal process for separating or treating a biomass fermentate separation residue.

Abstract: A method for operating a gas turbine engine including a compressor and a combustor is provided. The method comprises channeling between about 0% to about 8% of the total airflow discharged from a compressor towards a pilot swirler coupled within the burner, wherein the burner includes a main swirler and an annular centerbody extending between the pilot and main swirlers, injecting a portion of the total fuel flow supplied to the burner through a plurality of apertures defined in a hollow pilot centerbody coupled within the pilot swirler, channeling the remaining airflow discharged from the compressor towards the main swirler, and injecting the remaining fuel flow supplied to the burner through at least one main swirler vane coupled within the main swirler, such that the portion of fuel is pre-mixed with a portion of the total airflow.

Abstract: A method for operating a combustion system is provided. The method includes coupling the main swirler to the pilot swirler such that the main swirler substantially circumscribes the pilot swirler, supplying fuel to a first fuel circuit defined in the main swirler, and inducing swirling to the supplied fuel via a first set of swirler vanes positioned within the main swirler. The method also includes supplying fuel to a second fuel circuit defined in the main swirler, inducing swirling to the supplied fuel via a second set of swirler vanes positioned within the main swirler, each of the second set of swirler vanes comprising at least one second fuel passage defined therein, and coupling a shroud in flow communication to at least one of the first set of swirler vanes and the second set of swirler vanes, the shroud comprising at least one third fuel passage defined therein.