Abstract: An apparatus and method are disclosed that enable a multi-spool gas turbine engine to produce ISO-qualified power quality during block loading, while also achieving high efficiency over a wide power range. Such an engine would enable new markets, including modern data centers, to operate independently from the utility grid, while achieving high efficiency, reliability, and power quality. The engine includes a variable area nozzle upstream of the free power turbine. On experiencing the torque spike, the variable area nozzle is opened rapidly to provide rapid an increase in air flow aspirated by the engine. When combined with a proportionally increased fuel supply, the power and torque of the free power turbine increases with a time constant close to that of the fuel valve and variable area nozzle movement.

Abstract: A metallic-ceramic joint for a turbo-compressor spool is disclosed. A temperature-limited joint is moved from outside the bearings to between the bearings and near the center of the shaft joining the turbine and compressor. This placement can lower the temperature at and around the joint and reduces the sharp gradient (and associated thermal stress) naturally occurring between the turbine rotor and the cooler joint. The bearing closest to the compressor can be an oil bearing and the bearing closest to the turbine an air bearing. The bearing closest to the compressor and the bearing closest to the turbine can both be an oil bearing. The bearing closest to the compressor and the bearing closest to the turbine can both be an air bearing. Moving the metallic-ceramic joint between the bearings can provide sufficient isolation to enable the all-air bearing solution.

Abstract: A method and apparatus are disclosed for a gas turbine spool design combining metallic and ceramic components in a way that controls clearances between critical components over a range of engine operating temperatures and pressures. In a first embodiment, a ceramic turbine rotor rotates just inside a ceramic shroud and separated by a small clearance gap. The ceramic rotor is connected to a metallic volute. In order to accommodate the differential rates of thermal expansion between the ceramic rotor and metallic volute, an active clearance control system is used to maintain the desired axial clearance between ceramic rotor and the ceramic shroud over the range of engine operating temperatures. In a second embodiment, a ceramic turbine rotor rotates just inside a ceramic shroud which is part of a single piece ceramic volute/shroud assembly.

Abstract: A metallic-ceramic joint for a turbo-compressor spool is disclosed. A temperature-limited joint is moved from outside the bearings to between the bearings and near the center of the shaft joining the turbine and compressor. This placement can lower the temperature at and around the joint and reduces the sharp gradient (and associated thermal stress) naturally occurring between the turbine rotor and the cooler joint. The bearing closest to the compressor can be an oil bearing and the bearing closest to the turbine an air bearing. The bearing closest to the compressor and the bearing closest to the turbine can both be an oil bearing. The bearing closest to the compressor and the bearing closest to the turbine can both be an air bearing. Moving the metallic-ceramic joint between the bearings can provide sufficient isolation to enable the all-air bearing solution.

Abstract: An LNG fuel system for gas turbine engine systems is disclosed that allows more efficient management of cryogenic fuels such as LNG to reduce emissions and improve engine efficiency. In one configuration, an intercooled, recuperated gas turbine engine comprises an LNG tank incorporating a liquid-to-vapor LNG fuel circuit in parallel with a vapor fuel circuit. In a second configuration, an alternate vapor fuel circuit is disclosed. In either configuration, the fuel in the liquid fuel circuit is vaporized and heated by the engine's intercooler or by both the engine's intercooler and/or a heat exchanger on the exhaust. In another configuration, both the fuel in the liquid-to-vapor LNG fuel circuit and the vapor fuel circuit are heated by a heat exchanger on the exhaust.

Abstract: A method and apparatus are disclosed which are directed generally to gas turbine engine systems and specifically to a method utilizing a heat pipe or pipes associated with a thermal oxidizer for preheating a fuel-air mixture. This preheating of a fuel-air mixture allows a substantial reduction in size a thermal oxidizer used as a combustor so that it can be used with all fuels, especially natural gas.

Abstract: A heat exchange device of a type for affecting an exchange of heat between a first and second fluid is characterized by a plurality of heat exchange cells in a stacked arrangement wherein each cell includes inlet and outlet manifold rings which define inlet and outlet manifolds, respectively. Adjacent heat exchange cells are bonded to one another via metallurgical bonds between the contacting surfaces of the manifold rings. In a further aspect, a method for the manufacture of a heat exchange device is provided.

Abstract: This disclosure relates to a highly efficient gas turbine engine architecture utilizing multiple stages of intercooling and reheat, ceramic technology, turbocharger technology and high pressure combustion. The approach includes utilizing a conventional dry low NOx combustor for the main combustor and thermal reactors for the reheat apparatuses. In a first configuration, there are three separate turbo-compressor spools and a free power turbine spool. In a second configuration, there are three separate turbo-compressor spools but no free power spool. In a third configuration, all the compressors and turbines are on a single shaft. Each of these configurations can include two stages of intercooling, two stages of reheat and a recuperator to preheat the working fluid before it enters the main combustor.

Abstract: A heat exchange device of a type for affecting an exchange of heat between a first and second fluid is characterized by a plurality of heat exchange cells in a stacked arrangement and defining first, second and third manifolds. In certain aspects, an apparatus and method for reinforcing the heat exchange device against pressure loads while accommodating thermal expansion of the outlet manifold are provided.

Abstract: Various embodiments are disclosed to utilize various fuels, including liquid natural gas fuels, to improve engine efficiency in gas turbine engines. In one configuration, a fuel is heated by a heat exchanger utilizing waste exhaust heat of a gas turbine engine. In another configuration, LNG fuel is heated using a pre-cooler for the inlet air stream of a gas turbine engine. In another configuration, fuel is injected into the pressurized air, downstream of the air-to-air intercooler. In yet another configuration, fuel is pumped through the engine's intercooler or a secondary heat exchanger exchanging heat with the compressed air stream between the low-pressure compressor and high-pressure compressor. In another configuration, the fuel is first heated by the intercooler and then further heated by a heat exchanger utilizing waste exhaust heat of the gas turbine engine.

Abstract: A method and apparatus are disclosed for a gas turbine spool design combining metallic and ceramic components in a way that controls clearances between critical components over a range of engine operating temperatures and pressures. In a first embodiment, a ceramic turbine rotor rotates just inside a ceramic shroud and separated by a small clearance gap. The ceramic rotor is connected to a metallic volute. In order to accommodate the differential rates of thermal expansion between the ceramic rotor and metallic volute, an active clearance control system is used to maintain the desired axial clearance between ceramic rotor and the ceramic shroud over the range of engine operating temperatures. In a second embodiment, a ceramic turbine rotor rotates just inside a ceramic shroud which is part of a single piece ceramic volute/shroud assembly.

Abstract: A method and apparatus are disclosed for a multi-spool gas turbine power plant which utilizes motor/generator devices on two or more spools for starting the gas turbine and for power extraction after starting. Methods are disclosed for controlling engine responsiveness under changing load and/or ambient air conditions; providing a momentary power boost when required; providing some engine braking when needed; providing over-speed protection for the free power turbine when load is rapidly lowered or disconnected; charging an energy storage system; and restoring the compressors and/or turbines toward their operating lines when surge or choking limits are approached.

Abstract: An improved window system for a solar receiver provides a high level of impedance to thermal re-radiation while minimizing Fresnel losses. The window system is characterized by a bundled array of optically transmissive members. In further aspects, a solar receiver employing the window system and a method for manufacture are provided.

Abstract: A solar receiver for conversion of solar radiation to thermal energy includes an enclosure defining a cavity and having an aperture for receiving an influx of concentrated solar radiation. A heat exchanger is received within the cavity for transferring heat out of the solar receiver. The heat exchanger comprises a plurality of heat exchange cells arranged in polygonal array within the cavity. Each heat exchange cell comprises an inlet, an outlet, and a heat exchange matrix interposed within a first volume defined between a first plate and a second plate spaced apart from the first plate. The inlet and outlet are in fluid communication with the first volume and the first plate, second plate, and heat exchange matrix are monolithically bonded as a unit. The first plate receives concentrated solar radiation and the heat exchange media defines a pathway for a fluid flowing from the inlet to the outlet between the first and second plates.

Abstract: Power generation systems and methods are provided with features directed to various innovations including ones relating to the conversion of concentrated solar and biomass energy to electricity, load-shifting of electrical power supply systems, gas turbine devices and cycles, and power plant control systems.

Abstract: The present invention combines the principles of a gas turbine engine with an electric transmission system. A method and apparatus are disclosed for utilizing metallic and ceramic elements to store heat energy derived from a regenerative braking system. The subject invention uses this regenerated electrical energy to provide additional energy storage over conventional electrical storage methods suitable for a gas turbine engine. The subject invention provides engine braking for a gas turbine engine as well as reducing fuel consumption.

Abstract: A method and apparatus are disclosed for a gas turbine power plant with a variable area turbine nozzle and an integrated motor/alternator device for starting the gas turbine and power extraction after starting.

Abstract: A heat exchange device of a type for affecting an exchange of heat between a first and second fluid is characterized by a plurality of heat exchange cells in a stacked arrangement wherein each cell includes inlet and outlet manifold rings which define inlet and outlet manifolds, respectively. Adjacent heat exchange cells are bonded to one another via metallurgical bonds between the contacting surfaces of the manifold rings. In a further aspect, a method for the manufacture of a heat exchange device is provided.

Abstract: A heat exchange device of a type for affecting an exchange of heat between a first and second fluid is characterized by a plurality of heat exchange cells in a stacked arrangement and defining first, second and third manifolds. In certain aspects, an apparatus and method for reinforcing the heat exchange device against pressure loads while accommodating thermal expansion of the outlet manifold are provided.

Abstract: An apparatus and method are provided for permitting free rotation of turbine nozzle vanes, while minimizing or eliminating leakage on the vane side-walls. The device incorporates a plurality of nozzle vanes arranged around the circumference of a radial or mixed inflow turbine. Each of the nozzles is individually attached to a rod positioned perpendicular to the flow direction. The nozzle rods in the circumferential array protrude through a movable annular back-wall, and are rotated by a linkage or gear. Between discrete movements of the vane mechanism, a bellows device is used to provide pressure-actuated force in the movable back-wall, thereby clamping the nozzle between the two surfaces. Prior to rotating the nozzles, pressure within the bellows interior is decreased via venting to cause a retraction of the back wall.