Abstract: The invention provides systems, processes and methods for converting heterogeneous coal-fired power plants to cogenerate a sustainable, consistent, and economic cement. Such cogeneration enables a simultaneous production of both electric power and cement and thus provides significant economic and environmental efficiencies and benefits and eliminates a major source of greenhouse gas emissions and thereby mitigates a major contributor to climate change.

Abstract: A jet engine, in particular for an aircraft, having a high-pressure compressor that is situated inside a compressor housing, the high-pressure compressor having blade elements that, through their rotational motion, compress air flowing into the high-pressure compressor via an intake channel, the high-pressure compressor having a plurality of compressor stages on which the blade elements are situated, and the jet engine also having an integrated electric motor/generator unit, wherein the motor/generator unit is situated in the rotational plane of the at least first compressor stage of the high-pressure compressor, and includes a stator that extends around the periphery of the compressor housing, as well as a runner that is formed by the blade elements of the at least first compressor stage, and that the motor/generator unit has an output power of 100 kVA to 150 kVA.

Abstract: The invention is intended to maintain turbine reliability when, based on a gas turbine designed for one desired cycle, a gas turbine for another different cycle is manufactured. A channel of a compressor is formed such that a mass flow of a fluid compressed by the compressor changes. Thus, when manufacturing, based on the gas turbine designed for one desired cycle, the gas turbine for another different cycle, turbine reliability can be maintained.

Abstract: The present invention discloses a method and system for augmenting shaft output of stationary gas turbines that can be used in multiple modes of operation. The system comprises a washing unit (25, 27, 28) adapted to inject a spray (26) of atomized liquid so as to impinge on the compressor blades (12) in order to wet said blades (12), thereby obtaining a release of fouling material from said blades (12); and at least one liquid injection unit (21, 23, 24, 29, 210, 212, 214, 215, 216) adapted to inject a spray (22, 211, 213) of atomized liquid into an air stream of said turbine duct (101) or at the gas turbine (10) in order to increase a mass flow of said air flow, wherein the power output from said gas turbine engine can be augmented. With the invention follows also benefits such as fuel savings and improved environmental performance by reduction of emissions.

Abstract: A high energy system comprising a high energy electrical device powered by an electrical generator both of which are cooled by a cryogenic liquid oxidant stored in a storage tank. A power turbine powered by a combustor using fuel and the oxidant drives the electrical generator. A turbopump powered by a portion of exhaust flow from the power turbine pumps the cryogenic liquid oxidant from the storage tank to the generator and the device. In an exemplary embodiment of the system, the electrical device is a directed energy weapon, uses liquid air as the liquid oxidant, and uses a variable geometry turbine nozzle in the power turbine. A reheater may be used between a high pressure turbine and a lower pressure turbine of the power turbine. Compressor bleed from a gas turbine engine may provide air augmentation to the power turbine.

Abstract: Loss reduction apparatus for a fluid transfer system includes a fluid device. The fluid device defines a first fluid path along which a greater part of a fluid flows in a first condition, and a second fluid path along which a greater part of the fluid flows in a second condition. The apparatus is arranged so that when a leak occurs at a location in the system, the leak causes a relative reduction in fluid pressure at the location, which moves the device from the first condition to the second condition.

Abstract: The invention provides a production process of a gas turbine capable of being applied to various cycles. A principal part of a gas turbine is set in advance based on roughly set conditions, and the number of stages of a compressor and the number of stages of a turbine, which can provide conditions suitable for a desired cycle, are set based on the set principal part. The compressor and the turbine each having the set number of stages and included in the principal part are combined with each other to construct the gas turbine. When the set number of stages of the compressor or the turbine differs among a plurality of desired cycles, a substantially disk-shaped member having an outer periphery, which forms an inner peripheral wall of a substantially annular flow passage of the compressor or the turbine, is assembled into the cycle having a smaller number of stages so that the bearing-to-bearing distance is kept constant in the gas turbine operated in the plurality of desired cycles.

Abstract: An aircraft gas turbine engine fuel metering unit incorporating a memory device for storing data relevant to that unit, and an electrical connection arrangement whereby data can be read from and/or written to said memory device by an associated electronic engine controller, said stored data including data relating to at least one of the performance, the identification, the health, and the service life of that fuel metering unit. The invention further resides in an aircraft gas turbine engine fuel supply system and a method of operating such a system.

Abstract: A method for exchanging heat between a first fluid and a second fluid. The method includes providing a heat exchanger having a stack of at least two layers of support structures, wherein each support structure layer is formed from a lattice of support members, and substantially fluidly separating the at least two support structure layers using at least one barrier such that each layer defines a fluid passageway. The method also includes directing a flow of first fluid through a first of the fluid passageways, and directing a flow of second fluid through a second of the fluid passageways that is adjacent the first fluid passageway to facilitate exchanging heat between the first and second fluids.

Abstract: A combustion turbine power plant (10) incorporating a desiccating scrubber (140) for simultaneously removing water and sulfur from a flue gas (20) of the power plant (10). The desiccating scrubber (140) may include an inlet nozzle (145) for spraying an aqueous solution (142) containing a desiccant and a base into flue gas (20) so the aqueous solution (142) makes direct contact with flue gas (20). A filter (162) may be provided to collect sulfur compounds downstream of the desiccating scrubber (140) and a regenerator (164) may be provided for recovering water. A controller (148) may control a base supply (170) and a desiccant supply (172) to regulate the respective amounts of each introduced into the aqueous solution (142). Controller (148) may be responsive to sensors (142) measuring the water and sulfur content of flue gas (20) exhausted to atmosphere (144). The desiccating scrubber (140) may include a demister (160) to entrain carryover droplets from a sprayed aqueous solution (142).

Abstract: A mounting system for mounting an air-cooled device to a mount, the device having a mounting flange and a cooling air outlet radially inward of an outer periphery of the device, the mounting flange adapted to cooperate with the mount, where the mounting system has a cooling air exhaust collection shroud adapted to surround the device and at least a portion of the mount, the shroud having a discharge outlet.

Abstract: A multi-function spray nozzle for engine applications useful as a cooling device to introduce a fluid into the fluid stream of the engine, and as a cleaning device to introduce a fluid to clean internal components of the engine. The nozzle includes a multi-layered arrangement of etched plates defining flow paths for the first and second fluids. Non-radial feed slots direct the first fluid into a cylindrical swirl chamber. The swirling fluid exits the swirl chamber through a spray orifice or a prefilmer, depending on whether the nozzle is configured as a simplex or prefilmer nozzle. Other non-radial feed slots direct the second fluid inward, downstream of the first fluid, to create a fine dispersion of droplets for fluid stream cooling purposes. During cleaning, only the first fluid is introduced through the nozzle, which results in a larger droplet size suitable for cleaning purposes of the internal components of the engine.

Abstract: A turbocharger comprising at least one turbine wheel supplied with exhaust gas from a combustion motor. The amount of gas supplied is determined by a fluid control arrangement to which an actuation device is assigned for generating a controlling movement for the fluid control arrangement. In addition, a transmitting mechanism for this movement comprising an adjusting device is presented by which the control movement may be adjusted.

Abstract: In a gas turbine power generator, a compressor rotor and a junction boss are assembled by fitting a convex faucet joint provided on the compressor rotor and a concave faucet joint provided on the junction boss, in a freely releasable manner, and the compressor rotor and a rotor shaft are assembled by fitting the convex faucet joint provided on the compressor rotor and a concave faucet joint provided on the rotor shaft, in a freely releasable manner, and those compressor rotor, the rotor shaft and a generator core are combined in series and fastened by using a tie bolt and a nut, which is connected to the junction boss of the turbine rotor.

Abstract: A production process of a gas turbine capable of being applied to various cycles. A principal part of a gas turbine is initially set based on roughly set conditions, and the number of stages of the compressor and of the turbine for a desired cycle are set for the principal part. The compressor and the turbine each having the set number of stages and included in the principal part are combined to construct the gas turbine. When the set number of stages of the compressor or the turbine differs for a different desired cycle, a disk-shaped member having an outer periphery, which forms an inner peripheral wall of the annular flow passage of the compressor or the turbine, is assembled into the principal part having a smaller number of stages so that the bearing-to-bearing distance is kept constant.

Abstract: An acoustic-structural LPC splitter assembly which comprises a structural acoustic splitter through which are arranged a plurality of bleed exhaust ports, the acoustic splitter having a first and second end, an inner and outer surface, a front joint for securing the first end, and a slip joint formed at an FEGV interface for securing the second end, wherein the structural acoustic splitter provides support sufficient to maintain concentricity of an LPC inner case.

Abstract: In a gas and steam power plant for water desalination, a heat exchanger surface is arranged in the region of the cold end of a heat recovery boiler. This surface is provided for preheating the water to be desalinated.

Abstract: An electrical machine, such as a generator or motor, is incorporated in a gas turbine engine. The engine has compressor blades which are shrouded at. Beyond the shroud, an electrical machine is provided by rotor projections which run in a channel in flux cores, with which excitor coils are associated. The result is an electrical machine which is external to the combustion gas paths of the engine, for ready access, and can have optimised magnetic flux paths for efficiency. High relative speeds within the electrical machine provide further advantages.

Abstract: A mounting system, for installing a starter-generator to an accessory housing, where the starter-generator has a mounting end with a connecting flange and a cooling air outlet radially inward of a peripheral starter-generator housing edge, and where the accessory housing has a matching connecting flange radially inward of a peripheral accessory housing edge. The mounting system includes a cooling air outlet collection shroud enveloping the peripheral starter-generator housing edge and the peripheral accessory housing edge, the shroud having a discharge outlet. A V-band clamp releasably secures the connecting flanges together and is enveloped within the shroud in a compact mounting system that collects and discharges the exhausted cooling air.

Abstract: A system and method for creating power and pasteurizing water is provided. The system includes a power generation subsystem and a water pasteurization subsystem, which are linked together as follows. The power generation subsystem comprises a turbine power generator. Air (or other suitable working fluid) flows through the turbine power generator to generate power by known methods. The air is heated prior to flowing into the turbine to increase its speed for greater power generation. The water pasteurization subsystem includes one or more heat exchangers, at least one of which is connected to receive the hot airflow exiting the turbine. The heat from the turbine-exiting airflow is utilized for pasteurizing colder wastewater inside the heat exchanger.

Abstract: A method of separating oxygen using a ceramic membrane unit having one or more ceramic membranes, preferably formed of a mixed conducting ceramic, for instance, a perovskite, capable of conducting both oxygen ions and electrons. Oxygen is separated within the ceramic membrane unit under impetus of compressing an incoming oxygen containing feed. The compressor used in the compression is powered by the work of expansion produced by expanding a process stream composed of at least a portion of the retentate produced in the ceramic membrane unit. Prior to expansion, the process stream is cooled to allow the use of less expensive materials in expanders used in the expansion. As a result, expansion of the process stream alone is insufficient to meet the power requirements involved in the compression. Interstage expansion with reheating is used to make up for the power deficit.

Abstract: A gas turbine which is capable of operating in more than one pressure mode. The gas turbine, which may include a single fixed spool, multiple fixed spools, or a combination of fixed spool(s) and a free turbine, can operate in a positive pressure mode, a transatmospheric mode, or a subatmospheric mode. Valving is provided to control the particular pressure mode of operation in response to system requirements and to switch between pressure modes as required. The gas turbine is particularly useful with a catalytic combustor where the gas turbine can be started in a mode where the catalytic combustor, and its associated preheater, is at or below atmospheric pressure.

Abstract: A gas turbine which is capable of operating in more than one pressure mode. The gas turbine, which may include a single fixed spool, multiple fixed spools, or a combination of fixed spool(s) and a free turbine, can operate in a positive pressure mode, a transatmospheric mode, or a subatmospheric mode. Valving is provided to control the particular pressure mode of operation in response to system requirements and to switch between pressure modes as required.

Abstract: Flame arrestor to cover aircraft engines made up of one ventilation wire mesh (6), one upper metallic plate (9) where wire mesh sits (6) on the edges of a circular hole (10) and a wall (25) which is located next to a chamfer (26) placed at the edge of a central hole (5) existing in the platform (3). On the lower side of the thin composite wall (25) there is a ring (16) with outer flange whose width coincides with that of the wall, and another flanged ring (14) coinciding in height with the chamfer (26), creating an interior cavity (27) where gases are conducted and accumulated. All these elements are joined together by some bolts (22) that go through them and finish with a lower metallic plate (12) and an octagonal shaped part (19) separated by a specific distance established by the appropriate elements.

Abstract: A ventilation scheme for a rotary machine supported on pedestals within an enclosure having a roof, end walls and side walls with the machine arranged parallel to the side walls, includes ventilation air inlets located in a first end wall of the enclosure; a barrier wall located within the enclosure, proximate the first end wall to thereby create a plenum chamber. The barrier wall is constructed to provide a substantially annular gap between the barrier wall and a casing of the turbine to thereby direct ventilation air axially along the turbine; one or more ventilation air outlets located proximate a second, opposite end wall on the roof of the enclosure. In addition, one or more fans are provided for pulling ventilating air into said plenum chamber via the ventilation air inlets.

Abstract: A gas turbine engine borescope plug including a retainer that facilitates extending the useful life of the borescope plug is described. The borescope plug seals a pair of opposing inspection port openings in at least two respective spaced-apart walls and maintains sealing contact despite differential thermal growth between the two walls. The borescope plug includes the retainer, a plunger, and a biasing mechanism. The plunger extends through the biasing mechanism and the retainer. The retainer contacts the cylindrical biasing mechanism and maintains its position relative to the plunger to prevent contact between the plunger and the biasing mechanism.

Abstract: A gas turbine generator plant is provided in which, by forming auxiliary equipment, including a starter, a lubricating oil device, a control oil device, and a lubricating oil main tank, into a unit, the auxiliary equipment may be disposed with a building in a unitary manner with a generator and a gas turbine unit. The auxiliary equipment is made unitary to form the unitary auxiliary equipment. The unitary auxiliary equipment, the generator, and the gas turbine unit are disposed first, second, and third, respectively, within the building. Thus, the installed floor area of the plant may be dramatically reduced and in turn, construction costs may also be reduced. Furthermore, the unitary auxiliary equipment can be transported in one piece under a water resistant cover, so that it is possible to limit, all at once, the occurrence of rust on the unitary auxiliary equipment that could result from exposure to salt air during sea transport. The packing may also be high-density so as to reduce transportation costs.

Abstract: A system for the destruction of volatile organic compounds while generating power. In a preferred embodiment the system comprises a combustor and a reaction chamber connected to an exit of the combustor. A primary inlet to the combustor supplies a primary fuel to the combustor. A secondary fuel, comprising air and an amount of one or more volatile organic compounds, is supplied to a compressor, which compresses the secondary fuel and directs the secondary fuel to the combustor and the reaction chamber. The system is suitably configured to enable the stoichiometric reaction of the two fuels in a manner sufficient to destroy the volatile organic compounds contained in the secondary fuel and power a turbine engine connected to an exit of the reaction chamber.