Abstract: Embodiments of the disclosure include systems and methods for providing a flow of purge air and an adjustable flow of cooling air to a wheel space cavity or a stator cavity. According to one embodiment, there is disclosed a turbine assembly. The turbine assembly may include a rotor assembly, a stator assembly positioned adjacent to the rotor assembly, and a wheel space cavity formed between the rotor assembly and the stator assembly. At least one fixed purge air orifice may be associated with the stator assembly. The fixed purge air orifice may be configured to provide a flow of purge air to the wheel space cavity. Moreover, at least one adjustable cooling air orifice may be associated with the stator assembly. The at least one adjustable cooling air orifice may be configured to provide a flow of cooling air to the wheel space cavity.

Abstract: A system for sensing at least one physical characteristic associated with an engine including a turbine having a plurality of blades turning inside a casing, the system including: a pressure sensor coupled substantially adjacent to the casing and including at least one output; a port in the turbine casing for communicating a pressure indicative of a clearance between the blades and casing to the pressure sensor; a cooling cavity substantially surrounding the pressure sensor; and, an inlet for receiving fluid from the engine and feeding the fluid to the cooling cavity to cool the pressure sensor; wherein, the pressure sensor output is indicative of the clearance between the blades and casing.

Abstract: A fan case for a gas turbine engine includes an outer case defined about an engine axis and a hard ballistic liner defined about the engine axis, the hard ballistic liner within the outer case.

Abstract: An improved seal assembly for use with a combustion liner assembly is employed with a gas turbine engine so as to control fluid flow. The seal assembly has a bi-metal sealing member that is affixed to a first surface that is proximal to a second perpendicular surface that is not in contact with the first surface, thus providing a potential fluid flow path. Upon heating, the bi-metal sealing member “uncoils” contacting the second perpendicular surface, thus blocking the flowpath between the two surfaces. Various metals may be provided to provide predetermined sealing characteristics.

Abstract: A gas turbine engine is disclosed which includes a bypass passage that in some embodiments are capable of being configured to act as a resonance space. The resonance space can be used to attenuate/accentuate/etc a noise produced elsewhere. The bypass passage can be configured in a number of ways to form the resonance space. For example, the space can have any variety of geometries, configurations, etc. In one non-limiting form the resonance space can attenuate a noise forward of the bypass duct. In another non-limiting form the resonance space can attenuate a noise aft of the bypass duct. Any number of variations is possible.

Abstract: An ACC system and method of using such for changing a turbine blade to BOAS gap on an aircraft engine is disclosed. The ACC system may comprise a first ring, a first supply line and a first flow control assembly. The first ring may be configured to substantially encircle a portion of a case assembly that is disposed around an aircraft engine turbine. The first ring may include a plurality of segments that each define a chamber, an inlet port and a plurality of outlet ports. At least a portion of the outlet ports may be configured to be disposed adjacent to the case. The first supply line may be operatively connected to a first segment of the plurality of segments. The first flow control assembly may be operatively connected to the first supply line and configured to meter the flow of cool air into the first segment.

Abstract: An external supply pipe is disclosed, for supplying steam to a mid-span packing disposed about a shaft coupling a high pressure (HP) and an intermediate pressure (IP) section of an opposed flow steam turbine. The external supply pipe is disposed on an exterior of the steam turbine casing, which allows for direct measurement of steam flow to the mid-span packing.

Abstract: A wind turbine power plant comprises a plurality of wind turbines, each having a rated output and under the control of a power plant controller. The power plant also has a rated output which may be over-rated in response to one or more of electricity pricing data, power plant age and operator demand. The power plant controller can send over-rating demand signals to individual turbines. The controllers at the turbines include a fatigue life usage estimator which estimates a measure of the fatigue life consumed by key components of the turbine. If this measure exceeds a target value for any component, over-rating is prevented at that turbine.

Abstract: A gas turbine engine includes an inner shaft extending axially along the gas turbine engine, a plurality of disks extending radially inwardly and toward the inner shaft, at least one hole in at least one of the plurality of disks, and an obstruction positioned between the inner shaft and an end of the disk having the at least one hole, such that a bore flow that flows along an axial length of the inner shaft is obstructed from flowing along the shaft by the obstruction, and forced to flow radially outward from the obstruction, through the at least one hole, and radially inward toward the inner shaft.

Abstract: An exemplary geared turbomachine assembly includes an acoustic treatment that is in an unducted area of a geared turbomachine.

Abstract: A bifurcated inlet scoop frame for a gas turbine engine and method of using such frame for a gas turbine engine are disclosed. The bifurcated inlet scoop frame may include a nose, a first side panel, and a second side panel. The first side panel and the nose may define a first inlet port. The second side panel and the nose may define a second inlet port. The method may comprise providing a bifurcated inlet scoop frame, splitting the fan air flow, and receiving fan air through the bifurcated inlet scoop frame.

Abstract: A method for starting-up a wind turbine having a rotor with at least one rotor blade is provided. The method includes rotating the at least one rotor blade towards a main operating position using a pitch drive system including a pitch bearing supporting the at least one rotor blade, and a pitch-driving pinion meshing with the pitch bearing; and activating a pump to feed a lubricant to a lubrication pinion meshing with one of the pitch bearing and the pitch-driving pinion before the at least one rotor blade reaches the main operating position so that the lubricant is mainly transferred to a load portion of the pitch bearing and/or a load portion of the pitch-driving pinion. Further, a control assembly for use with the wind turbine is provided.

Abstract: The present application provides a rotor coupling guard for use with removing a flow of air about a rotor coupling of a turbo-machine. The rotor coupling guard may include an inner cover with a number of apertures surrounding the rotor coupling and an outer cover surrounding the inner cover. Rotation of the rotor coupling forces the flow of air through the apertures in the inner cover and away from the rotor coupling.

Abstract: A method of modifying a steam turbine to change from a first maximum thermal power of the steam generator to a second maximum thermal power of the steam generator. The method can include replacing, in the high-pressure module, at least one set of fixed blades sized for the first maximum thermal power by at least one set of fixed blades sized for the second maximum thermal power. The at least one set of moving blades are sized to operate at the first and second maximum thermal powers. The rotor and the at least one set of moving blades of the high-pressure module remain unchanged on changing from the first maximum thermal power to the second maximum thermal power.

Abstract: A compressor comprises an impeller wheel mounted within a housing defining an inlet and an outlet. The wheel has a plurality of vanes and is rotatable about an axis. The housing has an inner wall defining a surface located in close proximity to radially outer edges of the impeller vanes which sweep across said surface as the impeller wheel rotates about its axis. The inlet comprises a tubular wall extending away from the impeller wheel in an upstream direction. An enclosed chamber is defined between said inner wall and an outer wall and in communication with at least one opening in said in said inner wall. The outer wall is penetrated by at least one ventilation aperture that is designed to be connected via a conduit to a location upstream of the inlet and downstream of an air filter.

Abstract: The nozzles include inlet ports circumferentially arranged into a group and an opening and closing valve disposed so as to be commonly functioned. This arrangement realizes a gas turbine with no deterioration of efficiency against fluctuation of gas inflow rate by only one heat-resistant moving component additionally installed. The variable nozzle number turbine according to this invention also realizes a turbine compressor with no surge limit when used as a regenerator. These turbines further realizes a small-sized gas turbine with improved fuel economy under partial load conditions and a turbocharger for regenerating electric power as well as improving efficiency of a displacement engine.

Abstract: An axial oil scoop for a gas turbine engine includes an outer surface with a concave profile, the outer surface includes a multiple of radial holes.

Abstract: In some embodiments, an apparatus includes a target member, a sensor and a mounting assembly. The target member is coupled to a shaft that is disposed within an engine housing and that rotates about an axis. The target member includes a target surface that is substantially normal to the axis of rotation of the shaft. The sensor is configured to produce a signal associated with a distance between a sensor tip and the target surface. The mounting assembly is coupled to the sensor and the engine housing, and is configured to adjust the distance between the sensor and the target surface.

Abstract: A vacuum pump, in particular to a turbomolecular pump, has a pump inlet, a pump outlet and a pump space for a gas to be pumped arranged between the pump inlet and the pump outlet, and at least one cooling gas inlet for a cooling gas for cooling the vacuum pump, the pump further having one or more hollow regions for the cooling gas connected in a gas conducting manner to the cooling gas inlet and arranged outside the pump space, wherein the or each hollow region is bounded by at least one component of the vacuum pump to be cooled.

Abstract: A variable geometry mechanism suitable for use in a gas turbine engine is disclosed in which movable vane segments which are coupled to a rotatable ring, or rings, are used to change an aerodynamic property of a working fluid flowing through the gas turbine engine. The movable vane segments can be rotated through the ring, or rings, between a first position associated with the first vane and a second position associated with a second vane to place the movable vane segments in proximity to one or the other of the first and second vanes of the gas turbine engine. The movable vane segments can be used to alter, among other things, camber, exit flow area, and can be used to influence and/or accommodate such properties as incidence angle, and swirl angle.

Abstract: A gas turbine engine is disclosed having a particle separator and an ejector disposed downstream of the particle separator and structured to entrain a dirty flow from the separator. A container of working fluid can be placed in flow communication with the ejector to provide an ejector flow to entrain the dirty flow from the particle separator. Alternatively and/or additionally, the ejector can be configured to use a flow of working fluid from the gas turbine engine as an ejector flow.

Abstract: Systems and methods are provided for generating power by a hydrogenerator which can be attached to a portion of a towed marine streamer. A hydrogenerator includes: a stator configured to impart a spin to water which flows through the stator, wherein the stator is inline with and fluidly coupled to a propeller; the propeller configured to receive water which has passed through the stator, wherein the propeller is connected to a generator; the propeller configured to spin; and the generator configured to output power for use by components attached to the towed marine streamer.

Abstract: The present invention relates to a method of pressurizing a fluid comprising carbon dioxide, the method includes: obtaining the fluid from a unit for removing carbon dioxide from a process gas; compressing the fluid to a pressure above the critical pressure of carbon dioxide; and cooling the compressed fluid to a temperature above the critical temperature of carbon dioxide to produce a supercritical fluid. The invention further relates to an apparatus for pressurizing a fluid comprising carbon dioxide, the apparatus including: means for obtaining the fluid from a unit for removing carbon dioxide from a process gas; means for compressing the fluid to a pressure above the critical pressure of carbon dioxide; and means for cooling the compressed fluid to a temperature above the critical temperature of carbon dioxide to produce a supercritical fluid.

Abstract: A pressure sensor measures an organic Rankine cycle (ORC) working fluid pressure in front of a radial inflow turbine, while a temperature sensor measures an ORC working fluid temperature in front of the radial inflow turbine. A controller responsive to algorithmic software determines a superheated temperature of the working fluid in front of the radial inflow turbine based on the measured working fluid pressure and the measured working fluid temperature. The controller then manipulates the speed of a working fluid pump, the pitch of turbine variable inlet guide vanes when present, and combinations thereof, in response to the determined superheated temperature to maintain the superheated temperature of the ORC working fluid in front of the radial inflow turbine close to a predefined set point. The superheated temperature can thus be maintained in the absence of sensors other than pressure and temperature sensors.

Abstract: A gas turbine engine includes a fan section including a fan rotatable about an axis. A speed reduction device is connected to the fan. The speed reduction device includes a planetary fan drive gear system with a planet gear ratio of at least 2.5. A bypass ratio is greater than about 11.0.

Abstract: An inventive wind turbine device including an air intake with a curved interior surface for accelerating wind speed and an optional conical component to direct the captured wind directly to a portion of the turbine housed in the throat of the device. Annular slits are optionally included in the air intake to reduce back pressures of the introduced fluid stream. The device has an exhaust portion with a curved interior surface for discharging the wind. A method of generating electricity regardless of external wind speed by channeling wind into an air intake of the device, passing the wind over the curved interior surface of the intake thereby accelerating the wind speed through the device, reducing the back pressure in the intake by discharging a portion of wind through annular slits therein, and using the accelerated wind to generate electricity is also encompassed herein.

Abstract: Systems and methods Embodiments for facilitating onboarding of a cooling fluid are disclosed herein. According to one embodiment, a system may include a rotor assembly, a wheel space cavity adjacent to the rotor assembly, and a bucket shank cavity in fluid communication with the wheel space cavity. The system may also include at least one protrusion disposed on the rotor assembly in the wheel space cavity. The at least one protrusion may be configured to direct the cooling fluid radially from the wheel space cavity to the bucket shank cavity to minimize pressure loss in the cooling fluid.

Abstract: A turbine includes an inner casing to which at least a stator vane of a turbine section is mountable, and an outer casing arranged around the inner casing in such a way that an outer cooling channel is formed between the inner casing and the outer casing. The outer cooling channel includes a fluid inlet through which a cooling fluid is injectable from an outer volume of the turbine into the outer cooling channel. The cooling channel includes a fluid outlet such that the cooling fluid is exhausted into an inner volume of the turbine. The fluid inlet is located with respect to the fluid outlet such that the cooling fluid inside the outer cooling channel includes a flow direction which has a component that is orientated in opposite direction with respect to a main flow direction of a working fluid of the turbine.

Abstract: The invention relates to a method of mixing in a discharge conduit, in a turbine engine with two or more flows, of a primary flow and a secondary flow, the two flows emerging in said discharge conduit by two coaxial ducts, separated by an internal housing which has an end downstream relative to the flow direction of the flows, the two coaxial ducts each being defined between an internal wall and an external wall, upstream of the downstream end of the internal housing, and the secondary flow surrounding the primary flow, characterised in that it consists of disposing at least one divergent radial deflection means in primary duct, spaced apart from the walls of said primary duct.

Abstract: Systems and methods for a multiple spool engine turbocharger are described. In one example approach, a multi-spool turbocharger comprises a compressor including a plurality of counter-rotating compressor spools and a turbine including a plurality of counter-rotating turbine spools.

Abstract: A bearing is provided which includes a first set of rolling elements, a second set of rolling elements spaced away from the first set of rollers, a race at least partially enclosing the first and second sets of rolling elements, and a pre-loading element in the race between two outer sections of the race applying pre-load forces to the first and second set of rolling elements. In this way, a simplified bearing structure is achieved while better maintaining pre-load forces.

Abstract: A fan-turbine rotor assembly for a tip turbine engine includes a multiple of fan blades, which include an inducer section, a hollow fan blade section and a diffuser section. The hollow fan blade section defines an airflow passage. The core airflow is turned, spread and split toward opposite ends of the diffuser section by a multiple of internal turning vanes. The airflow streams are then further turned by discharge turning vanes before discharge from a diffuser discharge outlet. Along with turning and splitting the core airflow, the fan blade profile balances the mass of the diffuser section such that the center of mass thereof is over the hollow airfoil section structure.

Abstract: A double casing type pump and a performance adjusting method allow for adjustment of the performance of the pump, especially the head of the pump, without large-scale work or component disassembly. The pump includes impellers fixed to a rotation shaft, an inner casing shrouding the impellers, an outer casing shrouding the inner casing and having a suction opening and a discharge opening. A space is formed between the inner and outer casings that communicates with the discharge opening. A bypass hole connects the space to the working fluid passage in the inner casing and has a throat diameter adjusting member. A plurality of throat diameter adjusting members are prepared in advance, each member having different throat area. One of the throat diameter adjusting members is selected so that the performance of the pump remains within a predetermined range.

Abstract: A gas turbine engine includes a fan section including a fan that is rotatable about an axis. A speed reduction device is connected to the fan. The speed reduction device includes a star drive gear system with a star gear ratio of at least 1.5. A bypass ratio is greater than about 11.0.

Abstract: A machine includes a rotor supported to rotate about a rotational axis and an actuator arranged to act on the rotor and control a position of the rotor about the rotational axis. A bladed turbomachine wheel is coupled to the rotor and has blade tips that pass closely to an adjacent, non-rotating surface. A sensor is adjacent to the turbomachine wheel and arranged to sense the blade tips and output a position signal representative of the position of blade tips relative to the sensor. A controller is coupled to the sensor and the actuator and is adapted to receive the position signal from the sensor and generate and send a control signal to the actuator to control the position of the rotor based on the position signal from the sensor.

Abstract: Smooth, preferably variable-sweep fluid collection device surfaces disposed into opposition with wind, river, surf, ocean or tidal currents generate enhanced velocity fluid flows at length driven into onboard work-extracting disc turbines at advantageous angles of attack. Keyed to shafts turning freely through optionally extendable volutes, disc turbines comprising a dense population of smooth, axially fixed or adjustably spaced discs conducting preferably laminar flow between adjacent elements develop significant torque through boundary layer adhesion and viscous shear-stress between fluid layers. Exhaust of disc turbine throughput into divergent channels drafting into external currents of initially higher than ambient velocity and lower pressure may reduce turbine discharge backpressure, rapidly clear system throughput, and allow normally disadvantageous drag to be utilized to develop greater work generation.

Abstract: A centrifugal pump has alternating impellers and diffusers. One or more vent holes extend through one or more vanes of one or more diffusers. In an upthrust condition, high pressure production fluid from an upper impeller is able to pass through the one or more vent holes, and thereby exert force on the preceding impeller. The force exerted on the preceding impeller offsets the upthrust force acting against the preceding impeller.

Abstract: A wave energy converter for converting energy from a wave motion of a fluid into a different form of energy includes at least one rotor that is coupled to at least one energy converter. The rotor has a rotor base that has two sides with respect to the rotational plane of the rotor. At least one coupling body is attached to each side of the rotor base.

Abstract: A method of controlling plume exhaust heat and/or noise radiation from a turbofan engine assembly having a short nacelle. A mixer duct shell is supported such that a downstream edge of the short nacelle overlays an upstream portion of the mixer duct shell. A first portion of fan exhaust may be routed through the mixer duct shell between its inner surface and an outer surface of a core engine shroud. A second portion of fan exhaust may be routed over an outer surface of the mixer duct shell. At least one of the inner surface and an outer surface of the mixer duct shell may have an acoustic lining including a honeycomb core structure.

Abstract: In one embodiment, a hydraulic blocking rotary actuator including a stator housing having a through bore to position a rotor assembly. A rotor assembly includes an output shaft and at least one rotary piston disposed radially about the output shaft. The rotary piston includes an integral first vane element and an integral second vane element each with peripheral longitudinal faces substantially concentric to the other. A continuous seal groove is disposed in peripheral longitudinal faces and lateral end faces of the rotary pistons. A continuous seal is disposed in the continuous seal groove. The bore through the stator housing includes an interior cavity with surfaces adapted to receive the rotor assembly. With rotation fluid ports blocked the housing cavity is sealed with the continuous piston seal for hydraulic blocking, preventing actuator displacement by external forces. Other embodiments are disclosed.

Abstract: A tip turbine engine according to the present invention includes a plurality of independently variable inlet guide vanes for the fan and/or for the compressor. An actuator is operatively coupled to each of the flaps, such that each actuator can selectively vary the flap of its associated inlet guide vane. In one embodiment, the inlet guide vanes each include a pivotably mounted flap that is variable independently of the flaps of at least some of the other inlet guide vanes. In another embodiment, the inlet guide vanes each include at least one fluid outlet or nozzle directing pressurized air, as controlled by the associated actuator, to control inlet distortion.

Abstract: An example turbomachine geared architecture support assembly includes a subpart having a more compliant portion and a less compliant portion.

Abstract: A secondary flow lobe mixer increases the total-to-static pressure ratio across a Ram Air Turbine (RAT) by developing a localized pressure drop near the discharge of the turbine rotor exhaust. This pressure drop allows for additional power generation for a given free-stream flight condition.

Abstract: A high compression ratio compressor having multiple stages of airfoils to produce the high pressure rations, where the last stage airfoils are cooled by passing cooling air through the airfoils without discharging film cooling air. The cooling air for the airfoils is bled off from an upstream stage of the compressor, passed through the airfoil to provide for the cooling, passed through a heat exchanger to preheat a fuel, where the preheated fuel is passed into the combustor. the cooled cooling air form the heat exchanger can be reintroduced back into the compressor or passed through the turbine to cool last stage airfoils in the turbine.

Abstract: A variable outer air seal support system according to an exemplary aspect of the present disclosure includes, among other things, a case having a plurality of slots, and an extension of a variable outer air seal segment. The extension provides at least one extension aperture. A connector pin is configured to move within the slot to move the variable outer air seal segment from a first position to a second position. The variable outer air seal segment overlaps a circumferentially adjacent variable outer air seal segment more in the first position than in the second position.

Abstract: A device and method for reducing vibration in a compressor are provided. The device for reducing vibration in a compressor may include a compressor controlled to be operated at a target operating velocity after starting; a power supply that supplies power to the compressor; and a controller that controls the power supply so that a magnitude or a phase of the power supplied to the compressor is changed. The controller may control the power supply so that vibration generated in the compressor is offset by an exciting force generated in the compressor within a predetermined time interval multiple times when the compressor starts or when the compressor stops during a target operation velocity operating of the compressor.

Abstract: A system for attenuating sound emissions from an inlet to a flow path for an air inducting machine including an inlet duct structure having inlet and outlet passages. A planar vortex generator is located adjacent to the outlet passage and creates vortices that interact with a specific tonal acoustic frequency emitted from the inlet of the machine to effect formation of a standing wave at the vortex generator. The standing wave has an upstream propagating component that reflects off an acoustic reflector wall to form a reflected component that interferes with the upstream propagating component to attenuate the specific tonal acoustic frequency from the inlet of the machine.

Abstract: An airfoil assembly is disclosed. The airfoil assembly may comprise a series of airfoils such as vanes radially extending between an ID endwall and a substantially concentric OD endwall. The airfoils are circumferentially spaced apart and define a plurality of fluid flow passages between adjacent airfoils. The ID endwall and the OD endwall define contoured regions to optimize fluid flow through the passages. A geometric relationship between the ID endwall contoured regions and the OD endwall contoured regions assures that the throat area generally increases or decreases in the direction of fluid flow.

Abstract: An airfoil includes an airfoil body having a first section and a second section that differ by coefficient of thermal expansion. The second section is arranged in thermomechanical juxtaposition with the first section such that the first section and the second section cooperatively thermomechanically control a profile of the airfoil body responsive to varying thermal conditions.

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan with a plurality of fan blades rotatable about an axis and a shroud and a speed change device in communication with the fan.