Abstract: A system for removing heat from a gas turbine generally includes a plurality of stationary nozzles arranged in an annular array within the gas turbine. Each of the plurality of stationary nozzles may include a radially outer platform and a radially extending cooling passage. The radially extending cooling passage may have an inlet that extends generally axially and circumferentially across a portion of the radially outer platform. A closed loop cooling coil may extend continuously circumferentially around the radially outer platform of two or more of the plurality of stationary nozzles. The closed loop cooling coil may be disposed circumferentially across and outside of the inlet of the radially extending cooling passage of each of the two or more stationary nozzles, and a cooling medium may flow through the cooling coil and out of the gas turbine so as to remove heat from the gas turbine.

Abstract: An electric pump comprising: a rotor, a wet sleeve surrounding the rotor; and a stator surrounding the wet sleeve and the rotor; wherein the rotor and stator have a magnetic air gap of about 2 mm or less.

Abstract: A gas turbine engine includes a fan case radially outwardly of a core compartment. A compressor section is located within an engine core compartment and includes a front mount flange and an aft mount flange. An oil tank is mounted to at least one of the fan case or the front and aft mount flanges. The oil tank has a cooling structure integrated into an outer surface such that the oil tank is subjected to cooling air flow from a plurality of air sources.

Abstract: An outer diameter (OD) hex nut secures a hollow cooling rod to an outer case of an engine. The OD hex nut includes a flange portion and a hollow tube portion. The flange portion includes a central aperture for receiving cooling airflow and a plurality of vernier holes located circumferentially around the flange portion. The hollow tube portion extends from the flange portion and is in fluid communication with the central aperture to receive cooling airflow for distribution to the hollow cooling rod.

Abstract: An impeller radial pump includes a pump chamber with a central suction and with a pump chamber outlet, wherein an impeller is provided in the pump chamber. Radially outside of the impeller, a circular ring shaped and circumferential pump chamber ring section is provided as a part of the pump chamber, wherein the pump chamber ring section essentially has an extension along the axial direction of the pump from the impeller against the suction direction. The pump chamber ring section has a varying width and is configured to be narrower in a compression region in the circulation direction.

Abstract: A turbine end intake structure for a turbocharger includes a turbine housing, a turbine having multiple blades and located in a turbine shell, and thermal insulation located between the turbine end of the turbocharger and another part. A flow-guiding channel for engine exhaust gases is provided on the turbine housing in communication with the interior of the turbine housing. An inner surface of the turbine housing matching peripheral edges of the blades is a cylindrical surface coaxial with the turbine, while the shape of the peripheral edges of the blades follows the cylindrical surface. Angle-cut portions are provided on the blades at positions corresponding to an intake port of the flow-guiding channel. The thermal insulation has an outwardly extending flow-guiding part, and a flow-guiding path for engine exhaust gases formed by the flow-guiding channel and the flow-guiding part is perpendicular to the angle-cut portions of the blades.

Abstract: A turbine housing of the exhaust turbocharger, having an inlet, which is adjoined by a spiral; having an outlet; and having a coolant arrangement; wherein the coolant arrangement has a plurality of coolant ducts, which branch off from an inlet duct section and open into an outlet duct section.

Abstract: A stationary component includes an outer ring including a first plenum, a first passageway, and a second plenum defined therein. The first passageway extends between the first plenum and the second plenum. An airfoil is disposed radially inward of the outer ring. The airfoil includes a second passageway defined therein. The second passageway is coupled in flow communication with the second plenum.

Abstract: The present invention relates to an assembly comprising a duct, preferably a turbine duct, and at least one segment formed of at least two rigid shells, each shell comprising at least one fixing orifice for fixing to the duct and at least one fixing element at least one boss per shell which boss is fixed to the duct and against which boss the shell rests, such that at least one orifice and one boss face one another, and that the fixing element passes through the orifice facing the boss and is fixed to the boss.

Abstract: The invention relates to a housing 1 of an electrical compressor for a refrigerant circuit, comprising a wall 2 suitable for delimiting a first volume of the compressor in which the refrigerant circulates relative to a second volume of the compressor into which a control device of the electric motor extends, a first face of the wall 2 facing the second volume being configured to receive the control device while a second face 4 of the wall 2 facing the first volume comprises a heat dissipation means 5, characterized in that the heat dissipation means 5 takes the form of a plurality of tubular elements 6 originating from the second face 4.

Abstract: A centrifugal fan includes a casing and an impeller received in the casing. The casing defines an air outlet at one side thereof. An air channel is defined in the casing between a sidewall of the casing and outermost free ends of blades of the impeller. The air channel has an upstream end and a downstream end along a rotation direction of the impeller. A plurality of air guide plates is formed in the casing and disposed at a junction between the downstream end of the air channel and an area of the air outlet directly communicating with the downstream end of the air channel. The air guide plates are structured and arranged in a streamlined manner and pattern with respect to air flowing from the downstream end of the air channel towards the air outlet.

Abstract: A mounting system for a fire detection system for a turbofan engine propulsion system is provided to mount fire detection sensors on the inner fixed structure (IFS) of the nacelle. The mounting system mounts to an inner, engine facing surface of the IFS. Two IFS halves cooperate to form a substantially enclosed space around an engine core. The mounting system includes part of a fastening system mounted to the IFS, and an orientation clip mounted to a thermal blanket. Brackets for mounting the fire detection system sensing wires are positioned on the orientation clip, and the fastening system fixes the bracket to the IFS and traps the thermal blanket therebetween.

Abstract: An annular stator assembly includes a plurality of stator segments. Each stator segment includes a plurality of laminates having magnetic permeable properties; a plurality of thermally conductive laminates positioned between the permeable laminates; and a cooling pipe extending through the laminates for transferring heat from the laminates to coolant flowing through the cooling pipe. The stator segments are constructed independently. Coils are wound on each segment. The stator segments with the wound coils are subsequently arranged to form the annular stator assembly.

Abstract: A component wall in a turbine engine includes a substrate and at least one cooling passage that extends through the substrate for delivering cooling fluid from a chamber associated with an inner surface of the substrate to an outer surface of the substrate. Each cooling passage is divided into at least two branches that receive cooling fluid from an entrance portion of the cooling passage that is in communication with the chamber. The branches each include an intermediate portion that extends transversely from the entrance portion and that receives cooling fluid from the entrance portion, and an exit portion that extends transversely from the respective intermediate portion. The exit portions receive the cooling fluid from the intermediate portions and deliver the cooling fluid out of the respective branch through exit portion outlets.

Abstract: The compressor blade root heating system may be formed from one or more induction heaters formed from one or more induction coils positioned in close proximity to a root of a compressor blade. In one embodiment, the induction heater may be coupled to a static casing component positioned immediately upstream of a first row of compressor blades on a rotor assembly such that the induction heater is stationary during turbine engine operation. The induction heater causes eddy current formation, which heats the row one compressor blades. This heating increases the fracture toughness of the material forming the rotor and compressor blades, thereby increasing the mechanical life cycle.

Abstract: A pineapple pump is provided. The pineapple pump includes a rotor chamber and a rotor. The rotor chamber may include a plurality of cooling columns for thermal management. The rotor is rotatably disposed in the rotor chamber and the cooling columns are located at a fluid outlet of the rotor. The rotor has a rotary shaft to deliver a tangential torque. When the rotor rotates with the rotary shaft to guide a fluid, the fluid has a radial displacement perpendicular to the tangential torque of the rotor, thereby de-coupling the tangential torque and a pressure gradient of the fluid caused by the rotor.

Abstract: A turbocharger including a sealing device for prevention of fluid leakage from high to low pressure sides through a radially extending annular gap formed between a shroud and a shroud-confronting portion which constitute the turbocharger is provided. The sealing device includes a frustoconical disc spring seal member arranged in a pressed manner in the gap between the shroud and the shroud-confronting portion. Accordingly, fluid leakage from high to low pressure sides through an annular gap formed between constructional members of a turbocharger and extending radially of a turbine shaft may be prevented.

Abstract: A thermal management system for a gas turbine engine includes a high pressure compressor rotor having a plurality of disks and a shaft; at least one forward cavity formed between a rim of at least one of the disks and the shaft and at least one aft cavity formed between a rim of at least one other of the disks and the shaft; a first flow of cooling air in the at least one forward cavity; and a second flow of cooling air in the at least one aft cavity.

Abstract: A rotor and wheel cooling assembly for a steam turbine system includes a rotor operably connected to a plurality of rotating buckets. Also included is a flow diverting member having an inner radius and operably coupled to at least one nozzle stage, wherein the flow diverting member directs flow in at least one direction within the steam turbine system. Further included is a cooling flow dispenser disposed radially outwardly of a portion of the rotor and having at least one aperture, wherein the cooling flow dispenser is operably coupled to the inner radius of the flow diverting member.

Abstract: A turbocharger with a variable nozzle includes a pin mounted in the center housing and extending axially therefrom and engaged in a hole in the nozzle ring to orient the nozzle ring rotationally relative to the center housing. A portion of a length of the pin has a substantially greater compliance than the remainder of the length such that the pin has a flexible tip that engages the hole in the nozzle ring. The flexible tip reduces constraint of thermal deformation of the nozzle ring. The pin portion of greater compliance can be a section of the tube that is slit and expanded. The turbocharger can also include a one-piece locator and heat shield having a locating portion abutting the center housing and the nozzle ring for radially locating the nozzle ring relative to the center housing, and having a shield portion shielding the center housing from hot exhaust gas.

Abstract: An assembly of a rotor and case for a gas turbine engine comprises a rotor having a plurality of circumferential blades each with a blade tip. A case comprises a structural layer forming an annular body receiving therein the rotor, with a tip clearance being defined between the blade tips and the annular body, and a heating layer connected to the at least one structural layer. The heating layer has a resistivity to heat the structural layer when an electric current passes through the heating layer. An electric power source supplies current to the heating layer, the heating layer configured to in use change the diameter of the annular body to adjust the tip clearance. A method for adjusting a tip clearance between blade tips of a rotor and inner surface of a case in a gas turbine engine is also provided.

Abstract: A system for recirculating a hot gas flowing through a gas turbine generally includes a transition piece having a downstream surface, a stationary nozzle having a leading edge surface adjacent to the transition piece downstream surface, a gap defined between the transition piece downstream surface and the stationary nozzle leading edge surface, and a projection having an inner arcuate surface radially separated from an outer surface. The projection generally extends from the stationary nozzle leading edge surface towards the transition piece downstream surface and at least partially decreases the gap. A seal extends across the gap and may be in contact with the transition piece and the stationary nozzle leading edge surface. A recirculation zone may be at least partially defined between the projection inner arcuate surface, the stationary nozzle leading edge surface and the transition piece downstream surface.

Abstract: An engine includes a duct containing a flow of cool air and a pump system having an impeller with an inlet for receiving air from the duct and an outlet for discharging air into a discharge manifold. The discharge manifold containing at least one heat exchanger which forms part of a thermal management system.

Abstract: A heat exchange system includes a first flow passage and a second flow passage. The heat exchange system is configured to transfer heat between a first fluid flowing through the first flow passage and a second fluid flowing through the second flow passage. The first flow passage includes an inlet header, a plurality of tubes, and an outlet header. The inlet header includes a plurality of header-tube transition portions configured to allow the first fluid to flow from the inlet header and into the tubes, the plurality of header-tube transition portions each including a smoothly curved inlet portion and a tapered tube connection portion.

Abstract: According to an aspect of the invention, a method for ventilating a turbine compartment is provided, the method comprising directing an air flow from an air intake to a first air conduit, transferring a first heat between the air flow and a first fluid within a heat exchange apparatus and pumping the first fluid through a fluid circuit in fluid communication with the heat exchange apparatus, wherein a portion of the fluid circuit is located underground. The method further includes transferring a second heat between the first fluid and a surrounding ground and directing a conditioned air flow from the heat exchange apparatus to a turbine compartment via a second air conduit.

Abstract: A transition piece aft frame assembly is provided, and includes a transition piece aft frame and a heat shield. The transition piece aft frame has an aft face. At least a portion of the aft face is exposed to an exhaust gas stream. The heat shield is connected to the transition piece aft frame. The heat shield is oriented to generally deflect the exhaust gas stream away from the aft face of the transition piece aft frame.

Abstract: A leading edge structure for an air inlet of an aircraft nacelle includes a leading edge and an inner partition defining a longitudinal compartment that is located inside the leading edge and accommodates a de-icing and/or anti-icing mat. The leading edge structure includes a multi-axial composite structure placed on top of a heating element for anti-icing and/or de-icing.

Abstract: An example turbomachine hot-section component protrusion extends away from a base surface of a hot-section component along a longitudinal axis. A radial cross-section of the protrusion has a profile that is non-circular.

Abstract: A thermal management system for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a heat exchanger and a valve that controls an amount of a first fluid that is communicated through the heat exchanger A first sensor senses a first characteristic of a second fluid that is communicated through the heat exchanger to exchange heat with the first fluid and a second sensor senses a second characteristic of the second fluid. A positioning of the valve is based on at least one of the first characteristic and the second characteristic.

Abstract: A turbine shell is provided, and includes a body portion and at least one plate. The body portion has a forward portion and an aft portion. The plate is located between the forward portion and the aft portion. The plate is part of a plate frame heat exchanger, which is part of the body portion of the turbine shell.

Abstract: A turbocharger heat shield is disposed around a turbocharger turbine housing and comprises first and second heat shield members each having a wall structure that is generally semi-cylindrical in shape. The heat shield members are removably attached with one and include axially opposed openings, and a radial opening, to accommodate passage of other turbocharger components therethrough. A third heat shield member may be included to cover a further element of the turbocharger. One or more tabs project from an edge of the first or second heat shield member to register with an adjacent edge of the other member to facilitate alignment, engagement and/or attachment between the two members. An insulating material can be interposed between the heat shield and the turbocharger housing and, in a preferred embodiment, is attached to the heat shield.

Abstract: A turbine exhaust diffuser system includes a plurality of manways. The plurality of manways each extend between an outer wall of the turbine exhaust diffuser system and an interior access tunnel of the turbine exhaust diffuser system. The plurality of manways extend between the outer wall and the access tunnel at an angle that is not perpendicular to a central axis of the turbine exhaust diffuser system.

Abstract: A turbo compressor is provided that has first, second and third stage compressor blades rotated by a large gear shaft via an acceleration device, and includes a cast integral casing (1) which forms an acceleration unit cover housing the acceleration device, compression unit covers housing the compressor blades, and first, second and third stage cooler chambers (11a, 12a, 13a) which are arranged in parallel at a lower portion thereof, which communicate with the compressor unit covers by fluid passages, and into which first, second and third stage coolers are inserted from the side thereof. An oil tank (21) is integrally formed with the cast integral casing (1) so as to run along an insertion-directional innermost side of the coolers of the parallel-arranged first, second and third stage cooler chambers (11a, 12a, 13a).

Abstract: An apparatus (20) has a centrifugal compressor (24), a positive displacement compressor (26), a first heat exchanger (32), and a second heat exchanger (36). A plurality of valves (70, 72, 74) are positioned to provide operation in at least two modes. In a first mode, refrigerant is compressed in the positive displacement compressor and the centrifugal compressor at least partially in parallel. In a second mode, refrigerant is compressed in the positive displacement compressor and the centrifugal compressor is offline. In a third mode, refrigerant is compressed in the positive displacement compressor and the centrifugal compressor at least partially in series.

Abstract: A thermal barrier/cooling system for controlling a temperature of an outer case of a gas turbine engine. The thermal barrier/cooling system includes an internal insulating layer supported on an inner case surface, the internal insulating layer extending circumferentially along the inner case surface and providing a thermal resistance to radiated energy from structure located radially inwardly from the outer case. The thermal barrier/cooling system further includes a convective cooling channel defined by a panel structure located in radially spaced relation to an outer case surface of the outer case and extending around the circumference of the outer case surface. The convective cooling channel forms a flow path for an ambient air flow cooling the outer case surface.

Abstract: A blower housing of a hydrogen recirculation device for a fuel cell vehicle includes a plurality of cooling pins installed on a perimeter of a housing body installed in a fuel processing system of the recirculation device. The cooling pins are arranged in parallel with air flow, thereby reducing a temperature deviation and the highest temperature point.

Abstract: An exhaust gas housing for a gas turbine, in which an annular gas passage, through which exhaust gas discharges from the gas turbine to the outside, is formed by a concentric inner casing and an outer casing which concentrically encompasses the inner casing at a distance, wherein the inner casing and the outer casing are interconnected by a plurality of radial struts which extend through the gas passage and have in each case a leading edge and a trailing edge with regard to the exhaust gas flowing through the gas passage, and wherein the struts, the outer casing and the inner casing are equipped in each case with a heat-resistant lining towards the gas passage, wherein the lining of the struts is at least partially mechanically decoupled from the lining of the inner casing and/or of the outer casing for reducing thermal stresses on the periphery of the struts.

Abstract: A gas turbine article includes a substrate and a thermally insulating topcoat disposed on a surface of the substrate. The surface of the substrate includes a surface pattern defining first surface regions and second surface regions. The first surface regions include incubation sites that are favorable for deposition of the thermally insulating topcoat and the second surface regions are less favorable for deposition of the topcoat. The topcoat includes segmented portions that are separated by faults extending through the topcoat from the second regions.

Abstract: The invention relates to an oil management system for a compressor in a refrigeration system comprising: an oil temperature sensor; a heater arranged to heat oil in a crank case of the compressor; and a controller operatively associated with the temperature sensor and the heater, the controller arranged to control operation of the heater on the basis of ambient air temperature and oil temperature to maintain the oil temperature within a range Tmax?R?Tmin where Tmax>Tmin.

Abstract: An insulator includes a main body, a latching portion, and a slot. The main body covers a portion of a stator core around which a coil is wound to insulate the stator core from the coil. The latching portion is disposed at an end of a portion of the main body around which the coil is wound to latch the coil onto the main body. The slot is formed so as to expose the coil at a portion of the latching portion on a side where cooling oil for cooling the coil is supplied to the coil.

Abstract: An embodiment of the present invention takes the form of an IBH system that has a single conduit, which is positioned close to a downstream end of a silencer section. This arrangement may reduce the overall pressure drop associated with the inlet system. This arrangement may also promote a substantially uniform mixing between the cooler ambient air and the warmer heated air.

Abstract: An embodiment of the present invention takes the form of an IBH system that has two conduits, which are positioned close to a downstream end of a silencer section. This arrangement may reduce the overall pressure drop associated with the inlet system. This arrangement may also promote a substantially uniform mixing between the cooler ambient air and the warmer heated air.

Abstract: A self-adjusting device (25) for controlling the clearance (C), especially in the radial direction, between rotating and stationary components (21, 23) of a thermally loaded turbo machine, changes clearance (C) in a linear and/or non-linear way during transition of the machine between standstill and steady-state operation. Simple and effective control can be achieved, even in the case of a nonlinear variation of the clearance during transitional operation, by the self-adjusting device (25) including at least two different driving elements (A, B) to move the rotating and fixed components (21, 23) relative to each other in order to change the clearance (C) between them, and by the different driving elements (A, B) being configured to be activated at different times during the transition of the machine.

Abstract: A fan housing for a ram air fan includes an outer portion to connect the fan housing to ram air fan components; a tubular portion; a plurality of struts connecting the outer portion and the tubular portion; and a central disc portion inside of the tubular portion. The central disc portion comprises six cooling slots around an outer circumference.

Abstract: A power electronic device with cooling arrangement includes a housing that accommodates power electronic components. At least two adjacent axial fans are connected to the housing for inducing an airflow from outside into the housing in order to cool the power electronic components. Furthermore, the device can include a separating wall that extends outside the housing from between the at least two adjacent axial fans in order to reduce noise caused by the fans. Such a cooling arrangement can provide a power electronic device with effective cooling in compact size and also having an acceptable level of noise.

Abstract: A tungsten bronze structured ceramic material as a thermal barrier coating is described wherein the tungsten bronze structured ceramic coating material has the formula AO—BvOw—CyOz where O stands for Oxygen, A stands for a 2+ or a 1+ cation, B stands for a 2+ or 3+ cation and C stands for a 4+ or a 5+ cation. The thermal barrier coating may be applied for gas turbine components.

Abstract: A screw compressor includes a compressor body and a shell and tube heat exchanger for cooling of a compressed air discharged from the compressor body. A tube provided in the shell and tube heat exchanger has both ends each having a cylindrical shape, and a center part formed as a multi-lobate tube to have a corrugated shape with crest portions and trough portions alternately arranged in a circumferential direction. The multi-lobate tube provided at the center part of the tube is formed to have a multi-lobate spiral shape through twisting. Size reduction of the shell and tube heat exchanger may make the screw compressor compact as a whole.

Abstract: A clamp suitable for use in an anti-icing system of a gas turbine engine is provided is disclosed. The clamp has a clasping portion for clasping a heating element. Two resilient arms extend from the clasping portion to a substantially rigid outer collar. Translational movement of the clasping portion, which may be created by radial expansion of an annular heating element being clasped thereby, can be accommodated by the clamp by elastic deformation of the resilient arms. This allows radial expansion of the heating element to be accommodated without relative rotation between the clasping portion and the heating element.

Abstract: Provided is a wind power generator that reduces the amount of heat input into a nacelle from the outside of the nacelle due to the solar radiation, and that improves the heat dissipation performance from the inside of the nacelle to the outside air. In a wind power generator in which a driving mechanism and power generation mechanism that are connected with a rotor head, to which wind-turbine blades are attached, are accommodated and installed in a nacelle, an outer wall surface of the nacelle is provided with, on at least a part of the wall surface where no direct sunlight is radiated, a heat-dissipation-resistance reducing portion that uses a member having a higher thermal conductivity than that of a peripheral wall member.

Abstract: A thermal control system for a turbine casing (2) mounted radially outwardly of and circumferentially surrounding blade tips of the turbine blades, the system comprising: one or more circumferential chamber walls (6), each disposed around the casing (2), each to form a circumferential flow chamber (7) radially outward of said surface of the turbine casing (2), each to form a circumferential gap (12) between the circumferential chamber wall (6) concerned and said surface of the turbine casing (2), and the one or more circumferential chamber walls (6) define at least one opening (9) on the radially inward side of the chamber (7) adjacent the surface of the turbine casing (2) such that a thermal fluid injected into the flow chamber (7) concerned may leak out through the circumferential gap (12) via the opening (9), and means to induce circumferential flow on the surface of the casing (2) bounded by the circumferential flow chamber (7) comprising one or more ducts (8) radially outwardly connected to the or each c