Abstract: In accordance with one aspect of the present disclosure, a turbocharger includes a compressor having a compressor wheel, a turbine provided within a housing, and an exhaust gas recirculation (EGR) flow path. The EGR flow path includes a first fluid connection in the housing and located in proximity to the turbine, a second fluid connection located in proximity to a trailing edge of the compressor wheel, an EGR control valve disposed between the first fluid connection and the second fluid connection, the EGR control valve configured to selectively operate the turbocharger in a low-heat mode having an EGR up to 50% and an operational mode having an EGR rate typically less than 35%.

Abstract: A stand-on blower is provided that allows for fully powered nozzle angle adjustment. The blower may deliver an airflow for pneumatic cleanup tasks in different directions, including horizontal or left-right and vertical or up-down direction variability of the airflow. Position or angle of the blower's nozzle may be automatically reversed or driven to a rotational or angle limit upon demand.

Abstract: This present disclosure relates generally to propulsion systems and, more particularly, to adaptive ducted fan propulsion systems for use with aircraft such as unmanned aerial vehicles. Embodiments of ADF systems in accordance with the present disclosure feature automatic, fast operation, increase the intake section of the air mass fed to a propeller, and can increase thrust by 35%-40% as compared to existing ducted fans.

Abstract: A turbine rotor for aircraft turbine engine includes a mobile disc supporting mobile blades, the mobile disc including a plurality of slots into which are inserted the roots of the mobile blades a passage being formed between the bottom of the slots and the roots of the mobile blades inserted into the slots. The rotor also includes a circulation channel configured to allow circulation of fluid, the circulation channel including the passage, and a calibration device configured to allow the flow of a first fluid flow rate in the circulation channel when the temperature within the channel is less than a predetermined temperature threshold value, and to change state so as to allow the flow of a second fluid flow rate, greater than the first flow rate, in the channel, when the temperature within the channel is greater than or equal to said predetermined threshold value.

Abstract: A turbine for a turbo-machine is proposed in which, at a gas inlet for a turbine wheel, vanes extend from a nozzle ring though slots in a shroud. The nozzle ring and shroud are relatively rotatable about a rotational axis of the turbine by at least 0.1 degrees. In use, the nozzle ring and shroud are relatively rotated to bring one side of the vane into close contact with one surface of the slot, to inhibit leakage of gas between the vane and the slot surface. For this purpose the respective surfaces of the nozzle and slot can be configured to closely conform to each other. If there is differential thermal expansion of the shroud and nozzle ring, the nozzle ring and shroud can relatively rotate, to withdraw the vane from the edge of the slot to relieve the pressure between them.

Abstract: A turbocharger includes a turbine housing. The turbine housing includes a turbine inlet wall defining an inlet passage, an exducer shroud wall defining an exducer interior, a turbine outlet wall defining an outlet passage, a wastegate port wall defining a wastegate channel, and a bushing wall coupled to the wastegate port wall and defining a bushing boss extending along a bushing axis, and a valve seat disposed about the wastegate channel. The turbocharger also includes a wastegate assembly. The wastegate assembly includes a valve element engageable with the valve seat. The wastegate port wall is disposed outside of the exducer interior such that the wastegate port wall and the bushing wall are configured to be thermally decoupled from the turbine inlet wall and such that relative displacement between the valve seat and the bushing axis is reduced during operation of the turbocharger.

Abstract: A bearing structure includes: a rotation member including a plurality of extended portions extending radially outward from a shaft portion and arranged separated away from each other in an axial direction of the shaft portion; and a bearing member in which a counterface surface facing one of the plurality of extended portions in the axial direction is included in one or a plurality of main bodies.

Abstract: A valve device includes a valve casing 21, an intermediate rod portion 29, and an intermediate actuator unit 30. In the valve casing 21, a rod insertion hole into which the intermediate rod portion 29 can be inserted is formed. The intermediate actuator unit 30 includes a hydraulic cylinder that causes a piston rod portion to advance and retreat in a direction orthogonal to a second center axis direction D2. The hydraulic cylinder includes a rod guide portion that guides movement of the piston rod portion. A gap between an inner circumferential surface of the rod insertion hole and an outer circumferential surface of the intermediate rod portion 29 is formed to be wider than a gap between an inner circumferential surface of the rod guide portion and an outer circumferential surface of the piston rod portion.

Abstract: A turbine for a turbo-machine is proposed in which, at a gas inlet for a turbine wheel, vanes extend from a nozzle ring though slots in a shroud. The nozzle ring and shroud are relatively rotatable about a rotational axis of the turbine by at least 0.1 degrees. In use, the nozzle ring and shroud are relatively rotated to bring one side of the vane into close contact with one surface of the slot, to inhibit leakage of gas between the vane and the slot surface. For this purpose the respective surfaces of the nozzle and slot can be configured to closely conform to each other. If there is differential thermal expansion of the shroud and nozzle ring, the nozzle ring and shroud can relatively rotate, to withdraw the vane from the edge of the slot to relieve the pressure between them.

Abstract: A turbine bypass valve comprising: a casing defining first and second casing ports; and a valve cartridge mounted to the casing; wherein the valve cartridge comprises: first and second valve ports; and a valve member, the valve member being movable between a first position in which there is a flow path between the first and second valve ports, and a second position in which the valve member substantially blocks said flow path between the first and second valve ports; and wherein the valve cartridge is mounted to the casing such that the first valve port is aligned with the first casing port, and the second valve port is aligned with the second casing port.

Abstract: A turbocharger control valve having an extended feedback cap for altering the performance of a variable geometry turbocharger delivering boost pressure to an engine, the extended feedback cap has an increased cap length which displaces a spool within the turbocharger control valve to alter hydraulic fluid flow through the turbocharger control valve, causing the turbocharger to delay opening a variable inlet to release exhaust pressure, also causing the turbocharger to preemptively close the variable inlet to mitigate loss of exhaust back pressure and boost pressure without a command from a turbocharger control module.

Abstract: A turbocharger includes a turbine housing, an annular metal plate, and a scroll passage defining plate. The metal plate defines a connecting passage in the turbine housing. The connecting passage connects a turbine chamber and a turbine scroll passage to each other. The scroll passage defining plate includes a passage defining portion that defines the turbine scroll passage and an inner circumferential edge portion that extends from the inner circumferential edge portion of the passage defining portion and along the metal plate. The scroll passage defining plate has an inner circumferential edge that is fixed between the turbine housing and the metal plate. The scroll passage defining plate is arranged in the turbine housing such that the outer circumferential edge portion of the passage defining portion is movable relative to the turbine housing.

Abstract: A turbocharger includes a bearing housing, a turbine housing, a turbine chamber formed in the turbine housing, a turbine impeller rotating integrally with the impeller shaft by the exhaust gas flowing into the turbine chamber, a turbine scroll passage formed in the turbine housing, a communication passage, and a bearing housing side plate made of sheet metal and forming wall surfaces of the turbine scroll passage and the communication passage on the bearing housing side. The bearing housing side plate has an inner peripheral part of the bearing housing side plate is a stationary part relative to the bearing housing, and an outer peripheral end portion of the bearing housing side plate is a free end. The bearing housing side plate has an outer peripheral side surface of the bearing housing side plate is spaced from a first facing member that faces the outer peripheral wall side surface.

Abstract: A centrifugal blower assembly comprises a scroll wall and a pair of opposing sidewalls. The scroll wall is positioned between the pair of opposing sidewalls such that the scroll wall and opposing sidewalls together define a blower chamber and a blower outlet. The blower outlet defines a blower outlet area. An adjustable outlet plate is pivotably coupled to the pair of opposing sidewalls such that the adjustable outlet plate is moveable between a first position to define a first blower outlet area and a second position to define a second blower outlet area.

Abstract: A valve device for installing in a cylinder of a turbine casing includes a plurality of valves arranged within a casing of a pressure receiving steam chamber, a plurality of steam channels fluidly communicating between the plurality of valves and the cylinder of the turbine casing, and a pressure receiving plate configured to receive pressure of steam in the pressure receiving steam chamber to hold at least two valve seats of the plurality of valves on the casing of the pressure receiving steam chamber. The pressure receiving plate has locking holes corresponding to the at least two valve seats, and the at least two valve seats are fully circumferentially locked by inner peripheral edges of the locking holes.

Abstract: When A is a flow-path cross-sectional area of the scroll part, and R is a distance from a centroid of a flow-path cross-section of the scroll part to a rotational axis of the turbine rotor blade, the scroll part is configured so that a first graph, having a horizontal axis representing an angular position ? in a circumferential direction of the scroll part and a vertical axis representing ratio A/R of the flow-path cross-sectional area A to the distance R, at least partially has a concave distribution. The scroll part includes a first section belonging to a first angular range in the circumferential direction, and a second section belonging to a second angular range downstream of the first angular range in the circumferential direction and having a smaller throat width than a throat width of the first section in an axial direction of the turbine rotor blade.

Abstract: A multiple impeller type power generation turbine includes a body, at least a high pressure water tank, and two impellers, two first jet assemblies and two low pressure steam chambers installed in the body. The high pressure water tank is provided for containing a working fluid coming from a fluid source. The two impellers are synchronously and rotably linked with the power generator. The two first jet assemblies is provided for ejecting the working fluid contained in the high pressure water tank to fluid inlet ends of the two impellers and guiding the working fluid from the fluid outlet ends to the two low pressure steam chambers to drive the power generator to generate electric power, so s to improve the power generation efficiency and modularization and the convenience of installation and maintenance.

Abstract: A fixing device fixes a relative position in a rotational direction of an outer member and an inner member of a stationary body of the rotary machine, and includes: a radial pin that is inserted into a through hole passing through the outer member in a radial direction of a rotary machine and having a stepped portion formed therein to have a larger diameter at a portion on an outer side in the radial direction of the rotary machine than at a portion on an inner side in the radial direction, that has a part on the inner side in the radial direction of the rotary machine to be inserted into a concave portion of the inner member, and that has a flange portion on the outer side in the radial direction of the rotary machine.

Abstract: A pin insertion hole is formed in an outer member, and a pin groove is formed in an inner member. A positioning device includes a pin entering the pin insertion hole and the pin groove, and a groove contact member coming in contact with a groove side surface of the pin groove. In one member of the pin and the groove contact member, a position restriction concave portion recessed in a direction away from the other member is formed in a portion facing the other member. In the other member, a claw portion entering the position restriction concave portion and coming into contact with the position restriction concave portion is formed as a portion of the other member is plastically deformed.

Abstract: A variable geometry turbine having a turbine wheel, an inlet passageway, a movable wall member being moveable axially to vary the width of the inlet passageway, an annular seal being mounted to the movable wall member or an adjacent housing member to provide a seal between adjacent surfaces of the movable wall member and housing member respectively, wherein a bypass passage is provided in the other of said movable wall member or housing member, extending from an inlet bypass port to an outlet bypass port, said ports being spaced from each other and provided in said adjacent surface of said other of the movable wall member or housing member, arranged such that as the movable wall member moves axially, the annular seal moves axially relative to the ports to vary the flow that may pass from a region of the cavity inboard of the seal, through the bypass passage.

Abstract: A centrifugal compressor for a turbocharger includes an inlet-adjustment mechanism operable to move between an open position and a closed position. The inlet-adjustment mechanism includes a plurality of blades disposed about the compressor air inlet and located within an annular space within the air inlet wall. The blades are pivotable about respective pivot points such that the blades extend radially inward from the annular space into the air inlet when the blades are in the closed position so as to form an orifice of reduced diameter relative to a nominal diameter of the inlet. The blades include lever arms that engage the outer periphery of a rotatable unison ring that is linked to a linear actuator for rotating the unison ring so as to pivot the blades.

Abstract: A gas turbine engine includes a stator stage arranged in a core flow path that includes a vane that is configured to be retractable from the core flow path during engine operation.

Abstract: A casing for a radial turbine in an exhaust gas turbocharger for a motor vehicle includes a gas duct having an inlet section and an adjoining spiral section, between which a casing tab is arranged. The spiral section features a radially inner turbine inlet, the axial width of which in the region of the casing tab circumferentially decreases toward an end face of the casing tab in a circumferential section. An end face of the casing tab is inclined relative to a rotational axis of the radial turbine in an axial section.

Abstract: A turbocharger turbine (2) includes a wastegate subassembly (50) that includes a mounting plate (51) having a bore (55) therethrough, a valve shaft (60) disposed in the bore (55), and a wastegate valve (30) including a valve body (31) and a valve arm (36) that secures the valve body (31) to an end of the valve shaft (60). The wastegate subassembly (50) is preassembled prior to assembly with the turbocharger (1), and is detachably secured to an outer surface of the turbine exhaust gas inlet (10) such that valve body (31) is positioned to control exhaust gas flow through a bypass port (13) that extends between the exhaust gas inlet (10) and an exhaust gas outlet (12), and bypasses the turbine wheel (16).

Abstract: A stator wheel, located between a pump and a turbine of a torque converter, includes: a first annular portion configured to be rotatable about a center of rotation; a second annular portion away from the first annular portion in a radial direction of the first annular portion; and blades provided at intervals in a circumferential direction of the first annular portion, extending between the first and second annular portions in the radial direction of the first annular portion, extending toward one side in the circumferential direction as it goes in an axial direction of a rotational shaft, being formed integrally with the first and second annular portions, and including a first surface provided on one side in the circumferential direction and a second surface located on an opposite side from the first surface in the circumferential direction configured to receive pressure from the operating fluid flowing from the turbine.

Abstract: A turbocharger (10) for an internal combustion engine includes a symmetric twin-volute turbine housing (12) having first and second volutes (16, 18). A turbine wheel (22) is disposed within the symmetric twin-volute turbine housing (12) for rotation about a turbocharger axis (R1). A nozzle ring (42, 58) is fixedly secured to the symmetric twin-volute turbine housing (12). The nozzle ring (42, 58) includes a plurality of fixed vanes (44, 62, 66) disposed circumferentially around the turbocharger axis (R1). The plurality of fixed vanes (44, 62, 66) form nozzle passages leading from at least one of the first and second volutes (16, 18) to the turbine wheel (22) for directing exhaust gas against the turbine wheel (22) at an optimum angle.

Abstract: Disclosed is an austenitic stainless steel alloy that includes, by weight, about 22% to about 28% chromium, about 3.5% to about 6.5% nickel, about 1% to about 6% manganese, about 0.5% to about 2.5% silicon, about 0.5% to about 1.5% tungsten, about 0.2% to about 0.8% molybdenum, about 0.2% to about 0.8% niobium, about 0.3% to about 0.6% carbon, about 0.2% to about 0.8% nitrogen, and a balance of iron. The alloy is suitable for use in turbocharger turbine housing applications for temperature up to about 1020° C.

Abstract: Methods and systems for adjusting a branch communication and wastegate valve in a dual scroll turbocharger system are provided. In one example, a method may include adjusting the branch communication and wastegate valve in a passage connecting a first scroll, a second scroll, and a wastegate passage may control an amount of exhaust flow to a turbine during certain engine operating conditions.

Abstract: A steam valve control device of this embodiment controls a steam valve. The steam valve has: an upper cover in whose through hole a bush is installed; and a valve rod which is installed so as to penetrate through the through hole of the upper cover via the bush. The valve rod has a contact surface which is formed so as to come into mechanical contact with the bush when the steam valve is opened to a maximum opening degree. The steam valve control device has a control part. When a governor free operation is performed, the control part controls the steam valve by setting a limited opening degree limited to be smaller than the maximum opening degree as an upper limit. When a load limiter operation is performed, the control part controls the steam valve by setting the maximum opening degree as the upper limit.

Abstract: A turbocharger for an internal combustion engine includes a rotating assembly having a turbine wheel disposed inside a turbine housing and a compressor wheel disposed inside a compressor cover. The turbine housing defines a turbine outlet cavity, a turbine housing inlet, and a turbine housing outlet. The turbine housing inlet is configured to channel engine post-combustion gases to the turbine wheel and the turbine housing outlet is configured to exhaust the gases aft of the turbine wheel. A diffuser arranged inside the turbine outlet cavity is configured to channel the post-combustion gases aft of the turbine wheel and out to the turbine housing outlet, without discharging into the turbine outlet cavity.

Abstract: Disclosed is an austenitic stainless steel alloy that includes, by weight, about 22% to about 28% chromium, about 3.5% to about 6.5% nickel, about 1% to about 6% manganese, about 0.5% to about 2.5% silicon, about 0.3% to about 0.6% carbon, about 0.2% to about 0.8% niobium, about 0.2% to about 0.8% nitrogen, and a balance of iron. Molybdenum and tungsten are excluded. The alloy is suitable for use in turbocharger turbine housing applications for temperature up to about 980° C.

Abstract: A turbine engine including a stator including variable-pitch vanes that are controlled stage by stage. An actuator ring connected by crank-arms to the variable-pitch vanes is coupled to at least one adjacent specific drive unit in a general form of an actuator.

Abstract: A supercharged internal combustion engine, comprising a high-pressure turbine connected to a channel of a low-pressure turbine and a bypass line, branching from upstream the high-pressure turbine, connectable to the channels of the low-pressure turbine via a control element positioned within the bypass line, is provided. Adjusting the control element fluidly connects each of the channels of the low-pressure turbine to the bypass line responsive to the exhaust-gas flow rate to optimize the performance of the engine.

Abstract: Embodiments of a Gas Turbine Engine (“GTE”) are provided, as are embodiments of a plasma flow-controlled intake system for deployment on a GTE. In one embodiment, the GTE includes a turbine section, a combustion section upstream of the turbine section, a compressor section upstream of the combustion section, and intake section upstream of the compressor section. The intake section includes a plenum, a first inlet fluidly coupled to the plenum, and a flow-obstructing structure projecting into the plenum and having an outer surface impinged by the airflow directed into the plenum through the first inlet during operation of the GTE. A first array of plasma actuators is disposed on flow-obstructing structure and, when activated, suppresses vortex shedding of the air flowing over the outer surface of the flow-obstructing structure.

Abstract: There is provided a wind turbine apparatus which comprises blades having an aerofoil profile. The apparatus is arranged to start up even in light wind conditions and to act as a lift type device at higher rotational speeds. The apparatus may comprise wind deflectors to concentrate wind through the apparatus. Further, the blades may be orientated at less than 90° to a radius line which leads to improved performance. Still further, the apparatus may be arranged to heat water by means of solar energy.

Abstract: A centrifugal blower including a hollow housing and an impeller having a plurality of blades disposed in the hollow housing, wherein the impeller causes a fluid received in a fluid inlet of the hollow housing to flow in a radially outward direction to a fluid outlet of the hollow housing. A guide device for directing the flow of the fluid in the blower is disposed in the fluid inlet of the hollow housing, the guide device including a shroud configured to militate against turbulence, noise, a recirculation of flow of the fluid at the fluid inlet, and interference between the guide device and balance weights of the blower during an assembly of the blower.

Abstract: Various fluid turbine systems and methods are described. The turbine can be a vertical axis wind turbine configured to generate power from wind energy. The turbine system can have a blade assembly. The blade assembly can have a plurality of blades rotatable about an axis. The turbine system can have a concentrator positionable upwind and in front of a return side of the blade assembly. The concentrator can define a convex surface facing the wind. The turbine system can also have a variable concentrator positionable upwind of a push side of the blade assembly. The variable concentrator can be adjustable between a first position and a second position, the variable concentrator being capable of deflecting more wind toward the turbine in the first position than in the second position.

Abstract: An inner surface of each first supporting hole of a shroud ring has on both sides in the axial direction of a turbine impeller two first bearing portions by which first nozzle shaft is rotatably supported. An inner surface of each second supporting hole of a nozzle ring has a second bearing portion by which a second nozzle shaft is rotatably supported. The fitting clearance between the second bearing portion and the second nozzle shaft is set larger than the fitting clearance between each of the first bearing portions and the first nozzle shaft.

Abstract: The present invention relates to a blade of a turbomachine, in particular an adjustable guide blade or vane of a gas turbine, having at least one thickened area (18) on a pressure side (D) of the blade profile (P), wherein the thickened area (18) is disposed in a radially outer-lying, housing-side region of the blade (10), wherein the thickened area (18) is designed at a distance from a front edge (12) and a rear edge (14) of the blade (10).

Abstract: In a turbine for an exhaust gas turbocharger of an internal combustion engine comprising a turbine housing part, which has at least two spiral channels with respective inlets through which exhaust gas of the internal combustion engine is directed onto a turbine rotor disposed in the turbine housing part, the turbine housing part is disposed in an accommodating chamber, which is formed by a further housing part of the turbine, and from which accommodating chamber exhaust gas of the internal combustion engine can flow through the channel inlets into the spiral channels.

Abstract: A variable geometry turbocharger is simplified yet able to maintain pulse energy. In a first embodiment, a turbine housing is provided with a pivoting wall which pivots about a point near the entry to the turbine housing. By moving the wall about the pivot point, the effective volume of the turbine housing volute is varied, thus effectively reducing the volume of exhaust gas in the volute, allowing control of exhaust gas flowing to the turbine wheel. In the second embodiment of the invention, a rotating wedge segment within the volute is rotated from a first position to a second position, changing the effective volume of the volute and allowing control of exhaust gas flowing to the turbine wheel.

Abstract: An air inlet deflector for a structure having an air inlet. The deflector may be retractable within the structure, may be integrally formed with the structure, and may prevent the structure from ingesting foreign matter, such as birds. The deflector may include a series of ribs, spokes, or vanes that may vary in width and/or thickness from fore to aft, and/or may be curvilinear in one or more planes of view, and/or may serve double duty as inlet vanes for redirecting inlet air.

Abstract: An object is to provide a turbine housing assembly in which reduction of weight, facilitation of manufacture, cost-cutting, and reduction of heat capacity are further promoted compared to a conventional turbine housing made of sheet metal. A turbine housing assembly includes a plurality of constituent members connected to one another to constitute a turbine housing into which a turbine wheel is inserted. The turbine housing assembly at least includes a scroll part 2 and an exhaust part 8 of a tubular shape having a separate body separate from the scroll part 2. The scroll part 2 is formed by processing a single piece of sheet metal so that, on a back face side of a bottom face part 22 of the scroll part 2, a recess portion 22b on which a through-hole of an exhaust gas outlet 2B is formed and a projecting portion 22a formed by a bottom surface of an exhaust gas flow path 2A projecting toward the back face side are formed, the projecting portion 22a surrounding the recess portion 22b.

Abstract: An air shield apparatus includes a bracket and a number of baffles. The bracket includes a first side plate and a second side plate opposite to the first side plate. The first side plate defines a number of first shaft holes, and the second side plate defines a number of second shaft holes aligning with the first shaft holes. Each baffle includes a blocking piece between the first and second side plates, and two opposite posts protruding out from two opposite ends of the blocking piece. The posts of the baffles are pivotably received in the first shaft holes and the second shaft holes. An inner wall of each shaft hole defines a helical guiding groove. A helical sliding portion winds around each shaft. The sliding portion of each baffle is rotatably received in the corresponding guiding groove of the first and second side plates.

Abstract: A gas turbine engine includes a compressor section and a nosecone assembly. The compressor section includes an inlet guide vane assembly including an inner shroud, an outer shroud, and an inlet guide vane extending from the inner shroud to the outer shroud. The nosecone assembly is attached to the inner shroud.

Abstract: A compressor control device includes an inlet guide vane opening degree control unit configured to control an opening degree of an inlet guide vane. The inlet guide vane opening degree control unit includes an inlet guide vane opening degree command value calculation unit configured to calculate an inlet guide vane opening degree command value based on an outlet pressure detection value and a plurality of inlet guide vane opening degree correction units each configured to correct the inlet guide vane opening degree command value based on the post-merger pressure detection value and a corresponding inlet flow rate detection value for each of a plurality of upstream-most compressor bodies.

Abstract: A shut-off valve for a turbine of an oscillating water column may include a plurality of guide vanes configured to control a fluid flow into a flow passage defined by the turbine. The plurality of guide vanes may be at least partially disposed within the flow passage and may include a plurality of fixed guide vanes and a plurality of movable guide vanes. The plurality of fixed guide vanes and the plurality of movable guide vanes may be sequentially disposed in an alternating pattern in the flow passage.

Abstract: A hydro-pneumatic cylinder for converting buoyancy energy of compressed gas into mechanical energy. The cylinder can include a pair of end plates disposed at opposite ends of the cylinder and a drive axle extending longitudinally through the cylinder and passing through the center of each end plate. The cylinder can also include a core support coupled to each end plate and centrally disposed in the cylinder and a plurality of vanes for promoting a low-drag flow. Each of the plurality of vanes is coupled to the core support and the pair of end plates. A bucket is defined by the core support, two of the plurality of vanes, and the pair of end plates. The cylinder further includes a vane support coupled to the plurality of vanes and the core support. The vane support defines a plurality of openings formed therein through which a gas can pass for equalizing pressure in the bucket.

Abstract: A supersonic compressor provided may include an axial inlet and a centrifugal impeller fluidly coupled to the axial inlet. The centrifugal impeller may have a periphery and may be configured to impart energy to process fluid received via the axial inlet and discharge the process fluid from the periphery in at least a partially radial direction. The supersonic compressor may further include a static diffuser circumferentially disposed about the periphery of the centrifugal impeller and configured to receive the process fluid from the centrifugal impeller and convert the energy imparted. The static diffuser may include a plurality of diffuser vanes defining diffuser passageways therebetween. A supersonic ramp may be formed at an end of the at least one diffuser vane proximate the periphery of the centrifugal impeller. The supersonic ramp may be configured to generate a shock wave from the process fluid.

Abstract: A refrigerant compressor (10) for use in a chiller-heater system that can provide chilled water at less than 10° C. and hot water at more than 80° C. without the need for additional heat input, the compressor (10) being configured to provide a compression ratio of at least 18:1 and a temperature lift across the compressor of at least 80K, and the refrigerant fluid being selected to give the desired temperature lift without the pressure at the compressor outlet exceeding 25 bar.