Abstract: A turbomachine with a rotary shaft supporting a turbine wheel is supported for rotation in a housing. The shaft extends through a bore in the housing and a bearing assembly being disposed in the bore. At least one end of the shaft has a primary seal and a secondary seal. The primary seal comprises a non-contact seal defined by an annular clearance between a first non-rotating seal element and a second seal element that rotates with the shaft. The primary seal is arranged to receive lubricating oil from the bearing assembly. An oil slinging feature is provided between the primary and secondary seals.

Abstract: A turbomachine comprising a turbomachine shaft for rotation about an axis and for supporting a turbine wheel at one end of the turbomachine shaft; and a bearing housing having a wall defining a bore in which the turbomachine shaft is received with a substantially annular clearance, the turbomachine shaft being supported for rotation in the bore by at least one journal bearing located within the annular clearance. A surface of the turbomachine shaft which radially underlies the or each journal bearing has a surface roughness (Ra) of less than 0.15 microns and the or each journal bearing comprises a bronze alloy incorporating bismuth in an amount of up to around 6 wt %.

Abstract: A sensor apparatus comprising a housing having an inner perimeter which defines an area through which gas may flow, the housing being provided with a first chamber which extends around the area through which gas may flow, an entrance being distributed around the first chamber, and a second chamber which extends around the area through which gas may flow, an exit being distributed around the second chamber, the first chamber being arranged to be upstream of the second chamber in use, wherein the sensor apparatus further comprises one or more sensors arranged to measure a pressure difference between pressure in the first chamber and pressure in the second chamber. Corresponding turbocharger and method of measuring a mass flow rate are also provided.

Abstract: A compressor comprising a housing having an axial intake defining an intake passage and an annular outlet volute defining an annular outlet volute passage, an impeller mounted on a shaft for rotation about a shaft axis between the axial intake and the annular outlet volute, the impeller having a plurality of blades, a diffuser defining an annular diffuser passage surrounding the impeller, the annular diffuser passage having a diffuser inlet downstream of said plurality of blades, the tips of the blades sweeping across said diffuser inlet during use, wherein the compressor further comprises at least two vane members, each having a vane receivable in the diffuser passage and an actuator is coupled to the vane members to move each such that the axial length of it's vane within the diffuser passage is varied.

Abstract: A sensing apparatus for a turbomachine comprises: a magnet; a sensing coil; a power supply; and a processor. The magnet is arranged to produce a magnetic field and the sensing coil is at least partially disposed in the magnetic field. The power supply is operable to provide a voltage across the sensing coil. The processor is operable to determine a periodicity of a voltage across the sensing coil. The processor is further operable to determine a quantity indicative of temperature dependent characteristic of the sensing coil.

Abstract: A variable geometry turbine comprises a turbine wheel and a primary inlet passage of variable axial width. The turbine has a secondary inlet passage provides a flow path for a working fluid which circumnavigates at least part of the primary inlet passage. A seal element and one or more apertures are cooperable to selectively allow or prevent fluid flow through the secondary inlet passage. The ratio of the minimum cross-sectional area of the flow path through the primary inlet passage to that of the secondary inlet passage is between 1.3 and 1.7.

Abstract: A turbomachine with a shaft supporting a turbine wheel is supported for rotation in a housing. The shaft extends through a bore in the housing and a bearing assembly is disposed in the bore. The turbomachine has a first lubricating fluid slinger comprising a screw thread that is engageable with a threaded section of the shaft such that the first lubricating fluid slinger is screwable along the threaded section of the shaft so as to apply a compressive preload to the bearing assembly.

Abstract: A assembly comprises: a first member, a second member and an anti-rotation device. The first member is provided with a bore and a groove on a surface of the bore. At least a portion of the second member is disposed within the bore in the first member and a recess is provided on a generally axially facing surface of the portion of the second member. The anti-rotation device comprises an arcuate resilient body comprising a radially inner portion and a radially outer portion, the radially outer portion being received within the groove, the radially inner portion abutting a surface of the portion of the second member. A first anti-rotation feature is provided on the radially outer portion for cooperation with a complimentary feature of the first member. A second anti-rotation feature is provided on the radially inner portion, extending away from the radially inner portion of the body in a generally axial direction and is received within the recess on the second member.

Abstract: A method of manufacturing a compressor housing is provided comprising arranging a core with a die to define a mould cavity, solidifying a metal within the cavity to form a compressor housing comprising a diffuser first wall and an outlet volute first wall having an opening; the housing being formed such that a first angle is subtended between an outlet section of a surface of the diffuser first wall and a first section of a surface of the outlet volute first wall, wherein after the housing has been formed, the core is removed and a cut is applied, through the opening, to the first section of the surface of the outlet volute first wall to produce a cut section such that a second angle is subtended between the cut section and the outlet section of the surface of the diffuser first wall that is greater than the first angle.

Abstract: A variable geometry turbine comprises a turbine wheel and a primary inlet passage of variable axial width. The turbine has a secondary inlet passage provides a flow path for a working fluid which circumnavigates at least part of the primary inlet passage. A seal element and one or more apertures are cooperable to selectively allow or prevent fluid flow through the secondary inlet passage. The turbine wheel is of the radial-inflow axial-outflow type and secondary inlet passage has an outlet configured to direct working fluid to exit the secondary inlet passage in a direction which has an axial component in the opposite direction to the direction of axial outflow of the turbine wheel.

Abstract: A turbocharger arrangement comprises a turbocharger and a generator. The turbocharger comprises a turbine having a turbine wheel and a compressor having a compressor wheel. The turbine wheel and the compressor wheel are mounted to a shaft, the shaft being supported by a bearing assembly located in a bearing housing between the turbine and the compressor, such that the shaft may rotate about an axis; The compressor wheel is between the generator and the bearing assembly; and an inducer portion of the compressor wheel is between an exducer portion of the compressor wheel and the bearing assembly.

Abstract: A turbine housing has a cavity that defines a turbine axis, and has a volute. The volute comprises a volute passage spiralling radially inwards towards the cavity, a substantially annular throat positioned around the cavity between it and the volute passage, and a tongue terminating at a distal tongue tip. In a plane containing the turbine axis and the tongue tip, the throat defines a line of minimum clearance, the volute passage and tongue tip co-operatively define a preliminary inlet area, and the tongue tip defines a tongue tip lateral centerline. The line of minimum clearance and the preliminary inlet area co-operatively define a line of passage offset, which connects the centroid of the preliminary inlet area and a point half way along the line of minimum clearance. The line of passage offset is not perpendicular to the turbine axis, and the tongue tip lateral centerline and the line of passage offset define an angle therebetween of at least 60 degrees.

Abstract: A turbocharger system is provided comprising: a turbocharger having a compressor wheel and a turbine wheel connected by a shaft; a conduit configured to deliver a flow of lubricant to a bearing which supports the shaft, the conduit being provided with a valve; a sensor configured to monitor a speed of rotation of the shaft; and a controller configured to operate the valve to substantially stop the flow of lubricant to the bearing in response to detection of deceleration of the shaft and the speed of the shaft dropping below a threshold.

Abstract: A variable geometry turbine comprise a housing; a turbine wheel supported in the housing for rotation about a turbine axis; and an annular inlet passage upstream of said turbine wheel defined between respective inlet surfaces defined by an annular nozzle ring and a facing annular shroud. The nozzle ring and shroud are axially movable relative to one another to vary the size of the inlet passage; the nozzle ring having a circumferential array of inlet vanes extending across the inlet passage. The shroud covers the opening of a shroud cavity and defines a circumferential array of vane slots, each vane slot corresponding to an inlet vane, the vane slots and shroud cavity being configured to receive said inlet vanes to accommodate axial movement of the nozzle ring.

Abstract: An engine assembly includes an internal combustion engine and a waste heat recovery system. The waste heat recovery system is configured to direct refrigerant around a loop. The loop includes a heat exchanger configured to transfer heat from engine exhaust gases to the refrigerant such that the refrigerant is vaporized; a turbine configured to receive and be driven by the vaporized refrigerant; and a condenser configured to cool and condense the refrigerant for subsequent delivery in liquid form to the heat exchanger. The turbine includes a turbine wheel connected to a shaft which is held in a shaft housing, a bearing lubricated by liquid refrigerant being provided between the shaft and the shaft housing, and squeeze film dampers which utilize the liquid refrigerant are provided between the bearing and the shaft housing.

Abstract: A variable geometry turbine has a gas flow control mechanism located upstream of the turbine wheel and operable by an actuator assembly to control gas flow through said inlet passage. The control mechanism comprises a movable member for varying the size of the inlet passage. The movable member is coupled to a pair of rods that translate in an axial direction. The rods are supported for translation in guide bushes. A seal assembly seals against each rod and comprises a seal carrier coupled to an end of the guide bush. The seal carrier carries a lip seal that is in sealing contact with an external surface of the rod.

Abstract: A compressor comprises a housing defining an inlet, a volute, an outlet, and a compressor chamber between the inlet and the outlet within which a compressor wheel is rotatably mounted. The housing has discrete attached first and second housing portions, the first housing portion defining at least part of the inlet and the second housing portion defining at least part of a volute of the outlet. The first housing portion has a conductive element for conducting an electric signal and a second sensor arrangement in sensing communication with the inlet. The compressor further comprises a first sensor arrangement, the first sensor arrangement being configured such that it is in sensing communication with the volute or outlet and such that it is electrically connected to the conductive element.

Abstract: A variable geometry turbine comprising a turbine wheel mounted for rotation about a turbine axis within a housing. The housing defines an annular inlet surrounding the turbine wheel and defined between first and second inlet sidewalls. The turbine further comprises a cylindrical sleeve that is axially movable across the annular inlet to vary the size of a gas flow path through the inlet. The annular inlet is divided into at least two axially offset inlet passages. The inner diameter of the sleeve is greater than the inner diameter of the inlet passages.

Abstract: According to an aspect of the invention, there is provided a variable geometry turbine comprising: a turbine wheel mounted for rotation about a turbine axis within a housing, the housing defining an annular inlet surrounding the turbine wheel and defined between first and second inlet sidewalls; and a cylindrical sleeve axially movable across the annular inlet to vary the size of a gas flow path through the annular inlet, the annular inlet being divided into at least two axially offset inlet portions; and a ring-like seal adjacent a free end of the sleeve, at least a part of the ring-like seal being located in-between the sleeve and the inlet portions, or a structure defining the inlet portions.

Abstract: A variable geometry turbine has a housing for receipt of the turbine wheel. A gas flow control mechanism in the housing upstream of said turbine wheel is operable to control gas flow through a gas flow inlet passage. The control mechanism has a movable nozzle ring or shroud for varying the size of the gas flow inlet passage. A transmission mechanism for connection between an actuator and the control mechanism converts movement applied by the actuator into movement shroud or nozzle ring. The transmission mechanism comprises a yoke having a shaft that is rotatably supported by a wall of the housing. The yoke defines arms that extend outwardly of the shaft and which engage with the shroud or nozzle ring. There is provided at least one recess defined in an inside surface of the housing, the recess extending from shaft rotation axis and configured to allow passage of an end of the yoke shaft along it during insertion of the yoke into the housing.