Abstract: A fan unit includes a housing having an air inlet and an air outlet; a first fan and second fan mounted in the air inlet and the air outlet respectively and arranged in tandem so as to generate an air flow; a first valve mounted adjacent to the air inlet for allowing air to flow into the housing and preventing air from flowing out of the housing; and a second valve mounted adjacent to the air outlet for allowing air to flow out of the housing and preventing air from flowing into the housing.

Abstract: A compressor includes: a compressor spool rotatable about an axis carrying axially-spaced-apart blade rows of compressor blades; a casing surrounding the compressor blades, the casing carrying a liner assembly defining a boundary of a primary compressor flowpath; and a plurality of axially-spaced-apart stator rows of stator vanes carried by the liner assembly, the stator rows alternating axially with the blade rows. At least some of the stator rows are variable stator rows, the stator vanes of which are mounted on trunnions passing through the casing, and are pivotable relative to the casing. An actuator arm is coupled to each trunnions, outside the casing. At least one first bleed slot passes through the liner structure between axially adjacent first and second ones of the variable stator rows; and a first flow path defined by the casing communicates with the first bleed slot and with the exterior of the casing.

Abstract: A bifurcation aerofoil having a leading edge portion and flanks where the leading edge portion is mounted to an inner wall of the bypass duct using a floating seal which permits circumferential movement of the leading edge. A cowl has a wall that provides the flanks of the aerofoil. On closing of the cowl into its flight position any contact between the flanks and the leading edge portion enables realignment of the leading edge portion to the inner wall of the bypass duct.

Abstract: A steam turbine 10 is provided with a double-structure comprising an inner casing 20 and an outer casing 21. A turbine rotor 22, in which plural stages of moving blades 24 are circumferentially implanted, is operatively disposed in inner casing 20. A diaphragm outer ring 25 and a diaphragm inner ring are disposed along the circumferential direction in inner casing 20. Stationary blades 27 are circumferentially provided between diaphragm outer ring 25 and the diaphragm inner ring, so that diaphragm outer ring 25, the diaphragm inner ring and stationary blades 27 form a stage of stationary blades. The stages of the stationary blades are arranged alternately with the stages of moving blades 24 in the axial direction of turbine rotor 22. A cooling medium passage 40 for passing a cooling medium CM which is supplied through a supply pipe 45 is formed between inner casing 20 and diaphragm outer ring 25.

Abstract: An intermediate case (IMC) for use in a compressor section of a gas turbine engine includes a bleed duct and an IMC centerbody. The bleed duct is formed via sand casting. The IMC centerbody is formed via investment casting and is fixedly attached to the bleed duct.

Abstract: A pump assembly and components therefor including an impeller which has flow inducer elements on an inner surface of a front shroud thereof, a flow directing device or strainer having passageways for delivering material to the impeller and at least one flow circulating passageway and a pump casing having an intake section with flow distribution vanes in the region of a feed opening adjacent the intake section.

Abstract: A guide blade ring (1) arranged downstream of the fan in the bypass duct of a turbofan engine for untwisting the airflow generated by the fan includes guide stator vane support struts (3) integrated into the guide blade ring at regular intervals respectively in place of a guide stator vane, the guide stator vane support struts (3) having a larger thickness and chord length than the guide stator vanes (2). A flow channel (4), respectively defined between a suction side (7) of the guide stator vane support strut and a guide stator vane (2.1) adjacent thereto on the suction side, is expanded by a geometric modification of the guide stator vane (2.1) with respect to the remaining guide stator vanes (2) in accordance with the respective configuration of the guide stator vane support strut.

Abstract: Various embodiments of ported-shroud centrifugal compressors are described. In some embodiments a wall of a compressor housing defines a pair of bulb-shaped hollow spaces or “bulbs”, one located proximate the compressor wheel and the other spaced upstream from the wheel, and having a connection therebetween. The downstream bulb is connected to the main flow path of the compressor by a port slot through the wall. The upstream bulb is connected to the inlet area of the main flow path by a passage through the wall. The bulbs can provide acoustic wave cancellation through multiple internal reflections in various directions. In one embodiment, the upstream bulb has a second passage connected to it, facing axially upstream, for receiving a portion of the total flow in a choked-flow operating regime, and conducting that portion through the upstream bulb, through the connection to the downstream bulb, and through the port slot into the main flow path.

Abstract: A low pressure cooling system for a turbine engine for directing cooling fluids at low pressure, such as at ambient pressure, through at least one cooling fluid supply channel and into a cooling fluid mixing chamber positioned immediately downstream from a row of turbine blades extending radially outward from a rotor assembly to prevent ingestion of hot gases into internal aspects of the rotor assembly. The low pressure cooling system may also include at least one bleed channel that may extend through the rotor assembly and exhaust cooling fluids into the cooling fluid mixing chamber to seal a gap between rotational turbine blades and a downstream, stationary turbine component. Use of ambient pressure cooling fluids by the low pressure cooling system results in tremendous efficiencies by eliminating the need for pressurized cooling fluids for sealing this gap.

Abstract: In an air mixing arrangement wherein a primary fluid is introduced through an opening in a wall to be mixed with a secondary fluid flowing along the wall surface, the opening is airfoil shaped with its leading edge being orientated at an attack angle with respect to the secondary fluid flow stream so as to thereby enhance the penetration and dispersion of the primary fluid stream into the secondary fluid stream. The airfoil shaped opening is selectively positioned such that its angle of attack provides the desired lift to optimize the mixing of the two streams for the particular application. In one embodiment, a collar is provided around the opening to prevent the secondary fluid from contacting the surface of the wall during certain conditions of operation. Multiple openings maybe used such as the combination of a larger airfoil shaped opening with a smaller airfoil shaped opened positioned downstream thereof, or a round shaped opening placed upstream of an airfoil shaped opening.

Abstract: An assembly can include a turbine housing that includes a bore, a wastegate seat and a wastegate passage that extends to the wastegate seat; a bushing configured for receipt by the bore; a rotatable wastegate shaft configured for receipt by the bushing; a wastegate arm extending from the wastegate shaft; and a wastegate plug extending from the wastegate arm where the wastegate plug includes a profile, defined in part by a portion of a torus, for contacting the wastegate seat to cover the wastegate passage and, for example, defined in part by a portion of a modified sphere or a portion of a cone. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.

Abstract: An assembly can include a turbine housing that includes a bore, a wastegate seat and two wastegate passages that extend to the wastegate seat; a rotatable wastegate shaft configured for receipt by the bore; a wastegate arm extending from the wastegate shaft; and a wastegate plug extending from the wastegate arm where the wastegate plug comprises a profile defined in part by a portion of a torus, for contacting the wastegate seat in a closed state, and defined in part by two plug portions, for defining clearances with respect to the wastegate seat in an open state. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.

Abstract: An assembly can include a turbine housing that includes a bore, a wastegate seat and a wastegate passage that extends to the wastegate seat; a bushing configured for receipt by the bore; a rotatable wastegate shaft configured for receipt by the bushing; a wastegate arm extending from the wastegate shaft; and a wastegate plug extending from the wastegate arm where the wastegate plug includes a profile, defined in part by a portion of a torus, for contacting the wastegate seat to cover the wastegate passage. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.

Abstract: A wind generating device employs modules each having two turbines. Each of the turbines employs two rotors coaxially aligned by a shaft associated with an in-line generator. Alternatively, the turbine employs only one rotor for low wind areas. The arrangement includes a proximal channel with a leading portion having decreasing radius toward the first rotor which acts as a collector and a following portion connecting fluidly the first and second rotor and a distal channel which is separate from the proximal channel and opens into the following portion thereby adding to the airflow to the second rotor. Downstream from the second rotor is a diffuser with a radius increasing with distance from the rotor. The modules may be stacked vertically stacked which allows for yaw responsive to wind. The modules may be mounted on a tower.

Abstract: A waste-watermill for generating electrical energy from a flow of waste water running through an underground waste-water conduit. The flow of waste water defines a free surface and a flow direction inside the waste water conduit. The waste-watermill comprises 1) a water wheel for being driven by the flow of waste water in an undershot configuration, 2) an axle for defining an rotational axis for the water wheel, where the flow of waste water passes below and transverse to the rotational axis in the undershot configuration, 3) a wheel support for rotationally supporting the water wheel in the undershot configuration and in a stationary position relative to the underground waste-water conduit, and 4) an electric generator operatively connected with the water wheel and the axle for being driven by the water wheel to produce electrical energy.

Abstract: Supersonic Magnetic Advanced Generation Jet Electric Turbine (S-MAGJET) described herein, and a subsonic derivative, MAGJET, integrate a gas power turbine, superconducting electric power and propulsion generation, and magnetic power flux field systems along with an ion plasma annular injection combustor which utilizes alternative petroleum-based fuel and combustion cycles to create a hybrid turbine turbomachine for aerospace propulsion. The propulsion unit is able to achieve a dramatic increase in horsepower, combustion and propulsion efficiency, and weight reduction. In addition, the turbomachinery structures may be disposed within an exoskeleton architecture that achieves an increase in thrust to weight ratio with a concomitant increase in fuel efficiency and power generation. The engine continuously adjusts the temperature, pressure and mass airflow requirements using an electromagnetic power management system architecture.

Abstract: A pump device (1A) includes: an impeller (2) that rotates about an axis of rotation (A); an inlet passage (10a) that extends along the axis of rotation (A) of the impeller (2); a volute chamber (10b) provided around the impeller (2); a high-pressure chamber (4) provided around the inlet passage (10a); a circumferential wall (5) that separates the inlet passage (10a) and the high-pressure chamber (4); and a bypass passage (6) that communicates the volute chamber (10b) and the high-pressure chamber (4). The circumferential wall (5) has a plurality of through holes (51) provided in a circumferential direction. The central axis (B) of each of the through holes (51) is included in a plane substantially perpendicular to the axis of rotation (A). The central axis (B) is inclined with respect to a reference line (L).

Abstract: A heat exchanger assembly for use in a gas turbine engine includes a bypass valve and at least one body portion. The body portion includes at least one de-congealing inlet channel in flow communication with the bypass valve, a plurality of cooling channels in flow communication with the bypass valve and the at least one de-congealing inlet channel, and at least one de-congealing outlet channel in flow communication with the bypass valve and the at least one de-congealing inlet channel. The bypass valve is configured to deliver a fluid between the at least one de-congealing inlet channel and the plurality of cooling channels during a first mode of operation to facilitate reducing a temperature of the fluid. The bypass valve is further configured to deliver the fluid between the at least one de-congealing inlet channel and the at least one de-congealing outlet channel during a second mode of operation.

Abstract: An axially extending outer case for a gas turbine engine comprises an arcuate case wall, an opening, a boss and contouring. The arcuate case wall has an inner surface and an outer surface. The opening extends through the arcuate case wall. The boss extends radially from the outer surface of arcuate case wall and surrounds the opening. The contouring surrounds the opening along the inner surface of the arcuate case wall within the boss.

Abstract: A gas turbine engine includes a structure defining a circumferential passage in fluid communication with an internal passage in at least one strut radially extending into the engine, circumferential passage also in fluid communication with a plurality or nozzles or jets to provide a wash manifold integrated with the engine casing structure. One or more nozzles are provided in the manifold for directing a washing fluid injected into the duct.

Abstract: A baffle assembly for a housing of a combustor system of a gas turbine engine is provided. The baffle assembly includes a baffle retainer and a baffle. The baffle retainer includes a retainer tube and a collar. The retainer tube is received within a bleed port of the housing. The collar is defined at an upper end of the retainer tube and is configured to rest against the housing. The baffle includes a baffle tube rigidly attached to an inner surface of the retainer tube.

Abstract: An exemplary fluid supply system for use on a turbomachine includes a turbomachine fluid container having a moveable barrier. A pressurized fluid is delivered to one side of the moveable barrier, and an opposing side of the flexible barrier communicates with a source of lubricant. Pressurized fluid is selectively delivered to the one side to move the moveable barrier between a flow-permitting position that permits flow from the source of lubricant to the turbomachine fluid container and a flow-restricting position that restricts flow from the source of lubricant to the turbomachine fluid container.

Abstract: An axial flow turbine is described having a casing defining a flow path for a working fluid therein, a rotor co-axial to the casing, a plurality of stages, each including a stationary row of vanes circumferentially mounted on the casing a rotating row of blades, circumferentially mounted on the rotor, with an inner face of the casing exposed to the working fluid having one or more essentially circumferential grooves of increasing depth each ending in an extraction port with a bore.

Abstract: A gas turbine engine includes a bypass flow path. A core flow path has a reverse duct configured to reverse a direction of core flow. The core flow path includes an exhaust duct in fluid communication with the bypass flow path and is configured to introduce core exhaust flow in the core flow path back into the bypass flow path. A splitter is arranged in the bypass flow path and adjoins the exhaust duct.

Abstract: Various embodiments include systems for controlling the flow of main steam from a high-pressure (HP) turbine to a turbine packing. In some cases, a system is disclosed including: a high pressure (HP) turbine including a plurality of stages, the plurality of stages including an early stage, a middle stage and a later stage; an intermediate pressure (IP) turbine operably connected with the HP turbine; a packing separating the HP turbine and the IP turbine; a main conduit fluidly connecting the middle stage of the HP turbine and the packing, the main conduit including a main valve; and a bypass conduit fluidly connected to the main conduit and bypassing the main valve, the bypass conduit including: a blocking valve; and an opening between the blocking valve and a downstream connection with the main conduit.

Abstract: A compressor section includes a rotor platform; a rotor blade extending radially outwardly from the rotor platform, the rotor blade including a pressure sidewall and a circumferentially opposing suction sidewall extending in a radial direction between a root and a tip and in an axial direction between a leading edge and a trailing edge; a casing having an inner surface surrounding the tip and spaced radially outwardly thereform to define a gap therebetween; a plurality of grooves disposed in the inner surface of the casing and extending in a generally circumferential direction, the plurality of grooves including a first groove and a second groove; and a channel system comprising at least a first channel positioned within the casing and configured to provide fluid communication between the first groove and the second groove.

Abstract: Apparatus for reducing air mass flow through the compressor in a single shaft gas turbine engine having an extended operating range including part load conditions, to provide low emissions combustion. The apparatus includes one or more nozzles positioned for injecting compressed air into the inlet region of the compressor. The nozzles are oriented to direct the compressed air tangentially to, and in the same angular direction as, the direction of rotation to create a swirl in the inlet air flow to the compressor inducer. The apparatus also includes conduits in flow communication between the compressor diffuser and the nozzles, one or more valves operatively connected to control the flow of compressed air from the diffuser to the nozzles, and a controller operatively connected to the valves to cause compressed air flow to the nozzles during operation at part load conditions.

Abstract: A hydraulic machine through which a main flow of water passes including at least one turbine blade having an upstream end and a downstream end and a channel extending an entire length of the blade for tapping flow from the main flow adjacent the upstream end of the blade and discharging the tapped flow at the downstream end of the blade in a direction of the main flow.

Abstract: A bypass duct of a gas turbine engine has an inner bypass duct wall has a front end portion which is rigidly mounted to an engine core case and a rear end portion which is flexibly mounted to the core case. The flexible mounting between the rear portion of the inner bypass duct wall and the core case allows hot engine areas of the core case to thermally grow and contract relative to the inner bypass duct wall without imposing additional loads on the inner bypass duct wall.

Abstract: A bypass turbojet including a fan wheel carrying blades and surrounded by an annular casing, the casing including an air suction mechanism sucking air from an annular clearance formed between the casing and radially outer ends of the blades of the fan wheel. The air suction mechanism includes an inlet including at least one inlet slot formed in an inside wall of the casing and connected to a suction channel extending downstream. The inlet slot of the suction mechanism is situated axially in register solely with upstream portions of chords of the blades of the fan wheel at their radially outer ends.

Abstract: The present invention relates to a jet engine nacelle (1), of the type comprising an aft section forming an external structure (2) which, together with a concentric internal structure (4) comprising an internal panel (10) intended to surround a down-stream portion of the jet engine, defines an annular flow duct for a so-called secondary stream (3), characterized in that exhaust means (11) are formed in the internal panel such that any unwanted excess pressure is discharged into the annular duct.

Abstract: A bleed valve bleeds hot gases from a compressor into a bypass duct of a gas turbine engine. The valve comprises a diffuser having opposing walls and a divider located between the walls and which define at least two passages through which a bleed fluid flows and into a fluid flow through the bypass duct. The passages are angled towards each other to force the two gas flows together to form a high aspect ratio plume. This plume has a relatively large surface area that that improves mixing with the bypass flow to cool it and prevented otherwise hot bleed flows from impinging on heat sensitive components adjacent the bypass duct.

Abstract: A guide system for translating components of an aircraft engine nacelle includes a track assembly and a slider assembly. The track assembly includes a track guide member having a track channel. The slider assembly translatably engages the track assembly. The slider assembly includes a slider body configured to be received within the track channel. The slider assembly further includes a slider arm member pivotably coupled to the slider body with a hinge joint disposed within the track channel. The slider arm member extends from the body portion and outwardly of the track assembly. Associated apparatuses are also provided.

Abstract: A wastegate assembly (200) for a turbocharger (101) or the like is provided having a support plate (300), an actuator (275), a linkage (250) operably connected to the actuator (275), and a valve plate (225) operably connected to the linkage (250). The linkage (250) translates actuation of the actuator (275) to movement of the valve plate (225) thereby sealing or unsealing the bypass outlet (500). The actuator (275), linkage (250) and valve plate (225) can be pre-assembled to the support plate (300) prior to the support plate (300) being connected to the turbine housing (102). The actuator (275), linkage (250) and valve plate (225) can be calibrated prior to the wastegate assembly (200) being connected to the turbine housing (102). The bypass outlet (500) can be machined via access provided by the wastegate port (400).

Abstract: A turbocharger for a motor vehicle. The turbocharger includes a compressor mechanically coupled to a turbine. The wastegate of the turbine includes a valve head matched to a valve seat. The valve head is retained at one end of an actuator arm. A resilient spacer is arranged between the valve head and the actuator arm. The resilient spacer is configured to forcibly separate the valve head from the actuator arm when the valve head is unseated.

Abstract: A Pelton hydraulic machine through which a main flow of water passes including at least one Pelton turbine manifold with at least a turbulent zone or a reduced-pressure zone being formed close to the manifold and wherein a secondary flow drawn from the main flow, and unaltered in relation to the main flow, is injected into the turbulent or reduced-pressure zone so as to alter the main flow locally or increase the pressure in the zone.

Abstract: The invention relates to a nacelle for a turbojet engine, comprising a rear section forming an outer structure which defines, together with a concentric inner structure (4) comprising an inner panel (10) for surrounding a downstream part of the turbojet engine, an annular flow channel for a so-called secondary flow. The invention is characterized in that the exhaust means (11) are arranged in the inner panel in such a way that any inopportune surge is exhausted in the annular channel.

Abstract: An anti-vortex device for use in a compressor rotor assembly of a gas turbine engine is described. Spaced-apart radial passageways extend from an axially extending passage provided in a central area of the device to an outer peripheral rim surface thereof. The radial passageways channel air from the primary gaspath about the rotor assembly to the axially extending passage where the air is directed into a central axial passage of the rotor assembly.

Abstract: In the area of the support struts and/or the aerodynamic fairings downstream of the stator vanes, the cross-section of the bypass duct of a turbofan engine is enlarged such that the pressure variations caused by the stagnation effect of the installations and reacting on the fan are reduced, enabling the fan to be operated with more efficiency and stability and finally the losses of the overall system and the fuel consumption to be reduced. The cross-sectional enlargement is accomplished by modifying the course of the wall in a limited area, actually by gradually enlarging the flow cross-section in the bypass duct in the axial and in the circumferential direction, with this enlargement being confined to the area around the leading edge of the support struts and/or the aerodynamic fairings.

Abstract: A compressor having a purge circuit. In one embodiment, the compressor includes: a rotor having a plurality of stages, each of the plurality of stages including a set of radially extending rotor wheels; a working fluid supply path for providing working fluid to each of the plurality of stages for compression by each set of radially extending rotor wheels; a purge circuit for diverting a first portion of the working fluid from an upstream portion of the working fluid supply path to at least one downstream stage of the plurality of stages; and a substantially axial bypass path bypassing the at least one downstream stage, the substantially axial bypass path for diverting a second portion of the working fluid around the at least one downstream stage.

Abstract: A turbine housing includes a first shell member and a third shell member, which are formed from metal sheets and forming a housing body, and a tongue member, which is fixed to inner circumferential surfaces of the shell members and and discrete from the shell members and. The tongue member defines an inlet port and a scroll compartment in the housing body.

Abstract: The axial-flow turbine includes an extraction chamber 15 disposed on the outer circumference of a turbine blade chamber 12 and an extraction opening 16. An outer diaphragm 8 forming the downstream-side wall surface of the extraction chamber 15 is provided with a projection 21 formed more radially inwardly than the downstream-side edge on the outer circumference of an adjacent bucket 2 on the upstream side of the extraction opening 16 to form the downstream-side wall surface of the extraction opening 16. The projection 21 forms an upstream-side wall surface 18 of the outer diaphragm 8 for leading a part of the working fluid to the extraction chamber 15, and an inner wall surface 19 of the outer diaphragm 8 for leading the remaining working fluid to a bucket 11 on the downstream side of the extraction opening 16.

Abstract: A bypass turbojet engine including an outer fan duct and an inner fan duct (IFD), between which the secondary flow passes, and a high pressure compressor having an outer casing is disclosed. The IFD is fastened on the outer casing.

Abstract: A device for regulating the flow rate of air feeding a turbine ventilation cavity of a turbomachine turbine section is disclosed. The device includes at least one tubular duct opening into a take-off cavity and leading into a turbine ventilation cavity, the pressure inside the take-off cavity being higher than the pressure inside the turbine ventilation cavity; an air flow rate regulation valve disposed in the tubular duct, the valve being suitable for moving under the effect of the pressure difference between the take-off cavity and the turbine ventilation cavity; and a mechanical return device for holding the valve in a maximum closure position for the duct so long as the pressure difference between the take-off cavity and the turbine ventilation cavity remains below a predetermined threshold pressure.

Abstract: An extraction unit for a steam turbine includes an end plate mounted downstream of a selected stage of a steam turbine, the end plate sealing the selected stage from the atmosphere, and an extraction pipe passing through the end plate for extracting steam from the selected stage.

Abstract: In order to improve a turbo compressor comprising a compressor housing, in which an incoming gas volume flow is supplied to an impeller channel through an inlet channel, is compressed in the impeller channel by an impeller and is discharged from the impeller channel via an outlet channel, and a flow diversion channel which is provided in the compressor housing, extends outside of the impeller channel and the inlet channel, opens into the inlet channel with an opening on the inlet side and into the impeller channel with an opening on the impeller side and conveys a diversion volume flow between the openings as a function of a difference in pressure, in such a manner that it can be operated optimally with volume flows which are far below the volume flow provided for the design point it is suggested that the flow diversion channel have a cross-sectional flow area increasing in size up to the opening on the inlet side proceeding from the opening on the impeller side.

Abstract: A compressor including at least one cascade of fixed vanes, the vanes of which are mounted on a wall and between them form air-flow passages, and an air bleed system which bleeds air from the passages between two vanes, through openings made in the wall, the openings being discontinuous and each including a plurality of orifices arranged one behind the other in a direction of the air flow. An upstream orifice of each opening has a larger cross-sectional area than downstream orifices of the opening, and a number and cross section of the downstream orifices are adjusted to suit a predetermined bleed-off flow rate.

Abstract: The life of an actuator such as a turbocharger VTG actuator is extended by reducing heat conduction from the turbine housing along the control linkage to the actuator link and into the actuator, thereby protecting sensitive electronic components. To this end, the control linkage may be equipped with cooling fins, or be made hollow rather than solid, or be made of a thermal energy retarding material in order to retard heat from the turbine housing assembly reaching the actuator.

Abstract: A rotor wheel is provided and includes a body having first and second opposing faces and portions recessed from a plane of the first face to define therein an annular groove and a plurality of tributary grooves, the annular groove being receptive of fluid from an external source and formed to direct the fluid to flow along an annular flow path, and the plurality of tributary grooves being receptive of the fluid from the annular groove and respectively formed to direct the fluid to flow sequentially along radial and axial tributary flow paths while preventing inter-tributary groove fluid communication.

Abstract: A gas turbine engine system is disclosed which includes a core passage and a bypass passage which can be configured as a fan bypass duct or a third stream bypass duct. The core passage and bypass passage are routed to flow through a nozzle before exiting overboard an aircraft. The nozzle includes moveable members capable of changing a configuration of the nozzle. In one form the moveable members are capable of changing throat areas for portions of the nozzle that receive working fluid from the core passage and the bypass passage. The bypass passage can include a branch. In one form the branch can include a heat exchanger. The bypass passage can also provide cooling to one or more portions of the nozzle, such as cooling to a deck of the nozzle.