Entries |
Document | Title | Date |
20080247866 | Compressor and Compressor Housing - A housing is incorporated as part of a compressor having blades that impart to a fluid a momentum along a main gas flow direction and a swirl. The housing includes a channel that has at least one channel wall and defines an axis substantially aligned with the main gas flow direction. The channel is configured to duct at least some of the fluid. The channel wall defines an internal cavity that extends axially within the channel wall. A bleed passage connects and provides fluid communication between the channel and the cavity. The channel wall defines a plurality of injection passages providing fluid communication between the cavity and the channel at a location spaced in a direction opposite the main gas flow direction from both the bleed passage and the blades. The injection passages have a portion configured to direct fluid from the cavity into the channel with a component along the main gas flow direction and a component opposed to the swirl. | 10-09-2008 |
20080298953 | WASTEGATE ASSEMBLY - A wastegate assembly ( | 12-04-2008 |
20090010752 | PUMP AND METHOD - A pump for moving a liquid including a rotor rotatable within a housing and slidable relative to the housing between a first axial rotor position during normal pump operation and a second axial rotor position during a pump inoperative condition. | 01-08-2009 |
20090022579 | BURN RESISTANT ORGANIC MATRIX COMPOSITE MATERIAL - A burn resistant composite article includes at least one composite layer having first fibers within a first organic resin matrix. At least one burn resistance layer is disposed adjacent the at least one composite layer. The burn resistance layer includes second fibers within a second organic resin matrix. The composite layer and the burn resistance layer each have an associated thermal resistance, and the thermal resistance of the burn resistance layer is greater than the thermal resistance of the composite layer. | 01-22-2009 |
20090047121 | INTERNAL COMBUSTION ENGINE SYSTEM HAVING A POWER TURBINE WITH A BROAD EFFICIENCY RANGE - An engine system incorporating an air breathing, reciprocating internal combustion engine having an inlet for air and an exhaust for products of combustion. A centripetal turbine receives products of the combustion and has a housing in which a turbine wheel is rotatable. The housing has first and second passages leading from the inlet to discrete, approximately 180°, portions of the circumference of the turbine wheel. The passages have fixed vanes adjacent the periphery of the turbine wheel and the angle of the vanes in one of the passages is different than those in the other so as to accommodate different power levels providing optimum approach angles between the gases passing the vanes and the blades of the turbine wheel. Flow through the passages is controlled by a flapper valve to direct it to one or the other or both passages depending upon the load factor for the engine. | 02-19-2009 |
20090053043 | ATTACHMENT INTERFACE FOR A GAS TURBINE ENGINE COMPOSITE DUCT STRUCTURE - A composite gas turbine engine duct receives a support ring that operates as an interface arrangement for attachment of engine system components. The support ring interfaces with the composite duct through a fastener shear load arrangement to provide a structurally sound interface which minimizes the risk of ply delamination. | 02-26-2009 |
20090092480 | GAS TURBINE ENGINE HAVING CORE AUXILIARY DUCT PASSAGE - A gas turbine engine system includes a nacelle assembly, a core engine and a mixer disposed between the nacelle assembly and the core engine. The core engine includes a core passage and a core auxiliary duct passage. The core auxiliary duct passage includes an inlet for receiving a portion of a core airflow form the core engine and an outlet for discharging a portion of the core airflow received from the core engine. | 04-09-2009 |
20090116955 | TURBINE ENGINE COMPRISING MEANS FOR HEATING THE AIR ENTERING THE FREE TURBINE - The invention relates to a turbine engine ( | 05-07-2009 |
20090148272 | TIP TURBINE ENGINE AND OPERATING METHOD WITH REVERSE CORE AIRFLOW - A tip turbine engine ( | 06-11-2009 |
20090155056 | DEVICE FOR BLEEDING AIR FROM A TURBOMACHINE COMPRESSOR - A turbomachine compressor, such as a high-pressure compressor, including air bleed means comprising a duct having a suction end opening out into an outer casing of the compressor level with a rotor wheel and a stator stage of the compressor, a screen sheet of annular shape being mounted radially inside the casing facing a portion of the suction end of the duct so as to make the bleeding of air uniform over 360° around the axis of the compressor. | 06-18-2009 |
20090175716 | Integrated bypass engine structure - One form of the present invention contemplates an apparatus comprising a gas turbine engine core, a gearbox accessory mounted to the engine core and substantially enclosed by an inner fairing; a nacelle having a plurality of panels, wherein the nacelle panels substantially enclose and overlap at least a portion of the inner fairing; and a bypass duct defined between an exterior surface of the inner fairing and an interior surface of at least some of the nacelle panels. | 07-09-2009 |
20100034643 | Transition duct aft end frame cooling and related method - A transition duct for a gas turbine includes a tubular body having a forward end and an aft end, the aft end surrounded by a frame component; an interior closure band within the aft end, covering interior top, bottom and side wall surfaces of the frame; and a plurality of cooling channels between the frame and the closure band, each having an inlet and an outlet at the forward and aft ends, respectively. | 02-11-2010 |
20100196143 | AXIAL COMPRESSOR - An axial compressor comprises a stator component and a rotor component, which cooperate to perform work on a fluid flow in a primary flow-passage defined by the stator and rotor components, the stator component and the rotor component further defining a secondary flow-passage which interconnects a higher pressure region and a lower pressure region of the primary flow-passage, the rotor component being provided with at least one secondary rotor element which, in normal operation of the machine, pumps a bypass flow of fluid through the secondary flow passage from the lower pressure region to the higher pressure region. | 08-05-2010 |
20100221102 | CORE REFLEX NOZZLE FOR TURBOFAN ENGINE - A turbofan engine is provided that includes a core nacelle at least partially surrounded by a fan nacelle. The core nacelle includes a reflex nozzle providing a core exit. The core nacelle includes a contour on its exterior surface upstream from the reflex nozzle. The contour is generally conical and tapers toward the core exit at a first slope. The reflex nozzle tapers toward the exit at a second slope that is less steep than the first slope. The reflex nozzle includes a generally linear portion. In one example, the reflex nozzle is provided by a generally cylindrical extension that sufficiently turns the bypass flow away from the core exit so that the core flow does not become choked. | 09-02-2010 |
20100247292 | System and Method of Cooling Turbine Airfoils with Sequestered Carbon Dioxide - A turbine power generation system with enhanced cooling provided by a stream of carbon dioxide from a carbon dioxide source and a method of using a stream of carbon dioxide to cool hot gas path components. The turbine power generating system includes a compressor, a combustor, a turbine, a generator, and at least one shaft linking the compressor and turbine and generator together such that mechanical energy produced from the turbine is used to drive the compressor and the generator. Carbon dioxide that is sequestered from the exhaust of the turbine may be stored and injected back into the turbine to cool hot gas path components of the turbine. | 09-30-2010 |
20100316488 | MIXING HOTTER STEAM WITH COOLER STEAM FOR INTRODUCTION INTO DOWNSTREAM TURBINE - Apparatus and methods are presented for mixing a high temperature steam, perhaps leaked from an upstream turbine, with the cooler steam from a lower temperature, downstream turbine and introducing the mixture into the downstream turbine. | 12-16-2010 |
20110027072 | BYPASS SYSTEM FOR PURGING AIR FROM A SUBMERSIBLE PUMP - A submersible pump, and method of making the submersible pump, is disclosed. The pump comprises a housing, a plurality of impeller stages serially disposed in the housing from a bottom impeller stage to a top impeller stage, an impeller bypass hole extending through one of the impeller stages and a housing bypass hole extending through the housing radially outwardly from one of the impeller stages. | 02-03-2011 |
20110194928 | BLOW-OFF SYSTEM FOR MULTI-STAGE TURBO COMPRESSOR - The present invention relates to a blow-off system for a multi-stage turbo compressor that includes a plurality of blow-off pipes disposed according to respective stages of the multi-stage turbo compressor; a plurality of blow-off valves disposed correspondingly to the plurality of blow-off pipes; and a plurality of nozzles disposed at the front or back sides of the plurality of blow-off valves and adapted to prevent the generation of surge. | 08-11-2011 |
20120099964 | TURBOCHARGER TURBINE - A turbocharger turbine having a double-layer flow passage and a variable cross-section, including a turbine housing, a volute diffuser channel, a power turbine, a volute gas feeding passage, and a partition wall. The volute gas feeding passage is arranged in the turbine housing. The partition wall is arranged in the volute gas feeding passage and divides the volute gas feeding passage into an external volute gas feeding passage and an internal volute gas feeding passage. The external volute gas feeding passage is located outside the internal volute gas feeding passage. The combination of the external and internal volute gas feeding passages forms different flow areas, sufficiently utilizing the waste gas energy of engines in a segmented mode. The variable cross-section turbine has a simple structure, is easy to upgrade at low cost, and can be easily mass-manufactured. | 04-26-2012 |
20120171019 | ATTACHMENT INTERFACE FOR A GAS TURBINE ENGINE COMPOSITE DUCT STRUCTURE - A duct includes a first and second composite duct section and a first and second metallic support ring section the second metallic support ring section abuts the first metallic support ring section. | 07-05-2012 |
20120189432 | AGGREGATE VANE ASSEMBLY - An aggregate vane assembly is disclosed herein. The aggregate vane assembly includes a core vane assembly encircling a central longitudinal axis and having a plurality of core vanes each extending radially between an inner hub and an outer band. The core vane assembly extends along the central longitudinal axis between a first forward end and a first aft end. The aggregate vane assembly also includes a bypass vane assembly disposed on a radially opposite side of the outer band relative to the plurality of core vanes. The bypass vane assembly includes at least one bypass vane extending radially outward from a platform. The bypass vane assembly extends along the central longitudinal axis between a second forward end and a second aft end. The aggregate vane assembly also includes a splitter ring positioned proximate to the first forward end. The aggregate vane assembly also includes at least one retention plate overlapping a forward end of the at least one bypass vane along the central longitudinal axis and also overlapping at least a portion of the splitter ring along the central longitudinal axis. The splitter ring is releasibly engaged with both of the outer band and the at least one retention plate. | 07-26-2012 |
20120207590 | ANTI-AIRLOCK PUMP - A pump having anti-airlock provisions. The pump is comprised of a volute comprised of a volute wall, and an impeller comprising back vanes on a side of the impeller that is proximate to the volute wall, with the back vanes having a length extending radially outwardly along the impeller. A bleed hole is formed in the volute wall in communication with the portion of the volute between the back vanes and the volute wall, and the exterior of the volute, such that the bleed hole is located midway along the length of the back vanes. When the pump is operating with air, liquid, or a combination of air and liquid in the volute, the bleed hole is under positive pressure with respect to the exterior of the volute. The bleed hole may be in communication with the exterior of the volute through a lateral tunnel formed in the pump. | 08-16-2012 |
20120243972 | GAS TURBINE ENGINE SYSTEMS INVOLVING INTEGRATED FLUID CONDUITS - Gas turbine engine systems involving integrated fluid conduits are provided. In this regard, a representative engine casing for a gas turbine engine includes: a casing wall; and a fluid conduit integrated into the casing wall. | 09-27-2012 |
20130011243 | TURBOCHARGER CONTROL LINKAGE WITH REDUCED HEAT FLOW - 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. | 01-10-2013 |
20130022452 | ENGINE COMPRESSOR, PARTICULARLY AIRCRAFT JET ENGINE COMPRESSOR, FITTED WITH AN AIR BLEED SYSTEM - 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. | 01-24-2013 |
20130058762 | Turbo Compressor - 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. | 03-07-2013 |
20130108414 | TURBINE HOUSING AND EXHAUST GAS TURBINE SUPERCHARGER | 05-02-2013 |
20130309070 | INNER BYPASS DUCT WALL ATTACHMENT - 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. | 11-21-2013 |
20130330175 | REHEAT STEAM BYPASS SYSTEM - 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. | 12-12-2013 |
20140023487 | GAS TURBINE ENGINE OUTER CASE WITH CONTOURED BLEED BOSS - 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. | 01-23-2014 |
20140044525 | GAS TURBINE ENGINE HEAT EXCHANGERS AND METHODS OF ASSEMBLING THE SAME - 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. | 02-13-2014 |
20140072410 | TURBINE WASTEGATE - 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. | 03-13-2014 |
20140072411 | TURBINE WASTEGATE - 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. | 03-13-2014 |
20140072412 | TURBINE WASTEGATE - 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. | 03-13-2014 |
20140133967 | SPLIT INTERMEDIATE CASE - 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. | 05-15-2014 |
20140140820 | AEROENGINE SEALING ARRANGEMENT - 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. | 05-22-2014 |
20140169946 | EXHAUST-GAS TURBOCHARGER - An exhaust-gas turbocharger ( | 06-19-2014 |
20140234080 | DEVICE AND METHOD FOR BLEEDING COMPRESSOR AIR IN A TURBOFAN ENGINE - A device for bleeding compressor air in a turbofan engine includes a low-pressure compressor of a primary duct, a fan stator arranged in a secondary duct downstream of a fan, and an arrangement for discharging compressor air from the low-pressure compressor into the secondary duct. The arrangement includes air guiding devices to guide compressor air into the secondary duct upstream of the fan stator relative to the flow direction in the secondary duct, past the stator vanes of the fan stator in a separate duct in the axial direction and is only mixed with the air of the secondary duct downstream of the fan stator. The separate duct is formed by a plurality of hollow structures extending in the longitudinal direction each between two adjacent stator vanes of the fan stator, with the hollow structures having a closed circumference in cross-section. | 08-21-2014 |
20140341717 | SHROUD ARRANGEMENT FOR A GAS TURBINE ENGINE - A seal segment of a shroud arrangement for bounding a hot gas flow path within a gas turbine engine is described. The seal segment is upstream of a second component of the gas turbine engine relative to the hot gas flow path. The seal segment comprises: a plate having: a downstream trailing edge; an inboard side which faces the hot gas flow path when in use; an outboard side; and a first part of a two part seal attached on the outboard side, wherein a second part of the two part seal is attached to the second component such that in an assembled gas turbine engine the two part seal provides an isolation chamber which is in fluid communication with the hot gas flow path via the trailing edge of the plate. A gas turbine having the seal segment is also described. | 11-20-2014 |
20150086338 | Cooling System for Control Valve Actuators - The present application provides a control valve actuator cooling system for providing a flow of cooling air to a control valve actuator. The control valve actuator cooling system may include a pressurized air source with the flow of cooling air, an air timing valve system, and a cooling air discharge port positioned about the control valve actuator such that the air timing valve system provides the flow of cooling air to the control valve actuator on an intermittent basis. | 03-26-2015 |
20150132110 | HIGH DURABILITY TURBINE EXHAUST CASE - A turbine exhaust case has an outer housing to be secured within a gas turbine engine and a central hub. Struts extend between the outer housing and the central hub. The struts are formed at least in part of a first material. The central hub is formed at least in part of a second material. | 05-14-2015 |
20150330236 | BIFURCATION FAIRING - A gas turbine engine including an outlet guide vane and a bifurcation fairing is disclosed. The outlet guide vane is located in a bypass duct of the gas turbine engine downstream of a fan and is of aerofoil form. The bifurcation fairing traverses the radial extent of the bypass duct and has an upstream end that blends into a trailing edge of the outlet guide vane. The bifurcation fairing includes a scoop protruding outwards from its side corresponding to a pressure side of the upstream outlet guide vane. The scoop includes a forward facing inlet leading to a delivery conduit extending inside the bifurcation fairing for delivery in use of bypass air to one or more components of the gas turbine engine. | 11-19-2015 |
20150330308 | TURBOJET WITH A DISCHARGE DUCT - The invention relates to a unit comprising an intermediate turbojet casing formed by a hub including a downstream transverse endplate having formed therein at least one first opening putting the inside of the hub into communication with a duct extending downstream from the endplate and opening out at its downstream end via a second opening formed in an outer annular shroud extending downstream from the hub for defining the inside of an annular flow space for a secondary stream. More particularly, the upstream end of said duct is fastened to the downstream endplate of the hub by releasable elastic engagement. | 11-19-2015 |
20150337761 | INTEGRATED TURBINE EXHAUST STRUTS AND MIXER OF TURBOFAN ENGINE - A turbine exhaust case (TEC) of a turbofan aeroengine includes a mixer in an annular wavy configuration having alternate crests and valleys, and a plurality of radial deswirling struts interconnecting an annular hub positioned within the mixer and selected valleys of the mixer. A plurality of secondary trailing edge struts smaller than the deswirling struts in average chord dimensions interconnect the annular hub and other selected valleys free of connection with the deswirling struts. | 11-26-2015 |
20150367945 | AIRCRAFT WITH AN ENGINE HAVING A BY-PASS AIR INLET OPENING AND A BLEED AIR OUTLET - An aircraft having at least one first and one second engine, each engine comprising a main air inlet opening, a by-pass air inlet opening and a bleed air outlet, said main air inlet opening being provided with an inlet barrier filter for filtering a main air stream through said main air inlet opening into the engine, said by-pass air inlet opening being provided with a by-pass door that is operable by an associated operating element to enable a by-pass air stream through said by-pass air inlet opening into the engine, and said bleed air outlet being provided for creating an outgoing bleed air stream going out of the engine in operation, at least one associated operating element being controllable by an outgoing bleed air stream. | 12-24-2015 |
20150377127 | ROTARY VALVE FOR BLEED FLOW PATH - Disclosed is a gas turbine engine including a compressor section in communication with a bleed flow path. A rotary valve is provided in communication with the bleed flow path to selectively regulate a flow of fluid within the bleed flow path. | 12-31-2015 |
20160010501 | INTERMEDIATE CASING FOR A TURBOFAN ENGINE | 01-14-2016 |
20160024998 | A COMPACT ROTARY WASTEGATE VALVE - A turbocharger includes a turbine section and a compressor section. The turbine section includes a turbine housing ( | 01-28-2016 |
20160047256 | BLADE IN FAN, AND FAN - A platform of a fan outlet guide blade has a first rib and a second rib in an opposite surface of a flow passage surface thereof. The first rib and the second rib are formed in portions excluding a predetermined area separated to an upstream side and a downstream side by 8 to 30% of an inter-flange distance between a first flange and a second flange with respect to an axial center of the platform, the portions being located on a ventral surface side in the opposite surface. | 02-18-2016 |
20160053631 | GAS TURBINE ENGINE WITH MOUNT FOR LOW PRESSURE TURBINE SECTION - A turbine section of a gas turbine engine according to an example of the present disclosure includes, among other things, a first turbine section and a second turbine section. The first turbine section has a first exit area and rotates at a first speed. The second turbine section has a second exit area and rotates at a second speed. A first performance quantity is defined as the product of the first speed squared and the first exit area. A second performance quantity is defined as the product of the second speed squared and the second exit area. | 02-25-2016 |
20160061056 | GAS TURBINE ENGINE ANTI-ICING SYSTEM - An anti-icing system ( | 03-03-2016 |
20160061215 | COMPRESSOR ROTOR WITH ANTI-VORTEX FINS - A compressor rotor of a gas turbine engine includes a rotor body having a face adapted to face an adjacent rotor. The rotor body extends radially between an outer peripheral rim surface and an inner rim surface. The inner rim surface defines a bore of the rotor body. A plurality of blades extends radially from the outer peripheral rim surface. A plurality of anti-vortex fins extends axially from the face of the rotor body facing the adjacent rotor. The plurality of anti-vortex fins forms a plurality of open radial passageways. The plurality of anti-vortex fins extends axially to a predetermined thickness such that, when assembled with the second rotor, axial extremities of the plurality of anti-vortex fins being in close proximity with the adjacent rotor and the adjacent rotor closes the radial passageways. A method of providing a first rotor for assembly with a second facing rotor of a compressor rotor assembly is also presented. | 03-03-2016 |
20160084113 | NACELLE MOUNTED LATCHING SYSTEM - A nacelle for a gas turbine engine includes a bifurcation, an outer diameter cowl and a first latch system. The outer diameter cowl extends from the bifurcation and the first latch system is mounted on the outer diameter cowl. The first latch system is spaced along the outer diameter cowl from the bifurcation. | 03-24-2016 |
20160090992 | CENTRIFUGAL PUMP FOR HANDLING ABRASIVE-LADEN FLUID - A centrifugal pump for handling abrasive-laden fluid is described. A centrifugal pump system for handling abrasive-laden fluid includes an impeller including an annular balance ring extending longitudinally on a top side of the impeller and an annular skirt extending longitudinally on a bottom side of the impeller, one of the annular balance ring, the annular skirt or a combination thereof having portions defining a plurality of apertures, wherein the plurality of apertures form an abrasive-media relief path that bypasses at least a portion of a clearance gap and merges with a primary working-fluid flow path. A centrifugal pump impeller includes a bottom shroud, an annular skirt extending longitudinally upstream from the bottom shroud, the annular skirt encircling a central hub, and the annular skirt having an aperture extending through a thickness of the annular skirt. | 03-31-2016 |
20160123228 | AIR INTAKE SLEEVE FOR AN AIRCRAFT TURBOPROP ENGINE - Air intake sleeve ( | 05-05-2016 |
20160130961 | GAS TURBINE ENGINE - A gas turbine engine includes in axial flow series a fan rotor, a series of outlet guide vanes for guiding flow from the fan rotor; and a bifurcation. The gas turbine engine further includes a substantially annular fluid passageway extending from fan to the bifurcation, the outlet guide vanes being positioned within the passageway. The passageway includes a profiled region positioned upstream of the bifurcation, the profiled region including a first circumferential portion positioned adjacent a second circumferential portion, the first circumferential portion having a first average radial thickness and a second circumferential portion having a second average radial thickness, the first average radial thickness being smaller than second average radial thickness. The profiled region of the passageway is configured to modify the flow through the passageway so as to improve uniformity of a static pressure field from immediately upstream of the bifurcation to just downstream of the fan rotor. | 05-12-2016 |
20160138411 | Fully integrated air guide element - An air guide element of an aircraft gas turbine, including an external housing that is provided with an inflow opening, as well as with a flow channel that is arranged inside the housing, characterized in that a tubular intermediate element that is made of an elastic material is arranged inside the inflow opening, connecting the inflow opening to the flow channel in a sealing and position-adjusting manner. | 05-19-2016 |
20160138471 | AIR GUIDING DEVICE AND TURBO ENGINE WITH AIR GUIDING DEVICE - An air guiding device for an aircraft engine, characterized in that it has at least one valve element which is moveable between a first position, in particular an open position, and a second position, in particular a closed position, wherein in the first position of the at least one valve element, through a combined effect with at least one first air guiding element that is arranged inside the air flow, a cooling air flow can be guided from an air flow into a hollow space between the housing and the core engine of the aircraft engine, and the at least one first air guiding element is aligned at least approximately in parallel to the air flow for the purpose of reducing flow resistance. The invention also relates to an aircraft engine comprising at least one air guiding device. | 05-19-2016 |
20160138472 | VENTILATION OF A TURBOMACHINE NACELLE - The invention relates to a jet pump type ejector for a turbomachine, including a duct through which a secondary ventilation air flow passes, and a first end of which forms an air intake and a second end of which forms an air outlet, the two nozzles for spraying a primary air flow being mounted in the duct which defines a mixer and a diffuser downstream from the nozzle, said two nozzles being parallel and adjacent to one another, the mixer including two substantially planar longitudinal walls, bottom and top respectively, connected to one another by two side walls having a semicircular cross-section, in which the radius of curvature R | 05-19-2016 |
20160153363 | LIQUID SEPARATING AIR INLETS | 06-02-2016 |
20160169090 | WASTEGATE SUBASSEMBLY FOR A TURBOCHARGER | 06-16-2016 |
20160169108 | STEPPED FAIRING MODULATED EXHAUST COOLING | 06-16-2016 |
20160169240 | TURBOPUMP WITH ANTI-VIBRATION SYSTEM | 06-16-2016 |
20160177828 | STAGED HEAT EXCHANGERS FOR MULTI-BYPASS STREAM GAS TURBINE ENGINES | 06-23-2016 |
20160201604 | DECOUPLED TRANSLATING SLEEVE | 07-14-2016 |
20160201607 | EFFICIENT, LOW PRESSURE RATIO PROPULSOR FOR GAS TURBINE ENGINES | 07-14-2016 |
20160376924 | GAS TURBINE ENGINE - A gas turbine engine is provided defining a radial direction. The gas turbine engine generally includes a compressor section and a turbine section, the compressor section and turbine section together defining a core air flowpath. The gas turbine engine also includes a sump positioned inward of the core air flowpath along the radial direction. An air pump is positioned inward of the core air flowpath along the radial direction for providing a flow of air from the sump to lower an internal pressure of the sump and reduce a likelihood of lubrication leaking from the sump. | 12-29-2016 |
20180023576 | TWIN CENTRIFUGAL SINGLE SPOOL ENGINE | 01-25-2018 |