Aircraft Spinner Or Cowling Patents (Class 416/94)
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Patent number: 11454212Abstract: The lengths and/or chords and/or pitches of wind turbine or propeller blades are individually established, so that a first blade can have a length/chord/pitch that is different at a given time to the length/chord/pitch of a second blade to optimize performance and/or to equalize stresses on the system.Type: GrantFiled: December 14, 2018Date of Patent: September 27, 2022Assignee: ENERGYIELD LLCInventor: Robert Hotto
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Patent number: 11391206Abstract: An intake centre fairing for a gas turbine engine includes a body. The body includes an outer surface, an apex point and a base. The apex point is at a first end of the body and the base is at a second end of the body. The base includes a base centre. The body defines a longitudinal axis along its length, a radial direction relative to the longitudinal axis and a circumferential direction relative to the longitudinal axis. The outer surface of the body is tapered from the base to the apex point along the longitudinal axis. The apex point is radially offset relative to the base centre along the radial direction. The apex point is further circumferentially offset relative to the base centre along the circumferential direction.Type: GrantFiled: April 15, 2021Date of Patent: July 19, 2022Assignee: ROLLS-ROYCE PLCInventors: Robert E Christie, David G MacManus
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Patent number: 11247773Abstract: A tilt rotor system, comprising: a pylon portion that includes: an upper protrusion that is configured to be in contact with an upper surface of a wing and a lower protrusion that is configured to be in contact with a lower surface of the wing; and a rotor portion that includes a rotor, wherein the rotor portion is able to move between: (1) a first position that is associated with a vertical flight mode and (2) a second position that is associated with a forward flight mode. The pylon portion further includes an air intake vent, a horizontal surface, a rotor controller, and a heat sink.Type: GrantFiled: June 12, 2020Date of Patent: February 15, 2022Assignee: Kitty Hawk CorporationInventors: Campbell McLaren, Pranay Sinha
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Patent number: 10753218Abstract: An example turbomachine assembly includes, among other things, a nose cone of a turbomachine, and a pump at least partially within an interior of the nose cone. The pump is selectively rotated by a motor to communicate air to the interior.Type: GrantFiled: June 25, 2018Date of Patent: August 25, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Gabriel L. Suciu, Simon Pickford, William K. Ackermann, Nathan Snape
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Patent number: 10670037Abstract: A turbofan engine includes a compressor rotor, a plurality of main blades circumferentially mounted on the compressor rotor, and a plurality of spinner blades circumferentially mounted on the compressor rotor. Each of the spinner blades is located forward of a leading edge of a corresponding one of the main blades. Each of the spinner blades is circumferentially offset to the corresponding one of the main blades.Type: GrantFiled: November 21, 2017Date of Patent: June 2, 2020Assignee: General Electric CompanyInventors: Aspi Rustom Wadia, Deepak Manohar Kamath, Daniel Waslo
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Patent number: 10662875Abstract: A propulsion unit, notably for an aircraft, including a turbomachine; a propeller that can be selectively coupled to the turbomachine; a rotary electrical machine able to drive at least the turbomachine, and selective coupling of the rotary electric machine to the propeller and/or the turbomachine that is able to couple only the propeller to the rotary electrical machine during a defined stage of operation of the propulsion unit and that is able to couple or not couple the rotary electric machine to a gas generator and/or a free turbine of the turbomachine.Type: GrantFiled: November 24, 2015Date of Patent: May 26, 2020Assignee: SAFRAN HELICOPTER ENGINESInventors: Olivier Lafargue, Didier Chartrain, Camel Serghine
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Patent number: 10518869Abstract: A turboprop including a propeller including a blade extending in a direction, which also includes a root, a leading edge, a trailing edge, and a wing tip, and an inner air stream channel, wherein the inner air stream channel includes an inlet located at the root of the blade and an outlet leading to the trailing edge of the blade transversely directed in relation to the main elongation direction, such that an inner stream of air flowing in the inner air stream channel by entering via the inlet adjacent to the root of the blade is discharged via the outlet adjacent to the trailing edge of the blade by forming a stream of blown air that moves away from the trailing edge in a direction which is transverse to the main elongation direction and which has a component in the direction of a skeleton line of the blade at the trailing edge.Type: GrantFiled: January 27, 2016Date of Patent: December 31, 2019Assignee: Safran Aircraft EnginesInventors: Paul Antoine Foresto, Anthony Binder, Alexandre Gerard Francois Couilleaux, Norman Bruno Andre Jodet
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Patent number: 9902500Abstract: 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.Type: GrantFiled: June 4, 2015Date of Patent: February 27, 2018Assignee: Airbus Helicopters Deutschland GmbHInventors: Michael Stadler, Ralf Braeutigam
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Patent number: 9828914Abstract: A thermal management system and method of circulating air in a gas turbine engine are disclosed. The thermal management system includes a nose cone having an aperture communicating air to an interior space of the nose cone and a fan blade coupled to the nose cone and having a blade passage, wherein the nose cone rotates with the fan blade to circulate air from the aperture to the blade passage.Type: GrantFiled: April 13, 2015Date of Patent: November 28, 2017Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Gabriel L. Suciu, Jesse M. Chandler
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Patent number: 9790794Abstract: The main purpose of the invention is a propeller (32) for a turbomachine (1) comprising a plurality of blades (48) and a blade support ring (47) fitted with housings (50) each of which holding a pivot (52) supporting the root (58) of one of said blades (48), characterized in that at least one of the pivots (52) is associated with at least one dynamic scoop (100), capable of moving between distinct positions, an open position in which a cooling airflow (F) can be captured, and a closed position as a function of the orientation of the corresponding blade.Type: GrantFiled: October 8, 2013Date of Patent: October 17, 2017Assignee: SNECMAInventors: Sarah Chartier, Adrien Jacques Philippe Fabre, Dominik Igel, Christophe Jacquemard, Sébastien Tajan
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Patent number: 9777595Abstract: An oil cooling system is provided. The system may comprise an oil inlet, a manifold fluidly coupled to the oil inlet, and a support strut comprising internal tubing fluidly coupled to the manifold. A heat exchanger may be fluidly coupled to the internal tubing of the support strut. A nose cone may be disposed forward of the heat exchanger and configured to rotate about an axis. The heat exchanger may be radially inward from a portion of the nose cone. A gas turbine engine is also provided. The gas turbine engine may comprise an epicyclic gear system and fan mechanically coupled to the epicyclic gear system. The fan may be configured to rotate about an axis. A nose cone may be coupled to the fan and configured to rotate about the axis. A heat exchanger may be aft of the fan and in fluid communication with the epicyclic gear system.Type: GrantFiled: May 5, 2015Date of Patent: October 3, 2017Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: William G. Sheridan, Gabriel L. Suciu
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Patent number: 9127566Abstract: An example turbomachine assembly includes, among other things, a nose cone of a turbomachine, and a pump at least partially within an interior of the nose cone. The pump is selectively rotated by a motor to communicate air to the interior.Type: GrantFiled: April 2, 2012Date of Patent: September 8, 2015Assignee: United Technologies CorporationInventors: Gabriel L. Suciu, Simon Pickford, William K. Ackermann, Nathan Snape
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Patent number: 9109464Abstract: A gas turbine engine includes a spool, a gearbox having gearing driven by the spool, and a lubrication system. The lubrication system includes a first heat exchanger positioned in a first air flow path, a second heat exchanger positioned in a second air flow path, and a lubrication pump fluidically connected to both the first heat exchanger and the second heat exchanger. A first air fan is driven by the gearbox for inducing air flow through the first air flow path. A second air fan is driven by an electric motor for inducing air flow through the second air flow path.Type: GrantFiled: August 31, 2011Date of Patent: August 18, 2015Assignee: United Technologies CorporationInventors: Gabriel L. Suciu, Jorn A. Glahn, Brian D. Merry, Christopher M. Dye, Nathan Snape, Matthew J. Howlett, Matthew G. Dixon
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Patent number: 9085979Abstract: A device for controlling pitch of fan blades of a turboprop including at least one set of adjustable-pitch fan blades secured to rotate with a rotary ring centered on the longitudinal axis, and mechanically connected to a turbine rotor, each blade of the set being coupled for pitch adjustment to a synchronization ring centered on the longitudinal axis. An actuator is secured to rotate with the turbine rotor and is mechanically connected to the synchronization ring by a plurality of connection arms connected to the actuator rod and hinge-mounted on the synchronization ring such that actuating the actuator causes the synchronization ring to move in turning about the longitudinal axis.Type: GrantFiled: April 16, 2010Date of Patent: July 21, 2015Assignee: SNECMAInventors: Wouter Balk, Gilles Alain Charier, Francois Gallet
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Patent number: 9062566Abstract: An example turbomachine assembly includes, among other things, a nose cone of a turbomachine. The nose cone provides an aperture that communicates air to an interior of the nose cone.Type: GrantFiled: April 2, 2012Date of Patent: June 23, 2015Assignee: United Technologies CorporationInventors: Gabriel L. Suciu, Simon Pickford, William K. Ackermann, Nathan Snape, Harold W. Hipsky
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Patent number: 8932016Abstract: A deicing device for propfan-type aircraft propulsion unit blades, wherein the propulsion unit includes a turbomachine that drives in rotation at least one rotor including a plurality of blades arranged around an annular crown moving with the blades, which forms with its outer wall part of an outer envelope of the propulsion unit, the outer envelope being subjected to atmospheric conditions outside the propulsion unit, the turbomachine generating a flow of hot gases that exit via an annular vein, which is concentric with the moving annular crown, and defined for part of its surface by the inner wall of the moving annular crown. The deicing device includes: a mechanism capturing thermal energy from the annular vein, within the moving annular part; a mechanism transferring thermal energy towards the rotor blades; and a mechanism distributing the thermal energy onto at least a part of the surface of the blades.Type: GrantFiled: May 3, 2010Date of Patent: January 13, 2015Assignee: Airbus Operations S.A.S.Inventors: Guillaume Bulin, Jean-Michel Rogero, Christian Fabre
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Patent number: 8667775Abstract: Secondary air flow is provided for a ducted fan having a reverse flow turbine engine core driving a fan blisk. The fan blisk incorporates a set of thrust fan blades extending from an outer hub and a set of integral secondary flow blades extending intermediate an inner hub and the outer hub. A nacelle provides an outer flow duct for the thrust fan blades and a secondary flow duct carries flow from the integral secondary flow blades as cooling air for components of the reverse flow turbine engine.Type: GrantFiled: August 5, 2009Date of Patent: March 11, 2014Assignee: The Boeing CompanyInventors: Michael K. Kisska, Norman H. Princen, Mark S. Kuehn, Gary B. Cosentino
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Patent number: 8529204Abstract: A nose cone assembly for a gas turbine engine comprises a spinner and a plurality of circumferentially spaced mounting members for mounting the spinner on a fan hub of the gas turbine engine. Each of the mounting members is rigid in a generally axial direction and flexible in a generally radial direction.Type: GrantFiled: February 12, 2009Date of Patent: September 10, 2013Assignee: Rolls-Royce PLCInventor: Adam MacGregor Bagnall
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Publication number: 20120315141Abstract: An annular flow mixer is provided for use in a gas turbine engine. A core generator of the engine provides an annular duct for the flow of working gas, which exhausts from the duct through the flow mixer. The flow mixer has a plurality of circumferentially spaced exhaust chutes from which the working gas exits in respective exhaust plumes. The exhaust chutes are configured such that, at the discharge end of the flow mixer, a radially outer portion of each exhaust chute radially overlaps with a radially inner portion of at least one adjacent exhaust chute.Type: ApplicationFiled: February 7, 2011Publication date: December 13, 2012Applicant: ROLLS-ROYCE PLCInventor: Kenneth F. Udall
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Patent number: 8262344Abstract: A thermal management system and method for a miniature gas turbine engine includes a forward cover having a filter portion along an axis of rotation of a gas turbine engine, a first lubrication passage and a second lubrication passage.Type: GrantFiled: April 2, 2008Date of Patent: September 11, 2012Assignee: Hamilton Sundstrand CorporationInventors: Eric J. Alexander, Mark N. Shatz′, Gordon F. Jewess
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Patent number: 8221080Abstract: At a propeller (1) or a fan (2) of an aircraft engine, part of the inflowing air—at the air stagnation point forming at the tip (8a) of the hub cone (8)—is conducted into an interior of a hub cone via air inlet openings (9) and, via air outlet openings (10) in an area with minimum static pressure at the downstream end of the hub cone, on a circumference of the latter and at a velocity essentially corresponding to the velocity of the air inflow, is injected into a thick boundary layer on the hub cone, essentially in the direction of flow, thereby accelerating the boundary layer to the velocity of the air inflow. This enables the inflow of air also to the root areas (4a, 6a) of the fan blades/propeller blades (4, 6), to be effected at an aerodynamically favorable, less steep inflow angle.Type: GrantFiled: July 23, 2009Date of Patent: July 17, 2012Assignee: Rolls-Royce Deutschland Ltd & Co KGInventor: Carsten Clemen
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Patent number: 8182222Abstract: A spinner mounting at least one propeller hub and having a blade platform for each hub formed on the spinner body formed from a thermal insulating material capable of withstanding exhaust gasses. The platform is formed in a shape that presents an aerodynamic surface in the direction of travel of the system, preferably at a predetermined effective blade angle so as to act in concert with the blade and the gas path to minimize drag or to optimize thrust. The system may include two sets of propeller blades, and each includes a spinner and blade platform.Type: GrantFiled: February 12, 2009Date of Patent: May 22, 2012Assignee: Hamilton Sundstrand CorporationInventor: Robert H. Perkinson
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Publication number: 20110158808Abstract: A propeller blade root airflow system comprises a spinner for shrouding a propeller hub and propeller roots. The spinner has root holes disposed about a spinner circumference for receiving propeller roots, and airflow ducts disposed about a spinner circumference for drawing air into the spinner and away from the root holes. A method for preventing choked flow conditions between adjacent propeller blades in the area of a spinner in a propulsion system comprises rotating the spinner and propeller blades to produce propulsive thrust by driving an air stream past the propeller blades and spinner, and drawing a portion of the air stream into a plurality of ducts disposed within the spinner to prevent choked flow conditions.Type: ApplicationFiled: December 29, 2009Publication date: June 30, 2011Applicant: HAMILTON SUNDSTRAND CORPORATIONInventor: Chad M. Henze
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Patent number: 7886544Abstract: A propeller or propeller drive, the propeller being carried by a support shaft (3) which projects from the body (53) of the missile or vehicle and about which the propeller rotates, the drive unit for the propeller being situated in front of the propeller (23) in the propulsion direction or in the propeller spinner (1). According to the invention it is provided that the drive unit has at least one gas turbine (55), optionally a multiple-stage gas turbine, which is secured to the drive shaft and which drives it or jointly rotates with it, and that the drive shaft (6) is traversed by the support shaft (3) or is mounted thereon in a rotating manner and drives the propeller (23), optionally by way of a gear mechanism (14) situated between the turbine (55) and the propeller (23).Type: GrantFiled: April 24, 2006Date of Patent: February 15, 2011Inventor: Christian Koenig
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Patent number: 7559191Abstract: A system for cooling a ducted fan aircraft engine includes a first nacelle surrounding the engine and a second nacelle substantially concentrically surrounding the first nacelle. The system includes a first spinner coupled around a base of a rotor of the ducted fan and a second spinner substantially concentrically surrounding the first spinner and forming a duct between first and second spinners. The second spinner includes an opening to allow air to flow into the duct. The rotor includes a plurality of airfoils penetrating through the first and second spinners. Each of the airfoils includes a first portion located in the duct, and a second portion located between the second spinner and a fuselage of the ducted fan. The first portions of the airfoils provide cooling airflow over the engine and structural support for the second portions. The second portions of the airfoils provide thrust for the aircraft.Type: GrantFiled: September 19, 2005Date of Patent: July 14, 2009Assignee: Aurora Flight Sciences CorporationInventor: Robert Parks
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Patent number: 7306432Abstract: An apparatus for balancing a shaft of an aircraft engine preferably includes a nose cone and the use of standard fasteners. The nose cone is adapted to cooperate with at least one standard fastener to retain the standard fastener to the nose cone to rotationally balance the shaft.Type: GrantFiled: September 13, 2005Date of Patent: December 11, 2007Assignee: Pratt & Whitney Canada Corp.Inventors: Sean André Rockarts, Barry Barnett
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Patent number: 6887043Abstract: A method for enables a gas turbine engine to be assembled. The method comprises forming at least one substantially elliptically-shaped opening within a flange extending from a fan disk, inserting a fastener including a first body portion, a second body portion, and an anti-rotation stop extending therebetween, at least partially through the at least one flange opening, and coupling the fastener to the flange such that the fastener stop is positioned within the at least one flange opening.Type: GrantFiled: March 28, 2003Date of Patent: May 3, 2005Assignee: General Electric CompanyInventors: Brian Edward Dix, Joann Mari Takehara, Michael Ray Garrison
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Publication number: 20040258522Abstract: A method for enables a gas turbine engine to be assembled. The method comprises forming at least one substantially elliptically-shaped opening within a flange extending from a fan disk, inserting a fastener including a first body portion, a second body portion, and an anti-rotation stop extending therebetween, at least partially through the at least one flange opening, and coupling the fastener to the flange such that the fastener stop is positioned within the at least one flange opening.Type: ApplicationFiled: March 28, 2003Publication date: December 23, 2004Inventors: Brian Edward Dix, Joann Mari Takehara, Michael Ray Garrison
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Patent number: 6561763Abstract: A gas turbine engine nose cone (44) comprises a spinner (46) and a fairing (48). The spinner (46) has a conical upstream portion (50) and a cylindrical base portion (52). The fairing (48) is frustoconical and surrounds the base portion (52) of the spinner (46). The outer surface (68) of the fairing (48) forms a continuation of the outer surface (56) of the conical upstream portion (50) of the spinner (46). The outer surface (68) of the fairing (48) has a skin (80) to protect the fairing (48) from erosion and a protective member (86) extends around the upstream end (82) of the fairing (48) to retain the skin (80) on the upstream end (82) of the fairing (48).Type: GrantFiled: January 11, 2002Date of Patent: May 13, 2003Assignee: Rolls-Royce plcInventor: Ian S Breakwell
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Patent number: 6416280Abstract: An exemplary embodiment of the invention is a spinner for a front end of a fan assembly of a gas turbine engine. The spinner includes a single piece substantially conically shaped hollow body circumscribed about a centerline extending aftwardly from a tip to an axially aft spinner end. A plurality of bolt holes extend axially parallel to the centerline through the hollow body at an axial location between the tip and the aft spinner end. The hollow body may include a forward conical section extending aftwardly from the tip to a transition section, an aft conical section extending aftwardly from the transition section to the aft spinner end, and the bolt holes are axially located in the transition section. An aft spinner flange attached to the axially aft spinner end includes a plurality of flange lightening holes axially disposed through the aft spinner flange and the flange lightening holes.Type: GrantFiled: November 27, 2000Date of Patent: July 9, 2002Assignee: General Electric CompanyInventors: James Michael Forrester, Joseph Timothy Stevenson, Jeffrey Clayton Potter, Sean Joel Corrigan
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Patent number: 6358014Abstract: Increased impact resistance capability is achieved in a cost and weight efficient manner by providing a spinner made of a 3-D orthogonal woven composite material. The spinner defines a generally conical shell having a plurality of axial rib stiffeners and at least one circumferential rib stiffener integrally formed thereon. The combination of the integral rib stiffeners with the 3-D orthogonal woven composite material results in a substantially greater torsional stiffness. The use of the 3-D orthogonal woven composite material also eliminates delamination found in laminated composite spinners.Type: GrantFiled: March 24, 2000Date of Patent: March 19, 2002Assignee: General Electric CompanyInventors: Chen-Yu J. Chou, Gerald A. Pauley, Yiping Xu
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Patent number: 5833435Abstract: An assembly for a rotating composite inlet nose cone is reinforced or is repaired after having undergone delamination. The assembly strengthens the inlet nose cone and thus blacks delaminations of the inlet nose cone. In one particular embodiment, the assembly includes an outer ring that blacks delaminations in an undamaged rotating inlet nose cone. The outer ring has a higher stiffness to mass ratio than the adjacent portion of the inlet nose cone assembly. In one detailed embodiment, an inner ring is disposed inwardly of the adjacent portion of the inlet nose cone assembly. The inner ring in one detailed embodiment has a lower stiffness to mass ratio than the outer ring.Type: GrantFiled: December 24, 1996Date of Patent: November 10, 1998Assignee: United Technologies CorporationInventor: James R. Smith
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Patent number: 5230603Abstract: To control unsteady motion phenomena in turbomachines, it has been proposed to employ an active control system to modify the flow conditions. In the present invention, the modification is effected by devices mounted in a bullet or nose bullet at the entry to a rotor of the turbomachine.Type: GrantFiled: August 13, 1991Date of Patent: July 27, 1993Assignee: Rolls Royce plcInventor: Ivor J. Day
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Patent number: 5112191Abstract: The invention concerns a cowling for aircraft propulsion systems of the counterrotating propeller type. The cowling includes a pair of mounting rings located fore and aft of a propeller array. Removable panels extend between the mounting rings and contain openings through which the propeller blades extend.Type: GrantFiled: April 11, 1989Date of Patent: May 12, 1992Assignee: General Electric CompanyInventors: William J. Strock, Thomas G. Wakeman, Ambrose A. Hauser
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Patent number: 5039278Abstract: Air control mechanism within a power turbine section of a gas turbine engine. The power turbine section includes a rotor and at least one variable pitch propulsor blade. The propulsor blade is coupled to and extends radially outwardly of the rotor. A first annular fairing is rotatable with the propulsor blade and interposed between the propulsor blade and the rotor. A second fairing is located longitudinally adjacent to the first fairing. The first fairing and the second fairing are differentially rotatable. The air control mechanism includes a platform fixedly coupled to a radially inner end of the propulsor blade. The platform is generally positioned in a first opening and a first fairing. The platform and the first fairing define an outer space. In a first position corresponding with a first propulsor blade pitch, the platform is substantially conformal with the first fairing.Type: GrantFiled: April 11, 1989Date of Patent: August 13, 1991Assignee: General Electric CompanyInventors: Thomas G. Wakeman, Richard W. Brown
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Patent number: 4892269Abstract: A pusher turboprop engine is provided with an interior exhaust duct structure which directs the hot turbine gasses through and out of the engine nacelle to an annular duct mounted on the rear spinner which surrounds the propeller hub. The rotating annular duct includes blade-shaped shields which protect the roots of the propeller blades from the hot exhaust gasses and also pulls warmed cooling air through the engine nacelle thereby providing a rearwardly directed jet thrust to augment the propeller thrust.Type: GrantFiled: April 28, 1988Date of Patent: January 9, 1990Assignee: Allied-Signal Inc.Inventors: Robert J. Greco, Jack D. Betterton
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Patent number: 4732538Abstract: Air control means in a gas turbine engine having a variable pitch rotatable airfoil and means for varying the pitch of the airfoil are disclosed. The air control means comprises a platform fixedly attached to a radially inner end of the airfoil. The platform is generally positioned on a rotatable annular surface, which surface defines outer and inner spaces. In a first position, an edge portion of the platform substantially conforms to the annular surface. In a second position, the edge portion is displaced radially outwardly from the surface thereby allowing fluid communication between the outer and inner spaces.Type: GrantFiled: September 5, 1985Date of Patent: March 22, 1988Assignee: General Electric CompanyInventors: Gary C. Wollenweber, Wu-Yang Tseng, Thomas J. Sullivan
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Patent number: 4722666Abstract: An oil lubricating and cooling system is positioned in the engine cowl and includes a heat exchanger, a compressor for delivering air from air inlets in the surface of the cowl through the heat exchanger and hence to air outlets also in the cowl surface and oil pumps also located within the cowl for circulating oil from the sump in the cowl to the heat exchanger to the reduction gear within the cowl that serve to drive the fan also supported within the cowl and having the blades extending outwardly therefrom. The reduction gear, compressor and pumps are all driven from the engine shaft, the end of which is located in the cowl.Type: GrantFiled: June 29, 1987Date of Patent: February 2, 1988Assignee: United Technologies CorporationInventors: William T. Dennison, Robert F. Brodell
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Patent number: 4171183Abstract: A small diameter, highly loaded multiple bladed variable pitch propulsor having swept blades with thin advanced airfoil sections, integrated with a nacelle contoured to retard the airflow through the blades thereby reducing compressibility losses and designed to operate with a turbine engine and using a single stage reduction gear resulting in a high performance, lightweight propulsion system providing a substantial improvement in efficiency over the high bypass ratio turbofan engine.Type: GrantFiled: September 24, 1976Date of Patent: October 16, 1979Assignee: United Technologies CorporationInventors: Robert W. Cornell, Carl Rohrbach