Air And Diverse Fluid Discharge From Separate Discharge Outlets (e.g., Fan Jet, Etc.) Patents (Class 60/226.1)
  • Patent number: 11319899
    Abstract: The invention relates to a module of an aircraft bypass engine including an annular flow path of a secondary flow of gas wherein is mounted an annular row of stator blades configured to straighten the gas flow, an arm extending in the flow path downstream from said annular row of blades and being connected physically to one of the stator blades so as to form a unitary aerodynamic assembly, wherein at least one of the two blades adjacent to the blade of the unitary aerodynamic assembly is of a variable pitch type and capable of being rotationally moved about a substantially radial axis with respect to a longitudinal axis of the engine.
    Type: Grant
    Filed: June 27, 2019
    Date of Patent: May 3, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventor: Paul Antoine Foresto
  • Patent number: 11313250
    Abstract: A frangible strut for a gas turbine engine includes a first end to couple to a first structure of the gas turbine engine, and a second end opposite the first end. The second end is to couple to a second structure of the gas turbine engine. The second end includes an outer portion coaxial with and spaced radially apart from an inner portion. The inner portion is to receive a fastening device to couple the second end to the second structure. The outer portion is coupled to a body of the frangible strut. The inner portion is interconnected to the outer portion by a plurality of frangible members that are spaced apart about a perimeter of the inner portion, and each of the frangible members are configured to release the inner portion from the outer portion. The frangible strut includes the body interconnecting the first end and the second end.
    Type: Grant
    Filed: July 15, 2020
    Date of Patent: April 26, 2022
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Manjunath Subbarayachar, Anil Kumar Thokala, Jayanth Hirebelaguly Shivaprakash, Pavankumar Kadam, Avinash Kumar
  • Patent number: 11313326
    Abstract: The invention relates to a jet engine with a fixed housing in which a primary flow is formed in which incoming air is burned in at least one combustion chamber, in said housing a secondary flow being formed in which incoming air is accelerated by a fan and, said secondary flow being expelled at the outlet cone of the housing together with the exhaust gas from the combustion chamber, said fan being mounted on a main shaft rotatably about an axis and having a plurality of substantially radially-extending fan blades.
    Type: Grant
    Filed: August 10, 2018
    Date of Patent: April 26, 2022
    Inventors: Finn Schöning, Dragan Ko{hacek over (z)}ulović
  • Patent number: 11313282
    Abstract: A turbojet engine (2), such as an aircraft turbojet engine, comprising: an epicyclic gear train (36); a turbine rotating a transmission shaft (34) constrained to rotate with the inner planetary gear (60) of the epicyclic gear train (36); a fan (18) rigidly connected to the ring gear (66) of the epicyclic gear train (36); and an electric machine (70) comprising a rotor (72) and a stator (74), the rotor (72) being rigidly connected to the planet carrier (68) of the epicyclic gear train (36). Alternatively, the fan (18) is rigidly connected to the planet carrier and the electric machine (70) is rigidly connected to the ring gear. The invention also relates to methods for using said turbojet engine, in particular for controlling the reduction ratio between the transmission shaft and the turbine, in order to recover kinetic energy or for taxiing.
    Type: Grant
    Filed: June 21, 2019
    Date of Patent: April 26, 2022
    Assignee: SAFRAN AERO BOOSTERS SA
    Inventor: Stephane Maljean
  • Patent number: 11313327
    Abstract: An axial flow turbomachine (102) for producing thrust to propel an aircraft is shown. The turbomachine has an inner duct (202) and an outer duct (204), both of which are annular and concentric with one another. An inner fan (206) is located in the inner duct, and is configured to produce a primary pressurised flow (P). An outer fan (207) is located in an outer duct, and is configured to produce a secondary pressurised flow (S). The outer fan has a hollow hub (208) through which the inner duct passes. The outer fan has a diameter of from 2.5 to 3.5 times a diameter of the inner fan.
    Type: Grant
    Filed: July 31, 2019
    Date of Patent: April 26, 2022
    Assignee: ROLLS-ROYCE plc
    Inventor: Giles E Harvey
  • Patent number: 11313323
    Abstract: A propulsion unit for an aircraft including a nacelle with a D-shaped structure housing a thrust-reversing device with movable vanes, the nacelle containing two D-shaped half-structures each including an external reverser half-cowl. The propulsion unit contains an assembly box-type structure, attached in downstream cantilevered fashion to the turbojet engine fan casing, the box-type structure including two guide rails guiding the deflection vanes, a locking device between the assembly box-type structure and the half-beams in the six o'clock position of the D-shaped half-structures, the assembly box-type structure being arranged in the propulsion unit such that the guide rails guiding the vanes of the assembly box-type structure are situated in the continuation of the guide rails in the six o'clock position guiding the vanes attached to the fan casing, to provide continuity between the rails.
    Type: Grant
    Filed: June 15, 2020
    Date of Patent: April 26, 2022
    Assignee: Safran Nacelles
    Inventor: Patrick Boileau
  • Patent number: 11306682
    Abstract: An axial flow turbomachine (102) for producing thrust to propel an aircraft is shown. The turbomachine has an inner duct (202) and an outer duct (204), both of which are annular and concentric with one another. An inner fan (206) is located in the inner duct, and is configured to produce a primary pressurised flow (P). An outer fan (207) is located in an outer duct, and is configured to produce a secondary pressurised flow (S). The outer fan has a hollow hub (208) through which the inner duct passes. A swept area of the outer fan is from 2 to 20 times greater than a swept area of the inner fan.
    Type: Grant
    Filed: July 31, 2019
    Date of Patent: April 19, 2022
    Assignee: ROLLS-ROYCE plc
    Inventor: Giles E Harvey
  • Patent number: 11306681
    Abstract: Conventional commercial engine exhaust systems are defined with axi-symmetric surfaces (e.g., conical or nearly conical surfaces), which create an annular exhaust for the fan (bypass) nozzle of roughly constant duct-height around the circumference. In one example configuration, the fan sleeve has been sheared upward (towards the wing or pylon) causing a larger area and duct height near the pylon relative to the portion away from the pylon. For a given thrust generated by the turbofan engine housed in the nacelle, the shear toward the pylon mount realigns the thrust in the direction of flight which may, in some examples, reduce noise experienced downstream of the turbofan engine and decreases fuel consumed in the engine core.
    Type: Grant
    Filed: January 15, 2019
    Date of Patent: April 19, 2022
    Assignee: THE BOEING COMPANY
    Inventors: Kurt E. Acheson, David F. Cerra, Robert H. Willie
  • Patent number: 11293302
    Abstract: An anterior part of a nacelle of an aircraft propulsion unit having an air inlet lip at the front end, an internal structure and an external panel extending the air inlet lip, and an annular rigidifying frame having an external peripheral edge connected to the external panel is disclosed. The anterior part of the nacelle includes a shock-absorbing element connected rigidly on the one hand to an internal peripheral edge of the rigidifying frame and on the other hand to the internal structure.
    Type: Grant
    Filed: December 21, 2018
    Date of Patent: April 5, 2022
    Assignee: AIRBUS OPERATIONS (S.A.S.)
    Inventors: Frédéric Vinches, Gregory Albet, Julien Sentier
  • Patent number: 11286859
    Abstract: An acoustic panel comprises: a face sheet comprising a plurality of openings; a back sheet opposite to the face sheet; and an intermediate layer comprising a plurality of cells each comprising a cavity and a plurality of walls extending between the face sheet and the back sheet and surrounding the cavity, the plurality of walls comprising a plurality of drainage slots and a plurality of covers covering the plurality of drainage slots and openable for drainage. A method for making the acoustic panel is also described.
    Type: Grant
    Filed: August 9, 2018
    Date of Patent: March 29, 2022
    Assignee: General Electric Company
    Inventors: Egbert Geertsema, Kirk Alan Rogers
  • Patent number: 11286863
    Abstract: A gas turbine engine assembly according to an exemplary aspect of the present disclosure includes, among other things, a geared architecture configured to rotatably couple a turbine and a compressor of an engine to rotate the compressor at a different speed than the turbine and a fan. A method of adjusting rotational speeds within a gas turbine engine is also disclosed.
    Type: Grant
    Filed: November 2, 2018
    Date of Patent: March 29, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Gary D. Roberge
  • Patent number: 11286852
    Abstract: A gas turbine engine includes a buffer system that communicates a buffer cooling air to at least one bearing structure and at least one shaft of the gas turbine engine. The buffer system includes a first bleed air supply and a conditioning device that conditions the first bleed air supply to render the first buffer supply air at an acceptable temperature to pressurize the at least one bearing structure and cool the at least one shaft.
    Type: Grant
    Filed: September 12, 2019
    Date of Patent: March 29, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: William K. Ackermann, Peter M. Munsell
  • Patent number: 11268444
    Abstract: A cooling system for a component of a gas turbine engine includes a first airflow passage configured to direct a first airflow to a mixing chamber and a second airflow passage to configured direct a second airflow to the mixing chamber, the second airflow having a higher temperature than the first airflow, and a cooling airflow passage to direct a cooling airflow from the mixing chamber to the component, the cooling airflow comprising the first airflow and the second airflow. The airflow passages are configured and sized to allow an amount of cooling airflow for unrestricted engine operation. When the first airflow passage is disabled, the second airflow passage and cooling airflow passage are configured and sized to allow an amount of cooling airflow which is adequate to permit continued safe engine operation restricted to within only a portion of its normal parameters and operating envelope.
    Type: Grant
    Filed: May 18, 2017
    Date of Patent: March 8, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Paul R. Hanrahan, Jonathan Ortiz
  • Patent number: 11260983
    Abstract: This invention concerns an aircraft propulsion system in which an engine has an engine core comprising a compressor, a combustor and a turbine driven by a flow of combustion products of the combustor. At least one propulsive fan generates a mass flow of air to propel the aircraft. An electrical energy store is provided on board the aircraft. At least one electric motor is arranged to drive the propulsive fan and the engine core compressor. A controller controls the at least one electric motor to mitigate the creation of a contrail caused by the engine combustion products by altering the ratio of the mass flow of air by the propulsive fan to the flow of combustion products of the combustor. The at least one electric motor is controlled so as to selectively drive both the propulsive fan and engine core compressor.
    Type: Grant
    Filed: August 27, 2019
    Date of Patent: March 1, 2022
    Assignee: ROLLS-ROYCE PLC
    Inventors: Peter Swann, Paul Fletcher, Alvise Pellegrini, Ashog Kulathasan
  • Patent number: 11261800
    Abstract: An aspect includes a system for a gas turbine engine. The system includes one or more bleeds of the gas turbine engine and a control system configured to check one or more activation conditions of a dirt rejection mode in the gas turbine engine. A bleed control schedule of the gas turbine engine is adjusted to extend a time to hold the one or more bleeds of the gas turbine engine partially open at a power setting above a threshold based on the one or more activation conditions. One or more deactivation conditions of the dirt rejection mode in the gas turbine engine are checked. The dirt rejection mode is deactivated to fully close the one or more bleeds based on the one or more deactivation conditions.
    Type: Grant
    Filed: October 24, 2018
    Date of Patent: March 1, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Christopher J. Hanlon, James F. Krenzer, Becky E. Rose, Mark F. Zelesky
  • Patent number: 11255295
    Abstract: Propulsion assembly comprising: an inner casing (13); an outer casing (3); an inter-duct casing (15) delimiting a primary duct (12) between the inner casing (13) and an outer wall (14), and a secondary duct (16) between the outer casing (3) and an outer wall (17); a fan capable of generating an air flow (24) circulating from downstream to upstream in the secondary duct (16); the assembly further comprising: at least one duct (27) for bleeding air from said flow (24), this bleed duct (27) comprising an inlet port (28) in the outer wall (17) and an outlet port (29) in the inner wall (14); an outer flap (30) movable between an open position and a closed position of the inlet port (28); an inner flap (31) movable between an open position and a closed position of the outlet port (29).
    Type: Grant
    Filed: October 17, 2017
    Date of Patent: February 22, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Guillaume Rodolphe Jacques Gerard Pouyau, Gabriela Philippart, Christian Sylvain Vessot, Marc Patrick Tesniere
  • Patent number: 11248537
    Abstract: A gas turbine control device includes a first estimation unit configured to estimate a first temperature which is a first turbine inlet temperature estimation value based on a first model which is a physical model using a fuel flow rate to a gas turbine; a second estimation unit configured to estimate a second temperature which is a second turbine inlet temperature estimation value based on a second model which is a physical model using an exhaust gas temperature of the gas turbine; and a correction unit configured to correct the first temperature based on the second temperature to calculate a third turbine inlet temperature estimation value.
    Type: Grant
    Filed: February 22, 2018
    Date of Patent: February 15, 2022
    Assignee: MITSUBISHI POWER, LTD.
    Inventors: Kazushige Takaki, Akihiko Saito, Ryuji Takenaka, Koshiro Fukumoto, Yoshifumi Iwasaki
  • Patent number: 11236639
    Abstract: A gas turbine engine includes a core flowpath for flowing a core stream, a second flowpath located radially outward from the core flowpath for flowing a second stream, and an auxiliary flowpath located radially outward from the second flowpath for flowing an auxiliary stream. A heat exchanging device is constructed and arranged to divert a portion of the second stream into the auxiliary flowpath. A turbine exhaust case is constructed and arranged to flow the auxiliary stream into the core flowpath for mixing with the core stream.
    Type: Grant
    Filed: February 10, 2015
    Date of Patent: February 1, 2022
    Assignee: Raytheon Technologies Corporation
    Inventors: Christopher J. Hanlon, Daniel B. Kupratis, Walter A. Ledwith, William F. Schneider, Sean Danby, Robert H. Bush, Benjamin Bellows
  • Patent number: 11236679
    Abstract: An example gas turbine engine includes a propulsor assembly including at least a fan module and a fan drive turbine module; a gas generator assembly including at least a compressor section, a combustor in fluid communication with the compressor section, and a turbine in fluid communication with the combustor; and a geared architecture driven by the fan drive turbine module for rotating a fan of the fan module. A weight of the fan module and the fan drive turbine module is less than about 40% of a total weight of a gas turbine engine.
    Type: Grant
    Filed: August 21, 2020
    Date of Patent: February 1, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Frederick M. Schwarz, Gabriel L. Suciu
  • Patent number: 11230943
    Abstract: A turbine rear structure for a gas turbine engine includes a central hub and a circumferential outer ring coaxial with the central hub. The turbine rear structure further includes a plurality of guide vanes extending radially between the central hub and the circumferential outer ring, and an intermediate guide vane located in a space defined between adjacent guide vanes. The intermediate guide vane is located closer to one of the guide vanes than the other guide vane.
    Type: Grant
    Filed: November 6, 2018
    Date of Patent: January 25, 2022
    Assignee: GKN Aerospace Sweden AB
    Inventor: Fredrik Wallin
  • Patent number: 11225875
    Abstract: Vane assemblies are described. The vane assemblies include a platform, an airfoil extending from the platform, a forward rail extending from the platform and arranged along a forward side of the platform, and an aft rail extending from the platform and arranged along an aft side of the platform. At least one support beam is provided extending in a forward-aft direction between the forward rail and the aft rail and separated from the platform by a first distance. The at least one support beam has a thickness in a radial direction of 40% or less of a total radial extent from the platform to an outer diameter edge of at least one of the forward rail and the aft rail and the at least one support beam has a thickness in a circumferential direction of 30% or less of a total circumferential extent of vane assembly.
    Type: Grant
    Filed: January 27, 2021
    Date of Patent: January 18, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Nicholas J. Madonna, Kristopher K. Anderson, Justin M. Aniello, Jeffrey Michael Jacques, Daniel P. Preuss, Christina A. Ryan, Melissa Shallcross
  • Patent number: 11209012
    Abstract: The invention proposes a fan, in particular for a turbomachine of small size such as a jet engine, having a hub ratio which corresponds to the ratio of the diameter of the inner limit of the incoming air stream at the radially inner ends of the leading edges of the fan blades, divided by the diameter of the circle around which the outer ends of the fan blades pass, having a value of between 0.20 and 0.265.
    Type: Grant
    Filed: April 24, 2019
    Date of Patent: December 28, 2021
    Assignee: Safran Aircraft Engines
    Inventors: Laurent Jablonski, Philippe Gérard Edmond Joly, Christophe Perdrigeon, Damien Merlot, Hervé Pohier
  • Patent number: 11203976
    Abstract: A turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. Also included in the turbine engine is a mixing chamber. The mixing chamber is located between the compressor section and the combustor section and the mixing chamber is radially outward of a primary fluid flow path connecting the compressor section, the combustor section, and the turbine section.
    Type: Grant
    Filed: February 24, 2020
    Date of Patent: December 21, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Vito Guardi, Christopher B. Lyons, Nathan Snape
  • Patent number: 11203982
    Abstract: A turbofan engine includes a geared architecture for driving a fan about an axis. The geared architecture includes a sun gear rotatable about an axis, a plurality of planet gears driven by the sun gear and a ring gear circumscribing the plurality of planet gears. A carrier supports the plurality of planet gears. The geared architecture includes a power transfer parameter (PTP) defined as power transferred through the geared architecture divided by gear volume multiplied by a gear reduction ratio and is between 219 and 328.
    Type: Grant
    Filed: June 10, 2019
    Date of Patent: December 21, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Frederick M. Schwarz, William G. Sheridan
  • Patent number: 11199134
    Abstract: A gas turbine engine has an engine core including a primary flowpath. A first bypass duct is positioned radially outward of the engine core. A gas discharge protrudes radially into the first bypass duct. The gas discharge includes a fairing defining a lobed outlet. The lobed outlet includes a plurality of axially aligned peaks and axially aligned valleys. Each of the axially aligned valleys is configured to prevent a fluid passing through the valley from traveling radially inward immediately downstream of the fairing creating regions of relatively cool, mixed, and hot airflows.
    Type: Grant
    Filed: August 11, 2017
    Date of Patent: December 14, 2021
    Assignee: Ford Global Technologies, LLC
    Inventor: Edward Nicholas Shipley, Jr.
  • Patent number: 11193496
    Abstract: A gas turbine engine includes a combustor section arranged between a compressor section and a turbine section. The compressor section includes at least a low pressure compressor and a high pressure compressor. The high pressure compressor is arranged upstream of the combustor section. A fan section has an array of twenty-six or fewer fan blades. The low pressure compressor is downstream from the fan section. An airfoil is arranged in the low pressure compressor and includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a camber angle and span position that defines a curve with a decreasing camber angle within the range of 80% span to 100% span. The camber angle is less than 20° within the entire range of 40% span to 100% span.
    Type: Grant
    Filed: January 13, 2020
    Date of Patent: December 7, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
  • Patent number: 11174790
    Abstract: A gas turbine engine includes: a core engine surrounded by a core fairing; a propulsive fan; a nacelle surrounding the propulsive fan, the core fairing and the core engine; and a fan duct for receiving a bypass air flow accelerated by the propulsive fan, the fan duct being defined between the nacelle and the core fairing. The gas turbine engine further includes an air-oil heat exchanger for cooling engine oil using an air flow diverted from the bypass air flow, the heat exchanger being mounted behind a wall of the fan duct. The gas turbine engine further includes a flow passage which receives the diverted air flow at a first location in the fan duct, delivers the diverted air flow to the heat exchanger, and returns the diverted air flow to the fan duct at a second location which is downstream of the first location.
    Type: Grant
    Filed: October 12, 2018
    Date of Patent: November 16, 2021
    Assignee: ROLLS-ROYCE PLC
    Inventor: James Holt
  • Patent number: 11174796
    Abstract: The disclosure relates to a gas turbine engine having an accessory gearbox assembly having an accessory gearbox. The accessory gearbox assembly is mounted adjacent a core of the gas turbine engine and has a support formation for supporting a conduit. The conduit extends between a first location on the engine and a second location on the engine. The first location and the second location may be spaced from the accessory gearbox such that the conduit does not operatively communicate with the accessory gearbox in use. The accessory gearbox may be axially mounted and may provide a bridge for supporting a plurality of conduits.
    Type: Grant
    Filed: March 31, 2020
    Date of Patent: November 16, 2021
    Assignee: ROLLS-ROYCE PLC
    Inventors: Clare L Bewick, David A Edwards
  • Patent number: 11168618
    Abstract: A shaft apparatus for a gas turbine engine comprising: a first shaft portion; a second shaft portion; and a ratchet mechanism configured to permit the first shaft portion to rotate with respect to the second shaft portion in a first direction, and to prevent the first shaft portion from rotating with respect to the second shaft portion in a second direction opposite to the first direction. A gas turbine engines comprising the shaft apparatus and methods of operating a gas turbine engine are also disclosed.
    Type: Grant
    Filed: February 25, 2020
    Date of Patent: November 9, 2021
    Inventors: Michael Booth, Steven P. Culwick
  • Patent number: 11168586
    Abstract: The present invention enables machining to be easily performed and reduces stress concentration on a machined hole that is formed in a cylindrical member. Recesses (2) recessed in the depth direction of a machined hole (1) are formed on circumferential side-portions of the machined hole 1 formed in a cylindrical member (10). In each of the recesses (2), a part of the opening edge is formed to be a circular arc portion (2a) that has a circular arc shape, the bottom is formed to be gradually shallowed by an inclined surface (2c) toward an opened portion (2b) in which the circular arc shape is opened, from a part along the circular arc portion (2a), and the circular arc portion (2a) is disposed toward the machined hole (1).
    Type: Grant
    Filed: April 9, 2018
    Date of Patent: November 9, 2021
    Assignee: MITSUBISHI HEAVY INDUSTRIES AERO ENGINES, LTD.
    Inventors: Yasuyuki Uetsuki, Tadayuki Hanada, Yohei Fujimoto, Takafumi Ota, Yusuke Ichihashi
  • Patent number: 11168616
    Abstract: A gas turbine engine according to an exemplary embodiment of this disclosure includes among other possible things, a fan section including a plurality of fan blades, a first electric motor assembly that provides a first drive input for driving the fan blades about an axis, a turbine section, and a geared architecture driven by the turbine section and coupled to the fan section to provide a second drive input for driving the fan blades, and second electric motor assembly is coupled to rotate the geared architecture relative to a fixed structure controls a speed of the fan blades provided by a combination of the first drive input and the second drive input.
    Type: Grant
    Filed: May 16, 2018
    Date of Patent: November 9, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Daniel Bernard Kupratis, Christopher J. Hanlon, William G Sheridan
  • Patent number: 11162429
    Abstract: Provided is a turbo fan engine (TF) provided with a power transmission device that switches main shafts (MSs) connected to a starter generator (SG) so as to perform power transmission, between at startup and after the startup. The TF includes a first MS and a second MS. The power transmission device includes a first shaft, an intermediate shaft, and a second shaft that are coaxially disposed, and a clutch. The first shaft is connected to the first MS through bevel gears, the intermediate shaft is disposed outside of the first shaft and is connected to the SG through bevel gears, and the second shaft is disposed outside of the intermediate shaft and is connected to the second MS through bevel gears.
    Type: Grant
    Filed: April 16, 2020
    Date of Patent: November 2, 2021
    Assignee: IHI CORPORATION
    Inventors: Akihiko Oyama, Noriko Morioka, Naoki Seki
  • Patent number: 11162458
    Abstract: A ventilation device for controlling an air flow through at least one air inlet into an interior space of a gas turbine engine, comprises: at least one actuable closure device for the at least one air inlet, which has an open position for exposing the air inlet and can be transferred by actuation into a closed position for closing the air inlet; and a fire extinguishing device having an extinguishing agent arranged in a reservoir, wherein the fire extinguishing device is connected or can be connected to the interior space and the closure device in such a way that activation of the fire extinguishing device both leads to admission of extinguishing agent from the reservoir into the interior space and brings about actuation of the closure device to transfer the closure device into the closed position.
    Type: Grant
    Filed: December 3, 2019
    Date of Patent: November 2, 2021
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Michael Schacht
  • Patent number: 11162417
    Abstract: A scoop inlet for a turbomachine. The turbomachine includes a core engine casing relative to a centerline extending the length of the turbomachine. Further, the core engine casing at least partially defines a bypass flow passage. The scoop inlet includes an inlet at the core engine casing in fluid communication with the bypass flow passage. The inlet includes a mouth fluidly coupling the bypass flow passage to a cooling system. The mouth receives bypass bleed air from the bypass flow passage and defines a width in a circumferential direction relative to the centerline. The scoop inlet also includes a bypass bleed duct defined through the core engine casing. The bypass bleed duct fluidly couples the mouth to the cooling system. In addition, the scoop inlet includes a plurality of droplets at the mouth of the inlet partially extending from the mouth into the bypass flow passage.
    Type: Grant
    Filed: May 22, 2019
    Date of Patent: November 2, 2021
    Assignee: General Electric Company
    Inventors: Liangjun Qiu, Guohua Zhong
  • Patent number: 11162430
    Abstract: A speed change device includes a sun gear. A plurality of intermediate gears surround the sun gear. Each of the plurality of intermediate gears includes a forward set of teeth and an aft set of teeth. A ring gear surrounds the plurality of intermediate gears. The ring gear includes a forward portion with a forward set of teeth in meshing engagement with the forward set of teeth on each of the plurality of intermediate gears and an aft portion with an aft set of teeth in meshing engagement with the aft set of teeth on each of the plurality of intermediate gears. A carrier includes a carrier forward portion and a carrier aft portion. Each of the plurality of intermediate gears are located axially between the carrier forward portion and the carrier aft portion.
    Type: Grant
    Filed: June 2, 2020
    Date of Patent: November 2, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: William G. Sheridan
  • Patent number: 11156092
    Abstract: A method of manufacturing a multistage axial-centrifugal compressor for a gas turbine engine and a multistage axial-centrifugal compressor that includes a series of axial compressor stages each having a rotor mounted to a common shaft positioned upstream from a centrifugal compressor stage mounted to the common shaft. The method includes determining an operational rotor tip speed for each of the axial stages. The method includes comparing the operational rotor tip speed to a threshold range value and determining to machine an airfoil of the rotor for at least one of the axial stages by an arbitrary manufacturing approach based on the operational rotor tip speed as greater than the threshold range value. The method includes determining to machine an airfoil of the rotor for at least one of the axial stages by a flank manufacturing approach based on the operational rotor tip speed as less than the threshold range value.
    Type: Grant
    Filed: February 7, 2019
    Date of Patent: October 26, 2021
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Bruce David Reynolds, Richard David Conner, Michael T. Barton, Jeffrey W. Gluck, Nick Nolcheff
  • Patent number: 11149565
    Abstract: A turbine engine assembly including an air flow guide assembly, including at least one guide vane and at least one structural arm, the vane and arm extending radially about an axis. The arm includes an upstream end portion having a guide vane profile and including a leading edge aligned with that of the vane; a downstream portion; and an intermediate portion including an upper surface extending between an upstream end point and a downstream end point. The upstream end point is separated from the leading edge of the arm by an axial distance of between 0.2c and 0.5c, c being the length of the axial chord of the vane, and the angle of the tangent to the upper surface at the upstream end point is equal to that at the downstream end point ±1 degree.
    Type: Grant
    Filed: February 9, 2016
    Date of Patent: October 19, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Henri-Marie Damevin, Philippe Jacques Pierre Fessou, Vianney Christophe Marie Maniere, Michael Franck Antoine Schvallinger
  • Patent number: 11143193
    Abstract: A refrigerant compressor according to an exemplary aspect of the present disclosure includes, among other things, an impeller arranged in a main flow path and including a plurality of vanes. The impeller is configured to rotate about an axis. A channel is outside the main flow path. A first orifice fluidly couples the channel to the main flow path upstream of the vanes, and a second orifice fluidly couples the channel to the main flow path downstream of leading edges of the vanes.
    Type: Grant
    Filed: July 18, 2019
    Date of Patent: October 12, 2021
    Inventors: Jin Yan, Lin Xiang Sun, Arnold Martin Schaefer, Ruiguo Gao
  • Patent number: 11141960
    Abstract: A part for an aircraft turbojet engine nacelle is made of a composite material and includes at least one outer face (S1), a fibrous preform including fiber locks and having a surface(s) delimiting depressions between fiber locks, a covering material which at least partially covers the surface(s) of the fibrous preform and in particular the depressions, and a matrix which binds entirely the covering material and the fibrous preform. The covering material is a fibrous mat and the outer face (S1) is smooth. A method for manufacturing such a part includes manufacturing the fibrous preform, providing a fibrous mat, depositing the fibrous preform and fibrous mat in a mold, dispersing the matrix between the fibers of the preform and mat and consolidating the fibrous preform and mat.
    Type: Grant
    Filed: August 29, 2019
    Date of Patent: October 12, 2021
    Assignees: Safran Nacelles, SAFRAN CERAMICS
    Inventors: Bertrand Desjoyeaux, Davi Silva De Vasconcellos, Aline Planckeel
  • Patent number: 11131209
    Abstract: A gas turbine engine, in particular an aircraft engine, including: a turbine connected via an input shaft device to a gearbox device having a sun gear, a planet carrier having a plurality of planet gears attached thereto, and a ring gear, the sun gear is connected to the input shaft device, the planet carrier or the ring gear is connected to a propulsive fan via an output shaft device of the gearbox device, with an inter-shaft bearing system being positioned radially between the input shaft device and the planet carrier of the gearbox device.
    Type: Grant
    Filed: June 20, 2019
    Date of Patent: September 28, 2021
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Luca Fontana, Mathias Hoefgen, Hana Jahic, Christoph Herzog, Patrick Felscher
  • Patent number: 11130582
    Abstract: Systems and methods of heat management of turbine engines including turbofans, turboprops and turboshafts and fan driven propulsion systems. The propulsion system may comprise a fan, nacelle, an electrical or mechanical heat source and a cooling system consisting of heat exchangers in the fan duct and on the nacelle and coolant pumps. The heat source can be a motor or a generator or turbine machinery or accessories rotationally coupled to rotating shafts. The heat management system transfers heat to the air in the fan flow path to provide additional fan thrust. The heat management system also transfers heat to structural members in the gas flow path that require anti-icing.
    Type: Grant
    Filed: August 3, 2018
    Date of Patent: September 28, 2021
    Assignees: ROLLS-ROYCE CORPORATION, ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES INC.
    Inventors: Alan Smith, Paul O'Meallie
  • Patent number: 11118507
    Abstract: A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan rotor having fan blades, and a plurality of fan exit guide vanes positioned downstream of the fan rotor. The fan rotor is configured to be driven through a gear reduction. A ratio of a number of fan exit guide vanes to a number of fan blades is defined. The fan exit guide vanes are provided with optimized sweep and optimized lean.
    Type: Grant
    Filed: May 6, 2020
    Date of Patent: September 14, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Jonathan Gilson, Bruce L. Morin, Ramons A. Reba, David A. Topol, Wesley K. Lord
  • Patent number: 11111030
    Abstract: A system which includes a first propeller, a second propeller, an electromagnetic field emitter that is coupled to the first propeller, and an electromagnetic field receptor that is coupled to the second propeller. The electromagnetic field emitter emits an electromagnetic field and in response to the electromagnetic field, the electromagnetic field receptor and the second propeller rotate in a first rotational direction and the electromagnetic field emitter and the first propeller rotate in a second and counter-rotational direction.
    Type: Grant
    Filed: January 15, 2021
    Date of Patent: September 7, 2021
    Assignee: Kitty Hawk Corporation
    Inventors: Sebastian Thrun, Christopher Scott Saunders, Benjamin Otto Berry
  • Patent number: 11111856
    Abstract: The turbofan engine can have a core engine, a bypass duct surrounding the core engine, an annular bypass flow path between the bypass duct and the core engine, and a plurality of core links extending across the bypass path and supporting the core engine relative to the bypass duct, and a fluid passage having a heat exchange portion in a given one of the core links, the heat exchange portion being configured for heat exchange with the bypass flow path, an inlet leading into the given core link and to the heat exchange portion, and an outlet extending from the heat exchange portion and out of the given core link.
    Type: Grant
    Filed: March 4, 2019
    Date of Patent: September 7, 2021
    Assignee: PRATT & WHITNEY CANADA CORP
    Inventor: Bryan William Olver
  • Patent number: 11085400
    Abstract: An integrated propulsion system according to an example of the present disclosure includes, among other things, components that include a gas turbine engine, a nacelle assembly and a mounting assembly, the system designed by a process comprising identifying two or more of internal structural loading requirements, external structural mount loading requirements, aerodynamic requirements, and acoustic requirements for the system, and interdependently designing said components to meet said requirements. The nacelle assembly includes a fan nacelle and an aft nacelle, the fan nacelle arranged at least partially about a fan and the engine, and the fan nacelle arranged at least partially about a core cowling to define a bypass flow path.
    Type: Grant
    Filed: January 23, 2019
    Date of Patent: August 10, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Christopher A. Eckett, Gabriel L. Suciu
  • Patent number: 11085398
    Abstract: A exhaust nozzle assembly comprises a nozzle that extends about an axial centerline and includes an exhaust nozzle flange; an radially inner surface that comprises an axially forward inner surface; a noise attenuating structure; a through hole inlet formed in the axially forward inner surface; a through hole outlet formed in the axially rear inner surface. The nozzle assembly also includes a radially outer surface that is radially separated from the radially inner surface by a nozzle cavity, where engine core air enters the nozzle cavity from the through hole inlet and exits the nozzle cavity axially downstream of the hole inlet via the through hole outlet.
    Type: Grant
    Filed: March 12, 2019
    Date of Patent: August 10, 2021
    Assignee: Rohr, Inc.
    Inventors: Michael Aten, Adam Saunders, Gary E. Bowman
  • Patent number: 11078845
    Abstract: A gas turbine engine assembly includes first and second annular members having different first and second thermal expansion coefficients connected together with dual arm V brackets. Brackets include first and second arms angularly spaced apart from a bracket centerline and extending axially away from bracket bases attached to a first one of the first and second annular members. Arms are attached to a second one of the first and second annular members. A turbine frame includes struts extending between outer and inner rings. An annular mixer and centerbody substantially made from a ceramic matrix composite materials is connected to and supported by the outer and inner rings with first and second sets respectively of the dual arm V brackets. Bracket bases of the first and second sets are attached to the outer and inner rings respectively. Arms of the first and second sets are attached to mixer and centerbody respectively.
    Type: Grant
    Filed: September 6, 2018
    Date of Patent: August 3, 2021
    Assignee: General Electric Company
    Inventors: Michael Anthony Ruthemeyer, Darrell Glenn Senile, Bernard James Renggli, Randy Lee Lewis
  • Patent number: 11078837
    Abstract: A gas turbine engine includes a compressor section, a combustor, and a turbine section. A bleed tap taps air from the compressor section through a bleed valve. The bleed valve is selectively opened by a control to dump air from the compressor section to a dump outlet. A heat exchanger duct includes a duct air inlet to cool a fluid in a heat exchanger and a duct air outlet. The dump outlet is within the heat exchanger duct.
    Type: Grant
    Filed: February 6, 2019
    Date of Patent: August 3, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Steven H. Zysman, Karl D. Blume, James H. Anderson, Holly Teufel, Jesse W. Clauson, Xiaojun Campbell, William O. Taylor, Graham A. Kaiser, Karl Milenkovic, Michael C. Rhodes, Tsering Dolma
  • Patent number: 11073085
    Abstract: An intercooled cooling system for a gas turbine engine is provided. The intercooled cooling system includes a plurality of cooling stages in fluid communication with an air stream utilized for cooling. A first cooling stage of the plurality of cooling stages is fluidly coupled to a bleed port of a compressor of the gas turbine engine to receive and cool bleed air with the air stream to produce a cool bleed air. The intercooled cooling system also includes a pump fluidly coupled to the first cooling stage to receive the cool bleed air and increase a pressure of the cool bleed air to produce a pressurized cool bleed air. A second cooling stage of the plurality of cooling stages is fluidly coupled to the pump to receive and cool the pressurized cool bleed air to produce an intercooled cooling air, which is provided to the gas turbine engine.
    Type: Grant
    Filed: November 8, 2016
    Date of Patent: July 27, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Joseph B. Staubach, Nathan Snape
  • Patent number: 11073105
    Abstract: Aspects of the disclosure are directed to a fan ramp for use in a thrust reverser portion of a nacelle of a gas turbine engine, the fan ramp extending circumferentially about an axial fan ramp centerline. The fan ramp comprises a fan ramp forward edge disposed proximate an aft end of a fan case, the fan case at least partially surrounding a fan section of the gas turbine engine. The fan ramp also includes noise attenuating structure at a forward section of the fan ramp forward of a torque box.
    Type: Grant
    Filed: October 2, 2018
    Date of Patent: July 27, 2021
    Assignee: Rohr, Inc.
    Inventors: Bryce T. Kelford, Pablo T. Sanz Martinez, Jose S. Alonso-Miralles