Engine Driven Patents (Class 416/129)
  • Patent number: 12187403
    Abstract: A tapered counter rotating propeller hub assembly for a stern drive marine propulsion assembly. The propeller hub assembly having aligned forward and aft tapered hubs with a predetermined slope.
    Type: Grant
    Filed: November 12, 2021
    Date of Patent: January 7, 2025
    Inventor: Ken Konrad
  • Patent number: 12145734
    Abstract: A hybrid propulsion system can include a turbomachine having a compressor, a combustion chamber, and a compressor turbine. The compressor can be connected to the compressor turbine via a first shaft. The system can include a hybrid drive assembly which can include a power turbine in fluid communication with an outlet of the compressor turbine to be driven by compressor turbine exhaust to drive a second shaft that is disconnected from the first shaft. The hybrid drive assembly can also include an electrical machine mechanically coupled to the second shaft either to convert rotational energy to electrical energy or to convert electrical energy to rotational energy of the second shaft.
    Type: Grant
    Filed: December 28, 2020
    Date of Patent: November 19, 2024
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Leo J. Veilleux, Jr., Lubomir A. Ribarov
  • Patent number: 12146554
    Abstract: A counter rotating gear case. The counter rotating gear case may include a forward gear assembly; an aft gear assembly; a pinion gear assembly; a spool adapter having a first portion and a second portion, wherein the forward gear assembly, the aft gear assembly, and pinion gear assembly may be supported on the second portion of the spool adapter; and wherein, the pinion gear assembly may be disposed between the forward gear assembly and the aft gear assembly, and wherein the pinion gear assembly may be operatively engaged with both the forward gear assembly and the aft gear assembly, such that rotation of one of the forward gear assembly or the aft gear assembly in one direction causes rotation of the other of the forward gear assembly or the aft gear assembly in a second direction opposite that of the first direction.
    Type: Grant
    Filed: October 24, 2022
    Date of Patent: November 19, 2024
    Inventor: Michael C. Glaum
  • Patent number: 12103697
    Abstract: An aircraft includes a fuselage having a top surface opposite a bottom surface, a front section, a center section, and a rear section. A first mounting rod and a second mounting rod are coupled to the top surface. The first mounting rod and the second mounting rod are single rods. A first and a second wing are coupled to the center section. A plurality of power generator systems are coupled to the first mounting rod or the second mounting rod. Each power generator system includes a power source, a first propeller and a second propeller. The power source is configured to drive the first propeller and the second propeller. The first propeller and the second propeller have an axis of rotation, and are pivotable between a first position and a second position. A shroud encloses the power generator system.
    Type: Grant
    Filed: January 10, 2022
    Date of Patent: October 1, 2024
    Assignee: HELENG INC.
    Inventor: Jack Ing Jeng
  • Patent number: 12097940
    Abstract: The present invention relates to rotating equipment, and more specifically, to high efficiency rotating equipment which generates thrust through contra-rotating or produces electricity. The rotating equipment includes: a plurality of propeller modules (10, 20) including a plurality of blades (11, 21) installed inside along a circumferential direction; and a rotary module (40) which rotates the plurality of propeller modules (10, 20) or is rotated.
    Type: Grant
    Filed: March 28, 2022
    Date of Patent: September 24, 2024
    Assignee: VAM CO., LTD.
    Inventor: Dohyun Kang
  • Patent number: 12092020
    Abstract: Counter-rotating turbine of a turbomachine extending about an axis of rotation and comprising an inner rotor rotating about the axis of rotation, and comprising at least one inner movable blade rotatably supported by a first shaft, an outer rotor rotating about the axis of rotation in a direction opposite to the inner rotor, and comprising at least one outer movable blade rotatably supported by a second shaft coaxial with the first shaft, the first and second shafts extending axially from upstream to downstream of the turbine, wherein the first shaft is guided in rotation by a first bearing disposed between the first shaft and an upstream casing of the turbine, and the second shaft is guided in rotation by a second bearing disposed between the second shaft and said upstream casing of the turbine.
    Type: Grant
    Filed: April 2, 2020
    Date of Patent: September 17, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventor: Francois Gallet
  • Patent number: 12071889
    Abstract: A turbine section and an exhaust section for a gas turbine engine includes a low pressure (LP) turbine having first stage LP turbine blades that rotate in a first direction at a first speed, and final stage LP turbine blades downstream of the first stage LP turbine blades that rotate in a second direction opposite the first direction at a second speed. The second speed is lower than the first speed.
    Type: Grant
    Filed: April 5, 2022
    Date of Patent: August 27, 2024
    Assignees: General Electric Company, General Electric Deutschland Holding GmbH, GE Avio Srl
    Inventors: Paul Hadley Vitt, Lyle Douglas Dailey, Matteo Renato Usseglio, Andreas Peters, Jonathan Ong
  • Patent number: 12049848
    Abstract: The invention relates to a planetary gearbox in a gas turbine engine wherein a plurality of planetary gears are each mounted on a planetary gear bearing journal by a slide bearing, characterized in that a bushing is arranged in an inner bore of at least one planetary gear, which bushing spatially separates the sliding surface of the slide bearing from the inner bore of the planetary gear and the bushing is designed as a replacement part, in particular as a sacrificial part. The invention also relates to a gas turbine engine.
    Type: Grant
    Filed: October 7, 2020
    Date of Patent: July 30, 2024
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Michael Gräber, Greg Blake
  • Patent number: 12044183
    Abstract: An example gas turbine engine includes a propulsor assembly consisting of a propulsor and a first turbine. An epicyclic gear train defines a gear reduction ratio of greater than 2.3. A weight of the propulsor assembly is less than 40 percent of a total weight of the gas turbine engine, excluding any nacelle. A first spool includes a first shaft that connects a first compressor and the first turbine. The first shaft drives the propulsor through the gear train to drive the propulsor at a lower speed than the first spool. A second spool includes a second shaft connecting a second compressor and a second turbine. A weight of the propulsor is greater than a weight of the first turbine.
    Type: Grant
    Filed: May 16, 2023
    Date of Patent: July 23, 2024
    Assignee: RTX CORPORATION
    Inventors: Frederick M. Schwarz, Gabriel L. Suciu
  • Patent number: 12017762
    Abstract: A coaxial rotor system includes a center mast non-rotatably disposed at and extending from a helicopter. A rotation axis extends along the center mast. An inner mast is disposed along the center mast and is rotatable about the rotation axis in a first direction. A portion of the inner mast extends above an end of the center mast. An outer mast circumscribes the center mast and is rotatable about the rotation axis in an opposite second direction. The center mast extends above an end of the outer mast. An upper rotor blade assembly is rotatable with the inner mast. A lower rotor blade assembly is rotatable with the outer mast. A control system disposed at the center mast between the upper and lower rotor blade assemblies is operable to adjust pitch of a plurality of upper rotor blades and to adjust pitch of a plurality of lower rotor blades.
    Type: Grant
    Filed: April 4, 2023
    Date of Patent: June 25, 2024
    Assignee: Eagle Technologies, LLC
    Inventors: John P. Benner, Michael D. Bartley, Cary A. Kravets, Bruce E. Bailey
  • Patent number: 12012891
    Abstract: A turboprop powered aircraft having a cowling or nacelle surrounding the engine, said cowling incorporates an air inlet and internal ducting to the engine wherein the inlet incorporated anti icing ducts, said inlet shape has a closed oval or other non-circular shape that is not coaxial to the engine propeller drive shaft. Inlet anti-icing heating duct means are provided for channeling a portion of the engines exhaust to the interior of the inlet rim. A further improvement in inlet efficiency can be achieved by reducing the thickness of the inlet cross-section, but this results in less space available for the hot exhaust connections. To provide for the inlet reduced section thickness, the exhaust flow connections also incorporate reduced thickness sections to facilitate cooling and insulation of the adjacent cowling and inlet duct surfaces from the excessive heat associated with the hot exhaust gas connection.
    Type: Grant
    Filed: May 17, 2022
    Date of Patent: June 18, 2024
    Assignee: AMERICAN AVIATION, Inc
    Inventors: Stephen R. Speer, Alexlander J. Duncan, Jayme S. Bartlett, George R. Kemner
  • Patent number: 11982238
    Abstract: A gas turbine engine may include a high speed spool, a low speed spool, a first epicyclic gear system, and a second epicyclic gear system. Generally, the high speed spool mechanically connects a high pressure turbine to a high pressure compressor, and the low speed spool mechanically connects a low pressure turbine to at least one of a fan and a prop via the first epicyclic gear system and to a low pressure compressor via the second epicyclic gear system, according to various embodiments. The first epicyclic gear system and the second epicyclic gear system may include a common sun gear shaft.
    Type: Grant
    Filed: August 4, 2022
    Date of Patent: May 14, 2024
    Assignee: RTX CORPORATION
    Inventors: William G. Sheridan, Michael E. McCune
  • Patent number: 11976630
    Abstract: Disclosed is a method of monitoring relative blade pitch angle alignment of a set of at least two rotor blades in a rotary device. The rotary device may be a wind turbine generator. Also disclosed are operational schemes based on the observed relative blade pitch angle alignments.
    Type: Grant
    Filed: March 10, 2020
    Date of Patent: May 7, 2024
    Assignee: Ventus Engineering GmbH
    Inventors: Poul Anker Skaarup Lübker, Shavkat Mingaliev, Xavier Tolron
  • Patent number: 11975834
    Abstract: A high rise building escape drone is shown and described. The high rise building escape drone includes of a frame. The frame has a spine secured to an upper housing. The upper housing secures a motor and a CPU operably connected to the motor. The motor is rotatably coupled to at least one propeller. A seat is secured to the spine below the upper housing. A control panel is secured to the seat. The control panel is operably coupled to the CPU and is capable to control the drone. A plurality of feet are secured to a bottom of the spine such that the feet support the drone.
    Type: Grant
    Filed: January 20, 2021
    Date of Patent: May 7, 2024
    Inventor: Jaffer Shurie
  • Patent number: 11970279
    Abstract: A control system and methods for controlling the position of one or more engine-mounting links of an engine-mounting linkage system are provided. In one aspect, an engine-mounting linkage system includes one or more engine-mounting links that each have an adjustable inclination angle. An inclination angle of a link may be adjusted by an actuator of the control system. One or more controllers of the control system can control the actuator and thus the inclination angle of the link by determining a control command based at least in part on an output received from one or more sensors of the control system. The controllers can then cause the actuator to change the inclination angle of the link based at least in part on the determined control command.
    Type: Grant
    Filed: February 21, 2020
    Date of Patent: April 30, 2024
    Assignee: General Electric Company
    Inventors: Timothy Leo Schelfaut, Anthony Michael Metz, Jonathan Edward Coleman, Thomas P. Joseph
  • Patent number: 11970956
    Abstract: A gas turbine engine including: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order; a fan defining a fan axis and comprising a plurality of fan blades rotatable about the fan axis; and a pitch change mechanism operable with the plurality of fan blades, the pitch change mechanism including a plurality of linkages, the plurality of linkages including a first linkage coupled to a first fan blade of the plurality of fan blades and a second linkage coupled to a second fan blade of the plurality of fan blades; and a non-uniform blade actuator system operable with one or more of the plurality of linkages to control a pitch of the first fan blade relative to a pitch of the second fan blade.
    Type: Grant
    Filed: December 27, 2022
    Date of Patent: April 30, 2024
    Assignee: General Electric Company
    Inventors: Abhijeet Jayshingrao Yadav, Nicholas Joseph Kray, Nitesh Jain, Ricardo Hernandez Pandeli
  • Patent number: 11945610
    Abstract: A drone or an aircraft for personal air mobility includes at least one horizontal planar structure having four ducted propeller rotors with vertical axis, which are substantially coplanar with each other. Each of the rotors has a rotating ring rotatably mounted within a circular opening. The rotating ring is configured as to define an annular wall for ducting of air flow produced by the rotor. Each of the rotors has one or more blades which extend towards the central axis of the rotor, and have tips terminating at a distance from the axis of the propeller, such that each rotor is an annular propeller. The rotating ring of each rotor is controlled by an actuator.
    Type: Grant
    Filed: June 23, 2020
    Date of Patent: April 2, 2024
    Assignee: INTERACTIVE FULLY ELECTRICAL VEHICLES S.R.L.
    Inventors: Pietro Perlo, Davide Penserini
  • Patent number: 11932427
    Abstract: Provided is an unmanned aircraft which is capable of stably taking off. In one example, the unmanned aircraft has an aircraft body which includes an information acquisition device, a plurality of rotary wings, and a protective member disposed around the rotary wings. Each of the rotary wings has a rotation axis which is tilted with respect to a vertical direction by a given angle, such that the rotary wings generate a forward thrust force. The aircraft body has a lower edge which includes a middle lower edge and a forward lower edge, wherein the protective member has a lower edge including the forward lower edge. The forward lower edge is located above the middle lower edge, and the forward lower edge has a rear end located backward of a rear end of the rotary wing.
    Type: Grant
    Filed: August 16, 2021
    Date of Patent: March 19, 2024
    Assignees: ACSL Ltd., NIS Co., Ltd.
    Inventors: Soki Kuga, Yusuke Inagaki, Patrik Ken Takeuchi
  • Patent number: 11884386
    Abstract: A multi-rotor system for providing air thrust is disclosed comprising at least one multi-rotor assembly. The multi-rotor assembly comprising at least two rotors rotatable about a common axis wherein the outer radius of a first rotor is substantially similar to the inner radius of the second rotor. An airborne vehicle is also disclosed that is adapted to perform vertical takeoff and landing (VTOL). The airborne vehicle comprising at least two multi-rotor system disposed substantially symmetrically around the center of gravity of the vehicle.
    Type: Grant
    Filed: April 28, 2021
    Date of Patent: January 30, 2024
    Assignee: N.M.B. MEDICAL APPLICATIONS LTD
    Inventors: Oren Globerman, Mordechay Beyar
  • Patent number: 11885267
    Abstract: A gas turbine engine includes a fan assembly having a plurality of fan blades; and a turbomachine. The turbomachine includes a compressor section, a combustion section, and a turbine section in serial flow order. The turbomachine further including a first input power source; a second input power source configured to counter-rotate relative to the first input power source; a power output component operably connected to the fan assembly; and a gear assembly located forward of the combustion section of the turbomachine, the gear assembly configured to receive power from the first input power source and the second input power source and provide power to the power output component, the gear assembly comprising a helical gear.
    Type: Grant
    Filed: January 19, 2022
    Date of Patent: January 30, 2024
    Assignee: GE Avio S.r.l.
    Inventors: Paolo Altamura, Michele Gravina
  • Patent number: 11851158
    Abstract: A variable pitch fan assembly includes a plurality of rotating trunnion assemblies, a plurality of counterweight assemblies, a first unison ring gear engaged with the trunnion assemblies, and a second unison ring member that restricts out of synch movement of the counterweights relative to each other.
    Type: Grant
    Filed: November 21, 2022
    Date of Patent: December 26, 2023
    Assignee: General Electric Company
    Inventor: Daniel A. Niergarth
  • Patent number: 11821492
    Abstract: A transmission having a housing (18), at least a first input (20) rotatable about a first input axis (IA1), and at least a first output (26) rotatable about a first output axis (OA1). The transmission further includes a first outer side gear (14) connected to and drivable by the first input, a first planet gear set comprising a first inner planet gear (11) and a first outer planet gear (15) with the inner and outer planet gears being rigidly connected to, and in axial alignment with, one another. The first planet gear set is rotatable (22, 24) via the first outer side gear and is also rotatable (23) about the first output axis. The transmission further includes a second outer side gear (16) in mesh with the first outer planet gear, and a second inner side gear (12) connected to the first output and being rotatable about the first output axis via the first inner planet gear.
    Type: Grant
    Filed: January 14, 2021
    Date of Patent: November 21, 2023
    Assignee: THE GLEASON WORKS
    Inventor: Hermann J. Stadtfeld
  • Patent number: 11814154
    Abstract: A method of operating an aircraft engine coupled to a wing of an aircraft including: setting a pitch of a plurality of rotor blades of a rotor assembly of the aircraft engine at non-uniform pitch angles along a circumferential direction of the aircraft engine such that the plurality of rotor blades define a first pitch at a first position and a second pitch at a second position, wherein the second position is 180 degrees offset from the first position, and wherein the first pitch is different from the second pitch.
    Type: Grant
    Filed: July 22, 2021
    Date of Patent: November 14, 2023
    Assignee: General Electric Company
    Inventors: Brendan Michael Freely, Kurt David Murrow, Michael James McMahon
  • Patent number: 11787551
    Abstract: An electric propulsion system for a vertical takeoff-and-landing aircraft having an inverter assembly, a gearbox assembly, an electric motor assembly. The inverter assembly, the gearbox assembly, and the electric motor assembly may be substantially aligned along an axis. The inverter assembly, a gearbox assembly, and electric motor assembly may each abut at least one of the others. The electric engine may use a liquid, such as oil, for cooling and lubricating components of the inverter assembly, gearbox assembly, and electric motor assembly. Further, the electric engine may use volumes of oil for cooling and lubricating components below a threshold volume so that the electric engines do not require a fire protective barrier.
    Type: Grant
    Filed: December 28, 2022
    Date of Patent: October 17, 2023
    Assignee: Archer Aviation, Inc.
    Inventors: Scott Graves, Alan D. Tepe, Robert Wayne Moore
  • Patent number: 11761380
    Abstract: A turbofan gas turbine engine includes, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, and a turbine module. The fan assembly includes a plurality of fan blades defining a fan diameter, and the heat exchanger module is in fluid communication with the fan assembly by an inlet duct. The heat exchanger module includes a plurality of heat transfer elements for transfer of heat from a first fluid contained within the heat transfer elements to an airflow passing over a surface of the heat transfer elements prior to entry of the airflow into an inlet to the fan assembly. At full-power condition, the engine produces a maximum thrust T (N), the heat exchanger module transfers a maximum heat rejection H (W) from the first fluid to the airflow, and a Heat Exchanger Performance parameter PEX (W/N) defined as PEX=H/T is 0.4 to 6.0.
    Type: Grant
    Filed: September 24, 2021
    Date of Patent: September 19, 2023
    Assignee: ROLLS-ROYCE plc
    Inventors: Natalie C Wong, Thomas S Binnington, David A Jones, Daniel Blacker
  • Patent number: 11719161
    Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a propulsor section, a geared architecture, a high spool and a low spool. The high spool includes a high pressure compressor and a high pressure turbine. The low spool includes a low pressure compressor and a low pressure turbine. At least one stage of the turbine section includes an array of rotatable blades and an array of vanes. A ratio of the number of vanes to the number blades is greater than or equal to 1.55. A mechanical tip rotational Mach number of the blades is greater than or equal to 0.5 at an approach speed.
    Type: Grant
    Filed: September 29, 2021
    Date of Patent: August 8, 2023
    Assignees: RAYTHEON TECHNOLOGIES CORPORATION, MTU AERO ENGINES AG
    Inventors: Bruce L. Morin, David A. Topol, Detlef Korte
  • Patent number: 11692457
    Abstract: A turbomachine, a computing system for a turbomachine, and a method for overspeed protection are provided. The turbomachine includes a first rotor assembly interdigitated with a second rotor assembly together operably coupled to a gear assembly. A plurality of sensors is configured to receive rotor state data indicative of one or more of a speed, geometric dimension, or capacitance, or change thereof, or rate of change thereof, relative to the first rotor assembly or the second rotor assembly. A controller executes operations including receiving rotor state data from the plurality of sensors; comparing rotor state data to one or more rotor state limits; and contacting one or more of the first rotor assembly or the second rotor assembly to a contact surface adjacent to the respective first rotor assembly or the second rotor assembly if the rotor state data exceeds the rotor state limit.
    Type: Grant
    Filed: September 10, 2021
    Date of Patent: July 4, 2023
    Assignees: General Electric Company, GE Avio S.r.l.
    Inventors: Roberto Maddaleno, Antonio Giuseppe D'Ettole, Matteo Renato Usseglio, Alessandra Torri, Darek Tomasz Zatorski
  • Patent number: 11649767
    Abstract: A turbofan gas turbine engine includes, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, a turbine module, and an exhaust module. The fan assembly includes a plurality of fan blades defining a fan diameter (D). The heat exchanger module is in fluid communication with the fan assembly by an inlet duct, and the heat exchanger module includes a plurality of radially-extending hollow vanes arranged in a circumferential array with a channel extending axially between each pair of adjacent hollow vanes. An airflow entering the heat exchanger module is divided between a set of vane airflows through each of the hollow vanes and a set of channel airflows through each of the channels.
    Type: Grant
    Filed: September 24, 2021
    Date of Patent: May 16, 2023
    Assignee: ROLLS-ROYCE plc
    Inventors: Stephen J Bradbrook, Martin N Goodhand, Paul M Hield, Andrew Parsley, Natalie C Wong, Robert J Corin, Thomas S Binnington
  • Patent number: 11614036
    Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor including a circumferential array of blades, a low pressure compressor section including a low pressure compressor section inlet with a low pressure compressor section inlet annulus area and a low pressure turbine section. The low pressure turbine section includes a maximum gas path radius, the blades include a maximum radius, and a ratio of the maximum gas path radius to the maximum radius of the blades is equal to or greater than 0.35, and is less than 0.55.
    Type: Grant
    Filed: November 19, 2021
    Date of Patent: March 28, 2023
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Paul R. Adams, Shankar S. Magge, Joseph B. Staubach, Wesley K. Lord, Frederick M. Schwarz, Gabriel L. Suciu
  • Patent number: 11614097
    Abstract: The present disclosure is directed to providing impeller type oil transportation device including; a transport unit provided such that a mixed fluid including an oil is fed on one side; and an impeller provided in the transport unit, the impeller including a core connected to a rotation axis, and wings extending radially from the core and having hydrophilic teeth on an outer surface to transport the mixed fluid including the oil to the other side of the transport unit by rotation, wherein the impeller is provided in the transport unit such that parts of the wings are exposed above a surface of the mixed fluid, to separate the oil adhered to the teeth while the mixed fluid is fed into a space between the adjacent teeth by capillary flow when the wings exposed above the surface of the mixed fluid move on to the mixed fluid by the rotation.
    Type: Grant
    Filed: March 17, 2022
    Date of Patent: March 28, 2023
    Assignee: KOREA INSTITUTE OF SCIENCE AND TECHNOLOGY
    Inventors: Seong-Jin Kim, Myoung-Woon Moon, Young-jin Lee, Seo-Hyun Cho
  • Patent number: 11549463
    Abstract: Methods, apparatus, systems and articles of manufacture for compact compressors are disclosed including a gas turbine engine defining an axial direction and a radial direction, the gas turbine engine including an axial flow compressor and a radial flow compressor, wherein the axial flow compressor is located axially forward of the radial flow compressor, a blade assembly including a splitter shroud to divide incoming air into axial air flow for the axial flow compressor and radial air flow for the radial flow compressor, the blade assembly rotating relative to the axial flow compressor and counter-rotating relative to the radial flow compressor, and wherein the blade assembly is located axially aft of the radial flow compressor.
    Type: Grant
    Filed: February 22, 2021
    Date of Patent: January 10, 2023
    Assignee: General Electric Company
    Inventors: Vinod Shashikant Chaudhari, Bhaskar Nanda Mondal, Tsuguji Nakano, David W. Crall
  • Patent number: 11524777
    Abstract: A blade pitch control system includes a plurality of serially stacked swashplate assemblies, each having concentric, ring-shaped inner and outer sections, an associated output pitch link coupled to its outer section and an associated input pitch link coupled to its inner section. The inner and outer sections of each swashplate assembly includes pass through holes to accommodate input pitch links and output pitch links of adjacent ones of the stacked swashplate assemblies. The system also includes a plurality of actuators, each coupled to a respective input pitch link of a respective one of the stacked swashplate assemblies. A central static mast accommodates a rotor drive shaft and the stacked swashplate assemblies are configured to slide axially, parallel to a long axis of the static mast.
    Type: Grant
    Filed: August 19, 2020
    Date of Patent: December 13, 2022
    Assignee: Kinetic Analytics LLC
    Inventors: Neil Rohin Gupta, Terry Buelna
  • Patent number: 11486311
    Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, a fan including an array of fan blades rotatable about an engine axis, a compressor including a high pressure compressor section and a low pressure compressor section, the low pressure compressor section including a low pressure compressor section inlet with a low pressure compressor inlet annulus area, a fan duct including a fan duct annulus area outboard of the low pressure compressor section inlet, and a turbine having a high pressure turbine section and a low pressure turbine section driving the fan through a speed reduction mechanism, wherein the low pressure turbine section defines a maximum gas path radius and the fan blades define a maximum radius, and a ratio of the maximum gas path radius to the maximum radius of the fan blades is less than 0.6.
    Type: Grant
    Filed: April 14, 2021
    Date of Patent: November 1, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Paul R. Adams, Shankar S. Magge, Joseph B. Staubach, Wesley K. Lord, Frederick M. Schwarz, Gabriel L. Suciu
  • Patent number: 11480108
    Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, a fan including a circumferential array of fan blades, a compressor in fluid communication with the fan, the compressor including a low pressure compressor section and a high pressure compressor section, the low pressure compressor section including a low pressure compressor section inlet with a low pressure compressor section inlet annulus area, a fan duct including a fan duct annulus area outboard of the a low pressure compressor section inlet, a turbine in fluid communication with the combustor, the turbine having a high pressure turbine section and a low pressure turbine that drives the fan, a speed reduction mechanism coupled to the fan and rotatable by the low pressure turbine section to allow the low pressure turbine section to turn faster than the fan, wherein the low pressure turbine section includes a maximum gas path radius and the fan blades include a maximum radius, and a ratio of the maximum gas pat
    Type: Grant
    Filed: April 14, 2021
    Date of Patent: October 25, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Paul R. Adams, Shankar S. Magge, Joseph B. Staubach, Wesley K. Lord, Frederick M. Schwarz, Gabriel L. Suciu
  • Patent number: 11459074
    Abstract: A method is for making a marine drive for propelling a marine vessel in water. The method includes providing a gearcase; installing a propeller shaft assembly that extends forwardly from the gearcase; coupling front and rear propellers to the propeller shaft assembly, forwardly of the gearcase, such that rotation of the propeller shaft assembly causes rotation of the front and rear propellers, respectively, which thereby propels the marine vessel in the water; and reducing deleterious effects of cavitation on the gearcase by the combination of forming the gearcase with a wide trailing end portion, in particular to maintain pressure alongside the gearcase, and configuring the front and rear propellers so that the front propeller absorbs more torque/thrust load than the rear propeller during said rotation.
    Type: Grant
    Filed: August 24, 2020
    Date of Patent: October 4, 2022
    Assignee: Brunswick Corporation
    Inventors: John O. Scherer, III, Roger E. Koepsel, Andrew C. Gunderson
  • Patent number: 11414178
    Abstract: A boundary layer ingestion fan system for location aft of the fuselage of an aircraft is shown. It comprises a nacelle defining a duct, and a fan located within the duct. The fan comprises a hub arranged to rotate around a rotational axis (A-A) and a plurality of blades attached to the hub. A blade blockage, which is the ratio of the blade thickness to the product of the circumferential pitch and the cosine of a blade inlet angle (t/s·cos?1), is 0.25 or greater at the 0 percent span position.
    Type: Grant
    Filed: November 4, 2019
    Date of Patent: August 16, 2022
    Inventor: Martin N. Goodhand
  • Patent number: 11396370
    Abstract: A coaxial rotor system for a rotorcraft includes a mast, a top rotor assembly and a bottom rotor assembly. The top rotor assembly is coupled to the distal end of the mast. The bottom rotor assembly includes a motor configured to provide rotational energy to the mast, thereby rotating the top rotor assembly. The bottom rotor assembly experiences a torque reaction force responsive to the motor rotating the mast such that the top and bottom rotor assemblies counter rotate.
    Type: Grant
    Filed: March 19, 2020
    Date of Patent: July 26, 2022
    Assignee: Textron Innovations Inc.
    Inventor: Guy Bernard
  • Patent number: 11364991
    Abstract: An aircraft propulsion system comprises first and second co-axial propulsors, one of the first and second propulsor being positioned forward of the other propulsor. A first electric motor is configured to drive the first propulsor, and a second electric motor is configured to drive the second propulsor. The first electric motor comprising a rotor radially inwardly of the stator, and the second electric motor comprises a rotor radially outwardly of the stator. The stator of the first electric motor is mounted to the stator of the second electric motor.
    Type: Grant
    Filed: August 21, 2019
    Date of Patent: June 21, 2022
    Inventor: Giles E. Harvey
  • Patent number: 11326467
    Abstract: A turbine engine includes integrated electric machines in the compressor section and the turbine section to supplement power produced from fuel with electric power. The compressor section includes a compressor electric motor that is electrically coupled to a compressor generator. The example turbine section includes a turbine electric motor that is coupled to a geared architecture to supplement power driving the fan section. A turbine generator driven by a portion of the turbine section provides electric power to the turbine electric motor.
    Type: Grant
    Filed: June 12, 2020
    Date of Patent: May 10, 2022
    Assignee: Raytheon Technologies Corporation
    Inventors: Daniel Bernard Kupratis, Zubair Ahmed Baig, Gary Collopy, Coy Bruce Wood
  • Patent number: 11300003
    Abstract: An unducted thrust producing system has a rotating element with an axis of rotation and a stationary element. The rotating element includes a plurality of blades, each having a blade root proximal to the axis, a blade tip remote from the axis, and a blade span measured between the blade root and the blade tip. The rotating element has a load distribution such that at any location between the blade root and 30% span the value of ?RCu in the air stream is greater than or equal to 60% of the peak ?RCu in the air stream.
    Type: Grant
    Filed: December 28, 2018
    Date of Patent: April 12, 2022
    Assignee: General Electric Company
    Inventors: Andrew Breeze-Stringfellow, Syed Arif Khalid, Leroy Harrington Smith, Jr.
  • Patent number: 11220330
    Abstract: A mechanical system for transmitting rotary motion between firstly at least one inlet wheel driven in rotation by at least one engine, each inlet wheel being suitable for being driven in rotation by a corresponding dedicated engine, and secondly at least two distinct driven shafts of an accessory box, the at least one engine serving to drive rotation of one of the at least two driven shafts in isolation, or to drive the at least two driven shafts simultaneously, jointly with at least one aircraft rotor, the mechanical system including a selective rotary drive member that is movable axially between two distinct drive positions.
    Type: Grant
    Filed: September 11, 2017
    Date of Patent: January 11, 2022
    Assignee: AIRBUS HELICOPTERS
    Inventor: Olivier De Meerschman
  • Patent number: 11203413
    Abstract: Embodiments of the invention relate to advanced propeller assemblies that include a pressure modifying element that modifies its aerodynamic characteristics. Embodiments of the invention may provide benefits including but not limited to: increased thrust per rotation, greater efficiency, modified aerodynamics, and the ability to use such propellers for novel applications. Practical applications for embodiments of propellers of the invention include use with aircraft, drones, watercraft, autogyros, fans, blowers, pumps, generators, compressors, mixers, and blenders.
    Type: Grant
    Filed: November 6, 2019
    Date of Patent: December 21, 2021
    Assignee: N99 LLC
    Inventors: Henry Joyner Gold, Steven Kenneth Gold
  • Patent number: 11118506
    Abstract: A gear assembly for a turbo machine is provided. The gear assembly includes a first input shaft, a second input shaft, an output shaft, a fixed member, and a spindle. The spindle is extended along a spindle centerline axis. The first input shaft is drivingly connected to the spindle at a first interface. The second input shaft is drivingly connected to the spindle at a second interface. The spindle is connected to the fixed member providing a reactive force at a third interface. The spindle is connected to the output shaft at a fourth interface.
    Type: Grant
    Filed: December 21, 2018
    Date of Patent: September 14, 2021
    Assignee: General Electric Company
    Inventor: Bhaskar Nanda Mondal
  • Patent number: 11098678
    Abstract: A boundary layer ingestion engine includes a fan section configured to extend into a boundary layer of a full annulus of an aft end of a fuselage of an aircraft. The fan section includes a first fan stage and a second fan stage. The boundary layer ingestion engine also includes a differential planetary gear system is operable to transform rotation of an input shaft into counter rotation of a first shaft coupled to the first fan stage and a second shaft coupled to the second fan stage. The boundary layer ingestion engine further includes a motor operable to drive rotation of the input shaft.
    Type: Grant
    Filed: April 5, 2018
    Date of Patent: August 24, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Gabriel L. Suciu, Jesse M. Chandler
  • Patent number: 11053812
    Abstract: A fan for a gas turbine engine is provided. The fan includes a plurality of fan blades, a disk, and a trunnion mechanism for attaching the fan blades to the disk. The disk can be formed of a plurality of individual disk segments, with the trunnion mechanism attaching one of the plurality of fan blades to a respective disk segment. A retention member is also provided. The retention member includes a means for catching a portion of the trunnion mechanism should a primary attachment system of the trunnion mechanism fail.
    Type: Grant
    Filed: August 22, 2018
    Date of Patent: July 6, 2021
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Brandon Wayne Miller, Ian Francis Prentice, Daniel Alan Niergarth
  • Patent number: 10889362
    Abstract: A strut mounted gear box for counter rotating propellers. The gear box is strut mounted for securement to the hull of a boat. A main input shaft is coupled to a propulsion component of a boat with a distal end secured to an idler gear cage assembly located within the gear box. The main input shaft transfers torque and rotation from the propulsion component to an idler gear cage assembly. An inner tail shaft is coupled to the main input shaft and arranged to rotate the inner tail shaft in a first direction. A counter shaft is coupled to the idler gear cage assembly and arranged to rotate the counter shaft in a second direction. A first propeller is secured to the inner tail shaft providing rotation in the first direction; and a second propeller is secured to the counter shaft allowing rotation in the second direction.
    Type: Grant
    Filed: June 22, 2017
    Date of Patent: January 12, 2021
    Inventor: Peter R. Stolper
  • Patent number: 10815881
    Abstract: The present disclosure is directed to a gas turbine engine including a turbine section including a first rotating component interdigitated along a longitudinal direction with a second rotating component. The first rotating component and the second rotating component are each coupled to a speed reduction assembly in counter-rotating arrangement. The first rotating component comprising an outer shroud and a plurality of outer shroud airfoils extended inward along a radial direction from the outer shroud. A connecting member couples the outer shroud to a radially extended first rotor. The second rotating component comprising an inner shroud and a plurality of inner shroud airfoils extended outward along the radial direction from the inner shroud, the plurality of inner shroud airfoils in alternating arrangement along the longitudinal direction with the plurality of outer shroud airfoils.
    Type: Grant
    Filed: September 20, 2017
    Date of Patent: October 27, 2020
    Assignee: General Electric Company
    Inventors: Jeffrey Donald Clements, Darek Tomasz Zatorski, Alan Roy Stuart
  • Patent number: 10815888
    Abstract: A geared turbofan gas turbine engine includes a fan section and a core section. The core section includes a compressor section, a combustor section and a turbine section. The fan section includes a gearbox and a fan. A low spool includes a low turbine within the turbine section and a forward connection to a gearbox for driving the fan. The low spool is supported for rotation about the axis at a forward most position by a forward roller bearing and at an aft position by a thrust bearing.
    Type: Grant
    Filed: April 3, 2018
    Date of Patent: October 27, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Brian D. Merry, Gabriel L. Suciu
  • Patent number: 10800520
    Abstract: The present invention relates to a device for controlling the yaw of an aviation device, such as a helicopter, said aviation device comprising a bearing structure and a rotating member connected to the bearing structure to be mobile in rotation, around an axis of rotation, relative to said bearing structure, wherein the rotating member comprises fixing means for fixing at least one blade, the yaw control device comprising a rotor and a stator which form, in combination, an electrical machine, wherein the bearing structure is connected to the first of this stator and this rotor, and wherein the rotating member is connected to the second of this stator and this rotor, wherein the electrical machine is suitable for generating an electromotive force applied to the rotating member.
    Type: Grant
    Filed: February 5, 2016
    Date of Patent: October 13, 2020
    Inventor: Jean-Claude Tourn
  • Patent number: 10738617
    Abstract: A turbomachine includes a turbine section including a turbine center frame and a turbine, the turbine including a plurality of low-speed turbine rotor blades and a plurality of high-speed turbine rotor blades alternatingly spaced along the axial direction. The plurality of low-speed turbine rotor blades each extend between a radial inner end and a radial outer end. At least two of the plurality of low-speed turbine rotor blades are spaced from one another along the axial direction and coupled to one another at the radial outer ends. The turbomachine also includes a gearbox aligned with, or positioned forward of, a midpoint of the turbine. The gearbox includes a first gear coupled to the plurality of low-speed turbine rotor blades, a second gear coupled to the plurality of high-speed turbine rotor blades, and a third gear coupled to the turbine center frame.
    Type: Grant
    Filed: September 20, 2017
    Date of Patent: August 11, 2020
    Assignee: General Electric Company
    Inventors: Peeyush Pankaj, Shashank Suresh Puranik, Darek Tomasz Zatorski, Christopher Charles Glynn, Richard Schmidt