Means, Disposition Or Arrangement For Causing Supersonic Working Fluid Velocity Patents (Class 415/181)
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Patent number: 12158164Abstract: A low solidity diffuser vane includes a vane body having a shroud side, a hub side, and a sculpted leading edge connecting the shroud side to the hub side.Type: GrantFiled: August 21, 2023Date of Patent: December 3, 2024Assignee: FOXRES LLCInventor: Mark J. Kuzdzal
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Patent number: 12145714Abstract: An introduced autonomous aerial vehicle can include multiple cameras for capturing images of a surrounding physical environment that are utilized for motion planning by an autonomous navigation system. In some embodiments, the cameras can be integrated into one or more rotor assemblies that house powered rotors to free up space within the body of the aerial vehicle. In an example embodiment, an aerial vehicle includes multiple upward-facing cameras and multiple downward-facing cameras with overlapping fields of view to enable stereoscopic computer vision in a plurality of directions around the aerial vehicle. Similar camera arrangements can also be implemented in fixed-wing aerial vehicles.Type: GrantFiled: July 26, 2022Date of Patent: November 19, 2024Assignee: Skydio, Inc.Inventors: Benjamin Scott Thompson, Adam Parker Bry, Asher Mendel Robbins-Rothman, Abraham Galton Bachrach, Yevgeniy Kozlenko, Kevin Patrick Smith O'Leary, Patrick Allen Lowe, Daniel Thomas Adams, Justin Michael Sadowski, Zachary Albert West, Josiah Timothy VanderMey
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Patent number: 12110804Abstract: A gas turbine engine comprises a fan mounted to rotate about a main longitudinal axis; an engine core, comprising in axial flow series a compressor, a combustor, and a turbine coupled to the compressor through a shaft; a reduction gearbox that receives an input from the shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the shaft; wherein the compressor comprises a first stage at an inlet and a second stage, downstream of the first stage, comprising respectively a first rotor with a row of first blades and a second rotor with a row of second blades, the first and second blades comprising respective leading edges, trailing edges and tips, and wherein the ratio of a maximum leading edge radius of the first blades to a maximum leading edge radius of the second blades is greater than 2.8.Type: GrantFiled: November 30, 2023Date of Patent: October 8, 2024Assignee: ROLLS-ROYCE plcInventors: Ian J. Bousfield, Duncan A. Macdougall
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Patent number: 12098644Abstract: A turboshaft engine for a rotorcraft includes a first spool and an independently rotatable second spool. The first spool includes a low pressure compressor, a first set of variable guide vanes disposed at an entry of the low pressure compressor, and a low pressure turbine drivingly engaged to the low pressure compressor. The second spool includes a high pressure compressor, a second set of variable guide vanes disposed at an entry of the high pressure compressor, the second set of variable guide vanes independently operable relative to the first set of variable guide vanes, and a high pressure turbine drivingly engaged to the high pressure compressor. One or both of the low pressure compressor and the high pressure compressor includes a mixed flow rotor.Type: GrantFiled: November 16, 2022Date of Patent: September 24, 2024Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Keith Morgan, Eric Durocher
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Patent number: 12077316Abstract: An introduced autonomous aerial vehicle can include multiple cameras for capturing images of a surrounding physical environment that are utilized for motion planning by an autonomous navigation system. In some embodiments, the cameras can be integrated into one or more rotor assemblies that house powered rotors to free up space within the body of the aerial vehicle. In an example embodiment, an aerial vehicle includes multiple upward-facing cameras and multiple downward-facing cameras with overlapping fields of view to enable stereoscopic computer vision in a plurality of directions around the aerial vehicle. Similar camera arrangements can also be implemented in fixed-wing aerial vehicles.Type: GrantFiled: August 31, 2022Date of Patent: September 3, 2024Assignee: Skydio, Inc.Inventors: Benjamin Scott Thompson, Adam Parker Bry, Asher Mendel Robbins-Rothman, Abraham Galton Bachrach, Yevgeniy Kozlenko, Kevin Patrick Smith O′Leary, Patrick Allen Lowe, Daniel Thomas Adams, Justin Michael Sadowski, Zachary Albert West, Josiah Timothy VanderMey
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Patent number: 12066027Abstract: A counter-rotating supersonic compressor. A first subsonic rotor includes a plurality of unshrouded impulse rotor blades operating at sub-sonic conditions. A second, supersonic rotor includes a fixed second rotor portion and an adjustable second rotor portion. The fixed second rotor portion includes a plurality of supersonic passageways having converging-diverging sidewalls, and internal boundary layer bleed passageways. The adjustable second rotor portion includes a plurality of centerbodies which are disposed in the supersonic passageways. Helical movement (circumferential and axial) movement of the adjustable second rotor portion with respect to the fixed second rotor portion enables upstream and downstream movement of the centerbodies in the supersonic passageways. This movement facilitates ease of supersonic startup, and automatic adjustment for changes in operation conditions, such as pressure, temperature, or mass flow rate of a working fluid such as carbon dioxide.Type: GrantFiled: August 10, 2023Date of Patent: August 20, 2024Assignee: NEXT GEN COMPRESSION LLCInventor: Shawn P. Lawlor
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Patent number: 12055159Abstract: A fan guard includes a guard housing and a plurality of guard blades. The guard housing includes an outer tunnel wall forming a housing aperture to permit air to flow across the guard housing. The guard blades are disposed in the housing aperture. Each of the guard blades extend from the guard housing towards a center of the housing aperture. Each guard blade at least partially overlaps an adjacent guard blade. Each of the guard blades are droplet shaped.Type: GrantFiled: September 26, 2022Date of Patent: August 6, 2024Assignee: ZT GROUP INT'L, INC.Inventors: Cong Yao, Darell Sutton, Richard Gaugler
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Patent number: 12049900Abstract: A compressor or pump stage is provided. The compressor or pump stage at least comprising a central shaft (8) and one rotor (3), where the axis of rotation of the rotor (3) is the central shaft (8) and where the rotor comprises a number, n, of rows of impellers (5) arranged at an outer perimeter of the rotor with an axial distance between neighbouring rows of impellers (5), where n={2, 3, 4 . . . }.Type: GrantFiled: March 23, 2023Date of Patent: July 30, 2024Assignee: VETCO GRAY SCANDINAVIA ASInventors: Giacomo Landi, Vittorio Michelassi, Matteo Dozzini, Francesco Cangioli, Massimiliano Borghetti
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Patent number: 12037921Abstract: A fan for a turbine engine having a core air flowpath and a bypass air flowpath. The fan includes a disk, a plurality of fan blades, and a plurality of splitter blades. The disk rotates about a centerline axis. The plurality of fan blades are coupled to the disk. The plurality of splitter blades are coupled to the disk and positioned between the plurality of fan blades. The plurality of splitter blades are axially aligned on the disk at a splitter blade axial distance from an annular inlet of the core air flowpath such that the plurality of splitter blades direct debris that passes through the fan into the bypass air flowpath.Type: GrantFiled: August 4, 2022Date of Patent: July 16, 2024Assignee: GENERAL ELECTRIC COMPANYInventors: Nicholas J. Kray, David W. Crall, Anthony L. DiPietro
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Patent number: 12037951Abstract: A method includes routing a combustion gas through a turbine stage along a combustion gas path disposed between a turbine shaft and a turbine casing of a gas turbine, wherein the turbine shaft is disposed along a rotational axis, the turbine casing is disposed circumferentially about the turbine shaft, and the turbine stage includes a plurality of turbine vanes disposed upstream from a plurality of turbine blades. The method includes controlling an axial range of different axial positions of combustion within a turbine stage expansion of the turbine stage to reduce temperature variations over the turbine stage expansion via an isothermal expansion system coupled to the turbine stage in response to a change in a load on the gas turbine.Type: GrantFiled: December 30, 2022Date of Patent: July 16, 2024Assignee: GE INFRASTRUCTURE TECHNOLOGY LLCInventors: John Farrior Woodall, Joel Meador Hall
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Patent number: 12030399Abstract: A base station for an unmanned aerial vehicle (UAV) is disclosed that includes: an enclosure; a slide mechanism; and a cradle. The slide mechanism is repositionable between a retracted and extended positions and is secured in relation to the enclosure via first and second mounts, which are located between the slide mechanism and the enclosure so as to separate the slide mechanism from the enclosure and thereby reduce vibration of the slide mechanism during repositioning between the retracted and extended positions. The cradle is connected to the slide mechanism and is configured for docking with the UAV such that the UAV is movable into and out of the enclosure during repositioning of the slide mechanism between the retracted and extended positions.Type: GrantFiled: August 31, 2022Date of Patent: July 9, 2024Assignee: Skydio, Inc.Inventors: Christopher C. Berthelet, Shreetej Varakantam Reddy, Ioan Trayanov, Dylan Matthew Callaway
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Patent number: 12017553Abstract: A base station for an unmanned aerial vehicle (UAV) is disclosed. The base station includes: an enclosure; a slide mechanism that is connected to the enclosure and which is repositionable between a retracted position and an extended position; a cradle that is connected to the slide mechanism and which is configured for docking with the UAV such that the UAV is movable into and out of the enclosure during repositioning of the slide mechanism between the retracted position and the extended position; and a charging hub that is connected to the slide mechanism and which is configured for electrical connection to a power source of the UAV to charge the power source.Type: GrantFiled: August 31, 2022Date of Patent: June 25, 2024Assignee: Skydio, Inc.Inventors: Patrick Allen Lowe, Yevgeniy Kozlenko, Christopher C. Berthelet, Christopher Brian Grasberger, Roderick Donald Bacon
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Patent number: 11993408Abstract: A bladed disc for masking a moving disc of a jet engine, including blades, each blade including a pressure-side wall and a suction-side wall that meet at a leading-edge and at a trailing edge, and wherein each blade has a pressure-side wall and a suction-side wall each including a concave zone and a convex zone that are at a distance from the leading-edge and from the trailing edge and are spaced apart from one another, these concave zones and these convex zones each extending over the majority of the height of the blade, the concave zone of the pressure-side wall is opposite the convex zone of the suction-side wall, the concave zone of the suction-side wall is opposite the convex zone of the pressure-side wall.Type: GrantFiled: December 4, 2019Date of Patent: May 28, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventors: Michel Dumas, Laurent Christophe Francis Villaines
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Patent number: 11988170Abstract: A gas turbine engine generates noise during use, and one particularly important flight condition for noise generation is take-off. A gas turbine engine that has high efficiency provides low noise, in particular from the fan and the turbine that drives the fan. Values are defined for a noise parameter NP that results in a gas turbine engine having reduced combined fan and turbine noise.Type: GrantFiled: November 29, 2022Date of Patent: May 21, 2024Assignee: ROLLS-ROYCE plcInventors: Alastair D Moore, Robert J Telling
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Patent number: 11970979Abstract: A turbine engine and method of operating includes an engine core with a compressor, a combustor, and a turbine in axial flow arrangement. A flow path extends through the engine core from the compressor to the turbine to define a flow direction for a working airflow through the engine core.Type: GrantFiled: November 2, 2022Date of Patent: April 30, 2024Assignee: General Electric CompanyInventors: Christopher Ryan Johnson, Paul Hadley Vitt, Eric Joseph Schroeder, Carlos Gilberto Fernandez-Soto
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Patent number: 11970287Abstract: An introduced autonomous aerial vehicle can include multiple cameras for capturing images of a surrounding physical environment that are utilized for motion planning by an autonomous navigation system. In some embodiments, the cameras can be integrated into one or more rotor assemblies that house powered rotors to free up space within the body of the aerial vehicle. In an example embodiment, an aerial vehicle includes multiple upward-facing cameras and multiple downward-facing cameras with overlapping fields of view to enable stereoscopic computer vision in a plurality of directions around the aerial vehicle. Similar camera arrangements can also be implemented in fixed-wing aerial vehicles.Type: GrantFiled: July 26, 2022Date of Patent: April 30, 2024Assignee: Skydio, Inc.Inventors: Benjamin Scott Thompson, Adam Parker Bry, Asher Mendel Robbins-Rothman, Abraham Galton Bachrach, Yevgeniy Kozlenko, Kevin Patrick Smith O'Leary, Patrick Allen Lowe, Daniel Thomas Adams, Justin Michael Sadowski, Zachary Albert West, Josiah Timothy VanderMey
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Patent number: 11970993Abstract: A Brayton cycle engine and method for operation. The engine includes an inner wall assembly and an upstream wall assembly each extended from a longitudinal wall into a gas flowpath. An actuator adjusts a depth of the detonation combustion region into the gas flowpath between the inner wall assembly and the upstream wall assembly. The engine flows an oxidizer through the gas flowpath and the inner wall captures a portion of the oxidizer. The engine further adjusts the captured flow of oxidizer via the upstream wall and flows a first flow of fuel to the captured flow of oxidizer to produce rotating detonation gases. The engine flows the detonation gases downstream and to mix with the flow of oxidizer, and flows and burns a second flow of fuel to the detonation gases/oxidizer mixture to produce thrust.Type: GrantFiled: September 27, 2022Date of Patent: April 30, 2024Assignee: GENERAL ELECTRIC COMPANYInventors: Sibtosh Pal, Steven Clayton Vise, Arthur Wesley Johnson, Clayton Stuart Cooper, Joseph Zelina
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Patent number: 11965431Abstract: A turbine is provided with: a turbine wheel configured to rotate about an axis O1; a turbine housing accommodating the turbine wheel and defining an annular nozzle passage on the outer peripheral side of the turbine wheel; and a plurality of low solidity nozzle vanes 6 arranged in the nozzle passage at an interval in the circumferential direction. Circumferentially adjacent low solidity nozzle vanes 6 are disposed at different radial positions in a connection position of each of the low solidity nozzle vanes 6 with a hub-side wall surface of the hub-side wall surface and a shroud-side wall surface which define the nozzle passage.Type: GrantFiled: January 7, 2020Date of Patent: April 23, 2024Assignee: MITSUBISHI HEAVY INDUSTRIES ENGINE & TURBOCHARGER, LTDInventors: Nao Taniguchi, Toyotaka Yoshida, Makoto Ozaki, Nobuhito Oka
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Patent number: 11965527Abstract: A stator blade for a centrifugal compressor having a front portion configured to generate one or more strear-wise vortices in the gas flow around the stator blade in order to avoid and/or delay a detachment of the gas flow from the suction surface of the stator blade especially when the centrifugal compressor is not operating at its operational design speed.Type: GrantFiled: May 7, 2020Date of Patent: April 23, 2024Assignee: Nuovo Pignone Technologie SRLInventors: Marco Giachi, Filippo Rubechini, Andrea Arnone
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Patent number: 11920479Abstract: A method of operating a multi-engine system of a rotorcraft includes, during a cruise flight segment of the rotorcraft, controlling a first engine to provide sufficient power and/or rotor speed demands of the cruise flight segment; and controlling a second engine to by providing a fuel flow to the second engine that is between 70% and 99.5% less than a fuel flow provided to the first engine. A turboshaft engine for a multi-engine system configured to drive a common load is also described.Type: GrantFiled: August 8, 2019Date of Patent: March 5, 2024Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Keith Morgan, Stephen Mah, Philippe Beauchesne-Martel, Eric Durocher
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Patent number: 11913471Abstract: An air guide arrangement, for a ventilation system, has a housing forming a flow channel with a fan arranged in the flow channel to generate an airflow through the housing. A flow guide device is arranged in the flow channels. The flow guide device is axially connected downstream of the fan on the outflow side and directly influences the airflow generated by the fan. The flow guide device has an axis-central through opening delimited by a tubular element extending parallel to the flow direction. Multiple separate flow segments are formed along the tubular element and are evenly distributed in the circumferential direction. The flow segments in the circumferential direction are each separated from one another in terms of flow by flow guide elements extending radially outward from the tubular element.Type: GrantFiled: October 28, 2019Date of Patent: February 27, 2024Assignee: EBM-PAPST ABInventor: Erik Brisenheim
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Patent number: 11873731Abstract: A gas turbine engine comprises a fan mounted to rotate about a main longitudinal axis; an engine core, comprising in axial flow series a compressor, a combustor, and a turbine coupled to the compressor through a shaft; a reduction gearbox that receives an input from the shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the shaft; wherein the compressor comprises a first stage at an inlet and a second stage, downstream of the first stage, comprising respectively a first rotor with a row of first blades and a second rotor with a row of second blades, the first and second blades comprising respective leading edges, trailing edges and tips, and wherein the ratio of a maximum leading edge radius of the first blades to a maximum leading edge radius of the second blades is greater than 2.8.Type: GrantFiled: February 27, 2023Date of Patent: January 16, 2024Assignee: ROLLS-ROYCE plcInventors: Ian J. Bousfield, Duncan A. Macdougall
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Patent number: 11788557Abstract: A dynamic compressor includes an impeller having impeller vanes disposed around a hub, a shroud, and a diffuser having a shroud surface adjacent to the shroud and a hub surface adjacent to the hub, wherein the diffuser is circumferentially disposed around the impeller. The diffuser includes a plurality of diffuser vanes extending from the hub surface to the shroud surface, each having a vane leading edge and a vane trailing edge. The diffuser includes a centrifugal acceleration stabilizer ring formed in the shroud surface located in a vaneless region defined between an impeller trailing edge and the vane leading edge. The centrifugal acceleration stabilizer ring stabilizes the flow of the fluid by changing the circumferentially-flowing high velocity fluid flow exiting the impeller into a radially-flowing high velocity fluid flow before entering the diffuser, improving the efficiency of the dynamic compressor.Type: GrantFiled: May 6, 2022Date of Patent: October 17, 2023Assignee: Ingersoll-Rand Industrial U.S., Inc.Inventors: Chester V. Swiatek, Mikhail Grigoriev, Paul C. Brown, Charles Impastato
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Patent number: 11719440Abstract: A pre-swirler unit can include: a shroud including a bottom surface and a top surface opposite to the bottom surface; a blade disposed on the top surface and including a leading edge and a trailing edge, wherein the blade comprises a concave side surface and a convex side surface that are disposed between the leading edge and the trailing edge, wherein the convex side surface comprises a first plurality of dimples, and wherein the concave side surface comprises a second plurality of dimples.Type: GrantFiled: December 19, 2018Date of Patent: August 8, 2023Assignee: DOOSAN ENERBILITY CO., LTD.Inventors: Chad Garner, Andres Jaramillo
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Patent number: 11661854Abstract: A stator vane segment includes: a plurality of airfoil portions; and one outer band and one inner band joined to a tip portion and a hub portion of each airfoil portion. Each airfoil portion is formed by stacking airfoil profiles in a spanwise direction from the hub portion to the tip portion. Each profile includes a leading edge, a trailing edge, a pressure surface, and a suction surface, in a stacking line connecting respective trailing edges of the profiles at spanwise positions. A portion from the tip portion to a predetermined position is a straight line in a radial direction. A portion from the predetermined position to the hub portion is shifted from the pressure surface toward the suction surface in a circumferential direction from the straight line parallel to the radial direction. An amount of the shift monotonically increases from the predetermined position to the hub portion.Type: GrantFiled: July 23, 2021Date of Patent: May 30, 2023Assignee: IHI CORPORATIONInventor: Daisuke Nishii
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Patent number: 11639665Abstract: A turbomachine blade including a body that extends mainly in a plane defined by a main axis and a longitudinal direction, which is defined by a lower surface wall, an upper surface wall, a leading edge located at a first longitudinal end of the body and a trailing edge located at a second longitudinal end of the body, wherein the body of the blade includes a plurality of first pipes that extend mainly along the direction of the main axis, for circulation of a gas flow, and a plurality of second pipes that extend mainly along the longitudinal direction, for circulation of a second gas flow.Type: GrantFiled: February 6, 2020Date of Patent: May 2, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Cédric Zaccardi, Christophe Marcel Lucien Perdrigeon, Catherine Pikovsky
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Patent number: 11639723Abstract: A compressor or pump stage is provided. The compressor or pump stage at least comprising a central shaft (8) and one rotor (3), where the axis of rotation of the rotor (3) is the central shaft (8) and where the rotor comprises a number, n, of rows of impellers (5) arranged at an outer perimeter of the rotor with an axial distance between neighbouring rows of impellers (5), where n={2, 3, 4 . . . }.Type: GrantFiled: September 12, 2017Date of Patent: May 2, 2023Assignee: VETCO GRAY SCANDINAVIA ASInventors: Giacomo Landi, Vittorio Michelassi, Matteo Dozzini, Francesco Cangioli, Massimiliano Borghetti
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Patent number: 11619135Abstract: A gas turbine engine comprises a fan mounted to rotate about a main longitudinal axis; an engine core, comprising in axial flow series a compressor, a combustor, and a turbine coupled to the compressor through a shaft; a reduction gearbox that receives an input from the shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the shaft; wherein the compressor comprises a first stage at an inlet and a second stage, downstream of the first stage, comprising respectively a first rotor with a row of first blades and a second rotor with a row of second blades, the first and second blades comprising respective leading edges, trailing edges and tips, and wherein the ratio of a maximum leading edge radius of the first blades to a maximum leading edge radius of the second blades is greater than 2.8.Type: GrantFiled: March 31, 2021Date of Patent: April 4, 2023Assignee: ROLLS-ROYCE plcInventors: Ian J Bousfield, Duncan A MacDougall
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Patent number: 11598347Abstract: A compressor includes a housing, a shaft, and an impeller rotatable relative to the housing by the shaft. The impeller includes a hub, impeller blades, and external blades. The impeller blades extend from a front of the hub. The external blades protrude from a rear surface of the hub or an outer surface of a shroud of the impeller. The external blades are curved along the rear surface or the outer surface. A heat transfer circuit includes a compressor and a working fluid. The compressor includes an impeller having a hub, impeller blades, and external blades.Type: GrantFiled: June 28, 2019Date of Patent: March 7, 2023Assignee: TRANE INTERNATIONAL INC.Inventor: Joel Gronvall
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Patent number: 11592034Abstract: A mixed-flow compressor includes an impeller attached to a shaft and rotatable about a shaft axis. A vaneless diffuser is located axially downstream of the impeller and has a converging portion and a diverging portion. A vaned diffuser is located axially downstream of the vaneless diffuser.Type: GrantFiled: June 16, 2020Date of Patent: February 28, 2023Assignee: CARRIER CORPORATIONInventors: Chaitanya Vishwajit Halbe, Michael M. Joly, William T. Cousins, Vishnu M. Sishtla
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Patent number: 11585347Abstract: A centrifugal compressor includes a casing. An impeller is arranged within the casing. The impeller is rotatable about an axis. A diffuser section is arranged within the casing. The diffuser section is positioned axially downstream from an outlet of the impeller and includes a forward portion fixed relative to the impeller and an aft portion distinct from the forward portion.Type: GrantFiled: May 15, 2020Date of Patent: February 21, 2023Assignee: Carrier CorporationInventors: Michael M. Joly, Vishnu M. Sishtla
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Patent number: 11566587Abstract: An exemplary gas turbine engine includes a fan section including a fan rotor and at least one fan blade. A fan pressure ratio across the at least one fan blade is less than 1.45, noninclusive of the pressure across any fan exit guide vane system. The engine further includes a low-pressure compressor having a low-pressure compressor rotor that rotates together with the fan rotor at a common speed in operation, and a geared architecture that drives the low-pressure compressor rotor and the fan rotor. The geared architecture has a gear reduction ratio of greater than 2.5. The engine further includes a high-pressure compressor having a pressure ratio greater than 20, a low-pressure turbine having a pressure ratio greater than 5, and a bypass ratio greater than 10.Type: GrantFiled: March 9, 2020Date of Patent: January 31, 2023Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: William G. Sheridan, Michael E. McCune
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Patent number: 11499569Abstract: A compressor includes a housing. An impeller is located within the housing and rotatable about an impeller axis in a first rotational direction. A rotor section is rotatable about the impeller axis in a second rotational direction opposite the first rotational direction.Type: GrantFiled: June 16, 2020Date of Patent: November 15, 2022Inventors: Michael M. Joly, Chaitanya Vishwajit Halbe, William T. Cousins, Vishnu M. Sishtla
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Patent number: 11378100Abstract: A rechargeable electric fan with a fan portion, a base portion, and a telescoping mast hingedly attached to and connecting the fan portion and the base portion. The fan portion has removable front grille, engageable in a first position in which the grille is retained in the front opening of the housing of the fan portion. The grille is rotatable from the first position to a second position in which the grille is released from the front opening. Slots are disposed on a periphery of the grille, and are configured to engage with corresponding tabs disposed on a periphery of the front opening, to retain the grille in the first position, and to release the grille when it is rotated into the second position. To prevent inadvertent release of the grille, a latch mechanism is configured and disposed to lock the grille in the first position, the latch mechanism comprising a button and a latch configured and disposed to release the lock when the button is depressed.Type: GrantFiled: November 30, 2020Date of Patent: July 5, 2022Assignee: E. Mishan & Sons, Inc.Inventor: Bingo Hu
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Patent number: 11230934Abstract: An airfoil of an axial flow machine includes an airfoil part that has a suction surface and a pressure surface, an endwall as a shroud or a platform, and a fillet that is provided along a connecting portion between the airfoil part and the endwall. The fillet includes a first curved surface formed at least on a leading edge side and a trailing edge side in the airfoil part on the suction surface side and a second curved surface formed in a portion other than a portion where the first curved surface is formed. The second curved surface has a smaller curvature radius than the first curved surface.Type: GrantFiled: June 26, 2019Date of Patent: January 25, 2022Assignee: IHI CorporationInventor: Masaaki Hamabe
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Patent number: 11156098Abstract: A component for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section extending in a radial direction from a platform, the airfoil section extending in an axial direction between an airfoil leading edge and an airfoil trailing edge, and the airfoil section extending in the circumferential direction between pressure and suction sides. The platform extends in the axial direction between a platform leading edge and a platform trailing edge, and extends in the circumferential direction between a first mate face and a second mate face. The platform has a radially facing surface joined with the airfoil section and has a cold side surface opposed to the radially facing surface. A first thickness is defined between the radially facing surface and the cold side surface adjacent the first mate face, and a second thickness is defined between the radially facing surface and the cold side surface adjacent the second mate face.Type: GrantFiled: February 7, 2019Date of Patent: October 26, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Laengheng Khoun, Edward F. Pietraszkiewicz, David J. Hiskes
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Patent number: 11131210Abstract: A compressor of a gas turbine engine includes an impeller having a plurality of impeller blades. The compressor includes a diffuser downstream from the impeller that has a plurality of diffuser blades. Each diffuser blade extends from a hub to a shroud in a spanwise direction, and a leading edge of each diffuser blade is spaced apart from an impeller trailing edge of each of the plurality of impeller blades by a vaneless gap. Each diffuser blade includes a cutback region that extends from proximate the leading edge toward a trailing edge. The cutback region reduces a thickness of each of the diffuser blades such that a throat area defined between adjacent diffuser blades increases in the spanwise direction from the hub to the shroud and the vaneless gap increases in the spanwise direction from the hub to the shroud.Type: GrantFiled: January 14, 2019Date of Patent: September 28, 2021Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Shraman Narayan Goswami, Hasham Hamzamiyan Chougule, Jyotichandra Shivaji Roa Jingade, Mohd Abdullah Qizar
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Patent number: 11125085Abstract: A blade of a fan or compressor that reduces loss by enlarging a laminar flow region over a blade surface is provided. The blade is divided into a subsonic region where the relative Mach number of the inlet air flow during rated operation of a turbofan engine is lower than 0.8 and a transonic region where the relative Mach number is equal to or higher than 0.8. A blade surface angle change rate is based on an angle formed by a tangent to the blade surface and the axis of the engine, the leading edge blade surface angle, and the trailing edge blade surface angle at. In each of the subsonic region and the transonic region, values of the blade surface angle change rate on the pressure and suction surfaces are defined at predetermined axial locations along the chord on the pressure and suction surfaces.Type: GrantFiled: November 21, 2019Date of Patent: September 21, 2021Assignee: IHI CORPORATIONInventors: Ryuichi Okada, Ryosuke Hayashi, Takeshi Murooka, Tomonori Enoki
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Patent number: 11041405Abstract: A turbocharger turbine assembly can include a turbine housing that includes a longitudinal axis, an exhaust inlet, a shroud portion, and an exhaust outlet; and a turbine wheel that includes a hub that includes a rotational axis aligned with the longitudinal axis of the turbine housing, a backdisk and a nose, where the rotational axis defines an axial coordinate (z) in a cylindrical coordinate system; and blades that extend outwardly from the hub, where each of the blades includes a shroud edge, a leading edge, a trailing edge, a pressure side, and a suction side, where the shroud edge includes a minimum axial coordinate position where the shroud edge meets the leading edge, and a maximum axial coordinate position where the shroud edge meets the trailing edge, and where, from the minimum axial coordinate position to the maximum axial coordinate position, the shroud edge has a decreasing radial coordinate position.Type: GrantFiled: September 18, 2019Date of Patent: June 22, 2021Assignee: Garrett Transportation I Inc.Inventors: Ashraf Mohamed, Wagner Magalhaes
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Patent number: 11015449Abstract: The present invention provides a steam turbine blade and a steam turbine capable of further improving efficiency. A steam turbine blade includes a proximal end portion T11 which is formed in a blade shape having an intermediate reaction degree, an intermediate portion T12 which is formed in a blade shape having a low reaction degree; and a distal end portion T13 which is formed in a blade shape having a high reaction degree.Type: GrantFiled: December 4, 2019Date of Patent: May 25, 2021Assignee: MITSUBISHI HEAVY INDUSTRIES COMPRESSOR CORPORATIONInventors: Takuro Koda, Yuichi Sasaki
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Patent number: 11002141Abstract: An apparatus and method of managing negative incidence of an airfoil are provided. The apparatus includes a first row of stationary turbine main vanes and a second row of auxiliary vanes extending radially inwardly from a stationary casing of the turbine proximate the adjacent leading edge of the main vane. The apparatus also includes a flow channel defined between a pressure side of an auxiliary vane of the second row of auxiliary vanes and a suction side of an adjacent main vane of the row of stationary turbine main vanes.Type: GrantFiled: May 22, 2017Date of Patent: May 11, 2021Assignee: General Electric CompanyInventors: David Paul Lurie, Sherif Alykadry Abdelfattah, Michael Julian Castillo, Anthony Louis DiPietro, Jr., Aspi Rustom Wadia, Gregory Burr Heitland
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Patent number: 10995677Abstract: A gas turbine engine comprises a fan mounted to rotate about a main longitudinal axis; an engine core, comprising in axial flow series a compressor, a combustor, and a turbine coupled to the compressor through a shaft; a reduction gearbox that receives an input from the shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the shaft; wherein the compressor comprises a first stage at an inlet and a second stage, downstream of the first stage, comprising respectively a first rotor with a row of first blades and a second rotor with a row of second blades, the first and second blades comprising respective leading edges, trailing edges and tips, and wherein the ratio of a maximum leading edge radius of the first blades to a maximum leading edge radius of the second blades is greater than 2.8.Type: GrantFiled: March 10, 2020Date of Patent: May 4, 2021Assignee: ROLLS-ROYCE PLCInventors: Ian J Bousfield, Duncan A Macdougall
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Patent number: 10962021Abstract: A centrifugal impeller is disclosed having a non-axisymmetric flowpath surface. The centrifugal compressor may comprise a hub and a plurality of circumferentially spaced vanes. The hub has a flowpath surface and an axis of rotation. The plurality of circumferentially spaced vanes extend from the flowpath surface, with each of the vanes having a pressure-side fillet and a suction-side fillet extending from a leading edge to a trailing edge of the vane. The pressure-side fillet and suction-side fillet intersect the flowpath surface at a runout. The runout of the pressure-side fillet of a first vane is asymmetric to the runout of the suction-side fillet of the first vane.Type: GrantFiled: August 17, 2018Date of Patent: March 30, 2021Assignee: Rolls-Royce CorporationInventor: Steven Mazur
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Patent number: 10954798Abstract: A gas turbine engine 10 is provided in which a fan having fan blades 139 in which the camber distribution relative to covered passage of the fan 13 allows the gas turbine engine to operate with improved efficiency when compared with conventional engines, whilst retaining an acceptable flutter margin.Type: GrantFiled: October 25, 2018Date of Patent: March 23, 2021Inventors: Benedict Phelps, Stephane M M Baralon, Mark J. Wilson
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Patent number: 10934942Abstract: A high-Mach engine includes a gas turbine core, an inlet assembly, and a transmission. The inlet assembly including an inlet turbine and the transmission configured to couple the inlet turbine and a core turbine of the gas turbine core cooperate to control air moving through the high-Mach engine.Type: GrantFiled: January 27, 2017Date of Patent: March 2, 2021Assignee: Rolls-Royce North American Technologies Inc.Inventors: Douglas D. Dierksmeier, Edward C. Rice, Steven W. Tomlinson, Bradley E. Auker, Donald Klemen
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Patent number: 10914182Abstract: Disclosed is a gas turbine including a housing, a rotor rotatably provided in the housing to transfer a rotary force to a compressor, the compressor receiving the rotary force from the rotor and compressing air, a combustor mixing a fuel with the compressed air supplied from the compressor and igniting the mixture of the fuel and the air to generate combustion gas, and a turbine receiving the rotary force caused by the combustion gas generated by the combustor and rotating the rotor by using the received rotary force.Type: GrantFiled: October 3, 2018Date of Patent: February 9, 2021Assignee: Doosan Heavy Industries Construction Co., LtdInventor: Jin Ho Bae
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Patent number: 10898663Abstract: A fan unit that forms part of a gases supply unit used as part of a breathing assistance system for providing heated gases to a user is provided. The fan unit has an impeller surrounded by an upwardly sloped surface to facilitate improved airflow performance under surge conditions. The impeller includes a plurality of blades capped by a lid having a central aperture to provide an inlet to the impeller.Type: GrantFiled: July 11, 2016Date of Patent: January 26, 2021Assignee: Fisher & Paykel Healthcare LimitedInventor: Johannes Nicolaas Bothma
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Patent number: 10883515Abstract: An apparatus and method of managing negative incidence of an airfoil are provided. The apparatus includes a row of vane pairs including a first row of main vanes extending radially inwardly from a stationary casing member and spaced circumferentially about a first axial location of the stationary casing member. The apparatus also includes a second row of auxiliary vanes extending radially inwardly from the stationary casing member and spaced circumferentially about a second axial location of the stationary casing member. The apparatus also includes a flow channel defined between a pressure side of each auxiliary vane and a suction side of an adjacent main vane proximate a leading edge of the adjacent main vane.Type: GrantFiled: May 22, 2017Date of Patent: January 5, 2021Assignee: General Electric CompanyInventors: David Paul Lurie, Sherif Alykadry Abdelfattah, Michael Julian Castillo, Anthony Louis DiPietro, Jr., Aspi Rustom Wadia, Eric Andrew Falk, William Joseph Solomon, Andrew Breeze-Stringfellow
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Patent number: 10794282Abstract: An inlet assembly for a high-mach engine includes a gas turbine core, an inlet turbine, and a core-flow director. When in a closed position, the core-flow director forces air to interact with the inlet turbine before entering the gas turbine core.Type: GrantFiled: January 10, 2017Date of Patent: October 6, 2020Assignee: Rolls-Royce North American Technologies Inc.Inventors: Douglas D. Dierksmeier, Edward C. Rice, Steven W. Tomlinson, Bradley E. Auker, Donald Klemen
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Patent number: 10774842Abstract: Turbomachines having one or more flow guiding features designed to increase the performance of the turbomachine (3400, 3700, 4000, 4800). In some examples, flow guiding features are designed and configured to bias a circumferential pressure distribution at a diffuser inlet (2210, 2310, 3410, 4204, 4810, 5208, 808) toward circumferential uniformity, otherwise account for such low-frequency spatial pressure variations, increase the controllability of spatial flow field variations, or modifying flow field variations, etc.Type: GrantFiled: April 29, 2016Date of Patent: September 15, 2020Assignee: Concepts NREC, LLCInventor: David Japikse