Patents Examined by Edwin Kang
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Patent number: 11719188Abstract: A thrust reverser for an aircraft includes a jetpipe and a thrust reverser door. The thrust reverser door has an aft end, a forward end, and an interior surface facing radially inward. The interior surface defines a continuous profile with a downstream nozzle portion directly adjacent to the aft end, a concave portion directly adjacent to the downstream nozzle portion, and a convex portion directly adjacent to the forward end and adjacent to the concave portion.Type: GrantFiled: May 14, 2019Date of Patent: August 8, 2023Assignee: Gulfstream Aerospace CorporationInventors: Tyler Relf, Guilherme Oliveira, Vyacheslav Garb
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Patent number: 11719162Abstract: An embodiment of a torch igniter for a combustor of a gas turbine engine includes a combustion chamber oriented about an axis, a cap defining the axially upstream end of the combustion chamber and situated on the axis, a tip defining the axially downstream end of the combustion chamber, an igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, an outlet passage defined by the igniter wall within the tip, wherein the outlet passage fluidly connects the combustion chamber to the combustor of the gas turbine engine, and a cooling system. The cooling system has an air inlet, a cooling channel, and an aperture. The cooling channel forms a flow path having a first axial section, a second axial section, a radially inward section, and a radially outward section.Type: GrantFiled: March 4, 2022Date of Patent: August 8, 2023Assignee: Delavan, Inc.Inventors: Jason Ryon, Lev Alexander Prociw
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Patent number: 11698188Abstract: A flat-jet fuel injector for an aircraft turbine engine, comprising a body having a generally elongate shape having a longitudinal axis A, the body comprising a main pipe having a generally elongate shape having a longitudinal axis B substantially perpendicular to the longitudinal axis A, the two longitudinal ends of the main pipe being connected directly and respectively to longitudinal ends of two secondary pipes having a generally elongate shape having a longitudinal axis C at least substantially parallel to the longitudinal axis A, and being configured to form, respectively, two separate fuel flow inlets intended to meet substantially at the middle of the main pipe which comprises at least one ejection slot for ejecting the fuel jet, wherein at least one of the main and secondary pipes defines a flow area, at least one geometric parameter of which, such as the shape or a dimension, varies along the pipe and/or is different from the same geometric parameter defined by a flow area of another of the pipes.Type: GrantFiled: June 18, 2018Date of Patent: July 11, 2023Assignee: Safran Helicopter EnginesInventors: Denis Chanteloup, Thomas Lederlin, Guillaume Mauries, Simon Meilleurat
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Patent number: 11680709Abstract: A fuel injector is disclosed for reducing flashback. In an embodiment, the fuel injector may comprise an injector head with purge holes on a radial wall along a radial axis between an assembly axis of the fuel injector and a plurality of vanes arranged circumferentially around the assembly axis. In addition, the plurality of vanes may comprise fuel outlets connecting interior fuel passages to spaces between the vanes. The introduction of these purge holes near the bases of the vanes and the configuration and positioning of the fuel outlets in the vanes and elsewhere in the fuel injector may alter the stoichiometry (e.g., fuel-air ratio) within the premix passage of the fuel injector to reduce flashback. A plurality of such fuel injectors may be used in the combustor of a gas turbine engine.Type: GrantFiled: October 26, 2020Date of Patent: June 20, 2023Assignee: Solar Turbines IncorporatedInventors: Michael J. Ramotowski, Paul Economo, Christian Di Norscia, Donald J. Cramb, Nathan J. Kirksey
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Patent number: 11674687Abstract: A fuel injection system includes an outer support defining a fuel manifold and an inner support, with a feed arm extending radially between the inner support and the outer support. A plurality of outlet openings extending in an axial direction from the feed arm for feeding respective injection nozzles. The feed arm defines a plurality of fuel passages therethrough in fluid communication with the fuel manifold and outlet openings to supply fuel from the fuel manifold to the outlet openings. A heat shield extends from the outer support to the inner support and extends about the outer support and the feed arm to provide heat shielding to the fuel manifold and the fuel passages.Type: GrantFiled: May 25, 2021Date of Patent: June 13, 2023Assignee: Collins Engine Nozzles, Inc.Inventors: Jason Ryon, Lev A. Prociw, Gregory A. Zink
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Patent number: 11668199Abstract: A vane arc segment includes an airfoil fairing that has first and second platforms and an airfoil section. The platforms have first and second openings that open into the airfoil section. The platforms each define first and second circumferential mate faces, forward and aft sides, a gaspath side, a non-gaspath side. The first platform has a first flange that projects radially from the non-gaspath side aft of the first opening and a second flange that projects radially from the non-gaspath side forward of the first opening. The first and second flanges are exclusive flanges on the first platform. The second platform has a third flange that projects radially from the non-gaspath side aft of the second opening.Type: GrantFiled: March 5, 2021Date of Patent: June 6, 2023Assignee: Raytheon Technologies CorporationInventors: Jon E. Sobanski, Howard J. Liles, Chang Gao
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Patent number: 11668242Abstract: Fuel injection assemblies and combustors are provided. A fuel injection assembly includes a fuel injector having a first annular wall that about an axial centerline and extends from a primary inlet disposed at a first end to a primary outlet disposed at a second end. A second annular wall surrounds the first annular wall. A fuel plenum is defined between the first annular wall and the second annular wall. A fuel duct extends from a fuel outlet defined in the second annular wall to a fuel inlet. wherein the fuel duct is in fluid communication with the fuel plenum. The fuel duct includes a polygonal segment and a cylindrical inlet segment. The polygonal segment extends from the fuel outlet to the cylindrical inlet segment.Type: GrantFiled: September 29, 2020Date of Patent: June 6, 2023Assignee: General Electric CompanyInventors: Clay Thomas Griffis, Jonathan Dwight Berry, Keith Cletus Belsom, Heath Michael Ostebee
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Patent number: 11591962Abstract: Systems and methods for generating an oblique shock in a supersonic inlet are disclosed. The system can comprise an inlet with a slot disposed at an oblique angle to the main incoming air stream. High-pressure air can be provided through the slot into the main air stream. The high-pressure air can be introduced at a high enough pressure ratio—i.e., the ratio of pressure of the air stream from the slot to the pressure for the main flow—such that an aerodynamic ramp is created in the main air flow. The aerodynamic ramp, in turn, can cause one or more oblique shock waves to eventually slow the main air stream velocity to a subsonic speed prior to the face of the engine. Systems and methods for controlling the slot pressure ratio to create these shocks are also disclosed.Type: GrantFiled: May 29, 2020Date of Patent: February 28, 2023Assignee: The Boeing CompanyInventors: Richard K. Scharnhorst, Robert A. Olivo
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Patent number: 11512600Abstract: An airfoil incudes an airfoil section that defines an internal cavity. The airfoil section is formed of a fiber-reinforced composite that is comprised of fiber plies. The fiber plies include core fiber plies and an overwrap fiber ply that wraps around the core fiber plies. The core fiber plies are arranged as first and second tubes. each of the first and second tubes defines a plurality of windows therein. The windows of the first tube align with the windows of the second tube so as to form radially-spaced ribs that extend across the internal cavity. At least one of the first or second tubes has at least one tab that is radially between the radially-spaced ribs. The at least one tab interlocks the first and second tubes.Type: GrantFiled: March 30, 2021Date of Patent: November 29, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventor: Jonas S. Banhos
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Patent number: 11499480Abstract: A combustor cap assembly, combustor and related method are disclosed. The combustor cap assembly includes: an impingement plate defining a plurality of impingement cooling holes with a first side of the impingement plate in fluid communication with a cooling air plenum. The assembly also includes a combustor cap plate coupled to the impingement plate, such that an impingement air plenum is defined between a second side of the impingement plate and the combustor cap plate. Tubes extend from at least a portion of the plurality of impingement cooling holes at the second side of the impingement plate and extend partially towards the combustor cap plate through the impingement air plenum. The plurality of impingement cooling holes provides for fluid communication between the cooling air plenum and the impingement air plenum through the tubes.Type: GrantFiled: July 28, 2020Date of Patent: November 15, 2022Assignee: General Electric CompanyInventors: Neal William Grooms, Charlie Edmond Jones, Lucas John Stoia
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Patent number: 11486301Abstract: To suppress separation of air flows in air holes that are positioned in the outermost circumferential row in an air hole plate, but are far from a turn guide.Type: GrantFiled: December 11, 2019Date of Patent: November 1, 2022Assignee: Mitsubishi Heavy Industries, Ltd.Inventors: Keisuke Miura, Shohei Uramoto, Tomoya Murota, Yuki Kamikawa, Shingo Yoshida
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Patent number: 11486314Abstract: An environmental control system for an aircraft includes a higher pressure tap associated with a higher compression location in a main compressor section. The higher pressure tap leads into a turbine section of a turbocompressor such that air in the higher pressure tap drives the turbine section to in turn drive a compressor section of the turbocompressor. A combined outlet receives airflow from a turbine outlet and a compressor outlet intermixing airflow and passing the mixed airflow downstream to be delivered to an aircraft system. A buffer air outlet communicates airflow to an engine buffer air system.Type: GrantFiled: September 14, 2020Date of Patent: November 1, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Gabriel L. Suciu, William K. Ackermann, Harold W. Hipsky
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Patent number: 11473505Abstract: An embodiment of a torch igniter for a combustor of a gas turbine engine includes a combustion chamber oriented about an axis, a cap defining the axially upstream end of the combustion chamber and situated on the axis, a tip defining the axially downstream end of the combustion chamber, an igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, an outlet passage defined by the igniter wall within the tip, wherein the outlet passage fluidly connects the combustion chamber to the combustor of the gas turbine engine, and a cooling system. The cooling system has an air inlet, a cooling channel, and an aperture. The cooling channel forms a flow path having a first axial section, a second axial section, a radially inward section, and a radially outward section.Type: GrantFiled: November 4, 2020Date of Patent: October 18, 2022Assignee: Delavan Inc.Inventors: Jason Ryon, Lev Alexander Prociw
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Patent number: 11448127Abstract: Systems and methods for adjusting airflow distortion in a gas turbine engine using a translating inlet assembly are provided. In one embodiment, a core engine of a gas turbine engine can include a compressor section, a combustion section, and a turbine section in series flow and defining at least in part an engine airflow path. The compressor section can include an inner flowpath surface. A core casing can enclose the core engine. A forward end of the core casing can include a translating inlet assembly moveable between a first position and a second position. The translating inlet assembly and the inner flowpath surface can together define an inlet to an engine airflow path. A translating inlet assembly can define a first inlet area in the first position and a second inlet area in the second position, the first inlet area being greater than the second inlet area.Type: GrantFiled: July 14, 2020Date of Patent: September 20, 2022Assignee: General Electric CompanyInventors: Brian Francis Nestico, Brian K. Kestner, Brandon Wayne Miller
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Patent number: 11434849Abstract: A turbofan engine with a nacelle including a runner translationally mobile between advanced and back-off positions to open a window between a stream and an outside, a plurality of blades, each rotatable on the runner between retracted and deployed positions, and a maneuvering system displacing each blade and comprising, for each blade, a shaft rotatable on the runner and to which the blade is fixed, and a toothed segment on the shaft, and a toothed arc rotatable on the runner about a longitudinal axis, the tooth arc teeth meshing with the toothed segment teeth, a slip translationally mobile on the runner in a plane at right angles to the longitudinal axis between first and second positions, a connecting rod mounted articulated between the slip and the toothed arc, a rib integral to the fixed structure, and a guiding U integral to the slip and which straddles the rib.Type: GrantFiled: March 23, 2020Date of Patent: September 6, 2022Assignee: AIRBUS OPERATIONS SASInventors: Antoine Cousin, Frédéric Ridray
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Patent number: 11435080Abstract: A combustor includes at least one fuel nozzle extending from the end cover and at least partially surrounded by the forward casing. The combustor further includes a fuel injection assembly. The fuel injection assembly includes a fuel injector that extends through the outer sleeve, the annulus, and the combustion liner to the secondary combustion zone. A fuel supply conduit positioned outside of the outer sleeve. The fuel supply conduit extends to the fuel injector. The fuel injection assembly further includes a shielding assembly coupled to the outer sleeve and at least partially surrounding the fuel supply conduit. The shielding assembly includes a venturi nozzle having a circumferentially converging portion and a circumferentially diverging portion. At least one fuel sweep opening is defined in the outer sleeve and disposed within the shielding assembly.Type: GrantFiled: June 17, 2021Date of Patent: September 6, 2022Assignee: General Electric CompanyInventors: Dana Morgan, Shreekrishna Rao, Lucas John Stoia, Elizabeth Leigh Exley, Mohan Krishna Bobba, Emily Klara Happ
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Patent number: 11421602Abstract: A torch ignitor system provides a continuous flame to ignite fuel within a combustor of a gas turbine engine. The torch ignitor system includes a manifold and a plurality of torch nozzles to enable the flame or torch to simultaneously ignite multiple fuel nozzles within the combustor of the gas turbine engine.Type: GrantFiled: December 16, 2020Date of Patent: August 23, 2022Assignee: Delavan Inc.Inventor: Jason Ryon
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Patent number: 11421592Abstract: A gas turbine engine (100) for an aircraft comprises a pylon attachment (112) and a shaft (108) defining an engine centreline (110). The engine centreline lies in an engine central plane (120) which intersects the pylon attachment. The gas turbine engine comprises an intake (104) having a non-axisymmetric geometry and a medial plane (130) defining left and right halves of the intake. The left and right halves are configured for at least one of optimum cross wind performance, optimum incidence performance and optimum cruise performance when the medial plane is aligned with a vertical plane. The intake is installed so that the medial plane is angularly offset with respect to the engine central plane. The engine may be installed on a wing of an aircraft with the medial plane closer to its optimal orientation than is the case for a conventional engine.Type: GrantFiled: May 20, 2019Date of Patent: August 23, 2022Assignee: ROLLS-ROYCE plcInventors: Christopher T J Sheaf, Richard G Stretton, Chia Hui Lim
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Patent number: 11415057Abstract: An embodiment of a torch igniter for a combustor of a gas turbine engine includes a combustion chamber oriented about an axis, a cap defining the axially upstream end of the combustion chamber and situated on the axis, a tip defining the axially downstream end of the combustion chamber, an igniter wall extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall coaxial with and surrounding the igniter wall, an outlet passage defined by the igniter wall within the tip, wherein the outlet passage fluidly connects the combustion chamber to the combustor of the gas turbine engine, and a cooling system. The cooling system has an air inlet, a cooling channel, and an aperture. The cooling channel forms a flow path having a first axial section, a second axial section, a radially inward section, and a radially outward section.Type: GrantFiled: November 4, 2020Date of Patent: August 16, 2022Assignee: Delavan Inc.Inventors: Jason Ryon, Lev Alexander Prociw
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Patent number: 11396854Abstract: A thrust reverser for a gas turbine engine includes a frame, a first reverser door pivotally mounted to the frame, and a second reverser door pivotally mounted to the first reverser door.Type: GrantFiled: July 16, 2018Date of Patent: July 26, 2022Assignee: Rohr, Inc.Inventor: Timothy Gormley