Raytheon Technologies Corporation patent applications on September 12th, 2024
Patent Applications by Raytheon Technologies Corporation on September 12th, 2024
Raytheon Technologies Corporation: 17 patent applications
Raytheon Technologies Corporation has applied for patents in the areas of F01D5/18 (3), C04B41/45 (3), F02C3/30 (2), B28B7/00 (1), F01K23/10 (1) B28B7/0029 (1), F01D25/243 (1), F23R3/286 (1), F23R3/002 (1), F02C7/141 (1)
With keywords such as: core, section, turbine, engine, side, flowpath, configured, skin, wall, and through in patent application abstracts.
Patent Applications by Raytheon Technologies Corporation
Inventor(s): Brendan Lenz of Wethersfield CT (US) for raytheon technologies corporation, Mary Colby of West Hartford CT (US) for raytheon technologies corporation, Andrew Joseph Lazur of La Jolla CA (US) for raytheon technologies corporation, Lane M. Thornton of Tolland CT (US) for raytheon technologies corporation, Daniel P. Preuss of Glastonbury CT (US) for raytheon technologies corporation
IPC Code(s): B28B7/00
CPC Code(s): B28B7/0029
Abstract: a tooling fixture suitable for use in infiltrating a fibrous preform with a flow of reactant gas includes an outer surface and an inner surface defining a thickness therebetween, and a plurality of holes extending through the thickness of the tooling fixture. the plurality of holes includes a first hole having cylindrical geometry with a first pair of dimensions comprising a first length and a first diameter, a second hole having cylindrical geometry with a second pair of dimensions comprising a second length and a second diameter, and a third hole having cylindrical geometry with a third pair of dimensions comprising a third length and a third diameter. at least one dimension of the first pair of dimensions is different from at least one dimension of the second pair of dimensions, and at least one dimension of the second pair of dimensions is different from at least one dimension of the third pair of dimensions.
Inventor(s): Robert A. White, III of Meriden CT (US) for raytheon technologies corporation, Andrew Joseph Lazur of La Jolla CA (US) for raytheon technologies corporation, Mary Colby of West Hartford CT (US) for raytheon technologies corporation, Howard J. Liles of Newington CT (US) for raytheon technologies corporation, Robin H. Fernandez of East Haddam CT (US) for raytheon technologies corporation
IPC Code(s): B28B21/48, B28B7/30, C04B41/45
CPC Code(s): B28B21/48
Abstract: a mandrel suitable for supporting an airfoil preform includes a first piece extending along a longitudinal axis of the mandrel, and a second piece in physical contact with the first piece at first interface region and extending along the longitudinal axis of the mandrel. the first piece is formed from a first material, and the second piece is formed from a second material.
Inventor(s): Zubair A. Baig of South Windsor CT (US) for raytheon technologies corporation, Martin Amari of Glastonbury CT (US) for raytheon technologies corporation
IPC Code(s): B64D27/24, F01D15/10
CPC Code(s): B64D27/24
Abstract: an aircraft hybrid electrical propulsion (hep) system includes an electrical system configured to deliver power to a plurality of electrical loads, a propulsion system configured to generate thrust in response to an input power, and an hep controller in signal communication with the electrical system and the propulsion system. the hep controller is configured to monitor a load demand of at least one electrical load among the plurality of electrical loads and to actively control the input power to actively control the thrust in response to changes in the load demand.
Inventor(s): Zachary Paul Konopaske of West Hartford CT (US) for raytheon technologies corporation, Molly Kole of Hartford CT (US) for raytheon technologies corporation, John D. Riehl of Hebron CT (US) for raytheon technologies corporation
IPC Code(s): C04B35/80, C04B41/45, C04B41/83, C04B41/91
CPC Code(s): C04B35/80
Abstract: a method of forming a ceramic matrix composite includes arranging a plurality of ceramic fibers into a preform, mounting the preform within a tooling fixture, perforating the preform to form a plurality of z-channels, each of the plurality of z-channels extending completely through a thickness of the preform, pushing a pin array against a surface of the preform through infiltration holes in the tooling fixture to apply a compressive force on the preform, and subsequently, removing the pin array from the surface of the preform. the pin array includes a plurality of pins extending from a backplate. each of the plurality of pins is aligned with a respective infiltration hole of the tooling fixture.
Inventor(s): Daniel P. Preuss of Glastonbury CT (US) for raytheon technologies corporation, Andrew Joseph Lazur of La Jolla CA (US) for raytheon technologies corporation, Brendan Lenz of Wethersfield CT (US) for raytheon technologies corporation, Lane M. Thornton of Tolland CT (US) for raytheon technologies corporation, Mary Colby of West Hartford CT (US) for raytheon technologies corporation
IPC Code(s): C04B41/45
CPC Code(s): C04B41/4529
Abstract: a tooling fixture suitable for use in infiltrating a fibrous preform with a flow of reactant gas includes at least one wall. the at least one wall includes an outer surface and opposing inner surface defining a thickness therebetween, and a plurality of holes extending through the thickness. each hole of the plurality of holes includes an inlet at the outer surface, an outlet at the inner surface, a transition point between the inlet and the outlet, and a first corner defined by the outer surface and the inlet. an angle of the first corner is less than 90 degrees, each hole of the plurality of holes has a first diameter at the inlet and a second diameter at the outlet, and the second diameter is less than the first diameter.
Inventor(s): Lane M. Thornton of Tolland CT (US) for raytheon technologies corporation, Brendan Lenz of Wethersfield CT (US) for raytheon technologies corporation, Mary Colby of West Hartford CT (US) for raytheon technologies corporation, Andrew Joseph Lazur of La Jolla CA (US) for raytheon technologies corporation, Daniel P. Preuss of Glastonbury CT (US) for raytheon technologies corporation
IPC Code(s): C23C16/04
CPC Code(s): C23C16/045
Abstract: a tooling fixture suitable for use in infiltrating a fibrous preform with a reactant gas includes an outer surface and opposing inner surface defining a thickness therebetween, and a plurality of holes extending through the thickness. each hole of the plurality of holes includes an inlet at the outer surface, the inlet configured to receive a flow of the reactant gas, an outlet at the inner surface, a transition point between the inlet and the outlet, and an angled segment extending from the transition point to the outlet. each hole of the plurality of holes has a first diameter at the inlet and a second diameter at the outlet, and the second diameter is greater than the first diameter.
Inventor(s): Jaime G. Ghigliotty Rosado of Cabo Rojo PR (US) for raytheon technologies corporation, Brandon W. Spangler of Vernon CT (US) for raytheon technologies corporation
IPC Code(s): F01D5/18
CPC Code(s): F01D5/18
Abstract: a turbine engine airfoil element has an airfoil having: a pressure side and a suction side; and a plurality of spanwise passageway legs. the passageway legs include: a leading edge impingement cavity; and a plurality of main body feed passageway legs along a camber line. a wall separates the leading edge impingement cavity from a leading one of the main body feed passageway legs, the wall having a suction side section and a pressure side section joining at a junction, the junction forming a vertex of an angle of transverse cross-section of the wall; and a plurality of impingement feed holes through the wall. the plurality of impingement feed holes are larger thickness-wise than span-wise.
Inventor(s): Brandon W. SPANGLER of Vernon CT (US) for raytheon technologies corporation, Dominic J. MONGILLO, JR. of West Hartford CT (US) for raytheon technologies corporation, Jaime G. GHIGLIOTTY ROSADO of Cabo Rojo PR (US) for raytheon technologies corporation
IPC Code(s): F01D5/18
CPC Code(s): F01D5/186
Abstract: a turbine engine airfoil element has: a plurality of spanwise main body passageways along a camber line; and a plurality of spanwise skin passageways along the pressure side. the spanwise skin passageways include: first skin passageways each having a plurality of film cooling outlets to the pressure side; and second skin passageways each lacking film cooling outlets to the pressure side. linking passageways extend between the first skin passageways and the second skin passageways. the first skin passageways and second skin passageways are directly fed from one or more inlets of the airfoil element.
Inventor(s): Brandon W. Spangler of Vernon CT (US) for raytheon technologies corporation
IPC Code(s): F01D5/20, F01D5/18
CPC Code(s): F01D5/20
Abstract: a blade for a gas turbine engine, including: an airfoil having a leading edge, a pressure side, a suction side and a trailing edge that extend to a tip of the airfoil; a leading edge cavity located within the airfoil; at least one main body cavity located within the airfoil; pressure side skin core passages located within the airfoil; suction side skin core passages located within the airfoil, the at least one main body cavity being fluidly isolated from the pressure side skin core passages and the suction side skin core passages and the at least one main body cavity being located between the pressure side skin core passages and the suction side skin core passages; a trailing edge feed cavity located within the airfoil; and a tip plenum located proximate to the tip of the airfoil, the tip plenum being fluidly coupled to the at least one main body cavity, wherein the tip plenum is located above the pressure side skin core passages and the trailing edge feed cavity and extends to the trailing edge of the airfoil.
Inventor(s): Paul M. Lutjen of Kennebunkport ME (US) for raytheon technologies corporation, Dairus D. McDowell of Springvale ME (US) for raytheon technologies corporation
IPC Code(s): F01D25/24, F01D25/28
CPC Code(s): F01D25/243
Abstract: a component of a gas turbine engine includes a continuous hoop portion extending at least partially around an engine central longitudinal axis of the gas turbine engine and a bolting feature extending from the hoop portion, configured for securing the component to an adjacent component. the bolting feature includes a circumferential arm extending radially and circumferentially from the hoop portion. the circumferential arm defines a radial gap between the circumferential arm and the hoop portion. the circumferential arm includes a bolt opening for installation of a bolt therethrough. a connecting leg extends radially from the hoop portion across the radial gap toward the connecting arm. an arm interlocking feature is located at the circumferential arm and is configured to radially interlock with a complementary leg interlocking feature of the connecting leg. the arm interlocking feature and the leg interlocking feature have a radial interconnect gap therebetween in a free state.
Inventor(s): Jon E. Sobanski of Glastonbury CT (US) for raytheon technologies corporation
IPC Code(s): F01K23/10
CPC Code(s): F01K23/10
Abstract: a turbine engine with an axis is provided. this turbine engine includes a fan section, a turbine engine core, a bypass flowpath, an engine housing, an evaporator, a condenser and a core flowpath. the turbine engine core is configured to power the fan section. the turbine engine core includes a core compressor section, a core combustor section and a core turbine section. the bypass flowpath is fluidly coupled with and downstream of the fan section. the engine housing includes a cavity radially outboard of and axially overlapping the fan section and/or the bypass flowpath. the evaporator module is within the cavity. the condenser module is within the cavity. the core flowpath extends sequentially through the core compressor section, the core combustor section, the core turbine section, the evaporator module and the condenser module.
Inventor(s): Neil J. Terwilliger of Cheshire CT (US) for raytheon technologies corporation
IPC Code(s): F02C3/30, F01D25/32
CPC Code(s): F02C3/30
Abstract: a powerplant includes a turbine engine core configured to power a mechanical load. the turbine engine core includes a core compressor section, a core combustor section and a core turbine section. a recovery system includes a condenser and an evaporator. a core flowpath extends sequentially through the core compressor section, the core combustor section, the core turbine section, the evaporator and the condenser from an inlet into the core flowpath to an exhaust from the core flowpath. the recovery system is configured to condense water vapor flowing through the core flowpath into water using the condenser. the recovery system is configured to evaporate the water into steam using the evaporator and to provide the steam to the turbine engine core during a first mode of operation. the recovery system is configured to flow the water through the evaporator during a second mode of operation.
Inventor(s): Jon E. Sobanski of Glastonbury CT (US) for raytheon technologies corporation, Jacob C. Snyder of East Haddam CT (US) for raytheon technologies corporation, Neil J. Terwilliger of Cheshire CT (US) for raytheon technologies corporation
IPC Code(s): F02C6/18
CPC Code(s): F02C6/18
Abstract: a turbine engine with an axis is provided. this turbine engine includes a fan section, a turbine engine core, a bypass flowpath, a recovery system and a core flowpath. the turbine engine core is configured to power the fan section. the turbine engine core includes a core compressor section, a core combustor section and a core turbine section. the bypass flowpath is fluidly coupled with and downstream of the fan section. the recovery system includes an evaporator module and a condenser module. the condenser module is arranged radially outboard of and axially overlaps the bypass flowpath. the core flowpath extends sequentially through the core compressor section, the core combustor section, the core turbine section, the evaporator module and the condenser module.
Inventor(s): Jon E. Sobanski of Glastonbury CT (US) for raytheon technologies corporation, Jacob C. Snyder of East Haddam CT (US) for raytheon technologies corporation
IPC Code(s): F02C7/141, F02C3/22, F02C3/30
CPC Code(s): F02C7/141
Abstract: a turbine engine is provided that includes a fan section, a turbine engine core, an evaporator, a condenser, a core flowpath and a bypass flowpath. the turbine engine core is configured to power the fan section. the turbine engine core includes a core compressor section, a core combustor section and a core turbine section. the evaporator is arranged axially along an axis between the fan section and the turbine engine core. the condenser is arranged axially along the axis between the fan section and the turbine engine core. the core flowpath extends sequentially through the core compressor section, the core combustor section, the core turbine section, the evaporator and the condenser. the bypass flowpath is fluidly coupled with and downstream of the fan section. the bypass flowpath is radially outboard of and extends axially along the evaporator and the condenser.
Inventor(s): Ian Walters of Corvallis OR (US) for raytheon technologies corporation, Stephen K. Kramer of Cromwell CT (US) for raytheon technologies corporation, Baris A. Sen of S. Glastonbury CT (US) for raytheon technologies corporation, Gary J. Dillard of Gainesville FL (US) for raytheon technologies corporation, Eunice Allen-Bradley of Vernon CT (US) for raytheon technologies corporation
IPC Code(s): F23R3/00
CPC Code(s): F23R3/002
Abstract: an apparatus is provided for a turbine engine. this turbine engine apparatus includes a combustor wall, and the combustor wall includes a panel, a deflector and a quench aperture that extends along an aperture centerline through the combustor wall to an aperture outlet into a combustion chamber. the panel extends axially along and circumferentially about an axis. the panel extends radially between a first panel side and a second panel side. the first panel side forms a peripheral boundary of the combustion chamber. the panel forms a downstream side of the aperture outlet at the first panel side. the deflector projects out from the panel at the first panel side into the combustion chamber. the deflector forms an upstream side of the aperture outlet.
Inventor(s): Ian Walters of Corvallis OR (US) for raytheon technologies corporation, Stephen K. Kramer of Cromwell CT (US) for raytheon technologies corporation, Gary J. Dillard of Gainesville FL (US) for raytheon technologies corporation
IPC Code(s): F23R3/28, F23R3/14
CPC Code(s): F23R3/286
Abstract: an assembly is provided for a gas turbine engine. this turbine engine assembly includes a combustor and a fuel injector assembly. the combustor includes a combustion chamber that extends axially along and circumferentially about an axial centerline. the fuel injector assembly is configured to direct fuel and air into the combustion chamber. the fuel injector assembly includes a fuel injector nozzle and an air swirler structure. the fuel injector nozzle projects into and is coupled with the air swirler structure. the centerline axis of at least one of the fuel injector nozzle or the air swirler structure is angularly offset from the axial centerline by an offset angle in a circumferential direction about the axial centerline.
Inventor(s): Jon E. Sobanski of Glastonbury CT (US) for raytheon technologies corporation, Jacob C. Snyder of East Haddam CT (US) for raytheon technologies corporation
IPC Code(s): F28D7/00, F28F9/02
CPC Code(s): F28D7/0058
Abstract: a heat exchanger is provided that a flowpath extending longitudinally through a duct. the flowpath extends laterally within the duct between a first sidewall and a second sidewall. the flowpath extends vertically within the duct between a first manifold wall and a second manifold wall. the first manifold wall is configured to form a peripheral boundary of a first manifold plenum outside of the duct. the second manifold wall is configured to form a peripheral boundary of a second manifold plenum outside of the duct. a plurality of tubes extend vertically across the flowpath and are connected to the first manifold wall and the second manifold wall. each of the tubes has a bore configured to fluidly couple the first manifold plenum to the second manifold plenum. the tubes include a first tube and a second tube. the first tube is adjacent and angularly offset from the second tube.
Raytheon Technologies Corporation patent applications on September 12th, 2024
- Raytheon Technologies Corporation
- B28B7/00
- CPC B28B7/0029
- Raytheon technologies corporation
- B28B21/48
- B28B7/30
- C04B41/45
- CPC B28B21/48
- B64D27/24
- F01D15/10
- CPC B64D27/24
- C04B35/80
- C04B41/83
- C04B41/91
- CPC C04B35/80
- CPC C04B41/4529
- C23C16/04
- CPC C23C16/045
- F01D5/18
- CPC F01D5/18
- CPC F01D5/186
- F01D5/20
- CPC F01D5/20
- F01D25/24
- F01D25/28
- CPC F01D25/243
- F01K23/10
- CPC F01K23/10
- F02C3/30
- F01D25/32
- CPC F02C3/30
- F02C6/18
- CPC F02C6/18
- F02C7/141
- F02C3/22
- CPC F02C7/141
- F23R3/00
- CPC F23R3/002
- F23R3/28
- F23R3/14
- CPC F23R3/286
- F28D7/00
- F28F9/02
- CPC F28D7/0058
