RAYTHEON TECHNOLOGIES CORPORATION patent applications on December 12th, 2024
Patent Applications by RAYTHEON TECHNOLOGIES CORPORATION on December 12th, 2024
RAYTHEON TECHNOLOGIES CORPORATION: 18 patent applications
RAYTHEON TECHNOLOGIES CORPORATION has applied for patents in the areas of C01B3/04 (3), F01D21/00 (2), F02C3/30 (2), F01D9/04 (2), F01D5/18 (2) C01B3/042 (2), F02C3/30 (2), B01J6/008 (1), B22F10/73 (1), B60L50/16 (1)
With keywords such as: engine, flow, centrifuge, water, assembly, end, core, wall, side, and extends in patent application abstracts.
Patent Applications by RAYTHEON TECHNOLOGIES CORPORATION
Inventor(s): James P. Mitchell of Cedar Rapids IA (US) for raytheon technologies corporation
IPC Code(s): B01J6/00, C01B3/04
CPC Code(s): B01J6/008
Abstract: a hydrogen isolation system includes a protective chamber and a centrifuge situated in the protective chamber. the centrifuge is configured to receive water and configured to rotate within the protective chamber such that constituents inside the centrifuge separate according to their molecular weights. the hydrogen isolation system also includes an energy source configured to provide heat to the centrifuge such that at least some of the water splits into hydrogen and oxygen.
Inventor(s): Jesse R. Boyer of Middletown CT (US) for raytheon technologies corporation, Brian A. Fisher of West Hartford CT (US) for raytheon technologies corporation, Alexandru Cadar of Eastford CT (US) for raytheon technologies corporation, Joshua M. Norman of South Windsor CT (US) for raytheon technologies corporation
IPC Code(s): B22F10/73, B22F10/28, B22F10/80, B29C64/153, B29C64/357, B29C64/386, B33Y10/00, B33Y40/00, B33Y50/00
CPC Code(s): B22F10/73
Abstract: a method for determining whether build powder is fit for reuse in a laser powder bed fusion additive manufacturing (lpbf) process includes constructing a model for determining a powder reuse index indicative of whether build powder is fit for reuse in the lpbf process based upon lpbf process operating parameters. a build design is selected to be built using the lpbf process to collect data for constructing the model for determining the powder reuse index. a plurality of test pieces the selected build design are built using a lpbf system with different layouts or set ups. quality characteristics are determined for each of the plurality of test pieces and, using the quality characteristics for each of the plurality of test pieces, a relative importance of each lpbf process build parameter as to whether a batch of build powder is fit for reuse is determined.
Inventor(s): Zubair A. Baig of South Windsor CT (US) for raytheon technologies corporation, Martin Amari of Glastonbury CT (US) for raytheon technologies corporation, Tyler W. Hayes of Rockford IL (US) for raytheon technologies corporation
IPC Code(s): B60W20/13, B60L50/16, B60W10/06, B60W10/08
CPC Code(s): B60L50/16
Abstract: a distributed hybrid propulsion system is provided and includes an engine assembly that includes an engine, which is non-propulsive, an energy storage element, a motor-generator and a common bus to which the engine assembly, the energy storage element, the motor-generator and the controller are connected. the common bus includes bi-directional power flow control elements, which are controllable to manage bi-directional power flow between the engine assembly, the energy storage element and the motor-generator.
Inventor(s): James P. Mitchell of Cedar Rapids IA (US) for raytheon technologies corporation
IPC Code(s): C01B3/04, B01J6/00, C01B13/02
CPC Code(s): C01B3/042
Abstract: a water splitting includes a centrifuge situated in the protective chamber and rotatable within the protective chamber such that constituents inside the centrifuge separate according to their molecular mass; an inlet fluidly connected to the centrifuge and configured to provide water to the centrifuge; and an outlet fluidly connected to the centrifuge and configured to remove hydrogen isolated from the water from the centrifuge. a method of isolating hydrogen from water in a reactor is also disclosed.
Inventor(s): James P. Mitchell of Cedar Rapids IA (US) for raytheon technologies corporation
IPC Code(s): C01B3/04, B04B5/10
CPC Code(s): C01B3/042
Abstract: a method of isolating hydrogen from water in a reactor includes charging a centrifuge with water via an inlet including an inlet valve. the centrifugal centrifuge is situated in a protective chamber. the method also includes heating the centrifuge such that at least some of the water splits into hydrogen and oxygen, rotating the centrifuge within the protective chamber such that the hydrogen and oxygen separate within the centrifuge according to their molecular mass, and drawing off at least some of the hydrogen from the centrifuge via an outlet including an outlet valve.
20240410283. AIRFOIL COOLING CIRCUIT_simplified_abstract_(raytheon technologies corporation)
Inventor(s): Dana K. Bondarevsky of Sturbridge MA (US) for raytheon technologies corporation, Dominic J. Mongillo, JR. of West Hartford CT (US) for raytheon technologies corporation, Christopher Paul Perron of Tolland CT (US) for raytheon technologies corporation, Yuta Yoshimura of Meriden CT (US) for raytheon technologies corporation, David D. Chapdelaine of Ellington CT (US) for raytheon technologies corporation
IPC Code(s): F01D5/18
CPC Code(s): F01D5/187
Abstract: an airfoil for a gas turbine engine includes a first wall disposed in an interior cavity, the first wall extending in the spanwise direction from a base region to a tip wall and adjoining a pressure side wall and a suction side wall to form a first cooling channel; a second wall disposed in the interior cavity and extending in a chordwise direction from the first wall toward a trailing edge, the second wall adjoining the pressure side wall and the suction side wall to form a second cooling channel; a first hole through the first wall, the first hole connecting the first cooling channel to the second cooling channel; and a second hole though the second wall connecting the second cooling channel to a third cooling channel.
20240410284. TURBINE VANE BAFFLE CHIMNEY_simplified_abstract_(raytheon technologies corporation)
Inventor(s): Jeffrey T. Morton of Manchester CT (US) for raytheon technologies corporation
IPC Code(s): F01D5/18, F01D9/04, F01D9/06
CPC Code(s): F01D5/189
Abstract: a turbine vane includes an airfoil section with an airfoil wall defining a leading edge and a trailing edge. a first side extends from the leading edge to the trailing edge and extends from a first end of the airfoil section to a second end of the airfoil section. a second side extends from the leading edge to the trailing edge and extends from the first end to the second end of the airfoil section. the airfoil wall also circumscribes an internal core cavity. a platform is attached to the first end of the airfoil section and a platform cavity is formed in the platform. a baffle is in the internal core cavity and includes a baffle tube extending from a first tube end to a second tube end. a chimney is connected to the first tube end and extends completely through the platform cavity.
Inventor(s): Jacob Yochimowitz of East Haddam CT (US) for raytheon technologies corporation, Farruqh Shahab of East Hartford CT (US) for raytheon technologies corporation, Bradley Paul Kline of Middletown CT (US) for raytheon technologies corporation
IPC Code(s): F01D11/00, F01D9/04
CPC Code(s): F01D11/001
Abstract: a stator vane assembly is disclosed herein. the stator vane assembly includes a stator box having a top side and a bottom side, a vane coupled to the top side of the stator box, and an integral seal coupled to the bottom side of the stator box, the integral seal extending away from the stator box and forming a tortuous path to prevent airflow below the stator box.
20240410313. WATER COOLED EXHAUST DUCT_simplified_abstract_(raytheon technologies corporation)
Inventor(s): Jon Erik Sobanski of Glastonbury CT (US) for raytheon technologies corporation
IPC Code(s): F02C3/30
CPC Code(s): F02C3/30
Abstract: a turbine engine assembly includes a condenser where water is extracted from the exhaust gas flow and an evaporator system where thermal energy from the exhaust gas flow is utilized to generate a steam flow from at least a portion of water that is extracted by the condenser for injection into the core flow path. a duct for the exhaust gas flow includes a cooling passage for a flow of water that accepts heat from the exhaust gas flow to cool the duct.
Inventor(s): Jon Erik Sobanski of Glastonbury CT (US) for raytheon technologies corporation
IPC Code(s): F02C3/30
CPC Code(s): F02C3/30
Abstract: a turbine engine assembly includes an active clearance control system that is configured to utilize water that is extracted from the exhaust gas flow to control a clearance between a tip of a rotating blade and a case structure by controlling thermal growth of the case structure. water extracted by the condenser is also provided to an evaporator system where thermal energy from the exhaust gas flow is utilized to transform water into a steam flow. a portion of water utilized in the active clearance control system is communicated to the evaporator system.
20240410392. HYBRID SHROUD IMPELLER_simplified_abstract_(raytheon technologies corporation)
Inventor(s): Parag H. Mathuria of Palm Beach Gardens FL (US) for raytheon technologies corporation, Lajos H. Horvath of Jupiter FL (US) for raytheon technologies corporation, Tsing-yi Lui of Palm City FL (US) for raytheon technologies corporation
IPC Code(s): F04D29/52, F04D29/32, F04D29/38
CPC Code(s): F04D29/526
Abstract: a hybrid shroud impeller including a hub having a first and a second axial end; the hub including an outer surface formed radially opposite a hub bore; a full blade extending radially from the outer surface; a splitter blade extending radially from the outer surface adjacent to the full blade; a bleed feature formed in a casing; a partial shroud integrally formed with a portion of the full blade and the splitter blade opposite the outer surface of the hub; a flow path formed between the outer surface of the hub, a shroud inner surface of the partial shroud and a blade surface of each of the full blade and the splitter blade; and the flow path extending from an inlet proximate the first axial end and an outlet proximate the second axial end; the partial shroud extends from the inlet to the bleed feature.
Inventor(s): Matthew E. Bintz of West Hartford CT (US) for raytheon technologies corporation, Bernard W. Pudvah of Portland CT (US) for raytheon technologies corporation
IPC Code(s): F04D29/56, F02C3/06, F04D29/64
CPC Code(s): F04D29/563
Abstract: an actuation structure changes the orientation of a vane airfoil. a spindle is fixed to the airfoil such that when the arm turns the spindle, the spindle turns the airfoil, the spindle extends through a bore in the housing. a mount is between the spindle and the housing at the bore, with a metal wear sleeve pressed into the housing at the bore, such that it is part of the housing. a bushing is secured to an outer periphery of the spindle such that a bearing surface during rotation of the spindle is provided by an outer periphery of the bushing and an inner periphery of the metal wear sleeve. a seal is radially outward of the bushing with the seal providing an air seal between the spindle and the bore. a gas turbine engine is also disclosed.
Inventor(s): William K. Ackermann of East Hartford CT (US) for raytheon technologies corporation, Andrew E. Breault of Bolton CT (US) for raytheon technologies corporation, Thomas E. Clark of Wells ME (US) for raytheon technologies corporation, Daniel B. Kupratis of Wallingford CT (US) for raytheon technologies corporation
IPC Code(s): F02C7/22
CPC Code(s): F23R3/60
Abstract: a gas turbine engine having an axial centerline is provided that includes compressor, combustor, and turbine sections, a tangential on board injector (tobi) system, and an hpc leakage guide structure. the compressor section has a high pressure compressor (hpc) that includes an hpc aft hub. the tobi system extends circumferentially around the engine axial centerline, and has a plurality of nozzles and an inner radial flange. the hpc leakage guide structure has forward and aft ends. the forward end is disposed and configured to receive a leakage flow from the hpc and the aft end is engaged with the tobi inner radial flange. the hpc leakage guide structure and the hpc aft hub define an hpc aft hub cavity. the hpc aft hub cavity extends between the forward and aft ends and has a flow area that is non-decreasing in a direction from the forward end to the aft end.
Inventor(s): Michael G. McCaffrey of Windsor CT (US) for raytheon technologies corporation
IPC Code(s): F28D15/02, F23R3/00
CPC Code(s): F28D15/0233
Abstract: an assembly is provided for an engine. this engine assembly includes a heat exchange apparatus, and the heat exchange apparatus includes a core, a shell and an inner flowpath. the core includes a core sidewall and a plurality of internal passages. the core sidewall extends axially along and circumferentially around an axis. the core sidewall extends radially from a core inner side to a core outer side. the core inner side forms an outer peripheral boundary of the inner flowpath. the internal passages are arranged circumferentially about the axis. each of the internal passages extends axially in the core sidewall. the shell extends axially along and circumscribes the core. the shell is abutted radially against the core outer side.
Inventor(s): Denver B. Overend of Salem CT (US) for raytheon technologies corporation
IPC Code(s): G01M15/02, F01D21/00, G01M15/14
CPC Code(s): G01M15/02
Abstract: a test assembly includes multiple instrumentation egresses disposed throughout the test assembly. multiple sensors are disposed through the test assembly. the number of sensors in the multiple sensors exceeds the number of instrumentation egresses in the plurality of instrumentation egresses and at least one pair of sensors in the plurality of sensors shares a single instrumentation egress.
Inventor(s): Justin Roger DeLarm of Bolton CT (US) for raytheon technologies corporation
IPC Code(s): G06F30/27, F01D21/00
CPC Code(s): G06F30/27
Abstract: a method of optimizing the assembly of rotating hardware of a gas turbine engine (gte) includes obtaining a respective input data set indicative of one or more contributors to unbalance for one or of a plurality of stages of one or more modules of the gte. for each of the module(s), one or more neural networks associated with the module are utilized to obtain, based on the respective input data set for the module, a set of optimized clock angles for arranging the stages of the module relative to each other to mitigate vibration of the gte. each of the first neural network(s) has been trained with training data including the contributor(s) to unbalance, and at least one rotor dynamics model that uses the training data and the set of clock angles from the neural network(s) to predict vibration at one or more locations of interest in the gte.
Inventor(s): Kin Gwn Lore of Belmont MA (US) for raytheon technologies corporation, Ganesh Sundaramoorthi of Duluth GA (US) for raytheon technologies corporation, Xinhua Zhang of Weatogue CT (US) for raytheon technologies corporation
IPC Code(s): G06T7/73, G06T7/11
CPC Code(s): G06T7/75
Abstract: a method for generating an application specific pose estimation responsive to a camera pose, a scene pose and an object pose includes generating an observed image (i) of an object and a scene using a camera and generating a current pose estimate having an object image render and a scene image render. the method further includes generating a final rendered output (i) by combining the object image render and the scene image render and processing the final rendered output (i) and the observed image (i) to generate a final pose estimate, wherein the final pose estimate matches the observed image (i).
Inventor(s): Paul R. Hanrahan of Sedona AZ (US) for raytheon technologies corporation, Daniel B. Kupratis of Wallingford CT (US) for raytheon technologies corporation
IPC Code(s): F02C6/20, B64D27/10, F02C7/32, F02C7/36, H02K7/102, H02K7/116, H02K7/18
CPC Code(s): H02K7/102
Abstract: an aircraft system is provided that includes a first turbine engine, a second turbine engine and an electrical system. the electrical system includes a clutch, a first electric machine and a second electric machine electrically coupled to the first electric machine. the first electric machine is mechanically coupled to a first rotating assembly of the first turbine engine. the second electric machine is mechanically coupled to a second rotating assembly of the second turbine engine through the clutch.
RAYTHEON TECHNOLOGIES CORPORATION patent applications on December 12th, 2024
- RAYTHEON TECHNOLOGIES CORPORATION
- B01J6/00
- C01B3/04
- CPC B01J6/008
- Raytheon technologies corporation
- B22F10/73
- B22F10/28
- B22F10/80
- B29C64/153
- B29C64/357
- B29C64/386
- B33Y10/00
- B33Y40/00
- B33Y50/00
- CPC B22F10/73
- B60W20/13
- B60L50/16
- B60W10/06
- B60W10/08
- CPC B60L50/16
- C01B13/02
- CPC C01B3/042
- B04B5/10
- F01D5/18
- CPC F01D5/187
- F01D9/04
- F01D9/06
- CPC F01D5/189
- F01D11/00
- CPC F01D11/001
- F02C3/30
- CPC F02C3/30
- F04D29/52
- F04D29/32
- F04D29/38
- CPC F04D29/526
- F04D29/56
- F02C3/06
- F04D29/64
- CPC F04D29/563
- F02C7/22
- CPC F23R3/60
- F28D15/02
- F23R3/00
- CPC F28D15/0233
- G01M15/02
- F01D21/00
- G01M15/14
- CPC G01M15/02
- G06F30/27
- CPC G06F30/27
- G06T7/73
- G06T7/11
- CPC G06T7/75
- F02C6/20
- B64D27/10
- F02C7/32
- F02C7/36
- H02K7/102
- H02K7/116
- H02K7/18
- CPC H02K7/102
