RTX Corporation patent applications on February 27th, 2025
Patent Applications by RTX Corporation on February 27th, 2025
RTX Corporation: 24 patent applications
RTX Corporation has applied for patents in the areas of F01D5/28 (8), F01D5/18 (3), G01M15/14 (3), F02C3/04 (3), F01D21/00 (3) F01D5/282 (6), F01D5/18 (2), C04B35/80 (2), G01M15/14 (2), B22C9/061 (1)
With keywords such as: vane, platform, engine, build, face, configured, turbine, gas, assembly, and valve in patent application abstracts.
Patent Applications by RTX Corporation
20250065396. Casting Core Post and Socket Joint_simplified_abstract_(rtx corporation)
Inventor(s): Jordan T. Lowell of Crozet VA (US) for rtx corporation, Anthony J. Del Boccio of Charlottesville VA (US) for rtx corporation
IPC Code(s): B22C9/06, B22C9/10
CPC Code(s): B22C9/061
Abstract: a casting core assembly comprising: a first ceramic piece including a projecting post; a second ceramic piece including a socket encircling the post; and a ceramic filler material between the post and the socket, wherein at least one of: in axial section at at least one location the post has: a lateral protrusion of at least 15 micrometers relative to a location proximal thereof; and in axial section at at least one location socket has: a lateral recess of at least 15 micrometers relative to a location outboard thereof.
Inventor(s): Lawrence A. Binek of Glastonbury CT (US) for rtx corporation, Joseph E. Ott of Enfield CT (US) for rtx corporation, Benjamin G. Gardell of Bristol CT (US) for rtx corporation, Dean R. Sirois of Enfield CT (US) for rtx corporation, Alexandru Cadar of Eastford CT (US) for rtx corporation, Jesse R. Boyer of Middletown CT (US) for rtx corporation, Michael Walter Bennett of East Hartford AL (US) for rtx corporation
IPC Code(s): B22F12/30, B22F10/28, B22F12/90, B33Y10/00, B33Y30/00, B33Y50/00
CPC Code(s): B22F12/30
Abstract: a powder bed fusion (pbf) additive manufacturing (am) machine includes a build plate configured to function as a platform to support one or more parts built using the pbf am machine. the build plate further includes a thermal history indicator positioned on the build plate, attached to the build plate, or physically integrated with the build plate such that the thermal history indicator experiences the same temperature as the build plate. the thermal history indicator is configured to display a durable visual indication of achievement of a temperature associated with a post-processing step performed after the one or more parts are built on the build platform.
Inventor(s): Paul E. Denney of Northborough MA (US) for rtx corporation, Andrew H. Lubin of Weaverville NC (US) for rtx corporation, Joseph V. Paturzo of Avon CT (US) for rtx corporation
IPC Code(s): B23H7/32, B23H7/30
CPC Code(s): B23H7/32
Abstract: a manufacturing method is provided during which a workpiece is electrical discharge machined using an electrode to form an aperture in the workpiece. a first voltage is measured indicative of a gap voltage between the electrode and the workpiece using a first measurement device to provide a first measurement signal indicative of the first voltage. movement of the electrode is controlled using the first measurement signal. a second voltage is measured indicative of the gap voltage using a second measurement device to provide a second measurement signal indicative of the second voltage. a determination is made whether the electrode has broken through the workpiece using the second measurement signal.
Inventor(s): Paul E. Denney of Northborough MA (US) for rtx corporation, Peter M. Malicki of East Hampton CT (US) for rtx corporation
IPC Code(s): B23K26/03, B23K26/0622, B23K26/382
CPC Code(s): B23K26/032
Abstract: a manufacturing method is provided during which an aperture is machined into workpiece using a laser beam. an image of an interaction between the laser beam and the workpiece is captured during the machining of the aperture using a camera with an electronic shutter. a parameter associated with the aperture is determined based on information from the image.
20250065444. MULTI-PROCESS MACHINING OF A WORKPIECE_simplified_abstract_(rtx corporation)
Inventor(s): Paul E. Denney of Northborough MA (US) for rtx corporation
IPC Code(s): B23K26/382, B23K26/146
CPC Code(s): B23K26/382
Abstract: during a manufacturing method, a workpiece is provided that includes a face surface and a back surface. a first aperture is machined into the workpiece using an energy beam. the first aperture projects partially into the workpiece from the face surface to an end of the first aperture. a waterjet is directed into the first aperture to machine a second aperture into the workpiece. the second aperture extends from the end of the first aperture to the back surface.
Inventor(s): Lawrence A. Binek of Glastonbury CT (US) for rtx corporation, Joseph E. Ott of Enfield CT (US) for rtx corporation, Dean R. Sirois of Enfield CT (US) for rtx corporation, Jesse R. Boyer of Middletown CT (US) for rtx corporation, Benjamin G. Gardell of Bristol CT (US) for rtx corporation, Michael Walter Bennett of East Hartford CT (US) for rtx corporation, Alexandru Cadar of Eastford CT (US) for rtx corporation
IPC Code(s): B29C64/307, B29C64/153, B29C64/35, B29C64/393
CPC Code(s): B29C64/307
Abstract: a build powder characterization system for an additive manufacturing (am) machine includes a build powder collection system, a build powder analyzer, and a controller. the build powder collection system configured to collect build powder during an am machine build campaign. the build powder analyzer configured to receive from the build powder collection system the collected build powder, to analyze selected build powder properties, and to communicate to a controller data reflecting properties of the collected build powder. the controller is configured to process data, received from the build powder analyzer, reflecting properties of the collected build powder.
20250066259. MULTI-MANDREL BRAIDING PROCESS_simplified_abstract_(rtx corporation)
Inventor(s): Kathryn S. Read of Marlborough CT (US) for rtx corporation
IPC Code(s): C04B35/80, C04B35/628
CPC Code(s): C04B35/80
Abstract: a system for forming multiple braided preform segments includes a mandrel assembly disposed along a mandrel axis, a radial braider for winding fibers onto the mandrel assembly to form a continuous braided article, an applicator for applying a polymer binder to the braided article while mounted on the mandrel assembly, and a debulking tool for debulking the braided article while mounted on the mandrel assembly. the mandrel assembly includes a lead-in extension defining a first end, an end extension defining a second end, and a plurality of mandrels removably connected to a plurality of transition pieces and disposed axially between the lead-in extension and the end extension.
20250066260. POLYMER TOWPREG FOR CERAMIC MATRIX COMPOSITES_simplified_abstract_(rtx corporation)
Inventor(s): John D. Riehl of Hebron CT (US) for rtx corporation, Nitin Garg of Avon CT (US) for rtx corporation, Olivier H. Sudre of Glastonbury CT (US) for rtx corporation, Zachary Paul Konopaske of West Hartford CT (US) for rtx corporation, Brendan Lenz of North Branford CT (US) for rtx corporation, Nil Parikh of Newington CT (US) for rtx corporation
IPC Code(s): C04B35/80, C04B35/626, C04B35/628, C04B35/634, C04B35/64, D06M15/333, D06M101/16
CPC Code(s): C04B35/80
Abstract: a method of fabricating a fibrous ceramic preform includes impregnating a plurality of individual ceramic tows with a first polymer binder, incorporating the plurality of impregnated ceramic tows into a ceramic fabric, applying a solution comprising a second polymer binder and a second solvent to the ceramic fabric, and incorporating the ceramic fabric into the preform. the first polymer binder is insoluble in the second solvent.
Inventor(s): Zhiqiang Wang of South Glastonbury CT (US) for rtx corporation, Nicholas J. Lawliss of West Hartford CT (US) for rtx corporation
IPC Code(s): F01D5/02
CPC Code(s): F01D5/027
Abstract: a rotor module, including: a blade cluster of a plurality of blades secured to a rotor disk of the rotor module; and counter weights secured to the rotor disk, wherein the counter weights cause a center of gravity of the plurality of blades to be zeroed out with respect to an axis “o” of the rotor disk and wherein the counter weights cause a moment of inertia jx about an x axis of the rotor disk is equal to a moment of inertia jy about a y axis of the rotor disk when the rotor module is rotated about the axis “o”.
20250067182. BATHTUB SEAL INTEGRATED INTO CMC VANE LOAD PATH_simplified_abstract_(rtx corporation)
Inventor(s): David J. Wasserman of Hamden CT (US) for rtx corporation
IPC Code(s): F01D5/18, F01D5/28, F02C7/28
CPC Code(s): F01D5/18
Abstract: a vane assembly includes a vane having an outer platform with mount structure and an airfoil extending inwardly from the mount structure and formed of ceramic matrix composites (“cmc”). the vane has an internal cooling chamber. a metal baffle is received within the internal cooling chamber and extends beyond the platform. a bathtub seal has a central portion receiving the metal baffle. the metal baffle has a central chamber and cooling air holes to deliver cooling air into the internal cooling chamber. the bathtub seal has an inner wall and an outer wall outward of the metal baffle. the inner wall, the outer wall and a bottom wall define a bathtub seal chamber. the bottom wall is in contact with an upper surface of the vane. the vane is connected to the outer wall. static structure is received within the bathtub seal chamber. a gas turbine engine is also disclosed.
20250067183. BATHTUB SEAL FOR DAMPING CMC VANE PLATFORM_simplified_abstract_(rtx corporation)
Inventor(s): Thomas S. Heylmun of Palm City FL (US) for rtx corporation, Cheng Gao of South Glastonbury CT (US) for rtx corporation, David J. Wasserman of Hamden CT (US) for rtx corporation
IPC Code(s): F01D5/18, F01D5/28, F01D11/00, F02C3/04, F02C7/12
CPC Code(s): F01D5/18
Abstract: a vane assembly includes a vane having an outer platform with mount structure and an airfoil extending inwardly from the outer platform and formed of ceramic matrix composites (“cmc”). the vane having an internal cooling chamber. a metal baffle is received within the internal cooling chamber and extends beyond the outer platform. a bathtub seal has a central portion receiving the metal baffle. the metal baffle has a central chamber and cooling air holes to deliver cooling air into the internal cooling chamber. the bathtub seal having an inner wall and an outer wall outward of the metal baffle. the inner wall, the outer wall and a base wall define a bathtub seal chamber. the base wall is in contact with the outer platform. the vane is connected to the outer wall. the static structure is received within the bathtub seal chamber. a connection is configured to deliver pressurized air to the bathtub seal chamber. a gas turbine engine is also disclosed.
Inventor(s): Howard J. Liles of Newington CT (US) for rtx corporation
IPC Code(s): F01D5/28
CPC Code(s): F01D5/282
Abstract: a cmc component for a gas turbine engine includes an airfoil including a leading edge, a trailing edge, a suction sidewall, and a pressure sidewall having a locally-thickened region, the locally-thickened region being a maximum thickness region of the pressure sidewall. the locally-thickened region has a first thickness, a maximum thickness region of the suction sidewall has a second thickness, and the first thickness is greater than the second thickness.
Inventor(s): David J. Wasserman of Hamden CT (US) for rtx corporation, Craig R. McGarrah of Southington CT (US) for rtx corporation
IPC Code(s): F01D5/28, F01D5/18, F01D9/04
CPC Code(s): F01D5/282
Abstract: a method of forming a vane assembly for a gas turbine engine includes the steps of 1) determining a re-stagger angle for an airfoil on a ceramic matrix composite (“cmc”) vane, 2) determine an adjusted position of a baffle to be inserted within a central chamber in the vane, inserting the baffle into a bathtub seal, and adjusting an upper face of the baffle to an orientation relative to a bathtub seal support face to account for the adjusted position of the baffle and 3) fixing the baffle upper face to the bathtub seal flange support face. a vane assembly and a gas turbine engine are also disclosed.
20250067187. RADIAL SEAL BETWEEN CMC VANE AND VANE SUPPORT_simplified_abstract_(rtx corporation)
Inventor(s): Howard J. Liles of Newington CT (US) for rtx corporation
IPC Code(s): F01D5/28, F01D25/12
CPC Code(s): F01D5/282
Abstract: a gas turbine engine includes a ceramic matrix composite (cmc) vane arc segment that has first and second platforms and an airfoil section that extends radially therebetween. the airfoil section includes an internal through-cavity, and the first and second platforms include, respectively, platform inlet and outlet ports connected to the internal through-cavity for conveying cooling air. the cmc vane arc segment is radially mounted between first and second metallic vane supports. the second metallic vane support includes a plenum and a plenum inlet port connected with the platform outlet port for receiving the cooling air from the internal through-cavity. there is a seal located radially between the second platform and the second metallic vane support. the seal circumscribes the platform outlet port to limit leakage of the cooling air between the second platform and the second metallic vane support.
20250067188. TILTED CMC VANE ARC SEGMENT_simplified_abstract_(rtx corporation)
Inventor(s): Howard J. Liles of Newington CT (US) for rtx corporation, Cheng Gao of South Glastonbury CT (US) for rtx corporation, Bryan P. Dube of Chepachet RI (US) for rtx corporation
IPC Code(s): F01D5/28
CPC Code(s): F01D5/282
Abstract: an article includes a ceramic matrix composite (cmc) vane arc segment for disposal about an engine central axis. the cmc vane arc segment includes first and second platforms and an airfoil section that extends therebetween. the airfoil section defines a radial stacking axis that is oblique to a z-axis that is perpendicular to the engine central axis such that the radial stacking axis forms a non-zero angle with the z-axis.
20250067189. CMC VANE ARC SEGMENTS WITH FRICTION DAMPER_simplified_abstract_(rtx corporation)
Inventor(s): David J. Wasserman of Hamden CT (US) for rtx corporation
IPC Code(s): F01D5/28, F02C3/04
CPC Code(s): F01D5/282
Abstract: a gas turbine engine includes first and second cmc vane arc segments arranged about an engine central axis. each of the cmc vane arc segments has a platform and an airfoil section that extends off of the platform. the platform defines an axially trailing face, an axially leading face that is circumferentially offset from the axially trailing face, and first and second circumferential faces that extend from the axially trailing face to the axially leading face. the first circumferential face of the first cmc vane arc segment interfaces with the second circumferential face of the second cmc vane arc segment. there is at least one friction damper between the first circumferential face of the first cmc vane arc segment and the second circumferential face of the second cmc vane arc segment.
20250067190. CMC VANE WITH DETUNED PLATFORM_simplified_abstract_(rtx corporation)
Inventor(s): Cheng Gao of South Glastonbury CT (US) for rtx corporation, David J. Wasserman of Hamden CT (US) for rtx corporation, Thomas S. Heylmun of Palm City FL (US) for rtx corporation
IPC Code(s): F01D5/28, F02C3/04
CPC Code(s): F01D5/282
Abstract: a method is disclosed for a design geometry of a ceramic matrix composite (cmc) vane arc segment that has a platform and an airfoil section that extends off of the platform. the platform defines an axially trailing face, an axially leading face that is circumferentially offset from the axially trailing face, and first and second circumferential faces. in the method, a modal excitation response of the platform is determined based upon an external engine operation excitation frequency. if the modal excitation response is greater than a target modal excitation response, the design geometry of the platform is adjusted to be detuned with the external engine operation excitation frequency by reducing an overhang distance of the platform in which the modal excitation response at the external engine operation excitation frequency is equal to or lower than the target modal excitation response.
20250067194. OPTICAL IN-SITU INSPECTION SYSTEM_simplified_abstract_(rtx corporation)
Inventor(s): Jeremiah C. Lee of Coventry CT (US) for rtx corporation, David L. Lincoln of Cromwell CT (US) for rtx corporation, Scott Goyette of Moosup CT (US) for rtx corporation, Zaffir A. Chaudhry of Portland CT (US) for rtx corporation, Danbing Seto of Avon CT (US) for rtx corporation
IPC Code(s): F01D21/00
CPC Code(s): F01D21/003
Abstract: an in-situ system for a gas turbine engine blade inspection including a sensor system configured to capture images of a forward surface of at least one gas turbine engine blade; a processor coupled to the sensor system, the processor configured to determine damage to the at least one gas turbine engine blade based on video analytics; and a tangible, non-transitory memory configured to communicate with the processor, the tangible, non-transitory memory having instructions stored therein that, in response to execution by the processor, cause the processor to perform operations comprising receiving, by the processor, data for the forward surface of at least one gas turbine engine blade from the sensor system; determining, by the processor, a rotational speed of a fan; and determining, by the processor, a fan synchronization.
20250067284. FLUID SYSTEM WITH MULTI-MODE TRANSFER VALVE_simplified_abstract_(rtx corporation)
Inventor(s): Jeffrey R. Rigali of South Windsor CT (US) for rtx corporation, Christopher T. Koetsch of East Longmeadow MA (US) for rtx corporation, Ryan P. Susca of Windsor CT (US) for rtx corporation, David C. Kiely of West Springfield MA (US) for rtx corporation, Michael Voytovich of Madison CT (US) for rtx corporation
IPC Code(s): F15B13/043, F15B21/02
CPC Code(s): F15B13/043
Abstract: a fluid system is provided that includes a first actuator, a second actuator and a valve system. the valve system includes a first control valve, a second control valve and a transfer valve. during a first mode of operation, the transfer valve is configured to fluidly couple the first control valve to the first actuator and fluidly couple the second control valve to the second actuator, and the transfer valve is also configured to fluidly decouple the first control valve from the second actuator and fluidly decouple the second control valve from the first actuator. during a second mode of operation, the transfer valve is configured to fluidly couple the first control valve to the first actuator and the second actuator, and the transfer valve is also configured to fluidly decouple the second control valve from the first actuator and the second actuator.
Inventor(s): Steven C. Laudage of Portland ME (US) for rtx corporation
IPC Code(s): F16N25/04, B05C1/02, B05C11/10
CPC Code(s): F16N25/04
Abstract: an applicator assembly for applying a liquid to at least one fastener includes a housing, a vat body, at least one applicator roller pair, and at least one removal roller pair. the housing includes a sidewall assembly. the sidewall assembly extends between and to a bottom end and a top end. the vat body is disposed within the sidewall assembly. the vat body extends between and to a bottom side and a top side. the vat body forms a liquid cavity at the top side. the at least one applicator roller pair is disposed within the liquid cavity. the at least one applicator roller pair includes a first applicator roller and a second applicator roller. the at least one removal roller pair is disposed between the liquid cavity and the top end. the at least one removal roller pair includes a first removal roller and a second removal roller.
20250067515. MULTI-MODE COOLING FOR HEAT SOURCE_simplified_abstract_(rtx corporation)
Inventor(s): Michael K. Ikeda of West Hartford CT (US) for rtx corporation
IPC Code(s): F28D7/00, B64D33/08, F28F27/02, H10N19/00
CPC Code(s): F28D7/0066
Abstract: a method of operation is provided during which heat energy is transferred into a first heat exchange fluid during a first mode of operation and during a second mode of operation. the first heat exchange fluid is directed through a first flowpath of a heat exchanger during the first mode of operation and during the second mode of operation. a second heat exchange fluid is directed through a second flowpath of the heat exchanger during the first mode of operation. at least some of the heat energy is transferred from the first heat exchange fluid into the second heat exchange fluid. a third heat exchange fluid is directed through a third flowpath of the heat exchanger during the second mode of operation. at least some of the heat energy is transferred from the first heat exchange fluid into the third heat exchange fluid.
Inventor(s): Nicholas J. Lawliss of West Hartford CT (US) for rtx corporation, Zhiqiang Wang of South Glastonbury CT (US) for rtx corporation
IPC Code(s): G01M1/12, F01D5/16, G01M15/14
CPC Code(s): G01M1/122
Abstract: a counter weight for use with a rotor module, including: a root portion; a main body portion that extends away from the root portion; a pair of side portions each extending from opposite sides of the main body portion; and at least one plate secured to one of the opposite sides of the main body portion in order to adjust a weight of the counter weight.
20250067625. OPTICAL DEFECT DETECTION SYSTEM_simplified_abstract_(rtx corporation)
Inventor(s): Jeremiah C. Lee of Coventry CT (US) for rtx corporation, William K. Donat of Manchester CT (US) for rtx corporation, Scott Goyette of Moosup CT (US) for rtx corporation, Danbing Seto of Avon CT (US) for rtx corporation
IPC Code(s): G01M15/14, F01D21/00, G03B15/06, G06T7/00
CPC Code(s): G01M15/14
Abstract: an in-situ system for a gas turbine engine blade inspection including a sensor system configured to capture images of a forward surface of at least one gas turbine engine blade; a processor coupled to the sensor system, the processor configured to determine damage to the at least one gas turbine engine blade based on image analytics; and a tangible, non-transitory memory configured to communicate with the processor, the tangible, non-transitory memory having instructions stored therein that, in response to execution by the processor, cause the processor to perform operations comprising receiving, by the processor, data for the forward surface of at least one gas turbine engine blade from the sensor system; and determining, by the processor, surface damage responsive to the light source.
Inventor(s): Sheridon Haye of College Station TX (US) for rtx corporation
IPC Code(s): G01M15/14, F01D21/00, F01D25/32
CPC Code(s): G01M15/14
Abstract: an assembly for a gas turbine engine according to an example of the present disclosure may include at least one rotatable airfoil, at least one vibration sensor operable to detect vibration of the at least one airfoil at one or more rotational frequencies, and a controller operatively coupled to the at least one vibration sensor. the controller may be operable to determine an accretion level associated with accretion of glass on the at least one airfoil in response to comparing vibration of the at least one airfoil at the one or more rotational frequencies to a vibratory pattern associated with accretion of glass. a method of operation is also disclosed.
- RTX Corporation
- B22C9/06
- B22C9/10
- CPC B22C9/061
- Rtx corporation
- B22F12/30
- B22F10/28
- B22F12/90
- B33Y10/00
- B33Y30/00
- B33Y50/00
- CPC B22F12/30
- B23H7/32
- B23H7/30
- CPC B23H7/32
- B23K26/03
- B23K26/0622
- B23K26/382
- CPC B23K26/032
- B23K26/146
- CPC B23K26/382
- B29C64/307
- B29C64/153
- B29C64/35
- B29C64/393
- CPC B29C64/307
- C04B35/80
- C04B35/628
- CPC C04B35/80
- C04B35/626
- C04B35/634
- C04B35/64
- D06M15/333
- D06M101/16
- F01D5/02
- CPC F01D5/027
- F01D5/18
- F01D5/28
- F02C7/28
- CPC F01D5/18
- F01D11/00
- F02C3/04
- F02C7/12
- CPC F01D5/282
- F01D9/04
- F01D25/12
- F01D21/00
- CPC F01D21/003
- F15B13/043
- F15B21/02
- CPC F15B13/043
- F16N25/04
- B05C1/02
- B05C11/10
- CPC F16N25/04
- F28D7/00
- B64D33/08
- F28F27/02
- H10N19/00
- CPC F28D7/0066
- G01M1/12
- F01D5/16
- G01M15/14
- CPC G01M1/122
- G03B15/06
- G06T7/00
- CPC G01M15/14
- F01D25/32
