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公开(公告)号：US12216184B2
公开(公告)日：2025-02-04
申请号：US18310937
申请日：2023-05-02
Applicant: Raytheon Technologies Corporation
Inventor： Andrew DeBiccari , Zhong Ouyang
Abstract: A system for magnetically inspecting a metallic component uses a manipulator configured to manipulate a relative position between a part fixture that holds the metallic component and a probe fixture that holds a magnetic probe, thereby causing the probe tip to trace an inspection route along the surface of the metallic component so that the probe tip contacts the metallic component such that an angular difference between the probe axis and a vector normal to the surface is less than a predetermined angle delta. The magnetic probe has a probe tip that measures magnetic permeability of the metallic component along the inspection route, which the controller receives. A method of performing the magnetic inspection is also disclosed.
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公开(公告)号：US12215865B2
公开(公告)日：2025-02-04
申请号：US17714064
申请日：2022-04-05
Applicant: Raytheon Technologies Corporation
Inventor： Tianli Zhu , Richard Wesley Jackson, III , John A. Sharon , James T. Beals , Brian T. Hazel
IPC: F23R3/00
Abstract: A gas turbine engine component having a substrate; a thermal barrier coating on the substrate having a porous microstructure; and a reflective layer conforming to the porous microstructure of the thermal barrier coating, wherein the reflective layer comprises a conforming nanolaminate defined by alternating layers of platinum group metal materials selected from the group consisting of platinum group metal-based alloys, platinum group metal intermetallic compounds, mixtures of platinum group metal with metal oxides and combinations thereof. A capping layer can be added over the reflective layer. A supporting layer can be added between the reflective layer and the thermal barrier coating. A process is also disclosed.
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公开(公告)号：US12209997B2
公开(公告)日：2025-01-28
申请号：US17730114
申请日：2022-04-26
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Derek J. Michaels , Elizabeth F. Vinson , Zhong Ouyang
Abstract: An inspection device is disclosed herein. The inspection device may comprise: a support structure; a motor; a shaft operably coupled to the motor, the shaft extending from a first side of the support structure to a second side of the support structure, the shaft configured to couple to a bladed rotor; an optical device moveably coupled to the support structure; and a broad-band energy source configured to generate acoustic energy through the bladed rotor during inspection.
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公开(公告)号：US20250027422A1
公开(公告)日：2025-01-23
申请号：US18224908
申请日：2023-07-21
Applicant: Raytheon Technologies Corporation
Inventor： Andrew E. Breault , William K. Ackermann
Abstract: A buffer air assembly for an aircraft engine includes a low-pressure header, a high-pressure header, a low-pressure bleed air source, a high-pressure bleed air source, and an electric buffer compressor. The low-pressure header is connected to at least one low-pressure bearing compartment. The high-pressure header is connected to at least one high-pressure bearing compartment. The low-pressure bleed air source is connected to the low-pressure header. The low-pressure bleed air source is configured to direct a low-pressure buffering air to the at least one low-pressure bearing compartment through the low-pressure header. The high-pressure bleed air source is configured to direct a high-pressure buffering air to the at least one high-pressure bearing compartment through the high-pressure header. The electric buffer compressor is connected to the low-pressure header and the high-pressure header. The electric buffer compressor is configured to direct pressurized buffering air to the low-pressure header and the high-pressure header.
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公开(公告)号：US20250026482A1
公开(公告)日：2025-01-23
申请号：US18224430
申请日：2023-07-20
Applicant: Raytheon Technologies Corporation
Inventor： Cameron B. Sahirad , Alek Gavrilovski , Lichu Zhao
Abstract: A method of producing an operational data for an aircraft turbine engine is provided that including: sensing an inlet airflow to an aircraft turbine engine for CMAS particulate matter, the sensing performed during one or more ground portions of a flight operational cycle of the turbine engine, the sensing producing sensor signals indicative of the presence or absence of the CMAS particulate matter; determining a presence or absence of an exposure by the turbine engine to a CMAS environment based on the sensor signals; and producing an operational data indicative of the presence or absence of said exposure by the turbine engine to said CMAS environment.
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Patent Agency Ranking
6.发明授权公开(公告)号：US12203392B2
公开(公告)日：2025-01-21
申请号：US18117919
申请日：2023-03-06
Applicant: Raytheon Technologies Corporation
Inventor： Jon E. Sobanski
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.
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公开(公告)号：US20250020558A1
公开(公告)日：2025-01-16
申请号：US18352945
申请日：2023-07-14
Applicant: Raytheon Technologies Corporation
Inventor： Garrett KERNOZICKY , Jesse R. BOYER , Ashwin RAGHAVAN , Peter John BREITZMANN , Praba Kharan BAPTIST , Michael L. VUKOVINSKY , Lawrence A BINEK
IPC: G01N3/02
Abstract: A method for repairing a stator stage is disclosed herein. The method includes receiving a stator stage including a plurality of stator vanes disposed between an outer diameter and an inner diameter, analyzing the stator stage for defects, determining there is a first defect in a first segment of a the stator stage, the first segment including at least one of a first portion of the outer diameter, a first portion of the inner diameter, or a first stator vane, removing the first segment from the stator stage forming a void in the stator stage, manufacturing a second segment that is the same size as the first segment, attaching the second segment to the stator stage to fill the void, performing a blending process on the stator stage including the second segment to smooth the plurality of stator vanes including the second stator vane.
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公开(公告)号：US12196224B2
公开(公告)日：2025-01-14
申请号：US18207761
申请日：2023-06-09
Applicant: Raytheon Technologies Corporation
Inventor： Matthew E. Bintz , Bernard W. Pudvah
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.
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公开(公告)号：US12194522B2
公开(公告)日：2025-01-14
申请号：US17513720
申请日：2021-10-28
Applicant: Raytheon Technologies Corporation
Inventor： Agnieszka Wusatowska-Sarnek , John Palitsch
Abstract: An apparatus for backward flow forming a material may comprise a mandrel having a headstock at a proximate end of the mandrel, the mandrel configured to rotate about an axis, a plurality of rollers disposed radially outward of the mandrel configured to exert force on the material to form a work piece at a plastic deformation zone, wherein the work piece flows from the plastic deformation zone between the plurality of rollers and the mandrel toward a distal end of the mandrel, and a catcher, coaxial to the mandrel, and removably coupled to the work piece at a traveling end of the work piece.
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公开(公告)号：US12188563B2
公开(公告)日：2025-01-07
申请号：US18128568
申请日：2023-03-30
Applicant: Raytheon Technologies Corporation
Inventor： Caroline A. Karanian , Conway Chuong
Abstract: A seal assembly configured to reduce fluid flow from an axially upstream side of the seal assembly to an axially downstream side of the seal assembly includes a primary seal and a secondary seal assembly disposed at an axially forward end of the primary seal. The secondary seal assembly includes a seal support and a secondary seal. The seal support includes a downstream axial face disposed axially proximate to and facing the primary seal, an upstream axial face opposite the downstream axial face, a body extending from the downstream axial face to the upstream axial face, a first leg extending radially inward from the body, a second leg extending radially inward from the body, and a mistake-proofing protrusion extending from the upstream axial face and in an axially upstream direction.
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