公开(公告)号：US20240418177A1

公开(公告)日：2024-12-19

申请号：US18209272

申请日：2023-06-13

Applicant: Raytheon Technologies Corporation

Inventor： Lawrence A. Binek ,  Jose R. Paulino

IPC: F04D29/053 ,  F04D29/20

Abstract: A method of manufacturing is provided. During this method, a body is formed using an additive manufacturing process. The body includes a shaft, a bladed rotor and a support structure. The shaft projects axially along an axis out from the bladed rotor. The support structure projects radially out from the shaft and axially to the bladed rotor. The support structure includes a plurality of channels arranged circumferentially about the axis. Each of the channels projects radially into the support structure towards the axis and to a respective channel side. Each of the channels projects axially into the support structure towards the bladed rotor and to a respective channel end.

公开(公告)号：US20240416424A1

公开(公告)日：2024-12-19

申请号：US18334179

申请日：2023-06-13

Applicant: Raytheon Technologies Corporation

Inventor： Sergei F. Burlatsky ,  Andreas Karl Roelofs ,  Masoud Anahid ,  Ranadip Acharya ,  Tahany El-Wardany ,  David U. Furrer

IPC: B22F10/85 ,  B22F10/28 ,  B22F12/20 ,  B33Y10/00 ,  B33Y40/20 ,  B33Y50/02

Abstract: The present disclosure provides improved additive manufacturing methods and systems. More particularly, the present disclosure provides advantageous additive manufacturing methods and systems for the production of hierarchical design optimized components (e.g., composite or composite-like materials). The present disclosure provides a methodology to produce hierarchical design optimized additively manufactured parts/materials that include an inhomogeneous structure with variable local mechanical properties across the entire volume. Hierarchical inhomogeneous structure/composite materials can be produced through a laser powder bed fusion (LPBF) process. A novel LPBF method can be used to obtain location-specific properties through in-situ controlling of the local cooling rate during the additive manufacturing process.

公开(公告)号：US20240410587A1

公开(公告)日：2024-12-12

申请号：US18208113

申请日：2023-06-09

Applicant: Raytheon Technologies Corporation

Inventor： William K. Ackermann ,  Andrew E. Breault ,  Thomas E. Clark ,  Daniel B. Kupratis

IPC: F02C7/22

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.

公开(公告)号：US20240410284A1

公开(公告)日：2024-12-12

申请号：US18331124

申请日：2023-06-07

Applicant: Raytheon Technologies Corporation

Inventor： Jeffrey T. Morton

IPC: F01D5/18 ,  F01D9/04 ,  F01D9/06

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.

公开(公告)号：US20240410283A1

公开(公告)日：2024-12-12

申请号：US18208689

申请日：2023-06-12

Applicant: Raytheon Technologies Corporation

Inventor： Dana K. Bondarevsky ,  Dominic J. Mongillo, JR. ,  Christopher Paul Perron ,  Yuta Yoshimura ,  David D. Chapdelaine

IPC: F01D5/18

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.

公开(公告)号：US12163446B2

公开(公告)日：2024-12-10

申请号：US18187839

申请日：2023-03-22

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jon E. Sobanski ,  Howard J. Liles ,  Bryan P. Dube ,  Wojciech Lipka

IPC: F01D9/04 ,  F01D5/18 ,  F01D5/28

Abstract: A vane arc segment includes an airfoil fairing that has first and second fairing platforms and a hollow airfoil section that extends there between. A spar has a spar platform adjacent the first fairing platform and a spar leg that extends from the spar platform and through the hollow airfoil section. The spar leg has an end portion that is distal from the spar platform and that protrudes from the second fairing platform. The end portion has a clevis mount. There is a support platform adjacent the second fairing platform. The support platform has a through-hole through which the end portion of the spar leg extends such that the clevis mount protrudes from the support platform. A pin extends though the clevis mount and locks the support platform to the spar leg such that the airfoil fairing is trapped between the spar platform and the support platform.

公开(公告)号：US20240401537A1

公开(公告)日：2024-12-05

申请号：US18205333

申请日：2023-06-02

Applicant: Raytheon Technologies Corporation

Inventor： Paul R. Hanrahan ,  Gregory E. Reinhardt

IPC: F02C7/36 ,  F01D15/12

Abstract: An assembly is provided for an aircraft. This aircraft assembly includes a geartrain, a first bladed rotor, a second bladed rotor and a rotating structure. The geartrain includes a sun gear, a ring gear, a plurality of intermediate gears and a carrier. The ring gear circumscribes the sun gear and is rotatable about an axis. Each of the intermediate gears is between and meshed with the sun gear and the ring gear. Each of the intermediate gears is rotatably mounted to the carrier. The carrier is rotatable about the axis. The first bladed rotor is coupled to the ring gear. The second bladed rotor is coupled to the carrier. The rotating structure is coupled to the sun gear. The rotating structure includes a turbine rotor. The rotating structure is configured to drive rotation of the first bladed rotor and the second bladed rotor through the geartrain.

公开(公告)号：US12157708B2

公开(公告)日：2024-12-03

申请号：US17314434

申请日：2021-05-07

Applicant: Raytheon Technologies Corporation

Inventor： Robin H. Fernandez

IPC: C23C16/458 ,  C04B41/53

Abstract: A method for forming a hole in a ceramic matrix composite component includes providing a first tool component with a first hole, providing a fiber preform of the ceramic matrix composite component on the first tool component, positioning a second tool component on the fiber preform, such that the fiber preform is disposed between the first and second tool components, inserting a rod into the first and second holes and through the fiber preform, and performing a densification step of the fiber preform in the first and second tool components. The second tool component has a second hole coaxial with the first hole. The fiber preform is densified with a ceramic matrix.

公开(公告)号：US20240391599A1

公开(公告)日：2024-11-28

申请号：US18202688

申请日：2023-05-26

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Pratyush Kumar ,  Yasir Al-Nadawi ,  Milos Ilak

IPC: B64D31/00 ,  G06N3/08

Abstract: A method for a HEP system includes obtaining, for each of a plurality of mission profiles, a respective first power splitting profile to be used throughout one or more flights described by the mission profile to achieve a fuel consumption objective for the one or more flights. Each power splitting profile indicates a series of power splits between a gas turbine and an electric motor of the HEP system. A neural network is trained to mimic the first power splitting profiles for the plurality of mission profiles. During one or more actual flights corresponding to a particular mission profile of an aircraft that includes a particular HEP system, the neural network is utilized to obtain a second power splitting profile for the particular HEP system for the one or more actual flights, and an output action for the particular HEP system is performed based on the second power splitting profile.

公开(公告)号：US20240390987A1

公开(公告)日：2024-11-28

申请号：US18201790

申请日：2023-05-25

Applicant: Raytheon Technologies Corporation

Inventor： Masoud Anahid ,  Matthew E. Lynch ,  Amit Surana ,  Malcolm P. MacDonald ,  Brian A. Fisher

IPC: B22F12/90 ,  B22F10/28 ,  B22F10/31 ,  B22F10/322 ,  B22F10/366 ,  B22F10/85 ,  B22F12/41 ,  B22F12/45 ,  B22F12/70 ,  B33Y10/00 ,  B33Y30/00 ,  B33Y50/02

Abstract: A process for a laser plume interaction for a predictive defect model for multi-laser additive manufacturing of a part including executing computational fluid dynamics modeling of a gas flow in an additive manufacturing machine manufacturing chamber; approximating a laser plume relative to a melt pool on a powder bed disposed on a build plate within the manufacturing chamber; executing a space-time analysis to identify a laser plume interaction; creating a plume interaction zone map; feeding the plume interaction zone map prediction into a multi-laser defect model; and predicting defect location and density to accumulate lack-of-fusion risk as a function of part placement, orientation, and scan strategy.