公开(公告)号：US12158083B2

公开(公告)日：2024-12-03

申请号：US17988917

申请日：2022-11-17

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Tracy A. Propheter-Hinckley ,  Dominic J. Mongillo, Jr. ,  Allan Nyairo Arisi

IPC: F01D5/18

Abstract: An airfoil includes a platform and an airfoil section that extends from the platform. The airfoil defines leading and trailing ends and suction and pressure sides. The airfoil section has a transition region through which the airfoil section blends into the platform. The trailing end of the airfoil section has an axial cooling slot opening through the transition region and defines a circumferentially diverging ramp in the transition region.

公开(公告)号：US11959397B2

公开(公告)日：2024-04-16

申请号：US17857337

申请日：2022-07-05

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Allan N. Arisi ,  Tracy A. Propheter-Hinckley

IPC: F01D5/18

CPC classification number: F01D5/187

Abstract: An airfoil includes an airfoil section that has an airfoil wall that defines an arced leading end, a trailing end, and first and second sides that join the arced leading end and the trailing end. The first and second sides span in a longitudinal direction between first and second ends. The airfoil wall circumscribes an internal core cavity. There is an arced rib in the internal core cavity. A cooling passage network is embedded in the airfoil wall between inner and outer portions of the airfoil wall. The cooling passage network has a trailing edge and an arced leading edge.

公开(公告)号：US20220349311A1

公开(公告)日：2022-11-03

申请号：US17857337

申请日：2022-07-05

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Allan N. Arisi ,  Tracy A. Propheter-Hinckley

IPC: F01D5/18

Abstract: An airfoil includes an airfoil section that has an airfoil wall that defines an arced leading end, a trailing end, and first and second sides that join the arced leading end and the trailing end. The first and second sides span in a longitudinal direction between first and second ends. The airfoil wall circumscribes an internal core cavity. There is an arced rib in the internal core cavity. A cooling passage network is embedded in the airfoil wall between inner and outer portions of the airfoil wall. The cooling passage network has a trailing edge and an arced leading edge.

公开(公告)号：US20210332721A1

公开(公告)日：2021-10-28

申请号：US16856499

申请日：2020-04-23

Applicant: Raytheon Technologies Corporation

Inventor： Jonas S. Banhos ,  Tracy A. Propheter-Hinckley

IPC: F01D25/24

Abstract: An assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a composite gas turbine engine component including a first flange extending radially from a main body at a junction having an arcuate profile. An adapter ring includes a mate face dimensioned to follow a contour of the junction such that the junction sits on the mate face. A method of assembly for a gas turbine engine is also disclosed.

公开(公告)号：US20210332708A1

公开(公告)日：2021-10-28

申请号：US16856460

申请日：2020-04-23

Applicant: Raytheon Technologies Corporation

Inventor： Jonas S. Banhos ,  Tracy A. Propheter-Hinckley ,  Michael Parkin

IPC: F01D5/28 ,  F01D25/16

Abstract: An assembly for forming a gas turbine engine according to an example of the present disclosure includes, among other things, a layup tool including a main body extending along a longitudinal axis and a flange extending radially from the main body, the flange defining an edge face slopes towards the main body to an axial face. At least one compression tool has a tool body having a first tool section and a second tool section extending transversely from the first tool section. The first tool section is translatable along a retention member in a first direction substantially perpendicular to the edge face such that relative movement causes the second tool section to apply a first compressive force on a composite article trapped between the axial face of the flange and the second tool section. A method of forming a gas turbine engine component is also disclosed.

公开(公告)号：US11014145B2

公开(公告)日：2021-05-25

申请号：US16106294

申请日：2018-08-21

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Tracy A. Propheter-Hinckley ,  James T. Auxier ,  Eric A. Hudson

IPC: B22C9/10 ,  B22C21/14 ,  B22C7/02

Abstract: A core assembly for a casting system according to an exemplary aspect of the present disclosure includes, among other things, a core that includes a body and at least one hole formed through the body and a spacer that extends through the at least one hole. The spacer includes a stud portion and a chaplet portion configured to abut a surface of the body that circumscribes the at least one hole.

公开(公告)号：US12135209B2

公开(公告)日：2024-11-05

申请号：US17702486

申请日：2022-03-23

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Tracy A. Propheter-Hinckley ,  Derek J. Michaels ,  Garrett Kernozicky

IPC: G01B5/00 ,  F02C7/00 ,  G01B5/008 ,  G01B11/24 ,  G06T17/00

Abstract: An inspection device is disclosed herein. In various embodiments, the inspection system device comprises: 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; and a scanner moveably coupled to the support structure, the scanner configured to generate a three-dimensional model for the bladed rotor.

公开(公告)号：US11707779B2

公开(公告)日：2023-07-25

申请号：US17362092

申请日：2021-06-29

Applicant: Raytheon Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley

IPC: B22D25/02 ,  B22C9/04 ,  B22C9/10 ,  B22C9/24 ,  B22D29/00 ,  B22C1/00 ,  B22C9/18 ,  F01D5/18 ,  F01D9/04 ,  F01D25/12

CPC classification number: B22D25/02 ,  B22C1/00 ,  B22C9/04 ,  B22C9/10 ,  B22C9/103 ,  B22C9/108 ,  B22C9/18 ,  B22C9/24 ,  B22D29/001 ,  F01D5/188 ,  F01D9/041 ,  F01D25/12 ,  F05D2230/211 ,  F05D2230/232 ,  F05D2240/12 ,  F05D2240/126 ,  F05D2240/30 ,  F05D2260/201 ,  F05D2300/13

Abstract: A method and casting core for forming a landing for welding a baffle inserted into an airfoil are disclosed, wherein the baffle landing of the blade or vane is formed in investment casting by the casting core rather than by wax, reducing tolerances and variability in the location of the baffle inserted into the cooling cavity of airfoil when the baffle is welded to the baffle landing.

公开(公告)号：US11371390B2

公开(公告)日：2022-06-28

申请号：US16856499

申请日：2020-04-23

Applicant: Raytheon Technologies Corporation

Inventor： Jonas S. Banhos ,  Tracy A. Propheter-Hinckley

IPC: F01D25/24

Abstract: An assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a composite gas turbine engine component including a first flange extending radially from a main body at a junction having an arcuate profile. An adapter ring includes a mate face dimensioned to follow a contour of the junction such that the junction sits on the mate face. A method of assembly for a gas turbine engine is also disclosed.

公开(公告)号：US20220003166A1

公开(公告)日：2022-01-06

申请号：US17480325

申请日：2021-09-21

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Scott A. Kovach ,  Tracy A. Propheter-Hinckley

IPC: F02C7/18 ,  F01D5/18 ,  F01D9/04

Abstract: A gas turbine engine article includes a baffle that is configured to be mounted in a cavity of a gas turbine engine component. The baffle has a baffle wall that circumscribes an open interior region. The baffle wall includes a forward wall, side walls, and an aft wall. The side walls include impingement orifices, and the aft wall defines two datum features. At least one of the datum features is a dimple that is a portion of a sphere.