公开(公告)号：US20230158758A1

公开(公告)日：2023-05-25

申请号：US17894221

申请日：2022-08-24

Applicant: Raytheon Technologies Corporation

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

IPC: B29C70/54 ,  B29C70/56 ,  B32B37/10 ,  B32B37/18 ,  B32B38/18 ,  F01D5/28 ,  F01D25/16

CPC classification number: B29C70/541 ,  B29C70/543 ,  B29C70/56 ,  B32B37/10 ,  B32B37/18 ,  B32B38/1808 ,  F01D5/282 ,  F01D5/284 ,  F01D25/162 ,  B32B2305/72 ,  B32B2309/12 ,  F05B2230/90 ,  F05C2253/04 ,  F05D2220/323 ,  F05D2230/60 ,  F05D2260/30 ,  F05D2300/6033

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：US20230151737A1

公开(公告)日：2023-05-18

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

CPC classification number: F01D5/18 ,  F05D2220/32 ,  F05D2260/20 ,  F05D2230/21

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：US20220339667A1

公开(公告)日：2022-10-27

申请号：US17238356

申请日：2021-04-23

Applicant: Raytheon Technologies Corporation

Inventor： Guolin Oo ,  Tracy A. Propheter-Hinckley

IPC: B05D1/42 ,  B05C11/04 ,  B05D3/12

Abstract: Disclosed herein is a system for slurry coating leveling. The system includes a guide frame and a scrapper apparatus coupled to the guide frame. The scrapper apparatus includes a plurality of scrapper fingers aligned substantially parallel to each other. The system also includes a contour guide coupled to the scrapper fingers. The contour guide is configured to guide movement of the scrapper fingers across a surface of a component having a slurry coating. The scrapper fingers conform to a contour profile of the surface to level the slurry coating on the surface of the component.

公开(公告)号：US11479002B2

公开(公告)日：2022-10-25

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: B29C70/54 ,  B29C70/56 ,  B32B37/10 ,  B32B37/18 ,  B32B38/18 ,  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：US20220003120A1

公开(公告)日：2022-01-06

申请号：US17482478

申请日：2021-09-23

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： San Quach ,  Tracy A. Propheter-Hinckley ,  Steven Bruce Gautschi

IPC: F01D5/18 ,  F01D5/14 ,  F01D5/20

Abstract: A component for a gas turbine engine includes, among other things, an airfoil that includes a pressure sidewall and a suction sidewall that meet together at both a leading edge and a trailing edge, the airfoil extending radially from a platform to a tip, a tip pocket formed in the tip and terminating prior to the trailing edge, and one or more heat transfer augmentation devices formed in the tip pocket.

公开(公告)号：US20210163365A1

公开(公告)日：2021-06-03

申请号：US17020455

申请日：2020-09-14

Applicant: Raytheon Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley

IPC: C04B35/622 ,  B32B18/00 ,  B28B7/34 ,  F01D5/18 ,  C04B35/64 ,  C04B35/80 ,  B28B7/28 ,  B28B7/16

Abstract: A method for forming a hole within a ceramic matrix composite component includes forming a first core portion for a ceramic matrix composite component; embedding a hollow member into the first core portion at a desired location; wrapping the first core portion with a first ceramic matrix composite material; inserting a rod through the hollow member and into the first core portion; removing the hollow member; assembling a second core portion to the first core portion such that the rod extends into the second core portion; and wrapping the first core portion and the second core portion with a second ceramic matrix composite material.