公开(公告)号：US11512600B2

公开(公告)日：2022-11-29

申请号：US17216952

申请日：2021-03-30

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jonas S. Banhos

IPC: F01D5/00 ,  F01D5/28 ,  F02C3/04 ,  F02C7/00

Abstract: An airfoil incudes an airfoil section that defines an internal cavity. The airfoil section is formed of a fiber-reinforced composite that is comprised of fiber plies. The fiber plies include core fiber plies and an overwrap fiber ply that wraps around the core fiber plies. The core fiber plies are arranged as first and second tubes. each of the first and second tubes defines a plurality of windows therein. The windows of the first tube align with the windows of the second tube so as to form radially-spaced ribs that extend across the internal cavity. At least one of the first or second tubes has at least one tab that is radially between the radially-spaced ribs. The at least one tab interlocks the first and second tubes.

公开(公告)号：US11506065B1

公开(公告)日：2022-11-22

申请号：US17524809

申请日：2021-11-12

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Russell Kim ,  Jonas S. Banhos

IPC: F01D5/28 ,  F02C3/04

Abstract: An airfoil includes an airfoil section that is formed of a fiber-reinforced composite that has fiber plies. The fiber plies include at least one overwrap fiber ply, first and second support fiber plies, and a serpentine fiber ply. The overwrap fiber ply circumscribes an internal cavity and defines first and second sides and leading and trailing ends of the airfoil section. The first and second support fiber plies define respective first and second radial tubes in the internal cavity. The serpentine fiber ply winds from the first side and around the first radial tube to the second side, then from the second side back to the first side, and then from the first side and around the second radial tube back to the second side.

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：US20220316347A1

公开(公告)日：2022-10-06

申请号：US17216952

申请日：2021-03-30

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jonas S. Banhos

IPC: F01D5/28 ,  F02C3/04 ,  F02C7/00

Abstract: An airfoil incudes an airfoil section that defines an internal cavity. The airfoil section is formed of a fiber-reinforced composite that is comprised of fiber plies. The fiber plies include core fiber plies and an overwrap fiber ply that wraps around the core fiber plies. The core fiber plies are arranged as first and second tubes. each of the first and second tubes defines a plurality of windows therein. The windows of the first tube align with the windows of the second tube so as to form radially-spaced ribs that extend across the internal cavity. At least one of the first or second tubes has at least one tab that is radially between the radially-spaced ribs. The at least one tab interlocks the first and second tubes.