公开(公告)号：US11806953B2

公开(公告)日：2023-11-07

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：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：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：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.