公开(公告)号：US20220266977A1

公开(公告)日：2022-08-25

申请号：US17180141

申请日：2021-02-19

Applicant: Raytheon Technologies Corporation

Inventor： Howard J. Liles

IPC: B64C3/18 ,  B64C3/26

Abstract: An airfoil comprises a wall that defines a leading edge and a trailing edge and one or more cavities located within the wall along with a rib that separates the cavities. The rib or the wall comprises a first split ply that comprises a consolidated section and two or more split sections; wherein the split sections emanate from the consolidated section; and where the split sections define the wall and the cavities of the airfoil.

公开(公告)号：US11371371B1

公开(公告)日：2022-06-28

申请号：US17213705

申请日：2021-03-26

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jon E. Sobanski ,  Howard J. Liles

IPC: F01D9/04 ,  F01D5/14 ,  F01D5/28

Abstract: A vane arc segment includes an airfoil and a spar that has a spar platform adjacent a first fairing platform of the airfoil fairing and a spar leg that extends through a hollow airfoil section of the airfoil fairing. An end portion of the spar leg has a spar clevis mount. There is a support platform adjacent the second fairing platform that has first and second through-holes. The spar clevis mount protrudes from the support platform. There is a spar pin that extends through the spar clevis mount and locks the support platform to the spar leg. A baffle extends through the spar platform, through the hollow airfoil section, and through the second through-hole of the support platform. The baffle is secured in a joint to the support platform and thereby limits rotation of the support platform about the spar pin.

公开(公告)号：US20220178260A1

公开(公告)日：2022-06-09

申请号：US17113166

申请日：2020-12-07

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： San Quach ,  Tyler G. Vincent ,  Cheng Gao ,  Howard J. Liles

IPC: F01D5/18 ,  F01D5/14 ,  F01D5/28

Abstract: A vane arc segment includes an airfoil piece that defines first and second platforms and a hollow airfoil section that has an internal cavity and extends between the first and second platforms. The first platform defines a gaspath side, a non-gaspath side, and a flange that projects from the non-gaspath side. Support hardware supports the airfoil piece via the flange. There is a conformal thermal insulation blanket disposed on the flange.

公开(公告)号：US20210156266A1

公开(公告)日：2021-05-27

申请号：US17076043

申请日：2020-10-21

Applicant: Raytheon Technologies Corporation

Inventor： Bryan H. Farrar ,  Howard J. Liles

IPC: F01D5/28 ,  B29C70/32

Abstract: A method of fabricating an airfoil includes drawing a continuous woven fabric ply over a contoured surface that has a geometry that is analogous to a geometry of an airfoil. The continuous woven fabric ply takes the geometry of the contoured surface to thereby form a contoured continuous woven fabric ply. The contoured continuous woven fabric ply is then wrapped around an airfoil tool to produce an airfoil preform. The airfoil tool has a geometry that is analogous to the airfoil. The contoured continuous woven fabric ply takes the geometry of the airfoil tool. The airfoil preform is then densified with a ceramic matrix to produce a ceramic matrix composite airfoil.