公开(公告)号：US11536148B2

公开(公告)日：2022-12-27

申请号：US17102575

申请日：2020-11-24

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Raymond Surace ,  Mark F. Zelesky

IPC: F01D9/04 ,  F01D5/08 ,  F01D5/18 ,  F01D5/28

Abstract: A vane arc segment includes an airfoil piece that defines first and second platforms and an airfoil section that extends between the first and second platforms. The first platform defines a gaspath side, a non-gaspath side, and a first platform radial flange that projects from the non-gaspath side. Support hardware supports the airfoil piece via the first platform radial flange. A thermal insulation element is situated adjacent the first platform radial flange. The support hardware supports the airfoil piece through the thermal insulation element.

公开(公告)号：US11434768B2

公开(公告)日：2022-09-06

申请号：US17322211

申请日：2021-05-17

Applicant: Raytheon Technologies Corporation

Inventor： Christopher J. Peters ,  Emma J. Place ,  Jeffrey J. DeGray ,  Dominic J. Mongillo ,  Timothy J. Jennings ,  Raymond Surace ,  Jeremy B. Fredette

IPC: B22C9/10 ,  F01D5/18 ,  B22D25/02

Abstract: An airfoil core includes a first core portion that has a hybrid skin core, a tip flag core, and a trailing edge core. A second core portion has a serpentine core and a leading edge core.

公开(公告)号：US20220228496A1

公开(公告)日：2022-07-21

申请号：US17149944

申请日：2021-01-15

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jonas S. Banhos ,  Kathryn S. Read ,  Raymond Surace ,  Olivier H. Sudre

IPC: F01D5/28 ,  F01D5/18 ,  F01D5/14

Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, and pressure and suction sides that join the leading end and the trailing end. The airfoil wall includes a wishbone-shaped fiber layer structure that has a pair of arms that merge into a single leg. The pair of arms are formed by first and second S-shaped fiber layers each of which is comprised of a network of fiber tows. The first and second S-shaped fiber layers merge to form the single leg. The single leg comprises fiber tows from each of the first and second S-shaped fiber layers that are interwoven, and the single leg forms at least a portion of the trailing end of the airfoil wall.

公开(公告)号：US11220917B1

公开(公告)日：2022-01-11

申请号：US17010904

申请日：2020-09-03

Applicant: Raytheon Technologies Corporation

Inventor： San Quach ,  Raymond Surace

IPC: F01D5/18 ,  F01D9/06 ,  F01D25/12

Abstract: A gas turbine engine component according to an example of the present disclosure includes, among other things, an external wall extending in a thickness direction between first and second wall surfaces. The first wall surface bounds an internal cavity, and establishes at least one surface depression along an external surface contour. The external wall includes at least one cooling passage having an outlet port established along the at least one surface depression. A method of fabricating a gas turbine engine component is also disclosed.

公开(公告)号：US11215059B1

公开(公告)日：2022-01-04

申请号：US17011171

申请日：2020-09-03

Applicant: Raytheon Technologies Corporation

Inventor： San Quach ,  Bryan P. Dube ,  Raymond Surace ,  Alex J. Schneider ,  Tyler G. Vincent

IPC: F01D5/18 ,  F01D25/12 ,  F02C3/04

Abstract: An airfoil includes a ceramic airfoil section that defines leading and trailing edges, pressure and suction sides, and radially inner and outer ends. The span of the airfoil section has first, second, and third radial span zones. There is a row of cooling holes in an aft 25% of the axial span. The row of cooling holes extends though the first, second, and third radial span zones. The cooling holes in the first radial span zone define a first pitch P1, the cooling holes in the second radial span zone define a second pitch P2, and the cooling holes in the third radial span zone define a third pitch P3, wherein P2

公开(公告)号：US11125087B2

公开(公告)日：2021-09-21

申请号：US15863158

申请日：2018-01-05

Applicant: Raytheon Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley ,  Raymond Surace

IPC: B28B7/18 ,  F01D5/18 ,  F01D5/14 ,  F01D5/28 ,  B28B7/34 ,  B32B18/00 ,  B28B23/00 ,  B28B23/06

Abstract: A method for forming a passage in a ceramic matrix composite component includes forming a core for a ceramic matrix composite component; embedding a hollow member into the core at a desired location for a passage in the ceramic matrix composite component; wrapping the core with a ceramic material; and inserting a rod through the hollow member and into the core.