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：US20210277785A1

公开(公告)日：2021-09-09

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: 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：US12006836B2

公开(公告)日：2024-06-11

申请号：US17856042

申请日：2022-07-01

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

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

IPC: F01D5/18

CPC classification number: F01D5/18 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2260/20

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes an airfoil section extending in a radial direction from a root section to a tip portion. The airfoil section has an external wall and an internal wall. The airfoil section establishes an internal cooling arrangement including a first cooling passage having a first section and a tip flag section. The tip flag section extends in the chordwise direction along the tip portion from the first section. The first section includes a plurality of branched paths established by at least one turning vane.

公开(公告)号：US20230250725A1

公开(公告)日：2023-08-10

申请号：US17856042

申请日：2022-07-01

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

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

IPC: F01D5/18

CPC classification number: F01D5/18 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2260/20

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes an airfoil section extending in a radial direction from a root section to a tip portion. The airfoil section has an external wall and an internal wall. The airfoil section establishes an internal cooling arrangement including a first cooling passage having a first section and a tip flag section. The tip flag section extends in the chordwise direction along the tip portion from the first section. The first section includes a plurality of branched paths established by at least one turning vane.

公开(公告)号：US11255207B2

公开(公告)日：2022-02-22

申请号：US16549663

申请日：2019-08-23

Applicant: Raytheon Technologies Corporation

Inventor： Christopher J. Peters

IPC: F01D11/02 ,  F04D29/16 ,  F04D29/52 ,  F01D5/02 ,  F01D9/02 ,  F16J15/44

Abstract: Aspects of the disclosure are directed to a seal comprising: a shoe, and at least two beams coupled to the shoe, where a first width associated with the beams exceeds a second width associated with the shoe in a reference direction. Aspects of the disclosure are directed to an engine comprising: a compressor section, a turbine section, and a floating, non-contact seal that includes: a shoe, and at least two beams coupled to the shoe, where the beams extend past an edge of a flowpath surface associated with the shoe in a reference direction.