公开(公告)号：US20230043718A1

公开(公告)日：2023-02-09

申请号：US17882081

申请日：2022-08-05

Applicant: Raytheon Technologies Corporation

Inventor： Daniel P. Preuss ,  Dominic J. Mongillo, JR. ,  Jeremy B. Fredette ,  Robin Michael Patrick Prenter

IPC: F01D5/18

Abstract: A hollow airfoil body includes a baffle that is arranged in the airfoil body that extends in a radial direction and provides a fluid flow direction. The baffle has multiple holes that include first and second holes that are configured to conduct the cooling airflow in a chordwise direction toward the trailing edge of the airfoil body. The airfoil has a first standoff that extends from the airfoil body to support the baffle. The first axial standoff has a first length that defines an axial passage including the multiple holes. The airfoil includes a second standoff that has a second length less than the first length. The second standoff is arranged radially between the first and second holes. The first hole is smaller than the second hole. The second hole is downstream from the first hole relative to the fluid flow direction.

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：US20230045259A1

公开(公告)日：2023-02-09

申请号：US17881803

申请日：2022-08-05

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Emma J. Place ,  Dominic J. Mongillo ,  Jeremy B. Fredette

IPC: F01D5/18 ,  F01D5/14

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes a platform section and an airfoil section extending in a spanwise direction from the platform section to a tip portion establishing a tip. The airfoil section has an external wall defining pressure and suction sides extending in a chordwise direction between a leading edge and a trailing edge, and the pressure and suction sides are spaced apart in a thickness direction between the leading edge and the trailing edge. The tip portion includes a tip pocket and a tip shelf extending inwardly from the tip. The tip pocket and tip shelf are on opposite sides of a shelf wall.

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：US11913353B2

公开(公告)日：2024-02-27

申请号：US17881803

申请日：2022-08-05

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Emma J. Place ,  Dominic J. Mongillo ,  Jeremy B. Fredette

IPC: F01D5/18 ,  F01D5/14

CPC classification number: F01D5/186 ,  F01D5/141 ,  F05D2220/323 ,  F05D2240/30 ,  F05D2260/202

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes a platform section and an airfoil section extending in a spanwise direction from the platform section to a tip portion establishing a tip. The airfoil section has an external wall defining pressure and suction sides extending in a chordwise direction between a leading edge and a trailing edge, and the pressure and suction sides are spaced apart in a thickness direction between the leading edge and the trailing edge. The tip portion includes a tip pocket and a tip shelf extending inwardly from the tip. The tip pocket and tip shelf are on opposite sides of a shelf wall.

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.