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：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：US11459898B2

公开(公告)日：2022-10-04

申请号：US17245208

申请日：2021-04-30

Applicant: Raytheon Technologies Corporation

Inventor： Dominic J. Mongillo, Jr. ,  Atul Kohli ,  Jeffrey J. DeGray

IPC: F01D5/18 ,  F01D25/12

Abstract: Component for gas turbine engines are described. The components include a component wall having an inner wall surface and an outer wall surface and a cooling hole formed within the component wall. The cooling hole has an inlet formed in the inner wall surface and an outlet formed in the outer wall surface and defines a fluid path through the component wall. The cooling hole has a metering section extending from the inlet to a transition point and a diffusing section extending from the transition point to the outlet. The metering section is defined by a uniform geometry and the diffusing section is defined by a lobed portion that extends from the transition point toward the outlet. The lobed portion has a first lobe and a second lobe divided by a ridge surface and each lobe defines continuous curved surfaces along the length of the ridge surface.

公开(公告)号：US20220018260A1

公开(公告)日：2022-01-20

申请号：US17245208

申请日：2021-04-30

Applicant: Raytheon Technologies Corporation

Inventor： Dominic J. Mongillo, Jr. ,  Atul Kohli ,  Jeffrey J. DeGray

IPC: F01D5/18 ,  F01D25/12

Abstract: Component for gas turbine engines are described. The components include a component wall having an inner wall surface and an outer wall surface and a cooling hole formed within the component wall. The cooling hole has an inlet formed in the inner wall surface and an outlet formed in the outer wall surface and defines a fluid path through the component wall. The cooling hole has a metering section extending from the inlet to a transition point and a diffusing section extending from the transition point to the outlet. The metering section is defined by a uniform geometry and the diffusing section is defined by a lobed portion that extends from the transition point toward the outlet. The lobed portion has a first lobe and a second lobe divided by a ridge surface and each lobe defines continuous curved surfaces along the length of the ridge surface.

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.