公开(公告)号：US20220065129A1

公开(公告)日：2022-03-03

申请号：US17004714

申请日：2020-08-27

Applicant: Raytheon Technologies Corporation

Inventor： Scott D. Lewis

IPC: F01D25/12 ,  F01D11/00

Abstract: A gas turbine engine component according to an example of the present disclosure includes, among other things, an external wall including adjacent bounding pedestals that extend from an external wall surface to establish a cooling passage, and including a common pedestal situated between the adjacent bounding pedestals to establish a first branched section and a second branched section of the cooling passage that join together at a merged section of the cooling passage. A method of fabricating a gas turbine engine component is also disclosed.

公开(公告)号：US11352902B2

公开(公告)日：2022-06-07

申请号：US17004714

申请日：2020-08-27

Applicant: Raytheon Technologies Corporation

Inventor： Scott D. Lewis

IPC: F01D25/12 ,  F01D11/00

Abstract: A gas turbine engine component according to an example of the present disclosure includes, among other things, an external wall including adjacent bounding pedestals that extend from an external wall surface to establish a cooling passage, and including a common pedestal situated between the adjacent bounding pedestals to establish a first branched section and a second branched section of the cooling passage that join together at a merged section of the cooling passage. A method of fabricating a gas turbine engine component is also disclosed.

公开(公告)号：US20200368851A1

公开(公告)日：2020-11-26

申请号：US16993060

申请日：2020-08-13

Applicant: Raytheon Technologies Corporation

Inventor： Scott D. Lewis ,  Stephen Lynch ,  Shane Haydt

IPC: B23K26/384 ,  F01D5/18 ,  B23H9/14 ,  B23H1/04 ,  F23R3/00 ,  F01D9/06 ,  B23H9/10 ,  F23R3/06 ,  B23H7/24 ,  F01D9/02 ,  F01D25/12

Abstract: A gas path component for a gas turbine engine includes a film cooling hole disposed in the gas path component. The film cooling hole includes a metering section, a diffuser, and a tapered surface extending between the metering section and the diffuser. The tapered surface is oriented between twenty degrees and seventy degrees with respect to a centerline axis of the metering section. The tapered surface is oriented at an obtuse angle with respect to an immediately adjacent surface of the diffuser, the obtuse angle is open towards the centerline axis. The tapered surface is configured to mitigate flow separation in the diffuser.

公开(公告)号：US11143039B2

公开(公告)日：2021-10-12

申请号：US16669698

申请日：2019-10-31

Applicant: Raytheon Technologies Corporation

Inventor： Scott D. Lewis

IPC: F01D5/00 ,  F01D5/18 ,  F01D5/14 ,  F01D9/04 ,  F01D11/08 ,  F01D25/12 ,  F02C3/04 ,  F02C7/18 ,  F23R3/00

Abstract: A component for a turbine engine includes a fore edge connected to an aft edge via a first surface and a second surface. Multiple cooling passages are defined within the turbine engine component. A skin core passage is defined immediately adjacent the first surface, and at least one pedestal interrupts a flow path through the skin core passage.

公开(公告)号：US11407065B2

公开(公告)日：2022-08-09

申请号：US16993060

申请日：2020-08-13

Applicant: Raytheon Technologies Corporation

Inventor： Scott D. Lewis ,  Stephen Lynch ,  Shane Haydt

IPC: B23K26/00 ,  B23K26/384 ,  F01D5/18 ,  B23H9/14 ,  B23H1/04 ,  F23R3/00 ,  F01D9/06 ,  B23H9/10 ,  F23R3/06 ,  B23H7/24 ,  F01D9/02 ,  F01D25/12 ,  F02K1/82

Abstract: A gas path component for a gas turbine engine includes a film cooling hole disposed in the gas path component. The film cooling hole includes a metering section, a diffuser, and a tapered surface extending between the metering section and the diffuser. The tapered surface is oriented between twenty degrees and seventy degrees with respect to a centerline axis of the metering section. The tapered surface is oriented at an obtuse angle with respect to an immediately adjacent surface of the diffuser, the obtuse angle is open towards the centerline axis. The tapered surface is configured to mitigate flow separation in the diffuser.

公开(公告)号：US11168570B1

公开(公告)日：2021-11-09

申请号：US17004662

申请日：2020-08-27

Applicant: Raytheon Technologies Corporation

Inventor： Scott D. Lewis

IPC: F01D5/18 ,  F01D25/12 ,  F01D5/20

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, at least one of an airfoil section and a platform section including a wall. The wall includes a plurality of pedestals having adjacent pedestals extending from an external wall surface to establish a respective cooling passage, and the cooling passage includes an inlet and an outlet. The adjacent pedestals are dimensioned such that the adjacent pedestals taper inwardly from the inlet in a first direction towards the outlet to establish a throat in the respective cooling passage. A method of fabricating a gas turbine engine component is also disclosed.