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：US11078793B2

公开(公告)日：2021-08-03

申请号：US16574359

申请日：2019-09-18

Applicant: Raytheon Technologies Corporation

Inventor： Wolfgang Balzer ,  Thomas J. Praisner ,  Atul Kohli ,  Mark F. Zelesky ,  Dominic J. Mongillo, Jr.

IPC: F01D5/14 ,  F01D5/02 ,  F01D5/18

Abstract: An airfoil for a gas turbine engine includes an airfoil with pressure and suction sides that are joined at leading and trailing edges. The airfoil extends a span from a support to an end in a radial direction. 0% span and 100% span positions respectively correspond to the airfoil at the support and at the end. The leading and trailing edges are spaced apart from one another an axial chord in an axial direction. A cross-section of the airfoil at a span location has a diameter tangent to the pressure and suction sides. The diameter corresponds to the largest circle fitting within the cross-section. A ratio of the diameter to the axial chord is at least 0.4 between 50% and 95% span location.

公开(公告)号：US12065944B1

公开(公告)日：2024-08-20

申请号：US18118706

申请日：2023-03-07

Applicant: Raytheon Technologies Corporation

Inventor： Brandon W. Spangler ,  Dominic J. Mongillo, Jr. ,  Jaime G. Ghigliotty Rosado

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F05D2220/323 ,  F05D2230/21 ,  F05D2230/60 ,  F05D2260/202 ,  F05D2300/17

Abstract: A turbine engine airfoil element has: a plurality of spanwise main body passageways along a camber line; and a plurality of spanwise skin passageways along the pressure side. The spanwise skin passageways include: first skin passageways each having a plurality of film cooling outlets to the pressure side; and second skin passageways each lacking film cooling outlets to the pressure side. Linking passageways extend between the first skin passageways and the second skin passageways. The first skin passageways and second skin passageways are directly fed from one or more inlets of the airfoil element.

公开(公告)号：US11815022B2

公开(公告)日：2023-11-14

申请号：US17882114

申请日：2022-08-05

Applicant: Raytheon Technologies Corporation

Inventor： Daniel P. Preuss ,  Dominic J. Mongillo, Jr. ,  Timothy J. Jennings

IPC: F01D5/18 ,  F02C7/18 ,  F01D25/12 ,  F02C3/06

CPC classification number: F02C7/18 ,  F01D5/18 ,  F01D25/12 ,  F02C3/06 ,  F05D2220/323 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2260/232

Abstract: A gas turbine engine includes a compressor section that provides first and second compressor stages that are configured to respectively provide first and second cooling fluids. The first compressor stage has a higher pressure than the second compressor stage. The gas turbine engine further includes a component that has platform with an internal cooling passage fed by first and second inlets that respectively receive fluid from the first and second cooling sources. The second inlet is downstream from the first inlet.

公开(公告)号：US20230304412A1

公开(公告)日：2023-09-28

申请号：US18161484

申请日：2023-01-30

Applicant: Raytheon Technologies Corporation

Inventor： Daniel P. Preuss ,  Dominic J. Mongillo, Jr. ,  Kristopher K. Anderson ,  Nicholas J. Madonna

IPC: F01D9/04 ,  F01D5/18 ,  F01D9/06

CPC classification number: F01D9/042 ,  F01D5/18 ,  F01D9/065 ,  F05D2240/121 ,  F05D2240/126 ,  F05D2240/81

Abstract: Vane assemblies for gas turbine engines are described. The vane assemblies include a platform having an interior platform surface, a forward rail, and an aft rail, wherein the interior platform surface, the forward rail, and the aft rail define a plenum, an airfoil extending radially inward from the platform on a side opposite the forward and aft rails, the airfoil having a leading edge cavity and a baffle installed within the leading edge cavity, and platform feed structure arranged on the platform in the plenum and defining a fluid path through the forward rail and into the baffle of the leading edge cavity.

公开(公告)号：US20230243266A1

公开(公告)日：2023-08-03

申请号：US18161518

申请日：2023-01-30

Applicant: Raytheon Technologies Corporation

Inventor： Daniel P. Preuss ,  Dominic J. Mongillo, Jr.

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F05D2220/32 ,  F05D2240/30 ,  F05D2260/202

Abstract: Airfoil assemblies for gas turbine engines include an airfoil body and a leading edge baffle installed within a leading edge cavity of the airfoil body. The airfoil body includes a plurality of radially extending rails configured to engage with the baffle and define radially extending channels therebetween. First and second forward radially extending rails are segmented in the radial direction and a showerhead radial channel is defined along the leading edge. Pressure and suction side radial flow channels are defined between an interior surface of the airfoil body, an exterior surface of the baffle, and radially extending rails. An aft channel is defined between an interior surface of the airfoil body along pressure and suction side walls, an interior rib, exterior surfaces of the baffle, and the radially extending rails.

公开(公告)号：US11261749B2

公开(公告)日：2022-03-01

申请号：US16868781

申请日：2020-05-07

Applicant: Raytheon Technologies Corporation

Inventor： Adam P. Generale ,  Dominic J. Mongillo, Jr.

IPC: F01D9/06 ,  F01D5/18

Abstract: Airfoil assemblies for gas turbine engines are described. The airfoil assemblies include an airfoil body having a leading edge, a trailing edge, a pressure side, and a suction side, the airfoil body extending in a radial direction between a first end and a second end, wherein the airfoil defines an internal cavity bounded by interior surfaces of the airfoil body, the airfoil body formed from a high-temperature-material material and a metallic insert member installed within the internal cavity. One or more radially extending ribs are arranged on an exterior surface of the metallic insert member and defining one or more radially extending passages between the exterior surface of the metallic insert member and the interior surface of the airfoil body.

公开(公告)号：US11230931B1

公开(公告)日：2022-01-25

申请号：US16920496

申请日：2020-07-03

Applicant: Raytheon Technologies Corporation

Inventor： Lucas Dvorozniak ,  Dominic J. Mongillo, Jr.

IPC: F01D5/18

Abstract: Baffle inserts for airfoils of gas turbine engines are described. The baffle inserts include a baffle insert body having a first side portion and a second side portion, wherein each side portion has a respective end, a first set of vortex generation elements is arranged at the end of the first side portion, and a second set of vortex generation elements is arranged at the end of the second side portion. The first set of vortex generation elements and the second set of vortex generation elements are arranged at an aft end of the baffle insert body.

公开(公告)号：US11951532B2

公开(公告)日：2024-04-09

申请号：US16701614

申请日：2019-12-03

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Tracy A. Propheter-Hinckley ,  Dominic J. Mongillo, Jr. ,  Benjamin T. Fisk

IPC: B22C9/10 ,  B22C9/00 ,  B22C9/04 ,  B22C9/22 ,  B22C9/24 ,  B22F5/00 ,  B22F10/28 ,  B22F10/38 ,  B33Y10/00 ,  B33Y80/00 ,  C04B35/64 ,  F01D5/14 ,  F01D5/18 ,  F01D5/28 ,  F01D9/04 ,  F01D11/08 ,  F01D25/12 ,  B22F3/24

CPC classification number: B22C9/04 ,  B22C9/00 ,  B22C9/10 ,  B22C9/103 ,  B22C9/106 ,  B22C9/22 ,  B22C9/24 ,  B22F5/009 ,  B22F10/28 ,  B22F10/38 ,  F01D5/147 ,  F01D5/187 ,  F01D5/284 ,  F01D9/041 ,  F01D11/08 ,  F01D25/12 ,  B22F3/24 ,  B22F2003/244 ,  B33Y10/00 ,  B33Y80/00 ,  C04B35/64 ,  F05D2220/32 ,  F05D2230/211 ,  F05D2230/22 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2240/55 ,  F05D2260/202 ,  F05D2300/211 ,  F05D2300/2112

Abstract: A method of preparing a casting article for use in manufacturing a gas turbine engine part according to an exemplary aspect of the present disclosure includes, among other things, communicating a powdered material to an additive manufacturing system and preparing a casting article that includes at least one trunk and a skin core that extends from the at least one trunk out of the powdered material. A casting article is also disclosed.