公开(公告)号：US20210270138A1

公开(公告)日：2021-09-02

申请号：US17307997

申请日：2021-05-04

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

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

IPC: F01D5/18 ,  F01D9/02 ,  F01D9/04 ,  F01D25/12

Abstract: A gas turbine engine includes a compressor section rotatable about an axis, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. The turbine section includes a vane assembly including a radially outer platform with respect to the axis. A first airfoil extend from the radially outer platform to a radially inner platform. A rail extends radially inward from the inner platform, and a connected passage includes an airfoil passage within the first airfoil. A platform passage is located within the inner platform, and a rail passage is located within the rail. The airfoil passage, the platform passage, and the rail passage are fluidly connected.

公开(公告)号：US20240301547A1

公开(公告)日：2024-09-12

申请号：US18118450

申请日：2023-03-07

Applicant: Raytheon Technologies Corporation

Inventor： Lane M. Thornton ,  Brendan Lenz ,  Mary Colby ,  Andrew Joseph Lazur ,  Daniel P. Preuss

IPC: C23C16/04

CPC classification number: C23C16/045

Abstract: A tooling fixture suitable for use in infiltrating a fibrous preform with a reactant gas includes an outer surface and opposing inner surface defining a thickness therebetween, and a plurality of holes extending through the thickness. Each hole of the plurality of holes includes an inlet at the outer surface, the inlet configured to receive a flow of the reactant gas, an outlet at the inner surface, a transition point between the inlet and the outlet, and an angled segment extending from the transition point to the outlet. Each hole of the plurality of holes has a first diameter at the inlet and a second diameter at the outlet, and the second diameter is greater than the first diameter.

公开(公告)号：US11828193B2

公开(公告)日：2023-11-28

申请号：US17307997

申请日：2021-05-04

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

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

IPC: F01D5/18 ,  F01D9/02 ,  F01D9/04 ,  F01D25/12 ,  B22C9/10 ,  B22C9/24 ,  F01D9/06

CPC classification number: F01D5/186 ,  B22C9/10 ,  B22C9/24 ,  F01D5/18 ,  F01D9/02 ,  F01D9/041 ,  F01D9/047 ,  F01D25/12 ,  F01D5/187 ,  F01D9/06 ,  F05D2260/202

Abstract: A gas turbine engine includes a compressor section rotatable about an axis, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. The turbine section includes a vane assembly including a radially outer platform with respect to the axis. A first airfoil extend from the radially outer platform to a radially inner platform. A rail extends radially inward from the inner platform, and a connected passage includes an airfoil passage within the first airfoil. A platform passage is located within the inner platform, and a rail passage is located within the rail. The airfoil passage, the platform passage, and the rail passage are fluidly connected.

公开(公告)号：US20200332664A1

公开(公告)日：2020-10-22

申请号：US16851752

申请日：2020-04-17

Applicant: Raytheon Technologies Corporation

Inventor： Dominic J. Mongillo, JR. ,  Daniel P. Preuss ,  Brandon W. Spangler

IPC: F01D5/18 ,  F01D9/04 ,  F01D25/12 ,  F01D5/14

Abstract: Components for gas turbine engines are described. The components include an airfoil having a leading edge cavity with a baffle portion and a leading edge portion. A baffle is installed within the baffle portion and has a first metering flow aperture. At least one support element retention feature is located within the leading edge cavity and extends completely between a pressure side and a suction side of the leading edge cavity to form a full extension from the pressure side to the suction side. First and second axial extending ribs are formed on interior surfaces of the baffle portion and define axial extending flow channels between the baffle and an interior surface of the airfoil and extending from the aft end to the forward end in an axial direction. The first metering flow aperture is located proximate the aft end of the baffle to cause a forward flowing cooling flow.

公开(公告)号：US20240300863A1

公开(公告)日：2024-09-12

申请号：US18118460

申请日：2023-03-07

Applicant: Raytheon Technologies Corporation

Inventor： Daniel P. Preuss ,  Andrew Joseph Lazur ,  Brendan Lenz ,  Lane M. Thornton ,  Mary Colby

IPC: C04B41/45

CPC classification number: C04B41/4529 ,  C04B41/457 ,  C04B41/4584 ,  C04B2235/614

Abstract: A tooling fixture suitable for use in infiltrating a fibrous preform with a flow of reactant gas includes at least one wall. The at least one wall includes an outer surface and opposing inner surface defining a thickness therebetween, and a plurality of holes extending through the thickness. Each hole of the plurality of holes includes an inlet at the outer surface, an outlet at the inner surface, a transition point between the inlet and the outlet, and a first corner defined by the outer surface and the inlet. An angle of the first corner is less than 90 degrees, each hole of the plurality of holes has a first diameter at the inlet and a second diameter at the outlet, and the second diameter is less than the first diameter.

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：US20230243267A1

公开(公告)日：2023-08-03

申请号：US18161493

申请日：2023-01-30

Applicant: Raytheon Technologies Corporation

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

IPC: F01D5/18

CPC classification number: F01D5/189 ,  F05D2240/121 ,  F05D2260/201 ,  F05D2240/126 ,  F05D2240/122 ,  F05D2240/123 ,  F05D2260/22141

Abstract: Baffles for installation within airfoils include a baffle body defining a feed cavity and extending between inner and outer diameter ends. A forward standoff shelf is formed along an exterior surface of the baffle and defined by a depression, bend, or channel in a material of the baffle body extending between the inner and outer diameter ends. The forward standoff shelf is configured to engage with a forward rail of the airfoil body, and an aft standoff shelf is formed along an exterior surface of the baffle body and configured to engage with an aft rail of the airfoil body. A surface of the baffle body between the forward standoff shelf and the aft standoff shelf defines a side channel surface extending in a radial direction along the baffle body between the outer diameter end and the inner diameter end.

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：US20240300141A1

公开(公告)日：2024-09-12

申请号：US18118448

申请日：2023-03-07

Applicant: Raytheon Technologies Corporation

Inventor： Brendan Lenz ,  Mary Colby ,  Andrew Joseph Lazur ,  Lane M. Thornton ,  Daniel P. Preuss

IPC: B28B7/00

CPC classification number: B28B7/0029

Abstract: A tooling fixture suitable for use in infiltrating a fibrous preform with a flow of reactant gas includes an outer surface and an inner surface defining a thickness therebetween, and a plurality of holes extending through the thickness of the tooling fixture. The plurality of holes includes a first hole having cylindrical geometry with a first pair of dimensions comprising a first length and a first diameter, a second hole having cylindrical geometry with a second pair of dimensions comprising a second length and a second diameter, and a third hole having cylindrical geometry with a third pair of dimensions comprising a third length and a third diameter. At least one dimension of the first pair of dimensions is different from at least one dimension of the second pair of dimensions, and at least one dimension of the second pair of dimensions is different from at least one dimension of the third pair of dimensions.