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：US20200347734A1

公开(公告)日：2020-11-05

申请号：US16859181

申请日：2020-04-27

Applicant: Raytheon Technologies Corporation

Inventor： Brandon W. Spangler ,  Dominic J. Mongillo, JR.

IPC: F01D5/18

Abstract: Airfoils for gas turbine engines are described. The airfoils include a leading edge, a trailing edge, a pressure side exterior wall, and a suction side exterior wall. A plurality of cooling passages are formed within the airfoil. A plurality of first interior ribs extend from the pressure side exterior wall to the suction side exterior wall, and a plurality of second interior ribs extend from the suction side exterior wall toward the pressure side exterior wall and intersect with a first interior rib. At least one pressure side main body cooling passage is defined between the pressure side exterior wall and two first interior ribs of the plurality of first interior ribs and at least one suction side main body cooling passage is defined between the suction side exterior wall, a first interior rib, and a second interior rib.

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：US20210301668A1

公开(公告)日：2021-09-30

申请号：US17345246

申请日：2021-06-11

Applicant: Raytheon Technologies Corporation

Inventor： Dominic J. Mongillo, JR.

IPC: F01D5/18

Abstract: Airfoils for gas turbine engines are describe. The airfoils include a leading edge having an interior surface with an inflection point line extending radially between a root and a tip of the airfoil. The inflection point line is defined at a location of minimum radii that separates a pressure side and a suction side of the airfoil body. An interlaced trip strip array is arranged along the leading edge and includes a chevron trip strip having an apex and ligaments extending from the apex to form a chevron shape and a skew trip strip arranged proximate to the chevron trip strip with a leading end proximate the inflection point line. The skew trip strip is positioned adjacent to the chevron trip strip such that a gap is formed between the skew trip strip and one of the ligaments of the chevron trip strip.

公开(公告)号：US20240410283A1

公开(公告)日：2024-12-12

申请号：US18208689

申请日：2023-06-12

Applicant: Raytheon Technologies Corporation

Inventor： Dana K. Bondarevsky ,  Dominic J. Mongillo, JR. ,  Christopher Paul Perron ,  Yuta Yoshimura ,  David D. Chapdelaine

IPC: F01D5/18

Abstract: An airfoil for a gas turbine engine includes a first wall disposed in an interior cavity, the first wall extending in the spanwise direction from a base region to a tip wall and adjoining a pressure side wall and a suction side wall to form a first cooling channel; a second wall disposed in the interior cavity and extending in a chordwise direction from the first wall toward a trailing edge, the second wall adjoining the pressure side wall and the suction side wall to form a second cooling channel; a first hole through the first wall, the first hole connecting the first cooling channel to the second cooling channel; and a second hole though the second wall connecting the second cooling channel to a third cooling channel.

公开(公告)号：US20230151737A1

公开(公告)日：2023-05-18

申请号：US17988917

申请日：2022-11-17

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Tracy A. Propheter-Hinckley ,  Dominic J. Mongillo, JR. ,  Allan Nyairo Arisi

IPC: F01D5/18

CPC classification number: F01D5/18 ,  F05D2220/32 ,  F05D2260/20 ,  F05D2230/21

Abstract: An airfoil includes a platform and an airfoil section that extends from the platform. The airfoil defines leading and trailing ends and suction and pressure sides. The airfoil section has a transition region through which the airfoil section blends into the platform. The trailing end of the airfoil section has an axial cooling slot opening through the transition region and defines a circumferentially diverging ramp in the transition region.

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：US20230037659A1

公开(公告)日：2023-02-09

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

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：US20220003121A1

公开(公告)日：2022-01-06

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：US20210054754A1

公开(公告)日：2021-02-25

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

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.