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：US11852036B1

公开(公告)日：2023-12-26

申请号：US18136567

申请日：2023-04-19

Applicant: Raytheon Technologies Corporation

Inventor： Brandon W. Spangler

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F05D2240/305 ,  F05D2240/306 ,  F05D2260/202 ,  F05D2260/22141

Abstract: An airfoil element has first and second ribs each connecting the pressure side and the suction side. Each of the first and second ribs define: a tube portion circumscribing a rib passage; and first and second connector arms joining the tube portion to, respectively, the pressure side and the suction side. The first rib, the second rib, and the airfoil wall bound a continuous cooling channel having a pressure side portion to the pressure side of the mean line and a suction side portion to the suction side of the mean line. At least one of the pressure side portion and the suction side portion includes a skin passageway between at least one of the respective tube portions of the first rib and second rib and an adjacent portion of an interior surface of the airfoil wall. The skin passageway has an outer surface formed by the adjacent portion and an inner surface formed by said at least one of the respective tube portions. At least one of the outer surface and the inner surface has a plurality of protrusions into the skin passageway.

公开(公告)号：US20230160308A1

公开(公告)日：2023-05-25

申请号：US17971938

申请日：2022-10-24

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Brandon W. Spangler ,  David R. Pack

IPC: F01D5/18 ,  F01D5/14

CPC classification number: F01D5/188 ,  F01D5/141 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2240/301 ,  F05D2250/185

Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, and first and second sides that join the leading end and the trailing end. A rib connects the first and second sides of the airfoil wall. The rib defines a tube portion that circumscribes a rib passage, and first and second connector arms that solely join the tube portion to, respectively, the first and second sides of the airfoil wall.

公开(公告)号：US11624322B2

公开(公告)日：2023-04-11

申请号：US17392573

申请日：2021-08-03

Applicant: Raytheon Technologies Corporation

Inventor： Brandon W. Spangler

IPC: B22C9/10 ,  F02C7/18 ,  F01D5/18 ,  F01D25/12 ,  B22C9/00 ,  B22C9/24 ,  B22C9/22 ,  B22C13/12

Abstract: A core structure for a providing a cooling passage in a gas turbine engine includes a core body that has a first passage core. The first passage core has a first width in a chord-wise direction near a first wall. A second width in the chord-wise direction near a second wall. A third width in the chord-wise direction between the first and second walls. The third width being smaller than the first and second widths to form an hourglass shape.

公开(公告)号：US11220912B2

公开(公告)日：2022-01-11

申请号：US16850593

申请日：2020-04-16

Applicant: Raytheon Technologies Corporation

Inventor： Brandon W. Spangler

IPC: F01D5/14

Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, a first side wall, and a second side wall. A rib connects the first and second side walls of the airfoil wall. The rib includes first and second unbranched arms that initiate at the second side wall and extend there from to meet at a node. A third unbranched arm initiates at the first side wall. The third unbranched arm extends perpendicularly there from and connects at either the node, the first unbranched arm, or the unbranched second arm.

公开(公告)号：US20210325129A1

公开(公告)日：2021-10-21

申请号：US16854661

申请日：2020-04-21

Applicant: Raytheon Technologies Corporation

Inventor： Brandon W. Spangler ,  David R. Pack ,  William P. Stillman

IPC: F28F9/02 ,  F28F1/04

Abstract: A modified shaped heat exchanger hot air inlet and hot air outlet comprising a first heat exchanger manifold surrounding said hot air inlet and a second heat exchanger manifold surrounding said hot air outlet; an array of shaped inlets and shaped outlets, each of said shaped inlets and shaped outlets being configured to align vertices with thermal load directions responsive to a thermal expansion mismatch between the hot air inlet and hot air outlet and respective first heat exchanger manifold and second heat exchanger manifold.

公开(公告)号：US20210254504A1

公开(公告)日：2021-08-19

申请号：US17101712

申请日：2020-11-23

Applicant: Raytheon Technologies Corporation

Inventor： Brandon W. Spangler ,  Douglas M. Berczik

IPC: F01D25/12 ,  F23R3/00 ,  B23P15/04 ,  F01D9/04 ,  F01D5/14 ,  F01D5/18 ,  F01D9/06 ,  F01D11/10 ,  F01D25/00 ,  F01D25/28

Abstract: A method for forming a gas turbine engine component comprises the steps of forming a first portion from a high temperature alloy material, and forming a second portion from the high temperature alloy material, the first and second portions each defining an external surface and an internal surface. At least one heat transfer feature is formed directly on the internal surface of at least one of the first and second portions. The first and second portions are attached together to form a component. A component for a gas turbine engine is also disclosed.

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：US20230130326A1

公开(公告)日：2023-04-27

申请号：US17967252

申请日：2022-10-17

Applicant: Raytheon Technologies Corporation

Inventor： Brandon W. Spangler ,  David R. Pack

IPC: F01D5/18 ,  F01D5/14

Abstract: Airfoils and core assemblies for such airfoils are described. The airfoils include a leading edge cavity defined, in part, by a leading edge interior rib and a trailing edge cavity defined, in part, by a trailing edge interior rib. A plurality of pressure side cavities are defined by pressure side skin cavity walls with at least one pressure side skin cavity wall not extending to the suction side wall. A plurality of suction side cavities are defined by suction side skin cavity walls with at least one suction side skin cavity wall not extending to the pressure side wall. A main body cavity extends between the leading edge interior rib and the trailing edge interior rib and the plurality of side cavities are arranged in a staggered pattern to define the bounds of the main body cavity.