公开(公告)号：US20230012375A1

公开(公告)日：2023-01-12

申请号：US17371543

申请日：2021-07-09

Applicant: Raytheon Technologies Corporation

Inventor： Daniel Belotto ,  Robert B. Fowler ,  Brandon W. Spangler ,  Jose R. Paulino

IPC: F01D5/04 ,  B22D25/02

Abstract: A manufacturing method is provided that includes forming a radial flow turbine blade of a radial flow turbine rotor for a gas turbine engine. The radial flow turbine blade includes an internal cooling passage. At least a portion of the internal cooling passage has a passage thickness of less than 20 mils.

公开(公告)号：US20220403746A1

公开(公告)日：2022-12-22

申请号：US17841839

申请日：2022-06-16

Applicant: Raytheon Technologies Corporation

Inventor： Brandon W. Spangler ,  David R. Pack

IPC: F01D5/18

Abstract: Airfoil for gas turbine engines are described. The airfoils have internal walls and internal cavities. A leading edge cavity is defined within the airfoil body along a leading edge and a leading edge feed cavity is arranged aft of the leading edge cavity. A bent leading edge rib is arranged between the leading edge cavity and the leading edge feed cavity. A main body cavity is arranged aft of the leading edge feed cavity and defined at least in part by two interior ribs that define a part of the leading edge feed cavity. The main body cavity is fluidly connected to the leading edge feed cavity by an interior fluid connection through the intersection of the two interior ribs. A shield cavity is arranged to thermally shield the leading edge feed cavity from heat pickup along the suction side of the airfoil body.

公开(公告)号：US11459897B2

公开(公告)日：2022-10-04

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：US10975705B2

公开(公告)日：2021-04-13

申请号：US16660093

申请日：2019-10-22

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Brandon W. Spangler ,  Edwin Otero

IPC: F01D5/18 ,  B22C9/10 ,  B22C9/04 ,  B28B1/30 ,  B28B7/34 ,  F01D9/04 ,  F01D25/12

Abstract: A gas turbine engine component includes a structure including spaced apart first and second exterior walls that extend in a first direction to an endwall. The first and second exterior walls are joined at the endwall to provide a cooling cavity. A wishbone baffle is arranged in the cooling cavity and includes first and second interior walls respectively adjacent to the first and second exterior walls. The first and second interior walls extend in the first direction to and are joined by an apex to provide a first cavity. The wishbone baffle separates the first cavity from a second cavity provided between the apex and the endwall.

公开(公告)号：US20240301796A1

公开(公告)日：2024-09-12

申请号：US18118471

申请日：2023-03-07

Applicant: Raytheon Technologies Corporation

Inventor： Jaime G. Ghigliotty Rosado ,  Brandon W. Spangler

IPC: F01D5/18

CPC classification number: F01D5/18 ,  F05D2230/21 ,  F05D2260/201

Abstract: A turbine engine airfoil element has an airfoil having: a pressure side and a suction side; and a plurality of spanwise passageway legs. The passageway legs include: a leading edge impingement cavity; and a plurality of main body feed passageway legs along a camber line. A wall separates the leading edge impingement cavity from a leading one of the main body feed passageway legs, the wall having a suction side section and a pressure side section joining at a junction, the junction forming a vertex of an angle of transverse cross-section of the wall; and a plurality of impingement feed holes through the wall. The plurality of impingement feed holes are larger thickness-wise than span-wise.

公开(公告)号：US11982231B2

公开(公告)日：2024-05-14

申请号：US18179479

申请日：2023-03-07

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Brandon W. Spangler

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

CPC classification number: F02C7/18 ,  B22C9/00 ,  B22C9/10 ,  B22C9/103 ,  B22C9/106 ,  B22C9/22 ,  B22C9/24 ,  B22C13/12 ,  F01D5/187 ,  F01D25/12 ,  F05D2220/32 ,  F05D2260/204

Abstract: A core structure for a providing a cooling passage in a gas turbine engine includes a core body that has a first cooling passage core. The first cooling 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：US20230203991A1

公开(公告)日：2023-06-29

申请号：US18179479

申请日：2023-03-07

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Brandon W. Spangler

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

CPC classification number: F02C7/18 ,  F01D5/187 ,  F01D25/12 ,  B22C9/106 ,  B22C9/00 ,  B22C9/24 ,  B22C9/22 ,  B22C13/12 ,  B22C9/10 ,  B22C9/103 ,  F05D2220/32 ,  F05D2260/204

Abstract: A core structure for a providing a cooling passage in a gas turbine engine includes a core body that has a first cooling passage core. The first cooling 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：US11629602B2

公开(公告)日：2023-04-18

申请号：US17841839

申请日：2022-06-16

Applicant: Raytheon Technologies Corporation

Inventor： Brandon W. Spangler ,  David R. Pack

IPC: F01D5/18

Abstract: Airfoil for gas turbine engines are described. The airfoils have internal walls and internal cavities. A leading edge cavity is defined within the airfoil body along a leading edge and a leading edge feed cavity is arranged aft of the leading edge cavity. A bent leading edge rib is arranged between the leading edge cavity and the leading edge feed cavity. A main body cavity is arranged aft of the leading edge feed cavity and defined at least in part by two interior ribs that define a part of the leading edge feed cavity. The main body cavity is fluidly connected to the leading edge feed cavity by an interior fluid connection through the intersection of the two interior ribs. A shield cavity is arranged to thermally shield the leading edge feed cavity from heat pickup along the suction side of the airfoil body.

公开(公告)号：US11209221B2

公开(公告)日：2021-12-28

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：US20210363924A1

公开(公告)日：2021-11-25

申请号：US17392573

申请日：2021-08-03

Applicant: Raytheon Technologies Corporation

Inventor： Brandon W. Spangler

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

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.