公开(公告)号：US20210404659A1

公开(公告)日：2021-12-30

申请号：US17238021

申请日：2021-04-22

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jon E. Sobanski ,  Steven D. Porter

IPC: F23R3/06 ,  F02C7/18 ,  F23R3/00 ,  F23R3/50

Abstract: A heat shield panel for use in a gas turbine engine combustor is disclosed. In various embodiments, the heat shield panel includes a hot side, a cold side spaced from the hot side, a rail member disposed on the cold side proximate an outer perimeter, the rail member having an outer wall and an inner wall and an orifice extending through the rail member, from the inner wall to the outer wall, the orifice having an entrance portion having an entrance opening positioned on the inner wall and extending at least to an intermediate portion of the rail member and an exit portion having an exit opening positioned on the outer wall and extending at least to the intermediate portion of the rail member, the entrance portion of the orifice being angled relative to the exit portion of the orifice.

公开(公告)号：US12215620B2

公开(公告)日：2025-02-04

申请号：US18119154

申请日：2023-03-08

Applicant: Raytheon Technologies Corporation

Inventor： Jon E. Sobanski ,  Jacob C. Snyder ,  Neil J. Terwilliger

IPC: F02C6/18

Abstract: A turbine engine with an axis is provided. This turbine engine includes a fan section, a turbine engine core, a bypass flowpath, a recovery system and a core flowpath. The turbine engine core is configured to power the fan section. The turbine engine core includes a core compressor section, a core combustor section and a core turbine section. The bypass flowpath is fluidly coupled with and downstream of the fan section. The recovery system includes an evaporator module and a condenser module. The condenser module is arranged radially outboard of and axially overlaps the bypass flowpath. The core flowpath extends sequentially through the core compressor section, the core combustor section, the core turbine section, the evaporator module and the condenser module.

公开(公告)号：US12195191B2

公开(公告)日：2025-01-14

申请号：US17535200

申请日：2021-11-24

Applicant: Raytheon Technologies Corporation

Inventor： Jon E. Sobanski ,  Paul R. Hanrahan ,  Joseph B. Staubach ,  Jill Klinowski

IPC: B64D27/24 ,  B64C11/28 ,  B64C39/10 ,  B64D27/40 ,  B64D29/02

Abstract: A propulsor includes a propulsor body and a prop assembly in rotational communication with the propulsor body. The prop assembly includes a plurality of prop blades configured for rotation about an axial centerline of the propulsor. The plurality of prop blades are rotatable between a deployed position and a stowed position. The propulsor further includes at least one linkage having a first linkage end and a second linkage end. The first linkage end of the at least one linkage is rotatably mounted to the propulsor body and the second linkage end is configured to be rotatably mounted to an aircraft body. The propulsor further includes a first motor coupled to the at least one linkage and configured to rotate the at least one linkage relative to the propulsor body between a first rotational position and a second rotational position.

公开(公告)号：US12012892B1

公开(公告)日：2024-06-18

申请号：US18199767

申请日：2023-05-19

Applicant: Raytheon Technologies Corporation

Inventor： Abbas A. Alahyari ,  Jon E. Sobanski

IPC: F02C7/143 ,  F02C7/052

CPC classification number: F02C7/052 ,  F02C7/143 ,  F05D2260/213 ,  F05D2260/609

Abstract: A turbine engine is provided that includes a turbine engine core, a water separate and a core flowpath. The turbine engine core includes a core compressor section, a core combustor section and a core turbine section. The water separator includes a flowpath duct and a collector duct. The flowpath duct extends axially along and circumferentially about an axis. The collector duct extends axially along and circumferentially about the flowpath duct. The collector duct is fluidly coupled with the flowpath duct through a water permeable region in an outer wall of the flowpath duct. The core flowpath extends through the core compressor section, the core combustor section, the core turbine section and the flowpath duct from an inlet into the core flowpath to an exhaust from the core flowpath. The core flowpath extends axially along the water permeable region within the flowpath duct.

公开(公告)号：US12000334B1

公开(公告)日：2024-06-04

申请号：US18119169

申请日：2023-03-08

Applicant: Raytheon Technologies Corporation

Inventor： Jon E. Sobanski ,  Jesse M. Chandler

IPC: F02C3/30 ,  F02C7/12

CPC classification number: F02C3/30 ,  F02C7/12 ,  F05D2220/32 ,  F05D2260/213 ,  F05D2270/08

Abstract: A turbine engine is provided that includes a fan section, a turbine engine core and a recovery system. The turbine engine core is configured to power the fan section. The turbine engine core includes a core compressor section, a core combustor section and a core turbine section. A centerline axis of the turbine engine core is offset from a centerline axis of the turbine engine. The recovery system includes an evaporator module and a condenser module. A core flowpath extends sequentially through the core compressor section, the core combustor section, the core turbine section, the evaporator module and the condenser module from an inlet into the core flowpath to an exhaust from the core flowpath.

公开(公告)号：US11964772B2

公开(公告)日：2024-04-23

申请号：US17587638

申请日：2022-01-28

Applicant: Raytheon Technologies Corporation

Inventor： Jon E. Sobanski ,  Thomas G. Tillman ,  Stuart S. Ochs

IPC: B64D27/10 ,  B64D27/24 ,  B64D33/02 ,  B64D33/10 ,  B64D27/02

CPC classification number: B64D33/02 ,  B64D27/10 ,  B64D27/24 ,  B64D33/10 ,  B64D27/026 ,  B64D2033/024

Abstract: An aircraft propulsion system includes a propulsive fan assembly configured for assembly into an aircraft structure, the propulsive fan assembly that includes a fan rotatable about a fan axis, an inlet duct assembly disposed within the aircraft fuselage, the inlet duct assembly that includes an upper inlet duct with an upper inlet opening and a lower inlet duct with a lower inlet opening. The upper inlet duct and the lower inlet duct merge into a common inlet duct forward of the propulsive fan assembly, and an outlet duct is disposed aft of the propulsive fan assembly.

公开(公告)号：US11898463B2

公开(公告)日：2024-02-13

申请号：US17215513

申请日：2021-03-29

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jon E. Sobanski

IPC: F01D5/18 ,  F01D5/28 ,  F01D9/04 ,  F02C3/04 ,  F02C7/18

CPC classification number: F01D5/282 ,  F01D5/18 ,  F01D5/186 ,  F01D9/041 ,  F02C3/04 ,  F02C7/18 ,  F05D2220/32 ,  F05D2230/50 ,  F05D2240/24 ,  F05D2240/35 ,  F05D2260/232 ,  F05D2300/6033

Abstract: An airfoil assembly includes first and second fiber-reinforced composite airfoil rings. Each ring is comprised of inner and outer platform sections, a suction side wall that extends between the inner and outer platforms, and a pressure side wall that extends between the inner and outer platforms. the first ring mates at an interface with the second ring such that the suction side wall of the first ring and the pressure side wall of the second ring together form an airfoil that circumscribes an internal cavity. The interface along the airfoil includes a gap that is configured to emit cooling air from the internal cavity.

公开(公告)号：US11702984B1

公开(公告)日：2023-07-18

申请号：US17588541

申请日：2022-01-31

Applicant: Raytheon Technologies Corporation

Inventor： Jon E. Sobanski ,  Malcolm MacDonald

IPC: F02C7/12 ,  F02C7/04

CPC classification number: F02C7/12 ,  F02C7/04 ,  F05D2220/323 ,  F05D2230/60 ,  F05D2260/221

Abstract: A heat exchanger system for a propulsion system inlet duct includes a heat exchanger assembly that is disposed within an inlet duct assembly. The heat exchanger includes a heat exchanger with a front facing area that is greater than an area of the inlet duct that is transverse to a longitudinal length of the inlet duct.

公开(公告)号：US11591920B2

公开(公告)日：2023-02-28

申请号：US17504627

申请日：2021-10-19

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jon E. Sobanski ,  Kathryn S. Read

IPC: F01D9/04 ,  F02C3/04

Abstract: A vane arc segment includes an airfoil piece that defines first and second platforms and a airfoil section that extends between the first and second platforms. The airfoil section has a trailing edge, a leading edge, a pressure side, and a suction side. The platforms each define first and second circumferential mate faces, forward and aft sides, a gaspath side, a non-gaspath side, and a radial flange that projects from the non-gaspath side. Each radial flange extends continuously and includes a first leg portion that extends adjacent the trailing edge, a second leg portion that extends from the first leg portion and curves around the suction side, and a third leg portion that extends from the second leg portion toward the forward side.

公开(公告)号：US20230053047A1

公开(公告)日：2023-02-16

申请号：US17971999

申请日：2022-10-24

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Bryan H. Farrar ,  Jon E. Sobanski

IPC: F01D5/18 ,  B23P15/04 ,  B33Y80/00

Abstract: An airfoil vane includes an airfoil section which includes an outer wall that defines an internal cavity. A baffle is situated in the internal cavity. The baffle includes a leading edge portion and a trailing edge portion which is bonded to the leading edge portion at a joint. The leading edge portion and the trailing edge portion define an internal cavity therewithin. Both the leading edge portion and the trailing edge portion include a plurality of cooling holes which are configured to provide cooling air to the airfoil outer wall. The trailing edge portion is formed of sheet metal and the leading edge portion is formed of non-sheet-metal. A method of making a baffle for a vane arc segment and a method of assembling a ceramic matrix composite airfoil vane are also disclosed.