公开(公告)号：US20250012213A1

公开(公告)日：2025-01-09

申请号：US18217830

申请日：2023-07-03

Applicant: Raytheon Technologies Corporation

Inventor： Jon E. Sobanski ,  Brandon M. Evans ,  Simon W. Evans

IPC: F02C3/06 ,  F02C7/36

Abstract: A turbine engine is provided that includes a propulsor rotor and an engine core. The propulsor rotor is rotatable about a propulsor axis. The engine core is configured to power operation of the propulsor rotor. The engine core includes a core compressor section, a core combustor section, a core turbine section, a first rotating structure and a second rotating structure. The first rotating structure includes a first compressor rotor arranged within the core compressor section. The first rotating structure is rotatable about a first structure axis which is offset from the propulsor rotor axis. The second rotating structure includes a second compressor rotor arranged within the core compressor section. The second rotating structure is rotatable about a second structure axis which is offset from the propulsor rotor axis and the first structure axis.

公开(公告)号：US12163446B2

公开(公告)日：2024-12-10

申请号：US18187839

申请日：2023-03-22

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jon E. Sobanski ,  Howard J. Liles ,  Bryan P. Dube ,  Wojciech Lipka

IPC: F01D9/04 ,  F01D5/18 ,  F01D5/28

Abstract: A vane arc segment includes an airfoil fairing that has first and second fairing platforms and a hollow airfoil section that extends there between. A spar has a spar platform adjacent the first fairing platform and a spar leg that extends from the spar platform and through the hollow airfoil section. The spar leg has an end portion that is distal from the spar platform and that protrudes from the second fairing platform. The end portion has a clevis mount. There is a support platform adjacent the second fairing platform. The support platform has a through-hole through which the end portion of the spar leg extends such that the clevis mount protrudes from the support platform. A pin extends though the clevis mount and locks the support platform to the spar leg such that the airfoil fairing is trapped between the spar platform and the support platform.

公开(公告)号：US20240301808A1

公开(公告)日：2024-09-12

申请号：US18117919

申请日：2023-03-06

Applicant: Raytheon Technologies Corporation

Inventor： Jon E. Sobanski

IPC: F01K23/10

CPC classification number: F01K23/10 ,  F01D25/32 ,  F02C3/22 ,  F02C3/30 ,  F02C7/141

Abstract: A turbine engine with an axis is provided. This turbine engine includes a fan section, a turbine engine core, a bypass flowpath, an engine housing, an evaporator, a condenser 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 engine housing includes a cavity radially outboard of and axially overlapping the fan section and/or the bypass flowpath. The evaporator module is within the cavity. The condenser module is within the cavity. 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：US12037945B1

公开(公告)日：2024-07-16

申请号：US18213654

申请日：2023-06-23

Applicant: Raytheon Technologies Corporation

Inventor： Jon E. Sobanski ,  Jacob C. Snyder

IPC: F02C7/141 ,  F02C3/30 ,  F02C7/22

CPC classification number: F02C7/141 ,  F02C3/30 ,  F02C7/22 ,  F05D2220/323 ,  F05D2260/609

Abstract: A powerplant for an aircraft includes a turbine engine core, a recovery system and a flowpath. The turbine engine core includes a compressor section, a combustor section and a turbine section. The recovery system includes a condenser and a flow circuit. The flow circuit includes a separator and a treatment device. The recovery system is configured to condense water flowing within the flowpath from a gaseous phase to a liquid phase using the condenser. The recovery system is configured to direct the water in the liquid phase from the flowpath into the flow circuit using the separator. The recovery system is configured to treat a quantity of the water within the flow circuit using the treatment device to provide treated water. The recovery system is configured to provide a quantity of the treated water to the turbine engine core.

公开(公告)号：US11891953B2

公开(公告)日：2024-02-06

申请号：US17584909

申请日：2022-01-26

Applicant: Raytheon Technologies Corporation

Inventor： Jon E. Sobanski ,  Paul R. Hanrahan

IPC: F02C7/12 ,  B64D33/08 ,  F28D7/00

CPC classification number: F02C7/12 ,  B64D33/08 ,  F28D7/0041 ,  F05D2260/213

Abstract: An aircraft heat exchanger system according to an exemplary embodiment of this disclosure, among other possible things includes a first heat exchanger assembly that is disposed in an inlet duct assembly, and a skin heat exchanger assembly is in thermal communication with an outer surface of an aircraft structure. The skin heat exchanger is in fluid communication with the first heat exchanger such that a working fluid is communicated therebetween.

公开(公告)号：US20230243303A1

公开(公告)日：2023-08-03

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 ,  F05D2260/221 ,  F05D2230/60

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：US20230130242A1

公开(公告)日：2023-04-27

申请号：US18088166

申请日：2022-12-23

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jon E. Sobanski ,  Bryan P. Dube

IPC: F01D9/04 ,  F01D11/00

Abstract: A vane arc segment includes an airfoil fairing that has first and second fairing platforms and an airfoil section therebetween. The airfoil section has a pressure side, a suction side, and an internal cavity. The first fairing platform defines suction and pressure side circumferential mate faces, forward and aft faces, a gaspath side, a non-gaspath side, and a flange that projects from the non-gaspath side. The flange extends along one of the suction or pressure side circumferential mate faces. There is a rib that has a rib section in the internal cavity that spans the pressure and suction sides and a rib extension section that extends from the rib section in the internal cavity and along the non-gaspath side of the first fairing platform. The rib extension intersects the flange to form a gusset for reinforcing the flange.

公开(公告)号：US11603765B1

公开(公告)日：2023-03-14

申请号：US17377618

申请日：2021-07-16

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jon E. Sobanski

IPC: F01D5/18 ,  F01D5/14 ,  F01D5/28 ,  F01D5/08 ,  F01D9/04

Abstract: An airfoil assembly includes first and second fiber-reinforced composite airfoil rings that each have inner and outer platform sections, a suction side wall extending between the inner and outer platforms, a pressure side wall extending between the inner and outer platforms, and suction and pressure side mate faces along, respectively, edges of the suction and pressure side walls. The suction side mate face of the first fiber-reinforced composite airfoil ring and the pressure side mate face of the second fiber-reinforced composite airfoil ring mate at an interface to form an airfoil that circumscribes an internal cavity. A least one of the suction or pressure side mate faces includes protrusions along a trailing edge of the airfoil. The protrusions define a toothed exit slot for emitting cooling air from the internal cavity.

公开(公告)号：US11512601B2

公开(公告)日：2022-11-29

申请号：US16876197

申请日：2020-05-18

Applicant: Raytheon Technologies Corporation

Inventor： Lucas Dvorozniak ,  Jon E. Sobanski ,  David J. Wasserman

IPC: F01D5/28 ,  F01D5/18

Abstract: An airfoil vane includes an outer ceramic wall that defines an airfoil section and a cavity that extends through the airfoil section. A jumper tube is disposed in the cavity for transferring cooling air. The jumper tube includes a wall, a through-passage circumscribed by the wall, and a thermal barrier coating disposed on the wall.

公开(公告)号：US20220282628A1

公开(公告)日：2022-09-08

申请号：US17193369

申请日：2021-03-05

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jon E. Sobanski ,  Howard J. Liles ,  Chang Gao

IPC: F01D9/04 ,  F02C3/04

Abstract: A vane arc segment includes an airfoil fairing that has first and second platforms and an airfoil section. The platforms have first and second openings that open into the airfoil section. The platforms each define first and second circumferential mate faces, forward and aft sides, a gaspath side, a non-gaspath side. The first platform has a first flange that projects radially from the non-gaspath side aft of the first opening and a second flange that projects radially from the non-gaspath side forward of the first opening. The first and second flanges are exclusive flanges on the first platform. The second platform has a third flange that projects radially from the non-gaspath side aft of the second opening.