公开(公告)号：US20220307374A1

公开(公告)日：2022-09-29

申请号：US17212233

申请日：2021-03-25

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jon E. Sobanski ,  Robert A. White, III

IPC: F01D5/14 ,  F02C7/00

Abstract: A vane arc segment includes an airfoil fairing that has a platform and an airfoil section that extends therefrom. The platform defines periphery edge faces, a gaspath face, and a non-gaspath face. The platform has a flange that projects radially from the non-gaspath face. The flange defines a forward flange face, an aft flange face, and a radial flange face. The flange has an end portion adjacent one of the periphery edges. The end portion includes a step that defines a radial step face that is radially intermediate the radial flange face and the non-gaspath face.

公开(公告)号：US20220228509A1

公开(公告)日：2022-07-21

申请号：US17150252

申请日：2021-01-15

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jon E. Sobanski

IPC: F01D25/28 ,  F01D9/04 ,  F02C3/04

Abstract: A support system for an airfoil piece in a gas turbine engine includes first and second support platforms for supporting the airfoil piece there between. Each of the support platforms defines a forward support platform side, an aft support platform side, a first support platform circumferential side, a second support platform circumferential side, an airfoil side, and a non-airfoil side. The airfoil side of at least one of the support platforms has a radial channel therein for receiving a complementary radial flange of the airfoil piece. Each radial channel includes a radial channel first leg portion extending adjacent the aft support platform side, a radial channel second leg portion that extends from the radial channel first leg portion and that curves toward the forward support platform side, and a radial channel third leg portion that extends from the second leg portion toward the forward support platform side.

公开(公告)号：US11371371B1

公开(公告)日：2022-06-28

申请号：US17213705

申请日：2021-03-26

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jon E. Sobanski ,  Howard J. Liles

IPC: F01D9/04 ,  F01D5/14 ,  F01D5/28

Abstract: A vane arc segment includes an airfoil and a spar that has a spar platform adjacent a first fairing platform of the airfoil fairing and a spar leg that extends through a hollow airfoil section of the airfoil fairing. An end portion of the spar leg has a spar clevis mount. There is a support platform adjacent the second fairing platform that has first and second through-holes. The spar clevis mount protrudes from the support platform. There is a spar pin that extends through the spar clevis mount and locks the support platform to the spar leg. A baffle extends through the spar platform, through the hollow airfoil section, and through the second through-hole of the support platform. The baffle is secured in a joint to the support platform and thereby limits rotation of the support platform about the spar pin.

公开(公告)号：US11299995B1

公开(公告)日：2022-04-12

申请号：US17191121

申请日：2021-03-03

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jon E. Sobanski ,  Tyler G. Vincent ,  Bryan P. Dube

IPC: F01D9/04 ,  F01D5/18 ,  F01D25/12

Abstract: A vane arc segment includes an airfoil fairing that has first and second fairing platforms and a hollow airfoil section. A spar has a spar platform adjacent the first fairing platform and a hollow spar leg that extends from the spar platform and through the hollow airfoil section. The hollow spar leg has an internal passage for receiving cool air there through, a clevis mount, and a pin fairing. The clevis mount is distal from the spar platform and protrudes from the second fairing platform. The clevis mount includes first and second prongs with aligned holes. A pin extends through the aligned holes. The pin fairing extends over the pin between the first and second prongs for guiding the cooling air around the pin. There is a support platform adjacent the second fairing platform. The pin locks the support platform to the spar leg.

公开(公告)号：US20220082256A1

公开(公告)日：2022-03-17

申请号：US17535027

申请日：2021-11-24

Applicant: Raytheon Technologies Corporation

Inventor： Steven D. Porter ,  Jon E. Sobanski

IPC: F23R3/00 ,  B21D25/00 ,  B21D31/00 ,  F01D11/00 ,  F02C3/04 ,  F23M5/04 ,  F23R3/60

Abstract: An aerodynamic component of a gas turbine engine is provided and is fittable to a shell having a shell shape. The aerodynamic component includes a body having a component shape initially deviating from the shell shape prior to an assembly operation in which the aerodynamic component is to be fit to the shell. Deviation of the component shape from the shell shape aids in an establishment of a final desired shape of the aerodynamic component following the assembly operation.

公开(公告)号：US12203392B2

公开(公告)日：2025-01-21

申请号：US18117919

申请日：2023-03-06

Applicant: Raytheon Technologies Corporation

Inventor： Jon E. Sobanski

IPC: F02C7/141 ,  F01D25/32 ,  F01K23/10 ,  F02C3/22 ,  F02C3/30

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：US12173624B2

公开(公告)日：2024-12-24

申请号：US18199742

申请日：2023-05-19

Applicant: Raytheon Technologies Corporation

Inventor： Jon E. Sobanski ,  Neil J. Terwilliger

IPC: F01D9/06 ,  F02C7/141 ,  F02K3/06

Abstract: A turbine engine is provided that includes a bypass flowpath, a plurality of upstream vanes and a plurality of downstream vanes. The bypass flowpath is fluidly coupled with and downstream of a fan section. The bypass flowpath bypasses a turbine engine core. The upstream vanes are arranged circumferentially about an axis in an upstream vane array. Each of the upstream vanes extends radially across the bypass flowpath. The downstream vanes are arranged circumferentially about the axis in a downstream vane array. The downstream vanes are circumferentially interspersed with the upstream vanes. Each of the downstream vanes extends radially across the bypass flowpath. A first of the downstream vanes is axially offset from a first of the upstream vanes along the axis.

公开(公告)号：US12163470B2

公开(公告)日：2024-12-10

申请号：US18117916

申请日：2023-03-06

Applicant: Raytheon Technologies Corporation

Inventor： Jon E. Sobanski ,  Jacob C. Snyder

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

Abstract: A turbine engine is provided that includes a fan section, a turbine engine core, an evaporator, a condenser, a core flowpath and a bypass 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 evaporator is arranged axially along an axis between the fan section and the turbine engine core. The condenser is arranged axially along the axis between the fan section and the turbine engine core. The core flowpath extends sequentially through the core compressor section, the core combustor section, the core turbine section, the evaporator and the condenser. The bypass flowpath is fluidly coupled with and downstream of the fan section. The bypass flowpath is radially outboard of and extends axially along the evaporator and the condenser.

公开(公告)号：US20240271881A1

公开(公告)日：2024-08-15

申请号：US18107843

申请日：2023-02-09

Applicant: Raytheon Technologies Corporation

Inventor： Jacob C. Snyder ,  Jon E. Sobanski ,  James F. Wiedenhoefer ,  Kathryn L. Kirsch

IPC: F28F1/00 ,  F28D7/16

CPC classification number: F28F1/006 ,  F28D7/163 ,  F28F2210/08

Abstract: A tube bundle heat exchanger includes a flow space for a first heat exchange medium; and a plurality of heat exchange tubes for a second heat exchange medium, wherein the plurality of heat exchange tubes extends at least partially across the flow space, wherein the plurality of heat exchange tubes comprises at least a first plurality of tubes having a first diameter and a second plurality of tubes having a second diameter different from the first diameter.

公开(公告)号：US20240141837A1

公开(公告)日：2024-05-02

申请号：US18311460

申请日：2023-05-03

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jesse M Chandler ,  Marc J. Muldoon ,  Jon E. Sobanski ,  Neil J. Terwilliger ,  Joseph B. Staubach

IPC: F02C7/22 ,  F02C7/18

CPC classification number: F02C7/22 ,  F02C7/18 ,  F05D2260/211

Abstract: A propulsion system for an aircraft includes a gas generating core engine generates an exhaust gas flow that is expanded through a turbine section, a power turbine driven by the exhaust gas flow, a propulsor coupled to the power turbine, a hydrogen fuel system configured to supply hydrogen fuel to the combustor through a fuel flow path, a condenser arranged along the core flow path and configured to extract water from the exhaust gas flow, and an evaporator arranged along the core flow path receiving a portion of the water extracted by the condenser to generate a steam flow that is injected into the core flow path upstream of the turbine section.