公开(公告)号：US11512596B2

公开(公告)日：2022-11-29

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：US20220186620A1

公开(公告)日：2022-06-16

申请号：US17122017

申请日：2020-12-15

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jon E. Sobanski ,  Howard J. Liles

IPC: F01D5/18 ,  F01D25/12

Abstract: A spar for a vane arc segment of a gas turbine engine includes an elongated spar leg that has a spar wall that circumscribes a core passage. There is a plenum passage embedded in the spar wall between inner and outer portions of the spar wall. The inner portion of the spar wall is fully solid such that the plenum passage is fluidly isolated from the core passage. The outer portion of the spar wall has a plurality of cooling through-holes for emitting cooling air from the plenum passage.

公开(公告)号：US20220154587A1

公开(公告)日：2022-05-19

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：US11261736B1

公开(公告)日：2022-03-01

申请号：US17034200

申请日：2020-09-28

Applicant: Raytheon Technologies Corporation

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

IPC: F01D5/18 ,  F01D5/14

Abstract: A vane for a gas turbine engine includes an airfoil section that has an airfoil wall defining a leading edge, a trailing edge, a pressure side, and a suction side that bound an internal cavity. The airfoil section has associated characteristics including a center of pressure and an aerodynamic load vector through the center of pressure. The airfoil wall has a single rib connecting the pressure side and the suction side. The single rib is aligned with the aerodynamic load vector.

公开(公告)号：US20240384659A1

公开(公告)日：2024-11-21

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：US20240301830A1

公开(公告)日：2024-09-12

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

CPC classification number: F02C7/141 ,  F02C3/22 ,  F02C3/30 ,  F05D2260/606

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：US11668200B2

公开(公告)日：2023-06-06

申请号：US17149914

申请日：2021-01-15

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

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

IPC: F01D9/04 ,  F01D5/18 ,  F01D5/28

CPC classification number: F01D9/042 ,  F01D5/18 ,  F01D9/041 ,  F01D5/284 ,  F05D2300/6033

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 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：US20230020644A1

公开(公告)日：2023-01-19

申请号：US17377618

申请日：2021-07-16

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jon E. Sobanski

IPC: F01D5/18 ,  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：US11549378B1

公开(公告)日：2023-01-10

申请号：US17832256

申请日：2022-06-03

Applicant: Raytheon Technologies Corporation

Inventor： Jon E. Sobanski

IPC: F01D5/18 ,  F01D5/28

Abstract: An airfoil assembly includes first and second fiber-reinforced composite airfoil rings each having inner and outer platform sections. A sealing shelf extends from a suction side wall of one of the first and second fiber-reinforced composite airfoil rings, and towards the pressure side wall of the other of the rings. A first seal is captured radially inwardly of the sealing shelves on outer platforms of each of the first and second fiber-reinforced composite airfoil rings. A second seal is captured inward of the sealing shelves on the inner platforms of each of the first and second fiber-reinforced composite rings to provide a seal between the respective first and second fiber-reinforced composite airfoil rings, and a captured internal component. A gas turbine engine is also disclosed.

公开(公告)号：US20220307378A1

公开(公告)日：2022-09-29

申请号：US17215513

申请日：2021-03-29

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jon E. Sobanski

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

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.