公开(公告)号：US20240183276A1

公开(公告)日：2024-06-06

申请号：US18406438

申请日：2024-01-08

Applicant: RTX CORPORATION

Inventor： Jon E. Sobanski

IPC: F01D5/28 ,  F01D5/18 ,  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：US20240376834A1

公开(公告)日：2024-11-14

申请号：US18196690

申请日：2023-05-12

Applicant: RTX Corporation

Inventor： Jon E. Sobanski ,  Jacob C. Snyder

IPC: F01D25/16 ,  F01D25/12

Abstract: A turbine engine is provided that includes a first rotating assembly, a bearing, a turbine engine core and a flowpath. The first rotating assembly includes a propulsor rotor, a power turbine rotor and a power turbine shaft coupled with and axially between the propulsor rotor and the power turbine rotor. The bearing rotatably supports the first rotating assembly at an intermediate location along the power turbine shaft. The turbine engine core includes a second rotating assembly and a combustor. The second rotating assembly includes a core compressor rotor and a core turbine rotor. The power turbine rotor is arranged axially between the propulsor rotor and the second rotating assembly. The flowpath extends sequentially across the core compressor rotor, the combustor, the core turbine rotor and the power turbine rotor from an inlet into the flowpath to an exhaust from the flowpath.

公开(公告)号：US12006845B2

公开(公告)日：2024-06-11

申请号：US18088166

申请日：2022-12-23

Applicant: RTX CORPORATION

Inventor： Jon E. Sobanski ,  Bryan P. Dube

IPC: F01D9/04 ,  F01D11/00

CPC classification number: F01D9/041 ,  F01D11/005 ,  F05D2220/323 ,  F05D2240/80 ,  F05D2300/6033

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：US12163488B1

公开(公告)日：2024-12-10

申请号：US18243456

申请日：2023-09-07

Applicant: RTX Corporation

Inventor： Jon E. Sobanski ,  Neil J. Terwilliger ,  Abbas A. Alahyari

IPC: F02K1/82 ,  F02K1/32 ,  F02K1/38

Abstract: A propulsion system for an aircraft includes a propulsor rotor, an engine core, a housing, a flowpath and a heat exchange system. The engine core is configured to power rotation of the propulsor rotor. The housing includes an inner structure and an outer structure. The outer structure is radially outboard of and axially overlaps the inner structure. The flowpath is downstream of the propulsor rotor and radially between the inner structure and the outer structure. The heat exchange system includes a duct, an exterior orifice, an interior orifice, a flow regulator and a heat exchanger disposed within the duct. The exterior orifice is formed by the outer structure and disposed along an exterior of the housing. The interior orifice is formed by the outer structure and disposed along the flowpath. The flow regulator is configured to selectively fluidly couple the exterior orifice and the interior orifice to the duct.

公开(公告)号：US11927348B2

公开(公告)日：2024-03-12

申请号：US17535027

申请日：2021-11-24

Applicant: RTX Corporation

Inventor： Steven D. Porter ,  Jon E. Sobanski

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

CPC classification number: F23R3/002 ,  B21D25/00 ,  B21D31/005 ,  F01D11/005 ,  F02C3/04 ,  F23M5/04 ,  F23R3/60 ,  F23R2900/00018

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.