公开(公告)号：US20240133034A1

公开(公告)日：2024-04-25

申请号：US17970990

申请日：2022-10-20

Applicant: Raytheon Technologies Corporation

Inventor： Alyson T. Burdette ,  Raymond Surace ,  Jon Erik Sobanski

IPC: C23C16/458 ,  C23C16/04

CPC classification number: C23C16/458 ,  C23C16/045

Abstract: A tooling assembly suitable for use in infiltrating a fibrous preform comprises an outer tooling fixture and an inner tooling fixture. The outer tooling fixture comprises a first portion removably attached to a second portion, and a first pair of oppositely disposed windows defined by the first portion and the second portion. Each of the first portion and the second portion comprise a base with a recess. The inner tooling fixture comprises a body defined by at least one portion, the body configured to at least partially surround the fibrous preform, a plurality of holes extending through a thickness of the at least one portion, each hole of the plurality of holes having a length (L) and a diameter (D), and a first neck region engageable with a recess of the first portion or the second portion.

公开(公告)号：US20230374938A1

公开(公告)日：2023-11-23

申请号：US18314384

申请日：2023-05-09

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Joseph B. Staubach ,  Jon Erik Sobanski

IPC: F02C3/22 ,  F02C7/141 ,  F02C6/20

CPC classification number: F02C3/22 ,  F02C7/141 ,  F02C6/20 ,  B64D27/10

Abstract: A propulsion system for an aircraft includes a gas generating core engine that generates an exhaust gas flow that is expanded through a turbine section. A power turbine engine is forward of the core engine. A propulsor is coupled to the power turbine. A hydrogen fuel system supplies hydrogen fuel to the combustor through a fuel flow path. A condenser extracts water from the exhaust gas flow. An evaporator receives a portion of the water that is extracted by the condenser and generates a steam flow. The steam flow is injected into the core flow path upstream of the turbine section. An inlet duct communicates an inlet airflow to the compressor section aft at a location aft of the turbine section. An exhaust duct routes exhaust gas flow through the condenser and into thermal communication with a water flow of water extracted in the condenser in the evaporator.

公开(公告)号：US20240410314A1

公开(公告)日：2024-12-12

申请号：US18331503

申请日：2023-06-08

Applicant: Raytheon Technologies Corporation

Inventor： Jon Erik Sobanski

IPC: F02C3/30

Abstract: A turbine engine assembly includes an active clearance control system that is configured to utilize water that is extracted from the exhaust gas flow to control a clearance between a tip of a rotating blade and a case structure by controlling thermal growth of the case structure. Water extracted by the condenser is also provided to an evaporator system where thermal energy from the exhaust gas flow is utilized to transform water into a steam flow. A portion of water utilized in the active clearance control system is communicated to the evaporator system.

公开(公告)号：US20240410313A1

公开(公告)日：2024-12-12

申请号：US18331477

申请日：2023-06-08

Applicant: Raytheon Technologies Corporation

Inventor： Jon Erik Sobanski

IPC: F02C3/30

Abstract: A turbine engine assembly includes a condenser where water is extracted from the exhaust gas flow and an evaporator system where thermal energy from the exhaust gas flow is utilized to generate a steam flow from at least a portion of water that is extracted by the condenser for injection into the core flow path. A duct for the exhaust gas flow includes a cooling passage for a flow of water that accepts heat from the exhaust gas flow to cool the duct.

公开(公告)号：US20240377141A1

公开(公告)日：2024-11-14

申请号：US18314891

申请日：2023-05-10

Applicant: Raytheon Technologies Corporation

Inventor： Jon Erik Sobanski ,  Jacob C. Snyder

IPC: F28D7/16 ,  B23P15/26 ,  F28F9/02

Abstract: A heat exchanger assembly includes an inlet manifold that is configured to receive a working fluid, a plurality of microtube assemblies that define corresponding plurality passages for the working fluid and an outlet manifold that is configured to exhaust the working fluid. The plurality of microtube assemblies include a one-piece unitary structure that has a web portion that extends between at least a first microtube portion and a second microtube portion.

公开(公告)号：US12091183B1

公开(公告)日：2024-09-17

申请号：US18308766

申请日：2023-04-28

Applicant: Raytheon Technologies Corporation

Inventor： Jon Erik Sobanski

IPC: B64D35/02 ,  B64D27/10

CPC classification number: B64D35/02 ,  B64D27/10

Abstract: A propulsion system for an aircraft includes a propulsor section that includes a fan with a plurality of fan blades that are rotatable about a fan axis, a core engine that is configured to generate a gas flow, a power turbine where the gas flow from the core engine is expanded to generate shaft power, and a power turbine shaft that is coupled between the power turbine and the propulsor section. The power turbine shaft is of an axial length between a first end portion and a second end portion along the fan axis that is greater than half a distance between a leading edge of the fan blades and a mechanical coupling of the power turbine shaft to the power turbine, and includes an outer diameter that increases in a direction away from each of the first end portion and the second end portion.

公开(公告)号：US20240263578A1

公开(公告)日：2024-08-08

申请号：US18106161

申请日：2023-02-06

Applicant: Raytheon Technologies Corporation

Inventor： Jon Erik Sobanski ,  Jacob C. Snyder

IPC: F02C3/30 ,  F02C3/22

CPC classification number: F02C3/30 ,  F02C3/22 ,  F05D2260/211

Abstract: A propulsion system for an aircraft includes a core engine that generates a core gas flow, a propulsor section that is driven by the core engine and disposed aft of the core engine, a nacelle that surrounds the core engine and the propulsor section, a water recovery system that is disposed in the nacelle, an exhaust duct where the core gas flow is directed radially outward from the core engine to the nacelle, an evaporator assembly that is in thermal communication with the exhaust duct where water is recovered by the water recovery system and is heated to generate a steam flow that is subsequently communicated to the core engine.

公开(公告)号：US11655758B1

公开(公告)日：2023-05-23

申请号：US17709523

申请日：2022-03-31

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jon Erik Sobanski ,  Howard J. Liles

IPC: F02C7/28 ,  F02C3/06 ,  F01D9/04

CPC classification number: F02C3/06 ,  F01D9/041 ,  F02C7/28 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2240/55 ,  F05D2300/614

Abstract: A vane arc segment includes a platform and an airfoil section that extends in a radial direction from the platform. The airfoil section has a pressure side and a suction side. The platform defines fore and aft axial sides, a core gaspath side, a non-core gaspath side, and first and second flanges that project from the non-core gaspath side. The first and second flanges define, respectively, first and second circumferential mate faces. The first and second flanges each are formed of upturned fiber plies from the platform such that the fiber plies in the first and second flanges are radially-oriented. The first and second circumferential mate faces have, respectively, first and second seal slots that each extend in a ply through-thickness direction across two or more of the fiber plies.