公开(公告)号：US20240426242A1

公开(公告)日：2024-12-26

申请号：US18340529

申请日：2023-06-23

Applicant: Raytheon Technologies Corporation

Inventor： Neil J. Terwilliger ,  Joseph B. Staubach

IPC: F02C3/30 ,  F02C3/22 ,  F02C6/20 ,  F02C7/18

Abstract: A turbine engine assembly includes a compressor section where an inlet airflow is compressed, a cryogenic fuel system for generating flow of cryogenic fuel, an air separation system where an airflow is placed in thermal communication with a portion of the flow of cryogenic fuel for generating an enhanced oxygen flow. In a combustor section, the compressed inlet airflow and a portion of the enhanced oxygen flow is mixed with fuel and ignited to generate an exhaust gas flow that is communicated through a core flow path to a turbine section where expansion of the exhaust gas flow is utilized to generate a mechanical power output. Water is extracted from the exhaust gas flow in condenser transformed into a steam flow for injection into the core flow path in an evaporator system.

公开(公告)号：US12078104B2

公开(公告)日：2024-09-03

申请号：US18317545

申请日：2023-05-15

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Neil J. Terwilliger ,  Joseph B. Staubach ,  Charles E. Lents

IPC: F02C7/143 ,  F02C3/20 ,  F02C3/22 ,  F02C3/30 ,  F02C7/224 ,  F02C7/22 ,  F02C7/36

CPC classification number: F02C7/1435 ,  F02C3/20 ,  F02C3/22 ,  F02C3/30 ,  F02C3/305 ,  F02C7/143 ,  F02C7/224 ,  F02C7/22 ,  F02C7/36

Abstract: A propulsion system includes a core engine generating a high energy gas flow, a condenser configured to extract water from the high energy gas flow and an evaporator transforming the extracted water into a steam flow. The steam flow is injected into a core flow path of the core engine increase mass flow.

公开(公告)号：US11920526B1

公开(公告)日：2024-03-05

申请号：US17886950

申请日：2022-08-12

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Neil J. Terwilliger ,  Nathan A. Snape ,  Joseph B. Staubach

IPC: F02C9/40 ,  F02C3/06 ,  F02C7/22

CPC classification number: F02C9/40 ,  F02C3/06 ,  F02C7/22

Abstract: A propulsion system for an aircraft includes a core engine that includes a core flow path where a core flow is compressed in a compressor section, communicated to a combustor section, mixed with a hydrogen-based fuel and ignited to generate a gas flow that is expanded through a turbine section. A fuel system is configured to supply a hydrogen based fuel to the combustor through a fuel flow path. A condenser is arranged along the core flow path and configured to extract water from the gas flow. An intercooling system receives a portion of water from the condenser for cooling a portion of the core flow at a first location within the compressor section. Heated water from the intercooling system is exhausted to a second location within the core flow path downstream of the first location.

公开(公告)号：US11859910B2

公开(公告)日：2024-01-02

申请号：US17320853

申请日：2021-05-14

Applicant: Raytheon Technologies Corporation

Inventor： Joseph B. Staubach ,  Marc J. Muldoon ,  James F. Wiedenhoefer

IPC: F28F9/013 ,  F28D1/047 ,  F02C1/04 ,  F28F1/02 ,  F28F9/02 ,  F28D1/02 ,  F28D21/00

CPC classification number: F28D1/0475 ,  F02C1/04 ,  F28F1/025 ,  F28F9/013 ,  F28F9/0131 ,  F28F9/0221 ,  F05D2220/32 ,  F05D2260/20 ,  F28D2001/028 ,  F28D2001/0273 ,  F28D2021/004 ,  F28D2021/0026

Abstract: A heat exchanger for heat exchange between a first fluid and a second fluid has a plurality of tube sections, each having; an interior for passing the first fluid; an exterior for exposure to the second fluid; a first leg; a second leg; and a turn joining the first leg to the second leg. A has: fiber members passing between legs of the tube sections; and an end plate.

公开(公告)号：US11828200B2

公开(公告)日：2023-11-28

申请号：US17670043

申请日：2022-02-11

Applicant: Raytheon Technologies Corporation

Inventor： Neil J. Terwilliger ,  Walter A. Ledwith, Jr. ,  Joseph B. Staubach ,  David L. Ma

IPC: F01K25/00 ,  F01K27/02 ,  F01K15/02 ,  F01K7/16 ,  F01K7/12

CPC classification number: F01K25/005 ,  F01K7/12 ,  F01K7/16 ,  F01K15/02 ,  F01K27/02

Abstract: A powerplant is provided that includes an engine and a water recovery system. The engine includes an engine combustor, an engine turbine, a flowpath and a fluid delivery system. The flowpath extends out of the engine combustor and through the engine turbine. The fluid delivery system includes a hydrogen reservoir and an oxygen reservoir. The hydrogen reservoir is configured to store fluid hydrogen as liquid hydrogen. The oxygen reservoir is configured to store fluid oxygen as liquid oxygen. The fluid delivery system is configured to provide the fluid hydrogen and the fluid oxygen for combustion within the engine combustor to produce combustion products within the flowpath. The water recovery system is configured to extract water from the combustion products. The water recovery system is configured to provide the water to a component of the powerplant.

公开(公告)号：US20230374941A1

公开(公告)日：2023-11-23

申请号：US18317545

申请日：2023-05-15

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Neil J. Terwilliger ,  Joseph B. Staubach ,  Charles E. Lents

IPC: F02C7/143 ,  F02C3/22 ,  F02C6/20

CPC classification number: F02C7/1435 ,  F02C3/22 ,  F02C6/20 ,  F05D2260/2322

Abstract: A propulsion system includes a core engine generating a high energy gas flow, a condenser configured to extract water from the high energy gas flow and an evaporator transforming the extracted water into a steam flow. The steam flow is injected into a core flow path of the core engine increase mass flow.

公开(公告)号：US20230313735A1

公开(公告)日：2023-10-05

申请号：US17708095

申请日：2022-03-30

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Lance L. Smith ,  David Lei Ma ,  Joseph B. Staubach ,  Brian M. Holley ,  Sean C. Emerson

IPC: F02C3/24 ,  F02C7/224 ,  C01B3/04

CPC classification number: F02C3/24 ,  F02C7/224 ,  C01B3/047

Abstract: A gas turbine engine includes a core engine that includes a core flow path where air is compressed in a compressor section, communicated to a combustor section, mixed with an ammonia based fuel and ignited to generate a high energy combusted gas flow that is expanded through a turbine section. The turbine section is mechanically coupled to drive the compressor section. An ammonia flow path communicates an ammonia flow to the combustor section. A cracking device is disposed in the ammonia flow path. The cracking device is configured to decompose the ammonia flow into a fuel flow containing hydrogen (H2). At least one heat exchanger is upstream of the cracking device that provides thermal communication between the ammonia flow and a working fluid flow such that the ammonia fluid flow accepts thermal energy from the working fluid flow.

公开(公告)号：US20230258130A1

公开(公告)日：2023-08-17

申请号：US17669632

申请日：2022-02-11

Applicant: Raytheon Technologies Corporation

Inventor： Neil J. Terwilliger ,  Joseph E. Turney ,  Joseph B. Staubach

IPC: F02C7/14 ,  F02C3/22 ,  F02C3/30 ,  F02C7/18

CPC classification number: F02C7/14 ,  F02C3/22 ,  F02C3/30 ,  F02C7/18 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2260/207 ,  F05D2260/213 ,  F05D2260/232

Abstract: Aircraft engines include a turbine engine comprising a compressor section, a burner section, and a turbine section arranged along a shaft, with a core flow path through the turbine engine such that exhaust from the burner section passes through the turbine section, a condensing assembly arranged downstream of the turbine section of the turbine engine along the core flow path, and an exhaust compressor arranged downstream of the condensing assembly along the core flow path. The condensing assembly is configured to reduce a mass flow of the exhaust compressor by condensing water vapor from the core flow and removing liquid water from the core flow.

公开(公告)号：US11661889B1

公开(公告)日：2023-05-30

申请号：US17581375

申请日：2022-01-21

Applicant: Raytheon Technologies Corporation

Inventor： Marc J. Muldoon ,  Joseph B. Staubach

IPC: F02C7/18 ,  F02C3/22 ,  F02C7/141 ,  F02C5/02

CPC classification number: F02C7/18 ,  F02C3/22 ,  F02C5/02 ,  F02C7/141 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2250/312 ,  F05D2260/213 ,  F05D2260/232

Abstract: Aircraft propulsion systems include a fan shaft connected to a fan, the fan shaft defining a centerline axis of the aircraft propulsion system, one or more offset cores arranged at an angle to the centerline axis, the one or more offset cores each comprising a hydrogen burning combustor, a centerline cavity defined along the centerline axis, and a heat exchanger arranged within the centerline cavity. In operation, a portion of air is directed from the fan into the centerline cavity to provide a first working fluid to the heat exchanger within the centerline cavity.

公开(公告)号：US11635022B1

公开(公告)日：2023-04-25

申请号：US17670090

申请日：2022-02-11

Applicant: Raytheon Technologies Corporation

Inventor： Neil J. Terwilliger ,  Joseph B. Staubach ,  David L. Ma

IPC: F02C3/30 ,  F02C7/12

Abstract: A method is provided during which an aircraft powerplant is provided. The aircraft powerplant includes a combustor and a water recovery system. The water recovery system includes a condenser and a reservoir. Fuel is combusted within the combustor to provide combustion products. Water is extracted from the combustion products using the condenser. The water recovery system is operated in one of a plurality of modes based on likelihood of contrail formation. The modes include a first mode and a second mode, where the water is collected within the reservoir during the first mode, and where the water passes through the water recovery system during the second mode.