公开(公告)号：US20240301823A1

公开(公告)日：2024-09-12

申请号：US18119154

申请日：2023-03-08

Applicant: Raytheon Technologies Corporation

Inventor： Jon E. Sobanski ,  Jacob C. Snyder ,  Neil J. Terwilliger

IPC: F02C6/18

CPC classification number: F02C6/18 ,  F05D2240/35 ,  F05D2260/213

Abstract: A turbine engine with an axis is provided. This turbine engine includes a fan section, a turbine engine core, a bypass flowpath, a recovery system 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 recovery system includes an evaporator module and a condenser module. The condenser module is arranged radially outboard of and axially overlaps the bypass flowpath. 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：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：US12065964B1

公开(公告)日：2024-08-20

申请号：US18302081

申请日：2023-04-18

Applicant: Raytheon Technologies Corporation

Inventor： Neil J. Terwilliger

IPC: F02C3/34 ,  F02C3/30 ,  F02C6/20 ,  F02C7/141 ,  F02C7/143 ,  F02C9/18

CPC classification number: F02C3/34 ,  F02C3/30 ,  F02C6/20 ,  F02C7/141 ,  F02C7/1435 ,  F02C9/18 ,  F05D2260/212 ,  F05D2260/213

Abstract: A turbine engine assembly includes a heat exchanger that is in thermal communication with an exhaust gas flow. A bypass passage is provided that is configured to selectively route at least a portion of the exhaust gas flow around the heat exchanger in response to a predefined engine operating condition.

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：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：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：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.