公开(公告)号：US20240384684A1

公开(公告)日：2024-11-21

申请号：US18197558

申请日：2023-05-15

Applicant: Raytheon Technologies Corporation

Inventor： Neil J. Terwilliger ,  Simon W. Evans

IPC: F02K3/06 ,  F02C7/04 ,  F02C7/141

Abstract: A propulsion system is provided for an aircraft. This propulsion system includes a turbine engine, and the turbine engine includes a propulsor rotor, an engine core and a heat exchanger. The propulsor rotor is configured to rotate about an axis and direct a first air stream along a primary flowpath that bypasses the engine core. The propulsor rotor is configured to direct a second air stream along a secondary flowpath with a geometry extending at least eighty degrees about the axis. The turbine engine is configured such that the first air stream enters the primary flowpath at a first pressure and the second air stream enters the secondary flowpath at a second pressure that is different than the first pressure. The engine core is configured to drive rotation of the propulsor rotor. The heat exchanger is disposed within the secondary flowpath.

公开(公告)号：US12098645B2

公开(公告)日：2024-09-24

申请号：US18314958

申请日：2023-05-10

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Neil J. Terwilliger ,  Joseph B. Staubach

IPC: F01D15/02 ,  F01D15/10 ,  F01K3/26 ,  F01K7/16 ,  F01K7/38

CPC classification number: F01D15/02 ,  F01D15/10 ,  F01K3/26 ,  F01K7/16 ,  F01K7/38

Abstract: A turbine engine assembly includes a core engine generating a high energy gas flow that is expanded through a turbine section, a hydrogen fuel system supplying hydrogen fuel to a combustor through a fuel flow path, a condenser extracting water from the high energy gas flow, an evaporator inputting thermal energy into the water extracted by the condenser to generate a steam flow, and at least one superheater receiving the steam flow from the evaporator and input thermal energy for heating the steam flow. The steam flow from the at least one superheater is injected into the core flow path upstream of the turbine section.

公开(公告)号：US20240254913A1

公开(公告)日：2024-08-01

申请号：US18102356

申请日：2023-01-27

Applicant: Raytheon Technologies Corporation

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

IPC: F02C3/30

CPC classification number: F02C3/30 ,  F05D2220/323 ,  F05D2240/35

Abstract: A turbine engine assembly an inter-turbine burner that is disposed between at least two of a plurality of turbine stages where an additional amount of fuel is mixed with an exhaust gas flow to generate a reheated gas flow. A condenser extracts water from the reheated gas flow and an evaporator system generates a steam flow from at least a portion of water that is extracted by the condenser for injection into the core airflow.

公开(公告)号：US12031485B1

公开(公告)日：2024-07-09

申请号：US18304524

申请日：2023-04-21

Applicant: Raytheon Technologies Corporation

Inventor： Neil J. Terwilliger ,  Andressa L. Johnson ,  Joseph E. Turney ,  Christopher J. Hanlon ,  Justin R. Urban

IPC: F02C7/18

CPC classification number: F02C7/185 ,  F05D2220/323 ,  F05D2260/2322

Abstract: An aircraft propulsion system includes a core engine for generating an exhaust gas flow that is used to generate a power output. A condenser assembly extracts water from the gas flow and stores water in a water storage tank. A cooling system maintains water stored in the storage tank at a temperature within a predefined range.

公开(公告)号：US11927132B1

公开(公告)日：2024-03-12

申请号：US18108298

申请日：2023-02-10

Applicant: Raytheon Technologies Corporation

Inventor： Neil J. Terwilliger ,  Abbas A. Alahyari

IPC: F02C6/18

CPC classification number: F02C6/18 ,  F05D2240/123

Abstract: A propulsion system for an aircraft 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 a hydrogen based fuel and ignited to generate a core gas flow that is expanded through a turbine section. The propulsion system includes a hydrogen fuel system that is configured to supply hydrogen fuel to the combustor through a fuel flow path, a condenser that is arranged along the core flow path and configured to condense water within the core gas flow, and a separator that includes an inlet, a primary water outlet and an exit that includes a plurality of exit guide vanes for straightening the core gas flow that proceeds through the exit. The exit guide vanes include a secondary water outlet for removing condensed water in the core gas flow that proceeds through the exit.

公开(公告)号：US20240052792A1

公开(公告)日：2024-02-15

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 ,  F02C7/22 ,  F02C3/06

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

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：US11873766B2

公开(公告)日：2024-01-16

申请号：US18115986

申请日：2023-03-01

Applicant: Raytheon Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Neil J. Terwilliger ,  Michael M. Romero

IPC: F02C7/32 ,  F02C7/36 ,  F16H3/72

CPC classification number: F02C7/32 ,  F02C7/36 ,  F05D2220/50 ,  F05D2260/40311 ,  F16H3/724

Abstract: A disclosed drive assembly for an auxiliary power unit includes a first drive shaft driven by an auxiliary power unit, a second drive shaft driven by a first electric motor, a differential gear system including a ring gear driven by the second drive shaft, a and planet gears supported within a carrier attached to the ring gear. The first drive shaft and an output shaft are coupled to the planet gears and a generator is driven by the output shaft. The electric motor and the auxiliary power unit combine to drive the output shaft.

公开(公告)号：US11649763B1

公开(公告)日：2023-05-16

申请号：US17847804

申请日：2022-06-23

Applicant: Raytheon Technologies Corporation

Inventor： Michael M. Romero ,  Neil J. Terwilliger ,  Daniel B. Kupratis

IPC: F02C6/20 ,  B64D27/24 ,  B64D31/00 ,  B64D27/10 ,  H02K7/18

CPC classification number: F02C6/20 ,  B64D27/10 ,  B64D27/24 ,  B64D31/00 ,  F05D2220/70 ,  H02K7/1815

Abstract: Techniques for determining a fan spool speed value associated with a hybrid electric gas engine (“engine”) are described herein. For example, a method includes generating a first fan spool speed value based on a base extraction amount. The method further includes generating a change in the first fan spool speed value based on a flight condition and a change in extraction amount. The method further includes generating a second fan spool speed value based on the extraction amount and an augmentation value for intersection of a combustion instability and burner pressure limit. The method further includes generating a second change in the second fan spool speed value based on the flight condition and the change in extraction amount. The method further includes determining a final fan spool speed value and operating the engine at the final fan spool speed value.

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：US12161963B2

公开(公告)日：2024-12-10

申请号：US17943817

申请日：2022-09-13

Applicant: Raytheon Technologies Corporation

Inventor： Andressa L. Johnson ,  Neil J. Terwilliger

IPC: B01D5/00 ,  B64D33/04

Abstract: A powerplant is provided that includes a flowpath, a combustor and a water extraction system. The combustor is configured to generate combustion products and direct the combustion products through the flowpath. The combustion products are configured from or otherwise include water vapor. The water extraction system is arranged with the flowpath downstream of the combustor. The water extraction system includes a condensation seeder and a collector. The condensation seeder is configured to direct a plurality of small water droplets into the flowpath to promote condensation of the water vapor to grow the small water droplets into a plurality of large water droplets. The collector is configured to collect the large water droplets.