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公开(公告)号：US20220364802A1
公开(公告)日：2022-11-17
申请号：US17320817
申请日：2021-05-14
Applicant: Raytheon Technologies Corporation
Inventor： Joseph B. Staubach , Marc J. Muldoon , James F. Wiedenhoefer
Abstract: A heat exchanger for heat exchange between a first fluid and a second fluid has a plurality of tube sections, each comprising; an interior for passing the first fluid; an exterior for exposure to the second fluid; a first leg; a second leg; a turn joining the first leg to the second leg; and a first face and a second face. A support has at least one carbon member engaging the plurality of tube sections.
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公开(公告)号：US20220364504A1
公开(公告)日：2022-11-17
申请号：US17320853
申请日：2021-05-14
Applicant: Raytheon Technologies Corporation
Inventor： Joseph B. Staubach , Marc J. Muldoon , James F. Wiedenhoefer
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.
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公开(公告)号：US20220136440A1
公开(公告)日：2022-05-05
申请号：US17085184
申请日：2020-10-30
Applicant: Raytheon Technologies Corporation
Inventor： Robert E. Malecki , Andrew Hahn , Marc J. Muldoon , Jesse M. Chandler , Joseph B. Staubach
Abstract: A gas turbine engine and engine mount structure includes a core engine including a compressor section, a combustor section and a turbine section mounted within a core engine housing. The fan, the compressor section and the turbine section rotate about an axis of rotation. An outer nacelle surrounds the fan, and is spaced from the core engine housing to define a bypass duct. The fan delivers air into the bypass duct and into the core engine housing. The nacelle is formed with camber so as to be curved in a first plane away from the axis of rotation in a first lateral direction. An engine mount structure extends from the nacelle at an angle that is non-parallel and non-perpendicular to the first plane, and has a component in a lateral direction that is opposed to the first lateral direction. An aircraft is also disclosed.
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公开(公告)号：US20220128003A1
公开(公告)日：2022-04-28
申请号：US17571720
申请日：2022-01-10
Applicant: Raytheon Technologies Corporation
Inventor： Marc J. Muldoon , Joseph B. Staubach , Jesse M. Chandler , Neil Terwilliger , Gabriel L. Suciu
Abstract: An aircraft propulsion system includes a fan section that includes a fan shaft that is rotatable about a fan axis. The fan shaft includes a fan gear. The aircraft propulsion system also includes a boost turbine engine that includes a first output shaft that includes a first gear that is coupled to the fan gear. The boost turbine engine has a first maximum power capacity. The aircraft propulsion system further includes a cruise gas turbine engine that includes a second output shaft that includes a second gear that is coupled to the fan gear. The cruise turbine engine has a second maximum power capacity that is less than the first maximum power capacity of the boost turbine engine. The fan section produces a thrust that corresponds to power input through the fan gear from the boost turbine engine and the cruise turbine engine.
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公开(公告)号：US20210047969A1
公开(公告)日：2021-02-18
申请号：US16912110
申请日：2020-06-25
Applicant: Raytheon Technologies Corporation
Inventor： Neil Terwilliger , Marc J. Muldoon
Abstract: Hybrid electric propulsion systems are described. The hybrid electric propulsion systems include a gas turbine engine including a low speed spool and a high speed spool, the low speed spool including a low pressure compressor and a low pressure turbine, and the high speed spool including a high pressure compressor and a high pressure turbine, a mechanical power transmission configured to at least one of extract power from and supply power to at least one of the low speed spool and the high speed spool, an electric motor configured to augment rotational power of at least one of the low speed spool and the high speed spool, and a controller operable to control a power augmentation of at least one of the low speed spool and the high speed spool during an operational stress state of operation of the gas turbine engine.
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Patent Agency Ranking
公开(公告)号：US12123373B2
公开(公告)日：2024-10-22
申请号：US16931685
申请日：2020-07-17
Applicant: Raytheon Technologies Corporation
Inventor： Marc J. Muldoon , Michael E. McCune , Andrew J. Murphy
CPC classification number: F02K3/06 , F02C7/36 , F05D2220/323 , F05D2220/36 , F05D2240/35 , F05D2240/60 , F05D2260/40311
Abstract: A gas turbine engine includes a fan shaft rotatable about an axis, a fan connected to the fan shaft, and an outer housing surrounding the fan to define a bypass passage. A compressor section has both a low pressure compressor that is fixed to rotate with the fan shaft and a high pressure compressor. A turbine section has a low pressure turbine driving a low speed spool and a high pressure turbine driving the high pressure compressor. The low pressure turbine includes rotating blades and a static structure aft of the rotating blades. A fan drivetrain includes a geared architecture connecting the low speed spool to the fan shaft such that the fan and low pressure compressor rotate at a lower speed than the low pressure turbine. A thrust bearing is axially aft of the geared architecture and axially forward of the high pressure compressor. A tower shaft is rotatably driven by the low speed spool.
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公开(公告)号：US20240253806A1
公开(公告)日：2024-08-01
申请号：US18102164
申请日：2023-01-27
Applicant: Raytheon Technologies Corporation
Inventor： Neil J. Terwilliger , Marc J. Muldoon
IPC: B64D37/30
CPC classification number: B64D37/30 , B64D2041/005 , B64D2221/00
Abstract: A cryogenic fueled aircraft propulsion system includes a core engine where fuel is mixed with compressed air and ignited to generate a high energy exhaust gas flow, a fuel system that is configured to supply the fuel to the core engine, a cryogenic fuel tank for storing fuel cryogenically in a liquid phase, a gas collection system where boil off gas from the fuel system is collected, a fuel cell system where a flow of collected boil off gas is utilized to generate electric power, and an electrical coupling where electric power generated by the fuel cell is communicated to location outside of the aircraft.
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公开(公告)号：US20240141837A1
公开(公告)日：2024-05-02
申请号：US18311460
申请日：2023-05-03
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Jesse M Chandler , Marc J. Muldoon , Jon E. Sobanski , Neil J. Terwilliger , Joseph B. Staubach
CPC classification number: F02C7/22 , F02C7/18 , F05D2260/211
Abstract: A propulsion system for an aircraft includes a gas generating core engine generates an exhaust gas flow that is expanded through a turbine section, a power turbine driven by the exhaust gas flow, a propulsor coupled to the power turbine, a hydrogen fuel system configured to supply hydrogen fuel to the combustor through a fuel flow path, a condenser arranged along the core flow path and configured to extract water from the exhaust gas flow, and an evaporator arranged along the core flow path receiving a portion of the water extracted by the condenser to generate a steam flow that is injected into the core flow path upstream of the turbine section.
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公开(公告)号：US11965427B1
公开(公告)日：2024-04-23
申请号：US17956881
申请日：2022-09-30
Applicant: Raytheon Technologies Corporation
Inventor： Thomas E. Clark , Marc J. Muldoon
CPC classification number: F01D25/145 , F01D11/005 , F05D2240/15 , F05D2260/231 , F05D2260/232 , F05D2260/30 , F05D2260/60 , F05D2300/175
Abstract: A gas turbine engine includes a primary flow path fluidly connecting a compressor section, a combustor section and a turbine section. A cooling air flowpath is disposed radially outward of the primary flowpath. A first seal spans from an inner diameter of the cooling air flowpath to an outer diameter of the cooling air flowpath. The first seal includes at least one axial convolution and a plurality of pass through features defining a purge airflow. A heat shield is positioned immediately downstream of the first seal and is configured in relation to the first seal such that the purge airflow enters a mixing plenum defined between the heat shield and the first seal.
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公开(公告)号：US11927140B1
公开(公告)日：2024-03-12
申请号：US18305252
申请日：2023-04-21
Applicant: Raytheon Technologies Corporation
Inventor： Murat Yazici , Marc J. Muldoon
Abstract: A gas turbine engine includes a propulsor delivering air into a core engine inward of an outer core panel. The core engine has a compressor section, a combustor and a turbine section. A compressor bleed system includes a bleed valve on a conduit communicating with compressed air from the compressor section. The bleed valve is configured to deliver air into a chamber where it can flow outwardly of the core engine at an exit location radially inward of the outer core panel.
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