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公开(公告)号：US12065977B2
公开(公告)日：2024-08-20
申请号：US18091848
申请日：2022-12-30
Applicant: Raytheon Technologies Corporation
Inventor： Steven W. Burd
CPC classification number: F02C9/18 , F23R3/26 , F05D2220/323 , F05D2260/606
Abstract: A system is provided for an aircraft. This aircraft system includes an exhaust duct, an exhaust flow regulator, a nozzle bypass duct and a bypass flow regulator. The exhaust duct extends longitudinally to an exhaust nozzle. The exhaust flow regulator is configured to regulate fluid flow through the exhaust duct to the exhaust nozzle. The nozzle bypass duct projects out from a side of the exhaust duct. The bypass flow regulator is configured to regulate fluid flow from the exhaust duct into the nozzle bypass duct. The bypass flow regulator is disposed upstream of the exhaust flow regulator.
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公开(公告)号：US20240026818A1
公开(公告)日：2024-01-25
申请号：US18091867
申请日：2022-12-30
Applicant: Raytheon Technologies Corporation
Inventor： Steven W. Burd
CPC classification number: F02C6/12 , F02C7/36 , F05D2220/74 , F05D2220/40
Abstract: A system is provided that includes a compressor section, a turbine section, a first engine and a second engine. The compressor section includes a compressor rotor. The turbine section includes a turbine rotor configured to drive rotation of the compressor rotor. The first engine includes a first engine inlet, a first engine outlet and a first engine combustion zone fluidly coupled with and between the first engine inlet and the first engine outlet. The first engine inlet is fluidly coupled with and downstream of the compressor section. The first engine outlet is fluidly coupled with and upstream of the turbine section. The second engine includes a second engine inlet, a second engine outlet and a second engine combustion zone fluidly coupled with and between the second engine inlet and the second engine outlet. The second engine inlet is fluidly coupled with and downstream of the compressor section.
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公开(公告)号：US11927136B1
公开(公告)日：2024-03-12
申请号：US17742786
申请日：2022-05-12
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Steven W. Burd
CPC classification number: F02C7/143 , F02C3/04 , F02C7/04 , F02C7/18 , F05D2240/35 , F05D2260/20
Abstract: A gas turbine engine includes a core engine, including a compressor section, a combustor section and a turbine section positioned within a core flow path of the gas turbine engine; a bypass splitter positioned radially outward of the core engine and configured to house the compressor section, the combustor section and the turbine section; a bypass duct positioned radially outward of the bypass splitter; a fan section positioned axially upstream of the compressor section, the fan section including a fan and an inlet cone positioned upstream of the fan; an inlet duct configured to house the fan section; an inlet precooler disposed within the inlet duct; and a heat exchange system configured to provide a cooling fluid to the inlet precooler.
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公开(公告)号：US20220333533A1
公开(公告)日：2022-10-20
申请号：US17479502
申请日：2021-09-20
Applicant: Raytheon Technologies Corporation
Inventor： Steven W. Burd
IPC: F02C7/36
Abstract: Aircraft generator systems are described. The aircraft generator systems include a main engine having a fan and a compressor section, a generator assembly having at least one expansion turbine operably connected to a generator, and a working fluid flow path defined between at least one extraction point at at least one of the fan and the compressor section of the main engine and at least one outlet, wherein the working fluid is configured to flow through the at least one expansion turbine to generate power at the generator. There are no heat exchangers arranged between the at least one extraction point and the at least one outlet along the working fluid flow path.
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公开(公告)号：US12215628B2
公开(公告)日：2025-02-04
申请号：US18091860
申请日：2022-12-30
Applicant: Raytheon Technologies Corporation
Inventor： Steven W. Burd , Christopher A. Eckett
IPC: F02C7/32 , F02C3/073 , F02C3/10 , F02C3/113 , F02C3/14 , F02C6/18 , F02C6/20 , F02C7/36 , F02K3/06
Abstract: An aircraft system is provided that includes a gas turbine engine, a gearbox and at least one compressor. The gas turbine engine includes a compressor section, a turbine section, a combustor section and a rotating structure. The combustor section is fluidly coupled with and between the compressor section and the turbine section. The rotating structure includes a compressor section rotor within the compressor section and a turbine section rotor within the turbine section. The at least one compressor includes a compressor rotor rotatably driven by the rotating structure through the gearbox. The gas turbine engine may be dedicated to powering the at least one compressor.
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Patent Agency Ranking
公开(公告)号：US12071912B2
公开(公告)日：2024-08-27
申请号：US17734324
申请日：2022-05-02
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Steven W. Burd
CPC classification number: F02K3/02 , F02C3/04 , F02C7/36 , F02C9/18 , F05D2220/32 , F05D2240/35 , F05D2260/606
Abstract: A turboshaft engine includes a core engine, including a fan section, a compressor section, a primary combustor and a turbine section positioned within a core flow path of the gas turbine engine; a bypass splitter positioned radially outward of the core engine and configured to house the compressor section, the primary combustor and the turbine section; a bypass duct positioned radially outward of the bypass splitter; and a power spool operably coupled to the core engine and configured rotationally drive a fan included within the fan section.
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公开(公告)号：US20240026829A1
公开(公告)日：2024-01-25
申请号：US18091848
申请日：2022-12-30
Applicant: Raytheon Technologies Corporation
Inventor： Steven W. Burd
CPC classification number: F02C9/18 , F23R3/26 , F05D2220/323 , F05D2260/606
Abstract: A system is provided for an aircraft. This aircraft system includes an exhaust duct, an exhaust flow regulator, a nozzle bypass duct and a bypass flow regulator. The exhaust duct extends longitudinally to an exhaust nozzle. The exhaust flow regulator is configured to regulate fluid flow through the exhaust duct to the exhaust nozzle. The nozzle bypass duct projects out from a side of the exhaust duct. The bypass flow regulator is configured to regulate fluid flow from the exhaust duct into the nozzle bypass duct. The bypass flow regulator is disposed upstream of the exhaust flow regulator.
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公开(公告)号：US12158123B1
公开(公告)日：2024-12-03
申请号：US17333986
申请日：2021-05-28
Applicant: Raytheon Technologies Corporation
Inventor： Steven W. Burd
Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a supplemental thrust section and a duct. The supplemental thrust section includes a rotating detonation combustor. The duct includes a supplemental thrust section inlet fluidly coupled with and leading to the rotating detonation combustor. The supplemental thrust section inlet has a flow area that decreases as at least a first portion of the supplemental thrust section inlet extends towards the rotating detonation combustor.
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公开(公告)号：US20240151179A1
公开(公告)日：2024-05-09
申请号：US17980957
申请日：2022-11-04
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Steven W. Burd , Joseph B. Staubach , David Lei Ma
CPC classification number: F02C3/107 , F02C7/32 , F05D2220/323 , F05D2220/60 , F05D2240/35 , F05D2260/4031
Abstract: An aircraft power system includes an internal combustion core engine where an inlet airflow is mixed with a fuel and ignited to generate shaft power and a primary gas flow, a boost combustor where a portion of the primary gas flow from the core engine is combined with fuel and ignited to generate a boosted gas flow, and a drive turbine that includes a drive output shaft wherein the boosted gas flow is expanded to generate shaft power.
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公开(公告)号：US11933218B2
公开(公告)日：2024-03-19
申请号：US18091867
申请日：2022-12-30
Applicant: Raytheon Technologies Corporation
Inventor： Steven W. Burd
CPC classification number: F02C6/12 , F02B37/00 , F02C7/36 , F02K5/02 , F05D2220/40 , F05D2220/74
Abstract: A system is provided that includes a compressor section, a turbine section, a first engine and a second engine. The compressor section includes a compressor rotor. The turbine section includes a turbine rotor configured to drive rotation of the compressor rotor. The first engine includes a first engine inlet, a first engine outlet and a first engine combustion zone fluidly coupled with and between the first engine inlet and the first engine outlet. The first engine inlet is fluidly coupled with and downstream of the compressor section. The first engine outlet is fluidly coupled with and upstream of the turbine section. The second engine includes a second engine inlet, a second engine outlet and a second engine combustion zone fluidly coupled with and between the second engine inlet and the second engine outlet. The second engine inlet is fluidly coupled with and downstream of the compressor section.
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