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公开(公告)号：US12077311B1
公开(公告)日：2024-09-03
申请号：US18211130
申请日：2023-06-16
发明人： Scott Smith , Russell Stratton
摘要： An aircraft propulsion system is provided that includes a turbine engine and an exhaust gas condenser. The exhaust gas condenser includes a housing, a nozzle, air scoops, a bank of exhaust gas conduits, and a center collection channel. The housing includes an interior cavity, top and bottom sides, and first and second lateral sides. The bank of exhaust gas conduits is disposed in the interior cavity of the housing and includes exhaust gas conduits and bypass air passages. The exhaust gas conduits and bypass air passages are disposed in an alternating configuration. The center collection channel is disposed radially inside of the bank of exhaust conduits. The exhaust gas conduits and bypass air passages extend spirally along the central axis between the forward and aft ends. Each bypass air passage is in fluid communication with an air scoop and the center collection channel.
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公开(公告)号：US20240052791A1
公开(公告)日：2024-02-15
申请号：US17978621
申请日：2022-11-01
发明人： Russell Stratton
CPC分类号： F02C9/28 , B64D37/005 , B64D2045/0085
摘要： A system is provided for an aircraft. This aircraft system includes an aircraft powerplant, a powerplant sensor system, an environment sensor system and a monitoring system. The aircraft powerplant includes a heat engine. The powerplant sensor system is configured to provide engine data indicative of one or more operating parameters of the heat engine. The environment sensor system is configured to provide environment data indicative of one or more environmental parameters of an environment in which the heat engine is operating. The monitoring system is configured to determine formation of a contrail and quantify an impact of the contrail when formed based on the engine data and the environment data.
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公开(公告)号：US11840937B2
公开(公告)日：2023-12-12
申请号：US17554816
申请日：2021-12-17
发明人： Russell Stratton
CPC分类号： F01D25/30 , F01N3/24 , F01N2470/02 , F01N2570/14 , F01N2590/00 , F05D2220/323 , F05D2260/609 , F05D2260/61 , F05D2270/082
摘要： A diffuser nozzle for a gas turbine engine includes a housing disposed about a nozzle axis and extending between a first nozzle end and a second nozzle end. The housing defines a nozzle duct. A plurality of walls is disposed within the nozzle duct. The plurality of walls subdivides the nozzle duct into a plurality of duct sections. The plurality of walls further defines a plurality of axially-extending duct segments of the nozzle duct such that within a first axially-extending duct segment, the duct cross-sectional area of a first duct section of the plurality of duct sections is greater than the duct cross-sectional area of each other duct section and within a second axially-extending duct segment, the duct cross-sectional area of a second duct section of the plurality of duct sections is greater than the duct cross-sectional area of each other duct section.
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公开(公告)号：US12085043B1
公开(公告)日：2024-09-10
申请号：US18211105
申请日：2023-06-16
发明人： Scott Smith , Russell Stratton
CPC分类号： F02K1/822 , B64D33/04 , F01D25/32 , F05D2220/323
摘要： An aircraft propulsion system is provided that includes a turbine engine and an exhaust gas condenser. The exhaust gas condenser includes a housing, a nozzle, a plurality of air scoops, and a plurality of exhaust gas conduit banks. The housing has an interior cavity, a bottom side, and first and second lateral sides. The exhaust gas conduit banks are disposed in the interior cavity of the housing and are configured to form an interior bypass air chamber. Each exhaust gas conduit bank includes alternating exhaust gas conduits and bypass air passages. The exhaust gas conduits extend axially between the forward and aft ends, and are configured to conduct exhaust gases to the nozzle. The bypass air passages are configured to receive bypass air from the air scoops and direct the bypass air between the exhaust gas conduits and into the interior bypass air chamber.
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公开(公告)号：US12077310B1
公开(公告)日：2024-09-03
申请号：US18211125
申请日：2023-06-16
发明人： Scott Smith , Russell Stratton
CPC分类号： B64D33/04 , F01D25/32 , F02K1/822 , F05D2220/323
摘要： An aircraft propulsion system is provided that includes a turbine engine and an exhaust gas condenser. The exhaust gas condenser includes a housing, a nozzle, inlet and outlet air scoops, and an exhaust gas conduit bank. The housing has an interior cavity, top and bottom sides, and first and second lateral sides. The exhaust gas conduit bank is disposed in the interior cavity of the housing. The exhaust gas conduit bank includes a plurality of exhaust gas conduits and bypass air passages that are disposed in an alternating configuration. The exhaust gas conduits extend axially between the forward and aft ends, are open at the forward end and at the nozzle. The bypass air passages receive bypass air from the inlet air scoop and direct the bypass air laterally across the condenser to the outlet air scoop.
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公开(公告)号：US20230194096A1
公开(公告)日：2023-06-22
申请号：US17554844
申请日：2021-12-17
发明人： Russell Stratton
CPC分类号： F23R3/40 , F02C3/30 , F05D2220/323 , F05D2240/128 , F05D2260/60
摘要： A gas turbine engine for an aircraft includes a turbine section and an exhaust section configured to receive an exhaust gas stream from the turbine section. The exhaust section includes a monolithic catalyst structure configured to remove nitrogen oxides (NOx) from the exhaust gas stream.
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公开(公告)号：US20230193787A1
公开(公告)日：2023-06-22
申请号：US17554816
申请日：2021-12-17
发明人： Russell Stratton
CPC分类号： F01D25/30 , F01N3/24 , F05D2260/61 , F05D2260/609 , F05D2270/082 , F05D2220/323 , F01N2570/14 , F01N2590/00 , F01N2470/02
摘要： A diffuser nozzle for a gas turbine engine includes a housing disposed about a nozzle axis and extending between a first nozzle end and a second nozzle end. The housing defines a nozzle duct. A plurality of walls is disposed within the nozzle duct. The plurality of walls subdivides the nozzle duct into a plurality of duct sections. The plurality of walls further defines a plurality of axially-extending duct segments of the nozzle duct such that within a first axially-extending duct segment, the duct cross-sectional area of a first duct section of the plurality of duct sections is greater than the duct cross-sectional area of each other duct section and within a second axially-extending duct segment, the duct cross-sectional area of a second duct section of the plurality of duct sections is greater than the duct cross-sectional area of each other duct section.
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