-
公开(公告)号：US20180140996A1
公开(公告)日：2018-05-24
申请号：US15866184
申请日：2018-01-09
发明人： Jonathan Rheaume
CPC分类号： B01D53/326 , A62C2/04 , A62C3/002 , A62C3/065 , A62C3/08 , A62C99/0018 , B01D53/30 , B64D37/32 , B64D45/00 , B64D2045/009
摘要： An air inert gas generating system consists of heat exchangers, a heating element, and a plurality of solid oxide electrochemical gas separator (SOEGS) cells. The SOEGS cells are interconnected in series to create a stack. A voltage is applied to the stack causing oxygen ions to be transported from the air flowing through the cathode through the electrolyte to the anode side of the SOEGS, resulting in oxygen-depleted gas. The oxygen-depleted gas can be used to inert the ullage of aircraft fuel tank or support the fire suppression system in the cargo hold. The oxygen-enriched gas can be used for other purposes.
-
公开(公告)号：US11428170B2
公开(公告)日：2022-08-30
申请号：US15200149
申请日：2016-07-01
摘要： A gas turbine engine includes a core having a compressor section with a first compressor and a second compressor, a turbine section with a first turbine and a second turbine, and a primary flowpath fluidly connecting the compressor section and the turbine section. The first compressor is connected to the first turbine via a first shaft, the second compressor is connected to the second turbine via a second shaft, and a motor is connected to the first shaft such that rotational energy generated by the motor is translated to the first shaft. The gas turbine engine includes a takeoff mode of operation, a top of climb mode of operation, and at least one additional mode of operation. The gas turbine engine is undersized relative to a thrust requirement in at least one of the takeoff mode of operation and the top of climb mode of operation, and a controller is configured to control the mode of operation of the gas turbine engine.
-
公开(公告)号：US20190003747A1
公开(公告)日：2019-01-03
申请号：US16064822
申请日：2015-12-21
发明人： Craig R. Walker , Jonathan Rheaume , Michael L. Perry , Scott Alan Eastman , Subramanyaravi Annapragada , Parmesh Verma , Joseph V. Mantese
IPC分类号： F25B21/00
摘要： A heat transfer system is disclosed including a plurality of modules arranged in a stack. The stack modules include electrocaloric element and electrodes on each side of the film. A fluid flow path is disposed between two or more electrocaloric elements. A first electrical bus element (18) in electrical contact with the first electrode (14), and a second electrical bus element (20) in electrical contact with second electrode (16). The first electrical bus element is electrically connected to at least one other electrical bus of another electrocaloric element in the stack at the same polarity as said first electrical bus, or the second electrical bus element is electrically connected to at least one other electrical bus of another electrocaloric element in the stack at the same polarity as said second electrical bus.
-
公开(公告)号：US20180003071A1
公开(公告)日：2018-01-04
申请号：US15200128
申请日：2016-07-01
CPC分类号： F01D15/10 , B64D27/10 , B64D27/24 , B64D41/00 , F02C6/14 , F02C7/36 , F05D2220/76 , F05D2240/60
摘要： A gas turbine engine includes a compressor section having a first compressor and a second compressor, the second compressor having a higher pressure than the first compressor, and a turbine section having a first turbine and a second turbine, the second turbine having a higher pressure than the first turbine. The first compressor is connected to the first turbine via a first shaft. The second compressor is connected to the second turbine via a second shaft. An electric motor is connected to the first shaft such that rotational energy generated by the electric motor is translated to the first shaft. A fan is connected to the first shaft via a gear system. The gas turbine engine includes at least a takeoff mode of operations, a top of climb mode of operations and a maximum cruise mode of operations. The gas turbine engine is sized to operate at peak efficiency in the maximum cruise mode of operations.
-
公开(公告)号：US20180003109A1
公开(公告)日：2018-01-04
申请号：US15200240
申请日：2016-07-01
发明人： Charles E. Lents , Jonathan Rheaume
CPC分类号： F02C6/14 , B64D27/10 , B64D27/24 , B64D41/00 , B64D2221/00 , F01D15/10 , F02C3/22 , F02C3/24 , F02C7/32 , F05D2220/76 , F05D2260/42 , F05D2260/85
摘要： A gas turbine engine includes a compressor section having a first compressor and a second compressor and a turbine section having a first turbine and a second turbine. The first compressor is connected to the first turbine via a first shaft and the second compressor is connected to the second turbine via a second shaft. A motor connected to the first shaft such that rotational energy generated by the motor is translated to the first shaft. A power distribution system connects the motor to a stored power system including at least one of an energy storage unit and a supplementary power unit. The power distribution system is configured to provide power from the stored power system to the motor.
-
6.发明申请公开(公告)号：US20180003072A1
公开(公告)日：2018-01-04
申请号：US15200149
申请日：2016-07-01
IPC分类号： F01D15/10 , B64D27/16 , B64D27/24 , F02C6/14 , F02C7/36 , F02C9/50 , F02C3/04 , B64D31/06 , B64D27/02
CPC分类号： F01D15/10 , B64D27/10 , B64D27/24 , B64D31/06 , B64D2027/026 , F02C6/14 , F02C7/36 , F02C9/50 , F05D2220/76 , Y10S903/905 , Y10S903/906
摘要： A gas turbine engine includes a core having a compressor section with a first compressor and a second compressor, a turbine section with a first turbine and a second turbine, and a primary flowpath fluidly connecting the compressor section and the turbine section. The first compressor is connected to the first turbine via a first shaft, the second compressor is connected to the second turbine via a second shaft, and a motor is connected to the first shaft such that rotational energy generated by the motor is translated to the first shaft. The gas turbine engine includes a takeoff mode of operation, a top of climb mode of operation, and at least one additional mode of operation. The gas turbine engine is undersized relative to a thrust requirement in at least one of the takeoff mode of operation and the top of climb mode of operation, and a controller is configured to control the mode of operation of the gas turbine engine.
-
公开(公告)号：US20180002025A1
公开(公告)日：2018-01-04
申请号：US15200192
申请日：2016-07-01
CPC分类号： B64D27/10 , B64C25/405 , B64D27/16 , B64D27/24 , B64D41/00 , B64D2027/026 , B64D2205/00 , B64D2221/00 , F01D15/10 , F02C3/04 , F02C3/13 , F02C6/14 , F02K3/06 , F05D2220/323 , F05D2220/76 , Y10S903/905 , Y10S903/906
摘要： A gas turbine engine includes a core having a compressor section with a first compressor and a second compressor, and a turbine section with a first turbine and a second turbine. The first compressor is connected to the first turbine via a first shaft and the second compressor is connected to the second turbine via a second shaft. An electric motor is connected to the first shaft such that rotational energy generated by the electric motor is translated to the first shaft. An electric energy storage component is electrically connected to the electric motor, and electrically connected to at least one aircraft taxiing system. The gas turbine engine is configured such that the gas turbine engine requires supplemental power from the electric motor during at least one mode of operations.
-
-
-
-
-
-
搜索结果
7 条记录 (耗时 0.018 秒)
