-
公开(公告)号：US20230193856A1
公开(公告)日：2023-06-22
申请号：US17923418
申请日：2021-05-05
摘要： The present invention provides a multimode propulsion system, comprising at least one propellant ejector system, a high speed fluid ejection nozzle coupled to a propellant supply provided in the engine, and a propellant-air mixing system comprising at east one fluid intake member having an inlet end and an outlet end, the inlet end being in fluidic communication with the fluid ejection nozzle to receive the propellant ejected from the nozzle.
-
公开(公告)号：US12078127B2
公开(公告)日：2024-09-03
申请号：US17923418
申请日：2021-05-05
摘要： The present invention provides a multimode propulsion system, comprising at least one propellant ejector system, a high speed fluid ejection nozzle coupled to a propellant supply provided in the engine, and a propellant-air mixing system comprising at least one fluid intake member having an inlet end and an outlet end, the inlet end being in fluidic communication with the fluid ejection nozzle to receive the propellant ejected from the nozzle.
-
公开(公告)号：US20190101280A1
公开(公告)日：2019-04-04
申请号：US16086878
申请日：2017-03-21
发明人： Vladimir Mravcak , Dale Neuman
IPC分类号： F23C5/08
摘要： The present invention provides a fuel incinerating system comprising a fuel injector, a multi-stage fuel-air mixing device comprising a plurality of fuel intake tubes stacked vertically and configured to provide annular gaps between one or more of the vertically stacked fuel intake tubes to entrain ambient air to form a fuel-air mixture; and a combustor in communication with the fuel-air mixing device and defining a combustion chamber and in communication with an ignition source. The combustor is configured to impede flow of the fuel-air mixture through the combustion chamber to achieve a desired retention time of the fuel-air mixture within the combustion chamber to achieve substantially complete combustions of the fuel.
-
公开(公告)号：US20230313758A1
公开(公告)日：2023-10-05
申请号：US18192875
申请日：2023-03-30
摘要： The present invention relates to a propellant feed system for a rocket engine including a jet pump including a motive inlet for receiving a gaseous propellant, a driven inlet for receiving a liquid propellant, and an outlet for ejecting a mixed stream of the gaseous propellant and the liquid propellant. The propellant feed system further includes a heat exchanger configured to transfer thermal energy from a combustion chamber to the liquid propellant or the mixed stream, thereby transforming the liquid propellant or the mixed stream into the gaseous propellant. The propellant feed system further includes a pump configured to pump the liquid propellant or the mixed stream into the heat exchanger.
-
公开(公告)号：US20230272909A1
公开(公告)日：2023-08-31
申请号：US18017665
申请日：2021-07-23
CPC分类号： F23G7/08 , F23D11/24 , F23D14/64 , F23D14/105
摘要： The present invention relates to an incinerating system comprising an ejector system comprising an ejection nozzle and a fuel-air mixing system, a combustor, and an exhaust system, wherein the fuel-air mixing system and/or at least a portion of the combustor are oriented in a non-conventional direction/configuration, and wherein the ejector system is configured to provide required motive force in order to drive flame to continue through the burner in a desired direction.
-
-
-
-
搜索结果
5 条记录 (耗时 0.011 秒)
