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公开(公告)号：US11752837B1
公开(公告)日：2023-09-12
申请号：US16684775
申请日：2019-11-15
发明人： Joshua Peters , Igor Vaisman
CPC分类号： B60H1/3205 , B60H1/00899 , B64D33/04 , F01P3/20 , F02C7/16 , F02K3/11 , F02K7/00 , F02K9/00
摘要： Disclosed is a mechanism to exhaust refrigerant vapor resulting from operation of a thermal management system that is used to cool a thermal load by a vehicle, such as an airborne vehicle. The thermal management system includes an open circuit refrigeration system featuring a receiver configured to store a liquid refrigerant fluid, an evaporator configured to extract heat from the thermal load that contacts the evaporator, and an exhaust line, where the receiver, the evaporator, and the exhaust line are connected to provide an open refrigerant fluid flow path. Other implementations of open circuit refrigeration systems include the use of a gas receiver, a pump and an ejector are also described, as are other mechanisms to exhaust refrigerant vapor resulting from operation of the thermal management system.
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公开(公告)号：US11466856B2
公开(公告)日：2022-10-11
申请号：US17317073
申请日：2021-05-11
申请人： ROLLS-ROYCE plc
发明人： Michael Yeandel
摘要： An afterburner arrangement comprising: an internal casing and an external casing defining a bypass pathway between them; a mounting strut forming a structural connection between the internal casing and the external casing; and A plurality of fuel nozzles associated with the mounting strut, wherein the mounting strut at least partly houses a corresponding plurality of fuel pathways to provide fuel to the respective fuel nozzles.
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公开(公告)号：US20220136435A1
公开(公告)日：2022-05-05
申请号：US17085922
申请日：2020-10-30
申请人： LARRY BURFORD
发明人： LARRY BURFORD
摘要： A jet engine uses an entrainment compressor within a housing to compress intake air. The compressed air is routed to a combustion chamber where it is ignited. A portion of the exhaust is directed outward for thrust and a portion is rerouted through an energy feedback system to one or more entrainment nozzles within the compressor housing. The exhaust acts as motive fluid to mix with the intake air. The motive fluid imparts energy to create the compressive capability of the jet engine. A startup system is configured to generate startup motive fluid selectively routed through some or all of the entrainment nozzles to initiate a stable idle flow of motive fluid. Some of the entrainment nozzles may include combustion chambers to further enhance the compressive capability of the jet engine.
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公开(公告)号：US20190093553A1
公开(公告)日：2019-03-28
申请号：US16142337
申请日：2018-09-26
IPC分类号： F02C3/14 , F23G7/06 , F23R7/00 , F02C3/107 , F02K3/11 , F02C7/36 , F02C7/06 , F02C5/02 , F02K3/06
摘要： The engine (10) includes a low spool (16) disposed aft of an air inlet (12) and a high spool (34) disposed aft of the low spool (16). An intake reverse-duct (44) is disposed radially outward of the high spool (34) and reverses direction of low pressure compressed air from the low spool (16) into a forward-flow high pressure compressor (40) of the high spool (34). A discharge reverse-manifold (48) directs flow of an exhaust gas stream (50) from a forward-flow low pressure turbine (20) into a rearward-flow direction and into at least one pulse detonation firing tube (54). An annular bypass air duct (72) directs cooling air along the engine (10)—The at least, one firing tube is positioned radially outward of the high spool (34), overlies the high spool (34) and is also positioned within the bypass air duct (72).
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公开(公告)号：US07251941B2
公开(公告)日：2007-08-07
申请号：US10797212
申请日：2004-03-10
IPC分类号： F02K3/11
摘要： An afterburner includes an exhaust duct with a fixed area outer nozzle at an aft end thereof, and an ablative inner nozzle therein. The smaller inner nozzle is consumed during reheat operation to expose the larger outer nozzle for increased propulsion thrust.
摘要翻译： 加力燃烧器包括在其后端具有固定区域外部喷嘴的排气管道和其中的消融内部喷嘴。 在再热操作期间消耗较小的内部喷嘴以暴露较大的外部喷嘴以增加推进推力。
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公开(公告)号：US3879941A
公开(公告)日：1975-04-29
申请号：US36238073
申请日：1973-05-21
申请人： GEN ELECTRIC
CPC分类号： F02C7/04 , B64D33/02 , B64D2033/026 , F02K3/06 , F02K3/075 , F02K3/11 , Y10T137/0536
摘要： A variable cycle gas turbine engine for commercial supersonic aircraft is provided with variable geometry means to simultaneously control the bypass and pressure ratios for different engine flight conditions wherein the engine may be operated at supersonic speed with a lower bypass and higher pressure ratio than at subsonic speed. The relatively high noise levels generally associated with the supersonic mode of operation for conventional supersonic engines can be significantly reduced by controlling the variable geometry means in a manner which increases the bypass ratio and decreases the pressure ratio of the fan section of the engine. In this manner, supersonic aircraft may approach and take off from airports situated adjacent densely populated areas without unduly disturbing the local residents.
摘要翻译： 用于商用超音速飞机的可变循环燃气涡轮发动机设置有可变几何装置，以同时控制不同发动机飞行条件的旁路和压力比，其中发动机可以以比亚音速更低的旁路和更高压力比在超音速下操作 。 通常通过以增加旁路比并降低发动机的风扇部分的压力比的方式控制可变几何装置，通常与常规超音速发动机的超音速操作模式相关联的相对较高的噪声水平可以显着降低。 以这种方式，超音速飞机可以靠近人口稠密地区的机场接近起飞，而不会不当地扰乱当地居民。
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7.发明授权Ejecting nozzle for propellers provided with a plurality of driving streams and,more particularly,two driving streams 失效为具有多种驱动力的螺旋桨喷射喷嘴，更特别的是两个驱动流
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公开(公告)号：US2978868A
公开(公告)日：1961-04-11
申请号：US86107559
申请日：1959-12-21
申请人： GEN ELECTRIC
发明人： PUFFER SAMUEL R
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公开(公告)号：US10563619B2
公开(公告)日：2020-02-18
申请号：US16188283
申请日：2018-11-13
申请人： Minglong Ge
发明人： Minglong Ge
IPC分类号： F02K9/64 , F02K3/10 , F23R3/20 , F02K9/42 , F23R7/00 , F23R3/42 , F02K3/11 , F23R3/60 , F02K9/97 , F02K9/78 , F02K99/00 , F23R3/58
摘要： An aerospace turbofan engine that injects oxygen-enriched gas from an inlet includes an oxygen-enriched gas injection component, a body structure, an afterburner middle portion and a first afterburner outer ring. An aerospace turbofan engine that injects oxygen-enriched gas from an inlet and an afterburner individually or simultaneously includes an oxygen-enriched gas injection component, a body structure, an afterburner middle portion and a second afterburner outer ring. The aerospace turbofan engines which fully utilize oxygen in the atmosphere for combustion and work in various flight altitude ranges adopt regenerative cooling-type afterburners with acoustic cavity and baffle plates, so that an aircraft can fly to an altitude of 20-50 km and reach a speed of Mach 2-5. Variants of the aerospace turbofan engines are disclosed.
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