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1. 发明授权

US5454532A Aircraft deicer pumping system 失效
标题翻译：飞机除冰机抽水系统
公开(公告)号：US5454532A
公开(公告)日：1995-10-03
申请号：US5317
申请日：1993-01-15
申请人： Thomas W. Whitmire
发明人： Thomas W. Whitmire
IPC分类号： B64F5/00 , F04F5/46 , B64D1/00 , B64D15/00
CPC分类号： B64F5/0054 , B64F5/0063 , F04F5/46
摘要： In an aircraft deicer comprising a reservoir and a pump connected to the reservoir through a first conduit, the pump operating to circulate a fluid contained within the reservoir throughout at least a portion of the deicer, the improvement comprising: a jet pump located in the first conduit between the reservoir and the pump for increasing the pressure of the fluid within the first conduit between the jet pump and the pump; the jet pump comprising a tubular body portion having an inlet end and a discharge end and a nozzle located within the body portion between the inlet end and the discharge end; and a second conduit extending from a discharge end of the pump to the nozzle; whereby fluid from the discharge end of the pump is injected into the fluid flowing from the reservoir through the jet pump.
摘要翻译：在包括储存器和通过第一管道连接到储存器的泵的飞机除冰机中，所述泵操作以使包含在所述储存器内的流体遍及所述除冰机的至少一部分，所述改进包括：位于所述第一管道中的喷射泵储存器和泵之间的管道，用于增加喷射泵和泵之间的第一管道内的流体的压力; 喷射泵包括具有入口端和排出端的管状主体部分和位于入口端和排出端之间的主体部分内的喷嘴; 以及从所述泵的排出端延伸到所述喷嘴的第二管道; 其中来自泵的排出端的流体被注入从储存器流过喷射泵的流体中。

2. 发明授权

US5190249A Aircraft deicer fluid heating and propulsion system 失效
标题翻译：飞机除冰机加热和推进系统
公开(公告)号：US5190249A
公开(公告)日：1993-03-02
申请号：US414628
申请日：1989-09-25
申请人： Thomas W. Whitmire , Edwin C. Hightower
发明人： Thomas W. Whitmire , Edwin C. Hightower
IPC分类号： B64F5/00
CPC分类号： B64F5/0054 , B64F5/0063
摘要： The invention is a system for heating aircraft deicing fluid. The system is an aircraft deicer such as shown in FIG. 2 which includes an engine 210. The deicer systems comprises a tank 270 for holding deicing fluid. First pump means 250,252 and 254 are driven by engine 210 and pump deicing fluid from tank 270 through piping or conduit 266,264,230. Backpressure valve means 251,253,255 is positioned the outlet of the first pump means 250,252,254 respectively, to continuously, substantially and directly heat deicing fluid to a temperature sufficient to deice the aircraft.The system further comprises second pump means 212, 232 for directing deicing fluid through engine 210 to pick up heat rejected by engine 210. Once the deicing fluid has been pumped through engine 210, piping or a conduit means 216,222,228,230,266,264 connects the output of the second pump means 212,232 to the inlet of the first pump means 250,252 and 254.
摘要翻译：本发明是用于加热飞机除冰液的系统。该系统是如图1所示的飞机除冰机。除冰机系统包括用于保持除冰流体的罐270。第一泵装置250,252和254由发动机210驱动，并且通过管道或导管266,264,230从罐270驱动泵除冰流体。背压阀装置251,253,255分别定位在第一泵装置250,252,254的出口处，以将除冰流体连续地，基本上和直接加热到足以使飞机发射的温度。该系统还包括第二泵装置212,232，用于引导除冰流体通过发动机210以拾取由发动机210排出的热量。一旦除冰液被泵送通过发动机210，管道或导管装置216,222,228,230,266,264将第二泵的输出指向第一泵装置250,252和254的入口的装置212,232。

3. 外观设计

USD304024S Aircraft deicer vehicle 失效
公开(公告)号：USD304024S
公开(公告)日：1989-10-17
申请号：US857573
申请日：1986-04-25
申请人： Paul D. Eckstedt , Thomas W. Whitmire
设计人： Paul D. Eckstedt , Thomas W. Whitmire

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