| 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.
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