| 摘要 |
An emergency hydraulic power system for aircraft which becomes operable upon aircraft engine failure includes a hot gas turbine for driving a hydraulic pump, a decomposition chamber to provide hot gas for driving the turbine, a normally unpressurized fuel storage tank, and a fuel pump for delivering fuel from the tank to the decomposition chamber. A start system includes a start fuel bottle having a cell filled with fuel and provided with a movable wall, and a cylinder of gas under high pressure which is regulated to put intermediate pressure on the movable wall and expel fuel from the cell, and also to put low pressure on the fuel tank, after a start valve is opened. Both the fuel tank and the start fuel cell communicate with an inlet conduit which goes to the fuel pump inlet, and a valve is provided to prevent start fuel from going into the fuel tank; and there is also means normally blocking communication from the start bottle and the tank to the pump inlet. Upon aircraft engine failure, the start valve is opened and the communication between the cell and the pump inlet is opened so that fuel from the start cell goes through the pump and through a pump outlet conduit to the decomposition chamber. At the same time, low gas pressure is placed upon the fuel in the tank. As the pump speed rises, the pump draws fuel from the tank and forces the fuel into the decomposition chamber, whereupon the start sequence is completed.
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