| 摘要 |
<p>The use of a single main centrifugal fuel pump for supplying fuel to an aircraft gas turbine engine has advantages over other known systems however a problem has existed in that the centrifugal pump, when driven in a fixed ratio to the engine speed, cannot deliver fuel at adequate pressure under engine starting conditions. The disclosed fuel supply system using a main centrifugal pump (10) overcomes this shortcoming by having a turbine-driven start pump (30) added to the fuel supply system with both the turbine (32) and the start pump receiving fuel pumped by the main centrifugal pump and the turbine utilizing the high flow, low pressure fuel to drive the start pump which increases the pressure of the fuel to a value adequate for engine starting. The start pump delivers fuel until such time as the centrifugal fuel pump has reached a speed to provide the fuel to the engine at the required pressure, at which time the turbine is no longer driven and the output of the start pump goes to zero.</p> |
