| 摘要 |
The invention relates to a fuel drive pump, having a monolithic structure, for turbines of aircraft, comprising a pump body, wherein all the components are assembled to establish and control the pressure and flow in the pump, including an inlet port for supplying fuel at a controlled pressure, fuel return ports, fuel filter, pump rotor, port having an outlet pressure sensor, port having an inlet pressure sensor, pump cover having sealing system to maintain the pressure load, close the assembly and maintain the inlet pressure, pump impeller to establish the hydraulic outlet power, intermediate cap of the pump to regulate the pressure in the pump, and rotation arrow of the pump, having a hollow shaft for starting the driving of the system. |
