Construction and operation of aircraft fluid systems

Construction and operation of aircraft fluid systems. The turbine engine and the pneumatic power generation component are integral. Largely, the engine component is responsible to the pneumatic power generation. The constructional design of the power generation component takes into consideration the needs to regulate pressure and temperature. Normally, bled air conditions depend on the engine functioning conditions. Critics contend that bleeding the air from the engine can lead to engine suffocation consequently leading to mechanical breakdown. The pneumatic compressor bleeds air from the engine in various stages, a low-pressure port, intermediate and high-pressure port. The compressor has a check valve, which prevents air from moving to low pressure port during bleeding. By design, the low-pressure port is always open, but the shut valve may close it if the engine is a critical condition. The pneumatic power system in aircraft is a secondary power. By design, bleed air is tapped from one or more points along the engine compressor to provide pneumatic power. To achieve the requirement drive shafts, from the engine’s high pressure shaft, drive an accessory gear box on which are mounted generators and hydraulic pumps as well as engine’s own accessories.