Self-contained power unit for implementing a method for optimizing the operability of an aircraft propulsive unit
A main power unit implements an optimization method in an aircraft including energy-consuming equipments, a cabin in which air is renewed and temperature and/or pressure of which are regulated by a regulation system, main power-generating engines, and a flight control unit. The main power unit is built into a compartment which is insulated from other zones of the aircraft with a fireproof bulkhead and fitted with an outside-air intake and an exhaust nozzle. The main power unit includes an engine-type power unit as a main power source, fitted with a gas generator and with a power turbine for driving equipments including a supercharger. The supercharger is coupled, via a regulation control which communicates with the control unit, with the regulation system in order to supply a necessary pneumatic energy to the cabin.
1. A main power unit for implementing an optimization method in an aircraft including energy-consuming equipments, a cabin in which air is renewed and temperature and/or pressure of which is/are regulated by environmental control system (ECS), propulsive power-generating engines, and a flight controller, the main power unit being built into a compartment which is insulated from other zones of the aircraft with a fireproof bulkhead and fitted with an outside air intake and an exhaust nozzle, the main power unit comprising:
an engine said engine being fitted with a gas generator and with a power turbine that drive the energy consuming equipments including a supercharger, said supercharger being coupled with the ECS in order to supply a necessary pneumatic energy to the cabin, said supercharger being coupled with the ECS via a regulation control which communicates with the flight controller.
2. The main power unit according to claim 1 , wherein the main power unit is coupled with a recovery structure that includes an energy-recovery turbine for driving the energy-consuming equipments with the power turbine and is coupled, on an air-inlet side, with an outlet of the cabin in order to cool, on an air-outlet side, the energy-consuming equipments, the supercharger being built into this recovery structure as a supplier of the necessary pneumatic energy to the cabin.
3. The main power unit according to claim 2 , in which the recovery turbine ejects an air flow into the compartment of the main power unit which, after the air flow has cooled the energy-consuming equipments including auxiliary equipments contained in an intermediate compartment, is evacuated into the exhaust nozzle by a jet pump action resulting from an efflux velocity of a hot air flow coming out of the power turbine.
4. The main power unit according to claim 1 , wherein the engine includes a combustion chamber.
5. The main power unit according to claim 1 , wherein the engine is usable during all flight phases.