Electric supply for an aircraft gas turbine engine equipment
View Patent ↗A device supplying electricity power to and actuating equipments of a gas turbine airplane engine, including an electricity power supply circuit dedicated to the engine and distinct from an electricity network on board the plane and excitation, control or servo circuits for pieces of electrical equipment of the engine. The engine electrical power supply circuit includes a first bus distributing DC or AC voltage to excitation, control or servo circuits for first pieces of electrical equipment of the engine, a second bus distributing DC or AC voltage to excitation, control or servo circuits for other pieces of electrical equipment of the engine requiring higher electrical power compared with the first pieces of equipment, and a third bus connected to receive power from an electricity source such as an airplane on-board electricity distribution network or an electricity generator dedicated to the engine and driven thereby. The third bus supplies the first and second bus with electricity power.
1. A device for supplying electricity power to and actuating equipments of a gas turbine airplane engine, comprising:
an electricity power supply circuit dedicated to the engine and distinct from an electricity network on board of the airplane and circuits for excitation, control or servo-control of pieces of electrical equipment of the engine,
the engine electricity power supply circuit comprising:
a first bus configured to distribute DC or AC voltage to circuits for excitation, control or servo-control of first pieces of electrical equipment of the engine,
a second bus configured to distribute DC or AC voltage to circuits for excitation, control or servo-control of second pieces of electrical equipment of the engine which require a higher electrical power than the first pieces of equipment, and
a third bus that includes a connection configured to receive power from an electricity source and connected to the first bus and to the second bus for supplying the first bus and second bus with electric power,
wherein the third bus is connected to receive electric power from the electricity distribution network on board of the airplane.
2. A device according to claim 1 , in which the third bus is connected to receive electric power from an electricity generator dedicated to the engine electricity power supply circuit and driven by the engine.
3. A device according to claim 1 , in which the first bus is connected to the third bus via at least one voltage converter or transformer.
4. A device according to claim 1 , in which the second bus is connected to the third bus via at least one voltage converter or transformer.
5. A device according to claim 1 , in which the first pieces of electrical equipment of the engine are pieces that require electricity at a power of less than 100 W.
6. A device according to claim 1 , in which the first pieces of electrical equipment of the engine comprise at least one item selected from an electronic regulator module for the engine, valves for controlling an overall flow rate of fuel delivered to the engine, a system for managing health and usage of members of the engine, compressor transient bleed valves, valves for controlling a flow rate of fuel delivered to combustion chamber injectors of the engine, valves for controlling air flow rate to adjust clearance at the tips of turbine blades, or a device for igniting combustion.
7. A device according to claim 1 , in which the second pieces of electrical equipment of the engine comprise at least one item selected from: devices for controlling a pitch angle of variable pitch vanes, adjustable bleed valves for a compressor, or a pump of a circuit for supplying fuel to the engine.
8. A device according to claim 1 , in which at least some of the circuits for excitation, control, or servo-control are implanted locally with corresponding of the pieces of electrical equipment.
9. A device according to claim 8 , in which at least some of the circuits for excitation, control or servo-control are integrated in corresponding of the pieces of equipment.
10. A device according to claim 1 , in which systems configured to adjust clearance at tips of turbine blades comprise electrical heater devices powered directly from the third bus.
11. A device according to claim 1 , in which the first bus and the second bus are independently connected to the third bus.
12. A device according to claim 1 , in which a fuel shutoff valve is directly connected to the electricity distribution network of the airplane.