Modular fuel supply device for a gas turbine including a fuel supply device having an integrated control device

• US 8,881,529 B2
• Filed: 05/09/2007
• Issued: 11/11/2014
• Est. Priority Date: 05/18/2006
• Status: Expired due to Fees

• Current Assignee: MTU Aero Engines GmbH (MTU)
• Original Assignee: MTU Aero Engines GmbH (MTU)
• Inventors: Wittmann, Peter
• Primary Examiner(s): Wongwian, Phutthiwat
• Assistant Examiner(s): MEADE, LORNE EDWARD
• Application Number:
  US12/297,935
• Publication Number:
  US 20100064658A1
• Time in Patent Office: 2,743 Days
• Field of Search: 60/392.81, 60/392.7, 607/34, 607/41, 417/18, 417/26, 417/44.1
• US Class Current: 60/734
• CPC Class Codes: F02C 7/14 of fluids in the plant , e.g. lubricant or fuel F02C7/185 takes precedence
• CPC Class Codes: F02C 7/224 Heating fuel before feeding to the burner
• CPC Class Codes: F02C 7/236 Fuel delivery systems comprising two or more pumps
• CPC Class Codes: F02C 9/26 Control of fuel supply F02C9/48 takes precedence; fuel valves F02C7/232
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A gas turbine, in particular a gas turbine aircraft engine, including a fuel supply device and a control device, wherein at least parts of the control device, in particular of an engine control device, are integrated into the fuel supply device.

Claims

1. A gas turbine the gas engine comprising:

a fuel supply device;

an engine control device including parts that are contained in and form the fuel supply device, the parts of the engine control device forming an engine control unit;

a motor-pump unit including at least one pump, at least one electric motor and at least one motor control unit configured for controlling the operation of said at least one electric motor,

wherein said engine control unit is configured for controlling the operation of said at least one motor control unit, and

wherein said at least one motor control unit comprises a plurality of activated controllers that operate in parallel, each of said activated controllers including a power electronics system providing a portion of the power to said motor-pump unit based on at least one control signal provided by said engine control unit such that when one of the controllers fails, full power is still provided to said motor-pump unit by the combined power provided by the remaining activated controllers and when two of the activated controllers fail, the remaining of the activated controllers supply power to said motor pump unit up to 80% of full power.

2. The gas turbine as recited in claim 1, wherein

the motor-pump unit, the at least one motor control unit, and the engine control unit are each fashioned as modules coupled to each other via plug connectors to form an integral assembly.

3. The gas turbine as recited in claim 1, wherein

the motor-pump unit, the at least one motor control unit, and the engine control unit are fashioned as line replaceable units that can be exchanged in an installed gas turbine.

4. The gas turbine as recited in claim 1, wherein said controllers are configured for controlling the operation of the at least one motor control unit on the basis of at least one measurement quantity of at least one sensor integrated into the motor-pump unit.

5. The gas turbine as recited in claim 2, wherein the motor-pump unit, the at least one motor control unit, and the engine control unit are each fashioned as line replaceable units that can be exchanged in an installed gas turbine.

6. The gas turbine as recited in claim 3, wherein said controllers are configured for controlling the operation of the at least one motor control unit on the basis of at least one measurement quantity of at least one sensor integrated into the motor-pump unit.

7. A gas turbine the gas engine comprising:

a fuel supply device formed by a plurality of modules coupled together, one of said modules being an engine control device,

said fuel supply device including at least one pump and at least one electric motor configured to drive said at least one pump, wherein said at least one pump and said at least one electric motor form a motor-pump unit,

said fuel supply device further including at least one motor-regulating unit that controls the operation of said at least one electric motor, said at least one motor-regulating unit including a plurality of activated regulators that operate in parallel and control the operation of said motor-pump unit, wherein each of said activated regulators delivers a portion of the motor power generated by said at least one electric motor such that in an event of failure of one of said regulators, the full motor power is still delivered to said electric motor by the combined power delivered by the remaining activated regulators and when two of the regulators fail, the remaining of the activated regulators supply power to said electric motor up to 80% of full power.

8. The gas turbine of claim 7, wherein said engine control device module in said fuel supply device forms an engine-regulating unit configured to control an operation of said at least one motor-regulating unit.

9. The gas turbine of claim 8, wherein said motor-pump unit, said at least one motor-regulating unit and said engine-regulating unit are each formed as modules that are coupled together to form an integral assembly.

10. The gas turbine of claim 7, wherein said motor-pump unit, said at least one motor-regulating unit and said engine-regulating unit are each formed as line replaceable units that are exchanged when the gas turbine is assembled.

11. The gas turbine of claim 8, wherein said engine-regulating unit includes a plurality of redundantly operating regulators, each of said regulators including a first computing unit for regulation and a second computing unit for monitoring, said first and second computing units configured to control and regulate the operation of said at least one motor-regulating unit based on at least one measured variable of at least one sensor integrated into said motor-pump unit.