Method and system for facilitating no-break power transfer

• US 7,528,499 B2
• Filed: 04/03/2008
• Issued: 05/05/2009
• Est. Priority Date: 09/04/2003
• Status: Expired due to Fees

• Current Assignee: Hamilton Sundstrand Corporation (Rtx Corporation)
• Original Assignee: Hamilton Sundstrand Corporation (Rtx Corporation)
• Inventors: Suttie, Peter J.
• Primary Examiner(s): Jackson; Stephen W
• Assistant Examiner(s): AMAYA, CARLOS DAVID
• Application Number:
  US12/061,725
• Publication Number:
  US 20080179947A1
• Time in Patent Office: 397 Days
• Field of Search: 307/9.1, 307/87, 307/23, 307/57, 307/62, 307/68, 290/51, 290/52
• US Class Current: 307/9.1
• CPC Class Codes: F02C 9/00 Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants controlling air intakes F02C7/057; controlling turbines F01D; controlling compressors F04D27/00; controlling in general G05
• CPC Class Codes: F02C 9/42 specially adapted for the control of two or more plants simultaneously
• CPC Class Codes: F05D 2220/50 for auxiliary power units (APU's)

Abstract

An improved method and system for facilitating no-break power transfer between an APU and a main engine includes determining a required APU speed for conducting power transfer based on various APU operating parameters, such as engine speed, fuel, environmental temperature, etc. The APU controller then adjusts the APU speed up or down to the required APU speed. Communication between an aircraft computer and the APU controller may also be provided so that operational data can be exchanged to adjust the electrical load of the aircraft below a maximum load threshold set by the APU, avoiding overloading of the APU during power transfer. By exchanging operational data between the APU controller and the aircraft computer, both the APU and the electrical load can be adjusted to optimize no-break power transfer despite varying APU operating conditions and main engine generator frequencies.

Claims

1. A method of facilitating power transfer between a main engine and an auxiliary power unit (APU), comprising:

obtaining a main engine generator frequency;

determining a target APU speed that will generate an APU generator frequency that is the same as the main engine generator frequency;

adjusting an actual APU speed to the target APU speed;

conducting the power transfer between the main engine and the APU;

determining a maximum APU load; and

adjusting an aircraft electrical load requirement until the aircraft electrical load falls below the maximum APU load.

2. The method of claim 1, further comprising determining an APU rate limit, wherein the step of adjusting the actual APU speed includes keeping an adjustment rate below the APU rate limit.

3. The method of claim 2, wherein as said APU speed increases, said shut-down load devices are brought back on line.

4. The method of claim 1, wherein the load on the main engine comprises a plurality of load devices, and wherein the adjusting step comprises selecting at least one load device for shut-down during the power transfer.

5. The method of claim 1, wherein the step of determining the maximum APU load comprises checking a look-up table linking the target APU speed with at least one main engine operating parameter.

6. An engine control system that facilitates power transfer between a main engine and an auxiliary power unit, comprising:

a control unit in communication with an aircraft load management system;

an APU controller in communication with the APU; and

a communication bus that forms a communication link between the control unit and the APU controller,

wherein the APU controller obtains a main engine generator frequency from the control unit, determines a target APU speed that will generate an APU generator frequency that is the same as the main engine generator frequency, and adjusts an actual APU speed to the target APU speed to allow power transfer between the main engine and the APU, and at least one load is connected to the main engine, wherein the APU controller determines a maximum APU load and wherein the control unit selects at least one load device for the aircraft load management system to shut down during the power transfer to keep a load on the APU below the maximum APU load.

7. The engine control system of claim 6, wherein the APU controller determines an APU rate limit and adjusts the actual APU speed at an adjustment rate below the APU rate limit.

8. The engine control unit of claim 6, wherein the load on the main engine comprises a plurality of load devices, and wherein the adjusting step comprises selecting at least one load device for shut-down during the power transfer.

9. The engine control unit of claim 8, wherein as said APU speed increases, said shut-down load devices are brought back on line.