CONTROL OF GAS TURBINE ENGINE

• US 20100241331A1
• Filed: 03/19/2009
• Published: 09/23/2010
• Est. Priority Date: 03/19/2009
• Status: Active Grant

• Current Assignee: Pratt & Whitney Canada Corporation (Rtx Corporation)
• Original Assignee: Pratt & Whitney Canada Corporation (Rtx Corporation)
• Inventors: Lachance, Benoit, Duke, Brant, Jarvo, Jim R., Shafique, Harris
• Granted Patent: US 8,099,227 B2
• Time in Patent Office: Days
• US Class Current: 701/100
• CPC Class Codes: F01D 25/18 Lubricating arrangements of machines or engines in general F01M
• CPC Class Codes: F02C 3/145 the combustion chamber being in the reverse flow-type
• CPC Class Codes: F02C 7/06 Arrangements of bearings bearings F16C; Lubricating of turbo machines F01D25/18; of machines or engines in general F01M
• CPC Class Codes: F02C 7/22 Fuel supply systems
• CPC Class Codes: F02C 7/36 Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user F02C3/107 - F02C3/13 and F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H
• CPC Class Codes: F02C 9/28 Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed F02C9/30 - F02C9/38, F02C9/44 take precedence
• CPC Class Codes: F02K 3/06 with front fan
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

Systems, devices, and methods for controlling a fuel supply for a turbine or other engine using direct and/or indirect indications of power output and optionally one or more secondary control parameters.

Claims

1. A method of controlling a fuel supply for an aircraft-mounted turbine engine, the method comprising:

monitoring a differential oil pressure associated with an operating engine, the differential engine oil pressure determined using signals representing at least two measured operating engine oil pressures, to determine whether a change in the monitored differential engine oil pressure has occurred;

upon determining that a change in the monitored differential engine oil pressure has occurred, using signals representing at least one other aircraft or engine operating parameter to determine whether the change in differential engine oil pressure corresponds to a desired change in an output power level for the engine; and

if it is determined that the change in differential engine oil pressure does not correspond to a desired change in an output power level for the engine, calculating a desired fuel flow rate for the engine and providing a corresponding command signal to an engine fuel supply controller.

2. The method of claim 1, wherein the at least one other operating parameter comprises an acceleration of at least one portion of an aircraft.

3. The method of claim 1, wherein the at least one other aircraft of engine operating parameter comprises at least one of an engine operating temperature, and engine operating pressure, and air temperature, and an air pressure.

4. The method of claim 1, wherein the corresponding command signal provided to an engine fuel supply controller comprises signals adapted to modify a rate of fuel flow provided to the engine.

5. The method of claim 1, wherein, if a change in differential engine oil pressure does not correspond to a desired change in an output power level for the engine a current fuel flow rate to the engine is held for a determined time interval.

6. A method of controlling a fuel supply for an aircraft-mounted turbine engine, the method comprising:

monitoring a differential oil pressure associated with an operating engine, the differential engine oil pressure determined using signals representing at least two measured operating engine oil pressures, to determine a corresponding indicated engine output power level;

monitoring at least one other aircraft or engine operating parameter to determine whether the indicated engine output level corresponds to a desired output power level for the engine; and

if the indicated engine output level does not correspond to the desired output power level for the engine, calculating a desired fuel flow rate for the engine and providing a corresponding command signal to an engine fuel supply controller.

7. The method of claim 6, wherein the at least one other operating parameter comprises an acceleration of at least one portion of an aircraft.

8. The method of claim 6, wherein the at least one other aircraft of engine operating parameter comprises at least one of an engine operating temperature, and engine operating pressure, and air temperature, and an air pressure.

9. The method of claim 6, wherein the corresponding command signal provided to an engine fuel supply controller comprises signals adapted to modify a rate of fuel flow provided to the engine.

10. The method of claim 6, wherein, if the indicated engine output level does not correspond to the desired output power level for the engine, holding a current fuel flow rate to the engine for a determined time interval.

11. A controller for a fuel supply for an aircraft-mounted turbine engine, the controller adapted to:

receive from at least one transducer input signals representing a differential engine oil pressure;

receive from at least one other transducer input signals representing at least one other aircraft or engine operating parameter; and

using the input signals representing the differential engine oil pressure, determine whether a change in the differential engine oil pressure has occurred;

using input signals representing the at least one operating parameter, determine whether the determined change in differential engine oil pressure corresponds to a desired change in an output power level for the engine; and

upon determining that the determined change in differential engine oil pressure does not correspond to a desired change in an output power level for the engine, calculate a desired fuel flow rate for the engine and provide a corresponding output signal useful for controlling an engine fuel supply.

12. The controller of claim 11, wherein the at least one other transducer comprises an accelerometer.

13. The controller of claim 11, wherein the at least one other transducer comprises at least one of a temperature transducer, and a pressure transducer.

14. The controller of claim 11, wherein the corresponding output signal is adapted to modify a rate of fuel flow provided to an engine.

15. A controller for a fuel supply for an aircraft-mounted turbine engine, the controller adapted to:

receive from at least one transducer input signals representing a differential engine oil pressure;

receive from at least one other transducer input signals representing at least one other aircraft or engine operating parameter; and

using the input signals representing the differential engine oil pressure, determine whether a change in the differential engine oil pressure has occurred;

using input signals representing the at least one operating parameter, determine whether the determined change in differential engine oil pressure corresponds to a desired change in an output power level for the engine; and

upon determining that the determined change in differential engine oil pressure does not correspond to a desired change in an output power level for the engine, provide an output signal useful for maintaining a current fuel supply for an engine for a determined time interval.