Multi-compatible digital engine controller
A digital engine controller compatible with multiple variants of gas turbine engine is programmed to receive identification of a variant of gas turbine engine coupled to the digital controller and thereafter to automatically determine and adjust inputs to the engine, according to the received identification of engine variant, to meet user-specified output.
1. A digital engine controller compatible with multiple variants of gas turbine engine, the controller programmed to perform operations including receiving engine-specific data from a machine readable data source physically associated with a target gas turbine engine representing one of the multiple variants, responsive to receiving the engine-specific data determining combustion inputs to the target gas turbine engine in accordance with predetermined target-engine-specific rules and parameters stated or identified by the received engine-specific data, said determined combustion inputs including fuel, air, and ignition, and operating the target gas turbine engine in accordance with the determined combustion inputs.
2. The controller of claim 1 , where the machine readable data source includes a physical association with the target gas turbine engine by one or more of: physical attachment to the engine; physical attachment to a frame, skid, housing, or other structure attached to or containing the engine; physical proximity to the engine; where said controller is free of said physical association with the target gas turbine engine.
3. The controller of claim 1 , where the machine readable data source comprises a passive storage device or a transmitter that sends a signal continuously or upon interrogation, and further comprises any of: circuit storage, microcontroller with integrated electronic storage, magnetic or optical machine readable storage, a radio frequency identification device, wireless transmitter, optically transmissive or reflective tag, linear or matrix or other bar code, radio or other frequency beacon.
4. The controller of claim 1 , where:
the received engine-specific data includes an identification of the variant of the target gas turbine engine; and
the controller is programmed to perform further operations including using the identification of the variant to retrieve the predetermined target-engine-specific rules and parameters from storage outside the data source.
5. The controller of claim 1 , where:
the received engine-specific data includes the predetermined target-engine-specific rules and parameters for operating the target gas turbine engine.
6. The controller of claim 1 , where the controller is preprogrammed with multiple sets of target-engine-specific rules and parameters each set compatible with a different variant of gas turbine engine.
7. The controller of claim 1 , the predetermined target-engine-specific rules and parameters including at least one proportional-integral-differential control loop corresponding to each engine variant.
8. The controller of claim 1 , further comprising an operator interface coupled to the digital engine controller, the operator interface providing a substantially standardized interface regardless of the variant of gas turbine engine being controlled.
9. The controller of claim 1 , the predetermined target-engine-specific rules and parameters comprising one or more of the following function calls: come to idle, set compressor rotational speed (N1), set power turbine rotational speed (N2), engine on, engine off, natural gas test sequence, initiate diesel valve test sequence, initiate fault reporting, self-diagnostics, initiate prognostics.
10. The controller of claim 1 , the target-engine-specific rules and parameters comprising one or more of the following turbine engine traits expressed in a format including any of numbers, equations, ranges, lookup tables, or sequences: compressor rotational speed (N1) limits, power turbine rotational speed (N2) limits, exhaust gas temperature (EGT) limits, oil pressure limits, bleed band control parameters, operational range, proportional-integral-differential loop stability parameters.
11. A method of controlling a gas turbine engine, comprising operations of:
physically associating a machine readable data source with a target gas turbine engine;
providing a digital engine controller compatible with multiple variants of gas turbine engine including the target gas turbine engine, the controller being free from said physical association to the data source;
coupling the digital engine controller to controls and sensors of the target gas turbine engine; and
the digital engine controller receiving data from the data source, and responsive thereto, determining combustion inputs to the target gas turbine engine in accordance with predetermined target-engine-specific rules and parameters stated or identified by the received engine-specific data, said determined combustion inputs including fuel, air, and ignition; and
operating the target gas turbine engine in accordance with the determined combustion inputs.
12. The method of claim 11 , the operation of physically associating the machine readable data source comprising affixing the machine readable data source to the target gas turbine engine or a frame, housing, skid, or other structure containing or affixed to the target gas turbine engine.
13. The method of claim 11 , where:
the received data includes an identification of the variant of the target gas turbine engine; and
the operations further comprise the controller using the identification of the variant to retrieve the predetermined target-engine-specific rules and parameters from storage separate from the source.
14. The method of claim 11 , where:
the received data includes the predetermined target-engine-specific rules and parameters therein.
15. The method of claim 11 , where the operation of physically associating comprises physically attaching the machine readable data source to the target gas turbine engine or a frame, skid, housing, or other structure attached to or enclosing the target gas turbine engine, said physical attachment being independent of any coupling between the controller and the target gas turbine engine, and where the operation of the digital engine controller receiving data from the data source is performed wirelessly.
16. The method of claim 11 , the rules and parameters including at least one proportional-integral-differential control loop corresponding to each engine variant.
17. The method of claim 11 , where the data received from the data source identifies a variant representative of the target gas turbine engine, and the operations include the controller employing the received data to identify and retrieve the predetermined target-engine-specific rules and parameters.
18. The method of claim 11 , where the data received from the data source contains the predetermined target-engine-specific rules and parameters.
19. The method of claim 11 , further comprising providing an operator interface coupled to the digital engine controller, the operator interface providing a substantially standardized interface regardless of the variant of gas turbine engine being controlled.
20. The method of claim 11 , the target-engine-specific rules and parameters comprising one or more of the following function calls: come to idle, set compressor rotational speed (N1), set power turbine rotational speed (N1), engine on, engine off, natural gas test sequence, initiate diesel valve test sequence, initiate fault reporting, self-diagnostics, initiate prognostics.
21. The method of claim 11 , the rules and parameters comprising one or more of the following turbine engine traits expressed in a format including any of numbers, equations, ranges, lookup tables, or sequences: compressor rotational speed (N1) limits, power turbine rotational speed (N2) limits, exhaust gas temperature (EGT) limits, oil pressure limits, bleed band control parameters, operational range, proportional-integral-differential loop stability parameters.
22. A method of controlling a gas turbine engine, comprising operations of:
attaching a digital engine controller to a target gas turbine engine of a variant for which the digital engine controller is not programmed to manage;
coupling the digital engine controller to controls and sensors of the target gas turbine engine;
the digital engine controller receiving data from a machine readable data source physically associated or affixed to the gas turbine engine, the received data including predetermined target-engine-specific rules and parameters compatible with the variant of the target gas turbine engine; and
the controller managing combustion inputs to the target gas turbine engine in accordance with the received data including the predetermined target-engine-specific rules and parameters received from the data source.