초록

A method for detecting a surge condition during operation of a gas turbine engine includes detecting a change of pressure differential between fuel flows in a fuel system of the engine during engine operation.

대표청구항 ▼

The invention claimed is: 1. A method for detecting a surge condition during operation of a gas turbine engine, comprising: a) monitoring a pressure differential between a fuel flow to a pilot nozzle and a fuel flow to a main manifold of a combustor in a fuel system of the engine during engine oper

The invention claimed is: 1. A method for detecting a surge condition during operation of a gas turbine engine, comprising: a) monitoring a pressure differential between a fuel flow to a pilot nozzle and a fuel flow to a main manifold of a combustor in a fuel system of the engine during engine operation; and b) detecting an uncommanded momentary change of said pressure differential. 2. The method as defined in claim 1 comprising a step of indicating a surge condition in the engine operation when the uncommanded momentary change of the pressure differential is verified. 3. The method as defined in claim 1 wherein the uncommanded momentary change is a momentary increase of the fuel pressure of the fuel flow to the pilot nozzle over the fuel pressure of the fuel flow to the main manifold. 4. The method as defined in claim 1 wherein the steps (a) and (b) are conducted when the pilot nozzle and the main manifold are in direct fluid communication in the fuel system. 5. The method as defined in claim 1 wherein step (b) is practised by steps: b1) detecting a momentary change of the monitored pressure differential; and b2) identifying the detected momentary change of the monitored pressure differential as being uncommanded during engine operation. 6. The method as defined in claim 5 wherein the detected momentary increase of the pressure differential is recorded in a memory. 7. The method as defined in claim 5 further comprising indicating an occurrence of a surge condition in the engine when the uncommanded momentary increase of the pressure differential is identified. 8. An apparatus for detecting a surge condition during operation of a gas turbine engine comprising: a differential pressure transducer connected between first and second fuel passages of a fuel system, the first fuel passage leading to a pilot nozzle and the second fuel passage leading to a plurality of main nozzles, both the pilot nozzle and main nozzles being in fluid communication with a combustion chamber of the combustor; means for detecting an uncommanded momentary change of a pressure differential monitored by the differential pressure transducer during engine operation; and an indicator for indicating an occurrence of a surge condition in the gas turbine engine upon receipt of a signal relating to the detected uncommanded momentary pressure change. 9. The apparatus as defined in claim 8 wherein the differential pressure transducer has a maximum pressure indication smaller than 150 PSI. 10. The apparatus as defined in claim 8 wherein the means comprise a device for detecting a momentary change of the pressure differential monitored by the differential pressure transducer and a device for identifying the detected momentary change of the monitored pressure differential as being uncommanded. 11. The apparatus as defined in claim 10 wherein the means comprise a memory for recording the detected momentary change. 12. The apparatus as defined in claim 10 wherein the differential pressure transducer has a maximum pressure indication smaller than a maximum fuel pressure in the system established by the fuel pump. 13. A fuel system of a gas turbine engine, comprising: a fuel pump for pressurizing fuel from a fuel source; at least one pilot nozzle in fluidic communication with a combustion chamber of the engine; a main manifold including a plurality of main nozzles in fluidic communication with the combustion chamber of the engine; a fluidic connection extending from the fuel pump and dividing into at least first and second passages leading to the respective pilot nozzle and main manifold; a differential pressure transducer between the first and second passages of the fluidic connection for monitoring a pressure differential between the first and second passages; a control unit in contact with the fluidic connection for controllably operating the fuel system, the control unit including a device for detecting an uncommanded momentary change of a pressure differential monitored by the differential pressure transducer; and an indicator for indicating an occurrence of a surge condition when the uncommanded momentary change of the pressure differential is detected. 14. The system as defined in claim 13 further comprising a pressure valve adapted (1) to prevent fuel from flowing through the fluidic connection to the respective pilot nozzle and main manifold when a fuel pressure created by the fuel pump varies to become lower than a first value; (2) to allow fuel to flow only through the first passage to the pilot nozzle when the fuel pressure varies to become higher than the first value and lower than a second value; and (3) to allow fuel to flow through both the first and second passages to the respective pilot nozzle and main manifold when the fuel pressure varies to become higher than the second value. 15. The system as defined in claim 14 further comprising a first on-and-off valve associated with a bypass passage over the pressure valve, to selectively open and close the bypass passage. 16. The system as defined in claim 15 further comprising a cheek valve in the bypass passage. 17. The system as defined in claim 15 further comprising a second on-and-off valve between the first and second passages of the fluidic connection, in a parallel relationship with the differential pressure transducer, for selectively opening and closing a direct fluid communication between the first and second passages. 18. The system as defined in claim 15 wherein the first and second on-and-off valves are controlled by the control unit.