초록 ▼

Disclosed is an engine surge avoidance system and method which adapts the acceleration schedules (i.e., P 2.5 bleed valve and NDOT) to prevent engine surge events from occurring while minimizing reductions in engine response time. The surge avoidance system and method disclosed herein achieves this

Disclosed is an engine surge avoidance system and method which adapts the acceleration schedules (i.e., P 2.5 bleed valve and NDOT) to prevent engine surge events from occurring while minimizing reductions in engine response time. The surge avoidance system and method disclosed herein achieves this goal by adapting both the NDOT and the P 2.5 bleed schedules in an optimum fashion.

대표청구항 ▼

1. A method of preventing surge events in a gas turbine engine following an initial surge event, the method comprising the steps of:a) establishing a transient temperature limit for a gas turbine engine;b) estimating a combustor discharge gas temperature;c) comparing the estimated combustor discharg

1. A method of preventing surge events in a gas turbine engine following an initial surge event, the method comprising the steps of:a) establishing a transient temperature limit for a gas turbine engine;b) estimating a combustor discharge gas temperature;c) comparing the estimated combustor discharge gas temperature to the established transient temperature limit;d) modifying a low pressure compressor bleed air flow rate schedule stored in non-volatile computer memory if the estimated combustor discharge gas temperature is less than the established transient temperature limit so as to improve an engine surge avoidance margin; ande) modifying an engine fuel flow rate schedule stored in non-volatile computer memory if the estimated combustor discharge gas temperature is greater than the established transient temperature limit so as to improve the engine surge avoidance margin. 2. A method according to claim 1, further comprising the step of measuring the combustor discharge gas temperature with a sensing means operatively positioned on the engine housing. 3. A method according to claim 1, further comprising the steps of:a) measuring a plurality of engine operating parameters; andb) estimating the combustor discharge gas temperature using a thermodynamic engine model and the plurality of measured engine operating parameters. 4. A method according to claim 1, wherein prior to modifying an engine fuel flow schedule if the estimated combustor discharge gas temperature is greater than the established transient temperature limit, the method further comprises the steps of:a) establishing a maximum allowable modification to the fuel flow schedule;b) determining if the maximum allowable modification to the fuel flow schedule has been reached; andc) modifying the low pressure compressor bleed air flow rate schedule so as to improve the engine surge margin if the maximum allowable modification to the fuel flow schedule has been reached. 5. A method according to claim 1, wherein the step of modifying an engine fuel flow rate schedule if the predicted combustor discharge gas temperature is greater than the established transient temperature limit comprises the step of estimating the speed of the engine's high pressure compressor. 6. A method according to claim 1, wherein the low pressure compressor bleed air flow rate schedule defines a bleed valve position over an entire range of low pressure compressor shaft speeds. 7. A method according to claim 1, wherein the fuel flow rate schedule defines an acceleration rate for the engine's core shaft over an entire range of engine core shaft speeds. 8. A method according to claim 7, wherein the acceleration rate and core shaft speed for the engine are corrected by temperature of low pressure compressor inlet air. 9. A system for preventing subsequent surge events in a gas turbine engine following an initial surge event, the gas turbine engine including in serial flow communication a low pressure compressor, a high pressure compressor, a combustor, a high pressure turbine and a low pressure turbine, the system comprising:a) means for establishing a transient temperature limit for a gas turbine engine;b) means for estimating a combustor discharge gas temperature;c) means for comparing the estimated combustor discharge gas temperature to the established transient temperature limit;d) means for modifying a low pressure compressor bleed air flow rate schedule stored in non-volatile computer memory if the estimated combustor discharge gas temperature is less than the established transient temperature limit so as to improve an engine surge avoidance margin; ande) means for modifying an engine fuel flow rate schedule stored in non-volatile computer memory if the estimated combustor discharge gas temperature is greater than the established transient temperature limit so as to improve the engine surge avoidance margin. 10. A system as recited in claim 9, further comprising means for measuring the combustor dis charge gas temperature using a sensor operatively positioned on the engine housing. 11. A system as recited in claim 9, further comprising:a) means for measuring a plurality of engine operating parameters; andb) means for estimating the combustor discharge gas temperature using a thermodynamic engine model and the plurality of measured engine operating parameters. 12. A system as recited in claim 9, further comprising:a) means for establishing a maximum allowable modification to the fuel flow schedule;b) means for determining if the maximum allowable modification to the fuel flow schedule has been reached; andc) means for modifying the low pressure compressor bleed air flow rate schedule so as to improve the engine surge margin if the maximum allowable modification to the fuel flow schedule has been reached. 13. A system as recited in claim 9, wherein further comprising means for estimating the speed of the engine's high pressure compressor. 14. A system as recited in claim 9, wherein the low pressure compressor bleed air flow rate schedule defines a bleed valve position over an entire range of low pressure compressor shaft speeds. 15. A system as recited in claim 9, wherein the fuel flow rate schedule defines an acceleration rate for the engine's core shaft over an entire range of engine core shaft speeds. 16. A system as recited in claim 15, wherein the acceleration rate and core shaft speed for the engine are corrected by temperature of low pressure compressor inlet air.