METHOD AND DEVICE TO AVOID TURBO INSTABILITY IN A GAS TURBINE ENGINE

• US 20090245997A1
• Filed: 10/12/2006
• Published: 10/01/2009
• Est. Priority Date: 10/12/2006
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Levasseur, Glenn, Hurwitz, Wayne
• Granted Patent: US 8,313,280 B2
• Time in Patent Office: Days
• US Class Current: 415/1
• CPC Class Codes: F01D 17/08 responsive to condition of working-fluid, e.g. pressure
• CPC Class Codes: F01D 17/141 by means of shiftable members or valves obturating part of the flow path
• CPC Class Codes: F01D 21/00 Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
• CPC Class Codes: F02C 9/18 by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages F02C3/113 takes precedence
• CPC Class Codes: F02K 1/1207 of one series of flaps hinged at their upstream ends on a fixed structure F02K1/1215 - F02K1/1292 take precedence
• CPC Class Codes: F02K 3/025 the by-pass flow being at least partly used to create an independent thrust component
• CPC Class Codes: F02K 3/06 with front fan
• CPC Class Codes: F02K 3/075 controlling flow ratio between flows
• CPC Class Codes: F05D 2250/52 Outlet
• CPC Class Codes: F05D 2270/101 Compressor surge or stall
• CPC Class Codes: F05D 2270/301 Pressure
• CPC Class Codes: F05D 2270/304 Spool rotational speed

Abstract

(A1) A turbofan engine control system is provided for managing a fan operating line. The engine (10) includes a spool having a turbine housed in a core nacelle (12). A turbofan (20) is coupled to the spool (14). A fan nacelle (34) surrounds the turbofan and core nacelle and provides a bypass flow path having a nozzle exit area (40). A controller (50) is programmed to effectively change the nozzle exit area in response to an undesired turbofan stability margin which may result in a stall or flutter condition. In one example, the physical nozzle exit area is increased at the undesired stability condition in which the airflow into the engine creates a destabilizing pressure gradient at the inlet side of the turbofan. A turbofan pressure ratio, turbofan pressure gradient, low spool speed and throttle position are monitored to determine the undesired turbofan stability margin.

Claims

1-19. -19. (canceled)

20. A turbofan engine control system for managing a turbofan operating line comprising:

a spool including a turbine housed in a core nacelle;

a turbofan coupled to the spool;

a fan nacelle surrounding the turbofan and core nacelle and providing a bypass flow path having a nozzle exit area; and

a controller programmed to effectively change the nozzle exit area in response to an undesired stability margin for the turbofan by lowering the turbofan operating line and increasing the turbofan stability margin, wherein the controller detects the undesired stability margin.

21. The turbofan engine control system according to claim 20, wherein the spool is a low spool supporting a low pressure compressor and the turbine is a low pressure turbine.

22. The turbofan engine control system according to claim 21, comprising a high spool rotatable relative to the low spool, the high spool supporting a high pressure compressor downstream from the low pressure compressor.

23. The turbofan engine control system according to claim 20, wherein the undesired stability margin corresponds to a pressure ratio across the turbofan including turbofan inlet and outlet pressures.

24. The turbofan engine control system according to claim 23, wherein the inlet pressure includes multiple pressures indicative of a pressure gradient across a turbofan inlet.

25. The turbofan engine control system according to claim 23, wherein the undesired stability margin is generated during a condition corresponding to an undesired pressure gradient across a turbofan inlet.

26. The turbofan engine control system according to claim 20, comprising first and second pressure sensors in communication with the controller, the controller programmed to determine the undesired stability margin from the first and second pressure sensors.

27. The turbofan engine control system according to claim 20, comprising a speed sensor in communication with the controller, the controller programmed to determine the undesired stability margin from the speed sensor.

28. The turbofan engine control system according to claim 20, comprising a flow control device in communication with the controller, the controller programmed to command the flow control device to effectively increase the nozzle exit area in response to the undesired stability margin.

29. The turbofan engine control system according to claim 28, wherein the flow control device is adapted to increase the physical nozzle exit area in response to the undesired stability margin.

30. The turbofan engine control system according to claim 29, wherein the flow control device is adapted to open flaps arranged around a perimeter of the bypass flow path to increase the physical nozzle exit area.

31. The turbofan engine control system according to claim 29, wherein an actuator is in communication with the controller, the controller programmed to command the actuator to increase the physical nozzle exit area.

32. The turbofan engine control system according to claim 20, comprising a throttle position sensor in communication with the controller, the controller programmed to determine the undesired stability margin from the throttle position sensor.

33. The turbofan engine control system according to claim 20, comprising a sensing device in communication with the controller, the controller programmed to determine a direction of airflow into the turbofan engine relative to its inlet axis.

34. A method of managing a turbofan engine turbofan operating line, the method comprising the steps of:

detecting at least one of a turbofan pressure ratio, low spool speed, airflow direction and throttle position;

determining the undesired turbofan stability margin from the detecting step;

effectively increasing a nozzle exit area of a bypass flow path in response to an undesired turbofan stability margin; and

lowering the turbofan operating line and increasing the turbofan stability margin as a result of the nozzle exit area increasing.

35. The method according to claim 34, wherein the step of effectively changing the nozzle exit area includes physically increasing the nozzle exit area provided between core and fan nacelles.

36. The method according to claim 34, wherein the undesired turbofan stability margin corresponds to an undesired pressure gradient across a turbofan inlet resulting in a decrease in the turbofan stability limit.