A gas turbine engine is disclosed which is capable of being reconfigured for one operating mode to another. A display is provided that permits a pilot or other operator to select between engine modes. One aspect is the ability to provide variable cooling that can be controlled by various devices. Th
A gas turbine engine is disclosed which is capable of being reconfigured for one operating mode to another. A display is provided that permits a pilot or other operator to select between engine modes. One aspect is the ability to provide variable cooling that can be controlled by various devices. The variable cooling features can be used with devices such as cooled turbine components like vanes and/or blades. Devices can be used to reconfigure the performance and/or operability of a gas turbine engine.
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1. An apparatus for configuring a gas turbine engine, comprising: a gas turbine engine operation module structured to receive a requested engine configuration and control variable mechanical features of the gas turbine engine to achieve the requested engine configuration, the gas turbine engine oper
1. An apparatus for configuring a gas turbine engine, comprising: a gas turbine engine operation module structured to receive a requested engine configuration and control variable mechanical features of the gas turbine engine to achieve the requested engine configuration, the gas turbine engine operation module structured to provide a plurality of candidate operation modes for selection corresponding to a plurality of engine configurations, the plurality of candidate operation modes including:a nominal operation mode in which specific fuel consumption (SFC) is non-optimal in favor of rapid thrust response;an optimum SFC mode in which a cooling feature is in a minimum cooling setting;a bolster thrust operation mode in which the gas turbine engine is configured to produce a spoiled thrust through a variable mechanical feature that can be quickly reconfigured to produce a non-spoiled thrust;a flow holding operation mode in which fan speed is held and flow through an internal duct remains substantially constant while the gas turbine engine produces varying thrust levels through a configuration of variable mechanical features; anda power off-take mode in which engine is placed in a state that accommodates a heavy increase in demanded power without destabilizing the engine. 2. The apparatus of claim 1, which further includes an aircraft having a power plant capable of producing power to operate the aircraft, the power plant including a gas turbine engine having a core, a bypass flow path, and a third stream offtake. 3. The apparatus of claim 1, wherein the variable features include at least one of variable geometry turbomachinery components, variable fuel flow, variable nozzle geometry, variable inlet geometry and variable third stream duct features. 4. The apparatus of claim 1, further comprising a display in communication with the gas turbine engine operation module, wherein the display is structured to display a list of the plurality of candidate operation modes and receive an input selecting one of the plurality of candidate operation modes. 5. The apparatus of claim 1, wherein the variable cooling feature is a turbine cooling valve. 6. The apparatus of claim 1, wherein the requested engine configuration is provided to the gas turbine engine operation module via at least one of a touch screen display and a display having a physical button. 7. The apparatus of claim 6, wherein the display is structured to display a list of the plurality of candidate operation modes as well as to display a confirmation of selection of requested engine configuration. 8. The apparatus of claim 1, wherein the gas turbine engine operation module is hosted in an engine controller. 9. The apparatus of claim 1, wherein the selected one of the plurality of candidate operation modes corresponds to the requested engine configuration. 10. A gas turbine engine configuration apparatus comprising: an aircraft power management system having a computer based user interface capable of receiving a command from an operator, the computer based user interface structured to receive a command to place a gas turbine engine in one of a plurality of power modes by adjusting one or more variable features, wherein the plurality of power modes correspond to a plurality of engine configurations;a module structured to receive the command from the computer based user interface and adjust the variable features of the gas turbine engine to change a configuration of the engine corresponding to one of the plurality of power modes, wherein the module includes the following power modes: a nominal mode having a degraded specific fuel consumption (SFC) condition;an SFC mode having an optimal SFC condition;a bolter mode characterized by operating the fan at a relatively high speed and adjusting one or more variable features to spoil thrust, the bolter mode capable of producing a relatively rapid rise in thrust by re-adjusting the one or more variable features;a flow holding mode in which the engine can produce a range of thrust conditions while keeping flow through a third stream bypass constant; anda power off-take mode characterized by operating the fan at substantially constant speed during a demanded power event with an attendant reduction in thrust;wherein the computer based user interface includes a multi-function display structured to display a list of the plurality of power modes for selection, and wherein the selected power mode corresponds to the command. 11. The apparatus of claim 10, wherein the variable features include at least two of variable geometry turbomachinery components, variable fuel flow, variable nozzle geometry, variable inlet geometry, and cooling flow. 12. The apparatus of claim 11, wherein the cooling flow is a turbine cooling flow capable of varying one of a temperature and a flow rate of the cooling flow. 13. The apparatus of claim 11, wherein the variable features also include at least one of a variable mechanism to alter a flow rate through a third-stream duct. 14. The apparatus of claim 10, wherein the aircraft power management system is integrated with an aircraft having a gas turbine engine that includes a fan useful for generating thrust with a bypass duct and configured to remain aloft for a period of time useful to accomplish an aircraft task, the gas turbine engine having variable features including any of compressor variable vanes, turbine variable vanes, and a fuel delivery system capable of being modulated. 15. The apparatus of claim 14, wherein the variable features also include a turbine cooling feature, and wherein the aircraft power management system is structured to display a confirmation of a change in power mode. 16. The apparatus of claim 10, wherein the module is hosted in an engine controller. 17. A method for configuring a gas turbine engine comprising: during operation of an aircraft gas turbine engine, receiving a request to change an engine operating mode between a first mode and a second mode from among a list of operating modes each corresponding to a predetermined engine configuration, the list including: a nominal mode having a non-optimal specific fuel consumption (SFC) configuration;an SFC mode having an fuel economizing configuration of variable feature of a vehicle;a bolter mode in which fan speed is held at a go-around condition and thrust is spoiled by a variable feature;a flow holding mode; anda weapon mode;after the receiving a selection, receiving a confirmation of the request to change the engine operating mode;reconfiguring a variable feature associated with operation of the gas turbine engine to accommodate the change between first mode and second mode of the gas turbine engine; anddisplaying a message that confirms operation of the second mode. 18. The method of claim 17, which further includes configuring a plurality of variable features to accommodate the change in engine operating mode. 19. The method of claim 18, wherein the gas turbine engine is an adaptive gas turbine engine having a third-stream duct. 20. The method of claim 18, wherein the configuring includes changing one of a fuel flow rate, a nozzle actuator position, a variable vane position, an inlet door position, a third stream variable.
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이 특허에 인용된 특허 (5)
Brunell, Brent Jerome; Mathews, Jr., Harry Kirk; Kumar, Aditya, Adaptive model-based control systems and methods for controlling a gas turbine.
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