| 摘要 |
A method and system for maintaining a limiting gas temperature in a gas turbine engine working fluid flowpath by monitoring the gas temperature and adjusting one or more parameters when the gas temperature exceeds a predetermined or a calculated temperature limit during engine operation. The parameters include one or more of a group of engine parameters including high and low pressure turbine nozzle flow areas, fan and core flow areas, and a rotor speed. The one or more parameters are adjusted to lower the gas temperature to below the temperature limit during engine operation. The limiting gas temperature may be a turbine exhaust gas temperature such as a high pressure turbine exhaust gas temperature. The turbine nozzle flow areas may be adjusted with variable nozzle vanes and the fan and core exhaust nozzle flow areas with a translatable fan nozzle cowling and a translatable core nozzle plug, respectively.
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