초록 ▼

An active control system for use in gas turbine engines synchronizes exhaust nozzle area and burner fuel flow together with pas path variable engine parameters, such as fan variable vane and high compressor variable vane positions. As a result, extremely fast thrust transients are possible with opti

An active control system for use in gas turbine engines synchronizes exhaust nozzle area and burner fuel flow together with pas path variable engine parameters, such as fan variable vane and high compressor variable vane positions. As a result, extremely fast thrust transients are possible with optimized compression system stability, since fan and compressor rotor speeds are held high, allowing total engine power to be controlled by air flow and fuel flows directly.

대표청구항 ▼

A system for controlling power from an engine in an aircraft, said engine having a compressor affixed to a spool driven by a turbine and having variable gas path components including variably positioned vanes having selectable values, and a burner for generating hot exhaust gases, said system compri

A system for controlling power from an engine in an aircraft, said engine having a compressor affixed to a spool driven by a turbine and having variable gas path components including variably positioned vanes having selectable values, and a burner for generating hot exhaust gases, said system comprising: means for receiving aircraft parameter signals; means for receiving signals indicative of the variable gas path component values and burner fuel flow; scheduling means responsive to said aircraft parameter signals and said gas path component value signals for anticipating contemporary values of said burner fuel flow and at least one variable gas path component; and control means responsive to said scheduling means, for providing, in response to signals indicative of a selected engine power level, signals to engine components to select a magnitude of said burner fuel flow synchronously with selected variable gas path component values.