초록 ▼

A secondary control for a gas turbine engine powering fighter class of aircraft serves to modify the primary control solely during transient engine operation primarily in the combat box of between approximately 0.4 to 1.2 Mach number at an altitude between 10,000 to 30,000 feet of the flight envelop

A secondary control for a gas turbine engine powering fighter class of aircraft serves to modify the primary control solely during transient engine operation primarily in the combat box of between approximately 0.4 to 1.2 Mach number at an altitude between 10,000 to 30,000 feet of the flight envelope and does maintain higher compressor rpm, turbine inlet temperature, and engine air flow at the idle or part power thrust settings by concomitantly adjusting fuel flow and engine exhaust nozzle area thereby enhancing thrust response, low cycle fatigue life, and engine stability.

대표청구항 ▼

For a gas turbine engine for producing trust to propel aircraft having a variable area exhaust nozzle and being operable over a given flight envelope including a combat box of a given flight Mach number and altitude, a primary control system for monitoring given engine operating parameters for contr

For a gas turbine engine for producing trust to propel aircraft having a variable area exhaust nozzle and being operable over a given flight envelope including a combat box of a given flight Mach number and altitude, a primary control system for monitoring given engine operating parameters for controlling the rate of fuel delivered to said engine and said variable area exhaust nozzle, secondary control means operable primarily within said combat box but not solely and solely during transients of said gas turbine engine operation to further control said fuel delivered to said engine and said variable area exhaust nozzle to attain a higher part power and idle rotor speeds of said engine than is attained by said primary control.