United Technologies Corporation

Robert R Pollak

Juan A Marcos

Syed J Khalid

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.

Active geometry control system for gas turbine engines

The time responsiveness and engine stability for an acceleration and deceleration engine transient is enhanced by a control mechanism that synchronously adjusts fuel flow and high pressure compressor vane position as a function of corrected low pressure compressor speed in a twin spool axial flow turbine power plant. The acceleration and deceleration mode is targeted by power lever position and the target is attained by adjusting the vane position at a constant high pressure compressor speed and returned to a fuel efficient and engine stable steady state operating line by concomittantly adjusting fuel flow and vane position.

Control of high compressor vanes and fuel for a gas turbine engine

A closed loop control for starting a gas turbine engine is disclosed. Upon engine ignition, fuel flow is adjusted as a function of the difference between a desired torque and actual torque so as to provide an optimum schedule to accelerate the engine to the idle speed condition.

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North Palm Beach, FL, United States of America

Robert R Pollak