초록 ▼

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 tu

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.

대표청구항 ▼

A control for controlling a gas turbine engine for powering aircraft during rapid accelerations and decelerations operating modes, said gas turbine engine having a first spool comprising a high pressure compressor and a first turbine driving said high pressure compressor and a second spool comprisin

A control for controlling a gas turbine engine for powering aircraft during rapid accelerations and decelerations operating modes, said gas turbine engine having a first spool comprising a high pressure compressor and a first turbine driving said high pressure compressor and a second spool comprising a low pressure compressor and a second turbine driving said low pressure compressor and said first spool and said second spool being solely aerodynamically coupled, fuel metering means for regulating the flow of fuel to said engine, and variable vanes for said high pressure compressor for regulating the airflow thereto, means for controlling said engine to operate on a predetermined high pressure compressor steady state operating curve and having the speed of said first spool and said second spool being at a predetermined relationship, a power lever, said control including means responsive to the position of said power level for establishing a thrust value for adjusting said engine to accelerate and decelerate rapidly, said control having additional control means responsive to engine and aircraft operating variables for generating a first signal requesting a desired corrected low compressor speed (N1), means responsive to said first signal and a preselected fixed corrected high pressure compressor speed (N2) for generating a desired airflow from said variable vanes, means responsive too said power lever for selecting a constant N2, means responsive to the difference of said selected constant N2 and measured N2 including a proportional and integral controller for adjusting said variable vanes to accelerate or decelerate said engine to said value established by said power lever, and means responsive to a timed signal to adjust said variable vanes as a function of said desired corrected low pressure speed operating in cooperation with said means for adjusting said fuel metering means to return said engine to operate on said high pressure compressor steady state operating curve.