公开(公告)号：KR840002483B1

公开(公告)日：1984-12-31

申请号：KR800001810

申请日：1980-05-07

Applicant: UNITED TECHNOLOGIES CORP

Inventor： POLLAK ROBERT R

IPC: F02C9/28 ,  F02C7/26

公开(公告)号：CA1137192A

公开(公告)日：1982-12-07

申请号：CA350410

申请日：1980-04-23

Applicant: UNITED TECHNOLOGIES CORP

Inventor： POLLAK ROBERT R

IPC: F02C9/28 ,  F02C7/26

Abstract: CONTROL FOR START-UP OF 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.

公开(公告)号：DE68928159D1

公开(公告)日：1997-08-14

申请号：DE68928159

申请日：1989-09-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： POLLAK ROBERT R ,  MARCOS JUAN A ,  KHALID SYED J

IPC: F02C9/50 ,  F02C9/28 ,  F02C9/54 ,  F02K1/16 ,  F02K1/17

Abstract: An active control system for use in gas turbine engines synchronizes exhaust nozzle (26) area and burner fuel flow together with gas path variable engine parameters, such as fan variable vane and high compressor variable vane positions (36, 38, 40). 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. Time responsiveness to thrust demands for a fan jet engine of the type that includes twin spools and a variable inlet at the fan is enhanced by regulating air flow through the variable inlet while holding low pressure compressor speed constant. The thrust change is targeted as a function of power lever position which generates a low pressure compressor parametric as a function of engine and aircraft operating variables. This parameter is then utilized to control both the inlet variable vanes and fuel flow to 1) attain the targeted value and 2) return the engine to its steady state operating line after a given time interval. The time responsiveness and engine stability for acceleration and deceleration engine transient is enhanced by 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.

公开(公告)号：DE68928159T2

公开(公告)日：1997-10-30

申请号：DE68928159

申请日：1989-09-13

Applicant: UNITED TECHNOLOGIES CORP

Inventor： POLLAK ROBERT R ,  MARCOS JUAN A ,  KHALID SYED J

IPC: F02C9/50 ,  F02C9/28 ,  F02C9/54 ,  F02K1/16 ,  F02K1/17

Abstract: An active control system for use in gas turbine engines synchronizes exhaust nozzle (26) area and burner fuel flow together with gas path variable engine parameters, such as fan variable vane and high compressor variable vane positions (36, 38, 40). 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. Time responsiveness to thrust demands for a fan jet engine of the type that includes twin spools and a variable inlet at the fan is enhanced by regulating air flow through the variable inlet while holding low pressure compressor speed constant. The thrust change is targeted as a function of power lever position which generates a low pressure compressor parametric as a function of engine and aircraft operating variables. This parameter is then utilized to control both the inlet variable vanes and fuel flow to 1) attain the targeted value and 2) return the engine to its steady state operating line after a given time interval. The time responsiveness and engine stability for acceleration and deceleration engine transient is enhanced by 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.