[특허]Control system for gas turbine helicopter engines and the like

[미국특허] Control system for gas turbine helicopter engines and the like 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	G05B-013/02 G05B-007/02 F02C-009/00
출원번호	US-0418359 (1989-10-06)
발명자 / 주소	Parsons Douglas A. (Enfield CT) Johnston Mark A. (Windsor CT) Games John E. (Granby CT) DePardo Gerald L. (Glastonbury CT)
출원인 / 주소	United Technologies Corporation (Hartford CT 02)
인용정보	피인용 횟수 : 31 인용 특허 : 0

초록 ▼

A engine control system for helicopters and the like in which free turbine speed is isochronously controlled by a more robust control system having increased bandwidth due to loop architecture and filter implementation accomplished via closed loop control. Dual notch (feedback compensation) is used with design forward path compensation, including variable lead/position of the lead, variable gain and implementation of integrator/proportional. Superior transient control is achieved by the use of a multi-loop governing design using different error compensations when on “NF”loop control and when not on “NF”loop control, and with “bumpless”inner loop reference by the combination of compensation switching and re-initialization of a common integrator. Parallel select logic with dynamic compensation is used separating the system control loops and the selection process of the controlling functions, as they pertain to the application of control loops designed form small signal stability to large transients. A torque loop limitation as a direct function of the speed loop gains provides a predetermined limit to the governed speed excursion in the event of an in-range failure of the torque signal, or an unannounced fail fix on one engine or system of the twin engine application.

대표청구항 ▼

A control system for isochronously controlling free turbine speed (NF) of a gas turbine engine having a free turbine connected to a rotor system, having a gas generator speed (NG) to engine output torque (QF) (QF/NG) frequency characteristic with a variable lead and a variable dc gain, both that vary as a function of NG, and having an engine output torque (QF) to free turbine speed (NF) (NF/QF) rotor system frequency characteristic with a variable dominant rotor lag, a variable dc rotor gain, a variable resonance frequency, and a variable resonance peak magnitude, comprising: an inner closed loop control on NG, responsive to an NG reference signal, having a variable NG loop gain and a corresponding variable NG closed loop bandwidth being substantially a variable high order lag; said variable forward path NG gain being varied as a function of NG speed to cause said variable NG closed loop bandwidth to substantially match the variable lead of the QF/NG frequency characteristic; a double notch filter feedback compensator, disposed in a feedback path of said control system, responsive to the free turbine speed having a frequency response magnitude that attenuates substantially all of said resonance peak of said rotor system over the range of said variable resonance frequency; and a proportional-plus-integral (P+I) type NF forward path compensator, disposed in a forward path of said control system, having an integrator for providing said isochronous control of NF, having integral gain, and having a lead frequency, and providing a bias signal to said NG reference signal.

이 특허를 인용한 특허 (31) 인용/피인용 타임라인 분석

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Van Vactor, David R.; Noyes, Jr., Bertram S., Methods and systems to facilitate over-speed protection.
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Rucci, John; Stobiecki, Anthony Z.; Davis, Brent; Myers, Christopher James, Modules and methods for biasing power to a multi-engine power plant suitable for one engine inoperative flight procedure training.
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Kuras Brian D., Overspeed control system for a hydro-mechanical drive system.
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Karpman, Boris; Roadinger, Thomas J.; Meisner, Richard P., Robust flow parameter model for component-level dynamic turbine system control.
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[미국특허] Control system for gas turbine helicopter engines and the like 원문보기

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