Engine control system

Fluid reaction surfaces (i.e. – impellers) – With control means responsive to non-cyclic condition... – Impeller rotation speed responsive

Reexamination Certificate

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C060S791000, C060S039281

Reexamination Certificate

active

06986641

ABSTRACT:
A power turbine speed control system for a helicopter is disclosed which includes components for generating a power turbine speed signal based upon a demanded rotor speed, a high-order filter for filtering the power turbine speed signal by effectuating a rapid attenuation of main and tail rotor torsional frequencies in the power turbine speed signal without compromising phase at low frequencies, and a governor for providing isochronous power turbine speed and rotor speed control based upon the filtered power turbine speed signal.

REFERENCES:
patent: 4411595 (1983-10-01), Pisano
patent: 4423593 (1984-01-01), Zagranski et al.
patent: 4453378 (1984-06-01), Zagranski et al.
patent: 4466526 (1984-08-01), Howlett et al.
patent: 4493465 (1985-01-01), Howlett et al.
patent: 4531361 (1985-07-01), Zagranski et al.
patent: 4648797 (1987-03-01), Martin
patent: 5051918 (1991-09-01), Parsons
patent: 5189620 (1993-02-01), Parsons et al.
European Search Report dated Sept. 29, 2003.
Morrison, T., Howlett, J.J., Zagranski, R.D., “Adaptive Fuel Control Feasibility Investigation for Helicopter Applications,” 27thASME International Gas Turbine Conference and Exhibit, 1982, XP008021720, p. 3, col. 1, p. 4, col. 2; figure 3.
Wong, T.H., “Designing and Stimulating the Engine Speed Governor for Helicopter Applications,” ASME International Gas Turbine and Aeroengine Congress and Exposition, Jun. 5-8, 1995, XP0080211719.

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