ALAN D PISANO
Engineering in Chelsea, MA
License number
Massachusetts 28105
Expiration Date
Jun 30, 1990
Type
Electronic Engineer
Address
Address
Chelsea, MA 02150
Professional information
Control System For Gas Turbine Engine
US Patent:
4411595, Oct 25, 1983
Filed:
Feb 9, 1981
Appl. No.:
6/232925
Inventors:
Alan D. Pisano - Chelsea MA
Assignee:
General Electric Company - Cincinnati OH
International Classification:
F02C 310
US Classification:
416 1
Abstract:
A gas turbine engine control system is provided. In a preferred control system for use in combination with a helicopter, input signals respectively representative of power turbine speed error, power turbine shaft torque, and compressor shaft speed are employed. From these input signals, five intermediate signals are developed. One of the intermediate signals represents the main rotor speed error. Each of the five intermediate signals is provided with a separate predetermined gain and coupled to summation means. The predetermined gains are selected to be of values which reduce the effects of resonances provided by the main and tail rotors of the helicopter. The output of the summation means represents a control signal and may be employed to operate a fuel control valve.
Control System For Gas Turbine Engine
US Patent:
4276744, Jul 7, 1981
Filed:
Sep 19, 1979
Appl. No.:
6/076890
Inventors:
Alan D. Pisano - Chelsea MA
Assignee:
General Electric Company - Cincinnati OH
International Classification:
F02C 310, F02C 928
US Classification:
60 3916R
Abstract:
A gas turbine engine control system is provided. In a preferred control system for use in combination with a helicopter, input signals respectively representative of power turbine speed error, power turbine shaft torque, and compressor shaft speed are employed. From these input signals, five intermediate signals are developed. One of the intermediate signals represents the main rotor speed error. Each of the five intermediate signals is provided with a separate predetermined gain and coupled to summation means. The predetermined gains are selected to be of values which reduce the effects of resonances provided by the mail and tail rotors of the helicopter. The output of the summation means represents a control signal and may be employed to operate a fuel control valve.
Isochronous Gas Turbine Speed Control
US Patent:
4672806, Jun 16, 1987
Filed:
Apr 11, 1985
Appl. No.:
6/722035
Inventors:
Alan D. Pisano - Chelsea MA
Assignee:
General Electric Company - Cincinnati OH
International Classification:
F02C 928
US Classification:
60 3903
Abstract:
An invention is disclosed in which a signal indicating a rate of fuel flow desired for a gas turbine engine is bounded between limits imposed by maximal- and minimal-fuel rates allowed under the current operating conditions of the engine and between limits imposed by maximal- and minimal-accelerations allowed under the same operating conditions. The fuel rate limits are constantly modified by feedback information about the actual acceleration experienced by the engine. This feedback information about acceleration is obtained without directly measuring acceleration itself.
Isochronous Gas Turbine Speed Control
US Patent:
4532763, Aug 6, 1985
Filed:
Jan 28, 1983
Appl. No.:
6/461774
Inventors:
Alan D. Pisano - Chelsea MA
Assignee:
General Electric Company - Cincinnati OH
International Classification:
F02C 928
US Classification:
60 39281
Abstract:
An invention is disclosed in which a signal indicating a rate of fuel flow desired for a gas turbine engine is bounded between limits imposed by maximal- and minimal-fuel rates allowed under the current operating conditions of the engine and between limits imposed by maximal- and minimal-accelerations allowed under the same operating conditions. The fuel rate limits are constantly modified by feedback information about the actual acceleration experienced by the engine. This feedback information about acceleration is obtained without directly measuring acceleration itself.