GERALD BRACCI
Engineering in Jupiter, FL
License number
Massachusetts 24356
Issued Date
May 21, 1971
Expiration Date
Jun 30, 2018
Type
Mechanical Engineer
Address
Address
Jupiter, FL 33469
Professional information
Low Rotor Vibration Avoidance In Aircraft Gas Turbine Engines
US Patent:
5687564, Nov 18, 1997
Filed:
Dec 4, 1995
Appl. No.:
8/566846
Inventors:
James B. Kelly - Lake Worth FL
Kenneth D. Olson - Royal Palm Beach FL
Johnny B. Davis - Jupiter FL
Gerald Bracci - Tequesta FL
Kenneth D. Olson - Royal Palm Beach FL
Johnny B. Davis - Jupiter FL
Gerald Bracci - Tequesta FL
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F02K 115
US Classification:
60235
Abstract:
Corrected fan speed (N1C2) and engine pressure ratio (EPR) are controlled, by controlling exhaust nozzle area (EA) according to a schedule or map so that as altitude increases (P2 decreases) the axial forces on the low rotor are sufficient to minimize low rotor vibrations. The altitude band (critical load region) is determined that produces loading levels in which vibrations appear. As this band is approached, conventional control of N1C2 and EPR is automatically over-ridden. N1C2 is decreased with altitude and exhaust area is reduced, thereby increasing the axial force (load) on the low rotor. When the upper limit of the band is reached, conventional control of N1C2 and EPR is automatically resumed, resulting in crossing the critical load region rapidly over a narrow altitude band.
Constant Thrust Retention Turbine Temperature Limit System
US Patent:
5142860, Sep 1, 1992
Filed:
Jun 18, 1990
Appl. No.:
7/539940
Inventors:
Mark A. Strange - Florissant MO
Walter A. Ledwith - Palm Beach Gardens FL
Johnny B. Davis - Jupiter FL
Stephen N. Finger - Jupiter FL
Gerald Bracci - Tequesta FL
Walter A. Ledwith - Palm Beach Gardens FL
Johnny B. Davis - Jupiter FL
Stephen N. Finger - Jupiter FL
Gerald Bracci - Tequesta FL
Assignee:
United Technologies Corporation - Hartford CT
International Classification:
F02C 928
US Classification:
60 39281
Abstract:
A control system for controlling the margin of temperature between the turbine's operating temperature and temperature limit throughout the engine operating range is manifested by utilizing a trim logic schedule that provides a constant margin value for each operating condition of the gas turbine engine. The system allows the engine to achieve the requisite performance while maintaining durability requirements.