Low rotor vibration avoidance in aircraft gas turbine engines

Details Low rotor vibration avoidance in aircraft gas turbine engines Low rotor vibration avoidance in aircraft gas turbine engines

1995-12-04

1997-11-18

Casaregola, Louis J.

Power plants

Reaction motor

Condition responsive thrust varying means

60242, F02K 115

Patent

active

056875649

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.

REFERENCES:
patent: 2873576 (1959-02-01), Lombard
patent: 2918790 (1959-12-01), Schoch
patent: 2955412 (1960-10-01), Rhodes
patent: 4159625 (1979-07-01), Kerr

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