Patent ID: 6871487

Claim:
A turbo-jet engine with active compensation for aerodynamic instabilities comprising: a compressor having at least one compression section, a combustion chamber adapted to receive air from said at least one compression section and a turbine section coupled to said combustion chamber to receive said pressurized and heated air; a plurality of pressure transducers placed about a peripheral wall of said at least one compression section; said pressure transducers each having a wafer having piezoresistive regions fusion bonded to an insulating layer of a carrier wafer, said carrier wafer being etched to form a diaphragm and each of said pressure transducers being placed about the circumference to collectively measure aerodynamic excitation frequencies; a plurality of actuators adapted to adjust air flow in said at least one compression section and fuel flow in said combustion chamber; a processor located remotely from said engine and in signal communication with said actuators and said pressure transducers and adapted by software having routines to: measure pressure fluctuations in said at least one compression section; associate measured pressure fluctuations with aerodynamic excitation frequencies associated with an aerodynamic instability; and upon associating a measured pressure fluctuation with an aerodynamic instability, signal said actuators to adjust engine operation to minimize the occurrence of said aerodynamic instability; wherein said processor controls said actuators to compensate for said aerodynamic instabilities.