초록 ▼

The present invention relates to a system for detecting aerodynamic instabilities in a jet turbine engine having a pressure transducer mounted in the engine. The pressure transducer, welded to a circuit in signal communication with a controller, is adapted to send measured pressure readings from air

The present invention relates to a system for detecting aerodynamic instabilities in a jet turbine engine having a pressure transducer mounted in the engine. The pressure transducer, welded to a circuit in signal communication with a controller, is adapted to send measured pressure readings from air in a combustion chamber to the controller. The controller, located in spaced apart relation from the engine, is adapted by software to detect pressure patterns from the pressure signals generated by the transducer that are indicative of a stall or surge. A series of fuel and air valves located with compression and combustion chambers of the engine are in signal communication with the controller. The controller in response to detecting pressure signals indicating a stall or surge is operative to signals in the valves to change the air flow, air angle, fuel flow or speed to reduce the possibility of a stall or surge.

대표청구항 ▼

What is claimed is: 1. A method for accurately predicting aerodynamic instabilities in turbo-jet engines having at least one compression chamber comprising the steps of: placing a plurality of pressure transducers about a circumferential wall of the at least one compression chamber; initially formi

What is claimed is: 1. A method for accurately predicting aerodynamic instabilities in turbo-jet engines having at least one compression chamber comprising the steps of: placing a plurality of pressure transducers about a circumferential wall of the at least one compression chamber; initially forming said pressure transducers by fusion bonding an insulating layer of a carrier wafer to a wafer having piezoresistive regions to create a high temperature transducer; said placing step further including positioning each of said pressure transducers about the circumference to collectively measure aerodynamic excitation frequencies; measuring pressure fluctuations in said at least one compression chamber; and associating measured pressure fluctuations with aerodynamic excitation frequencies associated with a aerodynamic instability. 2. The method of claim 1 wherein said bonding step is diffusion enhanced fusion bonding. 3. The method of claim 1 wherein said initial forming step includes forming a resistance bridge circuit on said piezoresistive wafer. 4. The method of claim 1 wherein said associating step includes processing said measured fluctuations using Fourier transforms. 5. The method of claim 1 wherein said initial forming step includes forming said insulating layer by oxidizing a surface of said carrier wafer. 6. The method of claim 1 wherein said at least one compression chamber includes intermediate and high compression chambers and said placing step includes placing said transducers about the circumference of said intermediate compression chamber. 7. The method of claim 1 wherein said at least one compression chamber includes intermediate and high compression chambers and said placing step includes placing said transducers about the circumference of said high compression chamber. 8. The method of claim 1 wherein said initial forming steps includes incorporating a vibration compensator into said pressure transducer. 9. The method of claim 1 used in a compensation process for a turbo-fan engine further including a combustion chamber and actuators to adjust air flow in said at least one compression chamber and fuel flow in said combustion chamber, said method further including the steps of: providing a processor in signal communication with said pressure transducers and said actuators, wherein said processor receives said measured pressure fluctuation signals and performs said associating step; and upon associating a measured pressure fluctuation with an aerodynamic instability, signaling said actuators from said processor to adjust engine operation to minimize the occurrence of said aerodynamic instability. 10. The method of claim 9 wherein said processor providing step includes locating said processor remotely from said engine. 11. The method of claim 9 wherein said aerodynamic instability is rotating stall. 12. The method of claim 9 wherein said aerodynamic instability is surge.