Probes developed for use in an active tip clearance control system are described. Closed loop active control of high pressure turbine tip clearance is achieved over a simulated flight cycle using the outputs from optical triangulation probes. These probes are not to be used in actual operation. They serve as an accurate reference against which to judge other sensors which are being investigated.
Optical Sensors and Signal Processing Schemes for Use on Gas Turbine Engines
1988
10 pages
Report
No indication
English
Jet & Gas Turbine Engines , Optics & Lasers , Laboratory & Test Facility Design & Operation , Engine monitoring instruments , Gas turbine engines , Optical measuring instruments , Clearances , Triangulation , Blade tips , Feedback control , Tolerances (Mechanics) , Turbine blades , Foreign technology
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