Astigmatic Turbine Blade Tip Clearance Sensor For Gas Turbine Aero Engines

I. Davinson

doi:10.1117/12.943486

1 June 1988 Astigmatic Turbine Blade Tip Clearance Sensor For Gas Turbine Aero Engines

I. Davinson

Proceedings Volume 0863, Industrial Optoelectronic Measurement Systems Using Coherent Light; (1988) https://doi.org/10.1117/12.943486
Event: 1987 Symposium on the Technologies for Optoelectronics, 1987, Cannes, France

Abstract

The efficiency of gas turbine engines is strongly affected by the clearance between the rotating compressor or turbine blades and the stationary annulus around them. The most critical area is the high pressure turbine which, unfortunately, is the area where it is most difficult to make measurements, as the turbine blades run at temperatures in the region of 1000°C with hot gases containing unburnt fuel, soot etc., flowing over them at high pressure and speeds approaching sonic. The current trend is towards unshrouded blades, the efficiency of which is more strongly affected by tip clearance as the absence of the shroud creates overtip leakage (figure 1).

Citation Download Citation

I. Davinson "Astigmatic Turbine Blade Tip Clearance Sensor For Gas Turbine Aero Engines", Proc. SPIE 0863, Industrial Optoelectronic Measurement Systems Using Coherent Light, (1 June 1988); https://doi.org/10.1117/12.943486

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