Laboratory and flight technique for the measurement of the temperature of turbine blading

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DOI	Resolve DOI: https://doi.org/10.4224/40003679
Author	Search for: Cockshutt, E. P.¹; Search for: Levy, G. G.¹; Search for: Sharp, C. R.¹
Affiliation	National Research Council Canada. National Aeronautical Establishment
Format	Text, Technical Report
Physical description	32 p.
Abstract	The evolution of a flight-worthy instrumentation system for measuring turbine rotor blade temperatures in an Orenda 14 turbojet engine is described. The system comprises sheathed chromel-alumel thermocouples installed in drilled turbine blades and used in conjunction with mercury sliprings mounted in the exhaust bullet of the engine. The instrumentation has been used to measure under sea level static conditions the turbine blade cooling produced by the pre-turbine injection of reheat fuel. An instrumented engine is currently being flown in a Sabre 6 aircraft to obtain similar data at altitude.
Publication date	1958-08-27
Publisher	National Research Council Canada
Series	Laboratory Report (National Research Council Canada. National Aeronautical Establishment. Engine Laboratory), no. LR-229 (27 August 1958).
Language	English
Peer reviewed	No
NRC number	NRCC-0005823 NRC-5823
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Record identifier	43e81011-987e-4c49-b8b5-fea5632bc907
Record created	2025-09-03
Record modified	2025-11-03