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Temperature Measurement for Advanced Gas Turbine Controls
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English
Abstract
Modern gas turbine engines with turbine inlet temperatures higher than metal melting temperatures must have control systems which provide subsecond response to changes in gas or metal temperatures. High quality data are required to provide for the most efficient engine operation consistent with engine safety.
Recently developed instruments measure individual blade temperature; another non-immersion gas temperature sensor, not yet fully developed, will provide accurate gas temperature data up to 1900°C. These instruments are described with present and potential uses in control systems.
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Authors
Citation
Rohy, D., Duffy, T., and Compton, W., "Temperature Measurement for Advanced Gas Turbine Controls," SAE Technical Paper 750206, 1975, https://doi.org/10.4271/750206.Also In
References
- Duffy T. E. Seegall M. I. McElmury S. S. Napier J. C. Compton W. A. “Research Analysis of Advanced Sensors for Turbine Inlet Gas Temperature,” U.S. Navy Contract N00019-69-C-0574 Naval Air Systems Command October 1970
- Rohy David A. Duffy T. E. Compton W. A. “Radiation Pyrometer for Gas Turbine Blades.” SAE Transactions 81 1972 paper 720159
- Rohy David A. Compton W. A. “Radiation Pyrometer for Gas Turbine Blades.” Final Report, U.S. Navy Contract N00019-71-C-0288 Naval Air Systems Command September 1972
- Van Roberts J. Rohy David A. “Gas Temperature-Density (GTD) Sensor for Turbine Inlet Gas Temperature Measurement,” Instrumentation for Air-breathing Propulsion MIT Press 1974
- Seegall M. I. Rohy D. A. Compton W. A. “Turbine Inlet Gas Temperature Sensor for Engine Control.” Final Report, U.S. Air Force ContractF33615-71-C-1510, Technical Report AFFDL-TR-73-49 Air Force Flight Dynamics Laboratory Wright-Patterson Air Force Base, Ohio February 1973