Gas Turbine Combustor Exit Temperature Measurement
Abstract
A new gas temperature measurement technique is presented that has the capability to eliminate radiation errors typically observed in high-temperature environments. The technique should allow high measurement accuracy and high spatial resolution and can be implemented in rugged probe designs capable of surviving in a gas turbine combustor exit environment. The theoretical operation of the probe is described, and sources of measurement uncertainty are investigated. Probes fabricated for demonstration purposes are capable of surviving prolonged operation at temperatures up to 3,000 F. Tests were run in two facilities, the Astron High-Temperature Furnace and the NASA Lewis Combustor Rig, and results are presented in this report. The test results are favorable; however, further analysis should be performed and the method of qualifying probe accuracy should be defined. Currently the probe does not operate satisfactorily in a real-time mode, but algorithms developed for posttest data reduction should be suitable for implementation in a microprocessor-based controller allowing real-time operation.
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1991
- Accession Number
- ADA239936
Entities
People
- John D. Sullivan
- John E. Kendall