Non-uniform temperature distributions in aircraft turbine and compressor discs result in high thermal stresses, particularly during engine transients. This has an important role in limiting disc life and subsequently engine time on wing between overhauls. Typically, and in the absence of specific engine real-time information, disc life is computed and declared at the design stage, for the whole fleet assuming worst case scenarios and flight profiles. This approach potentially leads to conserv...

This paper describes the design and development of a major new facility capable of reproducing flow conditions for large civil aero engine turbine and compressor segment cavities. The facility reproduces in 3-D, typical secondary air system cruise temperatures, pressures and mass flows. The facility allows better understanding of the circumferential heat transfer effects of air system flows on turbine and compressor casings, as these have a significant influence on both steady-state and trans...

This paper presents a novel approach to modelling disc temperature distributions for use in health monitoring applications. The method combines singular value decomposition techniques with a series of low order transfer functions to predict the thermal response over a typical flight cycle. The model inputs reflect typical online measurements; engine speed, altitude, and compressor exit temperature. The model’s complexity has been reduced by projection and truncation of the reference data and ...