TY - GEN
T1 - An experimental study of passage-to-passage flow interactions in a single stage axial flow research turbine rotor
AU - Andichamy, Veerandra C.
AU - Camci, Cengiz
AU - Kim, Yong W.
N1 - Funding Information:
Funding for this research from Solar Turbines, Inc. is gratefully acknowledged. In particular, we thank Mr. David Voss from Solar Turbines, Inc. for assisting us with financial support. The experimental research greatly benefited from the early contributions of Drs. J. Town, B. Gumusel, N. Rao and D. Dey especially for the measurement systems, data acquisition setup, and data reduction procedures. Many thanks to Mr. G. Khokhar for his help in automating the data post-processing system. The authors of this paper also acknowledge Mr. Benjamin Enders and Mr. K. Heller for their help in overcoming technical difficulties. Mr. H. Houtz and Mr. N. Doroschenko's support for the development and implementation of the DTP probe is acknowledged.
Publisher Copyright:
Copyright © 2019 ASME and Solar Turbines Incorporated.
PY - 2019
Y1 - 2019
N2 - During the lifetime of a turbine stage, some of the blade tips may undergo changes due to mechanical rubbing with casing surface and also due to thermal oxidation. Understanding the effect these damaged blades have over the undamaged blades is essential to estimate the performance of the turbine stage in the operable tip clearance range. In this paper, the passage to passage aerodynamic interaction in a turbine stage is studied by modifying the tip gap of selected turbine blades and analyzing their effect on the neighboring blade passage flows. The experiments in this study are carried out in a single-stage low-speed axial turbine facility. All measurements are taken in the stationary frame of reference using a time-accurate differential dynamic pressure transducer mounted in a Kiel probe head. The experimental results from this study show that even with a significant increase on a selected blade's tip clearance, its effect on the AFTRF turbine flow is only confined to its neighboring blade passage. The disturbances due to the altered tip clearance of one passage are not measurably propagated to its neighboring turbine passages. The changes made in one of the blades in a turbine stage do not significantly alter the aerodynamic performance of other blades. This result is particularly important for large-scale turbine research rigs such as AFTRF where the unsteady total pressure field is mapped in a time-efficient and phase-locked manner.
AB - During the lifetime of a turbine stage, some of the blade tips may undergo changes due to mechanical rubbing with casing surface and also due to thermal oxidation. Understanding the effect these damaged blades have over the undamaged blades is essential to estimate the performance of the turbine stage in the operable tip clearance range. In this paper, the passage to passage aerodynamic interaction in a turbine stage is studied by modifying the tip gap of selected turbine blades and analyzing their effect on the neighboring blade passage flows. The experiments in this study are carried out in a single-stage low-speed axial turbine facility. All measurements are taken in the stationary frame of reference using a time-accurate differential dynamic pressure transducer mounted in a Kiel probe head. The experimental results from this study show that even with a significant increase on a selected blade's tip clearance, its effect on the AFTRF turbine flow is only confined to its neighboring blade passage. The disturbances due to the altered tip clearance of one passage are not measurably propagated to its neighboring turbine passages. The changes made in one of the blades in a turbine stage do not significantly alter the aerodynamic performance of other blades. This result is particularly important for large-scale turbine research rigs such as AFTRF where the unsteady total pressure field is mapped in a time-efficient and phase-locked manner.
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U2 - 10.1115/GT2019-91629
DO - 10.1115/GT2019-91629
M3 - Conference contribution
AN - SCOPUS:85075575354
T3 - Proceedings of the ASME Turbo Expo
BT - Turbomachinery
PB - American Society of Mechanical Engineers (ASME)
T2 - ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition, GT 2019
Y2 - 17 June 2019 through 21 June 2019
ER -