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Impact of Periodic Unsteadiness on Performance and Heat Load in Axial Flow Turbomachines

Author
Dring, Robert P.
Published
Jan. 1997.
Physical Description
1 electronic document
Additional Creators
Blair, Michael F., Sharma, Om P., Greitzer, Edward M., Daniels, William A,, and Stetson, Gary M.
Online Version

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Summary
Results of an analytical and experimental investigation, directed at the understanding of the impact of periodic unsteadiness on the time-averaged flows in axial flow turbomachines, are presented. Analysis of available experimental data, from a large-scale rotating rig (LSRR) (low speed rig), shows that in the time-averaged axisymmetric equations the magnitude of the terms representing the effect of periodic unsteadiness (deterministic stresses) are as large or larger than those due to random unsteadiness (turbulence). Numerical experiments, conducted to highlight physical mechanisms associated with the migration of combustor generated hot-streaks in turbine rotors, indicated that the effect can be simulated by accounting for deterministic stress like terms in the time-averaged mass and energy conservation equations. The experimental portion of this program shows that the aerodynamic loss for the second stator in a 1-1/2 stage turbine are influenced by the axial spacing between the second stator leading edge and the rotor trailing edge. However, the axial spacing has little impact on the heat transfer coefficient. These performance changes are believed to be associated with the change in deterministic stress at the inlet to the second stator. Data were also acquired to quantify the impact of indexing the first stator relative to the second stator. For the range of parameters examined, this effect was found to be of the same order as the effect of axial spacing.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19970009625.
Accession ID: 97N15024.
E-10624.
FR-24232.
NASA-CR-202319.
NAS 1.26:202319.
Terms of Use and Reproduction
No Copyright.
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