Miller, RJ and Moss, RW and Ainsworth, RW and Harvey, NW (2002) Wake, shock and potential field interactions in a 1.5 stage turbine: Part II: Vane-vane interaction and discussion of results. American Society of Mechanical Engineers, International Gas Turbine Institute, Turbo Expo (Publication) IGTI, 5 B. pp. 725-734.Full text not available from this repository.
The composition of the time-resolved surface pressure field around a high-pressure rotor blade caused by the presence of neighboring blade rows was studied, with the individual effects of wake, shock and potential field interaction being determined. Two test geometries were considered: first, a high-pressure turbine stage coupled with a swan-necked diffuser exit duct; secondly, the same high-pressure stage but with a vane located in the downstream duct. Both tests were carried out at engine-representative Mach and Reynolds numbers. By comparing the results to time-resolved computational predictions of the flowfield, the accuracy with which the computation predicts blade interaction was determined. Evidence was obtained that for a large downstream vane, the flow conditions in the rotor passage, at any instant in time, are close to being steady state.
|Divisions:||Div A > Turbomachinery|
|Depositing User:||Cron Job|
|Date Deposited:||09 Dec 2016 17:19|
|Last Modified:||10 Dec 2016 00:54|