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contributor authorR. J. Miller
contributor authorR. W. Moss
contributor authorR. W. Ainsworth
contributor authorN. W. Harvey
date accessioned2017-05-09T00:11:45Z
date available2017-05-09T00:11:45Z
date copyrightJanuary, 2003
date issued2003
identifier issn0889-504X
identifier otherJOTUEI-28700#33_1.pdf
identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/129288
description abstractThe composition of the time-resolved surface pressure field around a high-pressure rotor blade caused by the presence of neighboring blade rows is investigated, with the individual effects of wake, shock and potential field interaction being determined. Two test geometries are 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 conducted at engine-representative Mach and Reynolds numbers, and experimental data was acquired using fast-response pressure transducers mounted on the mid-height streamline of the HP rotor blades. The results are compared to time-resolved computational predictions of the flowfield in order to aid interpretation of experimental results and to determine the accuracy with which the computation predicts blade interaction. The paper is split into two parts: the first investigating the effect of the upstream vane on the unsteady pressure field around the rotor (vane-rotor interaction), and the second investigating the effect of the downstream vane on the unsteady pressure field around the rotor (rotor-vane interaction). The paper shows that at typical design operating conditions shock interaction from the upstream blade row is an order of magnitude greater than wake interaction and that with the design vane-rotor inter-blade gap the presence of the rotor causes a periodic increase in the strength of the vane trailing edge shock. The presence of the potential field of the downstream vane is found to affect significantly the rotor pressure field downstream of the Mach one surface within each rotor passage.
publisherThe American Society of Mechanical Engineers (ASME)
titleWake, Shock, and Potential Field Interactions in a 1.5 Stage Turbine—Part I: Vane-Rotor and Rotor-Vane Interaction
typeJournal Paper
journal volume125
journal issue1
journal titleJournal of Turbomachinery
identifier doi10.1115/1.1508386
journal fristpage33
journal lastpage39
identifier eissn1528-8900
keywordsPressure
keywordsWakes
keywordsShock (Mechanics)
keywordsRotors
keywordsBlades AND Turbines
treeJournal of Turbomachinery:;2003:;volume( 125 ):;issue: 001
contenttypeFulltext


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