28 research outputs found

    Case Wall Pressures in a Multistage Axial Compressor with Tip Clearance Variation

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    The article of record as published may be found at http://dx.doi.org/10.2514/3.24129Presented as Paper 93-2389 at the AIAA/SAE/ASME/ASEE 29th Joint Propulsion Conference, Monterey, CA, June 28-30, 1993Large cyclical pressure excursions from stator-averaged values are observed on the suction side of a rotor blade at the case wall in a multistage compressor as the rotor moves relative to the stator. The pressure changes correlate well with stator relative position, occur in the passage away from the blade, and are only slightly modified by tip clearance changes. Close to the entry and exit of the tip gap, however, the pressures remain stable. The pressures near the gap are only slightly affected by stator proximity and primarily vary with tip gap height.Naval Air Systems CommandAir Breathing Propulsion Research Progra

    Stator Averaged, Rotor Blade-to-Blade near Wall Flow in a Multistage Axial Compressor with Tip Clearance Variation

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    Presented at the International Gas Turbine and Aeroengine Congress and Exposition Orlando, FL June 3-6, 1991This paper describes the effect of tip clearance changes on the pressure at the case wall of a second stage rotor. Wall shear distributions under the rotor tip are also presented. The results show low pressure areas extending along the rotor suction side but lying away from the blade. Pressure contours indicate the tangential loading at the tip is lower than predicted by two dimensional calculations, however, the predicted loading is observed between the lowest pressure’s path in the passage and the blade pressure side. The results suggest a viscous or shearing layer, due to blade-to-wall relative motion, is generated on the blade side of the tip gap which modifies the inviscid relative flow field and produces an unloading on the blade tip.Naval Air Systems Comman
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