Stall Inception in Low-Pressure Ratio Fans

Journal of Turbomachinery - Tập 141 Số 7 - 2019
Seunghwan Kim1, Graham Pullan2, Cesare A. Hall1, Robert P. Grewe1, Mark Wilson3, E. J. Gunn4
1Whittle Laboratory, University of Cambridge, 1 JJ Thomson Avenue, Cambridge, CB3 0DY, UK
2Whittle Laboratory, University of Cambridge, 1 JJ Thomson Avenue, Cambridge CB3 0DY, UK e-mail:
3Rolls-Royce plc, Moor Lane, Derby, DE21 8BJ, UK
4Turbostream Ltd, 3 Charles Babbage Road, Cambridge, CB3 0GT, UK

Tóm tắt

A combined experimental and computational test program, with two low-pressure ratio aero-engine fans, has been used to identify the flow mechanisms at stall inception and the subsequent stall cell growth. The two fans have the same rotor tip clearance, annulus design, and downstream stators, but different levels of tip loading. The measurement data show that both the fans stall via spike-type inception, but that the growth of the stall cell and the final cell size is different in each fan. The computations, reproducing both the qualitative and quantitative behavior of the steady-state and transient measurements, are used to identify the flow mechanisms at the origin of stall inception. In one fan, spillage of tip leakage flow upstream of the leading edge plane is responsible. In the other, sudden growth of casing corner separation blockage leads to stall. These two mechanisms are in accord with the findings from core compressors. However, the transonic aerodynamics and the low hub-to-tip radius ratio of the fans lead to the following two findings: first, the casing corner separation is driven by shock-boundary layer interaction and second, the spanwise loading distribution of the fan determines whether the spike develops into full-span or part-span stall and both types of behavior are represented in the present work. Finally, the axial momentum flux of the tip clearance flow is shown to be a useful indicator of the leakage jet spillage mechanism. A simple model is provided that links the tip loading, stagger, and solidity with the tip clearance axial momentum flux, thereby allowing the aerodynamicist to connect, qualitatively, design parameters with the stall behavior of the fan.

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Journal of Turbomachinery

Tập 141 Số 7

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