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research-article

Uncertainty Quantification of Leakages in a Multistage Simulation and Comparison with Experiments

[+] Author and Article Information
Cosimo Mazzoni

ASME Membership, Osney Thermo-fluids Laboratory, Department of Engineering Science, Oxford University, Southwell building, Osney Mead, Oxford, OX2 0DP, United Kingdom
cosimo.maria.mazzoni@gmail.com

Richard Ahlfeld

Department of Aeronautics, Imperial College of London, South Kensington Campus, London, SW7 2AZ, United Kingdom
ahlfeld.richard@googlemail.com

Budimir Rosic

ASME Membership, Osney Thermo-fluids Laboratory, Department of Engineering Science, Oxford University, Southwell building, Osney Mead, Oxford, OX2 0DP, United Kingdom
budimir.rosic@eng.ox.ac.uk

Francesco Montomoli

Department of Aeronautics, Imperial College of London, South Kensington Campus, London, SW7 2AZ, United Kingdom
f.montomoli@imperial.ac.uk

1Corresponding author.

ASME doi:10.1115/1.4037983 History: Received August 28, 2016; Revised August 25, 2017

Abstract

The present paper presents a numerical study of the impact of tip gap uncertainties in a multistage turbine. It is well known that the rotor gap can change the gas turbine efficiency but the impact of the random variation of the clearance height has not been investigated before. In this paper the radial seals clearance of a datum shroud geometry, representative of steam turbine industrial practice, was systematically varied and numerically tested by means of unsteady CFD. By using a Non-Intrusive Uncertainty Quantification simulation based on a Sparse Arbitrary Moment Based Approach, it is possible to predict the radial distribution of uncertainty in stagnation pressure and yaw angle at the exit of the turbine blades. This work shows that the impact of gap uncertainties propagates radially from the tip towards the hub of the turbine and the complete span is affected by a variation of the rotor tip gap. This amplification of the uncertainty is mainly due to the low aspect ratio of the turbine and a similar behavior is expected in high pressure turbines.

Copyright (c) 2017 by ASME
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