Publications

Three-Dimensional Unsteady Hydrodynamic Modelling of Tidal Turbines

Authors:

Smyth, A., and Young, A.

Publication:

In proceedings from the 13th European Wave and Tidal Energy Conference, Napoli, Italy

DOI:

https://doi.org/10.17863/CAM.40077

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Predicting the Operability of Damaged Compressors Using Machine Learning

Authors:

Taylor, J., Conduit, B., Dickens, A., Hall, C., Hillel, M., & Miller, R.

Publication:

ASME Turbo Expo 2019

DOI:

https://doi.org/10.17863/CAM.38691

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The Effect of Non-Equilibrium Boundary Layers on Compressor Performance

The paper investigates the effect of non-equilibrium behaviour of boundary layers on the profile loss of a compressor. The investigation is undertaken using both direct numerical simulation (DNS) of a mid-height section of a compressor blade and a reduced order model, MISES. The solutions are validated using experimental measurements made in the embedded stage of a multistage low speed compressor. The paper shows that up to 35% of the suction surface boundary layer of the compressor blade exhibits non-equilibrium behaviour. The size of this region reduces as the Reynolds number is increased. The non-equilibrium behaviour was found to reduce profile loss in most cases, however, in a range of cases where transition occurs through a small separation the presence of non-equilibrium behaviour was found to increase profile loss.

Authors:

Andrew P. S. Wheeler, Anthony M. J. Dickens, Robert J. Miller

Publication:

Journal of Turbomachinery

DOI:

10.1115/1.4040094

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Angular response of hot wire probes

Authors:

L. di Mare, T. O. Jelly and I. J. Day

Publication:

Measurement Science and Technology

DOI:

10.1088/1361-6501/aa5014

A one-dimensional model for tidal array design based on three-scale dynamics

Authors:

Gupta, V. and Young, A. M.

Publication:

Journal of Fluid Mechanics

DOI:

https://doi.org/10.1017/jfm.2017.399

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The Effect of Rotor Casing on Low-Pressure Steam Turbine and Diffuser Interactions

The present study aims to investigate the interaction between a last-stage steam turbine blade row and diffuser. This work is carried out using computational fluid dynamics (CFD) simulations of a generic last-stage low-pressure (LP) turbine and axial–radial exhaust diffuser attached to it. In order to determine the validity of the computational method, the CFD predictions are first compared with data obtained from an experimental test facility. A computational study is then performed for different design configurations of the diffuser and rotor casing shapes. The study focuses on typical flow features such as effects of rotor tip leakage flows and subsequent changes in the rotor–diffuser interactions. The results suggest that the rotor casing shape influences the rotor work extraction capability and yields significant improvements in the diffuser static pressure recovery.

Authors:

Gursharanjit Singh, Andrew P. S. Wheeler and Gurnam Singh

Publication:

Journal of Engineering for Gas Turbines and Power

DOI:

10.1115/1.4034417

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Phase-averaged flow statistics in compressors using a rotated hot-wire technique

Authors:

T. O. Jelly, I. J. Day and L. di Mare

Publication:

Experiments in Fluids

DOI:

10.1007%2Fs00348-017-2326-x

Clocking in low-pressure turbines

Authors:

Evans, K.R. and Longley, J.P.

Publication:

Journal of Turbomachinery

DOI:

10.1115/1.4036341

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Hierarchical Immersed Boundary Method with Smeared Geometry

This paper presents a low-order model applying the immersed boundary method on smeared geometry. It is thus able to represent the effect of turbomachinery within a complex system. Assessment of this model on the NASA rotor 67 has been made under clean flow conditions. Good agreement has been achieved between the immersed boundary method on smeared geometry model, experiments, and a high-fidelity computational fluids dynamics model. For high-speed conditions, about within 0.5, 1, and 1% agreements are achieved on the pressure ratio, efficiency, and choking flow, respectively, between immersed the boundary method on smeared geometry model and the experiment. The capability of the model capturing the fan’s behavior under inlet distortion has also been assessed under the flow with a level of 10% distortion of the total pressure, which covers a 120 deg sector. The nonuniform work input of the fan, which is one of the key features of the fan–distortion interaction, has been captured by the i

Authors:

Teng Cao, Paul Hield and Paul G. Tucker

Publication:

AIAA Journal of Propulsion and Power

DOI:

https://doi.org/10.2514/1.B36190

Accounting for Eccentricity in Compressor Design

Authors:

Young, A. M., Cao, T., Day, I. and Longley, J.

Publication:

ASME Journal of Turbomachinery

DOI:

10.1115/1.4036201

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