Author ORCID Identifier

https://orcid.org/0000-0002-0297-4461 : Jeffrey J. Defoe

Document Type

Article

Publication Date

6-18-2018

Publication Title

Journal of Turbomachinery

Volume

140

Issue

7

First Page

071009

Keywords

Computational fluid dynamics, Fan, Fluid dynamics, Compressor, Turbine aerodynamic design, Heat transfer phenomena, Turbine components, Gas turbine engines

Last Page

071020

Abstract

Applications such as boundary-layer-ingesting fans, and compressors in turboprop engines require continuous operation with distorted inflow. A low-speed axial fan with incompressible flow is studied in this paper. The objectives are to (1) identify the physical mechanisms which govern the fan response to inflow distortions and (2) determine how fan performance scales as the type and severity of inlet distortion varies at the design flow coefficient. A distributed source term approach to modeling the rotor and stator blade rows is used in numerical simulations in this paper. The model does not include viscous losses so that changes in diffusion factor are the primary focus. Distortions in stagnation pressure and temperature as well as swirl are considered. The key findings are that unless sharp pitchwise gradients in the diffusion response, strong radial flows, or very large distortion magnitudes are present, the response of the blade rows for strong distortions can be predicted by scaling up the response to a weaker distortion. In addition, the response to distortions which are composed of non-uniformities in several inlet quantities can be predicted by summing up the responses to the constituent distortions.

DOI

https://doi.org/10.1115/1.4039433

ISSN

0889-504X

E-ISSN

1528-8900

Creative Commons License

Creative Commons Attribution 4.0 International License
This work is licensed under a Creative Commons Attribution 4.0 International License.

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