Next Article in Journal
Active Boundary Layer Control on a Highly Loaded Turbine Exit Case Profile
Previous Article in Journal
Development and Implementation of a Technique for Fast Five-Hole Probe Measurements Downstream of a Linear Cascade
Article Menu
Issue 1 (March) cover image

Export Article

Open AccessArticle
Int. J. Turbomach. Propuls. Power 2018, 3(1), 7; https://doi.org/10.3390/ijtpp3010007

Full Annulus Simulations of a Transonic Axial Compressor Stage with Distorted Inflow at Transonic and Subsonic Blade Tip Speed

Institute of Jet Propulsion, Bundeswehr University Munich, Werner-Heisenberg-Weg 39, 85577 Neubiberg, Germany
This paper is an extended version of our paper published in Proceedings of the European Turbomachinery Conference ETC12 2017, Paper No. 211.
*
Author to whom correspondence should be addressed.
Received: 7 December 2017 / Revised: 2 February 2018 / Accepted: 6 February 2018 / Published: 14 February 2018
View Full-Text   |   Download PDF [13237 KB, uploaded 2 March 2018]   |  

Abstract

This article reports on systematic numerical studies on an axial compressor stage with distorted inflow. Four operating points at two speedlines were simulated with an inflow distortion generated by a 120 -sector segment with a wedge-type cross-section. With this setup, the interaction between the distorted inflow and the rotor flow was studied. The focus was put on the differences of the interaction between the distorted inflow and rotor flow as well as on the compressor behaviour at subsonic and transonic blade tip speeds, as the general mechanisms have been analysed in more detail in previous publications. The distorted flow itself is not influenced by the blade tip speed, but the interaction phenomena depend strongly on the spool speed and operating point. Additionally, the blade tip speed influences the circumferential sector of the compressor stage exit, which is affected by the distorted flow. The impact reaches from a small sector at 65% spool speed, with the peak efficiency operating point up to nearly the entire annulus at 100% spool speed, near the stall operating point. View Full-Text
Keywords: distorted inflow; axial compressor; transonic compressor; CFD; computational fluid dynamics distorted inflow; axial compressor; transonic compressor; CFD; computational fluid dynamics
Figures

Figure 1

This is an open access article distributed under the Creative Commons Attribution License which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited. (CC BY 4.0).
SciFeed

Share & Cite This Article

MDPI and ACS Style

Haug, J.P.; Niehuis, R. Full Annulus Simulations of a Transonic Axial Compressor Stage with Distorted Inflow at Transonic and Subsonic Blade Tip Speed. Int. J. Turbomach. Propuls. Power 2018, 3, 7.

Show more citation formats Show less citations formats

Note that from the first issue of 2016, MDPI journals use article numbers instead of page numbers. See further details here.

Article Metrics

Article Access Statistics

1

Comments

[Return to top]
Int. J. Turbomach. Propuls. Power EISSN 2504-186X Published by MDPI AG, Basel, Switzerland RSS E-Mail Table of Contents Alert
Back to Top