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
Open AccessArticle

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
*
Author to whom correspondence should be addressed.
This paper is an extended version of our paper published in Proceedings of the European Turbomachinery Conference ETC12 2017, Paper No. 211.
Int. J. Turbomach. Propuls. Power 2018, 3(1), 7; https://doi.org/10.3390/ijtpp3010007
Received: 7 December 2017 / Revised: 2 February 2018 / Accepted: 6 February 2018 / Published: 14 February 2018
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
Show Figures

Figure 1

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 Access Map by Country/Region

1
Back to TopTop