CUED Publications database

Effect of vortex ingestion on transonic fan stability

Page, JH and Tucker, PG and Hield, P (2016) Effect of vortex ingestion on transonic fan stability. In: UNSPECIFIED.

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Abstract

© 2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All Rights Reserved. Inlet flow distortion can comprise complex flow patterns and significantly affect transonic fan rotor stability. In order to be able to design effcient rotor stabilization technologies it is important to understand which features of distorted flow are most important in stall margin reduction. In this paper, unsteady CFD was used to investigate the effect of vortical inlet distortion on stall margin. Steady wingtip vortices were introduced to a one-third annulus transonic rotor geometry. Using a choked nozzle downstream to control the position on the characteristic, the stall points were calculated for an array of vortex configurations. The spanwise vortex injection position was tested at 25%, 50% and 75% span. Three different vortex core radii, 5%, 10% and 20%, were then tested. Finally the maximum local tangential velocity of the vortex was doubled from 50m/s to 100m/s in a flow with a mass averaged axial inlet velocity of 160m/s. The results showed that in these cases, inlet vortical distortion alone caused no significant change in stall margin and could also result in small increases. The suggestion is that vortical inlet distortion should be given appropriately moderated priority when considering the design of rotor stabilizing technology.

Item Type: Conference or Workshop Item (UNSPECIFIED)
Subjects: UNSPECIFIED
Divisions: Div A > Fluid Mechanics
Depositing User: Cron Job
Date Deposited: 17 Jul 2017 19:18
Last Modified: 10 Aug 2017 01:38
DOI: