ePrints@IIScePrints@IISc Home | About | Browse | Latest Additions | Advanced Search | Contact | Help

Single stage axial compressor stability management with self-recirculating casing treatment

Kumar, SS and Chotalia, RJ and Jana, ST and Ganguli, R and Kandagal, SB (2019) Single stage axial compressor stability management with self-recirculating casing treatment. In: AIAA Scitech 2019 Forum, 7-11 January 2019, San Diego, California.

[img] PDF
AIAA_SCITECH_2019.pdf - Published Version
Restricted to Registered users only

Download (1MB) | Request a copy
Official URL: https://dx.doi.org/10.2514/6.2019-0942


A discrete self-recirculating casing treatment (RCT) with converging nozzle and Coanda jet is designed and introduced in a high speed transonic axial compressor stage. Numerical parametric studies for various injection skew/yaw angles are carried out to quantify the effect on the performance parameters such as stall margin improvement, total-to-total pressure ratio, and stage isentropic efficiency. All the investigated cases yield sufficient stall margin improvements with no loss in pressure ratio and compressor efficiency compared to the solid casing. Stall margin improvement is higher at lower speeds. Detailed flow investigation of the role played by the jet injection at the compressor endwall region is highlighted. Flow diagnostics is carried out numerically for various flow parameters such as Mach number, static pressure, and total pressure variations. The low momentum fluid that usually builds and occupies the adjacent blade passage at near stall condition is delayed further downstream due to the injection of the high-velocity jet. © 2019, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

Item Type: Conference Paper
Publication: AIAA Scitech 2019 Forum
Publisher: American Institute of Aeronautics and Astronautics Inc, AIAA
Additional Information: cited By 0; Conference of AIAA Scitech Forum, 2019 ; Conference Date: 7 January 2019 Through 11 January 2019; Conference Code:225819
Keywords: Aviation; Axial flow turbomachinery; Efficiency, Compressor efficiency; Flow investigations; Isentropic efficiency; Near stall conditions; Numerical parametric studies; Performance parameters; Total pressure ratio; Transonic axial compressors, Axial-flow compressors
Department/Centre: Division of Mechanical Sciences > Aerospace Engineering(Formerly Aeronautical Engineering)
Date Deposited: 07 Oct 2020 09:50
Last Modified: 07 Oct 2020 09:50
URI: http://eprints.iisc.ac.in/id/eprint/65396

Actions (login required)

View Item View Item