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

Hysteresis and Bistability in Transversely Excited Swirling Flows

Gupta, R and Gohiya, R and Vempati, C and Hemchandra, S and Panda, P (2023) Hysteresis and Bistability in Transversely Excited Swirling Flows. In: Journal of Engineering for Gas Turbines and Power, 145 (1).

[img] PDF
jou_gas_tur_145-1_2023.pdf - Published Version
Restricted to Registered users only

Download (6MB) | Request a copy
Official URL: https://doi.org/10.1115/1.4055669


We investigate the effect of transverse acoustic excitation on nonreacting swirling jets. The work is motivated by the azimuthal instabilities in annular gas turbine combustor which are one of the major challenges in aero-engines. We have designed and fabricated a multinozzle linear array combustor to simulate the flow conditions of an annular combustor. The nozzle features a dual corotating radial swirler configuration. Two compression drivers placed on either side of the combustion chamber are used to generate acoustic fields in the direction transverse to the flow. Simultaneous two-dimensional (2D) particle image velocimetry (PIV) and high-frequency pressure measurements are conducted to measure the time-averaged velocity field and the chamber acoustics, respectively. It is observed that once the swirling jet is excited with a transverse acoustic forcing, it instantaneously transitions to a wall-jet state. In wall-jet state, the flow moves radially outwards and remains attached to the walls on either side of the nozzle, and is characterized by a recirculation zone with a strong negative axial velocity. In our experiments, we demonstrate that transverse acoustic excitation can lead to a bistable state in swirling flows. We investigated the acoustic response to low-amplitude forcing on the combustion chamber by performing a forced acoustic response analysis using COMSOL. It is observed that acoustic forcing leads to a peak response of the radial and azimuthal velocities at the flare of the swirler, which could induce an axisymmetric deflection of the jet shear layer pushing it into a wall-jet state. Copyright © 2023 by ASME.

Item Type: Journal Article
Publication: Journal of Engineering for Gas Turbines and Power
Publisher: American Society of Mechanical Engineers (ASME)
Additional Information: The copyright for this article belongs to American Society of Mechanical Engineers (ASME).
Keywords: Acoustic fields; Aircraft engines; Combustion chambers; Combustors; Excited states; Jets; Shear flow; Swirling flow; Velocity measurement, Acoustic excitation; Acoustic forcing; Aero-engine; Azimuthal instability; Bi-stability; Flow condition; Gas turbine combustor; Linear-array; Swirling jets; Wall jet, Nozzles
Department/Centre: Division of Mechanical Sciences > Aerospace Engineering(Formerly Aeronautical Engineering)
Date Deposited: 17 Jan 2023 04:09
Last Modified: 17 Jan 2023 04:09
URI: https://eprints.iisc.ac.in/id/eprint/79180

Actions (login required)

View Item View Item