Show/Hide Menu
Hide/Show Apps
Logout
Türkçe
Türkçe
Search
Search
Login
Login
OpenMETU
OpenMETU
About
About
Open Science Policy
Open Science Policy
Open Access Guideline
Open Access Guideline
Postgraduate Thesis Guideline
Postgraduate Thesis Guideline
Communities & Collections
Communities & Collections
Help
Help
Frequently Asked Questions
Frequently Asked Questions
Guides
Guides
Thesis submission
Thesis submission
MS without thesis term project submission
MS without thesis term project submission
Publication submission with DOI
Publication submission with DOI
Publication submission
Publication submission
Supporting Information
Supporting Information
General Information
General Information
Copyright, Embargo and License
Copyright, Embargo and License
Contact us
Contact us
Experimental investigation of the confinement effects in radial-radial swirlers
Date
2021-01-01
Author
Kiyici, Firat
Perçin, Mustafa
Metadata
Show full item record
This work is licensed under a
Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License
.
Item Usage Stats
176
views
0
downloads
Cite This
© 2021 American Society of Mechanical Engineers (ASME). All rights reserved.This experimental study investigates the effect of confinement ratio (CR) on the flow field of a counterrotating radial-radial swirler. Two-dimensional twocomponent (2D2C) particle image velocimetry (PIV) measurements are performed at the mid-plane of the jet. Four different confinement ratios (i.e., 10.4, 23.4, 41.6 and unconfined) are considered at a swirl number of 1.2. The results reveal the presence of a central toroidal recirculation zone (CTRZ) in all cases extending inside the jet which indicates the existence of an adverse pressure gradient. For the unconfined swirling jet, the recirculation zone is small in size and exists at the exit of the jet. For the CR=41.6 case, on the other hand, there exist two separate recirculation zones with the first one being similar to the unconfined case in terms of size and axial position, while the second one being larger in size and positioned at a more downstream location. Variation of the axial velocity along the centerline of the jet for this case indicates the presence of an adverse pressure gradient only in the close-jet region correlated with the first recirculation zone. For the smaller CR values, a single massive CTRZ emerges. This leads to increase in the expansion angle of the swirling jet as the CR decreases. Correspondingly, the radial velocity at the jet exit increases. For the confined cases with a single recirculation zone, the length and the width to cross-section ratio increase with the CR. On the other hand, the ratio of the reverse flow rate to total mass flow rate decreases with increasing CR values.
URI
https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=85115613856&origin=inward
https://hdl.handle.net/11511/98938
DOI
https://doi.org/10.1115/gt2021-58653
Conference Name
ASME Turbo Expo 2021: Turbomachinery Technical Conference and Exposition, GT 2021
Collections
Department of Aerospace Engineering, Conference / Seminar
Suggestions
OpenMETU
Core
Experimental design and statistical modeling methodology for wind tunnel aerodynamics of an agile missile to improve the simulation accuracy and performance
Savas, Ozgun; Topbas, Eren; Unal, Kenan; Karaca, H. Deniz; Kutay, Ali Türker (2018-01-01)
© 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.Wind tunnel testing is an essential procedure to investigate the aerodynamics forces and moments. In this paper, a methodology is presented to perform such test in an efficient way. Experimental design process is carried out before the testing in order to cover the flight regime as much as possible with the least possible number of tests. After the determination of the test matrix and conducting the wind-on tests, the ...
Computational modelling and analysis of porous bleed holes at supersonic speeds
Akar, Gökhan; Eyi, Sinan (2020-01-01)
© 2020, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.Shock Wave / Boundary Layer Interaction is an important issue that should be taken into account when studying inlet design. Bleed holes have traditionally been used to remove the lower momentum part of the boundary layer to avoid separation from adverse Shock Wave / Boundary Layer Interaction. In this study, modeling of porous bleed holes investigated in computational fluid dynamics on a flat plate with and without an ...
Multi-Fidelity Aerodynamic Dataset Generation of a Fighter Aircraft with a Deep Neural-Genetic Network
Millidere, Murat; Gomec, Fazil Selcuk; Kurt, Huseyin Burak; Akgül, Ferhat (2021-01-01)
© 2021, American Institute of Aeronautics and Astronautics Inc.. All rights reserved.This paper is a follow-up study on prior research work on multi-fidelity aerodynamic dataset generation. The prior work studied a comparison of modified Variable-Complexity Modelling and co-Kriging methods applied to F-16 fighter aircraft. In this research, the multi-fidelity deep neural-genetic network method is introduced. The results provide evidence that the deep neural-genetic network method in this paper can be employ...
Investigation of a Solution Approach to Quadratic Eigenvalue Problem for Thermoacoustic Instabilities
Öztürkmen, Musa Onur; Özyörük, Yusuf (2022-01-01)
© 2022, American Institute of Aeronautics and Astronautics Inc.. All rights reserved.The interactions between the unsteady heat release and pressure fluctuations in a combustion chamber may lead to thermoacoustic instabilities. Linear stability characteristics of the chamber may be determined by solving the nonhomogeneous wave equation in frequency domain that takes these interactions into account. The discretization of the wave equation with frequency-dependent source terms due to heat release and impedanc...
Numerical investigation of subsonic flow over a typical missile forebody
Tuncer, İsmail Hakkı; Platzer, Max F. (1996-01-01)
© 1996, American Institute of Aeronautics and Astronautics, Inc. All Rights Reserved.The NASA-Ames developed Navier-Stokes solver OVERFLOW and the panel code PMARC are applied to the computation of the flow over a typical missile forebody. The flowfields at low angles of attack from 0° to 14° are investigated. The surface pressures along the missile forebody predicted by OVERFLOW and PMARC agree well up to 10°. This favorable agreement suggests that the panel codes may be a computationally efficient tool fo...
Citation Formats
IEEE
ACM
APA
CHICAGO
MLA
BibTeX
F. Kiyici and M. Perçin, “Experimental investigation of the confinement effects in radial-radial swirlers,” Virtual, Online, 2021, vol. 3A-2021, Accessed: 00, 2022. [Online]. Available: https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=85115613856&origin=inward.