Aerodynamic Studies in the Static Components of a Centrifugal Compressor Stage

Aerodynamic Studies in the Static Components of a Centrifugal Compressor Stage

Aerodynamic studies in the static components of a centrifugal compressor stage were conducted using the computational fluid dynamics solver FLUENT. For the simulation study, a typical centrifugal compressor stage geometry with a flow coefficient of 0.053 was chosen, The study is confined to the stat...

Full description

Bibliographic Details
Main Authors: Reddy, K. Srinivasa, Murty, G.V. Ramana, Sharma, Korada Viswanatha
Format: Article
Language:English
Published: Faculty Mechanical Engineering, UMP 2011
Subjects:
TJ Mechanical engineering and machinery
Online Access:http://umpir.ump.edu.my/id/eprint/13799/
http://umpir.ump.edu.my/id/eprint/13799/
http://umpir.ump.edu.my/id/eprint/13799/
http://umpir.ump.edu.my/id/eprint/13799/1/Aerodynamic%20Studies%20In%20The%20Static%20Components%20of%20A%20Centrifugal%20Compressor%20Stage.pdf
id ump-13799
recordtype eprints
spelling ump-137992016-12-28T01:53:30Z http://umpir.ump.edu.my/id/eprint/13799/ Aerodynamic Studies in the Static Components of a Centrifugal Compressor Stage Reddy, K. Srinivasa Murty, G.V. Ramana Sharma, Korada Viswanatha TJ Mechanical engineering and machinery Aerodynamic studies in the static components of a centrifugal compressor stage were conducted using the computational fluid dynamics solver FLUENT. For the simulation study, a typical centrifugal compressor stage geometry with a flow coefficient of 0.053 was chosen, The study is confined to the static components of the centrifugal compressor stage, i.e., the crossover bend (180° U-bend), a radial cascade of return channel vanes, and the exit ducting (90° L-turn). The aerodynamic performance is reported in terms of total pressure loss coefficient, static pressure recovery coefficient, return channel vane surface static pressure distribution, and stage exit swirl angle distribution. The simulated flow through the static components covered five different operating conditions of the actual centrifugal compressor stage: the design point with 100% flow rate, and the off-design operating conditions with 70%, 80%, 110%, and 120% flow rates. The standard k-ε model was used with standard wall functions to predict the turbulence. A minimum total pressure loss coefficient was observed near 80% flow rate when the average flow angle at the U-bend inlet was 24°. Better static pressure recovery was observed with 70%, 80%, and 100% flow rates. The swirl angle distribution at the stage exit was recognized as satisfactory. Faculty Mechanical Engineering, UMP 2011 Article PeerReviewed application/pdf en http://umpir.ump.edu.my/id/eprint/13799/1/Aerodynamic%20Studies%20In%20The%20Static%20Components%20of%20A%20Centrifugal%20Compressor%20Stage.pdf Reddy, K. Srinivasa and Murty, G.V. Ramana and Sharma, Korada Viswanatha (2011) Aerodynamic Studies in the Static Components of a Centrifugal Compressor Stage. Journal of Mechanical Engineering and Sciences (JMES) , 1. pp. 75-86. ISSN 2289-4659 (print); 2231-8380 (online) http://dx.doi.org/10.15282/jmes.1.2011.7.0007 DOI: 10.15282/jmes.1.2011.7.0007
repository_type Digital Repository
institution_category Local University
institution Universiti Malaysia Pahang
building UMP Institutional Repository
collection Online Access
language English
topic TJ Mechanical engineering and machinery
spellingShingle TJ Mechanical engineering and machinery
Reddy, K. Srinivasa
Murty, G.V. Ramana
Sharma, Korada Viswanatha
Aerodynamic Studies in the Static Components of a Centrifugal Compressor Stage
description Aerodynamic studies in the static components of a centrifugal compressor stage were conducted using the computational fluid dynamics solver FLUENT. For the simulation study, a typical centrifugal compressor stage geometry with a flow coefficient of 0.053 was chosen, The study is confined to the static components of the centrifugal compressor stage, i.e., the crossover bend (180° U-bend), a radial cascade of return channel vanes, and the exit ducting (90° L-turn). The aerodynamic performance is reported in terms of total pressure loss coefficient, static pressure recovery coefficient, return channel vane surface static pressure distribution, and stage exit swirl angle distribution. The simulated flow through the static components covered five different operating conditions of the actual centrifugal compressor stage: the design point with 100% flow rate, and the off-design operating conditions with 70%, 80%, 110%, and 120% flow rates. The standard k-ε model was used with standard wall functions to predict the turbulence. A minimum total pressure loss coefficient was observed near 80% flow rate when the average flow angle at the U-bend inlet was 24°. Better static pressure recovery was observed with 70%, 80%, and 100% flow rates. The swirl angle distribution at the stage exit was recognized as satisfactory.
format Article
author Reddy, K. Srinivasa
Murty, G.V. Ramana
Sharma, Korada Viswanatha
author_facet Reddy, K. Srinivasa
Murty, G.V. Ramana
Sharma, Korada Viswanatha
author_sort Reddy, K. Srinivasa
title Aerodynamic Studies in the Static Components of a Centrifugal Compressor Stage
title_short Aerodynamic Studies in the Static Components of a Centrifugal Compressor Stage
title_full Aerodynamic Studies in the Static Components of a Centrifugal Compressor Stage
title_fullStr Aerodynamic Studies in the Static Components of a Centrifugal Compressor Stage
title_full_unstemmed Aerodynamic Studies in the Static Components of a Centrifugal Compressor Stage
title_sort aerodynamic studies in the static components of a centrifugal compressor stage
publisher Faculty Mechanical Engineering, UMP
publishDate 2011
url http://umpir.ump.edu.my/id/eprint/13799/
http://umpir.ump.edu.my/id/eprint/13799/
http://umpir.ump.edu.my/id/eprint/13799/
http://umpir.ump.edu.my/id/eprint/13799/1/Aerodynamic%20Studies%20In%20The%20Static%20Components%20of%20A%20Centrifugal%20Compressor%20Stage.pdf
first_indexed 2023-09-18T22:16:49Z
last_indexed 2023-09-18T22:16:49Z
_version_ 1777415392625426432

Similar Items