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ITS » Master Theses » Rekayasa Konversi Energi - S2 Posted by aprill@is.its.ac.id at 29/09/2015 21:31:11 • 1972 Views
STUDY OF FLOW 3D SEPARATION CHARACTERISATION IN ENDWALL BODY AIRFOIL ASYMMETRY BRITISH 9C722.5C50 BY THE ADDITION OF FORWARD FACING STEP TURBULATOR FFST
Author : JANNAH, IKA NUR ( 2112 202 007 )
ABSTRAK
Fenomena separasi aliran 3D merupakan bentuk kerugian aliran yang tidak
bisa dihindari pada kompresor aksial. Terjadinya separasi aliran 3D pada
kompresor aksial akibat adanya interaksi antara lapisan batas sudu blade boundary layer dengan lapisan batas casing atau lapisan batas hub casing-hub boundary layer yang terletak pada bidang tumpu. Separasi aliran ini menyebabkan terjadinya penyumbatan aliran blockage effect dan menurunkan tekanan pada kompresor. Horlock dan Lakshminarayana menyebutkan kerugian akibat aliran 3D menyumbang sebesar 50 dari total kerugian hidrolis pada kompresor aksial sementara kerugian energi akibat gesekan pada dinding annulus
dan separasi 2D pada profile sebesar 30 dan 20. Dengan demikian salah satu
usaha untuk meningkatkan efisiensi dari kompresor aksial dapat dilakukan dengan
cara mengurangi kerugian akibat separasi aliran 3D. Penelitian ini dilakukan secara eksperimen dan numerik untuk mengkaji aliran melintasi pada bidang tumpu airfoil asimetri British 9C722.5C50 akibat penambahan forward facing step turbulator FFST dan tanpa FFST dengan variasi angle of attack 00 80 120 140 dan 160. Eksperimen dilakukan untuk menganalisa OFV yang terjadi pada bidang tumpu airfoil asimetri akibat penambahan FFST dan tanpa FFST pada wind tunnel dengan Reynolds number 1.64 x 105. Simulasi numerik menggunakan software Fluent 6.3.26 dengan model viscous standart k-epsilon. Hasil penelitian memperlihatkan bahwa dengan penambahan FFST dapat meningkatkan intensitas turbulent di daerah dekat dinding attachment line tidak terinduksi oleh horseshoe vortex sehingga aliran lebih mampu mengikuti kontur bodi akibatnya curling flow lebih lemah dan wake lebih sempit serta blockage energy loss dapat di reduksi. Reduksi energy loss yang paling efektif pada angle
of attack 80 sebesar 736 .
ABSTRACT
3D flow separation phenomenon is a form of flow loss that can not be avoided in axial compressors. The occurrence of 3D flow separation on axial compressor due to the interaction between blade boundary layer with the hubcasing
boundary layer which is located on endwall. This flow separation caused blockage effect and reduce pressure on the compressor. Horlock and Lakshminarayana mention of losses from the 3D flow donating 50 from total losses in the hydraulic axial compressor while the energy losses caused by friction on annulus and the 2D separation in profile by
30 and 20. Thus one of efforts to improve the efficiency from axial compressor can be accomplished by reducing losses due to 3D flow separation. This study was performed experimentally and numerically to study
the flow characteristics endwall body airfoil asymmetry british 9C722.5C50 by
the addition of forward facing step turbulator FFST dan without FFST with
variation angle of attack 00 80 120 140 and 160. Experiments carried out to
analyze the OFV that occurs at endwall body airfoil asymmetry with Reynolds
number 1.64 x 105. Numerical simulation using FLUENT 6.3.26 with models viscous
of standard k-epsilon. The results showed that the addition of FFST can increase the turbulent intensity in the region near wall attachment line is
not induced by the horseshoe vortex so flow better able to follow the contours of the body. Consequently curling flow is weaker and wake more narrow and blockage energy loss can be reduction. Reduction of energy loss is
most effective on angle of attack 80 at 7.36.
Source Mater Theses of Mechanical Engineering, RTM 621.43 Mah k, 2015
Coverage ITS Community
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