EMAIL: PASSWORD:
Front Office
UPT. PERPUSTAKAAN
Institut Teknologi Sepuluh Nopember Surabaya


Kampus ITS Sukolilo - Surabaya 60111

Phone : 031-5921733 , 5923623
Fax : 031-5937774
E-mail : libits@its.ac.id
Website : http://library.its.ac.id

Support (Customer Service) :
timit_perpus@its.ac.id








Welcome..guys!

Have a problem with your access?
Please, contact our technical support below:
LIVE SUPPORT


Taufik Rachmanu


Dewi Eka Agustina


Ansi Aflacha Putri


Tondo Indra Nyata


Aprillia Tri Wulansari


Moh. Fandika Aqsa




! ATTENTION !

To facilitate the activation process, please fill out the member application form correctly and completely
Registration activation of our members will process up to max 24 hours (confirm by email). Please wait patiently

Still Confuse?
Please read our User Guide

Keyword
Mode
Expanded Search (for Free text search only)
 
OR You May Search Our Knowledges Using Google Customize Search :

Custom Search

ITS » Undergraduate Theses » Teknik Mesin
Posted by setiawan04@its.ac.id at 31/12/2010 13:26:02  •  834 Views


PERANCANGAN SUDU KOMPRESOR AKSIAL PADA TURBIN GAS TIPE T-4702 (CENTAUR). STUDI KASUS DI ECHO FLOW STATION BP INDONESIA

DESIGN OF BLADE AXIAL FLOW COMPRESSOR IN GAS TURBINE TYPE T-4702 CASE STUDY IN ECHO FLOW STATION BP INDONESIA

Created by :
YOGANTARA, GEDE RIANA ( 2106100011 )



Subjectturbin
Alt. Subject Compressors
Keywordaxial flow compressor
gas turbine
blade
stage

Description:

Turbin gas tipe T-4702 (Centaur) di bp Indonesia digunakan sebagai penggerak kompresor sentrifugal untuk menghasilkan gas lift dalam proses produksi minyak bumi. Specific Gravity dari gas masukan kompresor sentrifugal mengalami penurunan sehingga mengakibatkan kondisi overspeed pada kompresor sentrifugal. Untuk mengatasi kondisi tersebut, dilakukan penurunan putaran turbin gas. Penurunan putaran turbin gas akan mengakibatkan penurunan efisiensi dari turbin gas. Impeller dari kompresor sentrifugal dan sudu gerak turbin gas telah dirancang ulang sesuai putaran di lapangan saat terjadi penurunan specific gravity. Hal ini akan mengakibatkan kompresor aliran aksial pada sistem turbin gas bekerja pada kondisi yang tidak maksimum. Perancangan sudu kompresor aliran aksial pada turbin gas tipe T-4702 diawali dengan mengetahui pengaruh operasi kerja kompresor sentrifugal terhadap kerja turbin gas. Selanjutnya ditentukan parameter perancangan pada kompresor aliran aksial. Setelah itu dilakukan perancangan sudu gerak kompresor aliran aksial pada setiap stage untuk mendapatkan kerja yang maksimum pada putaran yang dinginkan. Hasil perancangan sudu kompresor aksial ini menggunakan profil dasar airfoil NACA 65019. Profil ini dipilih karena memiliki nilai coefficient lift ≈ 1 dan efektif digunakan pada aliran fluida yang subsonik. Hasil perancangan yang lainnya adalah dimensi dari sudu. Tinggi sudu gerak pada stage 1 adalah 0.1183 m dan tinggi sudu diam pada stage 1 adalah 0.0961 m. Radius root pada sudu gerak stage 1 adalah 0.0788 m dan radius root pada sudu diam stage 1 adalah 0.0843 m.


Alt. Description

Gas turbine type T-4702 (Centaur) at bp Indonesia is used to drive a centrifugal compressor which is producing gas for lifting oil from the well. The decreasing specific gravity of gas properties at the centrifugal compressor inlet which is most likely to causes overspeed condition. To overcome that, it is needed to reduce the rotation speed of gas turbine but that condition will gave occasion to lower the efficiency at gas turbine. The Impeller of centrifugal compressor and rotor blade of gas turbine have been redesign according the decrease of specific gravity at actual condition. As a consequence, the work of axial flow compressor at gas turbine is not going to reach the maximum condition. The design of blade axial flow compressor at gas turbine type T-4702 is started with finding out how the changing work operation of centrifugal compressor would effecton gas turbine’s work. Then, determine the axial flow compressor design parameter. Afterwards, continue with designing blade axial flow compressor at each stage to get the maximum work at wanted rotation This design result shown that the blade is used NACA 65019 base profile. This base profile is selected because it is effective in subsonic flow and approximation value of lift oefficient is 1. The other design result are dimention of blade which is 0.1183 m in span for rotor and 0.0961 m in span for stator for the first stage. Then the root radius of rotor is 0.0788 m and the tip radius of stator is 0.0843 m.This radii are only for the first stage of compressor. With this dimention, the compressor has maximum efficiency in 14871 rotation per minute.

Contributor:
  1. Prof. Dr. Ir I Made Arya Djoni, MSc
Date Create:04/08/2010
Type:Text
Format:pdf
Language:Indonesian
Identifier:ITS-Undergraduate-3100010041033
Collection ID:3100010041033
Call Number:RSM 621.51 Yog p


Source :
Undergraduate Thesis, Mechanical Engineering, RSM 620.106 4 Irl s, 2010

Coverage :
ITS Community

Rights :
Copyright @2010 by ITS Library. This publication is protected by copyright and per obtained from the ITS Library prior to any prohibited reproduction, storage in a re transmission in any form or by any means, electronic, mechanical, photocopying, reco For information regarding permission(s), write to ITS Library


Publication URL :
http://digilib.its.ac.id/perancangan-sudu-kompresor-aksial-pada-turbin-gas-tipe-t4702-centaur-studi-kasus-di-echo-flow-station-bp-indonesia-13253.html




[ Free Download - Free for All ]

  1.  ITS-Undergraduate-13253-perancangan-sudu-kompresor-aksial-pada-turbin-gas-tipe-t-4702-centaur-studi-kasus-di-echo-flow-stati.pdf - 61 KB
  2.  ITS-Undergraduate-13253-design-of-blade-axial-flow-compressor-in-gas-turbine-type-t-4702-case-study-in-echo-flow-stationbp-i.pdf - 61 KB
  3.  ITS-Undergraduate-13253-Approval_Sheet.pdf - 140 KB
  4.  ITS-Undergraduate-13253-Abstract_id.pdf - 173 KB
  5.  ITS-Undergraduate-13253-Abstract_en.pdf - 155 KB
  6.  ITS-Undergraduate-13253-Preface.pdf - 124 KB
  7.  ITS-Undergraduate-13253-Table_of_Content.pdf - 187 KB
  8.  ITS-Undergraduate-13253-Tables.pdf - 122 KB
  9.  ITS-Undergraduate-13253-Illustrations.pdf - 125 KB
  10.  ITS-Undergraduate-13253-Simbols.pdf - 204 KB
  11.  ITS-Undergraduate-13253-Bibliography.pdf - 172 KB
  12.  ITS-Undergraduate-13253-Biography.pdf - 50 KB
  13.  ITS-Undergraduate-13253-Chapter1.pdf - 573 KB
  14.  ITS-Undergraduate-13253-Conclusion.pdf - 254 KB
  15.  ITS-Undergraduate-13253-Presentation.pdf - 1475 KB

[ FullText Content - Please, register first ]

  1. ITS-Undergraduate-13253-Chapter2.pdf - 642 KB
  2. ITS-Undergraduate-13253-Chapter3.pdf - 587 KB
  3. ITS-Undergraduate-13253-Chapter4.pdf - 1068 KB
  4. ITS-Undergraduate-13253-Enclosure.pdf - 565 KB



Give your Comment here...


 10 Similar Document...



 10 Related Document...






HELP US !
You can help us to define the exact keyword for this document by clicking the link below :

axial , axial flow compressor , blade , compressor , flow , gas , gas turbine , stage , turbine



POLLING

Bagaimana pendapat Anda tentang layanan repository kami ?

Bagus Sekali
Baik
Biasa
Jelek
Mengecewakan




49214804


Visitors Today : 1
Total Visitor : 2515709

Hits Today : 4347
Total Hits : 49214804

Visitors Online: 1


Calculated since
16 May 2012

You are connected from 10.199.13.5
using CCBot/2.0 (http://commoncrawl.org/faq/)


ITS Digital Repository Feeds



Copyright © ITS Library 2006 - 2014 - All rights reserved.
Dublin Core Metadata Initiative and OpenArchives Compatible
Developed by Hassan