Papers Submitted to WSEAS Conferences and WSEAS Journals: Wseas Transactions

Thursday 24 February 2011

Wseas Transactions

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The following information was submitted:

Transactions: WSEAS TRANSACTIONS ON FLUID MECHANICS
Transactions ID Number: 53-238
Full Name: B DEEPANRAJ
Position: Student
Age: ON
Sex: Male
Address: 73 BHARATHIAR STREET, MARAPATTU VOLL, GIRISAMUDIRAM PO, VANIYAMBADI-635751, TAMILNADU
Country: INDIA
Tel:
Tel prefix:
Fax:
E-mail address: babudeepan@gmail.com
Other E-mails:
Title of the Paper: Theoretical Analysis of Gas Turbine Blades by Finite Element Method
Authors as they appear in the Paper: B.Deepanraj, G.Sankaranarayanan, C.Dhanesh, P.Lawrence
Email addresses of all the authors: babudeepan@gmail.com, gs2000narayanan@gmail.com, lawphd2008@gmail.com
Number of paper pages: 10
Abstract: Gas turbine is an important functional part of many applications. Cooling of blades has been a major concern since they are in a high temperature environment. Various techniques have been proposed for the cooling of blades and one such technique is to have axial holes along the blade span. Finite element analysis is used to analyze thermal and structural performance due to the loading condition, with material properties of Titanium- Aluminum Alloy. Six different models with different number of holes (7, 8, 9, 10, 11, 12) where analyzed in this paper to find out the optimum number of holes for good performance. In Finite element analysis, first thermal analysis followed by structural analysis is carried out. Graphs plotted for temperature distribution for existing design (12 holes) and for 8 holes against time. 2D and 3D model of the blade with cooling passages are shown. Using ANSYS, bending stress, deflection, temperature distribution for number of holes are anal!
yzed. Results have been discussed and we found that when the numbers of holes are increased in the blade, the temperature distribution falls down. For the blade configuration with 8 holes, the temperature near to the required value i.e., 800oC is obtained. Thus a turbine blade with 8 holes configuration is found to be the optimum solution.
Keywords: Titanium Aluminium Alloy, Gas turbine blade, Cooling, Stress distribution, Deflection, Temperature distribution.
EXTENSION of the file: .doc
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How Did you learn about congress: Gas turbine blades
IP ADDRESS: 124.124.216.69

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