Numerical simulation of internal cooling effect of gas turbine blades using v shaped ribs

Kamat, Harishkumar and Kamath, Raghavendra C (2017) Numerical simulation of internal cooling effect of gas turbine blades using v shaped ribs. In: 3rd International Conference on Mechanical and Aeronautical Engineering, 18/01/2017, Bangkok, Thailand.

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Abstract

Thermal efficiency and power output of gas turbines increase with increasing turbine rotor inlet temperatures. The rotor inlet temperatures in most of the gas turbines are far higher than the melting point of the blade material hence, the turbine blades need to be cooled. The leading edge of the turbine is internally cooled by coolant passages having V-shaped ribs of rib angles of 300, 450 and 600 for each aspect ratio of 1:1, 1:2 and 2:3. Numerical analysis is carried out for each configuration and results are compared. The conclusions made were as follows: [1] the passage with V-shaped ribs with aspect ratio of 2:3 with 450 rib angle provides the best cooling in the leading edge [2] Temperature of the blade is reduced by approx. 30 % i.e. from 1561 K to approx.1100 K at the leading edge and approx. 17% at the trailing edge of the gas turbine blade

Item Type: Conference or Workshop Item (Paper)
Uncontrolled Keywords: Turbine blade cooling; ribs; leading edge; trailing edge
Subjects: Engineering > MIT Manipal > Mechanical and Manufacturing
Depositing User: MIT Library
Date Deposited: 29 Mar 2017 04:07
Last Modified: 29 Mar 2017 04:07
URI: http://eprints.manipal.edu/id/eprint/148600

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