CFD Analysis for Cooling of Gas Turbine Rotor Blade Cooling through Staggered Holes
Author(s):
Umesh Patel, Animesh Singhai
Keywords:
Computational fluid dynamics (CFD), staggered holes, Heat transfer rate, CAD, Turbulent-Intensity model.
Abstract
Gas turbines are the prime mover in critical industries such as power generation; processing plant and aircraft propulsion. Gas turbine inlet temperature have been increasing over the years due to positive economics of higher efficiency and higher firing temperatures. The turbine blade is the limiting component the gas turbines. Modern gas turbines operate at very high temperatures (1200-1500°C) for increasing power output, thermal efficiency and performance of the turbines. But material melting temperature of the turbine blades may exceed the limiting factor. Hence proper cooling system is used for the cooling of turbine blades for there long life. Blades of gas turbine can be cooled either internally or externally. Since the Cooling of blades of turbine is a major exposition for continuous and safe operation of gas turbines with the high performance. There are several methods for the cooling of blades. The examination of heat transfer analysis are done they with 14 , 15 and 16 staggered holes For the analysis uses CFD - ANSYS FLUENT. On evaluation the contour plot of the pressure, velocity and velocity vector; results that the temperature’s distributions on the 16 staggered holes, is uniformly distributed along the blade area, as compared to 14 and 15 staggered . Average blade temperature reduces by 3.98% when no. of staggered holes varied from 14 to 16. Heat transfer rate increases by 14.96 % when no. of staggered holes varied from 14 to 16.
Article Details
Unique Paper ID: 146797

Publication Volume & Issue: Volume 5, Issue 1

Page(s): 924 - 929
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