TY - GEN
T1 - A computational conjugate thermal analysis of HP stage turbine blade cooling with innovative cooling passage geometries
AU - Kini, Chandrakant R.
AU - Satish, Shenoy B.
AU - Sharma, N. Yagnesh
PY - 2011/11/14
Y1 - 2011/11/14
N2 - In most of the practical gas turbines, the turbine blades of HP stage are usually too small to employ the turbine blade cooling techniques effectively. The growing need for effective blade cooling techniques is a direct consequence of the continuous quest for greater fuel economy. It is very well known that the thermal efficiency and power output of gas turbines increase with increasing turbine entry temperature (TET). The current TET level in advanced gas turbines is far above the melting point of the blade material. Therefore, along with high temperature material development, a sophisticated cooling scheme must be developed for continuous safe operation of gas turbines for high performance. An attempt has been made in this paper to computationally analyze the coupled conjugate analysis of HP stage turbine blade for effective cooling using innovative cooling passages within the blade. An helicoidal shaped duct has been analyzed corresponding to different diameters and pitch length. It is found from the analysis that helicoidal cooling duct with larger diameter and with lower pitch length provides a vastly improved blade cooling in comparison to straight ducted cooling ducts for the HP stage turbine blade.
AB - In most of the practical gas turbines, the turbine blades of HP stage are usually too small to employ the turbine blade cooling techniques effectively. The growing need for effective blade cooling techniques is a direct consequence of the continuous quest for greater fuel economy. It is very well known that the thermal efficiency and power output of gas turbines increase with increasing turbine entry temperature (TET). The current TET level in advanced gas turbines is far above the melting point of the blade material. Therefore, along with high temperature material development, a sophisticated cooling scheme must be developed for continuous safe operation of gas turbines for high performance. An attempt has been made in this paper to computationally analyze the coupled conjugate analysis of HP stage turbine blade for effective cooling using innovative cooling passages within the blade. An helicoidal shaped duct has been analyzed corresponding to different diameters and pitch length. It is found from the analysis that helicoidal cooling duct with larger diameter and with lower pitch length provides a vastly improved blade cooling in comparison to straight ducted cooling ducts for the HP stage turbine blade.
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M3 - Conference contribution
AN - SCOPUS:80755184837
SN - 9789881925152
T3 - Proceedings of the World Congress on Engineering 2011, WCE 2011
SP - 2168
EP - 2173
BT - Proceedings of the World Congress on Engineering 2011, WCE 2011
T2 - World Congress on Engineering 2011, WCE 2011
Y2 - 6 July 2011 through 8 July 2011
ER -