Realization of High Pressure Turbine Blades of a Small Turbo Fan Engine through Investment Casting Process

D. Chatterjee; A.S. Chauhan; Venkat .; D.P. Tigga; D.K Das

doi:10.14429/dsj.73.18719

D. Chatterjee DRDO-Defence Metallurgical Research Laboratory (DMRL), Kanchanbagh PO, Hyderabad - 500 058, India https://orcid.org/0000-0003-1162-4655
A.S. Chauhan DRDO-Defence Metallurgical Research Laboratory (DMRL), Kanchanbagh PO, Hyderabad - 500 058, India https://orcid.org/0000-0002-3039-5723
Venkat . DRDO-Defence Metallurgical Research Laboratory (DMRL), Kanchanbagh, Hyderabad - 500 058, India https://orcid.org/0000-0003-0545-9657
D.P. Tigga DRDO-Gas Turbine Research Establishment (GTRE), CV Raman Nagar, Bengaluru – 560 093, India https://orcid.org/0000-0002-8890-0091
D.K Das DRDO-Defence Metallurgical Research Laboratory (DMRL), Kanchanbagh, Hyderabad - 500 058, India https://orcid.org/0000-0002-6757-8830

DOI: https://doi.org/10.14429/dsj.73.18719

Keywords: Gas turbine blade, Superalloy, Investment casting, Microstructure, Mechanical property

Abstract

Turbo-fan gas turbine engines, or simply turbo-fan engines (STFEs), are used for powering both manned aircrafts and unmanned air vehicles (UAVs). The high pressure turbine section of such engines use Ni-base superalloy cast rotor blades because of their good mechanical properties at high operating temperatures. The present paper provides the technical/technological details of the various aspects associated with development and manufacturing of high pressure turbine blades (HPTBs) for utilization in an indigenously-developed small turbo-fan engine. Vacuum investment casting process has been adopted for realization of the above equiaxed components using a Ni-base superalloy