Component Drawings for Compact By-Pass Engine

Abstract

Future military applications of small Gas Turbine Engine will require compact,lightweight engines delivering high specific thrust with low specific fuel consumption.It is also required that these engines should run over a wide operating range of Flight Mach Number and Altitudes. As a first phase of the project a design optimization study has been carried out a t Propulsion Division, National Aerospace Laboratories,Bangalore under sponsored project "Optimization of Compact by-pass engine - Preliminary Design" for the indigenous development engine for unmanned aerial vehicle by DRDO.The work has been extended as a second phase to generate preliminary component drawings for optimized engine cycle.For this the aerodynamic parameters and overall dimensions for the components were generated for the optimized engine cycle.From the generated aerodynamic parameters preliminary assembly,sub assembly and component drawings were prepared using AUTO CAD.This report describes the work done in the second phase of the project