Design of an axial flow research compressor operating in the subsonic and transonic ranges

Mohan, K (1986) Design of an axial flow research compressor operating in the subsonic and transonic ranges. Technical Report. National Aeronautical Laboratory, Bangalore, India.

[img] PDF
Restricted to Repository staff only

Download (631kB)


A high speed axial flow research compressor, which has been indigenously designed and fabricated has been installed and commissioned. This Compressor, which is fully operational, is meant for undertaking investigations on models of axial13; flow compressor stages in the subsonic, transonic and supersonic flow ranges. The compressor rotor is 450 mm in diameter and the maximum possible operating speed is 18,000 r.p.m. Investigations on compressor stages of widely varying geometric configurations can be undertaken with provision to vary different aerodynamic flow parameters, as and when required. Thus most of the aerothermodynamic investigations related to the advanced technology compressors required for modern aircraft engines and industrial gas turbine power plants can be undertaken in this versatile research compressor.13; The general description of the compressor and its various components along with their design are presented. The performance capabilities and operational characteristics of this research compressor, which has been satisfactorily13; running since its commissioning, are presented.

Item Type: Monograph (Technical Report)
Uncontrolled Keywords: Axial flow;Design analysis;Research facilities;Subsonic flow;Supersonic compressors;Transonic compressors; Turbocompressors;Aerodynamic loads;Aerothermodynamics; Aircraft engines;Compressor rotors;Gas turbines;High speed
Subjects: AERONAUTICS > Aircraft Propulsion and Power
Depositing User: Users 64 not found.
Date Deposited: 09 Nov 2006
Last Modified: 24 May 2010 04:23

Actions (login required)

View Item View Item