High speed axial flow compressor research facility

Mohan, K and Nagpurwala, QH and Girigoswami, H and Guruprasad, SA (1981) High speed axial flow compressor research facility. Technical Report. National Aeronautical Laboratory, Bangalore, India.

[img] PDF
tm_pr_un_o_103_1__1981_p._38.pdf
Restricted to Repository staff only

Download (1MB)

Abstract

In any turbojet or ,gas turbine, engine, compressor is the most important and The Success of an engine depends very much on the smooth and efficient operation of the compressor. design and development of these compressors are essentially based on model single storage performance under simulated conditions.In order to generate the design data and to undertake various investigations in axial flow compressors, a versatile research facility has been established and successfully commissioned in the propulsion division of the National Aeronautical Laboratory the main units of this facility are the high speed research compressor the 1150 k.W. D.C. motor (variable spped drive unit along with auxilary units, and sophisticated controls and instrumentation. This research facility is only one of its kind in Indir .

Item Type: Monograph (Technical Report)
Uncontrolled Keywords: Gas turbine engine;Turbojet;Propulsion division
Subjects: AERONAUTICS > Aircraft Propulsion and Power
Depositing User: Users 90 not found.
Date Deposited: 30 Nov 2006
Last Modified: 11 Aug 2015 06:30
URI: http://nal-ir.nal.res.in/id/eprint/3554

Actions (login required)

View Item View Item