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
Restricted to Repository staff only

Download (1MB)
[img] Indexer Terms (Generate index codes conversion from application/pdf to indexcodes)
Restricted to Repository staff only

Download (2kB)


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: M/S ICAST NAL
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