Establishment of aeropropulsion mach 3.6 test facility for high speed combustor research (AIAA 2013-2624)

Manjunath, P and Sathiyamoorthy, K and Venu, G and Venkat Iyengar, S and Jayaprakash, C and Srinivas, J and Prateesh Kumar, P (2013) Establishment of aeropropulsion mach 3.6 test facility for high speed combustor research (AIAA 2013-2624). In: AIAA Ground Testing Conference, 24-27 June 2013, San Diego, CA.

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Official URL: http://dx.doi.org/10.2514/6.2013-2624

Abstract

National Aerospace Laboratories has recently established the Aeropropulsion Mach 3.6 test facility for experimental research on 'High Speed Combustors'. This is a blow down type test facility and simulates the combustor inlet conditions of Mach number and Temperature corresponding to the flight Mach number of 6 and an altitude of 25 km. The details of the facility, it's operation and flow characteristics have been described in this paper. The salient features of the control system of the facility has also been discussed. The facility was commissioned and operationalized in March 2012 and the flow conditions obtained at the test section are Mach number 3.6, total temperature 1700 K, pressure 18 bar with 12 s of effective test duration. This facility can be used as a semi-freejet test facility for the experimental research on the high speed combustors.

Item Type: Conference or Workshop Item (Paper)
Uncontrolled Keywords: High speed combustors;Reference plane transfers;Flight mach number;Facility nozzle
Subjects: AERONAUTICS > Aeronautics (General)
AERONAUTICS > Aircraft Propulsion and Power
Depositing User: Ms. Alphones Mary
Date Deposited: 20 Jun 2014 08:25
Last Modified: 28 Aug 2015 10:16
URI: http://nal-ir.nal.res.in/id/eprint/11977

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