Development of combustion driven heating system for semi-free jet test rig
IR@NAL: CSIR-National Aerospace Laboratories, Bangalore
View Archive Info| Field | Value | |
| Title |
Development of combustion driven heating system for semi-free jet test rig
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| Creator |
Sathiyamoorthy, K
Venu, G Jayaprakash, C Srinivas, J Prateesh Kumar, P Manjunath, P |
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| Subject |
Research and Support Facilities (Air)
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| Description |
National Aerospace Laboratories, CSIR has recently established the Aero-propulsion Mach 3.6 Tunnel for the experimental research on 'High Speed Combustors. It is a blow down type test facility and simulates the scramjet inlet conditions of Mach number and temperature corresponding to the flight Mach number of 6 and altitude of 25 km. The flow conditions obtained at the test section are – Mach number 3.6, total temperature 1700 K, pressure 18 bar, mass flow rates of 25 kg/s with 10 seconds of test duration. The combustion driven heating method with upstream injection of replenishment oxygen has been adapted. The heating system consists of two combustors namely Pre-Heater -01 and Pre-Heater -02. Pre-heater -01 is an aero engine ‘can type’ combustor which heats air from 300 K to 800 K. The liners and fuel injectors from time expired R-11 aero engine were modified to suit to the requirements. Pre-Heater-02 is an ‘afterburner type’ combustion chamber developed for the facility, which heats the air from 800 K to 1700 K. This paper discusses about the development of the pre-heaters and its performances
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| Date |
2013
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| Type |
Conference or Workshop Item
PeerReviewed |
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| Format |
application/pdf
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| Identifier |
http://nal-ir.nal.res.in/12300/1/cp81.pdf
Sathiyamoorthy, K and Venu, G and Jayaprakash, C and Srinivas, J and Prateesh Kumar, P and Manjunath, P (2013) Development of combustion driven heating system for semi-free jet test rig. In: National Propulsion Conference 2013, 21 Feb 2013, Indian Institute of Madras, Chennai. |
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| Relation |
http://nal-ir.nal.res.in/12300/
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