Development of combustion driven heating system for semi-free jet test rig

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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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

Item Type: Conference or Workshop Item (Paper)
Uncontrolled Keywords: Aero-propulsion;High speed combustors;Combustion chamber
Subjects: AERONAUTICS > Research and Support Facilities (Air)
Depositing User: Ms. Alphones Mary
Date Deposited: 18 Aug 2015 07:26
Last Modified: 28 Aug 2015 10:15

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