12th AIAA International Space Planes and Hypersonic Systems and Technologies 15 - 19 December 2003, Norfolk, Virginia
AIAA 2003-6910
Intake Fuel Injection and Shock Induced Combustion in a Scramjet Engine Model Takakage ARAI*, Shigeto MASUDA+ and Fuminori SAKIMA++ Department of Mechanical Systems Engineering, Muroran Institute of Technology 27-1, Mizumoto-cho, Muroran, Hokkaido, 050-8585 Japan arai@mmm.muroran-it.ac.jp Abstract This paper presents flows and combustion phenomena in Scramjet engine model. Hypersonic flow was obtained by using a small high enthalpy shock tunnel. At Mach number of about 6.9, Scramjet engine model was set in the test section. At first, the oblique-shock compression process was studied. Gaseous Hydrogen was injected into the supersonic cross flow from intake wall. We conducted Shlieren-image visualization and wall static pressure measurements, self-emission observation. Shlieren-image visualization and self-emission were observed by using CCD camera. We verified the supersonic combustion and shock- induced combustion.
INTRODUCTION
combustion at a high flight Mach number. As this concept, the length of the combustion chamber is decreased to its minimum. The achievement of this concept is to ensure that combustion chamber is used to combust premixed fuel. This can be achieved by injecting the fuel from the intake allowing mixing to occur upstream of combustor[2] as shown in Fig.1[3].
Detonation wave and, more generally, shock-induced combustion ramjets represent an alternative to scramjets as propulsion devices for hypersonic vehicles[1]. A number of formidable tasks must be tackled to achieve satisfactory operation of such scramjets. Especially, it is important that the injected fuel must be more homogeneously mixed with airflow upstream of the intended detonation wave and shock-induced
The task of homogeneously mixing fuel and air in the high-speed, high-enthalpy flow is the most
Fig.1 Concept of Shock induced combustion ramjet or Detonation wave ramjet[3]
* Associate Professor, senior member AIAA Email:arai@mmm.muroran-it.ac.jp + Graduate Student ++ Graduate Student, student member AIAA Copyright â’¸ 2003 by the American Institute for Aeronautics and Astronautics, Inc. All right reserved
1 Copyright Š 2003 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.