Evaluation of Heat-flux on Scramjet Engine Wall in Mach 6 Flight Condition

Paper number

IAC-06-C4.5.04

Author

Mr. Shuichi Ueda, Japan Aerospace Exploration Agency (JAXA), Japan

Coauthor

Dr. Masao Takegoshi, Japan Aerospace Exploration Agency (JAXA), Japan

Coauthor

Dr. Toshinori Kouchi, Japan Aerospace Exploration Agency (JAXA), Japan

Coauthor

Mr. Fumiei Ono, Japan Aerospace Exploration Agency (JAXA), Japan

Coauthor

Mr. Toshihito Saito, Japan Aerospace Exploration Agency (JAXA), Japan

Coauthor

Mr. Muneo Izumikawa, Japan Aerospace Exploration Agency (JAXA), Japan

Year

2006

Abstract

The supersonic combustion ramjet (scramjet) is expected to be the most effective propulsion system for space transportation and hypersonic transportation of the next generation. The transportation system uses the liquid hydrogen of the fuel as a coolant of the engine and the air-frame. Therefore, it is necessary to predict the heat flux to the engine wall in high accuracy for efficient cooling with a minimum coolant. However, the prediction of the heat flux of the scramjet engine combustor, where the supersonic combustion occurs, is quite difficult due to complex interaction of flow and combustion. In this study, heat flux to the scramjet engine wall was measured using water-cooled heat flux meters installed on the sidewall within the combustor sections.
 
Japan Exploration Agency, Kakuda Space Center (JAXA-KSC) has been conducting firing tests of a variety of sub-scale scramjet engine models in Mach 4, 6, 8 simulated flight conditions using Ramjet Engine Test Facility (RJTF). A sidewall-compression-type scramjet engine (E2) was fabricated and tested under Mach 6 flight conditions. The E2 model was designed to reduce distortions caused by swept-angle in the frame and the airflow. In the test of the E2 model, we tried to apply a boundary-layer bleeding and multi-staged fuel injection schemes, such as strut first-stage injection and second-stage injections from several streamwise locations, to the E2 model at the Mach 6 flight condition. The engine model was half water-cooled, half heat sink model. Wall pressures and wall temperatures were measured on the top wall, the sidewall and the cowl of the engine. Water-cooled heat flux meters were installed on the sidewall within the combustor sections. Gas sampling was conducted at the engine exit using water-cooled sampling rakes which ensure reaction quenching during the sampling process. From the composition of the sampled gas, distributions of local equivalence ratio including the deduced reacted fuel, and combustion efficiency distributions were obtained.

In the presentation, the experimental results were compared with CFD analysis of the whole engine to predict heat flux distribution on the engine wall.

Abstract document

IAC-06-C4.5.04.pdf

Manuscript document

IAC-06-C4.5.04.pdf (🔒 authorized access only).

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