Details

Autor(en) / Beteiligte

• CAO, R. F
• CHANG, J. T
• TANG, J. F
• WANG, Z. Q
• YU, D. R

Titel

Study on combustion mode transition of hydrogen fueled dual-mode scramjet engine based on thermodynamic cycle analysis

Ist Teil von

• International journal of hydrogen energy, 2014-12, Vol.39 (36), p.21251-21258

Ort / Verlag

Kidlington: Elsevier

Erscheinungsjahr

2014

Quelle

Alma/SFX Local Collection

Beschreibungen/Notizen

• Hydrogen fueled scramjet is a candidate for use as the engine of the aerospace plane for its high specific impulse. To further improve the engine performance, analysis of combustion mode transition for a hydrogen fueled scramjet engine was investigated in this study. In order to identify the differences between Scram- and Ram-mode cycles in propulsive and economic performances for selection and optimization of operation modes, a thermodynamic cycle analysis was made with a dual-mode scramjet engine. It was found through comparative analysis that the specific impulse of the Ram-mode cycle was superior to that of the Scram-mode cycle in meeting the specific thrust requirement. From the viewpoint of performance optimization, the combustion mode transition in a dual-mode scramjet engine should occur in the range of Mach number 6-7. It was therefore concluded that a dual-mode scramjet engine should be operated as much at the Ram-mode cycle as possible when the flight Mach number is less than 6, and the combustion mode transition between Ram-mode cycle and Scram-mode cycle should take place in the range of flight Mach number 6-7.