| タイトル | Experimental Study of a Pulse Detonation Engine Driven Ejector |
| 著者（英） | Santoro, Robert J.; Pal, Sibtosh; Saretto, S.; Shehadeh, R.; Lee, S.-Y. |
| 著者所属（英） | Pennsylvania State Univ. |
| 発行日 | 2005-11-01 |
| 言語 | eng |
| 内容記述 | Results of an experimental effort on pulse detonation driven ejectors are presented and discussed. The experiments were conducted using a pulse detonation engine (PDE)/ejector setup that was specifically designed for the study. The results of various experiments designed to probe different aspects of the PDE/ejector setup are reported. The baseline PDE was operated using ethylene (C2H4) as the fuel and an oxygen/nitrogen (O2 + N2) mixture at an equivalence ratio of one. The PDE only experiments included propellant mixture characterization using a laser absorption technique, high fidelity thrust measurements using an integrated spring-damper system, and shadowgraph imaging of the detonation/shock wave structure emanating from the tube. The baseline PDE thrust measurement results are in excellent agreement with experimental and modeling results reported in the literature. These PDE setup results were then used as a basis for quantifying thrust augmentation for various PDE/ejector setups with constant diameter ejector tubes and various detonation tube/ejector tube overlap distances. The results show that for the geometries studied here, a maximum thrust augmentation of 24% is achieved. Further increases are possible by tailoring the ejector geometry based on CFD predictions conducted elsewhere. The thrust augmentation results are complemented by shadowgraph imaging of the flowfield in the ejector tube inlet area and high frequency pressure transducer measurements along the length of the ejector tube. |
| NASA分類 | Spacecraft Propulsion and Power |
| レポートNO | AIAA Paper 2003-4972 |
| 権利 | Copyright |
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