Experimental investigation of the thrust enhancement potential of ejector rockets

Dijkstra, F.; Marée, A.G.M.; Caporicci, Marco; Immich, H.

doi:10.2514/6.1997-2756

Cited by 25 publications

(12 citation statements)

References 4 publications

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“…The applicability of using a RBCC engine for single-stage-to-orbit vehicles was also investigated by researchers in Japan [26,27]. The TNO Prins Maurits Laboratory of Netherlands also conducted several experimental investigations on the ejector mode [28], for which experimental systems employing a traditional ejector rocket were developed. Most of the advances obtained in China over the last 20 years [29][30][31], such as combustion organization and rocket engine operation, have been in the ejector mode, with different approaches applied to the research challenge, including theoretical analyses, numerical simulations, and ground tests.…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation of Cowl Lip Adjustments for a Rocket-Based Combined-Cycle Inlet in Takeoff Regime

Shi¹,

Liu²,

He³

et al. 2016

International Journal of Turbo &Amp; Jet-Engines

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Numerical integration simulations were performed on a ready-made central strut-based rocket-based combined-cycle (RBCC) engine operating in the ejector mode during the takeoff regime. The effective principles of various cowl lip positions and shapes on the inlet operation and the overall performance of the entire engine were investigated in detail. Under the static condition, reverse cowl lip rotation in a certain range was found to contribute comprehensive improvement to the RBCC inlet and the entire engine. However, the reverse rotation of the cowl lip contributed very little enhancement of the RBCC inlet under the low subsonic flight regime and induced extremely negative impacts in the high subsonic flight regime, especially in terms of a significant increase in the drag of the inlet. Changes to the cowl lip shape provided little improvement to the overall performance of the RBCC engine, merely shifting the location of the leeward area inside the RBCC inlet, as well as the flow separation and eddy, but not relieving or eliminating those phenomena. The results of this study indicate that proper cowl lip rotation offers an efficient variable geometry scheme for a RBCC inlet in the takeoff regime.

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Section: Introductionmentioning

confidence: 99%

Numerical Investigation of Cowl Lip Adjustments for a Rocket-Based Combined-Cycle Inlet in Takeoff Regime

Shi¹,

Liu²,

He³

et al. 2016

International Journal of Turbo &Amp; Jet-Engines

View full text Add to dashboard Cite

show abstract

“…The applicability of using a RBCC engine for SSTO was also investigated [16,17]. Representing Europe, the TNO Prins Maurits Laboratory of Netherlands also conducted several experimental investigations on the ejector mode for which experimental systems consisting of a traditional ejector rocket were developed [18]. China began research on the RBCC engine relatively late, and most of the advances over the last 20 years have been obtained for the ejector mode [19,20], including combustion organization, rocket engine operation, etc., using different approaches, i.e., theoretical analyses, numerical simulations and ground tests.…”

Section: Introductionmentioning

confidence: 99%

Numerical Study of a Boundary Layer Bleedfor a Rocket-Based Combined-Cycle Inlet in Ejector Mode

Shi

Qin

et al. 2014

International Journal of Turbo &Amp; Jet-Engines

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Fully integrated numerical simulations were performed for a ready-made central strut-based rocketbased combined-cycle (RBCC) engine operating in ejector mode, and the applicability of using a boundary layer bleed in the RBCC inlet designed for supersonic speeds was investigated in detail. The operational mechanism of the boundary layer bleed and its effects on the RBCC inlet and the engine under different off-design conditions in ejector mode were determined. The boundary layer bleed played different roles in the RBCC inlet for different flight regimes. When the RBCC engine took off, some air was entrained into the inlet through the bleed block, thereby inducing significant flow separation and a low-speed vortex, which deteriorated the inner flow and reduced the entraining air mass flow rate: thus, the total pressure loss increased and extra drag was exerted on the inlet. In the low subsonic regime, the bleed block had almost no impact on the RBCC engine and its inlet. However, as the RBCC engine accelerated into a high subsonic flight regime, the boundary layer bleed had a clearly positive effect, comprehensively improving the performance of the RBCC inlet. A boundary layer bleed operation strategy for the RBCC inlet in ejector mode was also developed in this study.

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“…The function of this part is to make the main flow mix with the second flow in the ejection status of RBCC. And the length of this part is concerned with the mixing efficiency, which have an effect on the combustion efficiency [4]. Finally, it affects the thrust in this status.…”

Section: Introductionmentioning

confidence: 99%

Computational investigation of rocket based combined cycle

2013

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Based on Computational Fluid Dynamic technology, the mixing process of Rocket Based Combined Cycle (RBCC) propulsion system is researched. The idea of RBCC propulsion system means combining rocket engine with ramjet engine effectively, which can flight from sea level to high altitude in wide Mach ranges. In order to analyze how the length of the mixing part affects mixing process, different length of mixing part are researched. As it is indicated, with a constant Mach number, increasing the length of mixing part makes main flow and second flow mix more evenly. Moreover, the length of mixing part has a slight impact on the thrust. Obviously the main consequence of increasing the length of mixing part is promoting the mix of main flow and second flow. Therefore, in order to decrease the weight of aircraft, it is of importance to reduce the length. Through comparing distribution of different cases, when working in the situation of maximum power, the flow in the nozzle of rocket engine is under expansion, while that in the nozzle is fully expanded. Nevertheless, in the case of high altitude and high Mach number, there exists a vortex in the nozzle of rocket engine because of over expansion; meanwhile, the flow in the nozzle is under expansion. Therefore, it is necessary to adjust nozzle throat area in order to increase the thrust of RBCC at high altitude.

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Experimental investigation of the thrust enhancement potential of ejector rockets

Cited by 25 publications

References 4 publications

Numerical Investigation of Cowl Lip Adjustments for a Rocket-Based Combined-Cycle Inlet in Takeoff Regime

Numerical Investigation of Cowl Lip Adjustments for a Rocket-Based Combined-Cycle Inlet in Takeoff Regime

Numerical Study of a Boundary Layer Bleedfor a Rocket-Based Combined-Cycle Inlet in Ejector Mode

Computational investigation of rocket based combined cycle

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