Computational analysis of mixing and jet pumping in rocket ejector engines

Daines, Russell; Merkle, Charles L.

doi:10.2514/6.1995-2477

Cited by 11 publications

(9 citation statements)

References 1 publication

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“…The gas expands through the nozzles to the RBCC combustor, resulting in a significant difference in speed between the combustor and the still air outside [13]. At this point, a clear shear layer forms between the rocket plume and the air that, along with the shear stress, pulls the still air that is beginning to accelerate in the flowpath.…”

Section: Sea-level Static Conditionmentioning

confidence: 95%

“…The performance of the inlet and the RBCC engine are difficult to estimate accurately because of multiple-coupled influence factors, such as the changing incoming flow, the inlet configuration, rocket operation, etc., which are closely related to the real-time operation of the entire RBCC engine. Hence, numerical simulations based on fully integrated flowpath are highly suitable and necessary for a RBCC engine in ejector mode [13]. Moreover, the boundary condition setting is critical in the numerical investigation of a RBCC engine in ejector mode.…”

Section: Boundary Conditionsmentioning

confidence: 99%

“…In the late 1950s, the U.S. developed the RBCC and conducted many associated investigations. Many of these studies on RBCC engines in ejector mode focused on mixing enhancement between rocket plume and secondary flow [7][8][9][10][11], combustion organization for afterburning, and fuel injection to obtain thermal choking [12,13]. Japan studied the ejector mode of RBCC engines with a configuration based on a scramjet engine [14] and investigated the aerodynamics of these engines using freejet tests over a subsonic to a transonic flow region [15].…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

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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Section: Sea-level Static Conditionmentioning

confidence: 95%

Section: Boundary Conditionsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

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

View full text Add to dashboard Cite

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“…Concepts from classical theory and engineering algorithms for gas jet dynamics are used to calculate the location of the expansion boundary [20,21]. The main equations [21] used in the calculation are shown below.…”

Section: Effect Of Rocket Jetmentioning

confidence: 99%

Study of thermal throat of RBCC combustor based on one-dimensional analysis

Wang

Qin

et al. 2015

Acta Astronautica

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“…In the late 1950s, researchers in the United States began developing RBCC technology and conducted many associated investigations. Many of these studies on RBCC engines in the ejector mode focused on mixing enhancement between rocket plume and secondary flow [18][19][20][21], combustion organization for afterburning, and fuel injection to obtain thermal choking [22,23]. Researchers in Japan studied the ejector mode of RBCC engines with a configuration [24] based on a scramjet engine and investigated the aerodynamics of these engines using freejet tests over a subsonic to transonic flow region [25].…”

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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Computational analysis of mixing and jet pumping in rocket ejector engines

Cited by 11 publications

References 1 publication

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

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

Study of thermal throat of RBCC combustor based on one-dimensional analysis

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

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