Performances of a Rocket Chamber for the Combined-Cycle Engine at Various Conditions

Takegoshi, Masao; Tomioka, Sadatake; Ueda, Shuichi; Saito, Toshihito; Izumikawa, Muneo; Hayasaka, Osamu

doi:10.2514/6.2006-7978

Cited by 9 publications

(3 citation statements)

References 3 publications

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“…In-depth studies have now been conducted in every single mode, and it has become increasingly important for the RBCC engine to perform effectively over the entire flight regime for its applications [21][22][23]. For example, a RBCC inlet can be designed for super/hyper-sonic speeds and does not have to be tuned only to the sub/trans-sonic regime.…”

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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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

View full text Add to dashboard Cite

show abstract

“…At present, the United States, Australia, European Union, France, Russia, Germany, Japan, China and other countries or regions have been vigorously developing RBCC technology, 12–32 and the United States is the most representative country in RBCC-powered vehicles concept design. A summary of the current hypersonic vehicle conceptual design powered by RBCC engine is shown in Table 1, 33 in which ABLV-06 (RBCC Rocketdyne), ABLV-07A (RBCC Aerojet), ABLV-07c (RBCC Aerojet) and ABLV-07c-LaunchAssist (RBCC Aerojet) have the same working principle that could be described as follows: RBCC engine starts working in ejector mode, performs ramjet-scramjet mode transition at Ma 2.5+ and then operates in rocket mode.…”

Section: Introductionmentioning

confidence: 99%

A survey on the conceptual design of hypersonic aircraft powered by RBCC engine

Xue

Xia

Feixing

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part C:

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Rocket-based combined-cycle (RBCC) powered vehicles have been widely recognized as the most promising aircraft solution that could dramatically reduce the cost of space transportation. Researchers and scientists worldwide have conducted considerable overall design researches to cope with the challenges in RBCC development including mode transition, thermal protection and thrust enhancement. According to the way to orbit and the configuration characteristics, the hypersonic aircraft powered by RBCC engine are classified as four categories: single-stage-to-orbit (SSTO) two-dimensional configuration, SSTO axisymmetric configuration, two-stage-to-orbit (TSTO) two-dimensional configuration, and TSTO axisymmetric configuration. This paper systematically presents the development of the conceptual design of RBCC-powered vehicles. Both the structural and operating key parameters like the weight distribution, the RBCC propulsion performance and take-off mode, et al. are introduced in detail. On this basis, a comparative analysis of the advantages and disadvantages of the orbit model, the configuration selection and takeoff modes are conducted. In addition, the application prospect and technology development direction for hypersonic aircraft are also discussed. At the same time, the lessons that can be drew from previous hypersonic vehicle concept design are explored.

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“…Ignition and flame propagation are dependent of various physical properties in the combustion chamber (e.g., the mixing ratio of the propellant, the initial pressure and temperature in the thrust chamber and their heat transfer characteristics, the total energy deposited by the ignition system, the spark position, convection velocity, average droplet size, and its distribution) [9]. Takegoshi et al [10][11][12] of the Kakuda Space Center in Japan performed the tests on the combined cycle engine rocket ejector ignition under different conditions. Kim et al [13] observed the ignition transition of GOX/kerosene spray by directly visualizing the combustion flow field.…”

Section: Introductionmentioning

confidence: 99%

Experimental and Numerical Investigations on the Ignition of RBCC Gas-Oxygen/Kerosene Rocket Ejector

Liu

Jin

et al. 2021

International Journal of Aerospace Engineering

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The rocket ejector refers to a core component of a rocket-based combined cycle (RBCC) engine. The ignition is of critical significance for rocket ejection. Reliable and stable ignition crucially determines the normal operation of the engine. In this paper, a thrust chamber with coaxial swirl injector for the RBCC rocket ejection was developed and tested. Gas oxygen (GOX) and kerosene acted as propellants. As revealed from the test results, the process of ignition pressurizing comprised four phases. The oxygen prefilling time before ignition slightly impacted the ignition time, whereas it affected the peak pressure of ignition. In a confined range, the peak pressure decreased as the prefilling time was extended. The ignition was simulated by building a numerical model, and the results well complied with the experimentally achieved results. The numerical model is capable of specifically indicating the position of the kernel of fire and the process of flame propagation. The simulation results reveal that the propellant could form a combustible condition within 4 ms. The kernel was 6 mm away from the injector, located at the oxygen and kerosene mixing interface and approaching the upper wall. The above results reflected the vital role of the central recirculation zone formed by the prefilled oxygen. The ignition energy was transported near the injector under the convection effect, which ignited the stoichiometric mixture, and the entire ignition could reach a stable state within 20 ms. The numerical model which was developed in this paper can help clarify the combustion mechanism.

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Performances of a Rocket Chamber for the Combined-Cycle Engine at Various Conditions

Cited by 9 publications

References 3 publications

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

A survey on the conceptual design of hypersonic aircraft powered by RBCC engine

Experimental and Numerical Investigations on the Ignition of RBCC Gas-Oxygen/Kerosene Rocket Ejector

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