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8 results on '"RBCC engine"'

1. Secondary fuel jet strategies on mixing enhancement performance of rocket-based combined cycle engine.

Author

Dai, Jian and Huang, Chao

Subjects
*COMBINED cycle (Engines), *JET fuel, *JETS (Fluid dynamics), *NAVIER-Stokes equations, *MIXING, *SHOCK waves, *JET impingement
Abstract

The mixed augmentation performance between secondary fuel jet and uneven supersonic inflow is a significant evaluation index of the rocket-based combined cycle engine. In this study, the effects of the secondary fuel jet on the flow field structure and mixing enhancement performance are discussed by changing both the secondary fuel jet angle and spacing of multiple rows of jet holes. The three-dimensional coupled implicit Reynolds averaged Navier-Stokes equations, SST k - ω turbulence model, and eddy dissipation concept (EDC) reaction model were adopted to evaluate the flow field structure with a sonic hydrogen jet. It is indicated that the 135° fuel jet has the largest penetration depth value, followed by the 90° fuel jet, whereas the 45° fuel jet has the smallest penetration depth value. However, the 45° fuel jet possesses the best mixing performance, it easily induces a pair of downstream counter-rotating vortex, and the oblique torque is further generated to aggravate the tearing ability to the jet. The three jet holes induce a stronger shock wave and form a larger barrier under the 90° jet. Additionally, when the spacing between the multiple rows of jet holes reduces, penetration depth is easily created. Further, when the spacing of the three rows of jet holes is larger, the fluctuation of the mixing coefficient increases. • The influence of secondary fuel jet strategies on the mixing characteristics is studied. • The impact of jet angle and spacing on mixing zone is discussed. • The flow structures, penetration depth and mixing efficiency are analyzed. • Increasing jet angle is beneficial to augment the penetration depth value. • Decreasing the fuel jet spacing improves the fuel mixing in the far downstream. [ABSTRACT FROM AUTHOR]

Published
2021
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2. Research on shock wave characteristics in the isolator of central strut rocket-based combined cycle engine under Ma5.5.

Author

Wei, Xianggeng, Xue, Rui, Qin, Fei, Hu, Chunbo, and He, Guoqiang

Subjects
*SPACE vehicles, *SHOCK waves, *ISOLATORS (Engineering), *STRUTS (Engineering), *COMBINED cycle (Engines)
Abstract

A numerical calculation of shock wave characteristics in the isolator of central strut rocket-based combined cycle (RBCC) engine fueled by kerosene was carried out in this paper. A 3D numerical model was established by the DES method. The kerosene chemical kinetic model used the 9-component and 12-step simplified mechanism model. Effects of fuel equivalence ratio, inflow total temperature and central strut rocket on-off on shock wave characteristics were studied under Ma5.5. Results demonstrated that with the increase of equivalence ratio, the leading shock wave moves toward upstream, accompanied with higher possibility of the inlet unstart. However, the leading shock wave moves toward downstream as the inflow total temperature rises. After the central strut rocket is closed, the leading shock wave moves toward downstream, which can reduce risks of the inlet unstart. State of the shear layer formed by the strut rocket jet flow and inflow can influence the shock train structure significantly. [ABSTRACT FROM AUTHOR]

Published
2017
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3. Preliminary design of a rocket-based combined cycle engine for application aboard Mk-II Aurora suborbital spaceplane

Author

Grendysz, Michał (author) and Grendysz, Michał (author)

Abstract

The rocket-based combined cycle (RBCC) engines are a hybrid between rocket and air-breathing propulsion. They can offer performance gains when compared to traditional rocket engines. At the same time, they are relatively simple in design. Therefore, they generally do not require long development times or large funds so they could be an attractive alternative to rocket-only propulsion. This thesis presents research on RBCC engines with the main goal to investigate possible use of this type of engine aboard the Mk-II Aurora suborbital spaceplane that is being developed by Dawn Aerospace. The main criterion used in the assessment was the impact of implementing the engine on spaceplane's performance compared to current rocket-only propulsion. In this study a RBCC engine was designed based around the parameters of the core rocket motor. During the initial phase, the engine was optimized for performance using a developed and validated quasi-1D model. This design was then analysed using CFD methods to verify results of the early simulation. Later on the quasi-1D model was used to simulate engine operation in multiple flight conditions. Finally, the trajectory was optimised and compared with the trajectory of a rocket-propelled spaceplane to investigate the final performance gains. It was concluded that only a modified version with added compressor could possibly match or outperform rocket-only propulsion but only if its design does not add more than the threshold mass and drag to the existing spaceplane design., Aerospace Engineering

Published
2021

4. Mixture Evaluation with Incoming Air and the Rocket Exhaust of the RBCC Engine at Scramjet Mode

Author

Takagi, Shohei, Tomioka, Sadatake, Kudo, Kenji, Murakami, Atsuo, and Masuya, Goro

Subjects
RBCC engine, Auxiliary Injection, Hypersonic Flow
Abstract

平成24年度宇宙輸送シンポジウム (2013年1月17日-1月18日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)), 相模原市, 神奈川県, Space Transportation FY2012 (January 17-18, 2013. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, From the Mach 11 flight condition experiment result at HIEST, it was found that it was necessary to promote mixing to raise combustion efficiency. Therefore, the mixture state in the engine was investigated. The experiment conducted at supersonic wind tunnel. The mixture state was evaluated by gas sampling by the experiment without combustion. As a result, mixing promotion effect is match higher with the rocket side auxiliary injection than the cowl side auxiliary injection. Additionally, a mixture promotion effect by the incidence of the expansion wave to rocket exhaust was confirmed., 形態: カラー図版あり, 形態: PDF, Physical characteristics: Original contains color illustrations, Physical characteristics: PDF, 資料番号: AA0061856035, レポート番号: STCP-2012-035

Published
2013

5. Studies of the supersonic ejector for improvement of the performance in the RBCC engine model

Author

Hasegawa, Susumu, Tani, Kouichiro, and Ueda, Shuichi

Subjects
Ejector, RBCC Engine
Abstract

平成27年度衝撃波シンポジウム (2016年3月7日-9日. 熊本大学 黒髪南地区）熊本市, 熊本県, Symposium on Shock Waves in Japan, FY2015 (March 7-9, 2016. Kumamoto University), Kurokami Chuo-ku, Kumamoto, Japan, 資料番号: SA6000049006, レポート番号: 1A1-3

Published
2016

6. Mixinging Prediction with Incoming Air and the Rocket Exhaust of the RBCC Engine under Scramjet Mode

Author

Nakano, Ryosuke, Tomioka, Sadatake, Kudo, Kenji, Murakami, Atsuro, and Ueda, Shuichi

Subjects
Mixing, RBCC engine, Shear Layer
Abstract

平成26年度宇宙輸送シンポジウム（2015年1月15日-16日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県, Space Transportation Symposium FY2014 (January 15-16, 2015. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000036028, レポート番号: STCP-2014-028

Published
2015

7. CFDによる複合サイクルエンジンのエジェクタ・モード流れの空力解析

Author

Hasegawa, Susumu and Tani, Koichiro

Subjects
flow distribution, 流れの分布, rocket-based combined-cycle engine, Mach number, shock wave, 衝撃波, combustion chamber, 計算流体力学, 直接数値シミュレーション, マッハ数, computational fluid dynamics, Navier-Stokes equation, Physics::Fluid Dynamics, RBCCエンジン, conical nozzle, エジェクタ・モード, RBCC engine, ロケットベース複合サイクルエンジン, ナビエ・ストークス方程式, direct numerical simulation, ejector-mode, 円錐ノズル, 燃焼器
Abstract

Rocket Based Combined-Cycle (RBCC) engines are currently being explored as advanced propulsion for space transportation. JAXA has been conducting RBCC engine research by using various experimental facilities. In order to clarify the experimental results and contribute to the improvement of designing, the analysis of the RBCC engine in an ejector-jet mode was carried out using the CFD (Computational Fluid Dynamics) code developed in-house for unstructured grids. CFD replicated the basic flow structures in regard with barrel shocks and pseudo-shock waves. Two cases of Mach numbers (i.e. M = 1, 1.1) entering to the combustor were simulated and remarkable differences were found on the subsonic areas in the flowfields. The effect of Mach number was found to be one of the important parameters for better match to the experimental data. Vorticities and mixing were investigated. In addition to the transverse vorticity, the streamwise vorticity were generated in the air flow, and they stirred and affected the nitrogen/air mixing. Furthermore, the effects of the total pressure of the rocket gas were examined., 資料番号: AA0063154008, レポート番号: JAXA-SP-06-010

Published
2006

8. Study on a next-generation propulsion system

Author

Tokudome, Shinichiro and Habu, Hiroto

Subjects
SITVC, 深宇宙探査, 信頼性, general overview, reliability, deep space exploration, secondary injection, attitude control, chemical propulsion, 姿勢制御, N2O/エタノール, 2次噴射, RBCCエンジン, 総覧, RBCC engine, N2O/ethanol, 次世代推進系, 化学推進, next generation propulsion system
Abstract

宇宙工学輸送系研究の一環として今後取組まなければならない化学推進系の研究課題について具体的な意見を述べさせていただいた。地上〜周回軌道への大量輸送システムを構築するために欠かせないロケット複合サイクル推進システム、取扱い易さと信頼性を向上させるために推進薬を無毒化した衛星・探査機搭載用2液推進系の2点である。, 資料番号: AA0045441085

Published
2003

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