Study on Rocket-Based Combined-Cycle Engines

火箭联合循环发动机研究

• 批准号: 09305063
• 负责人: KAMIJO Kenjiro
• 金额: $ 23.68万
• 依托单位: Tohoku University
• 依托单位国家: 日本
• 项目类别: Grant-in-Aid for Scientific Research (A)
• 财政年份: 1997
• 资助国家: 日本
• 起止时间: 1997 至 1998
• 项目状态: 已结题
• 来源: https://kaken.nii.ac.jp/grant/KAKENHI-PROJECT-09305063/
• 关键词: Rocket-Based Combined-Cycle Engine; Liquefied Air Cycle Engine; Scramjet Engine; Heat Exchanger for Air liquefaction; Supersonic Intake; Scramjet Isolator; エンジンシステム解析; 超音速インテ-ク; 低温流体気液混相流

Recently, rocket-based combined-cycle (RBCC) engines have been discussed more frequently because of their attractive characteristics, such as an increased payload-to-take-off-weight ratio and a higher specific impulse. In this study the ScramLACE (liquefied air cycle / supersonic-combustion ramjet) engine was chosen for the transatmospheric accelerating mode of the RBCC system to investigate the feasibility of using the LACE mode and the Scramjet mode combination with the RBCC system.An experimental study on cooling the heat exchanger by liquid hydrogen was conducted to validate a method of estimating the air liquefaction ratio, alpha, based on the study of corrugated-straight-fin heat exchangers. The results showed that the measurements of alpha are well coincident with the calculations obtained by this method of estimating alpha. Based on this method of estimating alpha, the relationship between alpha and the flight Mach number, M, was obtained using a parameter of the heat transfer … More area of the heat exchanger in order to evaluate the system performance of a basic model of the LASE system. From the results, it was clarified that changing a hydrogen supply line from LACE 1 to LACE 2 at a selected value of the flight Mach number is one of the most reasonable ways to achieve a high specific impulse during the LACE mode operation, M=1 to 5.An experiment of an air intake model during the LACE mode operation was performed using a supersonic wind tunnel to validate numerical results obtained from Navier-Stokes equations. It was found that this computational method has sufficient accuracy to evaluate the qualitative performance of the supersonic intake. Based on this method, characteristics of two types of the intake model were investigated.Effect of airframe integration on scramjet performance were calculated on the assumption of quasi-one-dimensional flow. Three different types of airframe integration were investigated. From the results, it was clarified that it is desirable for the engine to be integrated on the airframe paralleled to the airframe axis, as well as to have an inlet inhaling the air compressed by the shock wave from the nose of the airframe.The pseudo-shock waves in rectangular scramjet isolators with steps were investigated, When the front of the pseudo-shock waves first reached to the step, pressure at the first shock vibrated with the clear frequency peak of 320-480 Hz. Then the pseudo-shock waves propagated further upstream of the step, the pressure around the first shock vibrated with 100-200 Hz. From these results, it was found that these features in the rectangular duct with the step were caused by the recirculation right downstream of the step. Less

近年来，基于火箭的联合循环（RBCC）发动机因其具有较高的有效载荷-起飞-重量比和比冲等特性而受到越来越多的关注。本研究选择了液化空气循环/超音速燃烧冲压发动机作为RBCC系统的跨大气加速模式，探讨了LACE模式和超燃冲压发动机模式与RBCC系统结合使用的可行性。在对波纹直翅片换热器进行研究的基础上，对液氢冷却换热器进行了实验研究，验证了估算空气液化比α的方法。结果表明，α的测量值与用这种方法估计α的计算结果吻合得很好。在此基础上，利用换热器换热面积参数，得到了α与飞行马赫数M之间的关系，从而对LASE系统的基本模型进行了系统性能评价。结果表明，在选定的飞行马赫数值下，将一条供氢线从LACE 1改为LACE 2，是在LACE模式运行（M=1 ~ 5）期间实现高比冲的最合理方法之一。为了验证Navier-Stokes方程的数值结果，在超音速风洞中对LACE模式下的进气模型进行了实验。结果表明，该计算方法具有足够的精度，可用于评价超声速进气道的定性性能。在此基础上，研究了两种进气模型的特性。在准一维流动假设下，计算了机身一体化对超燃冲压发动机性能的影响。研究了三种不同类型的机身集成。结果表明，发动机应安装在与机身轴线平行的机身上，并有一个吸入由机身前端冲击波压缩的空气的进气口。对带台阶的矩形超燃冲压发动机隔震器内的伪激波进行了研究，当伪激波前缘首次到达台阶时，第一激波处的压力以320 ~ 480 Hz的清晰频率峰值振动。然后伪激波向台阶上游进一步传播，第一次激波周围的压力以100-200 Hz的频率振动。从这些结果可以看出，带台阶的矩形风管的这些特征是由台阶下游的再循环引起的。少

项目成果

Katsuya Matsuura et al.: "An Experiment of Scramjet Isolators with Backward-Facing Step" Proceedings of the 21st International Symposium on Space Technology and Science Omiya. Vol.1. 104-109 (1998)

Katsuya Matsuura 等人：“An Experiments of Scramjet Isolators with Backward-Facing Step”第 21 届国际空间技术与科学大宫研讨会论文集。

Daiho Tanaka et al.: "Evaluation of Heat Exchanger Performance for LACE" Proceedings of the Annual Meeting and the 9th Symposium on Ram/Scramjets. 23-28 (1999)

Daiho Tanaka 等人：“LACE 热交换器性能评估”年会和第九届冲压/超燃冲压发动机研讨会论文集。

Mamoru Oike et al.: "LACE for Rocket-Based Combined Cycle" AIAA Paper 99-0091,37th Aerospace Sciences Meeting & Exhibit, Reno. (1999)

Mamoru Oike 等人：“LACE for Rocket-Based Joint Cycle”AIAA 论文 99-0091，第 37 届航空航天科学会议

Yoshinori Futonagane et al.: "Unsteady Motion of Pseudo-Shock Waves in Scramjet Isolators" Proceedings of the Annual Meeting and the 9th Symposium on Ram/Scramjets. 209-214 (1999)

Yoshinori Futonagane 等人：“超燃冲压发动机隔离器中伪冲击波的不稳定运动”年会和第九届冲压/超燃冲压发动机研讨会论文集。

上條謙二郎、他5名: "ロケットベース複合エンジン用LACEの性能" 日本機械学会第76期全国大会講演論文集. Vol. IV. 19-20 (1998)

Kenjiro Kamijo 等 5 人：“基于火箭的复合发动机的 LACE 性能”第 76 届日本机械工程师学会全国会议论文集，第 19-20 卷（1998 年）。