An innovative thermal management system for a Mach 4 to Mach 8 hypersonic scramjet engine
An innovative thermal management system for a Mach 4 to Mach 8 hypersonic scramjet engine
复制标题
DOI：
10.2514/6.1998-3734
复制
发表时间：
1998-07
期刊：
影响因子：
--
通讯作者：
Felix F. Chen;W. Tam;N. Shimp;R. Norris
中科院分区：
文献类型：
--
作者：
Felix F. Chen;W. Tam;N. Shimp;R. Norris
为了提高高超声速超燃冲压发动机技术的技术准备水平，美国空军研究实验室HyTech项目办公室资助Aerojet公司在可储存燃料超燃冲压发动机流道概念（SFSFPC）项目下开发一种创新的基于支柱的双模超燃冲压发动机设计。在整个飞行包线上有效的系统热管理是任务成功的关键。本文提出了一种适用于4 ~ 8马赫飞行包线的热管理系统。热系统的设计是基于（在每个马赫数下）在支持4马赫数点火和所有马赫数下高效燃烧所需的条件下向燃烧室输送燃料。发动机热管理系统包括C/SiC发动机壳体和支板、发动机与车辆之间的再生燃料冷却钛板、C/SiC支板内部的再生燃料冷却翅片、热交换器和固体推进剂气体发生器。由于辐射冷却，不需要吸热反应来冷却发动机在全速运行在马赫8。在8马赫的巡航条件下，在80%的功率水平下，辐射和燃料冷却通过吸热反应得到增强，只需要不到40%的裂解正癸烷燃料。这种水平的吸热反应已在实际发动机条件下得到证实。Aerojet一直在积极追求双模冲压发动机在高超声速导弹和全球到达飞行器（参考）上的应用。1 - 4)。为了提高高超声速超燃冲压发动机技术的技术准备水平，美国空军研究实验室（AFRL） HyTech项目办公室资助Aerojet公司在可储存燃料超燃冲压发动机流道概念（SFSFPC）项目下开发一种创新的、基于支柱的双模冲压发动机设计。4到8马赫液体碳氢燃料超燃冲压发动机推进系统的潜在应用是一种快速响应的远程高超音速导弹。任务目标包括战斗机和轰炸机在不超过12分钟的时间内飞行至少750海里。在整个飞行包线上有效的系统热管理是任务成功的关键。本文提出了一种适用于4 ~ 8马赫飞行包线的高效、灵活的热管理系统。技术上的挑战是确定一种灵活的热管理系统设计，该设计将响应燃烧室燃料调节要求以及整个飞行包线上结构热负荷、燃料温度、燃料密度和压力的显著变化。在4马赫运行期间，最具挑战性的任务是确保液体燃料在冲压发动机上有效点燃和燃烧。”航空喷气合同的技术负责人、AIAA成员、工程经理、项目经理# HyTech SFSFPC项目经理这项工作由空军研究实验室支持，合同编号为F33615-96-C-2693。本文被声明为美国政府的作品，在美国不受版权保护。
In order to increase the technology readiness level of the hypersonic scramjet technology, the Air Force Research Laboratory HyTech Program Office funded Aerojet to develop an innovative strut-based dual-mode scramjet engine design under the Storable Fuel Scramjet Flow Path Concepts (SFSFPC) program. Effective system thermal management over the entire flight envelope is critical to the success of the mission. This paper presents a thermal management system operational for a Mach 4 to 8 flight envelope. The design of the thermal system is based (at every Mach number) on delivering fuel to the combustor at the conditions required to support ignition at Mach 4 and high-efficiency combustion at all Mach numbers. The engine thermal management system includes the C/SiC engine shell and struts, a regeneratively fuel-cooled titanium plate between the engine and the vehicle, regeneratively fuel-cooled fins inside the C/SiC struts, a heat exchanger, and a solid propellant gas generator. Due to the radiation cooling, no endothermic reaction is required to cool the engine at full throttle operation at Mach 8. At the Mach 8 cruise condition at the 80 percent power level, the radiation and fuel cooling are augmented by an endothermic reaction requiring less than 40 percent of cracked n-decane fuel. This level of endothermic reaction has been demonstrated under realistic engine conditions. INTRODUCTION Aerojet has been actively pursuing the application of dual-mode ramjet to hypersonic missiles and global reach vehicles (refs. 1-4). To increase the technology readiness level of hypersonic scramjet technology, the Air Force Research Laboratory (AFRL) HyTech Program Office funded Aerojet to develop an innovative, strut-based, dual-mode ramjet engine design under the Storable Fuel Scramjet Flow Path Concepts (SFSFPC) program. A potential application for a Mach 4 to 8 liquid hydrocarbon fueled scramjet propulsion system is a fast-response long-range, hypersonic missile. Mission objectives include a range of at least 750 nautical miles in not more than 12 minutes with carriage from both fighter and bomber aircraft. Effective system thermal management over the entire flight envelope is critical to the success of the mission. This paper presents an efficient, flexible thermal management system for a Mach 4 to 8 flight envelope. The technical challenge is to identify a flexible thermal management system design that will be responsive to the combustor fuel conditioning requirements and to significant variations of structural heat load, fuel temperature, fuel density, and pressure over the entire flight envelope. During Mach 4 operation, the most challenging task is to ensure that the liquid fuel ignites and burns efficiently at ramjet '* Technical Principal, member AIAA, ** Engineering manager, *** Program manager # HyTech SFSFPC Program Manager on the Aerojet Contract This work has been supported by the Air Force Research Laboratory under Contract number F33615-96-C-2693. This paper is declared a work of the U.S. Government and is not subject to copyright protection in the United States.