涡轮基双燃烧室超燃组合循环发动机方案研究

Study on Turbine-Based Dual-Combustor Scramjet Combined Cycle Engine Concept

关键词:  组合循环发动机  超燃冲压发动机  推力陷阱  双燃烧室

Key words:  Combined cycle engine  Scramjet  Thrust gap  Dual combustor

摘要:

针对临近空间飞行器及空天飞行器使用需求，提出了涡轮基双燃烧室超燃组合循环发动机(Turbine-based dual-combustor scramjet combined cycle propulsion ，TBDC)概念，由成熟涡轮与双燃烧室超燃冲压发动机并联组成，Ma0～2.5以涡轮模态为主，Ma2.5～6+主要由双燃烧室超燃冲压发动机提供推力。分析了双燃烧室超燃冲压发动机启动马赫数低、工作包线下边界宽域特点对解决涡轮基与冲压级模态转换过程中普遍存在的“推力陷阱”的有效性和双燃烧室技术应用于组合发动机的可行性，研究了双燃烧室发动机适应组合发动机一体化构形和性能保持、统筹组合发动机可调进气功能拓展双燃模态工作边界的技术途径，完成了组合发动机典型状态点性能仿真和关键技术梳理。研究表明，涡轮基双燃烧室超燃组合循环发动机有望在Ma2.5～3实现模态转换、推力顺畅接力，适应Ma0～6+高速宽域飞行需求。

Abstract:

Turbine-based dual-combustor scramjet combined cycle propulsion (TBDC) is proposed for potential application to near-space flight vehicle and aerospace vehicle. For TBDC， an off-the-shelf turbo engine acts as the primary thrusters in the range of about Mach 0～2.5， and dual-combustor scramjet expanded performance for Mach 2.5～6+. Expansion of high performance at low speed and a wide working envelop under boundary has been studied， which could effectively solve the breakthrough in the thrust gap between turbo and dual-mode ramjet. The technical approach of the structural adaptability for combined cycle of the dual-combustor scramjet and expansion of working envelop of the dual-combustor mode with common adjustable intake and nozzle has been studied. Performance simulation for typical state point and key technology carding have been performed. Results suggest that TBDC is hopeful to accomplish mode transition with thrust smoothing， which allows operation form static to hypersonic speed (Mach 6+).