Simple model of turbine-based combined cycle propulsion system and smooth mode transition

IF 0.7 4区工程技术 Q4 ENGINEERING, AEROSPACE

International Journal of Turbo & Jet-Engines Pub Date : 2024-07-05 DOI:10.1515/tjj-2024-0047

Jun Liu, Zheng Kuang, Yunfei Wang, Huacheng Yuan

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引用次数: 0

Abstract

Abstract Turbine-based combined cycle (TBCC) propulsion system is becoming one of the most promising propulsion systems for two-stage-to-orbit reusable launch vehicle. Mathematic model of this combined cycle engine is helpful for the basic understanding of performance analysis of this propulsion system. We developed mathematic model of TBCC propulsion system based on C++ platform in this paper. Firstly, turbojet engine was built on component level and ramjet engine was calculated through stream thrust function. Then, performance of turbine-based combined cycle propulsion system along a specific flight trajectory was investigated. According to the thrust of this combined cycle engine, mode transition point was suggested at Ma 2.5, which may achieve smooth mode transition from turbine mode to ramjet mode. Finally, mode transition based on smooth mass flow and smooth thrust criteria were studied. The thrust gap arises during smooth mass flow mode transition, particularly when the turbojet engine afterburner is powered off at the start of the mode transition, and it meets 34 % of the total thrust. Smooth thrust mode transition may be achieved by delaying the turbojet engine afterburner power off and injecting additional fuel into ramjet burner.

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基于涡轮机的联合循环推进系统的简单模型及平稳模式转换

摘要涡轮基联合循环（TBCC）推进系统正成为两级入轨可重复使用运载火箭最有前途的推进系统之一。这种联合循环发动机的数学模型有助于对该推进系统性能分析的基本理解。本文基于 C++ 平台开发了 TBCC 推进系统的数学模型。首先，在组件层面建立了涡轮喷气发动机，并通过流推力函数计算了冲压发动机。然后，研究了基于涡轮的联合循环推进系统在特定飞行轨迹上的性能。根据该联合循环发动机的推力，提出了模式转换点位于 Ma 2.5，可实现从涡轮模式到冲压喷气模式的平滑模式转换。最后，研究了基于平稳质量流量和平稳推力标准的模式转换。在平滑质量流模式转换过程中，尤其是在模式转换开始时关闭涡轮喷气发动机后燃烧器时，会出现推力缺口，其推力占总推力的 34%。可通过延迟关闭涡轮喷气发动机后燃烧器电源并向冲压式喷气发动机燃烧器注入额外燃料来实现平稳的推力模式转换。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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来源期刊

International Journal of Turbo & Jet-Engines 工程技术-工程：宇航

CiteScore

1.90

自引率

11.10%

发文量

审稿时长

6 months

期刊介绍： The Main aim and scope of this Journal is to help improve each separate components R&D and superimpose separated results to get integrated systems by striving to reach the overall advanced design and benefits by integrating: (a) Physics, Aero, and Stealth Thermodynamics in simulations by flying unmanned or manned prototypes supported by integrated Computer Simulations based on: (b) Component R&D of: (i) Turbo and Jet-Engines, (ii) Airframe, (iii) Helmet-Aiming-Systems and Ammunition based on: (c) Anticipated New Programs Missions based on (d) IMPROVED RELIABILITY, DURABILITY, ECONOMICS, TACTICS, STRATEGIES and EDUCATION in both the civil and military domains of Turbo and Jet Engines. The　International Journal of Turbo & Jet Engines　is devoted to cutting edge research in theory and design of propagation of jet aircraft. It serves as an international publication organ for new ideas, insights and results from industry and academic research on thermodynamics, combustion, behavior of related materials at high temperatures, turbine and engine design, thrust vectoring and flight control as well as energy and environmental issues.