本研究針對微型渦輪噴射引擎後燃器系統進行設計、模擬與性能驗證，其具備結構簡單、製造成本低廉、達到音速等優勢，以因應現今對於推進系統性能提升的需求。並建立一套微型後燃器設計流程，並以數值模擬與性能驗證為依據，針對其幾何設計、燃燒行為與效能表現進分析與評估，提供後續推進系統設計之技術參考。
本研究首先應用GasTurb軟體建立微型渦輪引擎模型，並與實測數據進行驗證，將模擬誤差控制於合理範圍內，確保性能預測的可信度。接續於GasTurb中導入後燃器模組，初步評估燃燒後對推進性能之增益。最後，透過Ansys Fluent數值模擬，針對後燃器內部流場進行計算，包括速度場、溫度分布與馬赫數等參數，並探討幾何設計對燃燒之影響，建立後燃器設計驗證流程。
模擬結果顯示，於相同進氣條件下加入後燃器，可使推力提升約33%，且流場達到音速流；雖然後燃器有效增強了推力與噴氣速度，但燃油消耗率相對提高，模擬中顯示增加46%，顯示在應用上仍須針對燃油效率與任務效益進行權衡與優化。

This study investigates the design, numerical simulation, and performance validation of an afterburner system integrated into a micro turbojet engine, aiming to address the increasing demands for enhanced propulsion system performance. The micro-scale afterburner offers several engineering advantages, including structural simplicity, low manufacturing cost, and the capability to generate exhaust flows approaching sonic conditions. A comprehensive design methodology for the micro afterburner is proposed, incorporating numerical simulations and performance assessments to systematically evaluate its geometric configuration, combustion behavior, and overall efficiency. The results are intended to serve as a technical reference for future micro-propulsion system development.
The research begins with the establishing of a micro turbojet engine model by GasTurb software, which is subsequently validated against experimental data with simulation discrepancies constrained within acceptable error margins. The afterburner module is then implemented within the GasTurb framework to preliminarily evaluate the thrust enhancement resulting from secondary combustion. Following this, Ansys Fluent is employed to simulate the internal flow characteristics of the afterburner, focusing on parameters such as velocity field, temperature distribution, and Mach number. The influence of geometric configuration on combustion and fluidynamics is also examined, thereby establishing a validated methodology for afterburner design analysis.
Simulation results demonstrate that, under identical inlet conditions, the incorporation of the afterburner leads to an approximate 33% increase in thrust output and achieves flow conditions near Mach 1. However, while the afterburner significantly enhances thrust and jet velocity, it also results in a substantial increase in fuel consumption approximately 46%, indicating the necessity to balance propulsion performance with fuel efficiency in practical implementations.

Brayton Cycle, https://en.wikipedia.org/wiki/Brayton_cycle
Reheat Brayton Cycle, https://en.wikipedia.org/wiki/Afterburner
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