本研究為探討一具微型渦輪噴射引擎初步理論計算、製造流程規劃與控制系統設計。微型渦輪噴射引擎區分為進氣道、壓縮機、擴散器、燃燒室、渦輪入口導葉、渦輪與噴嘴,理論計算上,吾人以一維理想氣動力流場作為計算基礎,利用假設之壓縮比與環境條件計算出各部件氣動力參數與外型。而引擎製造上一直都是個難題,吾人規劃利用車削、銑削、鑄造、焊接、深孔鑽孔、放電加工與板金工法間的互相配合完成微型渦輪引擎的製造與組裝。控制系統設計上,利用LabVIEW搭配國家儀器的硬體與微型渦輪引擎周邊所需要的硬體來完成程式撰寫與流程規劃,並撰寫測試用程式確保引擎控制程式的流程與保護機制是否正常運作。
This reseach investigated preliminary theoretical calculations, manufacturing process and control system design for a micro turbojet engine. Micro turbojet engine divided into inlet, compressor, diffuser, combustor chamber, turbine inlet guide vanes, turbine and nozzle. For theoretical calculations, we use one-dimensional ideal flow as the basis for calculation to decide aerodynamic parameter and aerodynamic shape by assuming pressure ratio of compressor and environment condition. The engine manufacturing has always been a difficult problem. We use turning, milling, casting, welding, deep hole drilling, electrical discharge machining, sheet metal methods to complete micro turbojet engine. In control system design, we write LabVIEW program with hardware by National Instrument and micro turbojet engine to complete process planning, and we also write a testing program to ensure whether control system operating normally.