Three Dimensional Hypersonic Inlet with Rectangular-to-Elliptical Shape Transition Under Blunt Nose Effects

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Project title

Code/計畫編號

MOST105-2623-E019-003-D

Translated Name/計畫中文名

鈍角效應下之截面轉換三維極音速進氣道設計技術研發

Project Coordinator/計畫主持人

Juan-Chen Huang

Funding Organization/主管機關

National Science and Technology Council

Department/Unit

Department of Merchant Marine

Website

https://www.grb.gov.tw/search/planDetail?id=11773254

Year

2016

Start date/計畫起

01-01-2016

Expected Completion/計畫迄

31-12-2016

Bugetid/研究經費

777千元

ResearchField/研究領域

機械工程

"超音速燃燒衝壓引擎是現今最適合於極音速領域巡航之吸氣式引擎，極音速巡航載具具有快速反應與高穿透性之優勢，是先進國家積極投入研發的技術。其中極音速進氣道是超音速燃燒衝壓引擎的關鍵組件之一。近年發展出方轉橢圓型(REST Rectangular- to-Elliptical Shape Transition)三維極音速進氣道設計技術，進氣道入口截面與出口截面可為任意形狀。此種設計在幾何外型固定、不增加額外組件的前提下不但可增加進氣道與載具整合設計的彈性，同時也可直接與圓形截面燃燒室銜接，使引擎內流道具有較佳的結構效率，更重要的是此種進氣道讓超燃衝壓引擎的進氣道在較低速(3.5馬赫)啟動並可提高進氣道的偏離設計點操作性能，增加引擎的操作範園。因此中山科學研究院於本(105)年成立「矩形與橢圓截面轉換之超音速流道設計技術研發」之學術合作案。研究期程一年。計畫目的是發展截面轉換之三維進氣道設計技術，並考慮實際應用上的熱負荷問題，進氣道前緣、罩唇都將採鈍角設計。完成飛行速度(3.5~6.0馬赫)、攻角(0~6度)等參數變化範圍之流場分析，提供全壓損失與捕獲氣量等分析結果供需求單位參考。預期本計畫完成後將充分建立超音速進氣道分析與設計技術，可提供國內太空計畫、國防科技與產業發展等相當的助益。本計畫採用現行發展解三維可壓縮Navier-Stokes方程式數值計算程式；包括針對震波結構具有高解析度的守恆律算則(加權基本不振盪算則WENO)，補捉接觸面或滑線(slip line)相當有效的anti-diffuse WENO算則，具備混合多區塊網格(Mulit-block)及挖除式(Blocking- off)網格處理複雜幾何外型與平行計算的功能，時間積分則採穩定性佳之LU-SGS法，為改善收斂特性，以Bi-CGSTAB鬆弛法求解紊流變數傳輸方程式。本文研究成果績效指標訂定為(1)建立進氣道入口至隔離段出口的截面轉換流道設計技術。(2)完成鈍角效應與進氣道流場特性之相關性研究。全案完成後將可提供截面轉換之三維進氣道設計技術與流場分析等相關研究資料，供委託單位參考應用。 ""Scramjet is an aspirated engine by far the most suitable for hypersonic vehicles. The vehicles have the advantage of high penetration and very rapid maneuvering response. Many advanced countries actively involved in research of Scramjet techniques. Inlet is one of the key components of the Scramjet vehicles. In recent years, the design techniques of three-dimensional hypersonic inlet REST (Rectangular-to-Elliptical Shape Transition) have been proposed. The shapes of inlet and outlet cross section can be any shape. The main purpose of inlet with REST design is to start the engine and good operating performance at the flight conditions of Mach 3.5 under the premise of fixed geometric shape, no additional components. This REST design not only improves the flexibility of integration design between the inlet and vehicle, but also can directly connect with a circular cross section of the combustion chamber. Thus, the inner engine flow path has better structural efficient for combustion, more important, such inlet can improve the inlet performance, when the fight conditions deviate from the design point of REST inlet, increased engine operation envelope. CSIST offers the project in next year, and the purpose of current project is to develop the design techniques of REST hypersonic inlet. To consider the issue of thermal load in practical applications, the blunt leading edge and cowl lip are adopted. By using this design technique, we could design the flow path of inlet and isolator with arbitrary cross section of inlet entry shape, and connected with the combustor of circular or elliptical cross-sections. The flow simulations of flight Mach number ranging from 3.5 to 6.0, and angle of attack ranging from 0 to 6 degree are implemented. The inlet performance parameters of total pressure recovery, mass flow rate captured are evaluated. "

Keyword(s)

超音速燃燒衝壓引擎
方轉橢圓型
三維極音速進氣道
燃燒室
WENO 算則
SCRAMJET
inlet
REST
WENO scheme

DSpace CRIS

Three Dimensional Hypersonic Inlet with Rectangular-to-Elliptical Shape Transition Under Blunt Nose Effects

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