成果報告書詳細
管理番号20160000000304
タイトル*平成27年度中間年報 エネルギー・環境新技術先導プログラム 革新的な高熱効率を有する自発予圧縮機構付き回転デトネーションエンジンの研究開発
公開日2016/5/17
報告書年度2015 - 2015
委託先名国立大学法人名古屋大学 学校法人慶應義塾 国立研究開発法人宇宙航空研究開発機構 株式会社IHIエアロスペース・エンジニアリング 株式会社ネッツ
プロジェクト番号P14004
部署名イノベーション推進部
和文要約
英文要約Title: Advanced Research Program for Energy and Environmental Technologies/Research and Development of Innovative High-Thermal-Efficiency Rotating Detonation Engines with Spontaneous-Compression Mechanism (FY2014-FY2016) FY2015 Annual Report

In FY2015, we fabricated a rotating detonation engines (RDE) with a soundproofed combustion measurement setting with a device for exhausting burned gas in Nagoya University. As a proof-of principle experiment, we performed measurement of time-averaged pressure in the several types of RDE with injector. We performed visualization experiment for analyzing the structure of detonation wave in the disc-shaped RDE. We also optimized the injection angle of the injector in the discs-shaped RDE. We preliminarily designed a disc-shaped rotating detonation turbine engine for confirming optimal pressure gain in the disc-shaped combustor. We investigated exhaust velocity of a double annular type RDE and made a calculation model of this RDE system. We experimentally tried to test the double annular type RDE system with a radial turbine and a compressor. We show the detailed outcome listed below in an each issue.

Result 1-1: We performed design, detailed design and fabrication of rotating detonation engines (RDE) and a soundproofed combustion measurement setting with a device for exhausting burned gas. The setting was located in Mechanical & Aerospace Engineering Building in Nagoya University.
Result 1-2: We confirmed that combustor time-averaged pressure in the disc-shaped RDE combustor was larger than stagnation pressure in the plenum chamber of fuel and oxidizer. The optimal combustor shape was disc shape. Optimal conditions of pressure gain combustion were disc-shaped combustor, rectangular collision injector, and quasi-equivalent mixture.
Result 1-3: Novel oblique detonation wave structure (forward tilting detonation wave) were observed in the disc-shaped RDE. The difference of these forward tilting oblique detonations wave is having compression region in the burned gas region.
Result 1-4: Computer fluid dynamics (CFD) calculation results show that the detonation propagation stability was strongly dependent on the jet angle of the injectors. From CFD analysis, in the case of 90 degree rectangular injection, the mixing length was shortest.
Result 1-5: Preliminary design of disc-shaped rotating detonation turbine engine was performed for confirming optimal pressure gain in the disc-shaped combustor.

Result 2-1: Double annular RDE combustor had higher characteristics exhaust velocity when the convergent nozzle was attached to the combustor.
Result 2-2: We made calculation models for the double annular and disc-shaped RDEs.
Result 2-3: We fabricated double annular RDE combustor and performed cold gas (air) operation.
Result 2-4: We performed preliminary combustion test of the RDE system with a centrifugal compressor and radial turbine.
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