並列タイトル等A Study of Air Breathing Rockets (IV) - Direct Fuel Injection into a Secondary Combustor -
タイトル（掲載誌）航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-832
一般注記In order to reduce secondary combustor length of an air breathing rocket, an experimental study on the effect of direct fuel injection into the secondary combustor was conducted. Fuel was injected from eighteen circular ports of two millimeters diameter on the combustor wall. Injection direction was normal to the wall. Gas composition and pressure were measured on the wall and in the exit plane of the secondary combustor. The results were compared with those obtained in experiments without direct fuel injection, where all the fuel for secondary combustion was supplied only by the exhaust of a primary rocket. Significant improvement in both mixing and secondary combustion performances was achieved by injection. Turbulence in the air stream produced by fuel injection enhanced mixing of the air stream and the rocket exhaust. Fuel injection also made fuel distribution uniform in a cross section of the secondary combustor. The degree of improvement was proportional to the injected fuel mass flow rate while the rate was low. As the mass flow rate of injectant became higher, the improvement was saturated.
資料番号: NALTR0832000
レポート番号: NAL TR-832
連携機関・データベース国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
提供元機関・データベース宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ