INJECTION DEVICE, COMBUSTOR, AND ROCKET ENGINE

An injection device, a combustor and a rocket engine which are provided with an injection device body (21) that demarcates an oxidizer manifold (33) and a fuel manifold (34), and also provided with a plurality of injectors (22, 23, 24) that inject the fuel and the oxidizer into a combustion chamber...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	ISONO, Mitsunori, IKEDA, Kazufumi, MANAKO, Hiroyasu, WATANABE, Shinichiro, KAWASHIMA, Hideto
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING COMBUSTION APPARATUS COMBUSTION ENGINES COMBUSTION PROCESSES GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	An injection device, a combustor and a rocket engine which are provided with an injection device body (21) that demarcates an oxidizer manifold (33) and a fuel manifold (34), and also provided with a plurality of injectors (22, 23, 24) that inject the fuel and the oxidizer into a combustion chamber (12), and are arranged in the injection device body (21) with a prescribed interval interposed therebetween, wherein the plurality of injectors (22A, 22B, 22C, 22D) have: LOx channels (43a, 43b), the base end section of which is connected to the oxidizer manifold (33) and the tip end section of which is connected to the combustion chamber (12); diaphragm sections (45a, 45b) provided in the base end section of the LOx channels (43a, 43b); and GH2 channels (47a, 47b), the base end section of which is connected to the fuel manifold (34) and the tip end section of which is connected to the combustion chamber (12). Furthermore, the shape of each diaphragm section (45a, 45b, 45c, 45d) is different.