Each burner cup of the V2 rocket engine injector system has forty-four brass inserts, but each cup also has twenty-four 2mm diameter plain holes, 30 deg apart, drilled into the cup’s central wall. To mimic this for testing purposes, we created a brass insert that has a base with just a 2mm central hole. The base is sized to be consistent with the 4 to 5mm cup wall. V2RH image
Album: Testing fuel injectors
Categories: Combustion
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Sample set of 3303D type fuel injector inserts that were found in Peenemünde in part of a group that were bunched together in a space about 300mm in diameter with the remains of packaging. They appear to be manufacturing samples and and some have been graded with numbers 1,2,3, as well as with red and white paint to show the burner cup echelon position (C or D). Five different manufacturers are represented in this group. V2RH collection image
Album: V2 rocket fuel injector inserts
Categories: Combustion
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The injector head fragment shown here, is from an 4B 1000 kg thrust engine that was developed at Kummersdorf in 1938/39 by Dr Walter Thiel’s combustion research group. The fragment, clearly the remains of an explosion, was actually found in a scrap pile in Peenemüde but the engine was probably tested (and destroyed) at the Kummersdorf army testing station. V2RH collection image.
Album: V2 rocket fuel injector inserts
Categories: Combustion V2 Missile relics
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Photo shows a small section of the burner cup with row A (2131E) fuel injector inserts with three row B drilled holes below. The two undamaged inserts carry the armament code ‘csl’. The relic was found near a workshop in the Development works Pennemünde. Slag from the cutting flame and damage to the inserts at both ends of the relic would indicate that the section was cut from a steel burner cup using a gas cutter (fuel and oxygen) for purposes unknown. V2RH collection image
Album: V2 rocket fuel injector inserts
Categories: Combustion Electrical connection V2 Missile relics
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V2 Fuel Injector insert: part code 2131E from injector pot echelon A (nearest to LOX spray head). The push-together two part construction of the insert is shown here. The two parts were pushed together in a specially shaped tool set that compressed the thin skirt on the female part into a recess cut into the male part. The failure test for this component required that the mated parts resist a separating force of 300kg. The two part design was dictated by the small size of the 2mm exit orifice and the funnel shaped introduction to the exit orifice. In the case of the other three standard inserts, the large 6mm exit orifice allowed a sub 6mm milling cutter, with a thin support shaft and a top chamfer, to be used in such a way that the area below the exit orifice could be undercut to create an injector cavity with a diameter larger than the 6mm entry point.
Album: V2 rocket fuel injector inserts
Categories: Combustion
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Copyright: V2 Rocket History
