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LEV-3 V2 missile gyroscope system with mounting plate. The third component of this system, the Muller gyroscopic accelerometer, is missing – the 2x mounting points can be seen on the right-hand side of the mounting plate.

Photo shows cast aluminium thrust ring with electro-hydraulic servos in position. Note different crank lever shapes (pale green arm on servo) for fins 1/3 and 2/4 This excellent restoration is the work of Horst Beck. Photo copyright: The Horst Beck Collection

Photo shows restored air-rudder and fin detail. The grey painted barrel-strainers are both adjusted independently to reduce slack in the drive chain and avoid introducing a deflection bias in the air rudder. The 1.9kg counterbalance weight normally located at the top of the trim fin (or air rudder) is missing in this presentation. This excellent restoration is the work of Horst Beck. Photo copyright: The Horst Beck Collection

Photo shows four restored graphite jet vane support blocks and bearing housings. The round plates we can see here act as heat sinks and allow heat to radiate away from the support block and bearing to help prevent expansion due to relatively rapid and uneven temperature distribution accumulation. The graphite vanes were quite brittle and cracking caused by rapid and uneven expansion could cause the vane to disintegrate. The area around the graphite vanes was exposed to the accumulation of heat not merely as a result of duration of the motor burn time but temperature was also increased at higher rates as the jet plume expanded with the decreasing atmospheric pressure as the missile gained altitude. This excellent restoration is the work of Horst Beck. Photo copyright: The Horst Beck Collection

Image shows allied soldier examining remains of V2 rocket turbo-pump after impact. The soldier is holding the steam turbine rotor – the large size of this part is well shown in this photo. The still lagged steam inlet manifold can be seen in the left foreground and the LOX outlet manifold (and valve, topmost) can be seen in the lower right corner.

Picture shows tubo-pump debris from impact site. LOX manifold clearly seen (3 in 1 outlet pipes, upper center of image – the one to its right, 2 o’clock position, and left, 11 o’clock position are both broken off).The LOX flow electric control valve is also well displayed in this image (LOX valve head is slightly low and left of center, part nearest camera). The electrical connection to the LOX valve has broken away leaving its empty socket pointing upwards and to the right.

A4 missile steam generator detail. This excellent presentation was rebuilt from original refurbished parts by Horst Beck. See our video article The V2 Rocket Turbo-Pump for a technical exposition of the parts shown in this photo. Image courtesy The Horst Beck Collection

Klein Schanzlin & Becker electric centrifugal-pump advert.

Early belt powered centrifugal pump by Klein Schanzlin & Becker. This schematic shows an early 20th century centrifugal pump designed and manufactured by KSB. The drawing appears to show auto-purge pathways at points marked C as well continuous lubrication pathways at B. Both of these important ideas would later feature in the propellant pump of the A4-V2 missile.

Trade advertisement for Klein Schanzlin & Becker (KSB supplier code ebb). KSB were the primary contractor for A4-V2 missile’s steam turbine driven dual propellant pump system.

Large industrial volute case centrifugal pump by Klein Schanzlin & Becker. This image highlights the ‘genetic’similarity and family resemblance between KSB’s current and historical product range and the visible features of the A4-V2 missile Turbo-Pump (TP). Apart from the general shape of the cast spiral-volute case and its connection flanges, the ‘soft’ shaft connection (disk with holes on the extreme left of the pump) is very reminiscent of the semi-flexible shaft connection point linking one side the steam turbine rotor shaft to the shaft carrying a propellent pump rotor seen in the A4-V2 missile TP. Family photo? Industrial volute case centrifugal pump by KSB

Cover of catalogue published in 1880 showing the KSB product range

This image shows a cutaway of an A4-V2 turbo-pump. The section reveals the Curtis type 2-stage steam-turbine rotor and you can also see part of the stater inserted between the blades (bottom middle) and the adjacent steam distribution pipe (black open pipe on stater’s immediate left). Top left, a centrifugal pump rotor can be seen – cut through, it shows a multi-splined shaft running through the centre, simple bearing and end-cap.

Electric industrial volute case centrifugal pump by Klein Schanzlin & Becker. This image highlights the ‘genetic’similarity and family resemblance between KSB’s current and historical product range and the visible features of the A4-V2 missile Turbo-Pump (TP). Assembly is shown being spray painted.

A Stoff (liquid oxygen) pump casing diagram showing stress points that require X ray quality control photography before use. The diagram shows the specific locations where photographic film is to be placed for X-ray analysis.

In this diagram the V2 Turbo-pump is shown in a cutaway presentation and rotated 90 degrees counter clockwise. The B stoff (fuel) pump is nearest the viewer – the over-speed device can be seen on the B stoff pump’s case end-plate. The low pressure inlet ports our shown to the left, and high-pressure outlet ports are on the right. The steam distribution manifold can be seen at the furthest point from the viewer – the steam inlet pipe flange can also be seen. The feed pipe from the steam generator attaches to thus flange.

This mpe* drawing from 1945 shows the individual steam buckets or blades (labeled A and C) mounted to the rim of the rotor disk. As well as the fixed (i.e. stationary) stater blade B, positioned such that blades A & C can pass either side of it. The steam expansion is well shown by the increasing surface area of the blades from A to C, and growing larger, from left where the high pressure super heated steam enters the turbine, to right where it exits the blade pathway and passes in to the exhaust outlet. The lower graphic shows the way the super-heated high pressure steam is passed from the initial A blade and deflected by the reversed B stator blade for its energy to to be harvested for a second time by the C rotor blade. * mpe is the secret three letter armament code for Karlshagen, Werk Nord (North Works).

This HVP technical drawing from October 1940, shows a proposal from the Oddesse company – the full title of this company is KLEIN SCHANZLIN ODDESSE GmbH. Klein, Schanzlin & Becker A.G. (waffenamt code: ebb) took over Oddessa in 1929 and the company became formally known as KLEIN SCHANZLIN-ODDESSE GmbH (code ebc) in 1939. (NB: The company name has nothing to do with a similar sounding place name Odessa. The Oddesse trading name was formed from the partnership of English engineer Oddie, and German businessman Hesse.). The dual centrifugal turbo-pump shown in the drawing is a variant of a high pressure fire-fighting pump manufactured by Oddesse. Note the off-center outflow ports – not also that the outlet flanges are still level at this stage. Note also the incorrect spelling of the company name in the details panel lower right. (Digipeer.de image)

Another HVP technical drawing from later in October 1940, shows further data from the KLEIN SCHANZLIN ODDESSE (ebc) company A4-V2 turbo-pump project. See previous image for company details. The dual centrifugal turbo-pump shown in the drawing is a variant of a high pressure fire-fighting pump manufactured by Oddesse. Note the off-center outlet ports. Note also the corrected spelling of the company name in the details panel lower right (see previous Oddesse image) and the small note below the top table that indicates that the pumps are from Oddesse (ODD) and the turbine from a company indicated as SSW. (Digipeer.de image)

Signatur FA 014/21241 (Digipeer.de image)

V2 rocket turbo-pump preliminary dimension sheet for O series, drawing. Many of the final elements of the turbo-pump design can be seen in this ‘preliminary’ drawing and table form 1941. The word lieferfirma in the data box btm right mean supply company – and this is indicated to be KSB or Klein Schanzlin & Becker AG, Frankenthal. Signatur FA 014/14769
(Digipeer.de image)

Centrifugal impeller for A or liquid oxygen (LOX) pump. The drawing originated in Aug 1943 and was superseded in December 1944. A key to the image hatching can be seen with the label ‘Hochbeansprucht’ which in English means Highly Stressed. Next to the drawing numbers two secret three letter armament codes can be seen indicating the ‘origination’ of the document. The top one mpe = Heimat Artillerie Park 11 (HAP or Army Artillery Range). The lower code ebb = Klein Schanzlin & Becker AG, Frankenthal.
Signatur FA 014/02542 (Digipeer.de image)

Signatur FA 014/02537
Abmessungen: 42,9×59,8

Signatur FA 014/02534
Abmessungen: 60,5×82,9

Photo showing Werk Süd with IW on the left and F1 on the right taken on 19th August 1943. The photo shows only light damage to the main halls, although F1 was actually hit at least 11 times, and hits to the separate single storey workshops to the right of the IW hall. The long storage (oil and paint?) shed above IW and the woodworking shop at the top of the picture appear undamaged. Anti-aircraft platforms (at least 3) can be seen on the roof of IW but that seem to be empty of guns. F1 shows two AAA platforms (there was at least 3 at this stage and maybe more) and they may have guns installed. General W. Dornberger mentions defensive AA artillery fire from the from the roof of F1 in his 1952 book V2 (1954 in English).

The remains of the a rail and truck loading stage located in the long oil storage shed adjacent to the IW repair and maintenance hall (IW R&MH) are substantial and have intact steadying chains along the south edge of the platform. There are access steps to the west and east ends (east shown). This loading stage was originally furnished with a wooden platform.

Bomb damaged F1 factory 1945. The huge V2 rocket factory shown badly damaged by air attack at the end of the war in May 1945

A rare photo of the giant F1 production hall taken not long after the RAF raid of 17/18th August 1943. F1 was a forced labour camp with at least 600 prisoners living within the factory and at least eleven were killed in the raid. Parts of the electrified barbed wire fence can be seen close to the factory building, in the clearing in the middle of the photo. Two anti aircraft gun emplacements can be seen on the roof at the front of the building. Holes in the side walls of the upper vaults can be seen as well as the damage to lower vaults 9 and 10 (counting from left) from a direct hit in this region. Also of note are the numerous guy ropes, attached to the upper roof of the front of the building – and running down towards the trees, that are just visible in the photo. These may be supports for camouflage netting that was in the process of being fitted (by prisoner gangs) just before the raid. The work was never completed.

Peenemünde: Werk Sud attacked by US bombers August 1944 in a daring daylight raid. The two large halls F1 and IW in the lower middle of the photo are under direct attack and smoke can be seen originating from both buildings. Although the August 1944 raids did little to interrupt the volume manufacture of the V2, as virtually all manufacturing and assembly of the missile had moved to central Germany, the raids did bring to an almost complete halt the last small amount of manufacturing work still competed in the giant halls of Werk Sud.

Image shows a correctly formed nebular cone attended by a fine mist. the four injector cooling jets are well shown, and although fluid beading can be seen on the face of the injector, there is insufficient liquid to cause dripping.

3305D injector insert showing comparison nebular and jet stream pattern with high and low pressure. Top image shows correct hollow cone-shaped aerosol effect, from central 6mm orifice, that is also creating a fine mist around and within the cone, and steady steams emanating from cooling pores. Bottom image shows the effect of reduced pressure: a dropping poorly formed cone, composed of larger slower moving droplets, and a tendency for the thicker spray to combine and cause ‘dribbeling’ with much fluid failing to clear the injector face – unlike the image above, where the injector face is clear of drips.

3305D fuel njector insert showing comparison nebular and jet stream pattern with high and low pressure. Left image shows correct hollow cone-shaped aerosol effect from central 6mm orifice, that is also creating a fine mist around and within the cone, and 4 steady steams emanating from cooling pores. Right image shows the effect of reduced pressure: a dropping poorly formed cone, composed of larger slower moving droplets, and a tendency for the thicker spray to combine and cause ‘dribbeling’ with much fluid failing to clear the injector face.

3305D fuel injector insert showing swirl cone nebular, and 4 steady steams emanating from cooling pores.

3304D higher volume injector insert (with central jet) showing comparison nebular and jet stream pattern with high and low pressure. Top image shows correct hollow cone-shaped aerosol effect from central 6mm orifice, that is also creating a fine mist around and within the cone, and strong single central (non-swirl) jet can be seen as well as 4 steady steams emanating from cooling pores. Bottom image shows the effect of reduced pressure: a dropping poorly formed cone, composed of larger slower moving droplets, and a tendency for the thicker spray to combine and cause ‘dribbeling’ with much fluid failing to clear the injector face. The appearance of central jet however seem largely unchanged.

3304D higher volume fuel injector insert (with three inlet apertures: 2 swirl, 1 jet) showing swirl cone nebular, steady central jet, and 4 steady steams emanating from cooling pores.

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

3305D injector insert showing larger low-velocity droplets and ‘dribbly’ performance due to insufficient pressure. The cone shaped aerosol is not functioning. Broken streams can be seem emanating from the four cooling pores.

Single fuel injector water test rig showing a 3305D bress insert about to be tightened home using a pin-wrench. V2RH image

Single nozzle insert test rig used by V2 Rocket History to test spray shape and volume at supply pressures consistent with fuel pressures specified for the injector head of summer 1944. The test system features an adjustable pressure regulator and fluid pressure gauge. For test purposes the device was simply connected to a relatively high pressure mains water supply. And although water does not have the same viscosity of the 75% Ethenol to 25% water mix of the V2’s fuel it was considered close enough by the German technicians, who regularly used plain water as a substitute when testing issues related to furl flow rather than combustion. A 2131E fuel injector insert is shown installed in the holder at the front of the rig, but as the thread was the same on all inserts the nozzle can be changed for other models easily with aid of a pin spanner. See video for a demonstration of this simple test system.

Single nozzle insert test rig used by V2 Rocket History to test spray shape and volume at fluid supply pressures consistent with fuel pressures specified for the injector head of summer 1944. A 2131E fuel injector insert is installed in the holder at the front of the test rig, but as the thread was the same on all inserts the nozzle can be changed for other models easily with aid of a pin spanner. See video for a demonstration of this simple test system.

The chart shows water delivery in litres per minute per injector

V2 rocket engine fuel injector inserts – a part of our collection used for the water tests with various types shown. The tool shown is a pin-wrench used to fit the inserts into the test apparatus. V2RH collection image

Standard fuel injector inserts for production series 18-pot injector head. Insert 1 (3304D/3305D) shows four thin wires demonstrating the angles of all four ‘cooling’ pores. Insert 2 (3305D/2131E) has two 1.3mm twist drill showing the edge bores for the gyroscopic swirl inlets. Insert 3 (3305D) shows another view of the cooling pore angle and origin. V2RH image

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.

Fuel injector inserts for production series 18-pot injector head showing general shape and thread position. For further details see associated image. The lowermost insert have been halved to reveal the cavity shape, orifice edge, inlet and cooling apertures. V2RH image