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Sectioned general assembly view of the V2 turbo-pump (TP) dated September 1942. This image has been edited to show TP and document data closer together than the original.

A complete V2 rocket turbo-pump on public display in the USA at the Smithsonian National Air and Space Museum in Washington DC showing Klein Schanzlin & Becker’s wartime contractor armament code – ebb. Smithsonian National Air and Space Museum exhibit.

V2 rocket turbo-pump from a missile fired from Walcheren, Serooskerke, Vrederust, by battery no 444, at around 7am on September 17th 1944. The missile impacted East Ham with a direct hit on houses. Killing 6 people with 15 seriously injured. Much of the rocket debris was taken to the East Ham police station for examination by the military authorities. The serviceman in the picture is feeling the steam inlet manifold as it is still warm to the touch. Information porovided by www.v2rocket.com.

This photo shows a presentation of important vales from the A4-V2 missile. From the left: Main alcohol/B stoff valve (from the centre of injector head. Alcohol tank valve. Main LOX valve (with sub valve). Alcohol (B stoff) tank pressuring valve. Image courtesy Horst Beck Collection

Trade literature advert for the Preschona company (Adolf Meyer) in Berlin, Germany. The company was a supply contractor and (among other items) manufactured the non-return valve for the steam turbine exhaust heat exchanger, employed to volatilise a small portion of liquid oxygen (LOX) to pressurise the LOX tank to maintain critical flow volume to the LOX turbo-pump.

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

Brass liquid oxygen (LOX) spray nozzle.Note: the thread is shown in simplified graphic form. 3D model by Alexander Savochkin

Brass liquid oxygen (LOX) spray nozzle. Note: the thread is shown in simplified form. 3D model by Alexander Savochkin

One of the 18 liquid propellant (LOX and fuel) diffuser cups, showing three rows or echelons (A,D,& E) of brass injector inserts as well as two rows of drilled fuel feed holes. The LOX spray head is shown in the centre. 3D model by Alexander Savochkin

Cutaway showing echelon A with 2-part 2131E fuel injector inserts at the top of a propellant diffuser cup. Note the close proximity of the injector inserts to the simple ‘watering can’ type LOX spray head. One row of drilled fuel feed holes can be seen below the inserts. 3D model by Alexander Savochkin

This images shows a cutaway of a burner cup from outer Ring I of the injector head and shows injector insert eschelon D, & E as well as one row of drilled feed holes. Three fuel injector insert types can be seen: Top D, = 3303D (white), lower E, = 3304D (red), and E, = 3305D (blue). 3D model by Alexander Savochkin

This images shows a burner cup from outer Ring I of the injector head and the cutaway shows injector insert eschelon A,D, & E as well as two rows of drilled feed holes. Four fuel injector insert types can be seen: Top, A = 2131E, lower D, = 3303D (white), lowest E, = 3304D (red), and E, = 3305D (blue). 3D model by Alexander Savochkin

General view of the propellant diffuser cup inner core. The swirl caps of fuel injector inserts in positions A,D,& E can be seen clearly on the outside of the core as well as the central holes in the 3304D (red) inserts.The two rows of drilled fuel feed holes are also well shown. 3D model by Alexander Savochkin

Close-up detail showing independent pathway for fuel passing into injector head and fuel passed down from the head to be used for veil cooling system. Fig. A shows vertical passages for overall fuel feed to the head and Fig.B shows horizontal pathway for veil coolant fed from the head via the veil coolant distributor ring or manifold. 3D model by Alexander Savochkin

Underside view of injector head showing liquid propellant (LOX and fuel) diffuser cups, (see other images for insert and position nomenclature). Of note in this image are the pointing angles of the cups, positioned on a parabolic section to focus the propellant nebular stream into the central axis of the combustion space. Also of note are the large areas between each cup NOT employed in the injection process – initiating ‘clumpy’ and uneven propellant mixing initially below the injector face but also carried forward into the combustion space. The LOX spray head is shown in the centre of each cup. 3D model by Alexander Savochkin

Inverted view of injector head showing liquid propellant (LOX and fuel) diffuser cups, (see other images for insert and position nomenclature). Of note in this image are the pointing angles of the cups, positioned on a parabolic section to focus the propellant nebular stream into the central axis of the combustion space. Also of note are the large areas between each cup NOT employed in the injection process leading to structured propellant mixing as opposed to even homogeneous mixing. The four veil cooling inlet connectors are well shown. 3D model by Alexander Savochkin

View of injector head showing 18 liquid propellant (LOX and fuel) diffuser cups and head fuel valve seating ring at centre, (see other images for insert and position nomenclature). Visible immediately below the valve seat are the large connecting holes that allow fuel to flow from the inlet manifold and cooling jacket to the injector space (some brass injector inserts can be seen through the holes) after the head fuel valve is released to be opened by the turbo-pump supply pressure. The four veil cooling inlet connectors are well shown as are two of the outlet connection holes immediately above them. 3D model by Alexander Savochkin

View of the top of the injector head, with outer cups and pressed steel capping piece removed, showing, propellant diffuser inner cores with injector inserts and LOX supply pipe connection thread. The LOX spray head can be seen inside the LOX pipe connector. The swirl caps of fuel injector inserts in positions A,D,& E can be seen clearly on the outside of the cores and the two rows of drilled fuel feed holes are also well shown. 3D model by Alexander Savochkin

Another view of injector head showing liquid propellant (LOX and fuel) diffuser cups and head fuel valve seating ring at centre, (see other images for insert and position nomenclature). Visible immediately below the valve seat are the large connecting holes that allow fuel to flow from the inlet manifold and cooling jacket to the injector space (some brass injector inserts can be seen through the holes) after the head fuel valve is released to be opened by the turbo-pump supply pressure. The four veil cooling inlet connectors are well shown as are two of the outlet connection holes immediately above them. 3D model by Alexander Savochkin

A close-up view of the head fuel valve mounting flange (showing 12 fastener holes). Visible immediately below the top flange are the large connecting holes that allow fuel to flow from the inlet manifold and cooling jacket to the injector space (some brass injector inserts can be seen through the holes) after the head fuel valve is released to be opened by the turbo-pump supply pressure.

Exploded view showing some of the 1100 parts required for the complicated 18-pot injector head of the V2 25-ton thrust rocket engine. 3D model by Alexander Savochkin

Here the 18-pot head model has been cutaway to show the fuel cooling and fuel delivery spaces. the cooling jacket layer can be seen in the lowermost area of the head – below the centrally positioned fuel valve seat, between each cup at the lowest point, and ruining down toward the first set of veil cooling pores and the topmost coolant distributor ring. Note that the veil cooling system does not communicate with the regenerative cooling jacket and has its own feed pipes drawing fuel from the head injector space and not the cooling space. Visible immediately above the valve seat are the large connecting holes that allow fuel to flow from the inlet manifold and cooling jacket to the injector space after the head fuel valve is released to be opened by the turbo-pump supply pressure. 3D model by Alexander Savochkin

Liquid propellent (LOX and fuel) diffuser cup, showing three rings or echelons (A,D,& E) of brass injector inserts as well as two rows of drilled fuel feed holes. The LOX spray head is shown in the centre. Note the simple ‘shower head or watering can’ design of the LOX diffuser. A sealing washer can be seen fitted between the LOX diffuser and the steel cup. 3D model by Alexander Savochkin