A turbomolecular pump is a type of vacuum pump, superficially similar to a turbopump, used to obtain and maintain high vacuum.

When a turbopump is stopped, the oil from the backing vacuum may backstream through the turbopump and contaminate the chamber.

The purpose of a turbopump is to produce a high pressure fluid for feeding a combustion chamber or other use.

A turbopump can comprise one of two types of pumps: centrifugal pump, where the pumping is done by throwing fluid outward at high speed ; or axial flow pump, where alternating rotating and static blades progressively raise the pressure of a fluid.

The original liquid hydrogen turbopump is similar in size to an automobile engine ( weighing approximately ) and produces 72, 000 hp ( 53. 6 MW ) for a power-to-weight ratio of 153 kW / kg ( 93 hp / lb ).

The pneumatic system is nowadays often replaced by a computer-controlled turbopump.

Many jet engines, including rocket engines use a turbopump which is a centrifugal pump usually propelled by a gas turbine or in some cases a ram-air device ( particularly in ramjet engines which lack a shaft ).

* staged combustion cycle – the high pressure outlet from the turbopump is fed back to power a burner which then powers the turbopump in a self starting cycle.

Owing to inertia, if the speed of the vehicle suddenly increases, the fuel inside the fuel tank tends to ' fall behind ' and is forced into the turbopump, a situation somewhat similar to the slosh of liquid inside a tanker.

Like the RB545, the SABRE design is neither a conventional rocket engine nor jet engine, but a Precooled Hybrid Air Breathing Rocket Engine that burns liquid hydrogen fuel combined with an oxidant of either compressor-fed gaseous air or stored liquid oxygen fed using a turbopump.

* The propellant utilization ( PU ) valve was an electrically operated, two-phase, motor-driven, oxidizer transfer valve and is located at the oxidizer turbopump outlet volute.

The Merlin LOX / RP-1 turbopump was developed and is manufactured by Barber-Nichols.

A gas-generator cycle can also specifically refer to a way of designing a turbopump-fed liquid rocket engine, where some of the propellant is burned to drive the turbopump, and the exhaust is dumped overboard ( usually through a nozzle ) instead of being fed into the main combustion chamber.

** Though one division of the ECCS does not have high pressure flood ( HPCF ) capacities, there exists a steam-driven, safety-rated reactor core isolation cooling ( RCIC ) turbopump that is high-pressure rated and has extensive battery backup for its instrumentation and control systems, ensuring cooling is maintained even in the event of a full station blackout with failure of all 3 emergency diesel generators, the combustion gas turbine, primary battery backup, and the diesel firewater pumps.

The V-2 rocket used a circular turbopump to pressurize the propellant.

Gas turbines are also used in many liquid propellant rockets, the gas turbines are used to power a turbopump to permit the use of lightweight, low pressure tanks, which saves considerable dry mass.

*** propellant feed, turbopump type

combustion chamber to leak into the fuel system through the injector head before full propellant pressure was obtained from the turbopump.

Both propellant bleed valves were mounted to the bootstrap lines adjacent to their respective turbopump discharge flanges.

Prior to engine restart, the stage ullage rockets were fired to settle the propellants in the stage propellant tanks, ensuring a liquid head to the turbopump inlets.

The transition from vacuum to nitrogen and from a running to a still turbopump has to be synchronized precisely to avoid mechanical stress to the pump and overpressure at the exhaust.

The failure was suspected to be due to a failing turbopump bearing, causing the liquid oxygen pump to stop.

The gas generator itself was welded to the fuel pump turbine manifold, making it an integral part of the fuel turbopump assembly.

The valve in its open position depressed the speed of the oxygen pump during start, and in its closed position acted as a calibration device for the turbopump performance balance.

Three minutes and 31 seconds into the ascent, one of the center engine's two high pressure fuel turbopump turbine discharge temperature sensors failed.

One static and two dynamic seals in series prevented the turbopump oxidizer fluid and turbine gas from mixing.

The mission was again postponed when, during prelaunch external tank loading, a transducer on high-pressure oxidizer turbopump for main engine number three showed readings out of specification.

* gas generator cycle – a small percentage of the propellants are burnt in a preburner to power a turbopump and then exhausted through a separate nozzle, or low down on the main one.

Engine number 2036 featured the new high-pressure liquid oxygen turbopump, a two-duct powerhead, baffleless main injector, single-coil heat exchanger and start sequence modifications.

An alternative design, called a gas-generator cycle, exhausts the turbopump driving gases separately from the main combustion chamber, which leads to a few percent of loss of efficiency in thrust.

This was used to drive the main turbopump to pressurize the LOX-ethanol propellants.

# Close the oxidizer turbine bypass valve ( a portion of the gases for driving the oxidizer turbopump were bypassed during the ignition phase )

Environmentally, the turbopump was required to withstand temperatures ranging from input gas at 1, 500 ° F ( 816 ° C ), to liquid oxygen at − 300 ° F (− 184 ° C ).

The exhaust from the turbopump was fed into the nozzle extension by a large, tapered manifold ; this relatively cool gas formed a film which protected the nozzle extension from the hot ( 5, 800 ° F, 3, 200 ° C ) exhaust gas.

Power for operating the oxidizer turbopump was provided by a high-speed, two-stage turbine which was driven by the exhaust gases from the gas generator.

The turbines of the oxidizer and fuel turbopumps were connected in a series by exhaust ducting that directed the discharged exhaust gas from the fuel turbopump turbine to the inlet of the oxidizer turbopump turbine manifold.

Beginning the turbopump operation, hot gas entered the nozzles and, in turn, the first stage turbine wheel.

Bleeding off the turbine exhaust allows for a higher turbopump output by decreasing backpressure and maximizing the pressure drop through the turbine.

Power for operating the turbopump was provided by a high-speed, two-stage turbine.

Eutelsat II F5 and Turksat 1A were destroyed in a launch failure when the third stage turbopump of the Ariane 4 rocket that was carrying both satellites failed.

The fuel turbopump, mounted on the thrust chamber, was a turbine-driven, axial flow pumping unit consisting of an inducer, a seven-stage rotor, and a stator assembly.

The oxidizer turbopump was mounted on the thrust chamber diametrically opposite the fuel turbopump.

It was mounted between the fuel high-pressure duct from the fuel turbopump and the fuel inlet manifold of the thrust chamber assembly.

It was mounted between the oxidizer high-pressure duct from the oxidizer turbopump and the oxidizer inlet on the thrust chamber assembly.