Regenerative cooling (rocket)
|This article needs additional citations for verification. (February 2015)|
Regenerative cooling, in the context of rocket engine design, is a configuration in which some or all of the propellant is passed through tubes, channels or in a jacket around the combustion chamber or nozzle to cool the engine. This is effective because the fuel (and sometimes the oxidizer) are good coolants. The heated propellant is then fed into a special gas generator or injected directly into the main combustion chamber for combustion there.
1857 - Siemens introduced the Regenerative cooling concept. On 10 May 1898, James Dewar used regenerative cooling to become the first to statically liquefy hydrogen. The concept of regenerative cooling was also mentioned in 1903 in an article by Konstantin Tsiolkovsky. Robert Goddard built the first regeneratively cooled engine in 1923, but rejected the scheme as too complex. A regeneratively cooled engine was built by the Italian researcher, Gaetano Arturo Crocco in 1930. The first Soviet engines to employ the technique were Fridrikh Tsander's OR-2 tested in March 1933 and the ORM-50, bench tested in November 1933 by Valentin Glushko. The first German engine of this type was also tested in March 1933 by Klaus Riedel in the VfR. The Austrian scientist Eugen Sänger was particularly famous for experiments with engine cooling starting in 1933; however, most of his experimental engines were water-cooled or cooled by an extra circuit of propellant.
The V-2 rocket engine, the most powerful of its time at 25 tons (245 kN) of thrust, was regeneratively cooled, in a design by Walter Thiel, by fuel lines coiled around the outside of the combustion chamber. This was an inefficient design that required the burning of diluted alcohol at low chamber pressure to avoid melting the engine. The American Redstone engine used the same design.
A key innovation in regenerative cooling was the Soviet U-1250 engine designed by Aleksei Mihailovich Isaev in 1945. Its combustion chamber was lined by a thin copper sheet supported by the corrugated steel wall of the chamber. Fuel flowed through the corrugations and absorbed heat very efficiently. This permitted more energetic fuels and higher chamber pressures, and it is the basic plan used in all Russian engines since. Modern American engines solve this problem by lining the combustion chamber with brazed copper or nickel alloy tubes (although recent engines like in the RS-68 have started to use the Russian technique which is cheaper to construct). The American style of lining the engine with copper tubes is called the "spaghetti construction", and the concept is credited to Edward A. Neu at Reaction Motors Inc. in 1947.
Heat flow and temperature
The heat flow through the chamber wall is very high; 1-20 MW/m2 is not uncommon.
The amount of heat that can flow into the coolant is controlled by many factors including the temperature difference between the chamber and the coolant, the heat transfer coefficient, the thermal conductivity of the chamber wall, the velocity in the coolant channels and the velocity of the gas flow in the chamber or the nozzle.
Two boundary layers form; one in the hot gas in the chamber and the other in the coolant within the channels.
Very typically most of the temperature drop occurs in the gas boundary layer since gases are relatively poor conductors. This boundary layer can be destroyed however by combustion instabilities, and wall failure can follow very soon afterwards.
The boundary layer within the coolant channels can also be disrupted if the coolant is at subcritical pressure and film boils; the gas then forms an insulating layer and the wall temperature climbs very rapidly and soon fails. However, if the coolant engages in nucleate boiling but does not form a film, this helps disrupt the coolant boundary layer and the gas bubbles formed rapidly collapse; this can triple the maximum heat flow. However, many modern engines with turbopumps use supercritical coolants, and these techniques can be seldom used.
With regenerative cooling, the pressure in the cooling channels is significantly above the chamber pressure hence the inner liner is under compression, while the outer wall of the engine is under significant hoop stresses.
The metal of the inner liner is greatly weakened by the high temperature, and also undergoes significant thermal expansion at the inner surface while the cold-side wall of the liner constrains the expansion. This sets up significant thermal stresses that can cause the inner surface to crack or craze after multiple firings particularly at the throat.
In addition the thin inner liner requires mechanical support to withstand the compressive loading due to the propellant's pressure, this support is usually provided by the side walls of the cooling channels and the backing plate.
The inner liner is usually constructed of relatively high temperature, high thermal conductivity materials; traditionally copper or nickel based alloys have been used.
Three different construction techniques have been used for regenerative cooling; a corrugated metal sheet is sometime brazed between the inner and outer liner; hundreds of pipes are sometimes brazed into the correct shape, or the inner liner is sometimes milled with cooling channels and an outer liner is used around that.
- "LIQUID HYDROGEN AS A PROPULSION FUEL, 1945-1959". NASA History program Office. History.nasa.gov. Retrieved 9 August 2014.
- "What is Film Cooling?". Me.umn.edu. Retrieved 2015-02-24.
- Andrew Nowicki (2005-01-07). "sci.space.tech: Curtain cooling with molten salt". Sci.tech-archive.net. Retrieved 2015-02-24.
- George P. Sutton (November–December 2003). "History of Liquid-Propellant Rocket Engines in Russia, Formerly the Soviet Union" (PDF). JOURNAL OF PROPULSION AND POWER (Pdf.aiaa.org) 19 (6).