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**6** 

*Japan* 

**Control of LNG Pyrolysis and Application to** 

Rocket propellant has various requirements, such as higher specific impulse (Isp), large density, non-toxic, storablity, operational reliability and easy handling. In addition, large heat capacity of the fuel is also desirable. A regenerative cooling system is often adopted to cool a combustion chamber because of high combustion temperature (about 3000K), and high heat transfer rates from combustion gas. In the regenerative cooling system, the combustion chamber is a kind of a heat exchanger and fuel of a rocket engine is used as a coolant. The fuel heated in regenerative cooling passage is injected into the combustion chamber and burned. Heat loss from combustion gas to chamber wall is absorbed into the

Unfortunately, no propellant can satisfy all of those requirements. The requirements of higher Isp and larger thrust trade off each other. For example, Liquid hydrogen (LH2) has high Isp and "clean" propellant. In addition, hydrogen has large heat capacity, and thus, is favorable coolant for regenerative cooling. However, the molecular weight of hydrogen is the lowest among the all of chemical compounds, thus, it is difficult to obtain larger thrust by using LH2. For those reasons, LH2 is suitable for an upper staged rocket engine, rather than an booster staged one. Another disadvantage of LH2 is diffculity to handle because it is

The hydrocarbon fuels have been also widely used for rocket propulsion because they have advantages of non-toxic, lower cost, higher density and easier handling. RP-1 is the typical kerosene fuel for rocket propulsion, which was used for F-1 engien of Saturn 5. Kerosine can produce larger thrust than LH2, although it has a drawback of lower Isp. Therefore, kerosene fuel is suitable for a booster staged rocket engine. If kerosene fuel would be employed to the regenerative cooling system, the combustion chamber has fuel flow passage within its wall. The regenerative cooling combustion chamber plays role of heat exchanger. The temperature of fuel increases to begin the thermal decomposition and cause soot formation in the regenerative cooling fuel passage. The soot in the fuel passage can clog the fuel flow and deteriorate the heat transfer from a chamber wall to fuel. Thus, the rocket

Liqufied Natural Gas (LNG) is one of the hydrocarbon fuel and its main component is CH4. The volumetric fraction of CH4 typically ranges from 85% to 95%. The rest of them are etane

heat capacity of fuel and utilize them to propulsive work again. ( regeneration ).

cryogenic fluid (20K at tank) and easy to leak from the tank.

engine designers must pay attention to coking of hydrocarbon fuel.

**1. Introduction** 

**Regenerative Cooling Rocket Engine** 

R. Minato, K. Higashino, M. Sugioka and Y. Sasayama

*Muroran Institute of Technology* 

Exchangers. *International Journal of Heat and Mass Transfer*, Vol. 53, No. 7-8, (March 2010), pp. 1591-1602, ISSN 0017-9310

