![]() ![]() Solid Domain (Thrust chamber wall) - Conduction heat transfer Liquid Domain (Coolant) - Convection heat transfer Gas Domain (Combusted Gases) - Convection and Radiation heat transfer Heat transfer and structural characteristics are excellent.īasically there are three domains in a regenerative cooled rocket engine. One solution has been " channel wall" thrust chambers, so named because the hot gas wall cooling is accomplished by flowing coolant through rectangular channels, which are machined or formed into a hot gas liner fabricated from a high-conductivity material, such as copper or a copper alloy. But as chamber pressures and hot gas wall heat fluxes have continued to increase (>100 atm), still more effective methods have been needed. The primary advantage of the design is its light weight and the large experience base that has accrued. These chamber designs have been successfully used and several other Air Force and NASA rocket engine applications. This led to the design of " tubular wall" thrust chambers, by far the most widely used design approach for the vast majority of large rocket engine applications. It became necessary to design new coolant configurations that were more efficient structurally and had improved heat transfer characteristics. The coolant with the heat input from cooling the liner is then discharged into the injector and utilized as a propellant.Įarlier thrust chamber designs, had low chamber pressure, low heat flux and low coolant pressure requirements, which could be satisfied by a simplified " double wall chamber" design with regenerative and film cooling.įor subsequent rocket engine applications, however, chamber pressures were increased and the cooling requirements became more difficult to satisfy. Regenerative cooling is the most widely used method of cooling a thrust chamber and is accomplished by flowing high-velocity coolant over the back side of the chamber hot gas wall to convectively cool the hot gas liner. Most of this heat is expelled along with the gas that contains it however, heat is transferred to the thrust chamber walls in quantities sufficient to require attention. The heat created during combustion in a rocket engine is contained within the exhaust gases.
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