| 摘要 |
The invention relates to a combustion chamber ( 1 ) for a rocket engine, which is used to expel a hot gaseous stream, said combustion chamber ( 1 ) having cooling channels ( 2 ) that are traversed by a coolant. According to the invention, the cooling channels ( 2 ) have a substantially right-angular cross-section and at least some of said channels ( 2 ) comprise depressions ( 6 ), which prevent the stratification of the coolant in the channels ( 2 ). The depressions are formed by the drilling of bores in the combustion chamber wall prior to the production of the cooling channels.
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