CPC F02K 9/64 (2013.01) [B33Y 80/00 (2014.12); F05D 2260/202 (2013.01); F05D 2260/203 (2013.01)] | 13 Claims |
1. A rocket engine section comprising:
a combustion chamber body having an inner wall, the inner wall extending along an axial direction and along a circumferential direction, the inner wall including a porous portion formed integrally with the inner wall and integrated into the inner wall;
at least two channels carrying a cooling medium, which both run on the outside and along the inner wall, the at least two channels are offset from one another; and
a plurality of supply lines fluidly connecting the at least two channels carrying the cooling medium and the porous portion, and adapted to allow the cooling medium carried in the at least two channels to pass from the at least two channels to the interior of the combustion chamber body via the porous portion;
wherein a porosity of the porous portion determines a volume flow rate and mass flow rate of the cooling medium allowed to pass into the interior of the combustion chamber body; and
wherein the porous portion provides different transpiration cooling effects along at least one of the axial direction and the circumferential direction by permitting different amounts of cooling medium to be supplied to different areas of the porous portion through the plurality of supply lines.
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