Patent ID: 7603843
Filing Date: 2009-10-20
Classification: F02K,F05D,Y10T

Abstract:
1. A rocket combustion chamber for expelling a hot gas stream from a rocket engine, the rocket combustion chamber defining a longitudinal axis and comprising: a rocket combustion chamber wall; and, a plurality of cooling channels arranged inside the rocket combustion chamber wall and configured to receive a flow of a cooling medium, each cooling channel defining a depth direction in a radial direction relative to the longitudinal axis and a substantially rectangular cross section with respect to the longitudinal axis wherein at least one cooling channel includes a plurality of elongated depressions configured to prevent a stratification of the cooling medium in the at least one cooling channel, wherein each of the plurality of elongated depressions defines a depression length disposed in the radial direction and a depression depth disposed perpendicular to the radial direction and perpendicular to the longitudinal axis, and wherein the at least one cooling channel includes web walls and wherein the elongated depressions are provided in the web walls.