Patent ID: 8938970
Filing Date: 2015-01-27
Classification: F23R

Abstract:
1. A gas turbine combustion chamber comprising: a combustion chamber wall forming a combustion chamber; a combustion chamber head, into which cooling air can be introduced; a heat shield positioned between the combustion chamber head and the combustion chamber; a base plate having an outer rim area that is connected to a surface of the combustion chamber wall to define a forward end of the combustion chamber, the base plate being arranged at a certain distance from the heat shield and including a plurality of openings in the rim area for passing the cooling air to create a cooling air jet from each of the plurality of openings to form a starter film for cooling the combustion chamber wall, wherein a center axis of each opening is inclined at a shallow angle α relative to the combustion chamber wall, and each opening is constructed and positioned such that a straight line parallel to the center axis of the opening can pass through an entire length of the opening in a direct and unobstructed path from the cooling air in the combustion chamber head to the combustion chamber wall.