Patent ID: 6155056
Filing Date: 2000-12-05
Classification: F05B,F23R

Abstract:
In an annular gas turbine engine combustion chamber with a dome wall including an annular array of spaced apart fuel nozzles projecting therethrough, a centre point of each nozzle disposed on a circular median line of the annular dome wall, and including a like array of annular nozzle cup means for ducting cool compressed air from an outer surface of the dome wall into a cooling compressed air film in contact with an inner surface of the dome wall, like air films radiating in a direction outwardly from the centre point of each nozzle, the nozzle cup means comprising an annular cup encircling each nozzle and mounted through the dome wall, the improvement comprising:an array of elongate louver strips, each disposed symmetrically along said median line on the inner surface dome wall and extending between each nozzle cup of the annular array, each strip including:an elongate flange extending into the combustion chamber from the inner dome wall, the flange having an inner surface and lateral side walls;compressed air outlet means, disposed along each flange lateral side wall, for directing a compressed air film along the inner surface of the dome wall in a direction away from the median line;a compressed air inlet in the outer surface of the dome wall and in communication with the outlet means; andflange cooling jet means disposed along the inner surface of the flange, for directing a flow of cooling air over the flange inner surface, the air jet means in communication with the compressed air inlet.