| CPC F23R 3/002 (2013.01) [F02C 7/12 (2013.01); F23R 3/005 (2013.01); F23R 3/06 (2013.01); F23R 2900/00018 (2013.01); F23R 2900/00019 (2013.01)] | 17 Claims |
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1. A method of improving cooling performance of a combustor for a gas turbine engine, the method comprising the steps of:
providing the combustor comprising a liner having an inner porous wall and an outer porous wall and a plurality of porous tiles attached to the inner porous wall and the outer porous wall, wherein each porous tile comprises a base having a hot-side surface, a cold-side surface, a first circumferential extremity, a second circumferential extremity and a local radial axis;
operating the combustor to generate combustion products, wherein the plurality of porous tiles is exposed to the combustion products;
classifying regions of the plurality of porous tiles in accordance with an exposure of the regions to the combustion products, wherein regions with a higher level of exposure are classified as hot regions and regions with a lower level of exposure are classified as cool regions;
providing altered tiles by
(a) delimiting the classified regions on the cold-side surfaces of the plurality of porous tiles by attaching rail structures to the cold-side surfaces and forming delimited hot regions and delimited cool regions, wherein each delimited region has a corresponding porosity; and
(b) altering the porosities of the delimited regions and the porosities of the corresponding inner porous wall and outer porous wall in accordance with the classifications of the delimited regions; and
installing the altered tiles and the corresponding inner porous wall and outer porous wall in the combustor.
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