F - Mech Eng,Light,Heat,Weapons – 02 – C
Patent
F - Mech Eng,Light,Heat,Weapons
02
C
F02C 7/18 (2006.01) F02K 1/82 (2006.01) F23R 3/00 (2006.01)
Patent
CA 2048726
PATENT 13DV-9835 ABSTRACT A gas turbine engine combustor is provided, having a an annular single wall sheet metal liner which is generally annular in shape and having disposed therethrough a multi-hole film cooling means which includes at least one pattern of small closely spaced film cooling holes angled sharply in the downstream direction and angled in a circumferential direction wherein the circumferential angle generally coincides with the swirl angle of the flow along the surface of the liner. Another embodiment provides a corrugated aircraft engine sheet metal combustor liner which forms an axially extending wavy wall to help resist buckling, particularly useful for outer liners in the combustion section of the engine and in the exhaust section of gas turbine engines incorporating afterburners.
Company General Electric
Craig Wilson And Company
Napoli Phillip D.
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