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) F23R 3/06 (2006.01)
Patent
CA 2056592
PATENT 13DV 10600 ABSTRACT A gas turbine engine combustor is provided with a combustor liner film cooling means having a slotted nugget or ring for starting a cooling film on and upstream of a multi-hole single wall sheet metal combustor 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 sharply angled in the downstream direction. In one embodiment the cooling holes are angled in a circumferential direction which generally coincides with the swirl angle of the flow along the surface of the liner. Another embodiment provides a that the annular liner is corrugated so as to form an axially extending wavy wall to help resist buckling which is particularly useful for outer liners in the combustion section of aircraft gas turbine engines and in the exhaust section of gas turbine engines and afterburners.
Craig Wilson And Company
General Electric Compny
Napoli Phillip D.
LandOfFree
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