PROBLEM TO BE SOLVED: To provide a method for cooling a gas turbine engine combustor exit temperature.;SOLUTION: The combustor 16 for a gas turbine engine 10 includes an inner liner 44, an outer liner 40 defining a combustion chamber 54 between the outer linear and the inner liner, an outer support 42 arranged radially outward from the outer liner such that an outer passage 58 is defined between the outer support and the outer liner, and an inner support 46 arranged radially inward from the inner liner such that an inner passage 60 is defined between the inner support and the inner liner. One of the inner and outer supports includes two rows of impingement openings 140 arranged in a form of an array 144 to guide impingement cooling air toward one of the inner liner and the outer liner. One of the inner and the outer liners includes one row of dilution openings 120 extending to penetrate the liner to guide dilution cooling air into the combustion chamber.;COPYRIGHT: (C)2005,JPO&NCIPI
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