Patent ID: 8161752
Filing Date: 2012-04-24
Classification: F23R,Y02T

Abstract:
1. A combustor for a turbine engine, comprising: a first liner; a second liner forming a combustion chamber with the first liner, the combustion chamber configured to receive an air-fuel mixture for combustion therein, the first liner being a first dual wall liner comprising a first hot wall facing the combustion chamber and a first cold wall, the first cold wall having a first cold wall orifice and the first hot wall having a first hot wall orifice; and a first insert has a divergent inlet portion between the first cold wall and the first hot wall, the insert mounted in the first hot wall orifice configured to receive a first air jet of pressured air from the first cold wall orifice, and guide the first jet through the first hot wall orifice and into the combustion chamber, wherein the first jet has a first flow rate through the first cold wall orifice and a second flow rate through the first insert, and wherein the first flow rate is approximately equal to the second flow rate or differs from the second flow rate by approximately +10%.