Patent ID: 9038395
Filing Date: 2015-05-26
Classification: F23R,Y02T,Y10T

Abstract:
1. A combustor for a turbine engine, comprising: a first liner comprising a hot side and a cold side; 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 defining an air admission hole for directing a first jet of pressurized air into the combustion chamber, the air admission hole having a non-circular shape; and an insert positioned within the air admission hole to guide the first jet through the air admission hole and into the combustion chamber, wherein the insert includes a shoulder abutting the hot side and a flared inlet portion abutting the cold side, wherein the insert has an outer circumference swaged into the air admission hole such that the outer circumference of the insert matches the non-circular shape of the air admission hole.