Patent ID: 9488105
Filing Date: 2016-11-08
CPC Classification: F02C,F23R,Y10T

Claim Text:
1. An assembly for a gas turbine engine comprising: a flange with a first side and a second side, a rocket unit coupled to the first side of the flange, the rocket unit comprising one or more nozzles having a base in contact with the first side of the flange, a gas supply pipe connected to the base, and one or more swirlers connected to an axially opposite side of the one or more nozzles relative to the base, wherein the gas supply pipe is configured to pass through a bore in the flange for supplying gas to a combustion chamber of the gas turbine engine, and a sleeve, surrounding the gas supply pipe, having a first end and a second end, wherein the first end is sealingly coupled to the gas supply pipe, wherein the sleeve is sealingly coupled to the flange at the second end such that the sleeve extends along a thickness of the flange, wherein the sleeve has a longitudinal extension which is radially extended around a circumference of the sleeve, wherein the longitudinal extension comprises a V-shaped portion arranged perpendicular to a longitudinal axis extending through a central portion of the sleeve, and wherein a first portion of the V-shaped portion of the sleeve couples to the gas supply pipe at an oblique angle.