CPC F01D 25/162 (2013.01) [F01N 13/1811 (2013.01); F16L 27/1004 (2013.01); F16L 27/107 (2013.01); F16L 51/025 (2013.01); F01D 9/026 (2013.01); F01N 2310/14 (2013.01); F05D 2220/323 (2013.01); F05D 2260/39 (2013.01); F05D 2260/96 (2013.01)] | 20 Claims |
1. An aircraft engine comprising a combustion engine having an engine intake and an exhaust gas outlet; a gas turbine having a gas turbine intake; an exhaust pipe fluidly connecting the exhaust gas outlet to the gas turbine intake, the exhaust pipe having a length defined between the exhaust gas outlet and the gas turbine intake and an exhaust gas path extending inside the exhaust pipe along the length, the exhaust pipe having a damper segment located along a portion of the length, the damper segment having
a proximal end secured to a proximal segment and directed towards the combustion engine relative the exhaust gas path,
a distal end secured to a distal segment and directed towards the gas turbine intake along the exhaust gas path,
a rigid tube at the proximal end,
a damper tube extending between the rigid tube and the distal end, the damper tube being made of a metal mesh,
a proximal catch connecting a proximal end of the damper tube to the rigid tube, and
a distal catch structurally connected between a distal end of the damper tube and the distal segment, the damper tube having an unsupported length extending between the distal catch and the proximal catch,
the rigid tube having a liner portion projecting into the distal segment, the liner portion extending internally relative the damper tube.
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