US 7,464,536 B2
Methods and apparatus for assembling gas turbine engines
Bernard James Renggli, Cincinnati, Ohio (US); and Matthew Wilson Jumper, Cincinnati, Ohio (US)
Assigned to General Electric Company, Schenectady, N.Y. (US)
Filed on Jul. 07, 2005, as Appl. No. 11/176,770.
Prior Publication US 2007/0125065 A1, Jun. 07, 2007
Int. Cl. F02K 3/02 (2006.01)
U.S. Cl. 60—204  [60/226.3; 60/770] 20 Claims
OG exemplary drawing
 
1. A method for operating a gas turbine engine including a core engine having a core stream duct, at least one bypass duct, and a nozzle assembly downstream of the core engine and including a core engine nozzle and a bypass nozzle separated by a liner, said method comprising:
channeling a first airflow discharged from the core gas turbine engine to the core engine nozzle; and
channeling a second airflow through the at least one bypass duct such that the second airflow bypasses the core gas turbine engine, wherein the second airflow is channeled through a plurality slots defined at a downstream end of a plurality of fairings, wherein the plurality of fairings are upstream from a plurality of support struts coupled to the nozzle assembly liner, such that at least a portion of the second airflow is mixed with the first airflow.