Patent ID: 6983608

Claim:
A method for assembling a gas turbine engine, said method comprising: providing an engine frame including an integrally formed outer band, an inner band, and a plurality of circumferentially-spaced apart struts extending radially therebetween; providing at least one fairing that is formed as an integral single piece casting and includes a first sidewall and a second sidewall connected at a leading edge and a trailing edge such that at least one cooling chamber is defined therebetween; and coupling the at least one fairing around at least one strut such that the strut extends through the fairing said at least one cooling chamber and such that during the coupling process the fairing is only transitioned axially around the strut rather than being slid radially along the strut; wherein said providing at least one fairing comprises forming a parting line extending through the fairing between the fairing first and second sidewalls such that the fairing is divided into a forward fairing portion and an aft fairing portion that are axially removable and coupled together.