Fairing assembly

A fairing assembly for a gas turbine engine, comprising:

• a plurality of fairings, each fairing having an inner end radially spaced apart from an outer end, each fairing extending axially from a leading edge to a trailing edge;
• an inner ring defining a plurality of inner pocket forward segments;
• an annular inner band defining a plurality of inner pocket aft segments, the inner ring positioned against a forward edge of the inner band such that the inner pocket forward segments and inner pocket aft segments form a plurality of inner pockets, each inner pocket shaped complementary to the inner end of each fairing, each inner pocket having a forward end and an aft end;
• an annular outer band defining a plurality of outer pockets, each outer pocket shaped complementary to the outer end of each fairing, each outer pocket having a forward end and an aft end;
• a non-through hole defined in a first component;
• a grommet secured in the non-through hole;
• an opening defined in a second component;
• a swaged grommet secured in the opening;
• and
• a pin inserted into an opening defined by the grommet and the swaged grommet,
• wherein the pin is welded to the swaged grommet,
• wherein the inner ring is a single piece structure,
• wherein the inner band is a single piece structure,
• wherein the outer band is a single piece structure, and
• wherein the inner end of each fairing is received within an inner pocket of the plurality of inner pockets and the outer end of each fairing is received within an outer pocket of the plurality of outer pockets.

A method for assembling a fairing assembly in a gas turbine engine, the method comprising:

• installing an annular inner band in the gas turbine engine, the inner band defining a plurality of inner pockets;
• inserting an inner end of each of a plurality of fairings into an inner pocket of the plurality of inner pockets;
• sliding an annular outer band into position with respect to the plurality of fairings such than an outer end of each of the plurality of fairings is received in an outer pocket of a plurality of outer pockets defined by the outer band,
• defining a non-through hole in a component of the fairing assembly;
• and
• securing a grommet in the non-through hole,
• wherein the grommet is a flared grommet that has a distal end with a larger cross-section than a body of the grommet,
• defining an opening in a second component,
• securing a swaged grommet in the opening,
• inserting a pin into an opening defined by the grommet and the swaged grommet, and
• welding a pin to the swaged grommet,
• wherein the inner band is a single piece structure, and
• wherein the outer band is a single piece structure.