CPC F23R 3/002 (2013.01) [F23R 3/007 (2013.01); F23R 3/60 (2013.01); F23R 2900/00005 (2013.01); F23R 2900/00017 (2013.01); F23R 2900/00018 (2013.01)] | 18 Claims |
1. A method for manufacturing a combustor assembly of a gas turbine engine defining a centerline, an axial direction, and a radial direction, the combustor assembly comprising a liner and a dome, the dome comprising a forward surface and an inner surface, the method comprising:
forming the liner of a ceramic matrix composite material to include a forward end comprising a baseline geometry;
removing material from the forward end of the liner to change the baseline geometry to include an axial interface surface and a radial interface surface, the axial interface surface defining a more precise circular shape than the baseline geometry with respect to the centerline; and
mounting the liner to the dome including mounting the forward end of the liner to the dome such that the axial interface surface defines a radial gap with the inner surface of the dome and the radial interface surface defines an axial gap with the forward surface of the dome, wherein mounting the liner to the dome comprises mounting the liner to the dome with a mounting assembly, the mounting assembly including:
a grommet located in an opening in the liner, the grommet configured to reduce wear on the forward end of the liner;
a bushing installed in the opening of the liner and within the grommet;
a collar adjacent an outer surface of the liner;
a pin inserted through the bushing and extending through the dome and the opening in the liner; and
a nut tightened on the pin to secure the liner to the dome and to press the bushing between a yoke of the dome and a base plate of the dome, the nut located adjacent an inner surface of the liner,
wherein removing material from the forward end of the liner to change the baseline geometry to include the axial interface surface and the radial interface surface which results in defining of the radial gap and the axial gap, respectively.
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