Patent ID: 7845174
Filing Date: 2010-12-07
Classification: F23D,F23R

Abstract:
1. A combustor liner for a gas turbine engine, the liner being adapted to retain a plurality of heat shield portions each including at least first, second and third protruding fasteners, the combustor liner comprising a dome section having for each heat shield portion a positioning hole defined at a first radial distance from a central axis of the liner, the positioning hole being sized to receive the first fastener to at least substantially prevent radial and circumferential motion of the first fastener within the positioning hole, a circumferential slot extending circumferentially with respect to the central axis, the circumferential slot being sized to receive the second fastener to at least substantially prevent radial motion of the second fastener within the slot while allowing limited circumferential motion of the second fastener within the slot, and a clearance hole defined at a second radial distance from the central axis, the clearance hole being sized to receive the third fastener to allow limited radial and circumferential motion of the third fastener within the clearance hole, the limited circumferential motion of the second fastener within the slot and the limited radial and circumferential motion of the third fastener within the clearance hole accommodating a difference in thermal expansion between the dome section and each of the heat shield portions.