Patent ID: 8926284
Filing Date: 2015-01-06
Classification: F01D,F05D

Abstract:
1. An assembly for a gas turbine engine comprising: first and second components of the gas turbine engine having respective contact surfaces which contact each other over a contact zone, the first and second components being moveable relative to each other at their respective contact surfaces, the contact zone having a first edge and a second edge; and a groove formed in at least one of the contact surfaces, the groove extending entirely across the contact zone from the first edge to the second edge to form an opening between the contact surfaces at one or both of the first and second edges such that, in operation, a pressure difference across the contact zone causes contaminants entering the groove to be expelled along the groove from the contact zone, the first and second components remaining substantially undeformed at their contact surfaces during use, one of the components being an aerofoil component having a root portion accommodated in a slot of the other component, the contact surfaces comprising a surface of the root portion and a surface bounding the slot.