| 摘要 |
A method of repairing an part 29 of a gas turbine engine, the part 29 comprising a first aerofoil 30 and a second aerofoil 32, the method comprising: controlling machining of at least one of: the first aerofoil 30 and the second aerofoil 32; the machining causing an increase in a throat area 42 defined by the first aerofoil, the second aerofoil, a first platform 34 and a second platform 36, the first aerofoil and the second aerofoil being arranged to couple to the first platform and to the second platform; and controlling provision of a coating (46, figure 5A) to at least one of the first platform and the second platform subsequent to controlling machining to reduce the throat area. The coating may comprise a thermal barrier coating including yttria stabilised zirconia or an Aluminide (Al) alloy. The invention further provides apparatus including a controller, a computer program and storage media for performing the method. Another aspect of the invention is a platform having a coating, the thickness of the coating being greater than two hundred and fifty (250) microns. |
