Rope seal for gas turbine engines

1. A seal assembly in a region of a gas turbine engine subject to high operating temperatures, comprising:

first and second engine components defining first and second mutually confronting surfaces that define a gap therebetween, the gap being variable during operation of the gas turbine engine,

a recess in the second surface, the recess having a rear surface that faces toward the first surface,

a rope seal element comprising a high-temperature resistant material of at least one of ceramic and metal, and

a resilient seal carrier extending lengthways of the rope seal element and in which the rope seal element is located, the rope seal element being trapped between the seal carrier and the first surface to seal against the first surface, the seal carrier being resilient at the operating temperatures of the gas turbine engine to urge the rope seal element against the first surface,

the seal carrier having splayed leg portions that seal against the rear surface of the recess, the recess being substantially wider than the splay of the splayed leg portions upon assembly of the first and second components into the engine, and the splayed leg portions being operative to splay further apart on the rear surface of the recess as the gap between the first and second mutually confronting surfaces decreases.

2. The sealing arrangement of claim 1 , in which the seal carrier comprises a concave channel.

3. The sealing arrangement of claim 1 , in which the seal carrier comprises sheet metal.

4. The sealing arrangement of claim 3 , in which the seal carrier is roll-formed.

5. The sealing arrangement of claim 1 , in which the gap is annular and the seal carrier is a segmented annular structure.