Seal with integral assembly clip and method of sealing

A seal assembly for a gas turbine engine, the assembly comprising:

• a first split-ring seal comprising:
• circumferentially separated first and second ends;
• laterally separated first and second edges;
• a first sealing lobe adjacent the first edge, wherein the first sealing lobe comprises a curved surface extending laterally outward from the first edge;
• and
• a first integral clip portion adjacent the second edge;
• a second split-ring seal slidably received and nested in the first seal, the second split-ring seal comprising:
• circumferentially separated third and fourth ends;
• laterally separated third and fourth edges adjacent to first and second edges, respectively;
• and
• a second integral clip portion adjacent to the fourth edge;
• and
• an annular heat shield comprising:
• laterally separated fifth and sixth edges;
• a third integral clip portion, the third integral clip portion slidably received and nested in the second integral clip portion such that the first, second, and third integral clip portions together form a single concave shape configured to clip to a flange to position the seal assembly in the gas turbine engine;
• and
• an axially extending portion radially separated from a portion of the nested first and second split-ring seals.