Patent ID: 7174719

Claim:
A gas turbine engine comprising: a turbine section having a turbine rotor; a compressor section having a compressor rotor, the compressor section positioned in a proximity of the turbine section; a plenum disposed between the turbine section and the compressor section, the plenum having first and second fluid paths adjacent to an outermost tip of the compressor rotor and the turbine rotor, respectively; and a seal assembly positioned in the plenum, the seal assembly including: an annular seal member positioned in the plenum adjacent to the compressor section for restraining a fluid flow between the compressor section and the turbine section via the first fluid path of the plenum; and an annular heat shield member positioned in the plenum adjacent to the turbine section for limiting heat transfer from the turbine section to the compressor section via the second fluid path of the plenum, the annular heat shield member including a plurality of slots formed in the heat shield member.