Method and system for rotating air seal with integral flexible heat shield

A gas turbine engine comprising:

• a core engine including a multistage compressor, a combustor, and a high pressure (HP) turbine coupled in serial flow relation;
• a low pressure turbine configured to receive combustion exhaust gases from said core engine;
• and
• a seal and heat shield device positioned between a relatively low temperature space and a relatively high temperature space within said gas turbine engine, said seal and heat shield device comprising:
• an annular radially extending flange configured to couple to the rotating member of the rotatable machine;
• a multi-walled seal shield member extending axially from said flange, said multi-walled seal shield member formed integrally with said flange, said multi-walled seal shield member comprising:
• a first wall comprising a plurality of surface features;
• a second wall spaced radially inwardly with respect to said first wall, said second wall configured to direct a flow of fluid to a drain opening;
• and
• a cavity formed between said first and second walls;
• and
• a cap end integrally formed and configured to seal said first and second walls,
• each of said flange, said seal shield member, and said cap end being formed of a sintered metal.