Carlson, Gaskey & Olds, P.C.
Method and assembly for reducing secondary heat in a gas turbine engine
A turbine section for a gas turbine engine includes a first rotor assembly with a first rotor assembly bleed air source and an aft cavity that is in fluid communication with the first rotor assembly bleed air source. A second rotor assembly includes a forward cavity. A vane bleed air source is in fluid communication with the forward cavity. A seal extends between the first rotor assembly and the second rotor assembly.
UNITED TECHNOLOGIES CORPORATION
F F F F F F F F
F01D F02C F01D F02C F02C F01D F05D F05D
inventional inventional inventional inventional inventional inventional additional additional
Julian Gabriel L. David R. James D.
Partyka Suciu Pack Hill