GAS TURBINE LAMINATE SEAL ASSEMBLY COMPRISING FIRST AND SECOND HONEYCOMB LAYER AND A PERFORATED INTERMEDIATE SEAL PLATE IN-BETWEEN

摘要

A laminate seal assembly, disposed on a stator seal portion and opposite a rotor seal portion of a gas turbine engine comprises a first honeycomb layer having a first edge which engages the rotor portion and a second edge distal from said rotor seal portion, a plurality of honeycomb cells extending between the first edge and the second edge, an intermediate seal plate having a first material surface and a second material surface, the first material surface disposed against the second edge of the first honeycomb layer, a low conductivity structure disposed on the second surface, and a backing plate disposed on against said low conductivity structure, wherein the stator portion may be tuned for thermal growth to match the thermal growth of the rotor portion.

主权项

1. A laminate seal assembly disposed on a stator seal portion and opposite a rotor seal portion of a gas turbine engine, comprising:
a first honeycomb layer having a first edge which engages said rotor seal portion and a second edge distal from said rotor seal portion, a plurality of cells extending between said first edge and said second edge; an intermediate seal plate having a first material surface and a second material surface, said first material surface disposed against said second edge of said first honeycomb layer; a low conductivity structure disposed on said second material surface; and, a backing plate disposed against said low conductivity structure; wherein said stator portion may be tuned for thermal growth to match the thermal growth of said rotor portion.