| 摘要 |
A laminate seal assembly (34), disposed on a stator seal portion (33) and opposite a rotor seal portion (35) of a gas turbine engine (10) comprises a first honeycomb layer (40) having a first edge (42) which engages the rotor portion and a second edge (44) distal from said rotor seal portion, a plurality of honeycomb cells (41) extending between the first edge and the second edge, an intermediate seal plate (50) having a first material surface (51) and a second material surface (53), the first material surface disposed against the second edge of the first honeycomb layer, a low conductivity structure (60) disposed on the second surface, and a backing plate (70) 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. |
