Gas turbine engine blade tip clearance apparatus and method

Details Gas turbine engine blade tip clearance apparatus and method Gas turbine engine blade tip clearance apparatus and method

2005-10-17

2008-08-05

Nguyen, Hoang M (Department: 3748)

Rotary kinetic fluid motors or pumps

Bearing, seal, or liner between runner portion and static part

Between blade edge and static part

C415S127000

Reexamination Certificate

active

07407369

ABSTRACT:
A zero running clearance system for gas turbine engines includes a gas turbine engine compressor having one or more first rotor assemblies and one or more first stator assemblies disposed adjacent the one or more first rotor assemblies; a gas turbine engine turbine having one or more second rotor assemblies and one or more second stator assemblies disposed adjacent the one or more second rotor assemblies; one or more shroud segments having blade seal surfaces disposed radially outside of the tips of blades of both the first and second rotor assemblies and a clearance distance extending between the blade tips and blade seal surfaces; and, an actuator selectively operable to axially move the first and said second rotor assemblies to alter the clearance distance.

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