Gas turbine blade seal
Patent
·
OSTI ID:6211703
A gas turbine engine is described having a disk and a plurality of blades, each blade having a airfoil, a blade platform, a neck, and a root, the root of each blade secured in the disk, the platform of each blade being independent of the other; a seal arrangement comprising: a rigid damper disposed in an under blade zone and in contact with adjacent platforms; and a flexible seal located downstream of the rigid damper, the seal being clipped to the rigid damper and in contact with the adjacent platforms at a location downstream of the rigid damper.
- Assignee:
- United Technologies Corp., Hartford, CT (United States)
- Patent Number(s):
- US 5228835; A
- Application Number:
- PPN: US 7-981146
- OSTI ID:
- 6211703
- Resource Relation:
- Patent File Date: 24 Nov 1992
- Country of Publication:
- United States
- Language:
- English
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