Layered seal for turbomachinery
The present application provides seal assemblies for reducing leakages between adjacent components of turbomachinery. The seal assemblies may include outer shims, and at least a portion of the outer shims may be substantially impervious. At least one of the outer shims may be configured for sealing engagement with seal slots of the adjacent components. The seal assemblies may also include at least one of an inner shim and a filler layer positioned between the outer shims. The at least one inner shim may be substantially solid and the at least one filler layer may be relatively porous. The seal assemblies may be sufficiently flexible to account for misalignment between the adjacent components, sufficiently stiff to meet assembly requirements, and sufficiently robust to operating meet requirements associated with turbomachinery.
- Research Organization:
- GE Global Research, Niskayuna, New York (United States)
- Sponsoring Organization:
- USDOE
- DOE Contract Number:
- FC26-05NT42643
- Assignee:
- General Electric Company
- Patent Number(s):
- 9,188,228
- Application Number:
- 13/560,357
- OSTI ID:
- 1226450
- Resource Relation:
- Patent File Date: 2012 Jul 27
- Country of Publication:
- United States
- Language:
- English
Similar Records
Casing hanger seal assembly with diverging taper
Spf/db hollow core fan blade. [SuperPlastically Formed/Diffusion Bonded]