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US 2009/0214329 A1Published application
Filter system for blade outer air seal
AssigneeUnited Technologies Corporation
InventorsChristopher R. Joe, Eric A. Hudson, Keith A. Santeler
Life of this patent
Estimating the term…
Abstract
A gas turbine engine component having a filter mounted adjacent an impingement cavity to filter particles out of a secondary cooling airflow outboard of a cooling channel in communication with the secondary cooling airflow.
Claims18
A gas turbine engine component comprising:
- a blade outer air seal having an impingement cavity;
- and
- a filter mounted adjacent said impingement cavity.
A gas turbine engine component comprising:
- an air seal having an impingement cavity that defines a multitude of inlets which communicate with a multiple of cooling channels;
- and
- a filter mounted adjacent said impingement cavity.
A method of filtering a secondary cooling airflow within a gas turbine engine comprising:
- filtering particles out of a secondary cooling airflow outboard of a cooling channel in communication with the secondary cooling airflow.
Dependencies are inferred from the claim text.