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US 6,234,753 B1Granted
Turbine airfoil with internal cooling
AssigneeGeneral Electric Company
InventorChing-Pang Lee
Life of this patent
Estimating the term…
Abstract
The flow of cooling fluid through core tie holes formed between the internal cooling passageways of turbine airfoils is reduced by disposing flow deflectors on the wall adjacent to the holes. The deflectors alter the local static pressure near the holes, thereby minimizing the pressure differential across the holes so as to reduce the flow of cooling fluid.
Claims16
An airfoil comprising:
- first and second internal cooling passageways separated by a wall having at least one hole formed therein, said hole being formed by a core tie used during casting of said airfoil;
- and
- a deflector disposed on said wall adjacent to said hole.
An airfoil comprising:
- first and second internal cooling passageways separated by a wall having at least one hole formed therein, said first passageway having a greater pressure than said second passageway;
- and
- means for changing local static pressure immediately adjacent said hole so as to minimize the pressure differential across said hole.
An airfoil comprising:
- an internal serpentine coolant circuit having a plurality of series-connected coolant passageways, adjacent ones of said passageways being separated by a wall having a core tie hole formed therein;
- a first deflector disposed on said wall in a first one of said passageways, said first deflector being located adjacent to and upstream of said core tie hole;
- and
- a second deflector disposed on said wall in a second one of said passageways, said second deflector being located adjacent to and downstream of said core tie hole, wherein said second one of said passageways has a lower pressure than said first one of said passageways.
1 more element
Dependencies are inferred from the claim text.