GAS TURBINE ENGINE COMPONENT WITH COMPOUND COOLING HOLES AND METHOD FOR MAKING THE SAME
Assignee
General Electric
Filed as: GENERAL ELECTRIC COMPANY
Filed
Mar 17, 1993
Granted
Nov 4, 1997
Location
CALIFORNIA KY US
Abstract
A gas turbine engine component includes a wall portion with at least one compound cooling hole formed therein between an external surface of the component and an interior plenum. The at least one compound cooling hole includes a non-circular diffuser opening formed by a laser beam with a non-circular cross-sectional area, and a channel with a substantially circular cross-section connecting the diffuser opening and the interior plenum. The channel is also formed by the non-circular laser beam in the same laser drilling operation as the diffuser opening. The cooling hole further includes a transition point at which the compound hole begins to convert from a substantially non-circular cross-section to a substantially circular cross-section. The location of the transition point is controlled by positioning a focal point of the non-circular laser beam to undershoot the external surface of the component by a predetermined distance.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
May 21, 1993
Rescinded
Apr 9, 1997
Duration
3 years, 10 months
Inventor
- 1JAMES G. KELLEY
Record Details
- Patent number
- US 5683600
- Application
- 08038338
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
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