AIRFOIL BLADE HAVING A SERPENTINE COOLING CIRCUIT AND IMPINGEMENT COOLING
Assignee
GENERAL ELECTRIC COMPANY A NY CORP.
Filed
Jul 13, 1992
Granted
Aug 26, 1997
Location
CINCINNATI OH US
Abstract
An airfoil blade, such as a jet engine turbine rotor blade. An internal serpentine coolant circuit has a last downstream passageway bounded by four monolithic inner walls which are monolithic with at least a portion of the outer walls. Two of the inner walls are spaced from the outer walls and contain air impingement orifices creating two impingement chambers. Some coolant in the serpentine circuit exits the airfoil blade through a coolant exit in the blade tip. The remaining coolant in the circuit passes through the impingement orifices and exits the blade through film cooling holes in the outer walls.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Aug 4, 1993
Rescinded
Apr 9, 1997
Duration
3 years, 8 months
Inventor
- 1CHING-PANG LEE
Record Details
- Patent number
- US 5660524
- Application
- 00791244
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
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