TURBINE BLADE COOLING
Assignee
UNITED TECHNOLOGIES CORPORATION
Filed
Nov 29, 1991
Granted
Oct 6, 1998
Location
JUPITER FL US
Abstract
Internal heat transfer of air cooled turbine blades of a gas turbine engine is enhanced by orienting the impingement holes that interconnect the air-cooled feed passage to the hybrid passageway internally of the blade in a more radial direction to minimize pressure drop losses. By improved mixing of the cooling air in the hybrid passageway the additional mechanical turbulence promoters can be utilized without sacrificing pressure losses.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Jun 23, 1992
Rescinded
Mar 18, 1997
Duration
4 years, 8 months
Inventor
- 1KENNETH B. HALL
Record Details
- Patent number
- US 5816777
- Application
- 00779965
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
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