TURBINE BLADE HAVING AUXILIARY TURBULATORS
Assignee
GENERAL ELECTRIC COMPANY A NY CORPORATION
Filed
Dec 17, 1991
Granted
Dec 9, 1997
Location
IPSWICH MA US
Abstract
A gas turbine blade includes an airfoil having first and second sides and an internal passage extending longitudinally therebetween for channeling air to cool the airfoil. A plurality of longitudinally spaced apart primary turbulator ribs extend into the internal passage from at least one of the first and second sides. An auxiliary turbulator rib is spaced between adjacent ones of the primary ribs. The auxiliary rib has a height which is less than the height of the primary ribs for augmenting convective heat transfer enhancement with reduced pressure loss, and, therefore, reduced cooling air requirements.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
May 12, 1992
Rescinded
Mar 18, 1997
Duration
4 years, 10 months
Inventor
- 1DAVID M. KERCHER
Record Details
- Patent number
- US 5695320
- Application
- 07809602
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
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