TURBINE BLADE HAVING HAVING OFFSET TURBULATORS
Assignee
GENERAL ELECTRIC COMPANY A NY CORPORATION
Filed
Dec 17, 1991
Granted
Oct 28, 1997
Location
STRATHAM NH US
Abstract
A gas turbine engine blade includes an airfoil having first and second sides and an internal passage extending longitudinally therebetween for channeling air to cool the airfoil. Respective pluralities of first and second turbulator ribs extend inwardly from at least one of the first and second airfoil sides. Adjacent ones of second ends of the first and second ribs are staggered apart longitudinally and overlap chordally for defining a gap therebetween facing transversely for turning cooling air upon flow through the gap. The gap increases convective heat transfer enhancement for reducing cooling air requirements and improving blade creep life.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
May 12, 1992
Rescinded
Mar 18, 1997
Duration
4 years, 10 months
Inventor
- 1SAMUEL D. SPRING
Record Details
- Patent number
- US 5681144
- Application
- 07809193
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
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