TURBINE BLADE
Assignee
UNITED TECHNOLOGIES CORPORATION, A CORP. OF DE
Filed
Dec 5, 1988
Granted
Oct 7, 1997
Location
JUPITER FL US
Abstract
A bulkhead in the form of a rib extending spanwise adjacent the leading edge of the airfoil of a turbine blade of a gas turbine engine serves to stiffen the airfoil to attain protection from impact by foreign objects, but doesn't materially affect cooling effectiveness in the event of a puncture of the skin. Holes extending spanwise in the rib reduce the mass, allow radial flow, and restrict flow into the leading edge. This construct allows a reduction in the thickness of the skin of the airfoil, and hence a weight reduction.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
May 3, 1989
Rescinded
Mar 18, 1997
Duration
7 years, 10 months
Inventor
- 1KENNETH B. HALL
Record Details
- Patent number
- US 5674050
- Application
- 07279632
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
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