BOWED TURBINE BLADE
Assignee
General Electric
Filed as: GENERAL ELECTRIC COMPANY
Filed
Dec 12, 1983
Granted
Jul 28, 1987
Location
BEDFORD MA US
Abstract
The invention comprises a blade for a gas turbine engine including an airfoil portion having a non-linear stacking axis which is effective for generating a compressive component of bending stress due to centrifugal force acting on the blade. The compressive component of bending stress is provided in a life-limiting section of the blade, which, for example, includes trailing and leading edges of the blade. Inasmuch as the stacking axis, which represents the locus of centers of gravity of transverse sections of an airfoil portion of the blade, is non-linear, an increased amount of a compressive component of bending stress can be generated at a life-limiting section between root and tip sections of the blade without substantially increasing bending stress at the root of the blade.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Oct 18, 1985
Rescinded
Dec 13, 1985
Duration
1 month
Inventor
- 1JACK R. MARTIN
Technology Domains
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Record Details
- Patent number
- US 4682935
- Application
- 06560718
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
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