Gas turbine engine blade

Patent · Tue Apr 29 00:00:00 EDT 1986

OSTI ID:5636988

Nourse, J G; Bourneuf, J J; Abbott, D R

A blade is described for a gas turbine engine comprising an airfoil portion including a pressure side and a suction side joined at an edge, an intermediate section having an I/subMIN/ axis, and a non-linear stacking axis having a first portion having a first slope and a second portion having a second slope, the second slope having a negative sense with respect to the first slope, and the stacking axis being positioned in the blade to obtain bending about the I/subMIN/ axis for generating a compressive component of bending stress in the edge at the intermediate section due to centrifugal force acting on the blade.

• Assignee: General Electric Co., Lynn, MA
• Patent Number(s): US 4585395
• OSTI ID: 5636988
• Resource Relation: Patent File Date: Filed date 12 Dec 1983
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
GAS TURBINE ENGINES
TURBINE BLADES
AIRFOILS
BENDING
COMPRESSION
POSITIONING
PRESSURE EFFECTS
STRESSES
ENGINES
HEAT ENGINES
INTERNAL COMBUSTION ENGINES
330103* - Internal Combustion Engines- Turbine