Gas turbine bladed disk assembly

Patent · Tue Jun 17 00:00:00 EDT 1986

OSTI ID:5461796

Klassen, D D; Bullantyne, D B

A gas turbine engine blade is described which consists of: an airfoil having a root; a shank extending from the airfoil root; and a dovetail extending from the shank; the shank having two oppositely facing lateral surfaces, and first and second oppositely facing end surfaces, the lateral surfaces being wider than the end surfaces, and the shank second end surface including a pocket extending therein toward the shank first end surface and between the dovetail and the airfoil root, the pocket defining first and second laterally spaced and longitudinally extending legs, the shank including a solid forward portion extending from the first surface to the pocket, the airfoil being generally aligned with respect to a longitudinal axis of the blade along substantially only the first leg and the solid forward portion for providing a generally straight load path from the airfoil to the dovetail.

• Assignee: General Electric Co., Lynn, MA
• Patent Number(s): US 4595340
• OSTI ID: 5461796
• Resource Relation: Patent File Date: Filed date 30 Jul 1984
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
GAS TURBINE ENGINES
DESIGN
TURBINE BLADES
AIRFOILS
ALIGNMENT
SPACE DEPENDENCE
SURFACES
ENGINES
HEAT ENGINES
INTERNAL COMBUSTION ENGINES
330103* - Internal Combustion Engines- Turbine