Blade pitch varying mechanism

Patent · Tue Apr 19 04:00:00 EDT 1988

OSTI ID:7033666

Butler, L

A gas turbine engine is described comprising: (a) a stationary member; (b) first and second rotating structures coaxially disposed about the stationary member; (c) an annular gas flowpath coaxial with the first and second rotating structures; (d) first and second rotor blades attached to the first and second rotating structures; (e) forward and aft rows of variable pitch propulsor blades coupled to and disposed radially outwardly of the first and second rotating structures respectively; (f) a first gear coaxially coupled to one of the propulsor blades whereby angular displacement of the first gear about a radius of the rotating structure varies the pitch of the propulsor blade with respect to the rotating structure; (g) a second gear rotatably coupled to the first gear; (h) a third gear rigidly coupled to the second gear; (i) a fourth gear rigidly coupled to the rotating structure and rotatably coupled to the thrid gear, (j) means for eccentrically revolving the second gear and the third gear with respect to the first gear and the fourth gear, respectively, whereby the first gear is angularly displaced with respect to the fourth gear.

• Assignee: General Electric Co., Cincinnati, OH
• Patent Number(s): US 4738590
• OSTI ID: 7033666
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
330103* -- Internal Combustion Engines-- Turbine
COUPLINGS
DESIGN
ENGINES
GAS TURBINE ENGINES
GEARS
HEAT ENGINES
INTERNAL COMBUSTION ENGINES
MACHINE PARTS
MOTION
OPERATION
ORIENTATION
ROTATION
ROTORS
TURBINE BLADES