Blade pitch varying means

Claim 2

In a gas turbine engine including an annular flowpath, a rotor with rotor blades extending into said flowpath, a hollow static structure inward of and coaxial with said flowpath for supporting said rotor, and a plurality of propulsor blades connected to said rotor blades radially outward of said flowpath, propulsor blade pitch varying means comprising: actuation means located within said static structure along the engine centerline for delivering an axial force; bearing means for transmitting said axial force into a frame of reference with said rotor; linkage means for connecting said actuation means with said bearing means, said linkage means including a unison ring with a plurality of inwardly facing teeth adapted to slidingly engage a plurality of axially extending splines coaxial with said static structure; and gearing means rotating with said rotor for converting said axial force into a force for varying the pitch of each of said propulsor blades.

Claim 3

In a gas turbine engine including first and second counterrotating turbine rotors and blades for driving first and second counterrotating propulsor blades, respectively, and a hollow static structure radially inward of said rotors, said second rotor being supported by bearings on said structure and said first rotor being supported on said second rotor by differential bearings, pitch varying means for varying the pitch of said first and second propulsor blades comprising: actuation means located within said sttic structure along the engine centerline for delivering a first and second axial force; dual first bearing means for first transmitting said first axial force into a frame of reference with said second rotor and then into a frame of reference with said first rotor; first linkage means for connecting said actuation means with said first bearing means, wherein said first linkage means includes a first unison ring with a plurality of inwardly facing teeth adapted to slidingly engage a plurality of axially extending splines on said static structure; first gearing means rotating with said first rotor for converting said first axial force into a force for varying the pitch of each of said first propulsor blades; second bearing means for transmitting said second axial force into a frame of reference with said second rotor; second linkage means for connecting said actuation means with said second bearing means, said second linkage means includes a second unison ring with a plurality of inwardly facing teeth adapted to slidingly engage a plurality of outwardly facing and axially extending splines on said first unison ring; and second gearing means rotating with said second rotor for converting said second axial force into a force for varying the pitch of each of said second propulsor blades.

Claim 4

In a gas turbine engine including first and second counterrotating turbine rotors and blades for driving first and second counterrotating propulsor blades, respectively, and a hollow static structure radially inward of said rotors, said second rotor being supported by bearings on said structure and said first rotor being supported on said second rotor by differential bearings, pitch varying means for varying the pitch of said first and second propulsor blades comprising: actuation means located within said sttic structure along the engine centerline for delivering a first and second axial force; dual first bearing means for first transmitting said first axial force into a frame of reference with said second rotor and then into a frame of reference with said first rotor; first linkage means for connecting said actuation means with said first bearing means, wherein said first linkage means includes a first unison ring with a plurality of inwardly facing teeth adapted to slidingly engage a plurality of axially extending splines on said static structure; first gearing means rotating with said first rotor for converting said first axial force into a force for varying the pitch of each of said first propulsor blades; second bearing means for transmitting said second axial force into a frame of reference with said second rotor; second linkage means for connecting said actuation means with said second bearing means, said second linkage means includes a second unison ring with a plurality of inwardly facing teeth adapted to slidingly engage a plurality of outwardly facing and axially extending splines on said first unison ring; and second gearing means rotating with said second rotor for converting said second axial force into a force for varying the pitch of each of said second propulsor blades.

Claim 5

Pitch varying means, as recited in claim 2, wherein each of said first propulsor blades includes a pitch change shaft which extends radially inwardly through one of said first turbine blades; and wherein said first gearing means includes a rack and a pinion gear connected to the radially inner end of said pitch change shaft.

Claim 6

Pitch varying means, as recited in claim 2, wherein each of said second propulsor blades includes a pitch change shaft which extends radially inwardly through one of said second turbine blades; and wherein said second gearing means includes a rack and a pinion gear connected to the radially inner end of said pitch change shaft.

Claim 7

Blade pitch varying means, as recited in claim 1, wherein said linkage means includes a plurality of axially directed bar links connected to said unison ring.