Aircraft turbine engine with a pair of rotating and non-ducted propellers
An aircraft turbine engine has a pair of rotating and non-ducted propellers. An upstream propeller has an outer diameter D 1 and a downstream propeller has an outer diameter D 2 . The engine further includes a system for varying the diameter D 2 . The downstream propeller includes an annular row of blades, each of which is configured to be mounted telescopically in the radial direction (R) in an outer fan duct.
1. An aircraft turbine engine, comprising:
a pair of rotating non-ducted propellers, wherein one of the propellers is an upstream propeller having a first outer diameter D 1 , and the other propeller is a downstream propeller having a second outer diameter D 2 , the downstream propeller comprising means for varying said diameter D 2 , said downstream propeller comprising an annular row of blades, each blade being configured to be mounted telescopically in the radial direction (R) in an outer fan duct,
each blade being secured to a radial shaft that is connected to actuation means for the radial translation of the blade, the actuation means comprising at least one actuator associated with one or several blades, wherein each of the at least one actuator comprises a pneumatic cylinder comprising a radially closed inner chamber and a radially outer chamber connected by a duct with outer flow on the outer fan duct.
2. The aircraft turbine engine according to claim 1 , wherein each blade is associated with one of the at least one actuator, with each actuator being mounted on the radial shaft of said each blade.
3. The aircraft turbine engine according to claim 1 , wherein several blades are associated with the one of the at least one actuator.
4. The aircraft turbine engine according to claim 3 , wherein a transmission ring rotating with the downstream propeller, mechanically connected to several blades, is moved in axial translation by said at least one actuator.
5. The aircraft turbine engine according to claim 1 , wherein the actuation means is configured to selectively control an angular pitch of each blade about a radial axis (R) thereof.
6. The aircraft turbine engine according to one of claim 5 , wherein the actuation means comprise complementary means and wherein the actuation means transmit to the radial shaft secured to the blade, a radial translation and the complementary means use said translation to rotate the shaft about the axis (R) thereof on the hub, with the purpose of associating a modification of the pitch of the blade with the radial movement thereof.
7. The aircraft turbine engine according to claim 1 , wherein each actuator is configured to be activated according to an ambient pressure.
8. An aircraft turbine engine, comprising:
a pair of rotating non-ducted propellers, wherein one of the propellers is an upstream propeller having a first outer diameter D 1 , and the other propeller is a downstream propeller having a second outer diameter D 2 , the downstream propeller comprising means for varying said diameter D 2 , said downstream propeller comprising an annular row of blades, each blade being configured to be mounted telescopically in the radial direction (R) in an outer fan duct,
each blade being secured to a radial shaft that is connected to actuation means comprising actuators for the radial translation of the blade, wherein each blade is associated with an actuator, each actuator being mounted on the radial shaft of said each blade, the actuation means further comprising a swashplate with undulations, perpendicular to said shaft and connected to the latter by rods with a pivoting connection to modify the radial position of said shaft during a rotation around said radial direction (R).