Patent classifications
F02K1/1246
Variable-section nozzle, and aircraft turbojet engine nacelle equipped with such a nozzle
A variable-section nozzle for an aircraft nacelle includes a deformable portion of which is movable between a narrow section position and a wide section position. In particular, the variable-section nozzle includes piezoelectric actuators and a controller to control the piezoelectric actuators in order to displace the deformable portion between the narrow and wide section positions. The piezoelectric actuators can be disposed on at least one faces of the deformable portion or be disposed end-to-end to form actuating rods.
Nozzle with variable throat and exit areas
A nozzle for a gas turbine engine. An array of convergent petals hingedly coupled to a nozzle exit of fixed diameter. An array of divergent petals, each divergent petal hingedly coupled to one of the array of convergent petals. A cam surface associated with the array of convergent petals. A pivot point coupled to the array of divergent petals by a first linkage and to a fixed point by a second linkage. A cam follower coupled to the second linkage by a third linkage, the cam follower arranged to abut and travel in contact with the cam surface. An actuator coupled to the cam follower and arranged to translate the cam follower along the cam surface to move the convergent and divergent petals.
Aircraft nozzle with a variable nozzle area of a second flow path
A nozzle for an aircraft powerplant is disclosed which provides two separate flow paths. A flow path is provided in the nozzle for a core flow of the powerplant and another flow path is provided for a bypass flow of the powerplant. The nozzle can have a variety of configurations including, but not limited to, 2D and axisymmetric. Either or both the flow paths can be convergent, divergent, or convergent-divergent, and the flow paths need not be similar between the two. Actuators are provided to manipulate the configuration of the flow paths and the areas of the flow paths. For example, throat and/or exit areas can be manipulated.
NOZZLE
A nozzle for a gas turbine engine. An array of convergent petals hingedly coupled to a nozzle exit of fixed diameter. An array of divergent petals, each divergent petal hingedly coupled to one of the array of convergent petals. A cam surface associated with the array of convergent petals. A pivot point coupled to the array of divergent petals by a first linkage and to a fixed point by a second linkage. A cam follower coupled to the second linkage by a third linkage, the cam follower arranged to abut and travel in contact with the cam surface. An actuator coupled to the cam follower and arranged to translate the cam follower along the cam surface to move the convergent and divergent petals.