General Electric Company

Keith A Miedema

Randy M Vondrell

Ravindra Shankar Ganiger

Pradeep Hemant Sangli

Santosh Kumar Potnuru

James Grooms

Matthew D Brothers

A turbofan engine for an aircraft includes a fan and a fan actuation system. The fan has a plurality of fan blades coupled to a fan shaft having one or more fan bearings. The fan blades are rotatable about a pitch axis. The fan actuation system is disposed within a fan hub and includes one or more actuators for rotating the fan blades about the pitch axis and one or more radial thrust bearings. The fan actuation system is characterized by a fan actuation system length envelope in a range of 8.5 to 24 and given by Nis a number of the fan blades, Dis a fan tip diameter of the fan blades, Ris a thrust bearing radius of the radial thrust bearings, and Lis an axial length from a fan hub tip to the fan bearings.

Turbofan engine including a fan actuation system

A turbofan engine includes a fan and a fan actuation system. The fan has a plurality of fan blades. Each of the plurality of fan blades is rotatable about a pitch axis. The fan actuation system includes one or more actuators for rotating the plurality of fan blades about the pitch axis and one or more thrust bearings. The fan actuation system is characterized by a fan actuation system envelope in a range of 300 to 1860. The fan actuation system envelope is given by where Nis a number of the plurality of fan blades, Dis a fan tip diameter of the plurality of fan blades, Mis a Mach number of the turbofan engine at cruise operating conditions, and Ris a thrust bearing radius of the one or more thrust bearings.

Separators for use with gas turbine engines are disclosed herein. An example separator disclosed herein includes a first ring including a first surface, a second surface opposite the first surface, and a first opening extending from the first surface to the second surface, a second ring surrounding the first ring, the second ring including a third surface, a fourth surface, and a second opening extending from the first surface to the second surface, and a filter disposed between the first ring and the second ring, the filter disposed in a fluid pathway extending between the first opening and the second opening.

Separators for use with gas turbine engines

An example turbo engine includes a rotary hub and a propeller including a blade coupled to the rotary hub. The blade is rotatable about a radial axis to change a pitch of the blade. The turbo engine also includes a blade pitch actuation system including an actuator coupled to the blade. The actuator is moveable in a first direction to rotate the blade to a feather position and in a second direction to rotate the blade away from the feather position. The blade pitch actuation system also includes a hydraulic system to provide hydraulic fluid to one or more hydraulic chambers to move the actuator and a pressurized pneumatic chamber formed by a portion of the actuator. The pressurized pneumatic chamber biases the actuator in the first direction to move the blade to the feather position in an event of failure of the hydraulic system.

Growing community of inventors

Fairfield, OH, United States of America

Keith A Miedema