General Electric Company

Abhishek Goverdhan

Ravindra Shankar Ganiger

Kudum Shinde

Kishore Budumuru

Naveena K P

Domala Uma Maheshwar

Narayanan Payyoor

Abhijeet Jayshingrao Yadav

Suryarghya Chakrabarti

Nicholas M Daggett

Viswanadha Gupta Sakala

Richa Awasthi

Gary W Bryant

Balaraju Suresh

Ricardo Hernandez Pandeli

Vidya Lokammanahalli Shivashankar

Amarnath Kakarla

Illya Emmanuel Arcos Perez

Ashish Rajput

An engine for an aircraft. The engine includes a rotating airfoil assembly, at least one actuator, a torque producing system, and a controller. The rotating airfoil assembly includes a rotation axis and a plurality of rotating airfoils configured to rotate about the rotation axis in a plane of rotation. The at least one actuator is operable to change the plane of rotation of the plurality of rotating airfoils. The torque producing system is coupled to the rotating airfoil assembly and configured to rotate the rotating airfoil assembly about the rotation axis of the rotating airfoil assembly. The controller is configured to determine that the aircraft has an angle of attack and to operate the at least one actuator to change the plane of rotation of the plurality of rotating airfoils based on the angle of attack.

Rotating airfoil assembly for an aircraft engine

Disclosed herein are example variable flowpath casings for blade tip clearance control. An example casing for a turbine engine includes an annular substrate extending along an axial direction, the annular substrate including a first surface and a second surface that is radially inward relative to the first surface; an actuator structure coupled to the second surface of the annular substrate; and a smart structure cantilevered from the second surface of the annular substrate, the smart structure including: a support structure, a first region of the support structure coupled to the second surface of the annular substrate, a second region of the support structure coupled to the actuator structure; and a radially inward surface defining a variable surface, the support structure to move the variable surface in a radial direction.

Variable flowpath casings for blade tip clearance control

Disclosed herein are example variable flowpath casings for blade tip clearance control. An example casing for a turbine engine includes an annular substrate extending along an axial direction, the annular substrate defining a cavity at a radially inward surface of the annular substrate, and a smart structure coupled to the annular substrate, the smart structure including a support structure; an actuator structure to at least one of expand or contract in response to a change in temperature of the actuator structure, and a variable surface coupled to the support structure, the support structure to move the variable surface in a radial direction.

An aircraft spinner assembly includes collar stud joints connecting spinner to forward flange connected to fan rotor disk. Collar stud joint is operable to push out spinner when stud is un-torqued. Collar may be attached to stud disposed through spinner bolt hole in spinner and collar disposed in counterbore of spinner bolt hole. An aft stud thread on collar stud may be threaded into aft nut which may be swaged into flange bolt hole in forward flange. A washer may be in counterbore between collar and spinner and made from low friction and/or sacrificial material. A forward radial clearance may surround stud between stud and spinner. A forward nut may be threaded onto forward stud threads on forward end of the collar stud and abut spinner. External aft stud threads may be on collar studs and threaded into internal flange threads within flange bolt holes in forward flange.

Stud push out mount for a turbine engine spinner assembly having a spinner push out stud joint connecting through a counterbore of a spinner bolt hole

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Karnataka, India

Abhishek Goverdhan