General Electric Company

Ge Avio S.r.l.

Sanjeev Kumar Jha

Ravindra Shankar Ganiger

Bugra Han Ertas

Andrea Piazza

James Jonathan Grant

Harish Bommanakatte

Sheo Narain Giri

Richa Awasthi

Bhaskar Pemmi

Gontla Nagashiresha

Madhu Bharadwaj Sridharan

Rajarshi Saha

Indrajit Mazumder

Santhosh Donkada

Richard Francis Gutta

Ronald Stuart Denmark

Prem Navin Dhayanandam

Vasantharuban Subramanian

Krishna Kishore Gumpina

Rajesh Achudhan

Jayashankar Kn

Shravan Kumar Bhagavatula

Santhosh Kumar Kompally

A differential gearbox assembly for a turbine engine having a fan shaft and a drive shaft. The differential gearbox assembly includes an epicyclic gear assembly coupling the fan shaft to the drive shaft. The epicyclic gear assembly includes a sun gear, a planet gear constrained by a planet carrier, and a ring gear. The sun gear is coupled to the drive shaft and the planet carrier is coupled to the fan shaft. The sun gear, the planet gear, and the ring gear all rotate about the drive shaft. The differential gearbox assembly includes an electric machine assembly that includes an input coupled to the epicyclic gear assembly. The electric machine assembly provides mechanical power to the fan shaft through the epicyclic gear assembly.

Differential gearbox assembly for a turbine engine

An airfoil and shroud assembly includes an airfoil including a root end, a free end and a tenon extending from the free end, the tenon including a base and an externally threaded stud extending from the base. A shroud includes an opening configured to receive the base of the tenon. A nut is configured to be threadably coupled to the externally threaded stud on the tenon on the airfoil to couple the shroud to the airfoil.

Airfoil shroud assembly using tenon with externally threaded stud and nut

A cooling arrangement for a gas turbine engine. The cooling arrangement comprises a discharge channel for air flow from a compressor, a first cooling channel and at least one aperture providing communication between the flow of air through the discharge channel and the first cooling channel. A restrictor device in the aperture regulates the flow of air between the discharge channel and the first cooling channel. The restrictor device deforms to vary air flowing through the aperture in response to a physical condition of the engine. This physical condition of the engine may be that of the temperature of air flowing through the discharge channel, the restrictor device responding to regulate the flow of air based on that temperature. The restrictor device may be a two-way shape memory alloy.

Part load performance improvement using deformable bore plugs

Embodiments of the present application include a gas turbine system. The system may include a rotor wheel and one or more impeller vanes radially disposed on the rotor wheel. The system may also include one or more fluid passages defined by adjacent impeller vanes. The one or more fluid passages may be radially disposed across the rotor wheel. Moreover, the system may include one or more shape memory alloy valves disposed within each of the fluid passages. The one or more shape memory alloy valves may be configured to change shape to control a flow of fluid through the fluid passages.

Systems and methods to control flow in a rotor wheel

A connection ring assembly and connection ring support system for a dynamoelectric machine is provided. The connection ring assembly includes a plurality of connection rings, and a clamp element disposed around a portion of the connection rings. The clamp element provides axial and tangential support to the plurality of connection rings. The connection ring support system includes one or more primary spring bars connected to the connection ring assembly. The primary spring bars permit radial and tangential movement of the connection ring assembly. One or more secondary spring bars are connected to the primary spring bars, and permit axial movement of the connection ring assembly.

Support system for dynamoelectric machine

Embodiments of the invention relate generally to lead path configurations in generator rotors and, more particularly, to a support apparatus for a main lead and generator rotors incorporating such a support apparatus. In one embodiment, the invention provides a generator rotor comprising: a rotor shaft including an internal conductive bore; a main terminal electrically connected to the conductive bore; a plurality of rotor coil windings, including a plurality of coil end straps; a non-metallic support channel comprising: an elongate, axially-oriented channel; and at least one protrusion extending from the elongate, axially-oriented channel to a position between two of the plurality of coil end straps; and a main lead extending from the main terminal, through the elongate, axially-oriented channel of the non-metallic support channel, to at least one of the plurality of coil end straps.

Generator rotor main lead support and lead path configuration

Embodiments of the invention relate generally to lead path configurations in generator rotors and, more particularly, to a support apparatus for a main lead and generator rotors incorporating such a support apparatus. In one embodiment, the invention provides a support apparatus for a main lead of a generator rotor, the support apparatus comprising: a cross-sectionally L-shaped body having: a first portion; and a second portion substantially perpendicular to the first portion, wherein the first portion includes an arcuate first surface for interfacing with a centering ring of the generator rotor and an arcuate second surface adapted to be substantially parallel to a rotor shaft of the generator rotor; a main lead passage extending along the arcuate first surface of the first portion and through the second portion.

Growing community of inventors

Bengaluru, India

Sanjeev Kumar Jha