General Electric Company

Richa Awasthi

Ravindra Shankar Ganiger

Anusrita Raychaudhuri

Bhanu Kishore Battu

Nilesh Vilas Varote

James Jonathan Grant

Abhijeet Jayshingrao Yadav

Viswanadha Gupta Sakala

Sanjeev Kumar Jha

Shawn Patrick Riley

Madhu Bharadwaj Sridharan

Venkata Jayateja Nedunuri

Moorthi Subramaniyan

Vidyashankar Ramasastry Buravalla

Shalini Thimmegowda

Srinivasan Swaminathan

Michael Jason Bishop

Abhishek Goverdhan

Sachin Kumar Rai

Vidya Lokammanahalli Shivashankar

Shruti Kulkarni

Vishwanath Thippeswamy

K G V Siva Kumar

Clearance control systems with electromagnetic actuators are disclosed. An example electromagnetically-actuated clearance control system for a gas turbine engine comprises an electromagnetic coil coupled to a first end of a facesheet, the electromagnetic coil to generate a magnetic field in response to a connection of a power supply, a ferromagnetic sheet coupled to a second end of the facesheet, the ferromagnetic sheet drawn radially-inward toward the electromagnetic coil when the magnetic field is generated, a first end of the ferromagnetic sheet coupled to a first compression spring and a second end of the ferromagnetic sheet coupled to a second compression spring, the first and second compression springs to compress in response to the ferromagnetic sheet being drawn radially-inward.

Clearance control of fan blades in a gas turbine engine

Variable sleeve clearance control systems for gas turbine engines are disclosed. An example variable sleeve clearance control system for a gas turbine engine includes a sleeve comprising a first end and a second end, the first end of the sleeve coupled to a first spring that biases the sleeve inward, and the second end of the sleeve coupled to a second spring that biases the sleeve outward, a proximity sensor to measure a clearance width, and a controller for each of the first and second springs, the controller to obtain the measured clearance width from the proximity sensor and determine a response of the first and second springs.

Active clearance control of fan blade tip closure using a variable sleeve system

Systems and methods for measuring the clearance gaps between rotating and stationary components of a turbomachine are provided. In one exemplary aspect, flexible and degradable sensing arrays that include a plurality of microwave sensors are utilized to sense the clearance gaps between rotating and stationary components of the turbomachine. Microwaves generated by a microwave generator are transmitted to the sensors. Upon rotation of the rotating components, the rotating components reflect the microwaves transmitted thereto. The microwave sensors capture the transmitted signal and also capture a reflected signal indicative of the transmitted signal reflected by the rotating components. The signals are then forwarded to a computing device for processing. The amplitude difference at the interference fringes between the superimposed signals is representative of the clearance gaps between the rotating and stationary components. After measuring the clearance gaps, the turbomachine may be operated and the degradable sensing array may be consumed.

System and method for measuring clearance gaps between rotating and stationary components of a turbomachine

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

A fastener cover assembly is disclosed. The cover assembly includes a turbomachinery component having an outer surface exposed to an air flow path; at least one recess formed in the outer surface; a fastener contained in the at least one recess; and a fastener cover secured in the at least one recess, the cover having an outer surface substantially flush with the outer surface of the component to minimize air flow disruption.

Fastener cover for flowpath fasteners

An exhaust diffuser arrangement for a turbine system includes an inlet for receiving a flow proximate a last stage bucket of the turbine system, the flow flowing in a first flow direction. Also included is a flow redirecting component. The flow redirecting component includes a first wall having a first side of a concave surface geometry for redirecting the flow and a second side of a convex surface geometry. The flow redirecting component also includes a second wall spaced downstream of the first wall and having at least one flow exit for reducing a boundary layer along the second side of the first wall.

Exhaust diffuser arrangement for a turbine system and method of redirecting a flow

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.

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Bengaluru, India

Richa Awasthi