General Electric Company

James Paul Davidson

Darren John Danielsen

Kevin Wayne Kinzie

Andrew Mitchell Rodwell

Kattalaicheri Srinivasan Venkataramani

Scott Gabell Riddell

Alan Majors Walker

Jignesh Govindlal Gandhi

Roger Drobietz

Michael Christopher Booth

Ramy Michael Souri

Christopher Lee Tschappatt

Lawrence Nmn Butler

Philip James Verzella

Nicholas Michael Seruntine

David Patrick Cripps

Sebastien David Bertrand

Robert Karl Huck

Miguel Cabrera Lange

A method for manufacturing a rotor blade root assembly includes placing outer skin layer(s) onto a blade mold and arranging a root plate with a plurality of through holes adjacent to an end face of the blade mold. The method also includes placing a plurality of root inserts atop the outer skin layer(s) and abutting against the root plate, with each of the root inserts defining a fastener hole. The method also includes inserting a root fastener into each of the aligned through holes and longitudinal fastener holes. Moreover, the method includes placing inner skin layer(s) atop the root inserts. Further, the root plate may include at least one fluid hole configured therethrough to provide a non-gas tight root plate. Alternatively, at least one seal may be arranged between the root plate and the blade mold that forms a non-gas tight connection with either or both of the root plate or the blade mold during a vacuum infusion process. Thus, the method includes securing the outer skin layer(s), the root inserts, the inner skin layer(s), and the root fasteners together to form the root assembly via the vacuum infusion process.

Method for manufacturing a wind turbine rotor blade root assembly

A method for reducing loads of a wind turbine includes determining an angular pitch speed parameter of the rotor blade of the wind turbine. The method also includes determining an operational state of the wind turbine. Further, the method includes comparing the angular pitch speed parameter to a predetermined parameter threshold during turbine shutdown and/or a commanded pitch event. If the operational state corresponds to a predetermined operational state, the method includes yawing a nacelle of the wind turbine away from an incoming wind direction when the angular pitch speed parameter is below the predetermined parameter threshold during the turbine shutdown and/or the commanded pitch event.

System and method for reducing loads during an idling or parked state of a wind turbine with a stuck rotor blade

A method for automatically updating data associated with a wind turbine based on component self-identification may generally include providing instructions for transmitting a polling signal to an identification sensor associated with a wind turbine component and, in response to the transmission of the polling signal, receiving current configuration data for the wind turbine component from the identification sensor. The method may also include comparing the current configuration data received from the identification sensor to last-known configuration data for the wind turbine component and automatically updating one or more parameter settings associated with operating the wind turbine based on any differences identified between the current configuration data and the last-known configuration data.

System and method for automatically updating wind turbine data based on component self-identification

A rotor blade assembly for a wind turbine is disclosed. The rotor blade assembly includes a rotor blade having surfaces defining a pressure side, a suction side, a leading edge, and a trailing edge extending between a tip and a root. The rotor blade assembly further includes a noise reducer configured on a surface of the rotor blade. The noise reducer includes a plurality of noise reduction features and a plurality of auxiliary noise reduction features. Each of the plurality of auxiliary noise reduction features is configured on one of the plurality of noise reduction features.

Noise reducer for rotor blade in wind turbine

A gas turbine engine having a longitudinal centerline axis therethrough, including: a fan section at a forward end of the gas turbine engine including at least a first fan blade row connected to a first drive shaft; a booster compressor positioned downstream of the fan section, the booster compressor including a first compressor blade row and a second compressor blade row connected to a second drive shaft and interdigitated with the first compressor blade row; and, a pulse detonation system for powering the first and second drive shafts. The pulse detonation system powers only the second drive shaft during a first designated condition of the gas turbine engine and both the first drive shaft and the second drive shaft during a second designated condition of the gas turbine engine. The first and second drive shafts are powered independently of each other by the pulse detonation system.

Pulse detonation system for a gas turbine engine having multiple spools

Growing community of inventors

Greer, SC, United States of America

James Paul Davidson