General Electric Company

Bruce Clark Busbey

David William Crall

Christopher Charles Glynn

Gregory Terrence Garay

Stefan Herr

Ian Francis Prentice

Matthew Mark Weaver

Matthew John McKeever

Michael James Healy

Thomas Joseph Fischetti

Christian Aloysius Carroll

Aaron John Mashue

Robin Charles Payne

Jack W Baldwin

Ramesh Vedula

Damir Novak

Wilfried Rick

Carlos Alberto Cardoza

Thomas Peter Sommer

Olivier Anthony Bron

Revathy Murugappan

Satish Balusu

Yu Wang

Jan Christopher Schilling

Darren John Danielsen

Jamie Thomas Livingston

Xiaoming Liu

Scott Gabell Riddell

Xu Fu

Amir Riahi

Thomas Robbins Tipton

Rong Li

Christopher Edward LaMaster

Eric Richard Bonini

Kevin Michael Barnett

Afroz Akhtar

Jan Willem Bakhuis

Bart Jan Veldkamp

Joseph J Jackson

Eric Morgan Jacobsen

Stephen J Szpunar

Randall Charles Bauer

Sidney B Elston, Iii

Aaron David Williamson

James W Tucker

Edward McBeth Stewart

Saravakota Sambamurty

Qi Zhu

William John Miller

Juergen Esser

William E Dixon

Jamie Dean Lumpkin

James Robert Bailey

Donald Ray Bond

John A Ravenhall

Dejan Mikasinovic

Denis Stanković

Pradeepa Nagabhushana

Kevin Clement Metz

Josip Galic

Lynn M Naparty

Kerry W Quinn

Lukasz Marcin Maczka

Michael D Toye

Damir Fanjak

Lance William Smith

Gerrit Ruch

Alex David Hollanshead

Wilfred Aaw

James Alphonse Payant

Robert Roy Anderson

Cleveland Clifford Matthew Joseph, Jr

Ervin Alimani

Bhushan Suhas Thatte

A rotor blade includes an airfoil having an airfoil shape. The airfoil shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in one of Table I, Table II, Table III, Table IV, Table V, Table VI, Table VII, Table VIII, Table IX, Table X, Table XI, or Table XII. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values are joined smoothly with one another to form a complete airfoil shape.

Compressor rotor blade airfoils

A stator vane includes an airfoil having an airfoil shape. The airfoil shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in one of Table I, Table II, Table III, Table IV, Table V, Table VI, Table VII, Table VIII, Table IX, Table X, Table XI, or Table XII. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values are joined smoothly with one another to form a complete airfoil shape.

Compressor stator vane airfoils

A tool for removal of a bushing (such as a bushing of a variable stator vane assembly of a compressor) is provided. The tool includes a cylindrical housing, a lead screw, a threaded nut, and a pulling module with puller arms to engage the bushing. The housing defines a longitudinal axis along which the lead screw extends. The lead screw is rotatably secured within the cylindrical housing by a threaded nut engaged with the lead screw. The pulling module is removably attached to the threaded nut, such that the lead screw passes through the threaded nut before passing through the pulling module. The pulling module is provided with a pair of oppositely disposed puller arms, and each puller arm is provided with a hook portion having an engagement tab configured to engage a respective notch on the bushing. A method of removing the bushing using the tool is also disclosed.

Tool and method for removal of variable stator vane bushing

A wind turbine rotor blade assembly and associated method include a rotor blade having a pressure side, a suction side, a leading edge, and a trailing edge extending in a generally span-wise direction between a tip and a root. An edge extension panel is attached along either of the leading edge or trailing edge (or along both edges) in a generally span-wise direction from adjacent the root towards the tip. The edge extension panels include a cured and hardened viscous material continuous core formed onto the leading or trailing edge with a contoured generally aerodynamic outer surface.

Wind turbine rotor blade assembly with root extension panel and method of assembly

The present disclosure is directed to a system and method for reducing electrical arcs caused by lightning strikes in a rotor blade of a wind turbine. The rotor blade includes a lightning protection system with at least one lightning receptor connected to at least one conductor and a conduit assembly. The conduit assembly has one or more conduit members configured to route the conductor of the lightning protection system from a first blade location to a second blade location so as to maximize a distance between the conductor and one or more conductive rotor blade components.

Conduit assembly for a lightning protection cable of a wind turbine rotor blade

The present subject matter is directed to a wind turbine blade alignment method. A sensor provided on the blade at a blade station with a known twist angle is used to measure an installation angle of the blade station. The installation angle is adjusted if the installation angle measured by the sensor is not equal to the known twist angle. A wind turbine with such a sensor for measuring an installation angle used for blade alignment is also provided.

Wind turbine and blade alignment method thereof

A system and method for mounting a component to an internal web of a wind turbine blade includes, at a first mounting location on the internal web, at least one through-hole defined through the internal web. A bushing is located within the through-hole and is encased within an adhesive applied between the bushing and a wall of the through-hole. A plate is attached to each of the opposite panels of the internal web at the mounting location against an end face of the bushing, with each plate having a hole therein that is aligned with the through-hole. For mounting the component at the mounting location, a bolt is passed completely through the plates and bushing for attachment of a frame of the component to one of the plates.

System and method for attaching components to a web in a wind turbine rotor blade

A spar assembly for a rotor blade of a wind turbine is disclosed. The spar assembly includes a first spar cap segment and a second spar cap segment. The first spar cap segment is configured on an interior surface of a first blade segment and the second spar cap segment is configured on an interior surface of a second blade segment. Each spar cap segment includes an end having a joint section that is joinable at a chord-wise joint. Each of the first and second joint sections includes a plurality of holes formed therein. Further, the spar assembly includes a plurality of pins inserted into the plurality of holes of the first and second joint sections to join the first and second blade segments so as to improve stiffness of the rotor blade.

Spar assembly for a wind turbine rotor blade

A rotor blade assembly for a wind turbine has a rotor blade. A strip-member blade accessory is mounted to one of the rotor blade surfaces that stretches under normal operating conditions of the wind turbine. The blade accessory has a base portion. An attachment layer connects the base portion to the rotor blade surface and has a lower shear modulus than the base portion to allow for shear slippage between the base portion and the underlying rotor blade surface.

Attachment system for a wind turbine rotor blade accessory

A blade insert for coupling a first blade segment to a second blade segment is disclosed. The blade insert may generally include an aerodynamic body extending between a forward end configured to be coupled to the first blade segment and an aft end configured to be coupled to the second blade segment. The aerodynamic body may include a top side extending between a forward edge and an aft edge. The top side may define a top scarfed section at its forward edge. The aerodynamic body may further include a bottom side extending between a forward edge and an aft edge. The bottom side may define a bottom scarfed section at its forward edge. Additionally, at least a portion of the forward edge of the top side may be configured to be offset relative to the forward edge of the bottom side.

Blade insert for a wind turbine rotor blade

A system for installing a blade insert between a root portion and a tip portion of a rotor blade of a wind turbine is disclosed. The system may include a root cradle assembly configured to support the root portion of the rotor blade and a tip cradle assembly configured to support the tip portion of the rotor blade. At least one of the tip cradle assembly or the root cradle assembly may be movable relative to the other of the tip cradle assembly or the root cradle assembly to allow the tip portion to be spaced apart from the root portion after the rotor blade has been divided between the root and tip portions. In addition, the system may include an insert cradle assembly configured to support a blade insert for the rotor blade. The insert cradle assembly may be configured to be positioned between the root cradle assembly and the tip cradle assembly so as to position the blade insert between the root portion and the tip portion.

System and method for installing a blade insert between separate portions of a wind turbine rotor blade

An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE A. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances can be joined smoothly with one another to form a complete airfoil shape.

Airfoil shape for a compressor blade

A turbine rotor blade includes a hollow airfoil joined to a platform and dovetail. A main flow channel extends longitudinally in span through the blade and is bound chordally by opposite partitions transversely bridging opposite sidewalls of the airfoil. A damper rib and transversely opposite damper pad are arranged together in a plurality of pairs spaced longitudinally apart in the airfoil and chordally positioned intermediate to the partitions to provide unobstructed forward and aft portions of the flow channel for channeling a coolant therethrough. The damper ribs and pads are configured to receive a wire damper through the channel to locally dampen vibration while minimizing obstruction of the coolant flow therethrough.

Damper configured turbine blade

A turbine or compressor blade assembly includes a blade fixed to a dovetail section attachable to a wheel. The dovetail section has a dovetail shaped to fit in a correspondingly shaped slot in the wheel. A dovetail platform serves as an interface between the blade and the dovetail. An undercut fillet radius is formed at an intersection of the dovetail platform and a dovetail pressure surface, where the undercut radius has a multi-part profile shape configured to attenuate edge of contact stresses. An additional feature is the area where the undercut radius transitions into the P-cut area at the forward end (leading edge) of the dovetail.

Undercut fillet radius for blade dovetails

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Greer, SC, United States of America

Bruce Clark Busbey