General Electric Company

General Electric Renovables Espana, S.l.

Hiteshkumar Rameshchandra Mistry

Zachary James Taylor

Rohit Chouhan

Shashwat Swami Jaiswal

Ying Zhou

Randall Richard Good

Sandeep Dhar

Lucas Seth Wedmore

Ankit Rajesh Surti

Rwitam Mitra

Dinesh Rakwal

Luv Verma

A method for detecting actual slip in a coupling of a rotary shaft, for example, in a wind turbine power system, includes monitoring, via a controller, a plurality of sensor signals relating to the coupling for faults. In response to detecting a fault in the plurality of sensor signals relating to the coupling, the method includes determining, via the controller, whether the fault is indicative of an actual slip or a no-slip event of the coupling using one or more classification parameters. When the fault is indicative of the actual slip, the method includes estimating, via the controller, a magnitude of the actual slip using the plurality of sensor signals and a time duration of the actual slip. Further, the method includes implementing, via the controller, a control action based on the magnitude of the actual slip in the coupling.

System and method for detecting actual slip in a coupling of a rotary shaft

A rotor blade for a turbine of a gas turbine includes an airfoil. The airfoil may have a leading edge, a trailing edge, an outboard, and an inboard end that attaches to a root configured to couple the rotor blade to a rotor disc. The airfoil may have a cooling configuration that includes elongated cooling channels for receiving and directing a coolant through the airfoil. The rotor blade may further include: a tip shroud connected to the airfoil; outlet ports formed through an outboard surface of the tip shroud that fluidly communicate with the cooling channels; and flow directing structure formed on the outboard surface of the tip shroud. The flow directing structure may be positioned relative to the outlet ports and configured for directing the flow of coolant discharged from the outlet ports. The rotor blade may be useful to reduce local tip shroud temperature as well as improved stage aerodynamic efficiency by reducing the coolant supply needed to maintain the component at desired temperature levels.

Cooling arrangements in turbine blades

A rotor blade () for a turbine of a gas turbine that includes an airfoil (). The airfoil may have a leading edge, a trailing edge, an outboard tip, and an inboard end where the airfoil attaches to a root configured to couple the turbine blade to a rotor disc. The airfoil () may include a tip shroud () at an outboard tip. The rotor blade may have a cooling configuration that includes: elongated cooling channels () for receiving and directing a coolant through the airfoil (); and branching passages () formed through the tip shroud (), each of which elongates between a connection with one of the cooling channels () and an outlet port () formed on a surface of the tip shroud (). The branching passages () may have a canted orientation relative the outboard surface of the tip shroud ().

A turbine rotor blade that includes: an airfoil defined between a pressure face and a suction face; a tip shroud that includes a seal rail projecting from an outboard surface and, formed thereon, a cutter tooth; and a cooling configuration that includes a cooling channel for receiving and directing a coolant through an interior of the rotor blade. The cooling channel may include fluidly connected segments, in which: a supply segment extends radially through the airfoil; a cutter tooth segment is formed within the cutter tooth of the seal rail; and branching segments formed within at least one of the tip shroud and an outboard region of the airfoil. Each of the branching segments may extend between an upstream port, which connects to the cutter tooth segment, and an outlet port, which is formed on a target surface area, so that the branching segment bisects a target interior region.

Interior cooling configurations in turbine rotor blades

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Bengaluru, India

Hiteshkumar Rameshchandra Mistry