General Electric Company

General Electric Technology Gmbh

Xiuzhang James Zhang

Gary Michael Itzel

Benjamin Paul Lacy

Aaron Ezekiel Smith

Sandip Dutta

Adebukola Oluwaseun Benson

Melbourne James Myers

Camilo Andres Sampayo

Nicholas Alvin Hogberg

Sergio Daniel Marques Amaral

Haiping Wang

Brian Peter Arness

Stephen Paul Wassynger

Anthony Louis Giglio

Niraj Kumar Mishra

Mitchell Allan Merrill

Anthony Aaron Chiurato

Zhirui Dong

Lisa DeBellis

Rachel Kyano Black

Kevin Richard Kirtley

Scott Edmond Ellis

Shashwat Swami Jaiswal

Jeffrey Clarence Jones

Ibrahim Sezer

Kassy Moy Hart

Jalindar Appa Walunj

David Samuel Pesetsky

Joseph Anthony Cotroneo

James Tyson Balkcum, Iii

Michael Adelbert Sullivan

Jason Adam Neville

Felipe Roman-Morales

Ian Darnall Reeves

Sachin Kumar Rai

Mohankumar Banakar

Joseph Block

Murugesan Seerangan

Olivier Muller

Tahar Bouktir

Stuart Samuel Collins

Kenneth Earl Williams

Robert Joseph Testa, Jr

James Tyson Balkcum Iii

A blade for a turbomachine includes an airfoil extending radially between a root and a tip with a tip shroud coupled to the tip of the airfoil. The tip shroud includes a platform having an outer surface extending generally perpendicular to the airfoil. The tip shroud also includes a forward rail extending radially outward from the outer surface of the platform. The forward rail is oriented generally perpendicular to a hot gas path of the turbomachine. A cooling cavity is defined in a central portion of the platform. The tip shroud also includes a cooling channel extending between the cooling cavity and an ejection slot formed in the forward rail. The ejection slot is positioned radially outward of the outer surface of the platform of the tip shroud.

Turbomachine blade cooling structure and related methods

A turbine rotor blade that includes a tip shroud attached to the outboard tip of the airfoil. The tip shroud may include an axially and circumferentially extending planar component in which an inboard surface opposes an outboard surface, and a shroud edge that connects the inboard surface to the outboard surface and defines an outboard profile of the tip shroud. The tip shroud may include a seal rail protruding from the outboard surface of the tip shroud and a cutter tooth disposed on the seal rail. The cutter tooth may be formed as a circumferential section of the seal rail that is axially thickened. The seal rail may further include a leakage gap formed therethrough that is configured to increase a leakage level during operation.

Shroud configurations for turbine rotor blades

This disclosure provides components and methods for blade extensions with internal features. An airfoil extends from a root connector and includes an airfoil body defining at least one air channel enclosed within the airfoil body. The air channel extends to a build surface. An additive extension extends from the build surface of the airfoil body. The additive extension includes an additive structure extending the air channel from the build surface to an external surface of the additive extension.

Additively manufactured blade extension with internal features

The present disclosure is directed to a rotor blade for a gas turbine system. The rotor blade includes a platform having a radially inner surface and a radially outer surface. A shank portion extends radially inwardly from the radially inner surface of the platform. The shank portion and the platform collectively define a shank pocket. An airfoil extends radially outwardly from the radially outer surface of the platform. The shank portion, the platform, and the airfoil collectively define a cooling passage extending from a cooling passage inlet defined by the shank portion or the platform and directly coupled to the shank pocket through the platform to a cooling passage outlet defined by the airfoil.

Cooling passage for gas turbine system rotor blade

The present disclosure is directed to a rotor blade for a gas turbine engine. The rotor blade includes a platform comprising a radially inner surface, an undulating radially outer surface, a leading edge portion, a trailing edge portion, a pressure-side slash face, and a suction-side slash face. An airfoil extends outwardly from the undulating radially outer surface of the platform to an airfoil tip. A connection portion extends radially inwardly from the radially inner surface of the platform. The platform, the airfoil, and the connection portion collectively define a cooling circuit extending from an inlet in the connection portion through the airfoil to a plurality of outlet plena in the platform. Two or more outlet plena of the plurality of outlet plena are spaced equidistant from the undulating radially outer surface of the platform.

Rotor blade cooling circuit

A turbine blade includes a tip shroud having a seal rail. The seal rail includes a tangential surface extending between tangential ends. The turbine blade includes a root portion configured to couple to a rotor and an airfoil portion extending between the root portion and the tip shroud. The seal rail includes a cooling passage extending along a length of the seal rail. The cooling passage is fluidly coupled to a cooling plenum to receive a cooling fluid via an intermediate cooling passage extending between the cooling passage and a cooling plenum. The seal rail includes cooling outlet passages fluidly coupled to the cooling passage. The cooling outlet passages are disposed within the seal rail and extend between the cooling passage and the tangential surface of the seal rail. The cooling outlet passages are configured to discharge the cooling fluid from the tip shroud via the tangential surface.

System for cooling seal rails of tip shroud of turbine blade

In one aspect of the present disclosure, an airfoil for a rotor blade of a gas turbine includes a normalized pressure side wall portion thickness, a normalized suction side wall portion thickness, a normalized leading edge wall thickness, and a normalized trailing edge wall thickness. The values of theses thicknesses define the pressure side wall portion thickness, the suction side wall portion thickness, the leading edge wall thickness, and the trailing edge wall thickness, which improve heat transfer, flow distribution, and mechanical load transfer.

Turbine airfoil internal core profile

A rotor blade includes an airfoil having a blade tip and a tip cavity formed at the blade tip. The tip cavity includes a tip cap that is recessed radially inwardly from the tip and surrounded continuously by pressure and suction side walls of the airfoil. The tip cap further includes an aperture that extends through the tip cap and provides for fluid communication between an internal cavity defined within the airfoil and the tip cavity. An exhaust port provides for fluid communication out the tip cavity through one of the pressure side wall, the suction side wall or the trailing edge. A portion of at least one of the suction side wall and the pressure side wall that defines the tip cavity extends obliquely outwardly from the tip cavity with respect to a radial direction.

Rotor blade having a flared tip

A turbomachine blade is disclosed including an airfoil including a cooling fluid plenum extending therein and a trailing edge cooling opening extending from the cooling fluid plenum through a trailing edge of the airfoil. A platform may couple the airfoil to a shank, the platform including a trailing edge extending downstream relative to the shank. At least one cooling conduit delivers a cooling fluid radially inward from at least one of the cooling fluid plenum and the trailing edge cooling opening to a wheel space that is adjacent the shank and radially inward from the trailing edge of the platform. A related turbomachine is also disclosed.

Turbomachine blade with generally radial cooling conduit to wheel space

A turbine airfoil includes a leading edge and a trailing edge. Also included is a cooling channel extending in a radial direction and tapering inwardly toward the trailing edge, the cooling channel at least partially defined by a pressure side face and a suction side face. Further included is a first plurality of turbulators protruding from one of the pressure side face and the suction side face to define a first height, the first plurality of turbulators extending toward the trailing edge of the turbine airfoil and spaced radially from each other. Yet further included is a second plurality of turbulators protruding from one of the pressure side face and the suction side face to define a second height that is less than the first height, the second plurality of turbulators extending toward the trailing edge of the turbine airfoil and spaced radially from each other.

Turbine airfoil turbulator arrangement

A rotor blade includes a mounting portion comprising a mounting body that is formed to receive a coolant therein. An airfoil portion extends substantially radially outwardly from the mounting body and includes an airfoil body. The mounting body and the airfoil body define a plurality of primary cooling passages that extend substantially radially therein for routing the coolant through the airfoil body. Each of the primary cooling passages includes a cooling flow outlet that is formed along a tip portion of the airfoil body. The airfoil body further defines a plurality of trailing edge cooling passages, each having a coolant outlet that is formed along a trailing edge portion of the airfoil body. At least a portion of the trailing edge cooling passages are formed along a radially outer portion of the trailing edge proximate to the tip portion of the airfoil body.

Rotor blade cooling

The present application provides a turbine bucket. The turbine bucket may include an airfoil and a tip shroud attached to the airfoil. The tip shroud may include a cooling core and an enhanced cooling surface.

Turbine bucket tip shroud

A casted turbine bucket having at least one machined plenum including a plenum chamber and at least one plenum passage connected to a plenum inlet at a root portion of turbine bucket, and a method to feed cooling flow to the turbine bucket using the machined plenum that receives cooling flow from the root portion of the turbine bucket.

Turbine bucket plenum for cooling flows

A layered arrangement, a hot-gas path component, and a process of producing a layered arrangement are disclosed. The layered arrangement includes a substrate layer, a ceramic matrix composite layer, and a non-metal spacer between the substrate layer and the ceramic matrix composite layer configured to define one or more pockets. The hot-gas-path component includes a nickel-based superalloy layer, a ceramic matrix composite layer, and a ceramic spacer between the nickel-based superalloy layer and the ceramic matrix composite layer. The ceramic spacer is mechanically secured to one or both of the substrate layer and the ceramic matrix composite layer, and the ceramic spacer is bonded to the substrate layer or the ceramic matrix composite layer. The process includes securing a non-metal spacer between a substrate layer and a ceramic matrix composite layer of the layered arrangement.

Layered arrangement, hot-gas path component, and process of producing a layered arrangement

A turbine bucket having an airfoil is disclosed. The airfoil may include a pressure side and a suction side extending between a leading edge and a trailing edge. In addition, the airfoil may include a tip. The tip may include a tip floor and a tip wall extending outwardly from the tip floor. The tip wall may include an inner surface defining an inner perimeter of the tip wall. Moreover, a plurality of notches may be defined by the inner surface around at least a portion of the inner perimeter.

Turbine bucket with notched squealer tip

Growing community of inventors

Simpsonville, SC, United States of America

Xiuzhang James Zhang