General Electric Company

Sylvain Pierre

Rohit Chouhan

Paul Kendall Smith

Harish Bommanakatte

Spencer Aaron Kareff

Sumeet Soni

Srinivasa Govardhan Jayana

Santhosh Kumar Vijayan

Gunnar Leif Siden

Bradley Taylor Boyer

Kevin Weston McMahan

Zachary John Snider

Kurt Kramer Schleif

Brendon James Leary

Andres Jose Garcia-Crespo

Melbourne James Myers

Carl Gerard Schott

Thomas William Vandeputte

Alexander Stein

Prem Venugopal

Jalindar Appa Walunj

Joseph Anthony Cotroneo

Bryan David Lewis

Jason Adam Neville

Clint Luigie Ingram

Andrew Ray Kneeland

Michael Gordon Sherman

Zhirui Dong

Debdulal Das

Luke C Sponseller

Stephen Walter Newman

Marvin Luther Neeley

Le Trong Tran

Dustin James Hall

Dennis Scott Holloway

Holly Davis Brown

Jinmei Zhang

Gunnar Leaf Siden

A turbine rotor blade including an airfoil that extends from a platform. The platform may include a first portion of a nominal platform contour substantially in accordance with Cartesian coordinate values of X', Y&#x2032;, and Z&#x2032; as set forth in Table II. The Cartesian coordinate values of X&#x2032;, Y&#x2032;, and Z&#x2032; are non-dimensional values from 0% to 100% convertible to dimensional distances by multiplying the Cartesian coordinate values of X&#x2032;, Y&#x2032;, and Z&#x2032; by a height of the airfoil defined along a Z&#x2032; axis. The X&#x2032; and Y&#x2032; values of the first portion are coordinate values that, when connected by smooth continuing arcs, define contour lines of the first portion of the nominal airfoil profile at each Z&#x2032; coordinate value. The contour lines may be joined smoothly with one another to form the first portion.

Airfoil shape and platform contour for turbine rotor blades

A turbine nozzle has an airfoil that includes a pressure side portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a pressure side as set forth in Table I. The Cartesian coordinate values of X, Y, and Z are non-dimensional values from 0% to 100% convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil defined along the Z axis. The X and Y values of the pressure side are coordinate values that, when connected by smooth continuing arcs, define pressure side sections of the pressure side portion of the nominal airfoil profile at each Z coordinate value. The pressure side sections may be joined smoothly with one another to form the pressure side portion.

Airfoil shape for turbine nozzles

A turbine nozzle includes an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.

Turbine nozzle airfoil profile

A turbine rotor blade having an airfoil that includes a pressure side portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a pressure side as set forth in Table I. The Cartesian coordinate values of X, Y, and Z are non-dimensional values from 0% to 100% convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil defined along the Z axis. The X and Y values of the pressure side are coordinate values that, when connected by smooth continuing arcs, define pressure side sections of the pressure side portion of the nominal airfoil profile at each Z coordinate value. The pressure side sections may be joined smoothly with one another to form the pressure side portion.

Airfoil shape for turbine rotor blades

A turbine nozzle having an airfoil that includes a pressure side portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a pressure side as set forth in Table I. The Cartesian coordinate values of X, Y, and Z are non-dimensional values from 0% to 100% convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil defined along the Z axis. The X and Y values of the pressure side are coordinate values that, when connected by smooth continuing arcs, define pressure side sections of the pressure side portion of the nominal airfoil profile at each Z coordinate value. The pressure side sections may be joined smoothly with one another to form the pressure side portion.

Embodiments of the present disclosure are directed toward systems including a turbomachine blade tip shroud having a pressure side portion and a suction side portion. The pressure side portion and the suction side portion are divided by a mean camber line of a turbomachine blade, and the pressure side portion has a greater surface area than the suction side portion.

Turbomachine blade tip shroud

An assembly for use in a turbine engine is provided. The assembly includes a first bucket, a second bucket circumferentially adjacent to the first bucket, a shroud extending between the first and second buckets, and an aerodynamic shell substantially encircling the shroud such that a cavity is formed between the aerodynamic shell and the shroud.

Bucket assembly for use in a turbine engine

A method for enhancing one or more performance parameters of a gas turbine having at least one row of clocked airfoils may generally include choosing a first, a second and a third row of airfoils where the third row is clocked relative to the first row. An unsteady computational fluid dynamics model may be used to determine at least one wake parameter of a working fluid flowing from the second row of the airfoils to the third row of the airfoils. At least one design parameter of the airfoils of the second row may be modified, and the unsteady computational fluid dynamics model may then be used to determine the effect of the airfoil design parameter modification on the at least one wake parameter. The effect on the wake parameter may be compared to a predetermined target range.

Method for modifying gas turbine performance

Transition duct assemblies for turbine systems and turbomachines are provided. In one embodiment, a transition duct assembly includes a plurality of transition ducts disposed in a generally annular array and comprising a first transition duct and a second transition duct. Each of the plurality of transition ducts includes an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of each transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The transition duct assembly further includes an aerodynamic structure defined by the passages of the first transition duct and the second transition duct. The aerodynamic structure includes a pressure side, a suction side, and a trailing edge, the trailing edge having a modified aerodynamic contour.

Transition duct assembly with modified trailing edge in turbine system

Embodiments of the present disclosure include a turbomachine having a turbomachine blade and a stationary structural component. The turbomachine blade includes a tip shroud having a leading edge portion where the leading edge portion has a first surface. The stationary structural component is disposed about the turbomachine blade and includes a corresponding portion corresponding to the leading edge portion of the tip shroud, where the corresponding portion has a second surface, where the first surface and the second surface have generally parallel contours.

Turbomachine blade tip shroud with parallel casing configuration

A turbine blade includes an airfoil portion including a suction side having a suction side contour, a pressure side having a pressure side contour, a leading edge, a trailing edge and a tip portion, and a squeeler pocket formed in the tip portion. The squeeler pocket includes a first side wall and a second side wall. The first side wall includes a first internal surface having a first substantially continuous curvilinear profile and the second side wall includes a second internal surface having a second substantially continuous curvilinear profile. A bleed passage extends from the squeeler pocket towards the trailing edge. The first and second side walls are configured to deliver a substantially unobstructed fluid flow from the squeeler pocket to the bleed passage and limit the fluid flow spillage onto one of the pressure side and the suction side.

Turbomachine blade including a squeeler pocket

Turbine blade assemblies of a turbine include airfoils that are mounted on bases. The leading and/or trailing edges of the bases are provided with curved portions. Likewise, curved portions may be provided on leading and/or trailing edges of the angle wings of a turbine blade assembly. Also, curved portions may be provided on the leading and/or trailing edges of nozzle assemblies of a turbine.

Non-axisymmetric airfoil platform shaping

An instrumentation rake assembly comprises a rake tower capped at an immersed end and mated to a lead carrier at a base end. The rake tower comprises a curved wall oriented along a longitudinal axis and supporting a plurality of probe holders. The curved wall has an inner surface defining an internal passage for carrying instrumentation from the probe holders to the lead carrier. In another aspect, an instrumentation rake assembly comprises a plurality of rake towers, each having a base end and an immersed end, and each rake tower being coupled at its immersed end to one or more other rake towers.

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Greer, SC, United States of America

Sylvain Pierre