General Electric Company

Siemens Energy Global Gmbh & Co. Kg

Ross James Gustafson

Farzad Taremi

Rohit Chouhan

Sumeet Soni

Li Shing Wong

Christopher Michael Penny

Aaron Ezekiel Smith

William Scott Zemitis

Andres Jose Garcia-Crespo

Gunnar Leif Siden

Spencer Aaron Kareff

Xiaoyong Fu

Srinivasa Govardhan Jayana

Aaron Gregory Winn

Jason Adam Neville

Nicholas Alvin Hogberg

John Franklin Ryman

Matthew Peter Scoffone

Horia Flitan

Andrew Miller

Dipesh Dinesh Nanda

Luke C Sponsellar

Masayoshi Senga

Bharat Prabhu

Anne Maria Starke

A turbine blade includes a root arranged to attach the turbine blade to a rotor and a vane extending in a radial direction from the root to a tip surface. The vane includes a leading edge, a trailing edge, a pressure-side surface, and a suction-side surface that cooperate to define a vane perimeter. A perimeter wall extends radially from the tip surface and surrounds a portion of the vane perimeter. A first trench wall extends across the tip surface and cooperates with the perimeter wall to substantially enclose a pressure-side pocket and a second trench wall extends across the tip surface and cooperates with the perimeter wall to substantially enclose a suction-side pocket.

Turbine blade

A turbine operable to convey a flow of exhaust gas along a central axis includes a strut having a flow portion positioned within the flow of exhaust gas and a strut cover having a length and positioned to surround the flow portion of the strut, the strut cover including a leading-edge portion, a mid-chord portion, and a trailing-edge portion. The mid-chord portion has a uniform cross-section, and the trailing-edge portion has a trailing-edge center positioned such that the mid-chord portion and the trailing-edge portion define a master chord plane. The leading-edge portion defines a leading-edge nose, and the leading-edge portion is twisted with respect to the master chord plane and the leading-edge nose along the length defines a curve that is not coincident with the master chord plane.

Strut cover for a turbine

A turbine stage includes a first airfoil and a second airfoil extending respectively from a first platform and a second platform that form an endwall for a flow passage. The endwall has a nominal surface that is axisymmetric about an axis of the turbine stage. The endwall further includes at least one contoured region that is non-axisymmetric with respect to the axis. The at least one contoured region extends from the first platform to the second platform across a platform splitline. The global maximum variation in elevation &#x394;EW of the endwall is at least 3% of an axial chord length L of the airfoils on the endwall. The maximum variation in elevation &#x394;MF at the mate facea of the platforms lies in the range 15-60% &#x394;EW.

Turbine stage platform with endwall contouring incorporating wavy mate face

A turbine stage includes an array of airfoils spaced apart circumferentially to define a flow passage therebetween for channeling a working medium. The airfoils extend radially outward from an inner endwall located at a hub side thereof. The inner endwall is inclined at an angle to an engine axis such that the flow passage is divergent from an upstream side to a downstream side. The inner endwall is non-axisymmetric about the engine axis, having a mid-passage bulge located between circumferentially adjacent first and second airfoils. The bulge has a peak at a position between 20-60% Caxand at a position between 30-70% pitch.

Endwall contouring for a conical endwall

A turbomachine includes a plurality of nozzles, and each nozzle has an airfoil. The turbomachine has opposing walls defining a pathway into which a fluid flow is receivable to flow through the pathway. A throat distribution is measured at a narrowest region in the pathway between adjacent nozzles, at which adjacent nozzles extend across the pathway between the opposing walls to aerodynamically interact with the fluid flow. The airfoil defines the throat distribution, and the throat distribution is defined by values set forth in Table 1, where the throat distribution values are within a +/&#x2212;10% tolerance of the values set forth in Table 1. The throat distribution reduces aerodynamic loss and improves aerodynamic loading on each airfoil.

Turbomachine and turbine nozzle therefor

A turbine rotor blade is provided including an airfoil having an airfoil shape. The turbine rotor blade airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein 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, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.

Airfoil shape for a turbine rotor blade

A blade has an airfoil, and the blade is configured for use with a turbomachine. The airfoil has a throat distribution measured at a narrowest region in a pathway between adjacent blades, at which adjacent blades extend across the pathway between opposing walls to aerodynamically interact with fluid flow. The airfoil defines the throat distribution, and the throat distribution reduces aerodynamic loss and improves aerodynamic loading on the airfoil. The airfoil has a linear trailing edge profile.

Turbomachine and turbine blade therefor

A turbomachine includes a plurality of blades, and each blade has an airfoil. The turbomachine includes opposing walls that define a pathway into which a fluid flow is receivable to flow through the pathway. A throat distribution is measured at a narrowest region in the pathway between adjacent blades, at which adjacent blades extend across the pathway between the opposing walls to aerodynamically interact with the fluid flow. The airfoil defines the throat distribution, and the throat distribution reduces aerodynamic loss and improves aerodynamic loading on each airfoil.

Turbomachine and turbine blade transfer

Turbine frequency tuning, fluid dynamic efficiency, and performance can be improved using a particular airfoil profile, which can be used to determine a throat between adjacent airfoils. By shaping the throat according to the particular profile, the total pressure at an endwall can be energized, improving performance of the turbine.

Turbine bucket profile yielding improved throat

A turbine bucket is provided including a bucket airfoil having an airfoil shape, the bucket airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein 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, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.

Turbine bucket airfoil profile

The present application thus provides a gas turbine engine. The gas turbine engine may include a turbine and a diffuser positioned downstream of the turbine. The turbine may include a number of last stage buckets, a number of last stage nozzles, and a gauging ratio of the last stage nozzles of about 0.95 or more.

Turbine last stage flow path

Certain embodiments of the present disclosure include a system having a turbomachine including a plurality of turbomachine blades coupled to a rotor, wherein each turbomachine blade has a blade base portion and a flared blade tip portion flared relative to the blade base portion. Additionally, a trailing edge of each turbomachine blade extends along a common plane.

Turbomachine blade with tip flare

The present application provides a turbine nozzle including 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 1. 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 are distances in inches which, 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.

Growing community of inventors

Greenville, SC, United States of America

Ross James Gustafson