General Electric Company

Nuovo Pignone Holdings, S.p.a.

Jonathon Edward Slepski

Xiaoqiang Zeng

Tao Guo

Alexander Stein

Joshy John

Timothy Scott McMurray

Prakash Bavanjibhai Dalsania

Lorenzo Cosi

Sudhakar Neeli

Kenneth Michael Koza

Amir Mujezinovic

Carlo Cortese

Steven DeLessio

Andrey A Chernobrovkin

Muhammad Riaz

Airfoils according to embodiments of this invention result in a hybrid controlled flow concept that reduces leakage loss by creating a different vortexing concept near endwall regions of the airfoils than at the core region of the airfoils. Specifically, a turbine static nozzle airfoil is disclosed having a variable, non-linear, throat dimension, s, divided by a pitch length, t, distribution ('s/t distribution') across its radial length. In one embodiment, a plurality of static nozzle airfoils are provided, with each static nozzle airfoil configured such that a throat distance between adjacent static nozzle airfoils is larger proximate the hub regions of the airfoils than proximate the core regions of the airfoils, and the throat distance between adjacent static nozzle airfoils is smaller proximate the tip regions of the airfoils than proximate the core regions.

Hybrid flow blade design

A diffuser is provided for an exhaust steam housing adjacent a last stage row of buckets fixed to a rotor in a steam turbine, each bucket in the last stage row of buckets having a platform portion and an airfoil portion. The diffuser includes an annular inner diffuser ring and an outer annular diffuser ring defining a flow path for steam exiting the last stage row of buckets in a substantially axial direction at a diffuser inlet and turning substantially ninety degrees to a diffuser outlet. A first portion of the inner annular ring extends in a downstream direction beyond the last stage row of buckets substantially parallel to a center axis of the rotor, the first portion having a length dimension in the downstream direction from a radial center line of the last stage row of buckets in a range of between 0.40 and about 0.70 of a center line radial length from the platform portion to a radially outer tip of any bucket in the last stage row of buckets.

Low pressure exhaust gas diffuser for a steam turbine

A system for removing moisture from a steam/water mixture engaging a stationary component of a steam turbine. The system includes an airfoil located within a flow path of a steam turbine. The airfoil is configured for removing moisture from a steam/water mixture traveling in the flow path. To this end, the airfoil includes a cavity in flow communication with the steam path through at least one inlet and outlet opening, near the leading and trailing edge of the airfoil, respectively. Moisture and steam are extracted from the surface through the inlet openings, the steam and water are separated in the cavity, the separated water flows towards the bottom end, and the dry steam flows through the outlet opening and returns to the steam path. The dry steam blowing out of the trailing edge reduces the size of secondary droplets, and thereby prevents erosion.

System for reducing the level of erosion affecting a component

A seal is provided for preventing axial leakage through a radial gap between a stationary structure and a rotating structure. The radial gap is defined by an inner radial surface opposing an outer radial surface across the radial gap. The seal includes at least one land disposed on one of the inner radial surface and outer radial surface. At least one first tooth and at least one second tooth project from the other of the radial surfaces. The second tooth is shorter than the first tooth. At least one of the first tooth and second tooth, is configured to extend at an angle upstream. This angle is defined between a radial surface from which the first or second tooth projects and an upstream surface of the same tooth. The angle is less than or equal to about 80 degrees.

Turbine engine seals

A turbomachine includes a housing, and a plurality of turbomachine nozzles. At least one of the plurality of turbomachine nozzles includes a body having a first surface and an opposing second surface that extend between a first end and a second end. At least one of the first and second surfaces includes a profile having an angle of between about 3&#xb0; and about 8&#xb0; between a first line passing through the first end and a first position located between about 28% and about 38% from the first end and a second line passing through the first position and a second position located between about 53% and about 63% from the first end, and an angle of between about 10&#xb0; and about 20&#xb0; between the second line and a third line passing through the second position and a third position located between about 74% and about 84% from the first end.

Turbomachine nozzle

A turbine bucket including a bucket airfoil having an airfoil shape is provided. The airfoil shape has a nominal profile according to the tables set forth in the specification. The X and Y coordinate are smoothly joined by an arc of radius R defining airfoil profile sections at each distance Z. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape. The airfoil profile results in improved efficiency and airfoil loading capability.

High efficiency last stage bucket for steam turbine

A turbine bucket including a bucket airfoil having an airfoil shape is provided. The airfoil shape has a nominal profile according to the tables set forth in the specification. The X and Y coordinate are smoothly joined by an arc of radius R defining airfoil profile sections at each distance Z. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape.

Bucket for the last stage of a steam turbine

A rotating blade for a steam turbine includes a root section and an airfoil section contiguous with the root section. The airfoil section is shaped to optimize aerodynamic performance while providing optimized flow distribution and minimal centrifugal and bending stresses. The blade also includes a tip section continuous with the airfoil section, and a cover formed as part of the tip section. The cover defines a radial seal that serves to minimize tip losses. The rotating blade is capable of running at operating speeds between 5626 and 11250 rotations per minute.

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Clifton Park, NY, United States of America

Jonathon Edward Slepski