General Electric Company

Ge Vernova Technology Gmbh

Prakash Bavanjibhai Dalsania

Joshy John

Antanu Sadhu

Kamlesh Mundra

Michael James Dutka

Marc Edward Blohm

Nestor Hernandez Sanchez

Shashwat Swami Jaiswal

Jeremy Peter Latimer

Paul Griffin DeIvernois

Jonathon Edward Slepski

Srinivas Rao Pakkala

Siddaraja Mallikarjuna Devangada

Sunil Rajagopal

Sudhakar Neeli

Aaron David Williamson

Vasantharuban S

Steven Lynn Huskins

Timothy Edward DeJoris

Nandakumar A R

Narasimha K V Rao

Nancy Chaudhary

Satish Kumar

Bala Muralidhar Singh B

Phillip Matthew Malloy

Prabaharan K

Srinivas Pakkala

Exhaust frequency mitigation apparatus, exhaust diffusers, and turbomachines are provided. An exhaust frequency mitigation apparatus includes a main body extending along an axial centerline from a base to a tip. the base defines a first diameter and the tip defining a second diameter. the main body converges from the first diameter to the second diameter with respect to the axial centerline. The base is configured to extend from an inner shell of a turbomachine exhaust diffuser. The exhaust frequency mitigation apparatus further includes at least one rib extending from a root coupled to the main body to a free end.

Exhaust frequency mitigation apparatus

A stator vane includes an airfoil having an airfoil shape. The airfoil shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in one of Table I, Table II, Table III, Table IV, Table V, Table VI, Table VII, or Table VIII. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values are joined smoothly with one another to form a complete airfoil shape.

Compressor stator vane airfoils

An exhaust system for use with a steam turbine is provided. An exhaust hood includes an input and an output, the input receiving fluid from the steam turbine. The exhaust hood includes a first side wall that extends between the input and the output. The first side wall includes an aperture. An ejector is coupled to the exhaust hood. The ejector includes inlets and an outlet. At least one of the inlets receives fluid from the exhaust hood via the aperture.

Exhaust system for use with a turbine and method of assembling same

An asymmetric butterfly plate for a steam turbine exhaust hood includes a non-symmetrical curvilinear profile having a first section that extends to a second section through a vertex. The first section has a first curvilinear profile and the second section has a second curvilinear profile that is distinct from the first curvilinear profile.

Asymmetric butterfly plate for steam turbine exhaust hood

A steam turbine exhaust hood includes an exhaust hood section, and a butterfly plate arranged in the exhaust hood section. The butterfly plate includes a complex curvilinear cross-sectional profile having a first section that extends between a first end portion and a middle portion, and a second section that extends between the middle portion and a second end portion. One of the first and second sections is formed from at least two curvilinear segments including at least one curvilinear segment having a positive curvature and at least one curvilinear segment having a negative curvature.

Butterfly plate for a steam turbine exhaust hood

Various embodiments of the invention include a system including: at least one computing device operably connected with a steam turbomachine and an extraction conduit fluidly connected with the steam turbomachine and a steam seal header fluidly coupled with the steam turbomachine, the at least one computing device configured to modify an output of the steam turbomachine by performing actions including: determining a pressure within the steam turbomachine; comparing the pressure within the steam turbomachine with a pressure threshold range; and instructing the extraction conduit to extract steam seal header steam from the steam seal header and provide the extracted steam seal header steam to the steam turbomachine in response to determining the pressure within the steam turbomachine deviates from the pressure threshold range.

Turbomachine system with direct header steam injection, related control system and program product

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 method for assembling an exhaust hood for a turbine is provided. The method includes providing a bearing cone that substantially circumscribes a rotor of the turbine; and positioning a guide radially outward from the bearing cone. The guide and the bearing cone are configured to channel fluid from the turbine. The method also includes extending a guide cap from the guide. The guide cap is oriented to facilitate preventing the generation of fluid vortexes within the exhaust hood.

Exhaust hood for a turbine and methods of assembling the same

Tip shrouds on last stage buckets for condensing steam turbines may create significant blockage and form a vortex at the wall of the steam guide of the diffuser, causing the steam flow to separate from the wall of the steam guide. Vortex formation reduces the effective flow area for the remaining fluid to diffuse, causing poor recovery. An inward radial depression is provided of a predetermined depth and distance along an outer steam guide, which redirects the tip leakage flows slightly downward, reducing a shroud blockage effect. This deflection assists the main flow in rejoining the steam guide, thereby making the diffuser more effective.

Shroud vortex remover

A steam turbine includes a diffuser that has a bearing cone and an inner plate of a steam guide that define a passage through which steam flows. An outer plate is disposed with respect to the inner plate such that an opening is located between the inner and outer plates. At least one hole is located in the inner plate. A water tube is disposed in the opening, the water tube having water flowing therethrough which condenses at least a portion of a flow of steam flowing in the passage thereby creating at least a partial vacuum within the opening. The vacuum creates a suction effect through the at least one hole in the inner plate that can cause at least a portion of the flow of steam in the passage to attach itself to an inner surface of the inner plate.

Hollow steam guide diffuser having increased pressure recovery

An exhaust hood for an axial steam turbine that includes a radial channel, downstream from the normal flow pattern. The radial channel guides the exhaust steam flow in upper half of the hood in the flow momentum direction. Due to this pattern of flow direction, vortex generation in upper exhaust hood is reduced and increased flow diffusion results. The geometric arrangement can eliminate the outer casing of the exhaust hood over the axial length of the turbine inner casing, allowing the turbine inner casing to be supported directly by a foundation for the steam turbine.

Growing community of inventors

Bengaluru, India

Prakash Bavanjibhai Dalsania