General Electric Company

Ge Infrastructure Technology, LLC

Citrix Systems, Inc.

Exxonmobil Upstream Research Company

General Electric Technology Gmbh

Moorthi Subramaniyan

Gunnar Leif Dan Siden

Shashwat Swami Jaiswal

Nisha Singh

Adam John Fredmonski

Michael James Healy

Joshy John

Kevin Michael Barnett

Karthick Srivatsan

Praveen Raja Dhanabalan

Steven Sebastian Burdgick

Yu Wang

Richard Alan Huntington

Rohit Chouhan

Chaitra Maraliga Ramaiah

Matthew John McKeever

Pradeep Patel

Sabarinath Devarajan

Sandeep Manohar Nirikhi

Prabakaran Modachur Krishnan

Wilfried Rick

Manjunath Bangalore Chengappa

Sagar Kamble

Uday Krishna Pappala

Anand Medikeri

Rajnesh Raturi

Kumaran Vale Mudaliar

Kevin Joseph Barb

Paul Griffin DeIvernois

Debabrata Mukhopadhyay

Sameer Dinkar Vartak

Christian Michael Hansen

Richa Awasthi

Prashant Prabhakar Sankolli

Todd Franklin Denman

John David Dyer

Lakshmanan Valliappan

Kunal Upendra Sakekar

Francesco Soranna

Thangaraj Subbareddyar

Subodh Diwakar Deodhar

Srinivasarao Pakkala

Sachin Kumar Rai

Umesh Garg

Damir Novak

Sreenivasa Rao Gubba

Mariadas Anton Charles Anandarajah

Arun Kumar Sridharan

Thomas Peter Sommer

Shruti Kulkarni

Dejan Mikasinovic

Karan Ghule

Vignesh Radhakrishnan

Josip Galic

Jeyamani Doss

Srikeerthi Annaluri

Navaneeth Kishan T R

Ankur Maheshwari

Dragisa Ristic

Kamesh Lakshmi Narayanan

Jaya Rao Venkata Satya Vuppala

Michael Loetzerich

Marco Micheli

Gurulakshmi Polisetty

Aditya Rajeshbhai Shah

Vsevolod Yuriyevich Ostrovskiy

Rozila Nausheen

Srikanth Deshpande

Srinivasrao Pakkala

A system includes a turbine exhaust section having an exhaust flow path, an inner exhaust wall radially disposed along the exhaust flow path, and an outer exhaust wall radially disposed along the exhaust flow path and radially outward from the inner exhaust wall. The turbine exhaust section includes an auxiliary strut extending from the inner exhaust wall to the outer exhaust wall. The auxiliary strut is segmented and includes an inner portion, a central portion disposed radially outward from the inner portion, and an outer portion disposed radially outward from the central portion. The inner portion, the outer portion, or both are configured to rotate to an angled position. The auxiliary strut is circumferentially disposed between adjacent struts of the turbine exhaust section.

Mitigation of rotating stall in turbine exhaust section using segmented auxiliary struts

A system includes a turbine exhaust section downstream of a turbine. The turbine exhaust section includes an exhaust flow path. The turbine exhaust section also includes an inner wall radially disposed along the exhaust flow path. The turbine exhaust section also includes an outer wall disposed radially outward of the inner wall and along the exhaust flow path. The system also includes a fluid injection system configured to inject a fluid into a chamber radially disposed between the inner wall and the outer wall via a plurality of inner ports disposed in the inner wall. The plurality of inner ports is disposed downstream of a downstream edge of a last stage blade of the turbine.

Fluid injection system and method for mitigating rotating stall in turbine engine

An extraction impeller for an axial compressor includes first vanes having an elongated S-shape arranged on the surface of an impeller body. The first vanes extend radially from an outer flow inlet edge of the body to a flow outlet hub centered on the surface at the rotation axis. A radially inner end of each of the first vanes connects at the flow outlet hub in a direction perpendicular to a rotation axis. Second vane(s) are arranged between adjacent first vanes, and third vanes are arranged between second vanes and between first vanes and second vanes. Second vanes are radially longer than third vanes. The impeller extracts air from the axial compressor and forms an axial flow with reduced vortex whistle. When used in an axial compressor of a gas turbine system, the impeller reduces flow unsteadiness.

Extraction impeller for axial compressor

A system includes a turbine having an exhaust flow path, an inner turbine wall radially disposed along the exhaust flow path, an outer turbine wall disposed along the exhaust flow path and radially outward from the inner turbine wall, and an outer flow control vane configured to selectively extend radially inward from the outer turbine wall. A radial extent of the outer flow control vane is less than a radial distance between the inner turbine wall and the outer turbine wall. The outer flow control vane is disposed downstream of a last stage vane of the turbine and upstream of a last stage blade of the turbine. The turbine also includes an actuation assembly configured to actuate the outer flow control vane to cause the outer flow control vane to extend radially inward. The system also includes a controller configured to instruct the actuation assembly to actuate the outer flow control vane.

Mitigation of rotating stall in turbine section using outer flow control vanes

A system includes a turbine exhaust section. The turbine exhaust section includes an exhaust flow path. The turbine exhaust section also includes an inner exhaust wall radially disposed along the exhaust flow path and an outer exhaust wall disposed along the exhaust flow path and radially outward from the inner exhaust wall. The turbine exhaust section includes an inner flow control vane configured to selectively extend radially outward from the inner exhaust wall. An inner radial extent of the inner flow control vane is less than a radial distance between the inner exhaust wall and the outer exhaust wall. The inner flow control vane is disposed downstream of a last stage blade of a turbine and upstream of an exhaust diffuser strut of the turbine exhaust section.

Mitigation of rotating stall in turbine exhaust section using inner flow control vanes

A system includes a turbine exhaust section having an exhaust flow path, an inner exhaust wall radially disposed along the exhaust flow path, an outer exhaust wall disposed radially outward of the inner exhaust wall and along the exhaust flow path, and a flow control vane extending between a first end and a second end. The first and second ends are circumferentially offset from one another. The flow control vane is configured to move between a retracted position along the outer exhaust wall and an extended position extending from the outer exhaust wall toward the inner exhaust wall. The second end is disposed radially inward from the first end while the flow control vane is disposed in the extended position.

Mitigation of rotating stall in turbine exhaust section using flow control vanes disposed therein

A system and method of igniting a coal air-fuel mixture, including a burner having a burner tube operable to carry a flowing mixture of fuel and air to a furnace for combustion therein and a first flow directing device disposed within the tube, operable to direct a first portion of the flowing fuel and air mixture to a location in the burner tube. The system also includes a laser igniter within the burner tube, the laser igniter including a laser tube having a first end with a laser light input and a second end with a light output, and a laser light source operably coupled to the laser light input. The laser light source, including a laser. The laser ignitor directing photons from the light output at the location in the burner tube to ignite at least a part of the first portion of the fuel.

System and method for laser ignition of fuel in a coal-fired burner

Described embodiments provide systems and methods of forming overlay tunnels for delivery of data between networked devices. A first intermediary device may transmit, responsive to a connection request from a client, a request having a source IP address corresponding to a first virtual IP address of the first device and a first payload including first security hash information to be processed by a second intermediary device. The first device may receive, from the second intermediary device, a response. The response may have a source IP address corresponding to the IP address of the server and a second payload including a virtual IP address of the second device, responsive to second security hash information corresponding to the first security hash information. The first device may establish an overlay tunnel using the first virtual IP address and the second virtual IP address for communicating data between the client and the server.

Intelligent and dynamic overlay tunnel formation via automatic discovery of citrivity/SDWAN peer in the datapath in a pure plug and play environment with zero networking configuration

A rotor blade 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, Table VIII, or Table IX. 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 rotor blade airfoils

A stator vane includes an airfoil having an airfoil shape. The airfoil shape having 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, Table VIII, Table IX, Table X, Table XI, or Table XII. 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

A turbine blade for a rotary machine includes an airfoil that extends from a root to a tip along a radial span. The airfoil further includes a first sidewall and a second sidewall that are coupled together at a leading edge of the airfoil and that extend aftward to a trailing edge of the airfoil. One of the first sidewall or the second sidewall includes a tip region having an increased stagger angle that produces a non-linear, over-hanging trailing edge.

Turbine airfoil profile

Intelligent and dynamic overlay tunnel formation via automatic discovery of citrivity/SDWAN peer in the datapath in a pure plug and play environment with zero networking

Stator vanes including curved trailing edges are disclosed. The stator vanes may include a body including a central section, a tip section positioned radially above the central section, and a root section positioned radially below the central section. The body of the stator vanes may also include a leading edge extending radially adjacent the root section, central section, and tip section, respectively, and a trailing edge positioned opposite and aft to the leading edge. The trailing edge may include a concave contour including a first portion radially aligned with the central section of the body. The first portion may be axially offset and forward of a reference line that may be perpendicular to an axial direction and intersects the concave contour at the tip section and the root section. A concavity of the first portion of the concave contour may be formed radially aft of the central section.

Stator vanes including curved trailing edges

A system for a turbomachine includes a rotor blade configured to rotate along a circumferential direction within a casing of the turbomachine and a shroud positioned outward of the rotor blade along a radial direction. The rotor blade includes a root, a tip spaced radially outward from the root, a pressure side tip rail that extends around the tip of the rotor blade along a pressure side wall, and a suction side tip rail that extends around the tip of the rotor blade along a suction side wall. The shroud includes a radially inner surface facing the pressure side tip rail and the suction side tip rail of the rotor blade and spaced from the pressure side tip rail and the suction side tip rail of the rotor blade by a clearance gap. The shroud also includes a plurality of grooves extending continuously along the circumferential direction.

Systems including rotor blade tips and circumferentially grooved shrouds

Described embodiments establish at least one secure connection for a session. An intermediary device may intercept a domain name service (DNS) request from a client. The device may determine, according to the intercepted DNS request and configuration data of the device, that the client is preparing to establish a session with a server. The device may send a client hello message of the device to the server for establishing a first secure connection between the device and the server for the session, prior to the client sending a client hello message of the client for establishing a second secure connection between the client and the device for the session. The second secure connection may be established between the client and the device using a specified value for a session identifier received from the server in response to the client hello message of the device.

Method for SSL optimization for an SSL proxy

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Bengaluru, India

Moorthi Subramaniyan