General Electric Company

Ge Precision Healthcare LLC

Ge Avio S.r.l.

Ravikanth Avancha

Ganesh Seshadri

Jiang Hsieh

Peter Michael Edic

Saad Ahmed Sirohey

Darin Robert Okerlund

Robert F Senzig

Jerome F Knoplioch

Sandeep Dutta

Paul Edgar Licato

Giridhar Jothiprasad

Rahul Bhotika

Steven James Gray

John Irvin Jackson

Bijan Dorri

Mahendran Manoharan

Toshihiro Rifu

Basel Taha

Jeffrey Donald Clements

Aspi Rustom Wadia

Paul Hadley Vitt

Atanu Saha

Pranav R Kamat

Sesha Subramanian

Francesco Bertini

Lyle D Dailey

John Joseph

Chaitanya Venkata Rama Krishna Ongole

Mohsin Hasan Khan

Sarasija Sudharsan

Dhananjaya Gottapu

A turbomachinery apparatus () includes: a turbine (), including: a turbine component () defining at least one arcuate flowpath surface (); an array of axial-flow turbine airfoils () extending from the flowpath surface, the turbine airfoils defining spaces therebetween; and a plurality of splitter airfoils () extending from the at least one flowpath surface, in the spaces between the turbine airfoils, each splitter airfoil having opposed pressure and suction sides extending between a leading edge and a trailing edge, wherein the splitter airfoils have a thickness ratio which is less than a thickness ratio of the turbine airfoils.

Turbine incorporating splitters

In one aspect, the present disclosure is directed a gas turbine engine including a compressor, a combustor, and a turbine in a serial flow arrangement. The compressor includes a casing having an inner wall and an outer wall. The inner wall defines a passageway for airflow through the compressor. The casing defines a bleed cavity between the inner wall and the outer wall. The inner wall has an opening. The casing defining a channel between the opening and the bleed cavity to direct airflow into the bleed cavity. The channel is defined by a first wall and a second wall of the casing. The second wall being downstream of the first wall. A surface of the first wall has a pattern to reduce flow separation in the channel.

Compressor bleed air channels having a pattern of vortex generators

A system and method for estimating vascular flow using CT imaging include a computer readable storage medium having stored thereon a computer program comprising instructions, which, when executed by a computer, cause the computer to acquire a first set of data comprising anatomical information of an imaging subject, the anatomical information comprises information of at least one vessel. The instructions further cause the computer to process the anatomical information to generate an image volume comprising the at least one vessel, generate hemodynamic information based on the image volume, and acquire a second set of data of the imaging subject. The computer is also caused to generate an image comprising the hemodynamic information in combination with a visualization based on the second set of data.

System and method for estimating vascular flow using CT imaging

An apparatus and method for diffusing an airflow in a turbine engine can include a turbine center frame positioned between a high pressure turbine and a low pressure turbine of a turbine section of the engine. The turbine center frame can include two or more diffusion sections for diffusing the airflow. A stabilization section can be provided between the two or more diffusion sections to stabilize the airflow.

Turbine center frame

A turbine rear frame for a gas turbine engine comprises a plurality of struts disposed between an outer ring and an inner ring. The struts can be mounted adjacent to one or more mount surfaces defined within the outer ring. The mount surface can comprise a recess in the outer ring having a maximum radial distance upstream of engine mounts inserted therein. The struts can further comprise a pitch angle offset from a centerline of the mount surface and a tangentially curved trailing edge at a tip to improve aerodynamic performance of the turbine rear frame.

Turbine rear frame for a turbine engine

A turbine engine with a tip shroud and method for shaping the tip shroud where at least one pair of airfoils including a first and second airfoil each having an outer wall bounding an interior. Each airfoil extending between a pressure side and a suction side to define a circumferential direction and extending between a leading edge and a trailing edge to define an axial direction. Each airfoil extending between a root and a tip to define a radial direction. The first and second airfoils are circumferentially spaced to define an inlet between the leading edges and an outlet between the trailing edges where each airfoil is coupled to an inner platform at the root. A tip shroud circumscribing the airfoil operably coupled to the tip extending in the axial direction between axially spaced first and second planes where the tip shroud includes at least one scalloped portion.

Tip shroud for a turbine engine

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Bengaluru, India

Ravikanth Avancha