General Electric Company

Ge Precision Healthcare LLC

Ge Infrastructure Technology, LLC

Giridhar Jothiprasad

Thomas Malkus

Trevor Howard Wood

Kishore Ramakrishnan

Ramakrishna Venkata Mallina

Rudolf Konrad Selmeier

Jiang Hsieh

Ravindra Shankar Ganiger

Peter Michael Edic

Saad Ahmed Sirohey

Hiranya Kumar Nath

Byron Andrew Pritchard, Jr

Darin Robert Okerlund

Robert F Senzig

Jerome F Knoplioch

Sandeep Dutta

Corey Bourassa

Paul Edgar Licato

Jixian Yao

Rahul Bhotika

Steven James Gray

William Joseph Solomon

John David Stampfli

John Irvin Jackson

Bijan Dorri

Ambika Shivamurthy

Nageswar Rao Ganji

Ravikanth Avancha

Davide Giacché

Ajay Keshava Rao

Toshihiro Rifu

Nicholas Joseph Kray

Daniel Alan Niergarth

Mehmet Muhittin Dede

Changjie Sun

Vittorio Michelassi

Rodrigo Rodriguez Erdmenger

Erich Alois Krammer

Adam Joseph Wangler

Lana Maria Osusky

Li Zheng

Satoshi Atsuchi

David Vickery Parker

Gregory Alexander Natsui

Joel Meador Hall

Shourya Prakash Otta

Ivan Malcevic

Grover Andrew Bennett

Michael Macrorie

Mitchell Jay Headley

Jeffrey D Carnes

Swati Saxena

Sungho Yoon

Aaron J King

Christopher E LaMaster

Ya-tien Chiu

Dhinesh Thanganadar

Jason P Mortzheim

Todd Andrew Jankowski

An integration system for extracting power, the integration system including a flue flow source configured to supply flue flow thermal energy to a heat exchanger and an auxiliary energy source (AES) configured to selectively supply auxiliary thermal energy to a supplemental heat exchanger. The integration system includes a controller configured to determine whether the AES is supplying auxiliary thermal energy to the supplemental heat exchanger; and if the AES is supplying auxiliary thermal energy to the supplemental heat exchanger, cause a turbine to extract power from both the flue flow and from the auxiliary thermal energy.

Systems and methods for integrating auxiliary energy and waste heat recovery from gas turbine engines

A rotary component for a gas turbine engine includes a plurality of rotor blades operably coupled to a rotating shaft extending along the central axis and an outer casing arranged exterior to the plurality of rotor blades in a radial direction of the gas turbine engine. The outer casing defines a gap between a blade tip of each of the plurality of rotor blades and the outer casing. The outer casing includes a plurality of features formed into an interior surface thereof. Each of the plurality of features includes one or more design parameters that are perturbed about a mean design parameter for stall performance so as to provide a circumferential variation in wake strengths associated with the plurality of rotor blades, thereby reducing operational noise of the gas turbine engine.

Circumferentially varying fan casing treatments for reducing fan noise effects

Methods, apparatus, systems, and articles of manufacture are disclosed for a variable bleed valve assembly. An example variable bleed valve assembly a variable bleed valve (VBV) door corresponding to a bleed port and a first unison ring, the VBV door coupled to the first unison ring, the first unison ring to move in a circumferential direction between a first position and a second position causing the VBV door to move between the first position and the second position.

Bleed valve assemblies

Compact bleed valve assemblies are disclosed. An example turbine engine comprises a rotor blade having an axial chord (C) measured at a tip of the rotor blade, and a variable bleed valve (VBV) including a VBV port defining a bleed flowpath and an exit angle (β) for bleed air exiting the VBV port, the VBV port including a forward entrance edge and an aft exit edge and a first length (LA) therebetween, and a VBV door corresponding to the VBV port, the VBV door to generate a bleed cavity having a bleed cavity area (BA) in the VBV port when the VBV is in a closed position, the VBV door to move between an open position and the closed position at a rotation angle (Δθ), the VBV door to extend a distance (LA) beyond the first length (LA), wherein and wherein

Compact bleed valve assemblies

Aero-acoustically damped bleed valves are disclosed. An example variable bleed valve apparatus comprises a variable bleed valve door to actuate the variable bleed valve apparatus, and a variable bleed valve port including an upstream edge and a downstream edge, the VBV port to define a secondary flowpath, the VBV door to cover the VBV port in a closed position, and a vortex device at the upstream edge of the variable bleed valve port, the vortex device including a vorticity generating feature along the upstream edge of the variable bleed valve port.

Aero-acoustically dampened bleed valve

A stator structure including a plurality of stator blades and redirection structures including a first portion and a second portion, the first portion disposed on a front edge surface of a stator hub and a second portion disposed on a facing of the stator hub is provided. The stator hub includes the facing and the front edge surface, the facing being disposed generally perpendicular to the casing, and the front edge surface is disposed generally perpendicular to the facing. During operation of a turbine engine a core air flow moves along the longitudinal axis and past the plurality of stator blades, and a leakage air flow moves in a direction different to the core air flow, the redirection structures are effective to redirect the leakage air flow to merge into the core air flow.

Core air leakage redirection structures for aircraft engines

A thermal management system for a gas turbine engine is provided. The gas turbine engine includes a turbomachine comprising a compressor section, a combustion section, a turbine section, and an exhaust section arranged in serial flow order and together defining at least in part a core air flowpath; and a thermal management system comprising a supercritical carbon dioxide line thermally coupled to, or integrated into, a portion of the compressor section.

Thermal management system for a gas turbine engine

Jet engine thermal transport bus pumps are disclosed. Disclosed herein is an aircraft comprising a gas turbine engine configured to burn fuel at a fuel flow rate to generate an engine power (P), the fuel characterized by a first specific heat capacity (c) and a net heat of combustion (NHC); and a thermal management system configured to transfer heat from a working fluid to the fuel, the working fluid characterized by a second specific heat capacity (c) and a first density (ρ), the thermal management system including a pump configured to generate a pump power (P) to pressurize the working fluid, and wherein 0.008≤POW/FFR≤12, FFR is between 0.05 pounds-mass per second and 16 pounds-mass per second, and ρand cis the density and specific heat capacity of water, respectively.

Jet engine thermal transport bus pumps

A turbomachine includes an annular casing and a fan disposed inside the annular casing and mounted for rotation about an axial centerline. The fan includes fan blades that extend radially outwardly toward the annular casing. The fan has an average chord fan width according to a first performance factor. The fan has a quantity of fan blades according to a second performance factor.

Turbomachine and method of assembly

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

A compressor is provided including a casing, a hub, a flow path, a plurality of blades, and an end-wall treatment formed in at least one of the casing and the hub, and facing a tip of each blade. The flow path is formed between the casing and the hub, and the plurality of blades is positioned in the flow path. The tip of each blade and the end-wall treatment are configured to move relative to each other. Such end-wall treatment includes a first recess portion extending along a first axis to maintain a fluid flow substantially straight through the first recess portion. The end-wall treatment further includes a plurality of second recess portions spaced apart from each other and extending from the first recess portion along a second axis different than the first axis to maintain the fluid flow substantially straight through the plurality of second recess portions.

Compressor end-wall treatment with multiple flow axes

A compressor assembly for a turbomachine includes a compressor wall including circumferentially spaced stator vanes defining at least one row of stator vanes. The at least one row of stator vanes defines at least one stator passage therein. Each stator vane includes a leading edge, an opposite trailing edge defining an axial chord distance, and a pressure side. The compressor assembly also includes, at least one bleed opening defined within the compressor wall and disposed adjacent the pressure side in the at least one stator passage within a range from approximately 20% the axial chord distance upstream of the leading edge to approximately 20% the axial chord distance downstream of the trailing edge. The compressor assembly further includes at least one bleed arm extending from the at least one bleed opening with at least a portion of compressor airflow extractable through the at least one bleed arm.

Compressor bleed systems in turbomachines and methods of extracting compressor airflow

Growing community of inventors

Clifton Park, NY, United States of America

Giridhar Jothiprasad