General Electric Company

Ge Avio S.r.l.

Aspi Rustom Wadia

Ching-Pang Lee

David Glenn Cherry

Peter Nicholas Szucs

Je-Chin Han

Andrew Breeze-Stringfellow

Steven Robert Brassfield

Paul Hadley Vitt

Seyed Gholamali Saddoughi

Anthony Louis DiPietro, Jr

Jeffrey Donald Clements

Jan Christopher Schilling

Peter John Wood

Clark Leonard Applegate

David Paul Lurie

Sherif Alykadry Abdelfattah

Michael Julian Castillo

Kirk Douglas Gallier

Chander Prakash

Eric Joseph Schroeder

William Joseph Solomon

Francesco Bertini

Scott Michael Carson

Rolf R Hetico

Robert Bruce Dickman

Joseph Capozzi

Raymond Gust Holm

Hsin-Yi Yen

Timothy John Swenson

David William Crall

Ian Francis Prentice

Tingfan Pang

Daniel Edward Mollmann

Brian Keith

Kevin Richard Kirtley

Aaron Michael Dziech

Syed Arif Khalid

Frank Worthoff

Anurag Gupta

Matthew William Wiseman

John Jared Decker

Kenneth Edward Seitzer

John Christopher Brauer

Robert Carl Murray

Mark Joseph Mielke

Brian Alan Norton

Lyle D Dailey

Harjit Singh Hura

Kiyoung Chung

Max Robert Farson

Ravikanth Avancha

Ganesh Seshadri

Deepak Manohar Kamath

Daniel Waslo

Eric Andrew Falk

Mahendran Manoharan

Alan Glen Turner

David Scott Clark

Xiaoyue Liu

Padmakar M Niskode

Carl C Koch

Christopher Ryan Johnson

Andrea Arnone

Filippo Rubechini

Vidhu Shekhar Pandey

Gregory Scott McNulty

Jason Corey Slagle

Virginia Louise Wilson

David K Christensen

Eric Pierre Masse

Lyle Douglas Dailey

Tyler James Alexander

Pamela A Battle

Bruce A Hemmelgarn

Gregory Burr Heitland

Matteo Giovannini

Matteo Giovanni

Daniel Mollmann

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

A fan for a gas turbine engine is provided. The fan includes a rotor including at least one rotor stage having a rotatable disk defining a flowpath surface and an array of rotor airfoils extending outward from the flowpath surface; an array of splitter airfoils extending outward from the flowpath surface, wherein the splitter airfoils and the rotor airfoils are disposed in a sequential arrangement; and a shroud extending between the rotor airfoils and the splitter airfoils.

Shroud for splitter and rotor airfoils of a fan for a gas turbine engine

A turbomachinery apparatus includes: a turbine, including: a turbine component defining an 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 fences extending from the flowpath surface, in the spaces between the turbine airfoils, each fence having opposed concave and convex sides extending between a leading edge and a trailing edge, wherein the fences have a nonzero camber and a constant thickness, are axially located near the leading edges of adjacent turbine airfoils, and wherein at least one of a chord dimension of the fences and a span dimension of the fences is less than the corresponding dimension of the turbine airfoils.

Turbine incorporating endwall fences

An apparatus and method of managing negative incidence of an airfoil are provided. The apparatus includes a first row of stationary turbine main vanes and a second row of auxiliary vanes extending radially inwardly from a stationary casing of the turbine proximate the adjacent leading edge of the main vane. The apparatus also includes a flow channel defined between a pressure side of an auxiliary vane of the second row of auxiliary vanes and a suction side of an adjacent main vane of the row of stationary turbine main vanes.

Method and system for leading edge auxiliary turbine vanes

A turbine blade is described herein, the turbine blade including a blade root, a blade tip, and an airfoil extending between the blade root and the blade tip. The airfoil has opposite pressure and suction sides extending between a forward leading edge and an aft trailing edge of the airfoil, and a maximum thickness located between the leading edge and the trailing edge. The blade tip includes a winglet extending laterally outward from at least one of the pressure side and the suction side from a leading point between the leading edge and the maximum thickness aftward to a trailing point between the maximum thickness and the trailing edge.

Method and system for improving turbine blade performance

A rotary component for a gas turbine engine defining a central axis extending along an axial direction, a radial direction extending perpendicular to the axial direction, and a circumferential direction perpendicular to both the central axis and the radial direction. The rotary component 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 the radial direction and defining an annular gap between a tip of each of the plurality of rotor blades and the outer casing. The outer casing includes a plurality of features on an interior surface of the outer casing. A first feature of the feature(s) defines a first casing thickness, and a second feature positioned at least partially circumferentially or axially from the first feature defines a second casing thickness different than the first casing thickness.

Engine casing treatment for reducing circumferentially variable distortion

An apparatus and method of managing negative incidence of an airfoil are provided. The apparatus includes a row of vane pairs including a first row of main vanes extending radially inwardly from a stationary casing member and spaced circumferentially about a first axial location of the stationary casing member. The apparatus also includes a second row of auxiliary vanes extending radially inwardly from the stationary casing member and spaced circumferentially about a second axial location of the stationary casing member. The apparatus also includes a flow channel defined between a pressure side of each auxiliary vane and a suction side of an adjacent main vane proximate a leading edge of the adjacent main vane.

Method and system for leading edge auxiliary vanes

A turbofan engine includes a compressor rotor, a plurality of main blades circumferentially mounted on the compressor rotor, and a plurality of spinner blades circumferentially mounted on the compressor rotor. Each of the spinner blades is located forward of a leading edge of a corresponding one of the main blades. Each of the spinner blades is circumferentially offset to the corresponding one of the main blades.

Turbofan engine's fan blade and setting method thereof

An apparatus and method of managing negative incidence in a compressor is provided. The apparatus includes a first row of stationary main vanes, and a second row of stationary auxiliary vanes extending radially inwardly from a stationary casing of the compressor proximate the leading edges of the main vanes. A flow channel is defined between a pressure side of an auxiliary vane of the second row of auxiliary vanes and a suction side of an adjacent main vane of the row of main vanes.

Method and system for compressor vane leading edge auxiliary vanes

A turbine blade includes an airfoil and integral platform at the root thereof. The platform is contoured in elevation from a ridge to a trough, and is curved axially to complement the next adjacent curved platform.

Curved platform turbine blade

An instability mitigation system is disclosed, comprising a rotor having a row of blades arranged around a centerline axis, and a mitigation system comprising at least one plasma actuator mounted on a blade that facilitates the improvement of the stability of the rotor, and a control system for controlling the operation of the mitigation system. An instability mitigation system further comprising a detection system for detecting an onset of an instability in a rotor and a control system for controlling the detection system and the mitigation system are disclosed.

Instability mitigation system using rotor plasma actuators

A method of operating a compressor having a row of blades for preventing a compressor stall is disclosed, the method comprising the steps of mounting a plasma generator in a casing or a shroud radially outwardly and apart from the blade tips wherein the plasma generator comprises a radially inner electrode and a radially outer electrode separated by a dielectric material; and supplying an AC potential to the radially inner electrode and the radially outer electrode.

Method of operating a compressor

An instability mitigation system is disclosed, comprising a detection system for detecting an onset of an instability in a rotor during the operation of the rotor, a mitigation system that facilitates the improvement of the stability of the rotor when the onset of instability is detected by the detection system, a control system for controlling the detection system and the mitigation system.

Instability mitigation system

An instability mitigation system is disclosed, comprising a stator stage located axially proximate to a rotor, the stator stage having a row of a plurality of stator vanes arranged around a centerline axis, and a mitigation system comprising at least one plasma actuator mounted on the stator vane that facilitates the improvement of the stability of the rotor, and a control system for controlling the operation of the mitigation system. An instability mitigation system further comprising a detection system for detecting an onset of an instability in a rotor and a control system for controlling the detection system and the mitigation system are disclosed.

Instability mitigation system using stator plasma actuators

Growing community of inventors

Loveland, OH, United States of America

Aspi Rustom Wadia