General Electric Company

Ge Avio S.r.l.

General Electric Deutschland Holding Gmbh

Ge Avivo S.r.l.

Lyle D Dailey

Francesco Bertini

Jeffrey Donald Clements

Paul Hadley Vitt

Peter John Wood

Eric Andrew Falk

Matteo Renato Usseglio

Jonathan Ong

Jaikumar Loganathan

Ernesto Sozio

Saurya Ranjan Ray

Simone Rosa Taddei

Aspi Rustom Wadia

Vishnu Vardhan Venkata Tatiparthi

Ravikanth Avancha

Ganesh Seshadri

Andreas Peters

Andrea Arnone

Filippo Rubechini

John Joseph

Mohsin Hasan Khan

Sarasija Sudharsan

Matteo Giovannini

A turbine airfoil comprises an airfoil defining a leading edge, a trailing edge, a root portion, a tip portion, a chord line defining a chord length of the airfoil, a suction side surface extending in a spanwise direction from the root portion to the tip portion and in a flow-wise direction between the leading edge and the trailing edge, and a throat line extending spanwise along the suction side surface from the root portion to the tip portion. The turbine airfoil further includes a plurality of micro-riblet patches defined along the suction side surface aft of the throat line where each micro-riblet patch of the plurality of micro-riblet patches extends in the flow-wise direction between the throat line and the trailing edge.

Suction side micro-riblet patches for a turbine airfoil

An airfoil assembly has a platform and an airfoil. The platform has an upstream edge, a downstream edge, and a surface extending between the upstream edge and the downstream edge. At least a portion of the surface extends circumferentially along a surface baseline defined by a constant radial distance from the rotational axis. The airfoil has an outer wall. The outer wall extends between a root and a tip, and between a leading edge and a trialing edge. The airfoil assembly includes a fence provided along the outer wall.

Turbine engine with reduced cross flow airfoils

A turbine section and an exhaust section for a gas turbine engine includes a low pressure (LP) turbine having first stage LP turbine blades that rotate in a first direction at a first speed, and final stage LP turbine blades downstream of the first stage LP turbine blades that rotate in a second direction opposite the first direction at a second speed. The second speed is lower than the first speed.

Counter-rotating turbine

An airfoil assembly for a turbine engine comprising an outer band, an inner band radially spaced inwardly from the outer band to define an annular region, and multiple airfoils circumferentially spaced within the annular region. Each corresponding airfoil of the multiple airfoils can project from a surface at a root and can further include an outer wall defining a pressure side and a suction side. A projection can extend upwardly from the surface on the pressure side and a valley can extend into the surface on the suction side to define a contour in the surface.

A turbine engine with at least a compressor section, combustor section, turbine section and a set of airfoils. The airfoils include geometric characteristics to create a high contraction ratio (CR), a low blade turning (BT) at a radially inward location the airfoil, a low solidity, or a low aspect ratio (AR).

Turbine engine with airfoil having high acceleration and low blade turning

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 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

A compression stage having a plurality of stator vanes and rotor blades coaxial with a longitudinal centerline axis, each stator vane having an exit swirl angle distribution such that the exit swirl angle has a maximum value at an intermediate radius location and each rotor blade having a blade leading edge adapted to receive the flow from the stator vanes with the exit swirl angle distribution profile.

Advanced booster system

A stator vane includes leading and trailing edges extending longitudinally between a root and a tip, the trailing edge having an exit swirl angle distribution such that the exit swirl angle has a maximum value at an intermediate radius location.

Advanced booster stator vane

A rotor airfoil having a leading edge extending from a root to a tip, an inner span region and an outer span region the leading edge having a sweep angle profile such that the sweep angle increases from the root a first height location at a first rate of change of sweep angle that is substantially constant and thereafter increases at a second rate of change of sweep angle that is substantially constant.

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Maineville, OH, United States of America

Lyle D Dailey