General Electric Company

Craig Miller Kuhne

Joseph Steven Bubnick

Ching-Pang Lee

Brandon Wayne Miller

Darek Tomasz Zatorski

Christopher Charles Glynn

Andrew Breeze-Stringfellow

Randy M Vondrell

Kurt David Murrow

Donald Albert Bradley

Chander Prakash

David Glenn Cherry

Donald Scott Yeager

Nicholas Rowe Dinsmore

Robert John Beacock

Scott Andrew Burton

Joseph Machnaim

Samuel Jacob Martin

Alisha Vachhani

Alisha Vachhani Kalb

Joshua Luke Wiedemann

Darek T Zatorski

Systems and methods for forecasting aircraft engine operational data are provided. The forecasted data can be used for use with predictive analytics, for example. In one aspect, a method is provided. The method includes receiving engine data associated with an engine. The engine data includes data points for various operational parameters. The method further includes determining forecasted data points for the operational parameters. The forecasted data points for a given one of the operational parameters are determined by applying one or more regression techniques to the data points associated with the given one of the operational parameters. The forecasted data points can be input into various types of models, such as a cumulative damage model. For instance, using the forecasted data points, a cumulative damage model can generate a plurality of forecasts and can output a cumulative probability distribution.

System and method of forecasting aircraft engine operational data for predictive analytics

A gas turbine engine comprises a fan, a compressor, a turbine having first stage blades and second stage blades, the first stage blades rotates in a first direction and the second stage blades rotates in a second direction opposite the first direction. The first stage blades are directly adjacent to one another, a drive in operable input connection with the fan and in operable output connection with the first stage blades and the second stage blades, the first stage blades and the second stage blades driving the fan through the drive.

Engine architecture with reverse rotation integral drive and vaneless turbine

A turbine blade includes an airfoil and integral platform. The platform is biformally contoured in elevation to include bilaterally disposed elevated ridges and depressed troughs on opposite sides of the airfoil.

Biformal platform turbine blade

A turbine blade includes an airfoil having first and second tip ribs extending along the opposite pressure and suction sides thereof. A tip baffle bifurcates the airfoil tip into two pockets, with a first pocket being laterally open at its aft end to recover leakage flow, and a second pocket being laterally closed.

Recovery tip turbine blade

A transonic turbine blade. Expansion waves are generated by a lifting surface on the blade. The expansion waves extend downstream, through a shock generated at the trailing edge of an adjacent blade. The invention increases the strength of the shock, thereby attenuating the expansion waves passing through the shock. One stratagem for increasing the shock is to reduce the aerodynamic load of the trailing edge generating the shock.

Reduced shock transonic airfoil

A stator vane that may be used in an engine assembly is provided. The stator vane includes an airfoil that has a first sidewall and a second sidewall, which connects to the first sidewall at a leading edge and at a trailing edge. The airfoil also includes a root portion and a tip portion. The first and second sidewalls both extend from the root portion to the tip portion. The airfoil root portion is formed with a negative lean, and the airfoil tip portion is formed with a positive lean.

Gas turbine engines including lean stator vanes and methods of assembling the same

Growing community of inventors

Cincinnati, OH, United States of America

Craig Miller Kuhne