General Electric Company

Ronald George Maruscik

James Kenneth Aragones

Avinash Vinayak Taware

William Lee Herron

Matthew William Wiseman

Robert Marcel Mattheyses

Kevin Richard Leamy

Jeffrey William Stein

Jeremiah Francis Donoghue

Carol Lynn Kiaer

Jon Michael Vishnauski

Brian Edward Krupp

A method to compensate for blade tip clearance deterioration between rotating blade tips and a surrounding shroud in an aircraft gas turbine engine includes determining one or more variables based on at least one or more moving averages of one or more engine operating parameters respectively averaged over a fixed number of operational engine flight cycles and adjusting a flow rate of thermal control air to counter the blade tip clearance deterioration based on the one or more variables. The engine operating parameters may include running number of engine cycles, takeoff and cruise exhaust gas temperature margins, a cruise turbine efficiency, takeoff and cruise maximum turbine speeds, a cruise fuel flow. Some or all of the variables may be differences between the moving averages and corresponding baselines of the engine operating parameters respectively or the variables may all be moving averages. The flow rate may be adjusted incrementally.

Compensating for blade tip clearance deterioration in active clearance control

System, method and computer product for baseline modeling a product or process. A service database contains process data. A preprocessor processes the data into a predetermined format. A baseline modeling component builds a baseline model from the preprocessed data, wherein the baseline model relates process performance variables as a function of process operating conditions.

System, method and computer product for baseline modeling a product or process

A method for facilitating an optimization of a control space in n dimensions is provided. The control space includes a plurality of points, and the method includes removing at least one hyperplane of the control space, and perturbing the remaining points of the control space to lessen errors relative to the control space prior to the removal of at least one hyperplane.

Methods and apparatus for reducing hyperplanes in a control space

A method and system for monitoring engine performance in a gas turbine engine uses a plurality of sensors to sense data related to the operation and performance of the gas turbine engine. Selected data parameters from the sensed data are continuously sampled prior to completion of an engine start sequence. The selected data parameters are then evaluated to determine whether specific criteria have been met, and evaluation data are captured whenever the criteria are met. The evaluation data are used to normalize engine performance data to a particular thermal state of the engine. The normalized engine performance data are then trended by comparing it to a parametric baseline for the gas turbine engine.

System and method for monitoring thermal state to normalize engine trending data

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Lebanon, OH, United States of America

Ronald George Maruscik