Ronald G Maruscik

6871105, Mar 22, 2005

Sep 26, 2002

10/255887

James Kenneth Aragones - Clifton Park NY, US
Carol Lynn Kiaer - Argyle NY, US
Ronald George Maruscik - Lebanon OH, US
Avinash Vinayak Taware - Niskayuna NY, US
Robert Marcel Mattheyses - Schenectady NY, US

General Electric Company - Niskayuna NY

G05B013/02

700 28, 700 44, 700 45, 700 47, 701 96, 701300, 701301, 342455, 244 31, 244 321, 244 325, 244 75 R, 244 76 R

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.

7403877, Jul 22, 2008

Aug 17, 2001

09/682314

James Kenneth Aragones - Clifton Park NY, US
Jeffrey William Stein - Albuquerque NM, US
Jeremiah Francis Donoghue - Ballston Lake NY, US
Ronald George Maruscik - Lebanon OH, US

General Electric Company - Niskayuna NY

G06F 7/60
G06F 17/10
G06F 19/00
G06F 7/70

703 2, 703 8, 701 14

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.

7431557, Oct 7, 2008

May 25, 2006

11/441258

William Lee Herron - Cincinnati OH, US
Matthew William Wiseman - Fairfield OH, US
Jon Michael Vishnauski - Loveland OH, US
Brian Edward Krupp - Liberty Township OH, US
Ronald George Maruscik - Lebanon OH, US

General Electric Company - Schenectady NY

G06F 19/00

415 1, 415127

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.

20020173897, Nov 21, 2002

May 18, 2001

09/861337

Kevin Leamy - Loveland OH, US
Ronald Maruscik - Lebanon OH, US

G06F019/00

701/100000

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.