United Technologies Corporation

Gregory E Chetta

John J Marra

Stephen R Jones

Donna R Dickerson

David W Leung

Duncan C Meyers

Jeffrey M Simpson

Andreas Sadil

Daniel E Kane

Charles A Ellis

Karl D Blume

George F Titterton, Iii

Wilho V Aho, Jr

Thomas E Holladay

Scott A Ladd

Kevin L Worley

Allan D Krul

Henry Huizinga

Terry H Strout

Thomas B Fortin

Rodney L Giersdorf

Sergio Rinella

Randall G McKinney

Alfred Peduzzi

Dennis L Mackey

Amy U Serwinowski

Charlie Quackenbush

Frank Shurick

Robert Rozelle

Jonathan Schmid

William D Neff

Susan A Rose

Keith C Belson

Joey C Hayes

John V Diaz

Joseph A Oblak

A method and system for designing an impingement film floatwall panel system for a combustion chamber for a gas turbine engine comprising the steps of creating an impingement film floatwall panel knowledge base of information. The knowledge base has a plurality of design rule signals with respect to a corresponding plurality of parameter signals of associated elements of impingement film floatwall panels for a combustion chamber, wherein the knowledge base comprises at least one data value signal for each one of the plurality of design rule signals. The steps also include entering a desired data value signal for a selected one of the plurality of parameter signals of an associated element of the impingement film floatwall panels and comparing the entered desired data value signal for the selected one of the plurality of parameters with the corresponding at least one data value signal in the knowledge base for the corresponding one of the plurality of design rule signals. If the result of the step of comparing is such that the entered desired data value signal for the selected one of the plurality of parameter signals is determined to have a first predetermined relationship with respect to the corresponding at least one data value signal in the knowledge base for the selected one of the plurality of design rule signals, create signals representative of a geometric representation of the selected one of the plurality of parameter signals of the associated element of the impingement film floatwall panels.

Method and system for designing an impingement film floatwall panel system

A method for designing an engine case static structure of a gas turbine engine includes creating signals representing an engine case static structure knowledge base of information. The knowledge base has a plurality of design rule signals with respect to a corresponding plurality of parameter signals of associated elements of an engine case static structure, wherein the knowledge base comprises at least one data value signal for each of the plurality of design rule signals. A desired data value signal is entered for a selected one of the plurality of parameter signals of an associated element of the engine case static structure and compared to the corresponding data value signal in the knowledge base for the corresponding one of the plurality of design rule signals. Signals representative of a geometric representation of the selected parameter signal may be created.

Method and system for designing frames and cases

A method and system for designing a low pressure turbine shaft comprising the steps of creating a low pressure turbine shaft knowledge base of information. The knowledge base has a plurality of design rule signals with respect to a corresponding plurality of parameter signals of associated elements of a low pressure turbine shaft, wherein the knowledge base comprises at least one data value signal for each one of the plurality of design rule signals. The steps also include entering a desired data value signal for a selected one of the plurality of parameter signals of an associated element of the low pressure turbine shaft and comparing the entered desired data value signal for the selected one of the plurality of parameters with the corresponding at least one data value signal in the knowledge base for the corresponding one of the plurality of design rule signals. If the result of the step of comparing is such that the entered desired data value signal for the selected one of the plurality of parameter signals is determined to have a first predetermined relationship with respect to the corresponding at least one data value signal in the knowledge base for the selected one of the plurality of design rule signals, create signals representative of a geometric representation of the selected one of the plurality of parameter signals of the associated element of the low pressure turbine shaft.

Method and system for designing a low pressure turbine shaft

A method and a system for designing a spline coupling, comprising the steps of creating signals representing a spline coupling knowledge base of information having a plurality of rule signals with respect to a corresponding plurality of parameter signals of associated elements of the spline coupling, wherein the spline coupling knowledge base comprises at least one data value signal for each one of the plurality of rule signals. Included are the steps of entering a desired data value signal for a selected one of the plurality of parameter signals of an associated element of the spline coupling, and comparing the entered desired data value signal for the selected one of the plurality of parameter signals with the corresponding at least one data value signal in the spline coupling knowledge base for the corresponding one of the plurality of rule signals. The steps also include creating signals representative of a geometric representation of the selected one of the plurality of parameter signals of the associated element of the spline coupling if the result of the step of comparing is such that the entered desired data value signal for the selected one of the plurality of parameter signals is determined to have a first predetermined relationship with respect to the corresponding at least one data value signal in the spline coupling knowledge base for the selected one of the plurality of rule signals.

Method and system for designing a spline coupling

A method of designing an outer air seal for the turbine blades of a gas turbine engine utilizes a knowledge-based product model software program for generating a parametric, three-dimensional, geometric model of the air seal. The product model software program is embodied in a knowledge-based engineering system. The model is created by the program through user selection of various structural feature options available for the air seal. The product model software program uses its internal knowledge base of configuration dependent parameter relationships and rules to design the model. Various types of analyses may then be run to validate the model. The model may be changed, if necessary, as a result of the analyses. The air seal model output from the product model software program is in a file format that defines the topology and dimensions of the geometry of the air seal. Other software programs may then use this product model output file in various ways, such as to re-generate the model for use in a CAD system.

Method of designing a turbine blade outer air seal

The deaerator includes a chamber that includes vortex generators that centrifuge the oil/air to separate the components and the chamber may operate in all attitudes. In addition wake separators mounted in the inlet of the chamber remove a large percentage of the air from the oil prior to entering the chamber and reintroduce the separated air component in the air removal tube. A dam in the air removal tube is located downstream of the inlet of the wake separated air to assure no oil is extracted from the air tube leaving the chamber. The wake separator consists of one or more tubes extending transversely to the flow of the oil/air stream and the air is removed through rearwardly facing apertures formed in the tube(s).

Multi-attitude deaerator for oil tank

A deoiler for a jet engine which separates oil droplets from an air/oil mixture in three stages, the first stage employing external radial extending vanes having a curved inducer, the second stage employing vanes which are laid over in the direction of rotation of the deoiler, the windows through which the air/oil mixture flows from the second stage to the third stage being contoured to provide a maximum path for oil droplets to the second stage bleed holes.

Deoiler for jet engine

Growing community of inventors

Palm Beach Gardens, FL, United States of America

Gregory E Chetta