United Technologies Corporation

Thomas B Fortin

Sergio Rinella

Andreas Sadil

Daniel P Guinan

George F Titterton, Iii

Gregory E Chetta

Henry K Webster

Scott A Ladd

Thomas E Holladay

Duncan C Meyers

Mark A Sillence

David W Leung

Costante Salvador

Dennis J Nemecek

Keith C Belson

John V Diaz

Randall G McKinney

Revi K Nigam

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

The present invention relates to a scram jet engine for use with a hypersonic vehicle. The scram jet engine has an upper boundary wall, a lower boundary wall, and a plurality of side walls defining an inner air flowpath. The walls are formed by a plurality of tubular heat exchanger panels. Each of the heat exchanger panels comprises a plurality of structural panels, each having a plurality of cooling passages, joined together. In the scram jet engine of the present invention, fuel may be used as a coolant and supplied to the cooling passage.

Scram jet engine design

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Lauderhill, FL, United States of America

Thomas B Fortin