The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.
The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.
Patent No.:
Date of Patent:
Apr. 08, 2008
Filed:
May. 13, 2004
Robert Joseph Orlando, West Chester, OH (US);
Thomas Ory Moniz, Loveland, OH (US);
John C. Brauer, Lawrenceburg, IN (US);
John Leslie Henry, West Chester, OH (US);
Raymond Felix Patt, Cincinnati, OH (US);
Randy Marinus Vondrell, Sharonville, OH (US);
James Patrick Dolan, Cincinnati, OH (US);
Erich Alois Krammer, West Chester, OH (US);
David Cory Kirk, Mason, OH (US);
Robert Joseph Orlando, West Chester, OH (US);
Thomas Ory Moniz, Loveland, OH (US);
John C. Brauer, Lawrenceburg, IN (US);
John Leslie Henry, West Chester, OH (US);
Raymond Felix Patt, Cincinnati, OH (US);
Randy Marinus Vondrell, Sharonville, OH (US);
James Patrick Dolan, Cincinnati, OH (US);
Erich Alois Krammer, West Chester, OH (US);
David Cory Kirk, Mason, OH (US);
General Electric Company, Schenectady, NY (US);
Abstract
A method facilitates assembling a gas turbine engine including a compressor and a rotor assembly coupled in axial flow communication downstream from the compressor. The method comprises coupling a bypass system in flow communication with the compressor to channel a portion of flow discharged from the compressor towards the rotor assembly is channeled through the bypass system, and coupling a downstream end of the bypass system within the gas turbine engine such that the flow entering the bypass system flows past the rotor assembly and is discharged downstream from the rotor assembly.