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:
Oct. 13, 2009
Filed:
Oct. 31, 2003
Edward Durell Benjamin, Simpsonville, SC (US);
Jeffrey John Butkiewicz, Simpsonville, SC (US);
Mark Steven Honkomp, Taylors, SC (US);
Stephen Paul Wassynger, Simpsonville, SC (US);
Emilio Fernandez, Taylors, SC (US);
Carlos Alberto Collado, Simpsonville, SC (US);
Edward Durell Benjamin, Simpsonville, SC (US);
Jeffrey John Butkiewicz, Simpsonville, SC (US);
Mark Steven Honkomp, Taylors, SC (US);
Stephen Paul Wassynger, Simpsonville, SC (US);
Emilio Fernandez, Taylors, SC (US);
Carlos Alberto Collado, Simpsonville, SC (US);
General Electric Company, Schenectady, NY (US);
Abstract
A method and apparatus for a rotor assembly for gas turbine engine are provided. A first rotor blade including an airfoil, a platform, a shank, an internal cavity, and a dovetail is provided, wherein the airfoil extends radially outward from the platform, which includes a radially outer surface and a radially inner surface, the shank extends radially inward from the platform, and the dovetail extends from the shank, such that the internal cavity is defined by the airfoil, the platform, the shank, and the dovetail. The first rotor blade is coupled to a rotor shaft such that during engine operation, cooling air is channeled from the cavity through an impingement cooling circuit for impingement cooling the first rotor blade platform radially inner surface, and a second rotor blade is coupled to the rotor shaft such that a platform gap is defined between the first and second rotor blade platforms.