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:
Jun. 07, 2022
Filed:
Apr. 29, 2020
Pratt & Whitney Canada Corp., Longueuil, CA;
Ignatius Theratil, Mississauga, CA;
Krishna Prasad Balike, Brampton, CA;
Aldo Abate, Longueuil, CA;
Sean Kelly, Milton, CA;
Peter Townsend, Mississauga, CA;
Ronald Dutton, Guelph, CA;
Anthony Brown, Mississauga, CA;
Paul Stone, Guelph, CA;
Myron Klein, Higganum, CT (US);
Milica Kojovic, Oakville, CA;
Robert Venditti, Woodbridge, CA;
PRATT & WHITNEY CANADA CORP., Longueuil, CA;
Abstract
The gas turbine compressor for an aircraft gas turbine engine includes a compressor rotor having a plurality of compressor blades circumferentially distributed around a hub. Each of the compressor blades has an airfoil extending radially outward from the hub to a blade tip. A circumferential row of the compressor blades includes two or more different blade types, at least one modified blade of the two or more different blade types having means for generating different shock patterns between adjacent ones of the two or more different blade types when the gas turbine compressor operates in supersonic flow regimes. The means for generating different shock patterns on the modified blade aerodynamically mistune the two or more different blade types.