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US Patent 7147426 Shockwave-induced boundary layer bleed

Patent 7147426 was granted and assigned to Pratt & Whitney Canada on December, 2006 by the United States Patent and Trademark Office.

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Patent Citations Received
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US Patent 12066027 Variable geometry supersonic compressor
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Patent Citations Received
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US Patent 11840939 Gas turbine engine with an airfoil
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Patent Inventor Names
André Denis Leblanc0
Gilbert Ouellet0
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Patent abstract

An apparatus and method is provided for improving efficiency of a transonic gas turbine engine compressor by bleeding off a shockwave-induced boundary layer from the gas flow passage of the compressor using an array of bleed holes having a downstream edge aligned with a foot of an oblique shock wave which originates on the leading edge of an adjacent transonic rotor blade tip.

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Official Website
https://pdfpiw.uspto.gov/.piw?Docid=071474260
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US Patent 07147426 Shockwave-induced boundary layer bleed US Patent 7147426 Shockwave-induced boundary layer bleed

Infobox
Patent Number
071474260
Patent Number
71474260
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Infobox
Is a
Patent
Patent
0
Current Assignee
Pratt & Whitney Canada
Pratt & Whitney Canada
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Patent Jurisdiction
United States Patent and Trademark Office
United States Patent and Trademark Office
0
Patent Number
071474260
Date of Patent
December 12, 2006
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Patent Application Number
108402910
Date Filed
May 7, 2004
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Official Website
https://pdfpiw.uspto.gov/.piw?Docid=071474260
Patent Primary Examiner
Christopher Verdier
Christopher Verdier
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Website URL
https://pdfpiw.uspto.gov/.piw?Docid=07147426
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 US Patent 07147426 Shockwave-induced boundary layer bleed

Infobox
Is a
Patent
Patent
Current assignee
Pratt & Whitney Canada
Pratt & Whitney Canada
Patent jurisdiction
United States Patent and Trademark Office
United States Patent and Trademark Office
Patent number
07147426
Date of patent
December 12, 2006
Patent application number
10840291
Date Filed
May 7, 2004
Patent primary examiner
Christopher Verdier
Christopher Verdier

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