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Turbine vane cooled by a reduced cooling air leak
   
Document Number
US Patent 7011492
Issued Date
March 14, 2006
Link
Inventors
Dubois; Laurent (Dammarie les Lys,FR)
Redon; Damien (Issy les Moulineaux,FR)
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Abstract
A turbine vane includes a perforated liner defining an annular cavity between an outside wall of the liner and an inside wall of the vane, an air admission opening for feeding the inside of the liner with cooling air, and an air exhaust opening for exhausting a fraction of the cooling air from the vane. The liner is secured to the vane at one end and free at the other end to slide along an inside edge of the vane under the effects of relative thermal expansion between the liner and the inside wall of the vane. An annular gap between the free end of the liner and the inside edge of the vane defines a leakage zone for cooling air and the inside edge includes a recess for generating head loss in this leakage zone so as to reduce the flow rate of cooling air passing through the leakage zone.
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Number of Claims:
19
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Owner
Snecma Moteurs (Paris,FR)
Published
March 14, 2006
Application Number
10/776,280
Filed
February 12, 2004
US Classification
415/115   416/96A
Int'l Classification
F01D   9/06   (20060101)  
Priority Data
Feb 18, 2003 [FR] 03 01916
USPTO Field of Search
415/115   415/116   416/96R   416/96A   416/97R  
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