US2009269189A1PendingUtilityA1

Fan blade

51
Assignee: ROLLS ROYCE PLCPriority: Apr 23, 2008Filed: Mar 31, 2009Published: Oct 29, 2009
Est. expiryApr 23, 2028(~1.7 yrs left)· nominal 20-yr term from priority
Inventors:Kristofer J. Bottome
F04D 29/164F05D 2220/36F05D 2220/323F05D 2240/55F01D 11/12F05D 2240/307
51
PatentIndex Score
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Cited by
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References
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Claims

Abstract

A fan blade for the fan of a gas turbine engine has a radially outer tip portion which, in use, is adjacent to a fan case of the engine. The tip portion includes a movable sealing element for sealing a gap between the tip portion and the fan case. The sealing element movably adapts to changes in the spacing of the gap to maintain a seal between the tip portion and the fan case.

Claims

exact text as granted — not AI-modified
1 . A fan blade for the fan of a gas turbine engine, the blade having a radially outer tip portion which, in use, is adjacent to a fan case of the engine, the tip portion including a movable sealing element for sealing a gap between the tip portion and the fan case, wherein the sealing element movably adapts to changes in the spacing of the gap to maintain a seal between the tip portion and the fan case. 
   
   
       2 . A fan blade according to  claim 1 , wherein the sealing element is formed integrally with the blade. 
   
   
       3 . A fan blade according to  claim 1 , wherein the sealing element is removably attached to the blade. 
   
   
       4 . A fan blade according to  claim 1 , wherein the sealing element is formed of flexible material which flexes to adapt to changes in the spacing of the gap. 
   
   
       5 . A fan blade according to  claim 1 , wherein the sealing element responds to centrifugal loading by extending across the gap. 
   
   
       6 . A fan blade according to  claim 1 , which is configured to promote air film lubrication of the interface between the sealing element and the fan case. 
   
   
       7 . A gas turbine engine having a fan comprising circumferentially spaced fan blades according to  claim 1 . 
   
   
       8 . A gas turbine according to  claim 7 , wherein the fan case has an acoustic liner at the interface between the sealing element and the fan case. 
   
   
       9 . A gas turbine according to  claim 7 , wherein the fan case has debris removal channels at the interface between the sealing element and the fan case.

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