(19)
(11) EP 2 703 605 A3

(12) EUROPEAN PATENT APPLICATION

(88) Date of publication A3:
14.06.2017 Bulletin 2017/24

(43) Date of publication A2:
05.03.2014 Bulletin 2014/10

(21) Application number: 13179761.5

(22) Date of filing: 08.08.2013
(51) International Patent Classification (IPC): 
F01D 11/12(2006.01)
F01D 11/08(2006.01)
F01D 5/14(2006.01)
 F01D 5/28(2006.01)
F01D 5/20(2006.01)
(84) Designated Contracting States:
AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR
Designated Extension States:
BA ME

(30) Priority: 29.08.2012 GB 201215299

(71) Applicant: Rolls-Royce plc
London SW1E 6AT (GB)

(72) Inventors:
  • Care, Ian
    Derby, Derbyshire DE23 6EU (GB)
  • Zumpano, Giuseppe
    Derby, DE22 2BU (GB)
  • Merriman, Nicholas Michael
    Derby, DE22 1DA (GB)

(74) Representative: Rolls-Royce plc 
Intellectual Property Dept SinA-48 PO Box 31
Derby DE24 8BJ
Derby DE24 8BJ (GB)

   


(54) A gas turbine blade tip omprising a metallic foam material


(57) Tip rub in gas turbine engines is a well-known phenomenon, and may lead to increased tip clearances, with consequent detrimental effects on the engine's performance and blade flutter margins. Heavy or repeated rubbing may cause blade tip over temperature leading to cracking and fatigue failure. The invention provides a tip for a gas turbine engine rotor blade, which under contact with the casing surface interacts with the casing surface so as to reduce the contact force and thereby reduce the energy transferred to the blade. The tip may be designed to ablate under contact with the casing surface, or to cut or abrade the casing surface, or to crush or compress of deflect under contact with the casing surface. In a preferred embodiment, the tip comprises fibre-reinforced metallic foam material.







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