Method for manufacturing a hollow aerofoil

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EP 2 014 386 A8

(12)	CORRECTED EUROPEAN PATENT APPLICATION
	Note: Bibliography reflects the latest situation

(15)	Correction information:
	Corrected version no 1 (W1 A1)

(48)	Corrigendum issued on:
	11.03.2009 Bulletin 2009/11

(43)	Date of publication:
	14.01.2009 Bulletin 2009/03

(21)	Application number: 08011077.8

(22)	Date of filing: 18.06.2008

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International Patent Classification (IPC):

B21D 53/78^(2006.01)
F01D 5/18^(2006.01)

B23P 15/04^(2006.01)

(84)	Designated Contracting States:
	AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MT NL NO PL PT RO SE SI SK TR
	Designated Extension States:
	AL BA MK RS

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Priority:

13.07.2007 GB 0713699

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

(72)	Inventors:
	Goldfinch, Keith Christopher Hotwells Bristol BS8 4TE (GB) Strother, Oliver Michael Clifton, Nottingham NG11 8FB (GB) Mackechnie-Jarvis, Julian Meersbrook, Sheffield S8 9QB (GB)

(74)	Representative: Bird, Vivian John et al
	Rolls-Royce plc, Intellectual Property Dept WH 20 P.O. Box 3, Filton Bristol BS34 7QE Bristol BS34 7QE (GB)

(54)	Method for manufacturing a hollow aerofoil

(57) A method of manufacturing an aerofoil for a gas turbine engine (10). The method comprises the steps of providing first and second panels (16, 18), providing a web (30) between the first and second panels, deforming the panels by applying internal pressure between the panels so as to form an internal cavity. The method further includes the step of providing a pattern of ribs (60) on the web so as to define a aerofoil having first and second panels with at least one rib (60) forming a protrusion extending from the first panel partially across the space between the first and second panels.