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Component with internal damping

a technology of internal damping and components, applied in the direction of liquid fuel engines, marine propulsion, vessel construction, etc., can solve the problems of excessive stiffness of warren girders, unable to permit a significant degree of relative movement, and blades subject to vibration

Inactive Publication Date: 2009-01-15
ROLLS ROYCE PLC
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

[0022]The damping material may be injected into more than one of the cavities. However, a problem with this is that more than one of the cavities must be weakened with an inlet port, and more than o

Problems solved by technology

The blade is subject to vibration induced by flutter and distortions in the gas flow over the blades.
A problem with the arrangement of US 2004 / 0191069 A1 is that the warren girder structure is too stiff to permit a significant degree of such relative movement.
Furthermore, the warren girder structure is relatively heavy.

Method used

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Examples

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Embodiment Construction

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[0036]The fan blade shown in FIG. 1 comprises outer panels 2,4 between which a warren girder structure 6 is disposed. The panels 2, 4 and the warren girder structure 6 are made from a titanium alloy. The panels 2 and 4 are diffusion bonded to each other at the leading and trailing edges 8, 10 of the blade, and to the warren girder structure 6 at contact regions 12, so that the warren girder structure 6 provides a plurality of partitions extending across the interior of the blade.

[0037]The blade shown in FIGS. 1 and 2 is formed from a precursor assembly shown in FIG. 3. The precursor assembly comprises an opposed pair of panel precursors 2a, 4a (which eventually form the panels 2,4); and a membrane precursor 6a (which eventually forms the warren girder structure 6) disposed between the panel precursors. These precursors are initially flat.

[0038]A series of stripes 14 of stop-off material, for example yttria, are applied to the inner surface of the panel precursors, between the conta...

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Abstract

A method of manufacturing a component such as a gas turbine fan blade. The method comprises: disposing a plurality of webs between a plurality of panels; and deforming the panels and the webs by applying internal pressure between the panels, thereby forming a series of internal cavities (15) partitioned by the webs (20-22). Weakened regions (30a,30b,30c) are formed in the webs which open to form holes (30) in the webs (20-22) during the deformation step. A damping material (17) is introduced into at least one of the cavities (15) whereby it flows from the cavity into the other cavities via the holes in the webs.

Description

FIELD OF THE INVENTION[0001]The present invention relates to a component with internal damping, a method of manufacturing such a component, and a precursor assembly for forming such a component. The invention is particularly, although not exclusively, concerned with components for use in gas turbine engines, for example fan blades.BACKGROUND OF THE INVENTION[0002]In US 2004 / 0191069, a gas turbine blade is manufactured by a superplastic forming and diffusion bonding technique which results in a hollow blade, ie a blade having at least one internal cavity. A pair of panel precursors are laid in face-to-face contact with a membrane precursor. A predetermined pattern of stop-off material is applied to the panels. The precursors are diffusion bonded together, except where this is prevented by the stop-off material. Subsequently, internal pressure is created between the panels, causing the panels and membrane to deform superplastically to form a warren girder structure, with cavities in t...

Claims

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Application Information

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IPC IPC(8): F01D5/14B21K3/04B21D26/055
CPCB21D26/055Y10T29/49337B21D53/78B23P15/04F01D5/147F01D5/16F02K3/06F04D29/023F04D29/388F04D29/668F05D2300/501F05D2300/612F05D2300/615F05D2300/61B21D47/00F05D2300/43F05D2300/522
Inventor STROTHER, OLIVER M.
Owner ROLLS ROYCE PLC