IP Library Granted Patent US 9,764,382
Granted Patent B2
US 9,764,382 · App. 15/115,218 · Granted Sep 19, 2017

Lined centrifugal mould with controlled thermal inertia

Inventors: Guillaume Martin (Moissy-Cramayel, FR); Serge Fargeas (Moissy-Cramayel, FR); Marc Soisson (Moissy-Cramayel, FR); Valéry Piaton (Moissy-Cramayel, FR)
Assignee: Safran Aircraft Engines
B22D13/102B22D13/101B22D27/20
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Quick Facts
Patent No.
US 9,764,382
App. No.
15/115,218
Granted
Sep 19, 2017
Kind
B2
Abstract

The invention concerns a unit comprising a mold ( 4 ) adapted to receive a molten metal alloy and the said metal alloy poured therein. The alloy is TiAl. The mold is rotational and comprises receiving recesses ( 135 ) made of steel, metal alloy and/or ceramic, and, at the location of a plurality of section planes each passing through the mold and the poured metal alloy, the mold has a surface heat capacity less than that of the poured metal alloy.

Claims (21)

1. Unit comprising:

a mould rotating around an axis, for centrifuge casting,

and a TiAl metal alloy poured thereinto,

the mould including:

receiving recesses made of soft steel, steel, metal alloy and/or ceramic, adapted to receive the centrifuge casting of the said molten TiAl metal alloy, the recesses extending radially around the axis, and

liners defining all the recesses and which are housed in at least one hollow soft steel, steel or metal alloy exoskeleton, and

at the location of a plurality of section planes each passing through the mould and the poured metal alloy, the mould having a surface heat capacity less than that of the poured metal alloy,

of which:

the exoskeleton or exoskeletons is/are open-worked, or

an empty space exists around the periphery between each liner and the exoskeleton that surrounds it, or

an alveolar structure exists around the periphery between each liner and the exoskeleton that surrounds it.

2. A centrifuge casting mould, specific for the unit of claim 1 , the mould being rotational around an axis and comprising:

several receiving recesses to receive a molten TiAl alloy extending radially around the axis, and

liners defining all the recesses and which are housed in at least one hollow exoskeleton, the exoskeleton or exoskeletons being made of soft steel, steel or metal alloy, and the liner being made of soft steel, steel or metal alloy and/or ceramic, and

the exoskeleton or exoskeletons is/are open worked, or

an empty space exists around the periphery between each liner and the exoskeleton that surrounds it, or

an alveolar structure exists around the periphery between each liner and the exoskeleton that surrounds it.

3. The mould of claim 2 , comprising a central block having ducts through which the alloy is poured and which are connected to the interior liners, and at least one fixing, preferably removable, is implemented:

between each liner and the exoskeleton that surrounds it, and/or

between each liner and/or the exoskeleton that surrounds it and the central block.

4. The mould of claim 2 , wherein the liners being filled with molten metal alloy, the said mould has a surface heat capacity less than that of the contained metal alloy, this occurring at a plurality of section planes passing respectively through at least one of the said liners and the exoskeleton that surrounds it and the contained metal alloy.

Assignments (2)
ASSIGNMENT OF ASSIGNOR'S INTEREST Recorded Jul 28, 2016
From: GUILLAME, MARTIN; FARGEAS, SERGE; SOISSON, MARC; PIATON, VALEY
To: SNECMA
Reel/Frame 039285/0902 →
CHANGE OF NAME Recorded Jul 28, 2016
From: SNECMA
To: SAFRAN AIRCRAFT ENGINES
Reel/Frame 039504/0288 →
Priority Claims (1)
FR 14 50800 · Jan 31, 2014 · national
Continuity (1)
Related Publication 20160339512A1 · Nov 24, 2016