EP3129516A1

EP3129516A1 - Heat treatment of an alloy based on titanium aluminide

Info

Publication number: EP3129516A1
Application number: EP15719501.7A
Authority: EP
Inventors: Guillaume Martin; Céline Jeanne MARCILLAUD; Marie MINEUR-PANIGEON
Original assignee: SNECMA Services SA; SNECMA SAS
Current assignee: Safran Aircraft Engines SAS
Priority date: 2014-04-08
Filing date: 2015-04-02
Publication date: 2017-02-15
Anticipated expiration: 2035-04-02
Also published as: FR3019561B1; US10329655B2; US20170022594A1; FR3019561A1; WO2015155448A1; EP3129516B1

Abstract

The invention relates to a method for the treatment of an alloy based on titanium aluminide. The method comprises the following steps during which no hot isostatic pressing is carried out: a semi-finished product (7) produced by centrifugal casting is obtained; and said semi-finished product is then heat-treated in order to obtain a microstructure of the alloy comprising gamma grains and/or lamellar grains (alpha2/gamma).

Description

THERMAL TREATMENT OF AN ALUMINUM ALLOY

TITANIUM

The present invention relates to the heat treatment of metallurgical alloys and, more particularly, the heat treatments of a titanium aluminide alloy (titanium-aluminum alloy).

Titanium aluminides are a class of alloys whose compositions include at least titanium and aluminum, and typically some additional alloying elements.

Titanium aluminides, and in particular those of the gamma type (gamma titanium-aluminide alloys in English), have the advantage of low density, good resistance to cyclic deformation at low and intermediate temperatures, and good resistance to the environment. They find application in aircraft engines as low-pressure turbine (stator or rotor) vanes, bearing supports, high-pressure compressor housings, and low-pressure turbine sealing supports, among others.

Titanium aluminides, and in particular those of gamma type, are typically prepared by melting, molding and hot isostatic pressing in order to reduce the porosity resulting from the casting, followed by at least one heat treatment to obtain a good compromise between the mechanical properties in traction, fatigue and creep.

To obtain a microstructure and a porosity ratio ensuring good mechanical properties, it has been proposed in the past to use a combination of hot isostatic pressing at a temperature of about 1200 ° C., followed by a heat treatment at higher temperature, about 1300 ° C.

Unfortunately, this required a specialized oven that was expensive and may not be logistically available in all cases.

In US 5609698, it was subsequently proposed, to overcome this problem, to proceed as follows: - casting a gamma-type titanium aluminide alloy having from about 45.0 to about 48.5 atomic percent of aluminum (in the present application, all alloy compositions are present in atoms per cent -at %-, unless otherwise stated),

pre-heat treating (HIP heat treatement) of this alloy at a temperature of between about 1035 ° C (1900 ° F) and about 1150 ° C (2100 ° F) for about 5 to 50 hours,

then performing hot isostatic pressing (HIP) of the pretreated alloy, at a temperature of about 1175 ° C (2150 ° F) and at a pressure of about 1000 to 1700x10 ⁵ Pa, for about 3 to 5 hours ,

and then post-heat treating the post-HIP heat treating alloy at a temperature between about 1010 ° C (1850 ° F) and about 1200 ° C (2200 ° F), for about 2 to 20 hours .

The maximum values of these temperature ranges of heat treatments are certainly significantly below the temperature of about 1300 ° C (2375 ° F) previously used.

But, this requirement of strict control of the three parameters that are a high pressure (pressure HIP or CIC in French) a high temperature and a fairly long duration remains very restrictive.

However, it appeared against all odds to the inventors that, to facilitate the implementation of heat treatments of an alloy based on titanium aluminide, and in particular titanium aluminide gamma type, including in the context of the manufacture of a turbine blade in such an alloy, it is not so much (or essentially) the temperature that must be reduced in connection with hot isostatic compression that hot isostatic compression in itself that we must reconsider, contrary to what teaches at least US 5609698.

In fact, the quality of the finished products to be obtained (such as turbomachine turbine blades for aircraft), and the constraints imposed in particular by the previous techniques (costs, materials, specifications), led these inventors to dare to exonerate prejudices. techniques mentioned above. They were able to perceive that it seemed reasonable to be able to dispense with a hot isostatic compaction step under certain conditions.

They have thus been able to define a process for treating an alloy based on titanium aluminide, comprising the following steps:

performing a permanent mold casting mold to obtain a semi-finished product,

- then thermally treat the semi-finished product,

at a pressure lower than that of a hot isostatic pressing (CIC), preferably substantially equal to the atmospheric pressure, to obtain a microstructure of the alloy comprising gamma grains and / or lamellar grains (alpha2 /gamma).

In a comparable manner, they have defined a method of manufacturing a titanium aluminide based alloy turbine engine part comprising the following steps:

- Making a permanent mold casting mold to obtain a semi-finished product of less complex shape than that of the finished product,

- Then thermally treat the semi-finished product, without hot isostatic compression,

at a pressure lower than that of a hot isostatic pressing (CIC), preferably substantially equal to atmospheric pressure, to obtain a microstructure comprising gamma grains and / or lamellar grains (alpha2 / gamma),

- Then, machining, according to the shape of said part, the thermally treated semi-finished product.

On the basis of the elements previously provided, it will be understood that this "lower pressure than hot isostatic compression" will necessarily be less than 1700x10 ⁵ Pa, and preferably less than 1000x10 ⁵ Pa.

In addition, and in fact it could be verified:

- that the mold casting permanent mold casting can significantly reduce the number and size of pores, so that the criteria applied for example to a turbine blade are observed in the raw state of casting,

and that the simplest mold shapes are the most effective in reducing the rate of porosity.

This has also been noted by several analyzes (optical microscope observation, bleeding, radio X-ray) on TiAI 48-2-2 obtained in a cylindrical mold: the few observed porosities did not exceed a few hundred micrometers in diameter.

A preferred feature of the invention further provides that the step of obtaining the semi-finished product from the spin casting comprises a casting in said permanent mold that the alloy will then fill in such a way that the size of the internal pores of this alloy is reduced after casting compared to what it was before.

It will be sought in fact that the simple shape of the mold (without undercut) allows it to be rapidly filled by the alloy in such a way as to reduce the size of its internal pores compared to that this pore size would be without casting in such a mold.

In a practical way, one can favorably, to ensure for this purpose:

the mold can be filled at a speed (rate of flow of the alloy in the mold) which is greater than the solidification rate at the core (ie in the mold) of the alloy, and or

said simple form of the mold allows it to be filled in less than one minute, preferably 30 seconds, and more preferably 20 seconds, with the alloy (such as TiAl 48-2-2, in particular).

It will also be sought, favorably, that it does not generate hot spots (As known, a hot spot is typically an area where the temperature of the alloy cast in the mold is higher and / or the flow of this alloy is less favorable, or the diffusion of the heat of the metal towards the mold also less favorable, such at the place of a ridge of the mold).

In particular, if the speed of casting / filling of the mold is too slow, there is a risk of deterioration of the cast form. When the semi-finished product is thermally processed, after the molding thus produced on a simple form still to be machined to reach the finished part, it is also preferred that this be done at a pressure:

- lower than that of hot isostatic compression,

and preferably substantially equal to the atmospheric pressure.

It follows that, when compared to what is taught in US 5609698, where a complex solution involving a simultaneous control of a high temperature and a high pressure is implemented, the method then it will consist of replacing the step, judged in this essential prior patent, of hot isostatic compaction of a product of complex shape (having the shape of the finished part) resulting from molding in a temporary mold, by centrifugal casting in a permanent mold, by following this casting by a temperature treatment without necessarily the high pressure of hot isostatic compression.

Still in the same approach for the aforementioned effects, it is furthermore recommended that the step of obtaining the semi-finished product resulting from molding comprises:

from the casting of molten alloy, the production of a first ingot, in this material,

- Then, after a redone of this ingot in a cooled metal crucible, its pouring into a centrifuged permanent metal mold, in order to obtain a molded ingot,

- This being followed by a release of the ingot and if necessary its cutting (coarse) semi-finished product.

With regard to this molding / cutting aspect, it is furthermore recommended that the above-mentioned step of obtaining the semi-finished product resulting from molding comprises said molding in a metal mold, by centrifugal casting of the alloy, alone or followed by cutting (coarse) into parts of said molded alloy, according to a simple form blank (corresponding to the simple shape of the permanent mold used):

- having at least one plane of symmetry, or, - exhibiting externally at most an inflection by which the section of the semi-finished blank increases or decreases, with along said axis:

- maximum thicknesses of the blank located at ends (a priori opposed) thereof, or

a maximum thickness of the blank located at one end only.

Centrifugation in a permanent metal mold will:

to optimize the filling of the mold, especially if the shape is simple,

- to minimize the material used; in fact, the center of the mold may not be completely filled, unlike a temporary / lost casting foundry solution (lost wax) where the castings are filled with metal,

- Unmolding and cutting into a semi-product of simple shape that will not require dimensional control before machining.

A feature of the proposed solution also provides that the raw semifinished molding product can be heat treated and then machined directly without intermediate dimensional control of a blank.

A simple mold geometry, therefore of the blank that comes out of its cavity, (typically having at least one plane of symmetry and / or at most one inflection) will limit the risks of non-compliance (limitation of the porosity rate by avoiding create hot spots). In addition, the fact that the mold is a metal mold will eliminate the risk of obtaining ceramics inclusions from the ceramic shell in the case of lost-wax foundry process And a simple geometry of mold, so rough, will allow easy automation of machining.

It is specified that the values provided in the present application in connection with the proposed solution are to be considered to within 20%.

More precisely, it is advised that, in order to thermally treat the semi-finished product, it is carried successively:

at a temperature of between 1045 ° C. and 1145 ° C., for 5 to 15 hours, at a pressure lower than that of a hot isostatic pressing, preferably substantially equal to atmospheric pressure, at a temperature of between 1135 ° C. and 1235 ° C., for 3 to 10 hours, at a pressure lower than that of a hot isostatic pressing, preferably substantially equal to atmospheric pressure, and then

at a temperature of between 1155 ° C. and 1255 ° C., for 2 to 15 hours, at a pressure lower than that of a hot isostatic pressing, preferably substantially equal to atmospheric pressure.

Later in the description, test results conducted in this context establish the relevance of such values.

It will be noted again the advantage of the solution presented here if the machined part is an aircraft turbine blade, or if the alloy is intended for such a blade, when reading in WO2014 / 057222 pages 1-2 CIC isostatic pressing is [then] necessary in order to close the possible porosities ". The developments presented here allow to exonerate CIC compression, without the porosity rate being affected.

Before that, other features, details and advantages of the invention will become apparent from the following relating to implementation examples and whose contents refer to the accompanying drawings where:

FIG. 1 is a possible functional diagram for the method of the invention;

FIG. 2 is a block resulting from molding corresponding to a semi-finished product in which here blades will be able to be machined,

FIG. 3 is a schematic view of a permanent mold centrifugal casting molding device, which can be used here,

FIG. 4 is a schematic view from above of the permanent mold of FIG. 3 (arrow IV),

FIGS. 5, 6 are two schematic views of permanent molds, or molding cavities, of simple shapes that can be used on the aforementioned device, illustrated in FIG. 2;

8,9 schematically another example of permanent mold, of simple shape (cylindrical bar), seen from the rear (arrow VIII of FIG. 7), respectively closed and open, FIGS. 10, 11 show microstructures obtained respectively with and without hot isostatic compaction, for the same thermal history,

and FIG. 12 is a graph obtained from tests (numbered from 1 to 9 on the abscissa) and illustrates the difference between the result obtained obtained for test pieces (cylinders) treated thermally with isostatic compaction at hot (filled diamonds) or without hot isostatic compaction (hollow diamonds).

FIG. 1 therefore illustrates the main steps not only of treating the alloy concerned, but more generally, as a finished product, for example of a titanium aluminide based alloy turbine blade.

It can thus be confirmed that no hot isostatic compression has been achieved in this case.

As for treatment as such, it consists of:

- Making, in 3, a casting by centrifugal casting, pouring the alloy for this in a permanent mold 5, this to obtain a semifinished product 7 of simple shape, less complex than that of the finished product 9, such a turbomachine turbine blade,

- Heat treatment of the semi-finished product, 11, without necessarily using hot isostatic compression.

An alloy microstructure comprising gamma grains and / or lamellar grains (alpha2 / gamma) is thus obtained.

Then, for the manufacture of the finished product 9, it is going, in step 13, machining in this form here of one or more turbine blades, the thermally treated semi-finished product (see Figure 2).

For permanent mold casting, a device 15 may be used as illustrated in FIG. 3, which will make it possible to mold a series of semi-finished blanks 7, each of which may have a raw bar form of a foundry where it will then be machined ( s) the (the) part (s) finie (s), here two blades 17 turbomachine turbine. The device 15 comprises an enclosure 19 closed and sealed in which can be applied a partial vacuum. An ingot 21, in this case an alloy based on titanium aluminide, and more specifically gamma-type titanium aluminide, is first melted in a crucible 23. In melting, the alloy is then poured into a mold 25 permanent metal, via a funnel 26.

The mold 25 makes it possible to cast the alloy by centrifugation, in order to obtain the blanks 7. For this, it is rotated about an axis A. The mold 25 comprises several cavities 27 which extend radially (axes B1 , B2 ...; 3, 4) about the axis A, preferably via a motor 29. These cavities are preferably regularly spaced angularly about the axis A which is here vertical. The centrifugal forces generated by the rotation of the mold cause the molten alloy to penetrate and fill these cavities. Thus, the casting alloy, brought to the center of the mold, is distributed radially to the peripheral cavities.

After cooling, the mold 25 is opened and the molded blanks 7 are extracted. The walls of the mold which surround the cavities 27 for collecting the metal resist the centrifugal forces, typically more than 10 g.

During rotation around the axis A, the casting of alloy will thus be pressed against the walls of these cavities under the action of the centrifugal force. To do this, it is recommended a rotation speed of the order of 150 to 400 revolutions / min.

As known, by the rotation of the cast liquid metal, the particles are subjected to a centrifugal force, which can be increased with the angular velocity. This increase is distributed over the entire mass of the liquid metal, uniformly over the entire length of each cavity 27.

In FIG. 4, as in FIGS. 5, 6, 8, in addition to the cavities (according to one embodiment), the schematic outline of the blank corresponding to them is shown in dotted lines.

It should also be noted that FIGS. 8, 9 schematize a typical characteristic of a permanent mold that can be used several times: the mold comprises several shells, such as 150a, 150b, which open and close along a surface (here the joint plane 152) which is generally transverse to the axis (A) around which the mold rotates.

A separable attachment 153, such as a latch, is established between the shells so that, once the shells are separated, the molded blank can be released through the opening 154 released.

In FIGS. 5, 6, the lines 152 also represent a joint plane making it possible to close and open the mold in question.

Figure 5, the mold shown has first and second sides 33a, 33b opposite along the axis 35 and parallel to each other. These two sides are one the inlet side of the casting; It is therefore radially internal and the axis 34 is parallel (or even coincident) with one of the axes B, such as B1.

To optimize the attainment of a high quality of finished parts and of material consumption as limited as possible, this mold (and therefore the solid blank, polyhedron obtained) has here, between the first and second sides mentioned above, a third and a fourth side (33c, 33d) which widens between them from the first side 33a towards the second side, at a first angle and, from a break of slope (or inflection) 35, at a second greater angle than the first.

Overall, this mold (its molding cavity) is defined (e) by a first and a second truncated pyramids 37a, 37b, the second pyramid being the extension of the first pyramid by the large base of the first pyramid which is superimposed exactly on the small base of the second.

The mold and its molded blank have a plane of symmetry 39 perpendicular to the first and second sides 33a, 33b and which contains the axis 34.

In addition, in connection with the angles marked in FIG.

the first angle α is between 0 ° and 15 °,

the second angle γ is less than 120 °, and preferably less than 90 °,

and that the break in slope is less than 85%, and preferably less than 75%, of the shortest distance between the first and second sides, starting from the first side 33a. The embodiment of the molding cavity of FIG. 6 illustrates a polyhedral molding cavity having two opposite sides, each of generally trapezoidal shape 37a, 37b.

Like the cavity, the molded blank presents here:

two substantially trapezoidal bases located facing opposite sides of larger surfaces 41a, 41b, respectively, along the axis of elongation 43, and

- An angular opening (a2) of each of these two trapezoidal bases between 2 ° and 10 °, preferably between 3 ° and 8 °, x N, N being the number of finished products (intended to be) machined integrally in it.

The access to the interior of the cavity can be done radially by one of the two lateral sides, here the largest 41 c.

Thus, in both cases above, the blank has externally on a given side or face - at most an inflection by which the section of the semi-finished blank increases or decreases, with, according to its extension axis, here 34 or 43, a maximum cross section SJ_ of the blank located at one end, along this axis.

Still in the context of a thermal control, preferably in combination with that of the forces, FIG. 7 shows another advantageous solution of mold where, individually, the radially open inner end 45a of the cavity 27 for casting the alloy has a narrowing sectional shape (zone 47a) towards the center of the cavity, along the radial direction B. A truncated cone could be suitable. The shape is here in fact double funnel (head to tail), with a radially outer end portion of the cavity, which is supported, to present an enlarged end portion 47b.

Thus, mold / blank section S2, S3 maximums are molded towards the ends, it being specified that the sections S1, S2, S3 are each defined externally, transversely to the axis of elongation concerned, as illustrated.

Typically, if at least one turbomachine part is then machined in the corresponding cast form blank, the shape 47a can correspond to the heel area of this blade and the end portion 47b to the enlarged foot zone, or vice versa.

As already indicated, such simple shapes serve to favor at least part of the following:

- optimize the filling of the mold,

- facilitate dimensional checks,

- to limit the risks of nonconformities (by reducing the foundry defects),

- easily automate subsequent machining,

- avoid creating hot spots and therefore limit the rate of porosities.

Another effect expected / produced by this permanent mold mold casting thus simple form, is obtaining, at the end of molding, a blank 7 having, relative to the internal structure of the alloy provided in each cavity 27 , a (micro) internal structure whose pores have a smaller size (a volume), or have disappeared, to tend towards a (more) dense material. Figure 11 shows this result.

To promote this by combining the effects of gravity, it is recommended, as shown in Figure 1:

that from an initial casting of the alloy (not shown), is elaborated with this molten alloy a first blank corresponding to the ingot 21 which will then be cast,

- Then, this first blank 21 is thus remelted in the crucible 23, the remelted alloy being poured into the centrifuged permanent mold 25 to obtain a series of molded ingots corresponding to the blanks 7 (which may be called second blanks) .

For a good technical mastery, the elaboration of the first draft will be carried out by VAR (Vacuum Arc Remelting) or by PAM (Plasma Arc Melting - Fusion by arc under plasma) then the redesign of this first draft will be done by VAR SM (Skull Melter).

Then, and preferably, after unmolding these blanks 7, they can be cut (roughly) into semi-finished products (step 8, FIG. 1). following said "less complex" form than that of the finished products which will be finally machined.

In particular, if the shape of the demolded blank or that of the finished product requires it, for example to obtain a favorable plane of symmetry, the demolded blank can be cut into a shape that does not require dimensional control before this it is machined according to the expected end product; see the final step 14 of dimensional control after machining, Figure 1.

Meanwhile, each semi-finished product 7 will have been heat treated, without hot isostatic compression (CIC), in order to obtain an alloy microstructure comprising gamma grains and / or lamellar grains (alpha2 / gamma).

FIGS. 10, 11 show microstructures of TiAl 48-2-2: 48% Al 2% Cr 2% Nb (at%) obtained respectively with and without hot isostatic compaction (CIC), for the same thermal history.

In FIG. 12, for each test (numbered 1 to 9 on the abscissa), the difference between the result concerned obtained for a test piece (a cylinder) heat treated with hot isostatic compaction (solid diamonds) then a another, identical, treated without hot isostatic compaction (hollow diamonds) which is each time to be considered.

We thus find, from top to bottom on the graph:

- (in ordinates) between 0.8 and 1, the results of tensile tests (Maximum stress Rm),

between 0.58 and 0.8, the results of 0.2% plasticity yield stress tests (Rp0.2),

between 0.158 and 0.55, the results of elongation rupture tests (A%).

It has been found that the tests 1, in Rm, and 4, in A%, show an almost exact concordance (superposition) of the results with hot isostatic compaction (solid diamonds) and without (hollow diamonds). The other results are close, two by two. And when they exist, the dispersions are weak. All these tests were conducted at room temperature, after heat treatments, again with a test piece (a cylinder) in TiAI 48-2-2.

To achieve the results of FIGS. 11, 12, without hot isostatic compaction, the tests have shown that, when the semi-finished product was thermally treated, this should favorably take place for 10 to 40 hours, at a substantially equal pressure. at atmospheric pressure or, at least, significantly lower than the CIC pressure (800 - 1800x10 ^s Pa).

An intermediate pressure between the atmospheric pressure and this CIC pressure range applied to the alloy would not be detrimental. It just does not appear indispensable. The test results provided are the consequence of the application of atmospheric pressure.

In terms of times and temperatures, the results of FIGS. 11 and 12 are illustrations of what has been obtained indistinctly by testing the limit values mentioned below.

The comparative case of FIG. 10 was obtained under the following conditions (see US 5609698): first treatment, called PLL treatment, comprising a pre-HIP treatment of 1145 ° C. for 5 hours, HIP at 1255 ° C., and heat treatment at 1200 ° C for 2 hours.

In fact, FIGS. 11 and 12 show the effectiveness of the solution proposed here for treating the semifinished product still to be machined, brought successively:

at a temperature of between 1045 ° C. and 1145 ° C., for 5 to 15 hours, at a pressure substantially equal to atmospheric pressure,

at a temperature of between 1135 ° C. and 1235 ° C., for 3 to 10 hours, at a pressure substantially equal to atmospheric pressure, and then

at a temperature of between 1155 ° C. and 1255 ° C., for 2 to 15 hours, at a pressure substantially equal to atmospheric pressure at atmospheric pressure.

The alloy used may in particular be TiAl 48-2-2: 48% Al; 2% Cr; 2% Nb (at%), especially as this intermetallic material proves useful for achieving at least partly certain stages of a turbomachine turbine In aircraft, the invention is more generally applicable in particular to the titanium aluminide alloys mentioned below having a composition capable of forming alpha2 and gamma phases, when the alloy is cooled from a melt. It should be noted that these alloys are here, as generally in the prior art, called "gamma", even if they are not entirely within the gamma phase field, it being specified that gamma titanium aluminides are typically titanium alloys, about 40 to 50 atomic percent (at%) of aluminum, with possibly small amounts of other alloying elements such as chromium, niobium, vanadium, tantalum, manganese and / or boron.

Preferred compositions are from about 45.0 to about 48.5 atomic percent of aluminum, and are therefore at the upper end of the operating range.

Among the preferred and usable gamma titanium aluminides, mention will be made of: Ti-48Al-2 Cr -2nb, Ti-48Al-2Mn-2Nb, Ti-49Al-1 V, ΤΊ-47ΑΙ-1 Mn-2Nb-0.5W-0.5Mo -0.2 Si, and ΤΊ-47ΑΙ-5Nb-1 W. If the manufacturing conditions (in particular the heat treatment) applied to these specific alloys correspond to the aforementioned case of TiAl 48-2-2, in conjunction with FIGS. 12, the results provided in Figure 12 are applicable to them. The importance of such a heat treatment without hot isostatic compression (CIC) is therefore understood, at a pressure lower than that of a CIC, preferably substantially equal to atmospheric pressure, and this for 10 to 40 hours and between 1045 ° C and 1255 ° C. The conditions of flow velocity of the alloy in the mold and of simple shape of this mold are also important and are those used for tests whose results are comparable to those of FIGS. 11-12.

Claims

1. A process for treating a titanium aluminide alloy, the method comprising the steps of: performing a permanent mold centrifugal casting (25) to obtain a semi-finished product, and then heat treating the semi-finished product at a pressure lower than that of a hot isostatic pressing (CIC), preferably substantially equal to atmospheric pressure, to obtain a microstructure of the alloy comprising gamma grains and / or lamellar grains (alpha2 / gamma ).

2. A method of manufacturing, without hot isostatic compression, of a titanium aluminide based alloy turbine engine part comprising the following steps:

- performing a permanent mold casting mold (25) to obtain a semifinished product of less complex shape than that of the finished product (9,17),

heat-treating, without hot isostatic pressing, the semi-finished product, at a pressure lower than that of hot isostatic pressing (CIC), preferably substantially equal to atmospheric pressure, until a microstructure of alloy comprising gamma grains and / or lamellar grains (alpha2 / gamma),

- Then machining to the shape of said part the semi-finished product (9,17) heat treated.

A process according to claim 1 or 2, wherein the step of obtaining the semi-finished product from the spin casting comprises casting into said permanent mold (25) that the alloy fills in such a way that the size of the internal pores of this alloy is reduced after casting compared to what it was before, the mold being filled by the alloy:

with a speed of flow of the alloy in the mold greater than the rate of solidification of the alloy in the mold, and / or

in less than one minute, preferably 30 seconds, and more preferably 20 seconds.

4. Method according to one of the preceding claims, wherein said alloy is a titanium alloy, with 40 to 50 atomic percent (at%) of aluminum, such as preferably one of the following alloys: Ti-48AL- 2Cr-2Nb, Ti-48AL-2Mn-2Nb, Ti-49AI-1V, Ti-47A1 -1min-2Nb-0.5W-0.5Mo-0.2Si, and ΤΊ-47ΑΙ-5nb-1W, and said treatment Thermal of the semi-finished product takes place for 10 to 40 hours.

5. Method according to one of the preceding claims, wherein said alloy is TiAI 48-2-2: 48% AI 2% Cr 2% Nb (at%).

6. Method according to one of the preceding claims, wherein the step of obtaining a semi-finished product (7) from molding comprises:

said molding by centrifugal casting of the alloy, in a metal mold, or,

said casting by centrifugal casting in a metal mold, followed by cutting into portions of said molded alloy,

following a blank (7) having at least one plane of symmetry (39).

7. Method according to one of the preceding claims, wherein, the step of obtaining a semifinished product resulting from molding, which has an axis and, along this axis, a variable outer section, comprises:

said molding by centrifugal casting of the alloy, in a metal mold, or,

following a blank (7) having at most an inflection through which the section of the semi-finished blank increases or decreases, with along said axis:

section maximums (S2, S3) of the blank situated at the ends thereof, or

- a maximum section (S1) of the blank located at one end.

8. The method of claim 2 alone or in combination with any one of claims 3 to 7, wherein the raw product (7) raw molding is heat-treated and is machined directly without intermediate dimensional control.

9. The method of claim 2 alone or in combination with any one of claims 3 to 8, wherein the step of obtaining the semifinished product (7) from molding comprises:

- From a cast of said alloy, melted, develop a first ingot, in this material,

- remelt the first ingot in a cooled metal crucible (23) and pour into a centrifuged permanent metal mold (25) the first remelted ingot, to obtain a molded remelted ingot,

demolding the molded remelted ingot and cutting it into a semi-finished product, according to said less complex form.

The method of claim 9, wherein:

the first ingot is produced by VAR (Vacuum Arc Remelting) or by PAM (Plasma Arc Melting) by plasma arc;

- remelt the first ingot is operated by VAR SM (Skull Melter-cold melting crucible).

11. Method according to one of the preceding claims, wherein the semi-finished product is thermally treated by successively bearing it:

at a temperature of between 1045 ° C. and 1145 ° C., for 5 to 15 hours, at a pressure lower than that of a hot isostatic pressing, preferably substantially equal to atmospheric pressure,

at a temperature of between 1135 ° C. and 1235 ° C., for 3 to 10 hours, at a pressure lower than that of a hot isostatic pressing, preferably substantially equal to atmospheric pressure, and then

12. The method of claim 1 or one of claims 3 to 11 when appended to claim 1, wherein the treatment of the alloy is carried out without hot isostatic compression.

13. The method of claim 2 or one of claims 3 to 11 when appended to claim 2, wherein the machined part is an aircraft turbine blade.

The method of claim 1 or one of claims 3 to 11 when appended to claim 1, wherein the alloy is for an aircraft turbine blade.