HOT ISOSTATIC PRESSING HEAT TREATMENT OF BARS MADE FROM TITANIUM ALUMINIDE ALLOY FOR LOW-PRESSURE TURBINE BLADES FOR A TURBOMACHINE

Abstract

Disclosed is a method for the heat treatment of at least one bar made from titanium aluminide alloy for manufacturing at least one low-pressure turbine blade for a turbomachine, comprising hot isostatic pressing of the bar, characterised in that the hot isostatic pressing (121) is followed, after a temperature transition phase, by a step of heat treatment (122) of the bar at a temperature in the immediate vicinity of the eutectoid temperature of the alloy, the temperature being suitable for the formation of an alloy microstructure with a volume fraction of at least 90% single-phase grains γ and a volume fraction of at most 10% of lamellar grains α+γ, the step being followed by a controlled cooling step (123).

Claims

1. A method for heat treating a bar made from titanium aluminide alloy for manufacturing at least one blade of a low-pressure turbine of a turbomachine, comprising: hot isostatic pressing of the bar, subsequent to hot isostatic pressing and after a temperature transition phase, heat treating the bar at a temperature in an immediate vicinity of a target temperature that is the eutectoid temperature of the titanium aluminide alloy and forming an alloy microstructure with a volume fraction of at least 90% single-phase γ grains and a volume fraction of at most 10% lamellar α+γ grains, and further comprising after heat treating the bar, cooling the bar in a controlled manner to a given temperature.

2. The method according to claim 1, wherein heat treating the bar is carried out at the target temperature of 1150° C.+/−20° C. for a time period of between 3 hours and 7 hours.

3. The heat treatment method according to claim 1, wherein the hot isostatic pressing is implemented at a temperature of between 1175° C. and 1195° C., at a pressure of at least 1300 bar, for a time period of between 3 hours and 5 hours.

4. The method according to claim 1, wherein the steps of hot isostatic pressing, heat treating the bar, and cooling the bar are implemented in the same furnace.

5. The method according to claim 1, further comprising adjusting the temperature in the immediate vicinity of the target temperature depending on an amount of oxygen in a furnace in which heat treating the bar is implemented.

6. The method according to claim 1, wherein a duration of the temperature transition phase is 60 minutes or less.

7. The method according to claim 1, wherein cooling the bar is carried out at a cooling rate of between 2 and 56° C./minute, to a temperature of between 580° C. and 620° C.

8. A bar made from titanium aluminide alloy for manufacturing at least one blade of a low-pressure turbine of a turbomachine, wherein the bar is obtained by the method according to claim 1 and has the alloy microstructure with the volume fraction of at least 90% single-phase γ grains and the volume fraction of at most 10% lamellar α+γ grains.

9. A method for manufacturing at least one blade of a low-pressure turbine of a turbomachine, comprising following steps: heat treating the bar according to the method of claim 1, and machining the bar to form a blade.

10. A blade of a low-pressure turbine of a turbomachine, wherein the blade is obtained by the method according to claim 9 and has the alloy microstructure with the volume fraction of at least 90% single-phase γ grains and a volume fraction of at most 10% lamellar α+γ grains.

Description

DESCRIPTION OF THE FIGURES

[0062] Other features, aims and advantages of the invention will become clearer from the description that follows, which is purely illustrative and non-limiting, and which should be read in reference to the appended drawings, in which:

[0063] FIG. 1, which has already been described, is a schematic representation of a turbomachine;

[0064] FIG. 2, which has already been described, is a phase diagram of a TiAl alloy;

[0065] FIG. 3 is a flowchart showing the main steps of a method for manufacturing blades made from titanium aluminide alloy for a low-pressure turbine of a turbomachine, according to one possible embodiment of the invention;

[0066] FIG. 4 is a schematic representation, in perspective view, of a bar from which at least two blades are intended to be machined;

[0067] FIG. 5 is a temperature/time diagram showing the different phases of the heat treatment step of the manufacturing method of FIG. 3.

DETAILED DESCRIPTION OF THE INVENTION

[0068] The method for manufacturing blades for a low-pressure turbine of a turbomachine shown in FIG. 3 implements, successively: [0069] the production of the bars (step 11), [0070] heat treatment of same (step 12), [0071] a machining treatment (step 13).

[0072] Production of the Bars (Step 11)

[0073] An example of a bar 14 (in this instance, one bar), from which at least two blades 15 are intended to be machined, is provided in FIG. 4.

[0074] Such a bar is cylindrical or polyhedral.

[0075] For example, it has a length of between 20 and 50 cm and transverse dimensions ranging from 1 to 10 cm.

[0076] Different techniques may be used to produce such bars 14 (step 11).

[0077] In particular, the bars 14 may be obtained by being cut from an ingot that is itself obtained either by molding (“lost-wax molding” or “centrifugal molding”, for example) or by fusion (“plasma arc fusion” or “vacuum arc fusion”).

[0078] Examples as to how these parts may be obtained are described, in particular, in application WO2014/057222 to which reference is made here.

[0079] The titanium aluminide alloy used to produce the ingots is typically an alloy of composition Ti.sub.45-52—Al.sub.45-48—X.sub.1-3—Y.sub.2-5—Z.sub.<1, in which: X═Cr, Mn, V; Y═Nb, Ta, W, Mo; Z═Si, B, C or other accidental impurities.

[0080] A preferred alloy is TiAl 48-2-2, although other titanium aluminide alloys are possible.

[0081] Heat Treatment of the Bars (Step 12)

[0082] The bars 14 obtained in this way are then subjected to the heat treatment shown in FIG. 5.

[0083] This treatment combines a step 121 of hot isostatic pressing (HIP treatment) and, following this step of HIP and after a temperature transition phase, heat treatment 122 for the creation and nucleation of γ grains, this heat treatment itself being followed by controlled cooling 123.

[0084] To this end, the bars 14 are installed in a sealed furnace equipped with means for implementing hot isostatic pressing.

[0085] HIP treatment: In a first step (step 121 from time t.sub.1 to time t.sub.2), hot isostatic pressing is implemented.

[0086] This treatment is, for example, implemented at a temperature of between 1175° C. and 1195° C. (temperature of the furnace) and at a pressure of at least 1300 bar, for a time period of between 3 hours and 5 hours.

[0087] During this HIP step, the internal pores of the bars 14 are closed.

[0088] Heat treatment for the creation and nucleation of the γ grains: step 121 is followed by a step of heat treatment at a temperature T1 that allows the creation and nucleation of the γ grains (step 122 from time t3 to time t4).

[0089] Temperature T1 is in the vicinity of the eutectoid temperature. More specifically, the target temperature is 1150° C. (+/−20° C., i.e., a temperature of between 1130° C. and 1170° C., preferably +/−10° C., i.e., a temperature of between 1140° C. and 1160° C.). In the present text as a whole, the indicated temperatures refer to the temperatures at the core of the material (obtained by means of sensors and thermocouples).

[0090] The duration of this step is at most equal to 7 hours, and preferably at least 3 hours.

[0091] It is adjusted depending on the amount of oxygen in the furnace in order to allow the creation and nucleation of the γ grains, in order to form the almost 100% γ microstructure.

[0092] Indeed, the eutectoid temperature varies depending on the amount of oxygen. At an oxygen level of 400 ppm, the temperature T.sub.1 is 1150° C., and it drops to 1100° C. when the oxygen increases to 1000 ppm. The relationship between the amount of oxygen and the eutectoid temperature is almost linear.

[0093] In the context of the proposed heat treatment, the treatment temperature of the material is always 1150° C. (+/−20° C., preferably +/−10° C.). The oxygen level is adjusted empirically.

[0094] During this step 122, the pressure in the furnace may be kept at at least 1300 bar, which then allows the duration of the HIP step 121 to be reduced.

[0095] As a variant, the alloy may be placed under vacuum in order to prevent possible parasitic chemical reactions between the alloy and residual atmospheric gases.

[0096] It should be noted that the transition between steps 121 and 122 (from time t.sub.2 to time t.sub.3) is obtained by cooling, for example under an inert gas such as argon.

[0097] The duration of this cooling is less than 60 minutes and is preferably less than 40 minutes, or indeed than 20 minutes. This cooling duration (t.sub.3-t.sub.2) may be optimized according to industrial constraints and does not produce any particular microstructural advantages.

[0098] Controlled cooling: Following step 122, the bars 14 are subjected to controlled cooling (step 123 between t.sub.4 and t.sub.5).

[0099] The cooling speed is between 2 and 56° C. per minute.

[0100] The temperature at the end of this cooling is between 580° C. and 620° C.

[0101] This controlled cooling causes the residual lamellar grains to set and makes it possible to obtain the desired mechanical properties.

[0102] It should be noted that excessively swift cooling would have an impact on the mechanical properties. In particular, it would be likely to produce precipitates within the single-phase γ grain and adversely affect the mechanical properties thereof when hot (during operation).

[0103] Such cooling may, for example, be carried out with a furnace equipped with URC (Uniform Rapid Cooling) technology.

[0104] The bars 14 are then cooled in a non-controlled manner (starting from t.sub.5) until they reach room temperature (t.sub.6). This step has no particular effect on the microstructure.

[0105] As can be seen, the proposed heat treatment allows a cycle time far shorter than with the heat treatments known from the prior art.

[0106] Therefore, the parts are no longer removed from the furnace and brought to room temperature between each step, greatly shortening the heat treatment time.

[0107] Moreover, the proposed heat treatment makes it possible to obtain a “near γ” (90%) microstructure supplemented by lamellar structures or a 100% γ microstructure with the method according to the invention. A microstructure obtained in this way has optimal qualities in terms of machinability, production cost and mechanical properties at high temperature for the manufacture of blades of a low-pressure turbine.

[0108] Machining Treatment (Step 13)

[0109] Following the heat treatment, the bars 14 are subjected to machining with tools conventionally used for this purpose.

[0110] This machining makes it possible to obtain the blades 15 shown, by transparency, in the bar 14 in FIG. 4. The cutting is optimized in order to allow maximum use of the material.

[0111] Like the bar 14 from which it originates, the blade has an alloy microstructure with a volume fraction of at least 90% single-phase γ grains and a volume fraction of at most 10% lamellar α+γ grains.

[0112] Once cut, the blades 15 may be further treated (thermally or otherwise) before being considered to be fully finished.

[0113] Also, other heat treatments may be carried out on the bars 14 before machining.