Patent Application
20230046116
The present invention relates to the manufacture of blades made from titanium aluminide alloy for a low-pressure turbine of a turbomachine for an aircraft.
In particular, it proposes a method for the heat treatment of bars made from titanium aluminide alloy for blades of a low-pressure turbine of a turbomachine.
An axial flow turbofan engine is shown schematically in
The fan 1 and the low-pressure compressor 3 are linked to the low-pressure turbine 7 by a first transmission shaft 9, whereas the high-pressure compressor 4 and the high-pressure turbine 6 are linked by a second transmission shaft 10.
During operation, a flow of air compressed by the low- and high-pressure compressors 3 and 4 feeds combustion in the combustion chamber 5. The turbines 6, 7 recover kinetic energy from the expansion of the combustion gases before releasing it to the compressors 3, 4 and to the fan 2 via the transmission shafts 9,10.
During operation, the blades of a low-pressure turbine are used at very high temperatures and are subjected to major mechanical and thermal stress.
In some engines, the blades of a low-pressure turbine are now made from titanium aluminide (TiAl).
Indeed, TiAl, an alloy of titanium and aluminum, is an extremely high-performance material. In particular, it has excellent mechanical properties at very high temperatures (T>650° C.); its density allows the weight of a blade to be reduced by at least half compared to the nickel alloys traditionally used in low-pressure turbines.
In particular, a titanium alloy commonly used for the blades of a low-pressure turbine of a turbomachine is TiAl 48-2-2, of formula Ti48Al48Cr2Nb2 (in at %). Other alloys of composition Ti45-52—Al45-48—X1-3—Y2-5—Z21 1, in which X═Cr, Mn, V; Y═Nb, Ta, W, Mo; Z═Si, B, C or other accidental impurities, may also be considered.
The phase diagram of a TiAl alloy (Ti (left) and Al (right)) is shown in
liquid region L;
primary α solid solution region of Al in Ti;
primary γ solid solution region of Ti in Al;
primary α2 solid solution region of Al in Ti;
primary β solid solution region;
As can be seen in
Therefore:
For general presentations on TiAl alloys in the context of aeronautical applications, reference can advantageously be made to the following publications:
One technique for manufacturing the blades of a low-pressure turbine consists in machining them from bars made from titanium aluminide.
The term “bar” should be understood here in a fairly broad sense. It denotes a generally cylindrical unfinished product. Once obtained, the bars are machined. Various heat treatments may also be applied before, during or after machining, in order to create the blades.
It is known that, in order to facilitate the machining of the bars, it is desirable for them to be free of pores.
Heat treatments for TiAl alloy in which hot isostatic pressing (HIP) is applied to the bars are already known.
Hot isostatic pressing consolidates the materials at temperatures lower than their melting temperature and closes the pores.
In order to obtain the desired microstructure, the hot isostatic pressing phase is combined with other heat treatment phases, which help generate γ grains, typically:
The alloys obtained at the end of these different phases are conventionally alloys with a duplex microstructure with, at best, 60/70% single-phase γ grains (60/70% of the volume), the remainder consisting of lamellar α+γ grains.
Such duplex alloys offer the advantage of having the desired mechanical properties at high temperatures, of being low-density and of having, when cold, the ductility/strength characteristics required in order to allow the blades to be fitted or removed.
However, the heat treatments with hot isostatic pressing that are currently known have the major drawback of being particularly costly.
In particular, the various heat treatment phases and the cooling operations between these phases impose particularly long cycle times (up to 11/12 hours).
Furthermore, the various operations that involve handling the bars, including moving them in and out of furnaces, result in aluminum losses which may not be insignificant.
Documents U.S. Pat. No. 5,609,608, US2013251537, EP2641984 and U.S. Pat. No. 5,350,466 propose various examples of heat treatment following isostatic pressing of Ti—Al alloys.
A general aim of the invention is to overcome the disadvantages of the prior art.
In particular, one aim of the invention is to propose a solution that makes it possible to obtain a TiAl alloy that has mechanical properties compatible with what is required of blades of a low-pressure turbine of a turbomachine, at both high temperatures (operating temperatures of the low-pressure turbine) and when cold (fitting, removal of the blade).
Yet another aim of the invention is to propose a solution resulting in bars that offer good machinability, while being optimal in terms of cost.
In particular, according to one aspect, a method is proposed that makes it possible to produce pore-free bars made from a titanium aluminide alloy with a microstructure as close as possible to 100% γ (almost 100% γ).
An almost 100% γ microstructure (also known as a “near y” microstructure) should be understood here and in the present text as a whole to mean a microstructure with at least 90% single-phase γ grains (90% of the volume or more) and therefore with less than 10% lamellar α+γ grains (10% of the volume or less).
The parts obtained in this way have optimal qualities in terms of machinability and mechanical properties both at high temperatures and when cold.
The proposed method also has the advantage of greatly reducing the cycle time: it is implemented in a single heat treatment operation, without intermediate cooling to room temperature between the steps of this treatment.
Therefore, the invention proposes a method for the heat treatment of at least one 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, characterized in that said hot isostatic pressing is followed, after a temperature transition phase, by a step of heat treatment of the bar at a temperature in the immediate vicinity of the eutectoid temperature of the alloy, said temperature being suitable for the formation of 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, said step being followed by a controlled cooling step.
It should be noted that none of documents U.S. Pat. No. 5,609,608, US2013251537, EP2641984 and U.S. Pat. No. 5,350,466 cited above focuses on “near gamma” configurations. None of them provides teaching relating to how such a configuration is obtained by means of heat treatment at a target temperature corresponding to the eutectoid temperature.
Moreover, none of these documents discloses controlled cooling.
Such a method is advantageously supplemented by the various following features, taken individually or, where technically possible, in combination:
The invention also proposes a bar made from titanium aluminide alloy for manufacturing at least one blade of a low-pressure turbine of a turbomachine, characterized in that it is obtained by means of a method as cited above and 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.
It further proposes a method for manufacturing at least one blade of a low-pressure turbine of a turbomachine, and a turbine blade obtained by means of such a method and having 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.
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:
The method for manufacturing blades for a low-pressure turbine of a turbomachine shown in
Production of the Bars (Step 11)
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
Such a bar is cylindrical or polyhedral.
For example, it has a length of between 20 and 50 cm and transverse dimensions ranging from 1 to 10 cm.
Different techniques may be used to produce such bars 14 (step 11).
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”).
Examples as to how these parts may be obtained are described, in particular, in application WO2014/057222 to which reference is made here.
The titanium aluminide alloy used to produce the ingots is typically an alloy of composition Ti45-52—Al45-48—X1-3—Y2-5—Z<1, in which: X═Cr, Mn, V; Y═Nb, Ta, W, Mo; Z═Si, B, C or other accidental impurities.
A preferred alloy is TiAl 48-2-2, although other titanium aluminide alloys are possible.
Heat Treatment of the Bars (Step 12)
The bars 14 obtained in this way are then subjected to the heat treatment shown in
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.
To this end, the bars 14 are installed in a sealed furnace equipped with means for implementing hot isostatic pressing.
HIP treatment: In a first step (step 121 from time t1 to time t2), hot isostatic pressing is implemented.
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.
During this HIP step, the internal pores of the bars 14 are closed.
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).
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).
The duration of this step is at most equal to 7 hours, and preferably at least 3 hours.
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.
Indeed, the eutectoid temperature varies depending on the amount of oxygen. At an oxygen level of 400 ppm, the temperature T1 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.
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.
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.
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.
It should be noted that the transition between steps 121 and 122 (from time t2 to time t3) is obtained by cooling, for example under an inert gas such as argon.
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 (t3-t2) may be optimized according to industrial constraints and does not produce any particular microstructural advantages.
Controlled cooling: Following step 122, the bars 14 are subjected to controlled cooling (step 123 between t4 and t5).
The cooling speed is between 2 and 56° C. per minute.
The temperature at the end of this cooling is between 580° C. and 620° C.
This controlled cooling causes the residual lamellar grains to set and makes it possible to obtain the desired mechanical properties.
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).
Such cooling may, for example, be carried out with a furnace equipped with URC (Uniform Rapid Cooling) technology.
The bars 14 are then cooled in a non-controlled manner (starting from t5) until they reach room temperature (t6). This step has no particular effect on the microstructure.
As can be seen, the proposed heat treatment allows a cycle time far shorter than with the heat treatments known from the prior art.
Therefore, the parts are no longer removed from the furnace and brought to room temperature between each step, greatly shortening the heat treatment time.
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.
Machining Treatment (Step 13)
Following the heat treatment, the bars 14 are subjected to machining with tools conventionally used for this purpose.
This machining makes it possible to obtain the blades 15 shown, by transparency, in the bar 14 in
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.
Once cut, the blades 15 may be further treated (thermally or otherwise) before being considered to be fully finished.
Also, other heat treatments may be carried out on the bars 14 before machining.
| Number | Date | Country | Kind |
|---|---|---|---|
| FR2000949 | Jan 2020 | FR | national |
| Filing Document | Filing Date | Country | Kind |
|---|---|---|---|
| PCT/FR2021/050174 | 1/29/2021 | WO |
