Patent Grant
11174033
This application is a national stage of International Application No. PCT/FR2016/053189, filed on Dec. 2, 2016, which claims the benefit of French Patent Application No. 1561726, filed on Dec. 2, 2015, the contents of each of which are incorporated herein by reference.
The present invention relates to the field of thermal management.
It especially relates to an insulating part under a controlled atmosphere (in particular a vacuum insulated panel or VIP) and its manufacturing process.
Patent publications (such as U.S. Pat. No. 9,157,230) have already addressed these topics.
However, a problem remains in connection with the strength of the part over time, in other words its reliability and efficiency in terms of thermal management of the environment in which it is placed, and this even the more so if the environment is subject to strict standards, such as in the aerospace sector in which components in a vacuum are very rarely recommended, given the inherent risk of leakage and thus of loss of vacuum and of functionality.
Without specifically mentioning the areas of critical applications, U.S. Pat. No. 9,157,230 proposes a VIP part intended to reduce the leakage of heat with respect to a structure opposite which the part will be installed.
However, the described manufacturing process demands a restrictive implementation that is not justified in the eyes of the inventors in that it does not make it possible, in their opinion, to sufficiently guarantee a decadal or multi-decadal longevity of the parts under satisfactory operational conditions.
One aspect of the invention aims to address this problem and prejudice, which becomes critical when a flawed thermal management quality is not acceptable for many years, in a harsh environment: significant thermal stresses around an engine, risks of chemical or even mechanical aggression during maintenance, successive cycles of applied thermal stresses, in a vibratory environment and with pressure variations (in the case of aeronautical applications in particular).
Moreover, after analysis, it turns out that it is not the fineness of the metal sheet(s) that is involved, nor the fact that they are directly and continuously sealed together, or even the aforementioned thermal conductivity.
In fact, it has been found that the aforementioned flawed thermal management quality could be reduced if the welding conditions were reviewed and the leakage rate controlled in this area.
Consequently, what is proposed here is that a continuous weld of the enclosure, produced under a vacuum and/or under a controlled atmosphere, is such that it has a leakage rate of less than 10−6 Pa·m3/s after a first thermal treatment according to RTCA-DO 160-G, section 5, Cat A (from −55° C. to 400° C.) and a second thermal treatment at −196° C. for 1 hour, where the thickness of the metal sheet(s) may only be less than 1 mm, without any limitation as to its (their) thermal conductivity, where the overall thermal conductivity of the part must be less than 100 mW/m.K at 20° C. and in an environment under atmospheric pressure, over the range of possible temperatures at which the part may be used, i.e. at least from −200° C. to 600° C., or even −269° C. to 1,100° C.
The aforementioned thickness of 1 mm, in particular with materials as those mentioned below, will allow for the overall thermal conductivities of the part and the intrinsic thermal conductivity of this (these) metal sheet(s) to be merged, because the thermal diffusion and heat losses will then be low.
In the present application:
In terms of process, the solution becomes a method for manufacturing an insulating part, comprising steps in which:
It can be noted from the above that the maximum temperature of the test has been reduced to 400° C. from the 550° C., in relation to RTCA-DO 160-G, section 5, Cat A.
Moreover, the leakage rates at the location of the weld must favorably be identical (to within 20%) before the test is applied according to the standard and after.
To promote the effectiveness of the insulation, or even mechanical strength, it is proposed that, prior to the step of establishing the low pressure, an inorganic or organic core material is enclosed between the two metal sheets or two portions of said metal sheet. The depressurization of the welding chamber for welding and in particular of the inner enclosure to limit thermal conductivity will thus also be operative, which would not have been the case with a mineral core material.
And, to put the welding step into practice, one among seam welding, electron beam welding, diffusion welding, induction welding and micro-plasma welding will preferably be used, in all cases in a said welding chamber under a controlled atmosphere, as mentioned above.
Furthermore, it has been noted that by using (at least) one corrugated thin metal sheet to produce the closed casing, a material deformation reserve will be available that is particularly useful for the fold areas or for absorbing at least part of the deformations of the casing walls due, among others, to thermal stresses. The overall rigidity will also be improved for the thinnest sheets.
In fact, the term “corrugated thin metal sheet” should be understood as a sheet having at least one material reserve area that is useful for:
Thus, an alternative to actual corrugating, as shown in
Another problem that the invention has taken into account relates to identifying any loss of insulation on the part, if it occurs.
As a relevant solution, it is proposed that said insulating part, having all or some of the aforementioned characteristics, be associated with a sensor to be installed externally on the side of a second face of the part opposite to a first face, where the structure to be thermally protected is located, the sensor being suitable for providing visual, acoustic, mechanical, electrical, or magnetic information.
An advantage of the insulating part, which has been found subsequently, if it is in a low pressure, is that it can not only provide a thermal insulation effect but also an effect that limits the transmission of certain frequencies, with a potential effect on certain vibrations and/or on acoustics.
One consequence of this is the proven ability to install said insulating part in either of the following:
In both cases, this is a major development given the existing prejudices that excluded VIP parts from the aeronautical or aerospace field, particularly near the engines of flying machines and, more specifically, dual flow turboshaft engines.
Another application in the field of cryogenics provides for the use of at least one said thermally insulating part, under an atmosphere of controlled pressure and/or composition, on a heat exchanger or a storage tank respectively subjected to the following:
If necessary, the invention will be better understood and other characteristics, details and advantages thereof will become apparent upon reading the following description as a non-exhaustive example with reference to the appended drawings in which:
One aim of the present invention thus is to create a part under a controlled atmosphere (controlled pressure and/or composition) that is hermetically welded, puncture-resistant, inexpensive, has an actual longevity of several years (10 years and more are aimed for, or more than 50,000 duty cycles), is of arbitrary size and shape, and has a high thermal resistance R and thus a strong ability to reduce heat transfers in the location where it is installed.
One embodiment depicted in
This controlled atmosphere may consist in the presence of a gas having a thermal conductivity of less than 26 mW/m.K (stagnant air).
Additionally or alternatively, the controlled atmosphere may consist in a pressure lower than atmospheric pressure.
Although the enclosure 7 may contain no structural element intended for insulation or as a thermal barrier, in this case it preferably contains a thermal insulation, as shown in
In the embodiment shown in
Among fibrous insulation materials, those which are minerals are defined in standard NF B 20-001. Mineral fibrous insulation materials are grouped into two major families: volcanic rock wool or slag wool and glass wool.
In the embodiment as shown schematically in
This material provides structure to the part 1, i.e. it contributes to the mechanical strength of the part. In this embodiment, it is a monolith.
A core material 5 comprising an aerogel will be considered favorably, taking into account its advantages in terms of thermal conductivity, density, mechanical strength, ability to be molded into complex shapes.
In the illustrated versions, the casing 3 comprises two metal sheets 30, 31. The term “metal” covers alloys. The two sheets will in principle be identical, except for their size. Alternatively, one could use only one metal sheet, folded on itself, so as to only need to weld on three sides if the part has four sides, as shown in
If it is provided, the core material 5 (or the screen 50 presented hereinafter) will of course be interposed between the sheets 30, 31. In an alternative, as shown in
The controlled atmosphere in the enclosure 7 is a major parameter of the part 1, because it enables it to perform the function of super thermal insulation, if the core material 5 is a thermal insulation, and preferably a micro- or nanoporous insulation, in principle combined with a low pressure (with respect to the surrounding atmospheric pressure) in the enclosure 7.
In fact, combining a high-performance casing 3 with a controlled atmosphere and, in particular, a low pressure atmosphere, in the enclosure 7 will make it possible to obtain a VIP with a long service life, which, more specifically, can be installed in the nacelle 15, at the location of the internal structure 17 (also called inner fixed structure or IFS) that surrounds the upstream portion of the turbojet engine 13, as shown schematically in
Another very relevant possibility, as shown schematically in
In the first case (as shown in
A top end 35 of the nacelle receives a fastening pylon (which may be the structure 9 below) to fasten the nacelle 15 to a wing of the aircraft (not shown in
The parts 1 are arranged in the internal structure 17 (IFS), each part advantageously having a curved shape, in particular an rounded shape. An individual shape, generally in the form of ring sectors, will be suitable. The assembly then defines an annular shape, having end to end sectors along the circumference.
In the second case (as shown in
The engine assembly 40 intended to be fastened under the wing 11 (or hence on the side of a fuselage 110) here indeed comprises a fastening device 41 and the engine 13 fastened with it, below in the case of the wing. On the whole, the fastening device 41 comprises a rigid structure 9, carrying means for fastening the engine, these fastening means, to be fastened to the wing or to the fuselage, having a plurality of engine fasteners 45, 47, as well as a load transfer device 49. The rear aerodynamic fairing 51 of the engine fastening device is located under the rigid structure 43 in this case, the fairing is therefore interposed between the wings and the concerned engine 13. The fairing 51 may comprise two lateral parts 53, around which the secondary flow 55 of the engine is intended to curve.
In particular, in the two preceding applications, and more generally when safety requires it, sensors 56 may be arranged externally on the side of a second face 10b (less hot) of the insulating part(s) 1 opposite to a first face 10a on which the source or the structure to insulate is located (in this case, part of the engine's hot body). Each sensor can be active or passive and may provide visual, mechanical or electrical information. Stress, temperature, impedance and acoustic sensors are particularly suitable. Thus, using an indirect parameter sensed on or in the close proximity of the parts 1 and transmitted to a computer 58 and then to a display or warning device 60, it will be possible to provide information about the state of preservation of these parts and, specifically, about the preservation of the vacuum within.
It should also be noted that, in addition to a thermal protection, given the low pressure existing in the enclosure 7 and due to the limitation of the transmission of certain frequencies, the above two solutions are expected to provide a potential acoustic effect in the IFS application (first case) and a potential effect on some vibrations in the application with a primary fastening pylon structure (second case).
Two other applications are shown schematically in
In both cases, all or part of the walls of the heat exchanger or of the tank are made in the same way as the part 1. An internal useful volume 65 of the heat exchanger 60 or of the tank 61 thus is thermally insulated from the external environment (EXT).
The temperature in the internal useful volume 65 must range from −150° C. to −273° C. and the temperature difference between the volume 65 and this external environment (EXT; 67) must be greater than 100° C.
The volume 65 of the tank 61 can be closed by an openable or removable cover 67, also formed in the same way as a part 1.
In the heat exchanger 60, fluid inlets 69a, 69b and outlets 70a, 70b enable the circulation of at least two fluids to be placed in heat exchange relationship inside the heat exchanger 60 that the parts 1 protect thermally along its periphery. If the fluid inlets and outlets must pass through at least one part 1, a seal around each passage will be provided, typically by a continuous weld bead 6.
In both cases, all or part of the protective walls of the heat exchanger or of the tank are made in the same way as the part 1. An internal useful volume 65 of the heat exchanger 60 or of the tank 61 thus is thermally insulated from the external environment (EXT).
The temperature in the internal useful volume 65 must range from −150° C. to −273° C. and the temperature difference between the volume 65 and this external environment (EXT; 67) must be greater than 100° C.
The volume 65 of the tank 61 can be closed by an openable or removable cover 67, also formed in the same way as a part 1.
Whatever the application, it is the controlled atmosphere that prevails in each part 1 that will eliminate (reduce) the gaseous component of the thermal conductivity. However, at high temperature, as in the two applications above, the radiative component can have a great influence. This component can be absorbed by the opacity of the material. This absorption directly depends on the Rosseland mean extinction coefficient A of the material (see table below), when it comprises at least one porous insulating block:
In applications where the temperature substantially reaches or exceeds 200° C., or even 700° C., if not more in the second case, the interest in the blocks of core material 5 having a Rosseland mean extinction coefficient A greater than or equal to 30 should be noted. This is the case of a silica gel, or of the pyrolysed carbonaceous composition presented in FR-A-2996850 and whose evolution λ=f (P) is shown in
With such blocks or monoliths, it will be possible to form a thermal insulation 5 with a mechanically structuring effect (the polyurethane being an alternative, although significantly less thermally efficient). However, one advantage of the pyrolysate of the composition presented in FR-A-2996850 is that it is not flammable.
Alternatively, or in addition, a thermo-reflective screen 50 may be contained in the enclosure 7, as shown in
Thus, one may consider protections whose insulating function will be provided by a fairly high vacuum (typically less than 10−1 Pa) in combination with thermo-reflective films 500. These will advantageously be strips whose thermal wave reflection coefficient, a wavelength ranging from 0.1 μm to 100 μm, is high enough to stop the heat emitted by radiation by reflecting it. A relevant solution will comprise metal strips forming a casing with an internal pressure <103 Pa and one or several thermo-reflective films with a total thickness of less than 100 cm. Each film must have a very low emissivity: ideally <0.1. Another solution with a succession of layers of aluminised mylar™ film and of insulating felt is also possible.
Regardless of the nature of the element 5, and even if, for example, a CO2 atmosphere in the enclosure 7 may be suitable in some cases that are less demanding in terms of thermal insulation, it is considered that it is still the pressure in the enclosure which will enable the parts 1 to achieve a really low thermal conductivity. In practice, the pressure in the enclosure 7 will thus favorably range from 0.00001 mbar to less than 1,000 mbar (1,000 mbar=105 Pa), at the beginning of service life (within one year or the months following manufacture). Furthermore, with an internal pressure of 1 Pa, sheets and a core material 5 according to FR-A-2996850 with a thickness of 10 mm, a leakage rate as mentioned above (typically 10−10 Pa·m3/s), the part 1 must guarantee an internal pressure of no more than 103 Pa (10 mbar) after at least 50,000 temperature cycles in accordance with RTCA-DO 160-G, section 5, Cat A (from −55° C. to 400° C.), with identical leakage rates (within 20%) before the test is applied according to the standard and after.
In this respect, it can be inferred from
A low pressure in the casing 3 will generate a pressure difference, which can reach 105 Pa, between the external environment and the enclosure 7. The casing 3 cannot absorb this constraint alone if its thickness is less than 1 mm. Therefore, it is then the core material (structure 5) that will be subjected to compression. Reinforcements in this material may further assist in supporting the casing 3. These reinforcements may be shims or special structures such as honeycombs. However, no spacer, other than an organic or inorganic core material 5, may be considered in the enclosure 7, as it could/would create a thermal bridge between the two sheets 30, 31.
If the at least one of the sheets 30, 31 is made of corrugated metal (for example, achieved using embossed rollers), thus with domes 57 as shown schematically in
One or more getters (or gas traps) intended to prevent oxidation of the core material and to settle the gases that enter the enclosure 7 through the junction 6 or that are emitted by the core 5 during its life cycle may be provided. Each getter will allow for the pressure increase to be limited and moisture to be captured, hence an impact on conductivity.
Be that as it may, the part 1 will have a temperature range of −200° C. to 600° C., a thermal conductivity ranging from 1 mW/m.K to 300 W/m.K, and favorably less than 26 mW/m.K (air) at 20° C. and in an environment under atmospheric pressure.
And according to a characteristic that is essential for the strength of the part over time, as already mentioned, the continuous weld 6 of the metal sheet(s) of the casing, produced under a controlled atmosphere, must have a leakage rate of less than 10−6 Pa·m3/s, and less than 10−9 Pa·m3/s for sheet 30, 31 thicknesses greater than 70 μm, after a first thermal treatment according to standard RTCA-DO 160-G, section 5, Cat A (from −55° C. to 400° C.) and a second thermal treatment at −196° C. for 1 hour. This will at least make it possible to rule out the possibility that the sheet(s) 30, 31 are lined with plastic, for example, and that there is no direct metal/metal welding, each sheet effectively and in principle forming both the internal and external limit of the casing 3.
The internal pressure of the enclosure 7 can thus be maintained for periods of the order of 10 years and slightly more.
The leakage rate is expressed according to the following formula:
Δpadmissible is the difference, in Pa, between the admissible end-of-life pressure in the part and the admissible pressure at the beginning of its life;
The Volume under vacuum is the volume of the enclosure 7, in m3;
The Service life is expressed in s.
For example, for a protection consisting of an enclosure 7 with a volume of 1 L under vacuum, a service life of 3 years corresponds to a leakage rate of 10−8 Pa·m3/s. A table referencing the leakage rates and lifetimes to protect a volume of one litre and for an end-of-life pressure difference of 10 mbar is provided below.
Leakage rates will be measured according to the following standards:
A helium test may be required if the leakage rate to be measured is less than 10−4 Pa·m3/s. Above this figure, an air under water test can be used.
An important aspect will therefore be related to the type of weld 6 made.
Thanks to a gas evacuation system 61, the residing pressure is less than 105 Pa, preferably between 10−6 Pa and 102 Pa, and more preferably less than 100 Pa. And it is thus in this chamber 59 that a welding machine 63 has been previously placed. Once the suitable low pressure has been achieved in the volume 65′, this machine will thus perform the welding at the area 6, along a single continuous line, where the sheets or portions concerned will have preferably been clamped together.
Alternatively, or in, addition, the system 61 could be used to substitute air for CO2 in the volume 65 of the chamber 59.
It is also possible that only part of the continuous weld 6 is made in the chamber 59. It is therefore possible to continuously weld outside the chamber 59 three of the four sides in the solution shown in
Even if other types of welding under a controlled atmosphere may be provided, this seal will favorably include one among seam welding, electron beam welding, diffusion welding, induction welding or micro-plasma welding thus performed using the suitable machine 63.
Thus, if an organic or inorganic core material 5 is provided, when the time comes the following will be sufficient:
To test the leakage rate of the weld 6, the part 1 will be subjected to a first thermal treatment according to the standard RTCA-DO 160-G, section 5, Cat A (from −55° C. to 400° C.) and to a second thermal treatment at −196° C. for 1 hour. In practice, the leakage rates at the location of the weld must favorably be identical (to within 20%) before the test is applied according to the standard and after.
The lower the thickness of the metal at the location of the weld 6 to be achieved (typically less than 0.5 mm) is, the more the expected leakage rate will be difficult to achieve.
For an application (such as in aeronautics) where weight is a critical parameter, if the thickness of the sheet(s) 30, 31 is less than 0.5 mm per sheet (e.g. for 304 L grade stainless steel sheets, about 0.08 mm thick), it is advisable that around the entire periphery of the weld 6 the sheets or the portions concerned are folded on themselves, in the form of a double fold, reference 67 on
Three other parameters have been noted as being able to influence the expected performance of the part 1 over time. We recommend the following:
More specifically:
Regarding elongation at break: Bronze, with an elongation of 50%, and zinc, with an elongation of 80%, count among the most ductile metals. Furthermore, zinc and aluminum are not suitable for withstanding temperatures above 200° C., while temperatures in an IFS application, for example, can reach about 700° C. and even higher. As for ceramics, they have elongations of about 0.0001%. However, a material with an elongation of less than 5% is not formable (even when hot forming). It may thus be difficult, for some applications, to make a high-performance part 1, if the elongation at break is not contained between 5% and 50% (at room temperature).
Elongation may be measured using a tensile test according to “EN ISO 6892-1: Metallic materials—Tensile testing—Part 1: Method of test at room temperature ”
Regarding mechanical strength (Rm): The mechanical strength of metals typically range from 4 Mpa to 3000 Mpa. If we exclude gold and lead, which are not in common use, the lower Rm value can be set to 20 Mpa. Mechanical strength is measurable using a tensile or hardness test. For a tensile test, refer to the standard above. For a hardness test, see below.
Regarding hardness: The casing 3 is defined as a container that has the following hardness properties at its junction 6, after a test according to the standard RTCA-DO 160-G, section 5, Cat A (from −55° C. to 400° C.).
The hardness test can measure a Vickers hardness according to the following standards:
EN ISO 6507-1—Vickers hardness test—Test method
EN ISO 6507-2—Vickers hardness test—Verification and calibration of testing machines
EN ISO 6507-3—Vickers hardness test—Calibration of reference blocks
Tests performed on tested parts 1 indicate a hardness of 200 HV (660 N/mm2). However, when referring to the boundaries of the mechanical strength value range of steel alloys and titanium, the hardness should favorably range from 90 HV (310 N/mm2) to 670 HV (approx. 2,350 N/mm2). Aluminum and zinc have lower hardnesses.
| Number | Date | Country | Kind |
|---|---|---|---|
| 1561726 | Dec 2015 | FR | national |
| Filing Document | Filing Date | Country | Kind |
|---|---|---|---|
| PCT/FR2016/053189 | 12/2/2016 | WO | 00 |
| Publishing Document | Publishing Date | Country | Kind |
|---|---|---|---|
| WO2017/093692 | 6/8/2017 | WO | A |
| Number | Name | Date | Kind |
|---|---|---|---|
| 9157230 | Feinerman et al. | Oct 2015 | B2 |
| 9243726 | Reid | Jan 2016 | B2 |
| 9644781 | Thiery | May 2017 | B2 |
| 10697698 | Dherde | Jun 2020 | B2 |
| Number | Date | Country |
|---|---|---|
| 10 2011 002 248 | Oct 2011 | DE |
| 2 345 770 | Jul 2011 | EP |
| 2 829 689 | Jan 2015 | EP |
| 2 996 850 | Apr 2014 | FR |
| 2006-275186 | Oct 2006 | JP |
| 2014-163494 | Sep 2014 | JP |
| WO 2015121540 | Aug 2015 | WO |
| Number | Date | Country | |
|---|---|---|---|
| 20200283161 A1 | Sep 2020 | US |
