• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to an assembly for a turbomachine (1), the assembly comprising: - a casing (20) extending along a longitudinal axis (X-X ') of the turbomachine (1), - a surface heat exchanger Apparatus (100) disposed on an inner periphery (22) of said housing (20) and comprising a plurality of cooling fins (110) extending radially inwardly and longitudinally, and - a central body (30) concentrically disposed therein part inside said housing (20), said housing (20) and the central body (30) defining between them an annular airway (Va) whose width (hVa) at the heat exchanger (100) ) is substantially constant, the assembly being characterized in that the distribution of the fins (110) is distributed over more than 180 ° of the internal periphery (22) of the casing (20) and in that the average height (hMOY) of the fins (110) is greater than 5% of the width (hVa) of the annular airway (Va) at the level of the heat exchanger (100).
    公开号:FR3047270A1
    申请号:FR1650753
    申请日:2016-01-29
    公开日:2017-08-04
    发明作者:Josselin David Florian Regnard；Laurent Louis Robert Baudoin；Helene Monique Orsi
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    The invention relates to the architecture of heat exchangers located on an outer fan casing of a turbomachine intended to equip an aircraft.
    More specifically, the invention relates to the acoustic treatment of air / oil surface exchangers SACOC type ("surface air cooler oil cooied", see Figure 1), typically arranged between a blower and straightening vanes 40 ("OGV, outlet guides varies "), which make it possible to straighten the flow at the outlet of the fan.
    These exchangers comprise a plurality of fins disposed in the secondary flow of a turbomachine which is thus used to cool the turbomachine.
    STATE OF THE ART
    The development of turbomachinery, as the reduction of the length of the nacelles, leaves less and less room for the positioning of the acoustic treatments, while the constraints of reduction of the noise keep increasing.
    Therefore, the solutions of having the sound absorption elements downstream of the exchanger are not necessarily preferred. Other solutions have sought to reconcile heat dissipation and noise reduction by modifying the exchangers to optimize the volume occupied. As such, the documents US 2011/0303398 and US 2011/0126544 have an acoustic layer juxtaposed to the exchanger, the layer being typically honeycomb-shaped with outgoing pipes using the Helmholz resonance effect.
    US 2010/0155016 meanwhile uses specific materials at the exchanger to reduce sound diffusion.
    Finally, document US 2009/317238 proposes to use the fins of the exchanger to reduce the noise emitted by the turbomachine, either by using particular materials, for their porosity for example, or by using their interference property, generating secondary sources that interfere, destructively with a primary source (the determination of distance between two sources is then important).
    These solutions do not always show the results obtained. It is therefore desirable to put one before a new architecture to ensure both the functions of cooling and sound absorption.
    PRESENTATION OF THE INVENTION To this end, the invention relates to an assembly for a turbomachine, the assembly comprising: - a casing extending along a longitudinal axis of the turbomachine, - a surface heat exchanger disposed on an inner periphery of said casing and comprising a plurality of cooling fins extending radially inwardly and longitudinally, and - a central body concentrically arranged partly inside said housing, said housing and the central body defining between them an annular airway whose width at the heat exchanger is substantially constant, the assembly being characterized in that the distribution of the fins is distributed over more than 180 ° from the internal periphery of the casing and in that the average height of the fins is greater than at 5% of the width of the annular air path at the heat exchanger. The invention may comprise the following features, taken alone or in combination: the distribution of the fins on the inner periphery of the housing is distributed discontinuously, the height of the fins is constant, the height between the fins is variable, the height of the fins depends on their angular position and checks a sinusoidal function, - the equation is the following: h (0) = ho | cos (n.0) |, with n a natural integer and h0 such that h0> π / 2 x 0.05 x hVa, hva being the width of the air path Va, - the distribution of the fins is distributed over more than 270 ° from the inner periphery of the casing, - the spacing between two fins is less than 8 , 5 mm, so that the exchanger behaves acoustically like an expansion chamber for frequencies up to 10kHz, at ambient temperature of 20 ° C, - the spacing between two fins is less than 4.3 mm , so that the exchanger behaves acoustically like a room expansion point for frequencies up to 20kHz, at ambient temperature of 20 ° C, - the spacing between two fins is determined at iso-surface depending on the surface of a fin and the total area of the fins desired.
    Finally, the invention relates to a turbomachine comprising an assembly as described above.
    PRESENTATION OF THE FIGURES Other features, objects and advantages of the invention will emerge from the description which follows, which is purely illustrative and nonlimiting, and which should be read with reference to the accompanying drawings, in which: FIG. view of the fins of a SACOC exchanger as known from the prior art, - Figure 2 shows the positioning of an exchanger in a turbomachine, - Figure 3 shows a turbomachine, - Figures 4 and 5 show a exchanger and its geometric characteristics according to one embodiment of the invention, - Figures 6 to 13 show different embodiments of the invention, - Figure 14 shows two expansion chamber diagrams, - Figure 15 shows the transmission losses in a transmission chamber, - Figure 16 shows the expansion chamber created by the fins of the exchanger, - Figure 17 shows an infinity of fins es, thus creating a perfect expansion chamber, - Fig. 18 shows a finite number of vanes, - Fig. 19 shows a modeling of the acoustic propagation, - Fig. 20 shows a mode attenuation diagram, - FIG. 21 represents a curve illustrating the influence of various parameters; FIGS. 22a, 22b and 23a, 23b show two examples of mode attenuation diagrams as a function of two fin distribution densities.
    DETAILED DESCRIPTION
    Figures 2 and 3 show the positioning of a surface exchanger 100 in a turbomachine 1.
    The turbomachine 1 receives as input by a fan 2 air divided into two streams, a primary flow and a secondary flow.
    The primary stream is compressed and ignited with fuel. The generated gases drive a turbine that rotates the fan, or (fan). This causes the secondary flow that creates the thrust.
    The turbomachine 1 is housed in a nacelle 200 comprising a housing 20 extending along a longitudinal axis XX 'of the turbomachine 100. The turbomachine comprises, at least partially downstream of the fan, in the direction of the flow of air through the turbomachine, a central body 30. The central body 30 is partially inside this housing 20. The central body 30 is disposed concentrically or substantially concentric with respect to the longitudinal axis X-X '. The central body 30 includes in particular the different elements through which the primary flow.
    The housing 20 and the central body 30 define between them an annular air path Va, in the form of an annular channel, allowing the secondary flow to flow. In a plane orthogonal to the longitudinal axis X-X, the annular airway Va has a regular crown shape.
    A surface heat exchanger 100 is disposed on an inner periphery 22 of the casing 20. The exchanger 100 comprises a plurality of cooling fins 110 which extend both radially towards the inside of the casing 20, in the direction of the central body 30, and both longitudinally along the axis X-X '. The heat exchanger is called surface because the exchange is done through the surface of the fin 110, between the fluid flowing in the fins 110 and the secondary flow air that passes into the annular airway Va. Typically, such a heat exchanger 100 operates on an oil-air exchange principle, commonly known as SACOC.
    The thermal properties of the SACOC thus depend mainly on the total area of the fins 110 that make up the exchanger 100.
    According to the embodiments, the fins 110 have a shape of rectangular parallelepipeds, to which can be defined a thickness e, a length L and a height h. The height h and the length L being much greater than the thickness e, the contact surface is essentially surface, hence the term surface exchanger (see Figure 4).
    Conventionally, the thickness e is 1 to 2 mm and the length L of 100 m. Thermally and aerodynamically, it is preferable to have a low thickness e to promote heat exchange and to obstruct the secondary flow as little as possible. The length L is a purely aerothermal criterion and intervenes little acoustically (low sensitivity in terms of acoustics).
    At the heat exchanger 100, that is to say at an orthogonal plane P to the longitudinal axis XX 'which intersects said exchanger 100, the width, or section, of the air channel Va is constant or substantially constant (see Figure 5).
    In other words, the section in such a plane of the casing 20 and the central body 30 forms two concentric circles of respective radii r2o and r30. The width of the airway Va, which corresponds to the thickness of the ring or the radial distance between the casing 20 and the central body 30, that is to say the difference between the two r2o rays and r30, is therefore constant (see Figure 5).
    We denote hVa the previously defined width.
    In a particular embodiment, sections in the plane P may not form circles, or at least not concentric circles. The width hVa then designates the average radial distance between the casing 20 and the central body 30.
    The terms upstream and downstream are defined by the direction of flow of the air in the air path when the turbomachine 1 is in operation.
    For reasons of clarity of the description, the phenomena and physical principles contributing to the feasibility and operation of the invention are explained in the appendices at the end of the present description.
    In order to improve the acoustic properties of the turbomachine 1, the distribution of the fins 110 is distributed over more than 180 ° of the inner periphery 22 of the casing 20 and the average height hMov of the fins 110 is greater than 5% of the width of the annular air path at the heat exchanger hVA, hMov 0,0 0.05 hVA), ie in the plane P.
    The term medium height means that the heights h are averaged fins. When a zone is without wings 110, zero pitch is not assigned. This means that the average height hMoY is only calculated for zones comprising fins 110.
    This value of 5% of the air channel Va makes it possible to take advantage of the physical principles of acoustics detailed in the appendices while maintaining the exchange surface useful for the heat dissipation.
    The value of 180 ° is also linked to obtaining a minimum benefit in terms of noise reduction.
    Several embodiments will now be described. Indeed, there are several adjustment levers: the height h of the fins 110, the distribution of the fins 110 on the inner periphery 22 of the housing 20 and the distance d between fins 110. This last parameter can nevertheless be determined by performance calculation equal thermal ("iso-surface") with respect to a heat exchanger 100 conventionally implemented in a turbomachine 1 or against a previously established specifications. In this case, it is adjusted a posteriori to obtain the necessary heat exchange surface, while remaining sufficient to verify the physical effects presented in the appendices.
    The height h of the fins 110 can verify the condition introduced previously in several ways.
    In connection with FIG. 6, the first embodiment consists in having a constant height of blades 10: this gives h = hMov 0,0 0.05 hVa [1000]. By way of example, for an airway Va of width hVa of 40 cm, the height h must be greater than 20 mm.
    Alternatively, the height h of the fins 110 may be variable. More particularly, this is defined as a function of the angular position of the fin 110 on the inner periphery 22 of the casing 20.
    We then define the height h as a function of type h = h (0).
    We can cite the parametric function called "daisy": hn (6) = h0 | cos (n0) | with n a natural integer and h0 such that h0> π / 2 x 0.05 hVa, that is h0> 0.08hVa, so that hMov always checks the inequality [1000] introduced previously.
    Figures 7, 8, 9 and 10 show the previous parametric height with respectively n = 1, n = 2, n = 3, n = 10.
    The parameter n is adjusted according to the modal forms that propagate in the air path Va.
    We can also mention other sinusoidal functions, of type: hn (6) = h0 (1 + cos (n0)) with h0> 0,05 hVa, or else hn (6) = h0 cos2 (n0) with h0> 0.10 hVa.
    More generally, a sinusoidal type function can be applied, while ensuring that the average height hMoY of the fins 110 satisfies the condition [1000].
    The distribution of fins 110 as for it may also vary according to the embodiments.
    If the 360 ° distribution seems the most natural, it is not always implementable because the entire periphery 22 of the housing 20 is not necessarily available to put the fins 110 of the exchanger 100, particularly because of the passage of cables, structural arms for fixing or crossing easements, pylon, etc. these elements represented by the reference 3 in FIG.
    In one embodiment, the distribution is greater than 270 °. See in particular Figure 11 in which the distribution is equal to 270 °.
    In one embodiment, the distribution is continuous, that is to say that all the fins form a single angle greater than 180 ° (see Figure 11 too).
    Alternatively, the distribution of the distribution may be discontinuous, that is to say with breaks in the distribution on the inner periphery 22, as shown in FIGS. 12 and 13. Summing up the angles covered by fins 110, it is necessary to nevertheless check the condition of the 180 °, which is therefore a condition of cumulative angles.
    The criteria of height h and distribution are cumulative and all the combinations satisfying the two criteria, hMov 0,0 0.05 hVa and more than 180 ° of distribution, are conceivable.
    Figure 13 thus illustrates a distribution greater than 270 ° continuous, with a parametric height in sinusoidal function.
    The different embodiments thus allow the passage of the service arms (cables, servitudes), or structural (casing arm, pylons on the casing 20), which are represented by the reference 3 in FIG.
    For example, it is possible for these elements 3 to pass longitudinally through the exchanger 100, passing where the height of the fins 110 is zero, thanks to the sinusoidal function, or else where a discontinuity is present.
    In relation to the annexes present at the end of the description, the values of 5% of the width hVa of the air path Va are chosen so that the effects of acoustics are sensitive. It is the same for the 180 ° of the distribution of fins 110; below, it is estimated that the desired effects are not sufficient.
    Finally, it is possible to modify the distance d between the fins 110. Typically, this parameter can be adjusted once known the height h and the distribution of the fins 100 to obtain the area necessary for heat exchange. In other words, it is determined according to the surface of a fin 110 and the total area of the fins 110 desired.
    It is said that the distance d is determined by iso-surface with respect to the heat dissipation constraints, generally provided by a specification.
    A consequence related to the new height h fins 110, which is greater than a standard heat exchanger, lies in the possibility of spacing a little more fins 110 with equivalent total heat exchange surface.
    Another possibility is to choose the inter-fin distance to ensure a good acoustic reflection effect as explained in the appendices.
    For the exchanger 100 to act as an expansion chamber as explained in the appendices, the wavelength λ of the sound must be four times greater than the inter-fin distance 110.
    For example, to take advantage of the reflection effect up to 10kHz, respectively 20kHz, under normal temperature conditions of the order of 20 ° C, the inter-fin distance must be less than 8.5mm, respectively 4 , 3mm.
    This criterion of distance d as a function of the wavelength tuned to the frequency of the noise that one wishes to attenuate can however be redundant with the distance d calculated by iso-surface. Be that as it may, it is a question of determining a distance d which satisfies at the same time the dimensioning for the thermal effects and for the acoustic effects.
    Finally, the shape of the fins 110, which we have presented as parallelepiped rectangle, can be optimized to improve the aerodynamics (criteria of "best aero"). The height h mentioned in the present description will be either the average height of each fin, or the maximum height.
    Thus, the invention proposes a solution for acoustically treating a turbomachine by using the geometry of the fins of the exchanger.
    As it is ensured that the total surface of the fins 110 remains equal to that of a conventional heat exchanger or at least sufficient to allow heat exchange, the heat exchanger advantageously combines its functions of thermal diffuser and acoustic treatment, where a saving of space in the turbomachine.
    In addition, since it relies solely on geometric considerations, the invention is not related to a specific type of material.
    Annex 1: acoustic reflection on the exchanger 100
    The first physical principle for the operation of the invention lies in the optimization of the reflection coefficient in the duct via the modification of the apparent section.
    Figure 14 shows two illustrative diagrams.
    For plane mode propagation, that is to say below the cutoff frequency, the transmission loss ("TL for transmission ioss") is expressed as a function of the wave number k {k = 2nf / c, where c is the speed of sound in the middle), the length L of the section change and the section ratio m: m = S2 / Si.
    The transmission loss is written as: TL = 10logw l + i (m-£) sin2 {kL) [1001]
    By symmetry of the expression [1001] between m and 1 / m, it is noted that it does not matter whether the apparent section narrows or widens: the transmission loss curve presented in FIG. 15 is the same.
    In the present case of the exchanger 100, the expansion ratio m is less than 1, that is to say that it is on a narrowing of the section. From an acoustic point of view, if the wavelength of the sound is sufficiently large relative to the inter-fin distance d of the heat exchanger 100, the presence of the fins 110 modifies the apparent section, as shown in FIG. FIG. 16, and the heat exchanger 100 behaves like an expansion chamber: the geometry of FIG. 17, comprising an infinity of fins, and that of FIG. 18, comprising a finite but sufficient number of fins, exhibit However, since the propagation is multimodal, that is to say also taking place above the first cut-off frequency of the air path Va, the propagation is not only in a plane mode, but in radial r and azimuth modes a. For these modes, the curve shown in Figure 15 no longer applies.
    We distinguish in the secondary vein (thus here the air path Va) two types of noise in a turbomachine 1 bi-flow: - Line noise, linked to a periodicity, produced by the interactions of the blades of turbines, blades (OGV, outlet guides vanes), or the fixed guide vanes (IGV), - Wideband noise (BLB), of random origin, resulting from the noise of turbulence on the leading edges, the trailing edges of the fan 2 (or "fan") ...
    In the case of broadband noise, the maximum amplitude of the acoustic energy is deployed in high order azimuthal modes on the outer periphery 22 of the casing 20: any reflecting or refracting element in this zone will have an optimal influence on the propagation. sound. This is why the exchanger 100 is of major interest for broadband noise reduction.
    By numerical calculation shown in FIG. 19 which shows a modeling of the acoustic propagation of a high order azimuth mode, for example for r = 1 and a = 40, in the air path Va, a reflection of the acoustic energy downstream of the exchanger 100, which reduces the external radiation. In Fig. 19, the lighter the color, the lower the sound amplitude.
    As shown in FIG. 20, by simulating the computation on more radial modes, represented by r on the abscissa, and azimuths, represented by the order a on the ordinate, we confirm the strong attenuation of the high azimuthal modes of order a, in positive and negative. The color represents the losses by PL transmission (the darker the color, the stronger the attenuation).
    FIG. 21 presents a set of curves illustrating the effects of the height h of the fins, the number of fins as well as the distribution of the distribution on the periphery of the casing: the curve Ci concerns one hundred fins of height h = 5cm distributed at 360 °, C2 curve concerns one hundred fins height h = 2 cm distributed at 360 ° C, the curve C3 relates to an infinity of fins, this is equivalent to a perfect expansion chamber, as shown in FIG. height h = 2cm distributed at 360 °, - The curve C4 relates to an infinity of fins of height 2 cm distributed at 240 °.
    Note that the number of fins and the positioning condition the loss by TL transmission of the expression [1001] at high frequencies, especially more than 1kHz, while the height h of the fins drives more attenuation at low frequency.
    Annex 2: modal redistribution by exchanger 100
    The second physical phenomenon contributing to the operation of the invention is a modal redistribution effect in the presence of a rotor-stator system. We refer to Tyler & Sofrin whose model allows to estimate the modes which in theory can not propagate - one speaks of modal cutoff. For a rotor-stator system, these cuts are controlled by the number of blades of the fan and the number of stators.
    This modal redistribution depends to a large extent on the number of fins 110 of the heat exchanger 100 on the inner periphery 22 of the casing 20. This number can be determined so as to deploy acoustic energy to modes that are not propagated in the channel. of air Va.
    FIGS. 22a, 22b and 23a, 23b represent amplitude diagrams of the modes at the outlet of the air path Va for a radial order r = 1 and azimuth a = 18, for a height h of the fins 110 of 5 mm and a Distribution distribution 360 °. Take as an example, a blower composed of 18 blades: at the fundamental line 1F, the spatial distribution of the acoustic energy requires that the mode 18 propagates mainly the acoustic energy.
    In this case, while crossing the SACOC, a part of the acoustic energy will be deployed on other modes: - In figure 22a and 22b, with twenty fins 110, the acoustic energy is deployed on the propagating modes a = 18, a = -2 and a = -22, - In Figure 23a and 23b, with 100 fins 110, the acoustic energy is deployed in the mode a = 18 and a = 82. The latter is evanescent, therefore non-propagating at the target frequency of 1200 Hz, it does not appear in Figure 23b.
    The number of fins controls the modal content propagating in the air path Va.
    This reorganization responds to the formulation of Tyler & Sofrin linking the azimuthal order of the acoustic modes a with the geometrical elements of the stator, in Figure 23, the exchanger 100). At the harmonic k of the frequency of passage of the blades, the azimuthal orders generated take the form a = kB - sV, where B is the number of blades of the fan, B the number of stator elements and s a relative number any.
    权利要求:
    Claims (11)
    [1" id="c-fr-0001]
    claims
    1. Turbomachine assembly (1), the assembly comprising: - a casing (20) extending along a longitudinal axis (X-X ') of the turbomachine (1), - a surface heat exchanger (100) disposed on an inner periphery (22) of said housing (20) and comprising a plurality of cooling fins (110) extending radially inwardly and longitudinally, and - a central body (30) concentrically arranged partly inwardly said housing (20), said housing (20) and the central body (30) defining between them an annular air path (Va) whose width (hVa) at the heat exchanger (100) is substantially constant, the assembly being characterized in that the distribution of the fins (110) is distributed over more than 180 ° from the inner periphery (22) of the casing (20) and in that the average height (hMov) of the fins (110) is greater than 5% of the width (hVa) of the annular air path (Va) at the heat exchanger (100).
    [2" id="c-fr-0002]
    2. The assembly of claim 1, wherein the distribution of fins (110) on the inner periphery (22) of the housing (20) is distributed discontinuously.
    [3" id="c-fr-0003]
    3. An assembly according to any one of claims 1 to 2, wherein the height (h) of the fins (110) is constant.
    [4" id="c-fr-0004]
    4. An assembly according to any one of claims 1 to 3, wherein the height (h) between fins (110) is variable.
    [5" id="c-fr-0005]
    5. The assembly of claim 4, wherein the height (h) of the fins (100) depends on their angular position and verifies a sinusoidal function.
    [6" id="c-fr-0006]
    6. An assembly according to claim 5, wherein the equation is: h (0) = h0 | cos (n0) |, with n a natural integer and h0 such that h0> π / 2 x 0.05 xh is , hva being the width of the airway Va.
    [7" id="c-fr-0007]
    7. An assembly according to any one of claims 1 to 6, wherein the distribution of the fins (110) is distributed over more than 270 ° of the inner periphery (22) of the housing (20).
    [8" id="c-fr-0008]
    8. An assembly according to any one of claims 1 to 7, wherein the spacing between two fins (110) is less than 8.5 mm, so that the exchanger (100) behaves acoustically as a chamber of expansion for frequencies up to 10kHz, at room temperature of 20 ° C.
    [9" id="c-fr-0009]
    9. An assembly according to any one of claims 1 to 7, wherein the spacing between two fins (110) is less than 4.3 mm, so that the exchanger (100) behaves acoustically like a chamber of expansion for frequencies up to 20kHz, at ambient temperature of 20 ° C.
    [10" id="c-fr-0010]
    An assembly according to any one of claims 1 to 7, wherein the spacing between two fins (110) is determined at isosurface as a function of the surface of a fin (110) and the total area of the fins (110). ) desired.
    [11" id="c-fr-0011]
    11. Turbomachine (1) comprising an assembly according to any one of the preceding claims.
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    法律状态:
    2017-01-13| PLFP| Fee payment|Year of fee payment: 2 |
    2017-08-04| PLSC| Publication of the preliminary search report|Effective date: 20170804 |
    2017-12-21| PLFP| Fee payment|Year of fee payment: 3 |
    2018-09-14| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20180809 |
    2019-12-19| PLFP| Fee payment|Year of fee payment: 5 |
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    优先权:
    申请号 | 申请日 | 专利标题
    FR1650753|2016-01-29|
    FR1650753A|FR3047270B1|2016-01-29|2016-01-29|SURFACE HEAT EXCHANGER AND ACOUSTIC TREATMENT|FR1650753A| FR3047270B1|2016-01-29|2016-01-29|SURFACE HEAT EXCHANGER AND ACOUSTIC TREATMENT|
    CN201780008840.4A| CN108603442B|2016-01-29|2017-01-25|Surface heat exchanger and acoustic treatment|
    PCT/FR2017/050152| WO2017129894A1|2016-01-29|2017-01-25|Surface heat exchanger and acoustic treatment|
    EP17706288.2A| EP3408514B1|2016-01-29|2017-01-25|Surface heat exchanger and acoustic treatment|
    US16/072,069| US10774745B2|2016-01-29|2017-01-25|Surface heat exchanger and acoustic treatment|
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