[0001] The present invention relates to the field of high gas turbine blades aerospace pressure, in particular the internal structure of the vanes, and a gas turbine having such blades.

STATE OF THE ART

[0002] The moving blades of a gas of an aircraft turbine engine, and in particular of the high-pressure turbine, are subjected to very high temperatures of the combustion gases during engine operation. These temperatures reach values ​​well above those that can withstand without damage the various parts that are in contact with the gas, which has the effect of limiting their lifespan.

[0003] Furthermore, an elevation of the gas temperature of the high-pressure turbine improves the efficiency of an engine, therefore the ratio between the engine thrust and weight of an aircraft powered by the engine. Therefore, efforts are undertaken to make turbine blades that can withstand temperatures higher and higher, and in order to optimize the cooling of these vanes.

[0004] It is well known to provide such cooling circuits blades to reduce the temperature of the latter. With such circuits, the cooling air to (air or "cold"), which is generally introduced into the blade by its foot passes therethrough following a path formed by cavities formed in the thickness of the blade before being ejected through orifices opening on the surface of the blade.

[0005] Such cooling systems are called "advanced" when they are composed of several independent cavities in the thickness of the blade, or when some of these cavities are dedicated to localized cooling. These cavities are used to set consistent with the dawn engine performance requirements and service life of parts. One can for example be mentioned as an example of circuit

Advanced cooling the coolant circuit as presented in EP 1,741,875.

[0006] Such advanced circuits have the disadvantage of generating a large temperature difference between the outer walls of the vane into contact with the vein and the heart walls of the vane. These significant temperature differences induce expansions and stresses which may jeopardize the mechanical strength of the dawn in operation and thus impact its lifespan. walls dilations in the ortho-radial plane give rise to particular constraints around the junction area of ​​the heart of the blade and the blade walls may rupture.

[0007] The solutions proposed to address these problems usually involve increasing the thickness of the various walls to improve the outfit. However, it understands that it penalizes the overall performance of the blade.

PRESENTATION DE L'INVENTION

[0008] The present disclosure relates to an aeronautical turbine blade extending in the radial direction from a blade root to an upper wall, said vane including a plurality of internal cavities defining at least one cooling circuit, said cavities internal each being defined by walls among the inner walls, a pressure side wall, a suction wall, the blade root and the top wall, said blade being characterized in that it comprises at least a first cavity intrados and extrados each first cavity adjacent to a first through-cavity and a second through-cavity, the first cavity being adjacent to suction the suction wall, the first cavity pressure side being adjacent to the wall soffit,each said first and second through holes extending from the pressure side wall to the upper wall of the second through-cavity comprising a first inner wall extending from the wall to the first suction through cavity and a second inner wall extending from the pressure side wall to the first through-cavity, said first inner wall and second inner wall being disjoint.pressure side to the first through-cavity, said first inner wall and second inner wall being disjoint.pressure side to the first through-cavity, said first inner wall and second inner wall being disjoint.

[0009] In one example, the second through-cavity comprises a portion extending between the first cavity and the pressure-side first cavity suction.

[0010] In one example, the first concave side cavity is fluidly connected to the first through-going cavity and the first suction cavity is fluidly connected to the second through-going cavity.

[0011] In one example, the blade comprises a second cavity pressure face, a second convex side cavity and a third through-going cavity,

[0012] wherein the third through-going cavity extending from the pressure side wall to the suction wall, the second concave side cavity and the second suction cavity are each adjacent to the second through-going cavity and the third through-cavity, the second cavity suction is adjacent to the suction wall, the second cavity pressure face adjacent the pressure side wall, and wherein the third through-cavity comprises a third internal wall extending since the suction wall to the second through-going cavity, and a fourth inner wall extending from the pressure side wall to the second through-cavity, said third inner wall and fourth inner wall being disjoint.

[0013] The third through-going cavity then typically includes a portion extending between the second cavity pressure face and the second cavity suction.

[0014] The second concave side cavity is then typically fluidly connected to the first convex side cavity, and the second suction cavity is fluidly connected to the third through-going cavity.

[0015] According to one embodiment, the blade comprises a third cavity pressure face, a third suction cavity and a fourth through-cavity, wherein the fourth through cavity extending from the pressure side wall to the extrados wall, the third cavity of the third lower surface and upper surface of each cavity are adjacent to the third through-going cavity and the fourth through-cavity, the third suction cavity is adjacent to the wall suction, the third cavity pressure face adjacent the pressure side wall, and wherein the third through-cavity comprises a fifth internal wall extending from the upper wall to the fourth through-cavity, and a sixth inner wall s' extending from the wall ofpressure side to the fourth through-cavity, said fifth and sixth inner wall inner wall being disjoint.

[0016] All or part of through cavities may comprise at least one reinforcing beam disposed in one of said through cavities and connecting the blade root to the top wall, said reinforcing beam being disjoint from the inner walls of the pressure side wall and upper wall.

[0017] The present disclosure also relates to a gas turbine having blades of the present disclosure.

BRIEF DESCRIPTION OF DRAWINGS

[0018] The invention and its advantages will be better understood from reading the detailed description given below of various embodiments of the invention given as non-limiting examples. The description refers to the accompanying figures of pages, where:

- Figure 1 shows an exemplary perspective view of an aeronautical turbine blade,

- Figure 2 shows an exemplary cross-sectional view of such a blade,

- Figure 3 shows another example of a sectional view of such a blade.

[0019] In all figures, the common elements are identified by like reference numerals.

DETAILED DESCRIPTION OF EXAMPLES OF REALIZATION

[0020] The following describes the invention with reference to FIGS 1 to 3.

[0021] Figure 1 illustrates a rotor blade 10, for example metal, of a turbine engine high pressure turbine. Of course, the present invention can also be applied to other mobile or fixed blades of the turbomachine.

[0022] The blade 10 includes an airfoil 12 (or blade) extending radially between a blade root 14 and a blade head 16.

[0023] The blade root 14 is adapted to be mounted on a rotor disc of the high-pressure turbine, the blade head 16 is radially opposed to the blade root 14.

[0024] The airfoil 12 has four distinct areas: a board 18 disposed attack next to the flow of hot gases from the combustion chamber of the turbomachine, a trailing edge 20 opposite the edge 18 , a pressure side wall 22 and an extrados wall 24, walls intrados 22 and extrados 24 connecting the leading edge 18 to trailing edge 20.

[0025] At the level of the blade head 16, the aerodynamic surface 12 of the blade is closed by a transverse wall 26. Furthermore, the aerodynamic surface 12 extends radially slightly beyond the transverse wall 26 of to form a bowl 28, referred to hereinafter bath of the blade. This bath 28 therefore has a bottom formed by the transverse wall 26, an edge formed by the aerodynamic surface 12 and is open towards the blade head 16. The ports 30 are typically formed in the pressure side wall 22 and / or in the wall of upper 24, so as to allow an inlet and / or air discharge between internal cavities at dawn and the external environment.

[0026] The blade 10 typically comprises one or more cooling circuits formed by the internal structure of the blade 10 which is described below.

[0027] Figures 2 and 3 are two sectional views of two variants of a blade as shown in Figure 1, for example according to the section plane P shown in Figure 1.

[0028] As seen in these figures, the blade 10 is hollow, and its inner volume is composed of a plurality of internal cavities separated by internal walls.

[0029] In the examples shown in Figure 2, the blade 10 comprises internal cavities 11 designated by the references Cl CH.

[0030] As seen in Figure 2, for the example shown, some of these internal cavities, namely the internal cavities Cl, C4, C7, C10 and Cll extending between the pressure side wall 22 and the wall suction face 24; thus refers to as internal through-cavities. The internal cavities Cl, C4, C7, C10 and Cll are designated respectively as first, second, third, fourth and

fifth internal cavities therethrough. The first through cavity Cl form the leading edge 18 of the blade 10, while the fifth through cavity Cil is positioned in the extension of the internal cavity IOC, and forms the trailing edge 20 of the blade 10.

[0031] The remaining internal cavities, namely the internal cavities C2, C3, C5, C6, C8 and C9 are not traversing, that is to say they are each adjacent to one of the walls of intrados 22 and extrados 24, but do not extend to the other of the walls 22 intrados or extrados 24.

[0032] Among these internal non-through cavities, internal cavities C3, C6 and C9 are adjacent to the wall suction face 24; thus refers to respectively as first, second and third cavities suction. The internal cavities C2, C5 and C8 are for their part adjacent to the pressure side wall 22; thus refers to respectively as first, second and third cavities intrados.

[0033] It is well understood that such an example of internal structure of the blade 10 is only illustrative, and the invention presented can be applied regardless of the internal structure of the blade 10.

[0034] As indicated in the preamble of the present patent application, one of the major problems for the design of such a blade 10 is the held in operation particularly because of the expansion gaps occurring in different regions of the blade 10, and specifically stress that result in an ortho-radial plane of the blade 10.

[0035] To address these issues, this paper proposes a particular structure to the walls defining the through holes and cavities of pressure and suction.

[0036] As seen in Figure 2, the second, third and fourth inner through cavities C4, C7 and C10 have a specific structure, so that their walls extend to another through inner cavity.

[0037] Specifically, considering the second through inner cavity C4, the latter is delimited especially by a first inner wall PI which extends from the wall of upper 24 to the first through-going cavity Cl, and a second inner wall P2 which extends from the pressure side wall 22 to the first through-going cavity Cl. the first inner wall PI and the second inner wall P2 are disjoint. Such a structure allows the second through cavity C4 to extend between the first pressure face cavity C2 and the first suction cavity C3, so that the fluid, which is heated on passing through the second concave side cavity C5 then the first suction cavity C3, flows through the second through-going cavity C4 and washes the walls of the first cavity intrados C2 and the first cavity suction C3, and thus reduce the thermal gradient between the outer walls of the blade 10 (that is to -dire the pressure side wall 22 and the suction wall 24) and the inner walls (here the first inner wall PI and the second inner wall P2). Furthermore, severing the first inner wall PI and the second inner wall P2 reduces the stresses around their respective junctions with the walls of extrados and intrados, for example with respect to a structure in which these inner walls PI and P2 would be confused. is to say the pressure side wall 22 and the suction wall 24) and the inner walls (here the first inner wall PI and the second inner wall P2). Furthermore, severing the first inner wall PI and the second inner wall P2 reduces the stresses around their respective junctions with the walls of extrados and intrados, for example with respect to a structure in which these inner walls PI and P2 would be confused. is to say the pressure side wall 22 and the suction wall 24) and the inner walls (here the first inner wall PI and the second inner wall P2). Furthermore, severing the first inner wall PI and the second inner wall P2 reduces the stresses around their respective junctions with the walls of extrados and intrados, for example with respect to a structure in which these inner walls PI and P2 would be confused.

[0038] The third through-going cavity C7 has a substantially separate structure. This third C7 through cavity is delimited in particular by a third inner wall P3 which extends from the upper wall 24 to the second through-going cavity C4, by a fourth wall internal P4 which extends from the pressure side wall 22 to the second through-going cavity C4, the third inner wall P3 and fourth P4 inner wall being disjoint, and is also bounded by a fifth P5 inner wall which extends from the wall 24 to the suction fourth C10 through cavity, a sixth internal wall extending P6 extending from the pressure side wall 22 to the fourth through cavity C10

third cavity suction C6 and C9, and thus reduce the thermal gradient between the outer walls of the blade 10 (that is to say the pressure side wall 22 and the suction wall 24) and the inner walls (here the third inner wall P3, the fourth internal wall P4, P5 inner wall fifth and sixth inner wall P6. in addition, severing the inner walls P3 and P4 on the one hand, and the inner walls P5 and P6 other hand allows to reduce the stresses around their respective junctions with the walls of extrados and intrados compared with a structure in which these walls are combined in pairs.

[0039] Each cavity intrados and extrados is thus adjacent two through cavities, and is not adjacent to another cavity intrados or extrados. By adjacent is meant that the considered cavities have at least one common wall.

[0040] A blade 10 having a structure as shown in Figure 2 is thus advantageous especially in that it reduces the thermal gradient between the various inner and outer walls to the blade 10, and thus limit the difference in expansion between the walls which is an important factor for the generation of efforts during operation. Furthermore, the fact to realize a circulation of air between the various internal walls, in particular between the first internal wall PI and the second inner wall P2 via the second through C4 cavity to control the temperature of the inner walls, and the maintain a temperature range for which the considered materials have optimum mechanical properties. It is the same for other internal walls P3 to P6.

[0041] The direction of fluid flow in the various cavities of the vane forming the cooling system can be defined in several configurations, the geometry of the inner walls PI to P6 are not binding. For example, mention may be made a configuration in which each cavity pressure side is fluidly connected to at least one through cavity, and each cavity suction is fluidly connected to at least one through cavity. Each concave side cavity and suction can also be fluidly connected to another cavity pressure side or suction side. All or part of the cavities of intrados and extrados therethrough may also be connected to the ports 30 arranged in the pressure side wall 22 and / or in the wall of extrados 24 of the blade 10.

[0043] In the example shown in FIG 3, the fifth P5 inner wall is removed, so that the cavities C9 and C10 are merged to form a single cavity C12. Such embodiment allows for direct cooling of the suction wall 24 adjacent the trailing edge 20 while maintaining a mechanically flexible avoiding forming a transverse wall structure extending between the pressure side wall 22 and the suction wall 24 within the cavity C12. Such embodiment is particularly suited for cases where the fluid temperature of the vein in which changing the blade presents a significant deviation from the coolant temperature flowing in the blade 10.

[0044] In the examples shown in Figures 2 and 3, the blade 10 comprises reinforcing beams extending in through cavities of the vane 10, since the root of the blade 10 to the partition higher, typically the transverse wall 26 defining the bottom of the tub 28 of the blade 10.

[0045] In the examples shown in Figures 2 and 3, the blade 10 thus comprises two reinforcing beams 50 and 60 respectively disposed within the second through-going cavity C4 and third through-going cavity C7.

[0046] Each of these reinforcing beams 50 and 60 extends from the root of the blade 10 to its upper wall, and is disposed within a through cavity while remaining disjoint from the wall of intrados 22 with the extrados wall 24 and internal walls defining the through cavities.

[0047] The reinforcing beams 50 and 60 are thus each located fully into a cooling stream of the blade 10, and thus the temperature of the air flowing in the cooling vein considered, and are thus not impacted directly by the temperature of the pressure side wall 22 and the suction wall 24. the root of the blade is located right below the air stream, and operates at the cooling air temperature of the blade 10.

[0048] The presence of such reinforcing beams 50 and 60 allows to retain the centrifugal force without causing efforts in the ortho-radial plane. To the extent that the reinforcing beams 50 and 60 retain the centrifugal force, the other of the blade walls 10 can be thinned, thereby enabling to minimize or even cancel the impact of reinforcing beams on the weight of the blade 10 and its cooling circuit.

[0049] The reinforcing beams 50 and 60 are typically centered on a center line of the blade 10 as a sectional view in the radial direction, as shown in Figures 2 and 3, which improves the recovery of the effort centrifugal by reinforcing beams 50 and 60.

[0050] The number and location of the reinforcing beams may vary depending on the geometry of the blade 10 and under the conditions in which it is intended to evolve. good It will be understood that the embodiments shown in Figures 2 and 3 each include two reinforcing beams is not limitative and that the blade 10 may include a single beam reinforcement, or 3, 4, 5 or more than 5 reinforcing beams arranged in separate through cavities or more reinforcing beams may be arranged within a through cavity.

[0051] The reinforcing beams may be solid or hollow. Figures 2 and 3 each show an embodiment wherein the reinforcing beams 50 and 60 are full.

[0052] In the case where the reinforcing beams are hollow, they may have holes in the form of slots and / or holes thereby achieving an air flow within the reinforcing beams, for example to define a cooling fluid flow to be supplied to a critical area of ​​the blade 10 to the extent that such flux is thermally insulated from the pressure side wall 22 and the suction wall 24.

[0053] The reinforcing beams typically have a circular, oval or ovoid, with the proviso that in the case of a blade 10 having a plurality of reinforcing beams, they may have distinct geometries. reinforcing beams can also have a constant or variable section over the height of the blade 10.

[0054] While the invention has been described with reference to specific embodiments, it is obvious that modifications and changes can be made to these examples without departing from the general scope of the invention as defined by the revendications. In particular, cooling circuits and numbers of cavities each component of these circuits are not limited to those presented in this example. Therefore, the description and drawings should be considered illustrative rather than restrictive sense.

[0055] It is also clear that all the features described with reference to a method are transposed, alone or in combination, to a device, and vice versa, all the features described with reference to a device can be transposed, alone or in combination, to a method.

CLAIMS

1. blade (10) of aviation turbine extending in the radial direction from a blade root (14) to an upper wall (26), said blade (10) comprising a plurality of internal cavities defining at least one cooling circuit, said internal cavities each being defined by walls among the inner walls, a pressure side wall (22), a suction wall (24), the blade root (14) and the upper partition (26 )

said vane (10) being characterized in that it comprises at least a first cavity pressure face (C2) and a first suction cavity (C3) each adjacent a first through cavity (Cl) and a second through cavity (C4), the first suction cavity (C3) being adjacent to the wall suction (24), the first cavity pressure face (C2) being adjacent the pressure side wall (22), each of said first and second through cavities (Cl, C4) extending from the pressure side wall (22) to the suction wall (24),

the second through-going cavity (C4) having a first inner wall (PI) extending from the suction wall (24) to the first through-going cavity (Cl), and a second inner panel (P2) extending from the pressure side wall (22) to the first through-going cavity (Cl), said first inner wall (PI) and the second inner panel (P2) being disjoint.

2. blade (10) according to claim 1, wherein the second through-going cavity (C4) comprises a portion extending between the first pressure face cavity (C2) and the first suction cavity (C3).

3. blade (10) according to one of claims 1 or 2, wherein the first pressure face cavity (C2) is fluidly connected to the first through-going cavity (Cl), and the first suction cavity (C3) is fluidically connected to the second through-going cavity (C4).

4. blade (10) according to one of claims 1 to 3, comprising a second cavity pressure face (C5), a second suction cavity (C6) and a third through-going cavity (C7),

wherein the third through-going cavity (C7) extends from the pressure side wall (22) to the suction wall (24), the second pressure face cavity (C5) and the second suction cavity ( C6) are each adjacent to the second through-going cavity (C4) and the third through-going cavity (C7), the second suction cavity (C6) is adjacent to the suction wall (24), the second cavity intrados (C5) is adjacent the pressure side wall (22), and wherein the third through-going cavity (C7) includes a third inner wall (P3) extending from the suction wall (24) to the second through cavity (C4), and a fourth inner wall (P4) extending from the pressure side wall (22) to the second through-going cavity (C4),said third inner wall (P3) and fourth inner wall (P4) being disjoint.

5. blade (10) according to claim 4, wherein the third through-going cavity (C7) comprises a portion extending between the second cavity pressure face (C5) and the second suction cavity (C6).

6. blade (10) according to one of claims 4 or 5, wherein the second pressure side cavity (C5) is fluidly connected to the first suction cavity (C3) and the second suction cavity (C6 ) is fluidly connected to the third through-going cavity (C7).

7. blade (10) according to one of claims 4 to 6, comprising a third cavity pressure face (C8), a third suction cavity (C9) and a fourth through-cavity (C10),

wherein the fourth through cavity (C10) extends from the pressure side wall (22) to the suction wall (24), the third cavity pressure face (C8) and the third suction cavity ( C9) are each adjacent to the third through-going cavity (C7) and the fourth through-cavity (C10), the third suction cavity (C9) is adjacent to the suction wall (24), the third cavity intrados (C8) is adjacent the pressure side wall (22), and wherein the third through-going cavity (C7) comprises a fifth internal wall (P5) extending from the suction wall (24) to the fourth through cavity (C10), and a sixth inner wall (P6) extending from the pressure side wall (22)

to the fourth through-cavity (IOC), said fifth internal wall (P5) and sixth inner wall (P6) being disjoint.

8. blade (10) according to one of the preceding claims, wherein at least one of the through cavities (C4, C7) comprises at least one reinforcing beam (50, 60) disposed within one of said through cavities ( C4, C7) and that connects the blade root (14) to the upper partition (26), said reinforcing beam (50, 60) being disjoint from the inner walls of the pressure side wall (22) and suction wall (24).

9. A gas turbine comprising blades (10) according to any one of claims 1 to 8.