BLADE PROVIDED WITH A COOLING CIRCUIT

Abstract

A blade for a turbomachine, extending longitudinally between a base and an apex, comprising a lower surface wall, an upper surface wall, a leading edge and a trailing edge and comprising a plurality of internal ventilation cavities which form a cooling circuit of the blade, wherein at least one ventilation cavity is a ventilation cavity of a first type comprising at least one ascending portion which extends substantially longitudinally between the base and the apex, engaged with the lower surface wall and spaced from the upper surface wall, and at least one discharge portion which extends substantially transversely and which opens at the trailing edge via at least one port of the trailing edge, and wherein at least one ventilation cavity of the first type further comprises at least one descending portion which extends substantially longitudinally from the apex, engaged with the upper surface wall and spaced from the lower

Claims

1. A blade for a turbomachine extending longitudinally between a base and an apex, comprising a lower surface wall, an upper surface wall, a leading edge and a trailing edge and comprising a plurality of internal ventilation cavities which form a cooling circuit of the blade, wherein several ventilation cavities are ventilation cavities of a first type comprising at least one ascending portion which extends longitudinally between the base and the apex, engaged with the lower surface wall and spaced from the upper surface wall, and at least one discharge portion which extends towards and which opens at the trailing edge via at least one port of the trailing edge, and wherein at least one ventilation cavity of the first type further comprises at least one descending portion which extends longitudinally from the apex engaged with the upper surface wall and spaced from the lower surface wall.

2. The blade according to claim 1, comprising at least three ventilation cavities of the first type.

3. The blade according to claim 1, wherein said discharge portion extends from the lower end of said descending portion.

4. The blade according to claim 1, wherein said ascending portion and said descending portion are separated by a partition.

5. The blade according to claim 1 any one of claims 1, wherein each ventilation cavity of the first type comprises between 2 and 5 ports of the trailing edge.

6. The blade according to claim 1, wherein the wall of at least one ventilation cavity of the first type includes a fillet or an inclined surface at the border between its discharge portion and its descending portion.

7. The blade according claim 1 to, wherein the discharge portion of at least one ventilation cavity of the first type has, in section in a plane perpendicular to the longitudinal direction of the blade, a generally curved profile devoid of ridge.

8. The blade according to claim 1, wherein at least one ventilation cavity of the first type is provided with at least one deflector at the border between its discharge portion and its descending portion.

9. The blade according to claim 1, wherein the cooling circuit comprises a first ventilation cavity of a second type not opening at the trailing edge, this first ventilation cavity of the second type extending along the leading edge.

10. A bladed wheel for a turbomachine module, comprising at least one blade according to claim 1.

11. A turbine, comprising at least one bladed wheel according to claim 10.

12. A turbomachine, comprising at least one bladed wheel according to claim 10.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0049] The appended drawings are schematic and are intended primarily to illustrate the principles of the disclosure.

[0050] In these drawings, from one figure to another, identical elements (or parts of elements) are identified by the same reference signs. Furthermore, elements (or parts of elements) belonging to different exemplary embodiments but having a similar function are identified in the figures by numerical references incremented by 100, 200, etc.

[0051] FIG. 1 is an axial sectional diagram of a turbomachine according to the disclosure.

[0052] FIG. 2 is a perspective view of a blade according to the disclosure.

[0053] FIG. 3 is a diagram illustrating the cooling air circulation through the blade of FIG. 2.

[0054] FIGS. 4A, 4B and 4C illustrate the Coriolis effect in three different planes of the blade of FIG. 2.

[0055] FIG. 5 is a view from the lower surface side of a first example of a core.

[0056] FIG. 6 is a view of the upper surface side of the first example of a core.

[0057] FIG. 7 illustrates a core according to a first variant embodiment.

[0058] FIG. 8 illustrates a cooling circuit according to a second variant embodiment.

[0059] FIG. 9 is a view from the lower surface side of a second example of a core.

[0060] FIG. 10 is a view of the upper surface side of the second example of a core.

[0061] FIG. 11 is a view illustrating a cooling circuit of the prior art.

DESCRIPTION OF THE EMBODIMENTS

[0062] In order to make the description more concrete, examples of blades are described in detail below, with reference to the appended drawings. It is recalled that the invention is not limited to these examples.

[0063] FIG. 1 shows, in section along a vertical plane passing through its main axis A, a bypass turbojet engine 1 according to the disclosure. It includes, from upstream to downstream according to the circulation of the air flow, a fan 2, a low pressure compressor 3, a high pressure compressor 4, a combustion chamber 5, a high pressure turbine 6, and a low pressure turbine 7.

[0064] FIG. 2 illustrates a movable blade 10 of the high pressure turbine 6. It comprises a fir-tree-shaped base 11, a platform 12 and a vane 13. This vane 13 comprises a leading edge 14, a trailing edge 15, a lower surface wall 16, an upper surface wall 17 and a blade head 18.

[0065] The blade 10 further comprises a cooling circuit 20 shown in FIGS. 3 and 4. More specifically, FIG. 3 superimposes three sectional views of the blade 10, along the transverse planes A, B and C of FIG. 2, and represents the circulations of the cooling air between these three planes. FIG. 3A, 3B and 3C are placed in section planes A, B and C of FIG. 2, respectively.

[0066] In this example, the cooling circuit 20 of the blade 10 comprises three ventilation cavities of a first type 21, 22, 23 and a ventilation cavity of a second type 27.

[0067] The first ventilation cavity of the first type 21 comprises an ascending portion 21a which extends longitudinally from the blade base 11 over approximately two thirds of the height of the vane 13 then is extended by a discharge portion 21c which extends transversely from the upper end of the ascending portion 21a towards the trailing edge 15 before opening at the trailing edge 15 via at least one port of the trailing edge 21d. The ascending portion 21a is engaged with the lower surface wall 16 and spaced from the upper surface wall 17. The discharge portion 21c is engaged both with the lower surface wall 16 and with the upper surface wall 17; it extends along the upper third of the trailing edge 15. A first cooling air flow 21e circulates in this first ventilation cavity of the first type 21: this cooling air flow 21e is supplied from the disc carrying the blade 10 through the base 11 and circulates along the ascending section 21a, then along the discharge section 21c, then finally escapes via the ports of the trailing edge 21d.

[0068] The second ventilation cavity of the first type 22 comprises an ascending portion 22a which extends longitudinally from the blade base 11 over the entire height of the vane 13 then is extended by a descending portion 22b which extends longitudinally from the upper end of the ascending portion 22a over about third the height of the vane 13 then is extended by a discharge portion 22c which extends transversely towards the trailing edge 15 before opening at the trailing edge 15 via at least one port of the trailing edge 22d. The ascending portion 22a is engaged with the lower surface wall 16 and spaced from the upper surface wall 17. The descending portion 22b is provided between the ascending portion 22a and the upper surface wall 17: it is therefore engaged with the upper surface wall 17 and spaced from the lower surface wall 16. The discharge portion 22c is firstly only engaged with the upper surface wall 17 in an upstream section along the ascending portions 2a, 22a of the first two cavities of the first type 21, 22, then engaged both with the lower surface wall 16 and with the upper surface wall 17 in a downstream section; it extends along the middle third of the trailing edge 15.

[0069] A second cooling air flow 22e circulates in this second ventilation cavity of the first type 22: this cooling air flow 22e is supplied from the disc carrying the blade 10 through the base 11 and circulates along the ascending section 22a, then along the descending section 22b, then along the discharge section 22c, then finally escapes via the ports of the trailing edge 22d.

[0070] The third ventilation cavity of the first type 23 comprises an ascending portion 23a which extends longitudinally from the blade base 11 over the entire height of the vane 13 then is extended by a descending portion 23b which extends longitudinally from the upper end of the ascending portion 23a over about two thirds of the height of the vane 13 then is extended by a discharge portion 23c which extends transversely towards the trailing edge 15 before opening at the trailing edge 15 via at least one port of the trailing edge 23d. The ascending portion 23a is engaged with the lower surface wall 16 and spaced from the upper surface wall 17. The descending portion 23b is provided between the ascending portion 23a and the upper surface wall 17: it is therefore engaged with the upper surface wall 17 and spaced from the lower surface wall 16. The discharge portion 23c is firstly only engaged with the upper surface wall 17 in an upstream section along the ascending portions 2a, 22a, 23a of the first three cavities of the first type 21, 22, 23, then engaged both with the lower surface wall 16 and with the upper surface wall 17 in a downstream section; it extends along the lower third of the trailing edge 15.

[0071] A third cooling air flow 23e circulates in this third ventilation cavity of the first type 23: this cooling air flow 23e is supplied from the disc carrying the blade 10 through the base 11 and circulates along the ascending section 23a, then along the descending section 23b, then along the discharge section 23c, then finally escapes via the ports of the trailing edge 23d.

[0072] The ventilation cavity of the second type 27 comprises a single ascending portion 27a which extends longitudinally from the blade base 11 over the entire height of the vane 13, along the leading edge 14.

[0073] A fourth cooling air flow 27e circulates in this ventilation cavity of the second type 27: this cooling air flow 27e is supplied from the disc carrying the blade 10 through the base 11 and circulates along the ascending section 27a; it escapes via small ventilation ports (not shown) provided all along the cavity 27.

[0074] Thus, the ascending portions 2a, 22a, 23a of the cavities of the first type 21, 22, 23 are all located engaged with the lower surface wall 16. Therefore, as can be seen in FIGS. 4A to 4C, the Coriolis force Fc tends to press the cooling air circulating radially outwards in these ascending portions 2a, 22a, 23a against the lower surface wall 16, which allows greater exchange with the cooling air and therefore greater cooling of the lower surface wall 16.

[0075] Likewise, the descending portions 22b and 23b are all located engaged with the upper surface wall 17. Therefore, as can be seen in FIGS. 4A to 4C, the Coriolis force Fc tends to press the cooling air circulating radially inwards in these descending portions 22b, 23b against the upper surface wall 17, which allows greater exchange with the cooling air and therefore greater cooling of the upper surface wall 17.

[0076] In addition, the presence of an internal partition 25 separating the ascending sections 2a, 22a, 23a of the cavities of the first type 21, 22, 23 on the one hand and the descending sections 22b, 23b or the discharge sections 22c, 23c of these same cavities 21, 22, 23 on the other hand is noticed in FIGS. 3 and 4. This partition 25, extending in the leading edge-trailing edge direction, substantially equidistant from the lower surface 16 and upper surface 17 walls, is thus spaced from the lower surface 16 and upper surface 17 walls: its operating temperature is therefore less than the outer walls 16, 17 of the blade 10.

[0077] This blade 10 is obtained by casting, in particular according to a lost wax method. The cooling circuit 20 of this blade 10 can then be obtained thanks to the core 30 shown in FIGS. 5 and 6, the latter preferably being produced by additive manufacturing. This core 30 comprises several core elements 31, 32, 33 and 37 disposed relative to each other in the desired geometry at the time of casting. Each core element 31-37 has a geometry corresponding to the negative of the geometry of one of the ventilation cavities 21-27 of the final blade 10.

[0078] Thus, similarly to the first ventilation cavity of the first type 21, the first core element 31 has a longitudinal ascending portion 31a and a transverse discharge portion 31c. In addition, it is noted in FIG. 6 that this discharge portion 31c has three end segments 31d intended to form three ports of the trailing edge 21d.

[0079] Similarly to the second ventilation cavity of the first type 22, the second core element 32 has a longitudinal ascending portion 32a, a longitudinal descending portion 32b, along the upper section of the ascending portion 32a, and a transverse discharge portion 32c. Here again, this discharge portion 32c has three end segments 32d intended to form three ports of the trailing edge 22d.

[0080] Similarly to the third ventilation cavity of the first type 23, the third core element 33 has a longitudinal ascending portion 33a, a longitudinal descending portion 33b, along the upper section of the ascending portion 33a, and a transverse discharge portion 33c. Here again, this discharge portion 33c has three end segments 33d intended to form three ports of the trailing edge 23d.

[0081] Finally, in turn, similarly to the ventilation cavity of the second type 27, the fourth core element 37 has a single longitudinal ascending portion 37a.

[0082] FIG. 7 illustrates a first variant embodiment. In this variant, the core 130 again comprises four core elements 131, 132, 133 and 137 having the same general configuration as those of the first example: thus, this core 130 allows to lead to a cooling circuit generally similar to that in FIG. 3.

[0083] However, in this first variant, the junction between the transverse portions (that is to say the discharge portions 131c, 132c, 133c) of the core elements 131, 132, 133 and their longitudinal portions (that is to say the ascending 131a or descending 132b, 133b portions as the case may be) is no longer done at right angles but through inclined surfaces 131f, 132f, 133f, both inside and outside the bend, if applicable. Accordingly, the cavities formed by these core elements 131, 132, 133 which are thus modified each have a passage section which gradually increases at the entrance to its discharge portion.

[0084] Therefore, in order to fill the space thus freed, and therefore continue to properly cool the entire surface of the outer walls of the blade, the fourth core element 137 also has an inclined surface 137f at its lower end, facing the inclined surface 133f of the third core element 133.

[0085] A second difference that this core 130 has in this first variant is the presence of openings 135 in the form of a crescent formed in the second and third core elements 132, 133 at the transition between the descending section 132b, 133b and the discharge section 132c, 133c of the considered core element 132, 133. These openings 135 thus result in the formation of deflectors in the ventilation cavities of the final blade facilitating the transition of direction at the inlet of the discharge portion.

[0086] FIG. 8 shows a second variant embodiment. In this variant, the cooling circuit 220 is generally similar to that of FIG. 3. However, in this variant, the geometry of the internal partition 226, separating each discharge portion 222c from the ascending portion 221a of the first ventilation cavity of the first type 221, is modified in order to reduce the bottleneck located at the border between the upstream section and the downstream section of each discharge portion 222c.

[0087] Consequently, in this variant, the same internal partition 226, which is continuous and without breaking the slope, extends from the intersection between the ascending sections 223a and 223b of the third ventilation cavity of the first type 223 and the ascending section 227a of the ventilation cavity of the second type 227, to the lower surface wall 216.

[0088] In addition, in this variant, the ascending portion 221a of the first ventilation cavity of the first type 221 has a triangular section and no longer a quadrangular section.

[0089] FIGS. 9 and 10 show a second example of a core 330 allowing to obtain a more complex cooling circuit composed of six ventilation cavities of the first type and a ventilation cavity of the second type. This core 330 comprises seven core elements 331, 332, 333, 334, 335, 336 and 337 disposed relative to each other in the desired geometry at the time of casting.

[0090] The first core element 331 has a longitudinal ascending portion 33a, and a transverse discharge portion 331c, having two end segments 331d intended to form two ports of the trailing edge.

[0091] The second to sixth core elements 332-336 are similar and each have a longitudinal ascending portion 332a-336a, a longitudinal descending portion 332b-336b, along the upper section of the ascending portion 332a-336a, and a transverse discharge portion 332c-336c. The descending portion 332b-336b of each core element 332-336 is as long as it settles away from the trailing edge. As with the first core element 331, each discharge portion 332c-336c has two end segments 332d-336d intended to form two ports of the trailing edge per ventilation cavity of the first type. Thus, in this second example, each ventilation cavity of the first type covers approximately one sixth of the length of the trailing edge.

[0092] The fourth core element 337, in turn, has a single longitudinal ascending portion 337a.

[0093] Although the present 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 claims. In particular, individual features of the different illustrated/mentioned embodiments can be combined in additional embodiments. Consequently, the description and the drawings should be taken in an illustrative rather than a restrictive sense.

[0094] It is also obvious that all the features described with reference to a method can be transposed, alone or in combination, to a device, and conversely, all the features described with reference to a device can be transposed, alone or in combination, to a method.