Turbine engine comprising a straightening assembly

Abstract

The invention relates to a straightening assembly (28) comprising two radially inner and outer coaxial shells (34) between which extend vanes (36) made of composite material, fixed to a first end portion on the radially inner shell and to a second end portion on the radially outer shell, characterized in that: for each vane (36), in a plane perpendicular to the axis of the radially inner and outer shells (34), a straight line passing through a junction between said first and second end portions and the useful part forms an angle α with a radius of the radially inner shell, passing through the junction between said first end portion and the useful part of said vane (36), such that 0°<α≤30°; the radially inner shell has a diameter ranging from 1,000 mm to 1,600 mm; and in that the radially outer shell has a diameter ranging from 2,000 to 2,800 mm; the number of vanes (36) ranges from twenty-five to forty-five.

Claims

1. A dual-flow turbine engine (30) comprising a fan wheel (38) arranged at an upstream end of the turbine engine (30) and a straightening assembly (28) positioned axially downstream of the fan wheel (38), said assembly (28) comprising two radially inner and outer coaxial shells (32, 34) between which extend vanes (36) made of composite material, the radially inner shell (32) being arranged around a compressor and delimiting with the radially outer shell (34) an annular stream for the flow of a secondary air flow, the vanes (36) being fastened at a first end portion (44) on the radially inner shell (32) and at a second end portion (46) on the radially outer shell (34), the vanes (36) further comprising a useful part (48) extending between said first and second end portions (44, 46), characterized in that: a) for each vane (36), in a plane perpendicular to the axis of the radially inner and outer shells (32, 34), a straight line (d) passing through a junction between said first and second end portions (44, 46) and the useful part (48) forms an angle α with a radius (R) of the radially inner shell (32) passing through the junction between said first end portion (44) and the useful part (46) of said vane (36) such that 0°<α≤30°, b) the difference in radius between the inner (32) and outer (34) shells ranges from 200 to 900 mm; wherein the radially inner shell (32) comprises, on its radially outer periphery, breaks (56) forming walls that extend radially between a radially outer surface of a first portion of the radially inner shell (32) and a radially inner surface of a second portion of the radially inner shell (32), a pressure surface of the first end portion (44) of the vanes (36) resting against and fastened to said breaks.

2. The turbine engine according to claim 1, wherein the number of vanes (36) ranges from 25 to 45.

3. The turbine engine according to claim 2, wherein the radially inner shell (32) has a diameter ranging from 1,000 mm to 1,600 mm.

4. The turbine engine according to claim 3, wherein the angle α ranges from 10 to 30 degrees.

5. The turbine engine (30) according to claim 4, wherein the outer shell has a diameter from 2,000 to 2,800 mm.

6. The turbine engine (30) according to claim 3, wherein the diameter of the inner shell (32) ranges from 1,000 mm to 1,200 mm and the number of vanes (36) ranges from 30 to 40.

7. The turbine engine (30) according to claim 2, wherein the outer shell has a diameter from 2,000 to 2,800 mm.

8. The turbine engine according to claim 1, wherein the radially inner shell (32) has a diameter ranging from 1,000 mm to 1,600 mm.

9. The turbine engine (30) according to claim 1, wherein the diameter of the radially inner shell (32) is 1,000 mm, the angle α is 10° and the assembly comprises 45 vanes (36).

10. The turbine engine (30) according to claim 1, wherein the diameter of the radially inner shell (32) is 1,100 mm, the angle α is 30° and the assembly comprises 30 vanes (36).

11. The turbine engine (30) according to claim 1, wherein the diameter of the radially inner shell (32) is 1,200 mm, the angle α is 20° and the assembly comprises 36 vanes (36).

12. The turbine engine (30) according to claim 1, wherein the secondary stream lacks a structural arm upstream of the straightening assembly (28).

13. The turbine engine (30) according to claim 12, wherein the outer shell has a diameter from 2,000 to 2,800 mm.

14. The turbine engine (30) according to claim 1, wherein at least one among the first end portion (44) and the second end portion (46) is curved in a first direction that is circumferential with respect to the useful part of the vane.

15. The turbine engine (30) according to claim 14, wherein said first circumferential direction is directed towards a suction surface (52) of an adjacent vane (36).

16. The turbine engine (30) according to claim 14, wherein the second end portion (46) comprises a first strip for bonding to the radially outer shell (34) curved in the first circumferential direction with respect to the useful part (48) of the vane (36) and a second strip (34) for bonding to the radially outer shell curved in a second circumferential direction that is opposite to the first circumferential direction.

17. The turbine engine (30) according to claim 1, wherein the first end portion (44) is straight and extends in line with the useful part (48) of the vane (36).

18. The turbine engine (30) according to claim 1, wherein the radially inner shell (32) comprises a number of breaks (56) identical to the number of vanes (36) in the assembly (28).

19. The turbine engine (30) according to claim 1, wherein the outer shell has a diameter from 2,000 to 2,800 mm.

Description

BRIEF DESCRIPTION OF THE FIGURES

(1) The invention will be better understood and other details, characteristics, and advantages of the invention will appear on reading the following description given by way of non-limiting example and with reference to the accompanying drawings, in which:

(2) FIG. 1 is a schematic view of a straightening assembly of the prior art;

(3) FIG. 2 is a simplified half-section of a turbine engine comprising a straightening assembly according to the prior art;

(4) FIG. 3 is a simplified half-section of a turbine engine comprising a straightening assembly according to the invention;

(5) FIG. 4 is a simplified front view of the straightening assembly according to a first embodiment of the invention;

(6) FIG. 5 is a simplified front view of the straightening assembly according to a second embodiment of the invention;

(7) FIG. 6 is a simplified front view of the straightening assembly according to a third embodiment of the invention;

(8) FIG. 7 is a schematic view showing the fastening of the turbine engine according to a first embodiment of the invention;

(9) FIG. 8 is a schematic view showing the fastening of the turbine engine according to a second embodiment of the invention;

(10) FIG. 9 is a schematic view showing the fastening of a vane according to a first embodiment of the invention;

(11) FIG. 10 is a schematic view showing the fastening of a vane according to a second embodiment of the invention;

(12) FIG. 11 is a schematic view showing the fastening of a vane according to a third embodiment of the invention.

DETAILED DESCRIPTION

(13) In the following description, elements that are identical in the prior art and in the invention are designated using the same reference numbers.

(14) FIGS. 3 and 11 show several embodiments of a straightening assembly 28 according to the invention.

(15) A schematic representation of a half-section of a turbine engine 30 comprising the straightening assembly 28 according to the invention is shown in FIG. 3.

(16) It should be noted that the turbine engine 30 is free of structural arms downstream of the straightening assembly 28. In fact, in this case, it is the straightening assembly 28 itself that provides the structuring function, which the structural arms provide in the turbine engine of the prior art.

(17) This assembly 28 includes two respectively radially inner 32 and outer 34 coaxial shells between which extend vanes 36. The vanes 36 are advantageously made of composite material so as to reduce the mass of the straightening assembly 28.

(18) The outer shell 34 preferably has a diameter ranging from 1,000 to 1,600 mm.

(19) The number of vanes 36 equally preferably ranges from twenty-five to forty-five.

(20) As shown in FIG. 3, the straightening assembly 28 is placed downstream of a fan wheel 38, with the arrow 40 representing the direction of the air flow within the turbine engine 30 and the radially inner shell 32 surrounding the low-pressure compressor 42.

(21) The vanes 36 of the straightening assembly 28 are fastened to a first end portion 44 on the radially inner shell 32 and a second end portion 46 on the radially outer shell 34, and include a useful part 48 that extends between the two end portions 44, 46 and defines a pressure surface 50 and a suction surface 52 used to straighten the secondary flow so that if flows in a substantially laminar manner downstream of the straightening assembly 28.

(22) On the vanes 36, the pressure surface 50 is directed towards the radially inner shell 32 and the suction surface 52 is directed towards the radially outer shell 34.

(23) FIGS. 4 to 6 respectively show a straightening assembly 28 according to a first, second and third embodiment.

(24) In the first and second embodiments, shown in FIGS. 4 and 5, the assembly includes forty-five composite vanes 36.

(25) In the third embodiment, shown in FIG. 6, the assembly includes thirty composite vanes 36.

(26) Composite vanes 36 among others offer better resistance to tensile and compressive stresses than the metal vanes generally used in assemblies of the prior art.

(27) FIGS. 7 and 8 show two types of fastening F for mounting the turbine engine 30 onto an aircraft, the fastenings F being shown schematically in the figures.

(28) In the first type shown in FIG. 7, the turbine engine is fastened to the aircraft by its radially inner shell. Also, during operation, the rotation of the fan wheel 28, as shown by the dotted arrow in FIG. 7, imparts torsional stress to the shell, which has a tendency to make the radially outward shell rotate counter-clockwise when considering the direction of air flow. This rotational movement also causes the vanes of the assembly of the prior art operate under bending loads. However, in the assembly 28 of the present invention, the vanes operate under compressive loads.

(29) In the second type shown in FIG. 8, the turbine engine 30 is fastened to the aircraft by its radially outer shell 34. Therefore, during operation, the rotation of the fan wheel 38, as shown by the solid line arrow in FIG. 8, causes torsional stress on the shell, which has a tendency to make the radially inner shell rotate counter-clockwise when considering the direction of the air flow. This rotational movement then causes the vanes of the assembly of the prior art to operate under bending loads. However, in the assembly 28 of the present invention, the vanes 36 operate under tensile loads.

(30) Composite vanes 36 are inclined with respect to the radii R of the radially inner shell 32. More specifically, as shown in FIGS. 9 to 11, the useful part of each vane has an angular offset with respect to a radius R of the radially inner shell 32 passing through the fastening 54 between the vane 36 concerned and the radially inner shell 32.

(31) A straight line (reference “d” in FIGS. 9 to 11) is drawn through the junction between said first and second end portions 44, 46 and the useful part 48 of the vane 36, this straight line forming an angle α with the radius R of the radially inner shell, passing through the junction between the first end portion 44 and the useful part 48 of said vane 36, such that 0<α≤30°.

(32) In the first embodiment, shown in FIG. 4, the vanes 36 are inclined at an angle α of 10°.

(33) In the second and third embodiments, shown in FIGS. 5 and 6, the vanes 36 are inclined at an angle α of 30°.

(34) The formation of an angle α between the useful part 48 of the vane 36 and the radius R of the radially inner shell 32 reduces the formation of corner vortices between the pressure surface 50 of the vane 36 and the suction surface 52 of an immediately adjacent vane 36, at the level of the inner shell 32. This results in a better air flow and, therefore, a better efficiency of the turbine engine 30.

(35) Furthermore, this angle α also increases the service life of the vanes 36 compared to vanes of the prior art, since composite vanes 36 offer better tensile and compressive strength when they are inclined with respect to the radii R of the inner shell 32 to which they are fastened.

(36) The tables below provide examples of how to produce a straightening assembly according to the diameter of the radially inner shell 32 and to the diameter of the radially outer shell 34. For each diameter of the radially inner shell 32, various values can be combined, on the one hand, with the number of vanes and, on the other, with the value of the angle α. The difference in diameter specified in the table below is measured between the radially outer surface of the inner shell and the radially inner surface of the outer shell, for example at the axial level halfway along the chord of the vanes 36.

(37) TABLE-US-00001 Radial distance available to mount vanes between the inner and outer shells Alpha (in degrees) Number of vanes 200 Between 20 and 30 Between 25 and 40 200 Between 0 and 20 Between 25 and 45 900 Between 20 and 30 Between 25 and 35 900 Between 10 and 20 Between 25 and 40 900 Between 0 and 10 Between 25 and 45 Diameter of Diameter of the radially the radially inner shell outer shell Difference Number of (mm) (mm) in radius vanes Angle α (°) 1,000 2,000 500 25 30 1,000 2,800 900 25 30 1,000 2,800 900 30 20 1,000 2,000 500 36 10 1,000 2,400 700 40 15 1,000 2,800 900 45 10 1,100 2,300 600 30 30 1,200 2,000 400 36 20 1,300 2,300 500 36 20 1,400 2,600 600 45 10 1,600 2,800 600 45 15

(38) From this table, it can therefore be understood that, for a radially inner shell 32 having a given diameter, taking into account the size of the outer shell and the mechanical strength of the vanes, the number of vanes can change and the angle α can be such that 0°≤α≤30°, for example at least 3 degrees. FIGS. 9 to 11 also highlight different methods for fastening the vanes to the radially inner 32 and outer 34 shells. More specifically, for a given angle α, the greater the difference in radius between the inner and outer shells, the fewer vanes can be fitted from a geometrical standpoint. For a given value of difference in radius, the number of vanes can be increased by decreasing the angle. The diameter parameter of the radially inner shell 32 is taken into consideration for the largest values in terms of angle and number of vanes.

(39) In a first embodiment shown in FIG. 9, the first end portion 44 and the second end portion 46 used to fasten the vane 36 to the radially inner shell 32 and to the radially outer shell 34, respectively, may be curved to ensure that the angle α is observed.

(40) Thus, at least one of the end portions 44, 46 can be curved in a first circumferential direction with respect to the useful part 48 of the vane 36. Said first circumferential direction is advantageously directed towards the suction surface 52 of an adjacent vane 36.

(41) However, each end portion 44, 46 can also be curved in a second circumferential direction towards the pressure surface 50 of an adjacent vane 36.

(42) In FIG. 9, the first end portion 44 is curved in the second direction and the second end portion 46 is curved in the first direction.

(43) The second embodiment shown in FIG. 10 differs from the first embodiment in that the first end portion 44 of the vane 36 is straight and is substantially in line with the useful part 48 of the vane 36.

(44) To allow the first end portion 44 to be fastened, the radially inner shell 32 includes breaks 56 forming walls that extend radially and against which the first part 44 of the vanes 36 comes to rest.

(45) The third embodiment shown in FIG. 11 differs from the first embodiment in that the second end portion 46 of the vane 36 is divided into two bonding strips, also called debondings. A first bonding strip is curved in the first circumferential direction, i.e. in the circumferential direction with respect to the useful part of the vane 36 towards the suction surface 52 of an adjacent vane 36, and a second bonding strip is curved in a second circumferential direction opposite to the first circumferential direction.

(46) The embodiments of the vanes' 36 fastening to the shells 32, 34 particularly allow for the vanes 36 of the present invention to be simplified with respect to the vanes of the prior art. As a matter of fact, it is no longer necessary to provide the vane roots and tips with locking tabs to secure the vane to the shells, which form a substantially right angle with the useful part of the vane and therefore an area that is highly subject to mechanical stress.

(47) The vanes are advantageously fastened to the radially inner and outer shells by bolting 54 the end portions 44, 46 and bonding strips, if necessary, to said radially inner 32 and outer 34 shells.

(48) This fastening method offers the advantage of good mechanical resistance to the stress to which the vane 36 is subjected and allows for quick assembly and disassembly in order to facilitate and accelerate maintenance operations.

(49) The air flow straightening assembly 28 and the turbine engine 30 described above have many advantages, including the following: Better mechanical strength of the vanes 36 Better aerodynamic performance Mass gain and lower environmental impact Lower manufacturing cost and easy maintenance

(50) The good mechanical resistance of the vanes 36 is achieved by the way in which the vanes 36 are positioned, in particular the angle α, which allows the vanes 36 to operate both under tensile and compressive loads depending on the type of fastening used for the turbine engine 30. Unlike the vanes of the prior art, which mainly operate under bending loads, the vanes 36 of this straightening assembly 28 have a longer service life and greater fatigue strength.

(51) The aerodynamic performance is improved, compared to the prior art, by the way in which the vanes 36 are positioned, in particular owing to the angle α, which makes it possible to enlarge the suction surface 52 of the vanes 36 and therefore the useful part 48 of the vanes 36. Moreover, the fact that there is the angle α reduces the effects of vortices from the corner to the root of the 36 vanes. This results in a more laminar air flow, which increases the performance of the turbine engine 30.

(52) The performance of the turbine engine 30 is also increased by reducing the mass and thus reducing consumption. In fact, the removal of the structural arms of the prior art de facto leads to reducing the mass of the turbine engine 30, and, consequently, reduces its energy consumption, so that the turbine engine 30 has a lower environmental impact. Moreover, the use of composite materials, as opposed to using metallic materials, also reduces the mass of the turbine engine 30.

(53) Finally, manufacturing and maintenance costs are also reduced, in particular owing to the quick fastening (by bolting) of the vanes 36 on the radially inner 32 and outer 34 shells, which speeds up service calls by maintenance technicians. In addition, the fact that the vanes 36 can operate both under tensile and compressive loads also reduces their deterioration, which in turn reduces the frequency of preventive and/or curative maintenance periods.