Turbine shaft of a turbomachine and method for protecting against overspeed of said shaft

Abstract

A turbine shaft of a turbomachine extending along a longitudinal axis (A) includes a main tubular portion with a length L1 and a maximum outer main diameter. The shaft further includes a secondary tubular segment with a length L2 and a maximum outer secondary diameter greater than the maximum outer main diameter. The secondary tubular segment extends radially from the shaft such that the main tubular portion extends on either side of the secondary tubular segment along the longitudinal axis (A). The secondary tubular segment includes a weak point that is configured to break the shaft into two distinct parts when the value of a tangential stress applied to the shaft exceeds a predetermined threshold value, and thus cause retraction of the turbine.

Claims

1. A turbine shaft of a turbomachine extending along a longitudinal axis (A), comprising a main tubular portion of length L1 and having a maximum outer main diameter, the turbine shaft further comprising a secondary tubular segment of length L2 and having a maximum outer secondary diameter larger than the maximum outer main diameter, the secondary tubular segment extending radially from the main tubular portion such that the main tubular portion extends on either side of the secondary tubular segment along the longitudinal axis (A), the secondary tubular segment comprising a weak section configured to break the shaft into two distinct parts when the value of a tangential stress applied to the shaft exceeds a predetermined threshold value, wherein the weak section comprises a thinned portion having a maximum inner diameter larger than a minimum inner secondary diameter of said secondary tubular segment, the thinned portion having a maximum outer diameter equal to the maximum outer secondary diameter.

2. The turbine shaft according to claim 1, wherein the maximum outer secondary diameter is at least 1.8 times larger than the maximum outer main diameter.

3. The turbine shaft according to claim 1, wherein the length L2 is greater than 0.3 times the maximum outer diameter of the thinned portion.

4. The turbine shaft according to claim 1, wherein the thinned portion extends over not more than 80% of the length L2.

5. The turbine shaft according to claim 1, wherein the thinned portion comprises at least one tooth that extends radially from the thinned portion.

6. The turbine shaft according to claim 1, wherein the thinned portion comprises a plurality of teeth that extend radially from the thinned portion, the plurality of teeth being evenly distributed over the thinned portion.

7. The turbine shaft according to claim 1, wherein at least one through-hole is formed in the secondary tubular segment.

8. The turbine shaft according to claim 1, wherein the weak section is formed on at least one angular sector of the secondary tubular segment.

9. A turbomachine, comprising a turbine comprising the turbine shaft according to claim 1, the secondary tubular segment being arranged downstream of a thrust bearing configured to guide the shaft.

10. A method for protecting against overspeed of a turbine shaft of a turbomachine according to claim 1, the method comprising a step of breaking the weak section when the value of a tangential stress applied to the shaft exceeds a predetermined threshold value.

11. The turbine shaft according to claim 1, wherein the secondary tubular segment is arranged downstream of a thrust bearing configured to guide the shaft.

12. The turbine shaft according to claim 1, wherein the turbine shaft is a low pressure shaft.

13. A turbine shaft of a turbomachine extending along a longitudinal axis (A), comprising a main tubular portion of length L1 and having a maximum outer main diameter, the turbine shaft further comprising a secondary tubular segment of length L2 and having a maximum outer secondary diameter larger than the maximum outer main diameter, the secondary tubular segment extending radially from the main tubular portion such that the main tubular portion extends on either side of the secondary tubular segment along the longitudinal axis (A), the secondary tubular segment comprising a weak section configured to break the shaft into two distinct parts when the value of a rotational speed of the shaft exceeds a predetermined threshold value.

14. The turbine shaft according to claim 13, wherein the maximum outer secondary diameter is at least 1.8 times larger than the maximum outer main diameter.

15. The turbine shaft according to claim 13, wherein the weak section comprises a thinned portion having a maximum inner diameter larger than a minimum inner secondary diameter of said secondary tubular segment, the thinned portion having a maximum outer diameter equal to the maximum outer secondary diameter.

16. The turbine shaft according to claim 13, wherein the length L2 is greater than 0.3 times the maximum outer diameter of the thinned portion.

17. The turbine shaft according to claim 13, wherein the thinned portion extends over not more than 80% of the length L2.

18. The turbine shaft according to claim 13, wherein the thinned portion comprises at least one tooth that extends radially from the thinned portion.

19. The turbine shaft according to claim 13, wherein the thinned portion comprises a plurality of teeth that extend radially from the thinned portion, the plurality of teeth being evenly distributed over the thinned portion.

20. The turbine shaft according to claim 13, wherein the weak section is formed on at least one angular sector of the secondary tubular segment.

Description

DESCRIPTION OF THE FIGURES

(1) The invention will be better understood and other details, characteristics and advantages of the invention will appear more clearly when reading the following description as a non-limitative example and with reference to the annexed drawings in which:

(2) FIG. 1 is a half-view in axial section of a turbomachine according to the prior art,

(3) FIG. 2 is a half-view in axial section of a part of a turbomachine according to the invention, and

(4) FIG. 3 is an enlarged axial section view of a part of a turbine shaft of a turbomachine according to the invention,

(5) FIG. 4 is a perspective view of a turbine shaft of a turbomachine according to an embodiment of the invention,

(6) FIG. 5 is a side view of the turbine shaft of FIG. 4,

(7) FIG. 6 is a front view of the turbine shaft of FIG. 4, and

(8) FIG. 7 is a half axial section view of the turbine shaft of FIG. 4.

DETAILED DESCRIPTION

(9) FIG. 1 shows an aircraft turbomachine 10, which is here a turbofan engine with dual flow and dual casing. In a known manner, the turbomachine 10 comprises, from upstream to downstream in the direction of flow of the gas flow F in the turbomachine, a fan 12, a low-pressure compressor 14, a high-pressure compressor 16, an annular combustion chamber 18, a high-pressure turbine 20 and a low-pressure turbine 22.

(10) The rotors of the high-pressure compressor 16 and the high-pressure turbine 20 are connected by a high-pressure shaft 24 and form a high-pressure body with it. The rotors of the low-pressure compressor 14 and the low-pressure turbine 22 are connected by a low-pressure shaft 26 and form a low-pressure casing. The high-pressure and low-pressure shafts extend along a longitudinal axis A of the turbomachine 10.

(11) The fan 12 comprises blades 28 which are connected to a fan shaft 30. The fan shaft 30 can be connected to the low-pressure shaft 26 by means of a reduction gear 32, e.g. of the epicyclic train type.

(12) The turbomachine 10 also comprises a fan casing 34 which extends around the blades 28, is carried by aerodynamic arms 36, and defines an inlet air duct of the flows F. A part of this air enters an inner annular flow duct 38 of a primary flow and the other part feeds an outer annular flow duct 40 of secondary flow. The duct 38 passes through the low-pressure 14 and high-pressure compressors 16, the combustion chamber 18, and the high-pressure 20 and low-pressure turbines 22. The outer duct 40 surrounds the compressor and turbine casings and joins the inner duct 38 at a nozzle 42 of the turbomachine 10.

(13) The high-pressure 24, low-pressure 26 and fan 30 shafts are centred and guided in rotation around the axis A by bearings, e.g. rolling bearings. The fan shaft 30 is supported here by an upstream bearing 44 and a downstream bearing 46. The high-pressure shaft 24 is supported by an upstream bearing 48 and a downstream bearing 50, while the low-pressure shaft 26 is supported by four bearings 52, 54, 56 and 58.

(14) The upstream 48 and downstream 50 bearings of the high pressure shaft 24 are usually mounted at least partly on the high pressure shaft.

(15) The first bearing 52 of the low-pressure shaft 26 is located furthest upstream of the low-pressure shaft 26 and is mounted on the low-pressure shaft 26 and downstream of the reduction gear 32. The second, third and fourth bearings 54, 56, 58 of the low-pressure shaft 26 are mounted at least partly on the low-pressure shaft 26.

(16) The turbomachine in FIG. 1 comprises four enclosures 60, 62, 64 and 66, namely an enclosure 60 housing the two fan bearings 44 and 46, the reduction gear 32 and the low-pressure bearing 52, an enclosure 62 housing the low-pressure bearing 54 and the upstream high-pressure bearing 48, an enclosure 64 housing the downstream high-pressure bearing 50, and an enclosure 66 housing the low-pressure bearings 56 and 58.

(17) Because the rotational speed of the high-pressure shaft 24 is high, and the stresses transmitted from the rotors of the high-pressure compressor 16 and the high-pressure turbine 20 to the stators of the compressor and of the turbine through the upstream 48 and downstream 50 bearings, these bearings are lubricated and cooled as a result of the bearing heat from friction. Similarly, because the rotational speed of the low-pressure shaft 26 and the stresses transmitted from the rotors of the low-pressure compressor 14 and the low-pressure turbine 22 to the compressor and turbine stators by means of bearings 52, 54, 56 and 58 are high, these bearings are lubricated and cooled.

(18) The lubrication of the bearings is generally carried out with oil and is carried out inside the enclosures 60, 62, 64 and 66, in order to limit the oil consumption of the turbomachine and to contain the oil to avoid any risk of ignition within the turbomachine 10.

(19) FIG. 2 shows a turbine shaft of the turbomachine 10, here the low-pressure shaft 26, connecting means 67 between the low-pressure shaft 26 and the turbine rotor (not shown) and two discs 69 of the rotor of the turbine.

(20) In accordance with the invention, and as shown in FIG. 2, the low-pressure shaft 26 comprises a main tubular portion 68 of length L1 and having a given maximum outer main diameter.

(21) Since the turbine shaft has a tubular shape, the outer main diameter corresponds to the outer diameter of the main tubular portion 68, and the inner main diameter corresponds to the inner diameter of the main tubular portion 68.

(22) The outer main diameter of the main tubular portion 68 may vary along the axis A. The maximum outer main diameter is defined as the largest outer diameter of the main tubular portion 68 along the axis A. Similarly, the minimum outer main diameter is defined as the smallest outer diameter of the main tubular portion 68 along the axis A. For example, in FIG. 2, the maximum outer main radius R1 and the minimum outer main radius R2 are shown.

(23) The inner main diameter of the main tubular portion 68 may vary along the axis A. The maximum inner main diameter is defined as the largest inner diameter of the main tubular portion 68 along the axis A. Similarly, the minimum inner main diameter is defined as the smallest inner diameter of the main tubular portion 68 along the axis A. For example, in FIG. 2, the maximum inner main radius R3 and the minimum inner main radius R4 are shown.

(24) In other words, the thickness of the main tubular portion 68, that is, the difference between the outer main radius and the inner main radius, may vary along the axis A.

(25) The turbine shaft also comprises a secondary tubular segment 70.

(26) In particular, the turbine shaft is monolithic, i.e. the main tube portion 68 and the secondary tube segment 70 are monolithic.

(27) The secondary tubular segment 70 has a length L2 and a given maximum outer secondary diameter.

(28) The outer secondary diameter corresponds to the outer diameter of the secondary tubular portion 70, and the inner secondary diameter corresponds to the inner diameter of the secondary tubular portion 70.

(29) The outer secondary diameter of the secondary tubular portion 70 may vary along the axis A. The maximum outer secondary diameter is defined as the largest outer diameter of the secondary tubular portion 70 along the axis A. Similarly, the minimum outer secondary diameter is defined as the smallest outer diameter of the secondary tubular portion 70 along the axis A. For example, in FIG. 2, the maximum outer secondary radius R10 is shown.

(30) The inner secondary diameter of the secondary tubular portion 70 may vary along the axis A. The maximum inner secondary diameter is defined as the largest inner diameter of the secondary tubular portion 70 along the axis A. Similarly, the minimum inner secondary diameter is defined as the smallest inner diameter of the secondary tubular portion 70 along the axis A. For example, in FIG. 2, the minimum inner secondary radius R11 is shown.

(31) In other words, the thickness of the secondary tubular portion 70, i.e. the difference between the outer secondary radius and the inner secondary radius, may vary along the axis A.

(32) The maximum outer secondary radius is larger than the maximum outer main radius.

(33) Preferably, the maximum outer secondary diameter is at least 1.8 times larger than the maximum outer main diameter.

(34) The length L2 may be less than the length L1, as shown in FIG. 2. In other words, the secondary tubular segment 70 may correspond to a local increase of the diameter of the shaft in relation to the main diameter. Of course, the length L2 can be approximately equal to or greater than the length L1.

(35) Advantageously, the secondary tubular segment 70, the maximum outer secondary diameter of which is larger than the maximum outer main diameter of the main tubular portion 68, extending locally with respect to the main tubular portion 68, makes it possible to limit the size of the shaft.

(36) The secondary tubular segment 70 may extend, for example, over one end of the shaft, or substantially in the middle of the shaft. More generally, the secondary tubular segment 70 can be arranged on any part of the shaft.

(37) Preferably, the secondary tubular segment 70 extends radially protruding from the shaft 26, and thus from the main tubular portion 70, so that the main tubular portion 68 extends on either side of the secondary tubular segment 70 along the axis A.

(38) In other words, the secondary tubular segment 70 is arranged so that on either side of the secondary tubular segment 70 the diameter of the shaft is smaller than the diameter of the secondary tubular segment 70.

(39) Thus, a part of the main tubular portion 68 extends on one side of the secondary tubular segment 70 and another part of the main tubular portion 68 extends on the other side of the secondary tubular segment 70 along the axis A.

(40) As shown in FIG. 2, the secondary tubular segment 70 has a general “U” shape. The secondary tubular segment 70 comprises a first portion 80 extending substantially radially with respect to the axis A, followed by a second portion 82 extending substantially axially, followed by a third portion 84 extending substantially radially with respect to the axis A. Thus, the second portion 82 connects the first and third portions 80, 84.

(41) The length of the second portion 82 of the secondary tubular segment 70 is substantially equal to the length L2. The height, i.e. the radial dimension relative to the axis A, of the first and third portions 80, 84 of the secondary tubular segment 70 is substantially equal to the maximum outer secondary radius R10.

(42) The secondary tubular segment 70 comprises a weak section 72 configured to break the shaft 26 into two distinct parts when the value of a tangential stress applied to the shaft exceeds a predetermined threshold value. In other words, the weak section 72 is intended to break when the value of a tangential stress applied to the shaft is greater than a threshold value. Advantageously, the weak section 72 is configured to be the only one to break the shaft 26 into two distinct parts when the value of a tangential stress applied to the shaft exceeds a predetermined threshold value.

(43) The tangential stress depends on the density and tangential speed of the shaft. The tangential speed of the shaft depends on the rotational speed and the outer radius of the shaft.

(44) As the shaft radius increases, the value of the tangential stress increases. Likewise, as the rotation speed of the shaft increases, the value of the tangential stress increases.

(45) The value of the tangential stress can be determined by measuring the tangential speed of the shaft, since the density of the shaft is a determinable or given physical data. Specifically, the value of the tangential stress can be determined by measuring the rotational speed of the shaft, since the radius of the shaft is a determinable or given physical data.

(46) A threshold value of the tangential stress can be determined by setting a maximum tangential shaft speed not to be exceeded, i.e. by setting a maximum shaft speed not to be exceeded.

(47) Advantageously, the weak section 72 arranged on the secondary tubular segment 70 of the shaft, having a maximum outer secondary diameter larger than the maximum outer main diameter, makes it possible to have the tangential stress which generates the breakage of the weak section 72, and not a torsional stress due to the torque.

(48) A torsional stress, also called shear stress, is dependent on the torque, the outer radius of the shaft or the calculated torsional stress and the inertia of the shaft, the inertia of the shaft being proportional to the diameter of the shaft.

(49) As the radius of the calculated torsional stress increases, the inertia increases, and the value of the torsional stress decreases.

(50) The main tubular portion 68 of the shaft is torque-sensitive, but not very sensitive to rotational speed. In other words, the tangential stress is low for the main tubular portion 68, while the shear stress is high.

(51) The secondary tubular segment 70 of the shaft is sensitive to rotational speed, but not very sensitive to the torque. In other words, since the secondary tubular segment 70 has a maximum outer secondary diameter larger than the maximum outer main diameter, the tangential stress is high for the secondary tubular segment 70, while the shear stress is low.

(52) The weak section 72 can be formed over at least one angular sector of the secondary tubular segment 70. In other words, only part of the secondary tubular segment 70 can form the weak section 72.

(53) The weak section 72 can be formed over a plurality of angular sectors, e.g. evenly distributed, around the axis A.

(54) The weak section 72 can be annular. In other words, the secondary tubular segment 70 can comprise the weak section 72 all around the axis A. In other words, the entire secondary tube segment 70 can form the weak section 72.

(55) The weak section 72 may comprise a thinned portion 74. A thinned portion 74 corresponds to a portion of the weak section 72, and thus of the secondary tubular segment 70, whose thickness, i.e. the distance between the outer secondary radius and the inner secondary radius, is reduced in relation to the rest of the secondary tubular segment 70.

(56) The thinned portion 74 may extend over not more than 80% of the length L2. Preferably, the thinned portion 74 extends over at least 50% of the length L2.

(57) Advantageously, the thinned portion 74 extends over at most 80% of the length L2, which makes it possible not to weaken the secondary tubular segment 70, while making it possible to have a weak section on said secondary tubular segment configured to break the shaft into two distinct parts when the value of the tangential stress applied to the shaft exceeds a predetermined threshold value.

(58) The thinned portion 74 can be formed on at least one angular sector of the weak section 72, and thus of the secondary tubular segment 70. In other words, only a part of the weak section 72 can comprise a thinned portion 74.

(59) The thinned portion 74 can be formed on a plurality of angular sectors, for example evenly distributed, around the axis A.

(60) The thinned portion 74 can be tubular. In other words, the weak section 72 may comprise, all around the axis A, a thinned tubular portion 74.

(61) The outer diameter of the thinned tubular portion 74 may vary along the axis A. The maximum outer diameter of the thinned tubular portion 74 is defined as the largest outer diameter of the thinned tubular portion 74 along the axis A. Similarly, the minimum outer diameter of the thinned tubular portion 74 is defined as the smallest outer diameter of the thinned tubular portion 74 along the axis A. For example, in FIG. 2, the maximum outer radius of the thinned tubular portion 74 is equal to the maximum outer secondary radius R10.

(62) The inner diameter of the thinned tubular portion 74 may vary along the axis A. The maximum inner diameter of the thinned tubular portion 74 is defined as the largest inner diameter of the thinned tubular portion 74 along the axis A. Similarly, the minimum inner diameter of the thinned tubular portion 74 is defined as the smallest inner diameter of the thinned tubular portion 74 along the axis A. For example, in FIG. 2, the maximum inner radius R12 of the thinned tubular portion 74 is shown, and is equal to the maximum inner secondary radius.

(63) In particular, the maximum inner diameter of the thinned tubular portion 74 may be larger than the minimum inner secondary diameter. In other words, the maximum inner diameter of the thinned tubular portion 74 may be larger than the minimum inner diameter of the secondary tubular segment 68 outside the thinned tubular portion.

(64) The maximum outer diameter of the thinned tubular portion 74 may be equal to the maximum outer secondary diameter. In other words, the maximum outer diameter of the thinned tubular portion 74 and the minimum outer diameter of the secondary tubular segment 68 may be equal.

(65) The length L2 may be greater than 0.3 times the maximum outer diameter of the thinned tubular portion 74.

(66) As shown in FIG. 3, the secondary tubular segment 70 may comprise one or more through-holes 76. For example, two through-holes 76 arranged on either side of the thinned portion 74 are shown in FIG. 3.

(67) The through-holes 76 may be formed on an angular sector of the secondary tubular segment 70 around the axis A, or they may be evenly distributed over the secondary tubular segment 70 with respect to the axis A.

(68) A through-hole 76 can be formed in the weak section 72, and more precisely in the thinned portion 74.

(69) A through-hole 76 may have any cross-sectional shape, in particular a circular, oval or polygonal cross-section.

(70) Advantageously, at least one through-hole 76 formed in the secondary tubular segment 70 allows the weak section 72 to decorrelate the torsional and tangential stresses. In other words, the presence of a through-hole in the secondary tubular segment allows the shaft to break at high speed, rather than at high torque.

(71) In addition, a through-hole 76 allows for the removal of any oil that may have accumulated in the event of a leak in a lubricated enclosure 60, 62, 66 extending around the shaft.

(72) The secondary tubular segment 70 can be arranged downstream of a thrust bearing for guiding the shaft. For example, the secondary tubular segment 70 can be arranged downstream of the bearing 56 of the low pressure shaft 26.

(73) Advantageously, in the event of an overspeed start resulting from the breakage of the shaft, here the low-pressure shaft, downstream of the bearing 56, the weak section 72 allows the rotor of the low-pressure turbine 22 to move backwards, which allows the vanes of said rotor to be broken, for example via a cambered in the stator vanes of the low-pressure turbine 22, and consequently to slow down said rotor.

(74) FIGS. 4 to 7 show an embodiment of the low-pressure shaft 26. This embodiment can be based on all the characteristics shown in FIGS. 1 to 3.

(75) In FIG. 7, the maximum outer radius of the thinned portion 74 is smaller than the maximum outer secondary radius R10 and the maximum inner radius of the thinned portion 74 is equal to the minimum inner secondary radius R11.

(76) In addition, the secondary tubular segment 70, specifically the thinned portion 74 of the weak section 72, may comprise one or a plurality of radially extending teeth 86 protruding from the thinned portion 74.

(77) The plurality of teeth 86 can be formed on at least one angular sector around the axis A, or on a plurality of angular sectors, e.g. evenly distributed, around the axis A, or all around the axis A.

(78) The teeth 86 can be arranged substantially in the middle of the thinned portion 74.

(79) A tooth 86 may be of a general parallelepipedal shape, as shown in FIGS. 4 to 7.

(80) A tooth 86 may extend substantially radially to the axis A, as shown in FIG. 7.

(81) The teeth 86 may be spaced apart so that teeth 86 are evenly distributed over the thinned portion 74. Alternatively, the teeth 86 can be unevenly distributed over the thinned portion 74.

(82) The teeth 86 make it possible to locally increase the radius of the thinned portion 74, which makes it possible during an overspeed start by the centrifugal force, to be able to tear off the thinned portion 74 and thus to break the weak section 72.

(83) The invention also relates to a method for protecting against overspeed of a turbine shaft as described above.

(84) The method comprises a step of breaking the weak section 72 when the value of a tangential stress applied to the shaft exceeds a predetermined threshold value. In other words, the method comprises a step of breaking the turbine shaft into two distinct parts when the value of a tangential stress applied to the shaft exceeds a predetermined threshold value.

(85) This breaking step advantageously allows the tangential stress that generates the breaking of the weak section, and not the torsional stress due to the torque. This allows advantageously a breakage of the weak section at high speed, and not at high torque.