MODULE FOR AN AIRCRAFT TURBOMACHINE

Abstract

The invention relates to a module (100) for an aircraft turbomachine, this module (100) comprising a rotor part (200) movable in rotation about an axis (X), and a stator part (300) mounted coaxially to the rotor part (200), the rotor part (200) comprising a longitudinal end (220) which is separated by a given distance (D) from an element (310) carried by the stator part (300), the rotor part (200) being capable of moving or expanding in operation along the axis (X) which generates variations of said distance (D). According to the invention, the module (100) further comprises a measuring system (400) capable of detecting and measuring these variations, this measuring system (400) comprising a sensor (320) carried by said element (310) and configured to cooperate with said longitudinal end (220) or a component (230) carried by this longitudinal end (220). Abbreviated figure: Figure 3

Description

Title of the invention: MODULE FOR AN AIRCRAFT TURBOMACHINE Technical field of the invention

[0001] The present invention relates in particular to a module for an aircraft turbomachine and the aircraft turbomachine comprising such a module. Technical background

[0002] As is known, a turbomachine is intended to provide the thrust necessary for the propulsion of an aircraft. It classically comprises, from upstream to downstream with respect to the direction of gas flow within the turbomachine, a fan, a low-pressure compressor, a high-pressure compressor, a combustion chamber, a high-pressure turbine, a low-pressure turbine, and an exhaust nozzle.

[0003] Controlling the axial clearances of the turbomachine, i.e., the clearances in the longitudinal direction of the turbomachine, is important. This control is particularly important downstream of the turbomachine, notably for validating low-pressure turbine clearances (blower holes, turbomachine length), and for dimensioning bearing raceways with rolling elements such as rollers or balls, seal raceways, abradable lengths of labyrinth seals, non-contact clearances downstream of the engine, etc.

[0004] There are two solutions for measuring these axial clearances. The first involves the use of wear indicators. This solution specifically involves positioning felt pads at relevant locations on the turbomachine, determined by analysis, and measuring the wear at the end of a test campaign. This solution thus makes it possible to determine the minimum clearance during operation, but not to associate it with the moment of maximum wear, because the clearances are not measured in real time but only at the end of the test campaign.

[0005] The second solution involves using X-rays to measure axial clearances. Unlike the first solution, this method allows for real-time determination of axial clearances, but its implementation is expensive and requires an isolated and protected implementation environment.

[0006] The present invention proposes a simple, effective and economical solution to the need mentioned above. Summary of the invention

[0007] The invention relates to a module for an aircraft turbomachine, this module comprising a rotor part that rotates about an axis, and a part of The stator is mounted coaxially upstream or downstream of the rotor part. The rotor part has a longitudinal end separated by a given distance from an element carried by the stator part and located axially opposite this longitudinal end. The rotor part is capable of moving or expanding during operation along its axis, which causes variations in this distance. According to the invention, the module further comprises a measuring system capable of detecting and measuring these variations. This measuring system is centered on the axis and includes a sensor carried by said element and configured to cooperate with said longitudinal end or a component carried by this longitudinal end.

[0008] The measurement system of the invention is simple to implement in the module, inexpensive, and allows for real-time measurement of the axial clearances between the rotor and stator components. Compared to existing solutions (particularly the X-ray solution), the invention offers the advantage of being less expensive, easier to install, and does not require positioning in an isolated environment.

[0009] The module according to the invention may comprise one or more of the following features, taken individually or in combination with each other: • the sensor is configured to cooperate by contact with said longitudinal end or said organ; • the sensor is configured to cooperate without contact with said longitudinal end or said organ; • the sensor is chosen from a capacitive sensor, an optical sensor and a hydraulic sensor; • the hydraulic sensor is in the form of a cylinder and includes a cylinder body fixed to the element and a piston rod movable relative to the cylinder body and on which the element is able to bear weight; • the organ is axially projecting on said longitudinal end and is oriented towards said sensor; • the organ has an elongated shape and comprises a first longitudinal end integral with the longitudinal end of the rotor part, and a second longitudinal end opposite its first longitudinal end and configured to cooperate with said sensor; • the second longitudinal end of the organ is shaped into a point or a disc; • the organ is centered on said axis. • the sensor is axially projected on said element and is oriented towards said longitudinal end; • the sensor is connected to an information processing device; • the longitudinal end of the rotor part is axially mounted to slide in a tubular part of the stator part which carries at least one annular sealing gasket around this longitudinal end; • the rotor part is a degassing tube and the stator part is mounted downstream of a downstream longitudinal end of the degassing tube; • the element is a flame-resistant cartridge; • The degassing tube is mounted coaxially in a turbine shaft, the rotor part being liable to move or expand during operation inside this turbine shaft.

[0010] The invention further relates to an aircraft turbomachine, comprising at least one module as described above. Brief description of the figures

[0011] Other features and advantages will become apparent from the following description of a non-limiting embodiment of the invention with reference to the accompanying drawings in which:

[0012] [Fig-1] [Fig.1] is a schematic axial cross-sectional view of a turbomachine aircraft,

[0013] [Fig.2] [Fig.2] is a partial schematic view of a turbomachine degassing tube,

[0014] [Fig.3] [Fig.3] is a larger-scale schematic view of [Fig.2], and illustrates one embodiment of the invention,

[0015] [Fig. 4a-4c] Figures 4a-4c illustrate variations in axial clearances when the The turbomachine is in operation, during takeoff and engine shutdown, and

[0016] [Fig.5] [Fig.5] is a view similar to [Fig.3] and illustrates another embodiment of the invention. Detailed description of the invention

[0017] Referring to [Fig. 1], we see a turbomachine 1, which conventionally comprises a fan S, a low-pressure compressor 1a, a high-pressure compressor 1b, a combustion chamber 1e, a high-pressure turbine Id, and a low-pressure turbine 1e. The high-pressure compressor 1b includes rotors connected to the high-pressure turbine Id by a high-pressure shaft 5 or HP. The low-pressure compressor 1a includes rotors connected to the low-pressure turbine 1e by a low-pressure shaft 4 or LP. The turbomachine 1 is thus of the double-shaft type, HP and LP, although this example is not limiting. The fan S is carried by a fan shaft 3, which is connected by a reduction gear 7 to The BP 4 shaft. The reducer 7 is here of the epicyclic or planetary type. This reducer 7 is optional.

[0018] The HP and BP shafts extend along an X axis which is the axis of rotation of the turbomachine 1. In the following description, the notions of longitudinal or radial, and of inside or outside, are relative to this X axis.

[0019] The turbomachine 1 includes structural housings. The HP body is held by two structural housings: the inter-compressor housing and the inter-turbine housing, and the LP body is held by at least two structural housings: the intermediate housing 2 and the inter-turbine housing and / or the exhaust housing 6.

[0020] The intermediate housing 2 supports bearings of the turbine shaft BP 4 which are housed in a front or upstream enclosure denoted EL. The exhaust housing 6 supports bearings of the turbine shaft BP 4 which are housed in a rear or downstream enclosure denoted E2.

[0021] The enclosures E2, E2 are generally partially delimited by bearing supports. These bearings are lubricated with oil to optimize their operation and dissipate the thermal energy produced.

[0022] To evacuate this flow of oiled gases, the turbomachine includes a degassing tube ([Fig.2]), also commonly called a “CVT” tube for the English acronym “Center Vent Tube”, extending along the X axis, and mounted coaxially inside the low-pressure turbine shaft.

[0023] Venting of the enclosure El is thus carried out by the degassing tube 20 which passes axially through the turbine shaft BP 4, from the upstream enclosure El to an ejection cone 6a of the turbomachine.

[0024] Fig. 2 illustrates an example of a degassing tube 20 which can be used in the context of the invention.

[0025] The degassing tube 20 is made in several sections in the example shown and comprises an upstream section 20a, an intermediate section 20b and a downstream section 20c. The sections 20a, 20b, 20c are coaxial and extend one behind the other, their opposite axial ends being nested one inside the other.

[0026] The upstream section 20a is configured to be attached to the turbine shaft BP and includes independent sealing means intended to cooperate with an input shaft 8 of the reducer 7. These sealing means are not visible here and are, for example, formed by an annular seal.

[0027] A module 100 according to the invention is illustrated in Figures 3 to 5. Such a module 100 comprises a rotor part 200 that rotates about an axis, here the X-axis, and a stator part 300 mounted coaxially downstream of the rotor part 200. The rotor part 200 is, for example, a degassing tube as shown in [Fig. 2]. The stator part 300 is mounted, in particular, downstream of a downstream longitudinal end (220). of the degassing tube. Alternatively, the stator part could be mounted upstream of the rotor part.

[0028] The rotor part 200 includes, for example, a longitudinal end 220 which is separated by a given distance D from an element 310. The element 310 is in particular supported by the stator part 300 and is in particular located axially opposite the longitudinal end 220. The element 310 is in particular integral with the stator part 300. The element 310 is, for example, a flame-resistant cartridge.

[0029] Flame-resistant cartridges, for example, are designed to force the front of a flame through channels too narrow to allow the flame to propagate. The channels can be regular or irregular and made of wire mesh or sintered metal. At the heart of the flame-resistant cartridge's operation are flame cells, which represent areas where the flames interact with the cartridge's internal structure. These flame cells facilitate flame extinguishing and heat dissipation.

[0030] The longitudinal end 220 of the rotor part 200 is preferably mounted axially sliding in a tubular part 305 of the stator part 300 which carries at least one annular sealing gasket 306 around this longitudinal end 220.

[0031] During operation of the turbomachine, the rotor part 200 is likely to move or expand along the X axis, which can cause variations in the distance D. The variations in this distance D are representative of the variations in the axial clearance between the rotor part 200 and the stator part 300. When the rotor part 200 is a vent tube, the rotor part 200 is thus likely to move or expand during operation inside the low-pressure turbine shaft.

[0032] When the turbomachine is running but the aircraft is stationary (Figure 4a), component 230 (or the distal end 220) is at a first distance DI from element 310. Furthermore, during aircraft takeoff (Figure 4b), component 230 (or the distal end 220) is at a second distance D2 from element 310, which is greater than the first distance DI. In addition, when the turbomachine is stationary (Figure 4c), component 230 (or the distal end 220) is at a third distance D3 from element 310, this third distance being less than both the second distance D2 and the first distance DI. Each of the first, second, and third distances D1, D2, and D3 is variable.

[0033] Module 100 of the invention includes, in particular, a measuring system 400 capable of detecting and measuring these variations. The measuring system 400 is, for example, centered on the X-axis and includes a sensor 320. The sensor 320 may, in particular, be a capacitive or optical sensor (Figures 3 and 4a, 4b, 4c) or even a hydraulic sensor ([Fig. 5]).

[0034] The sensor 320 is in particular carried by the element 310. The sensor 320 is in particular configured to cooperate with the longitudinal end 220 or as illustrated in the figures, with a member 230 carried by this longitudinal end 220. The sensor is for example axially projecting on the element 310 and is in particular oriented towards the longitudinal end 220.

[0035] The sensor 320 is in particular connected to an information processing device 450. The information processing device 450 makes it possible in particular to calculate the value of the distance D and therefore the axial clearance between the rotor part 200 and the stator part 300 from the readings of the sensor 320.

[0036] The choice of the degassing tube for the rotor part 200 and the flame-resistant cartridge for the element 310 allows enough space to be available to install the system measuring 400 which has a certain size, and offers an environment not too exposed to thermal and mechanical stresses.

[0037] The member 230 is, for example, axially projecting from the longitudinal end 220 and is, in particular, oriented towards the sensor 320, i.e., here, downstream. The member 230 is, in particular, centered on the axis A and has, in particular, an elongated shape. The member 230 comprises, in particular, a first longitudinal end 231 integral with the longitudinal end 220 of the rotor part 200, and a second longitudinal end 232, for example, opposite its first longitudinal end 231 and configured to cooperate with the sensor 320. The second longitudinal end 232 of the member 230 is, in particular, shaped into a disc 234 (Figures 3, 4a, 4b and 4c).

[0038] The installation of the organ 230 and the sensor 320 on the module 100 is done in such a way as not to obstruct the air passage section (in particular so as not to disrupt the degassing function of the enclosures E2, E2 when the rotor part 200 is a degassing tube).

[0039] In the embodiment illustrated in Figures 3, 4a, 4b and 4c, the sensor 320 is configured, in particular, to cooperate without contact with the member 230 (or the longitudinal end 220). This is especially the case when the sensor 320 is capacitive. In this case, the member 230 and the sensor 320 together form a capacitor whose plates are formed by the disk 234 of the member 230 on one side and the element 310 on the other, and whose air gap is the clearance between the plates.

[0040] In other words, the capacitor air gap is the distance between component 230 and element 310, and therefore the distance between rotor part 200 and stator part 300, i.e., the axial clearance. A variation in the air gap, and thus in the axial clearance, leads to a variation in the capacitor's conductance, which sensor 320 measures. This allows the information processing device 450 to determine the axial clearance. Alternatively, if sensor 320 is optical, it measures Optically, the distance separating it from organ 230 or longitudinal end 220 without them coming into contact with each other. The optical sensor 320 thus allows the distance D to be measured.

[0041] Figure 5 is similar to Figure 3 but illustrates an embodiment of the invention in which the sensor 320 is a hydraulic sensor 330. The hydraulic sensor 330 is in particular in the form of a cylinder and includes, for example, a cylinder body 340 integral with the element 310. The hydraulic sensor 330 includes, in particular, a piston rod 350 movable relative to the cylinder body 340 and on which the member 230 is, for example, able to bear. Thus, when the rotor part 200 moves or expands along the X-axis, the member 230 moves, in particular along the X-axis, and displaces the piston rod 350 since the member 230 and the piston rod 350 are in contact. The piston rod 350 in turn moves, in particular along the X axis, inside the cylinder body 340.The interior of the cylinder body 340 then undergoes a pressure variation dependent on the movement of the piston rod 350 and therefore on the variation of the distance D and the axial play.

[0042] The hydraulic sensor 330 measures pressure variations inside the cylinder body 340, which are directly related to variations in axial play. The information processing device 450 then determines the axial play using the hydraulic sensor 330. The hydraulic sensor 330 thus allows the axial play to be determined at any time during operation (or when not in operation) of the turbomachine. According to this embodiment, the sensor 320 is configured to cooperate by making contact with the longitudinal end 220 or the component 230.

[0043] The second longitudinal end 232 of the component 230 is shaped here into a point 233. Specifically, the point 233 is in contact with the piston rod 350. The point 233 extends longitudinally along the X-axis and, in particular, downstream. The point 233 allows, in particular, the decoupling of the rotational movement of the rotor part 200 from the stator part 300, specifically the decoupling of the rotational movement of the rotor part 200 from the piston rod 350. Indeed, when the rotor part 200 is rotating, the point 233 rotates but does not cause the piston rod 350 to rotate.

[0044] A return spring 360 can be located around the piston rod 350. The return spring 360 is located in particular against a downstream end of the piston rod 350 and against an upstream wall of the cylinder body 340. The return spring makes it possible to maintain permanent axial contact between the member 230 and the piston rod 350.

[0045] Thanks to the invention, the variations in axial play during operation, but also when the turbomachine is stopped, are thus captured in real time by the measurement system 400.

Claims

Demands

1. Module (100) for an aircraft turbomachine (1), said module (100) comprising a rotor part (200) movable in rotation about an axis (X), and a stator part (300) mounted coaxially upstream or downstream of the rotor part (200), the rotor part (200) comprising a longitudinal end (220) which is separated by a given distance (D) from an element (310) carried by the stator part (300) and which is located axially opposite this longitudinal end (220), the rotor part (200) being capable of moving or expanding during operation along the axis (X) which generates variations in said distance (D), characterized in that the module (100) further comprises a measuring system (400) capable of detecting and measuring these variations,this measuring system (400) being centered on the axis (X) and comprising a sensor (320) carried by said element (310) and configured to cooperate with said longitudinal end (220) or a component (230) carried by this longitudinal end (220).

2. Module (100) according to claim 1, wherein the sensor (320) is configured to cooperate by contact with said longitudinal end (220) or said member (230).

3. Module (100) according to claim 1, wherein the sensor (320) is configured to cooperate without contact with said longitudinal end (220) or said member (230).

4. Module (100) according to any one of the preceding claims, wherein the sensor (320) is selected from a capacitive sensor, an optical sensor and a hydraulic sensor (330).

5. Module (100) according to claim 4, wherein the hydraulic sensor (330) is in the form of a cylinder and comprises a cylinder body (340) integral with the element (310) and a piston rod (350) movable relative to the cylinder body (340) and on which the member (230) is able to bear.

6. Module (100) according to any one of the preceding claims, wherein the member (230) is axially projecting on said longitudinal end (220) and is oriented towards said sensor (320).

7. Module (100) according to claim 6, wherein the member (230) has an elongated shape and comprises a first longitudinal end (231) integral with the longitudinal end (220) of the rotor part (200), and a second longitudinal end (232) opposite its first longitudinal end (231) and configured to cooperate with said sensor (320).

8. Module (100) according to claim 6 or 7, wherein the second longitudinal end (232) of the member (230) is shaped into a point (233) or a disc (234)

9. Module (100) according to any one of the preceding claims, wherein the component (230) is centered on said axis (X).

10. Module (100) according to any one of the preceding claims, wherein the sensor (320) is axially projecting on said element (310) and is oriented towards said longitudinal end (220).

11. Module (100) according to any one of the preceding claims, wherein the sensor (320) is connected to an information processing device (450).

12. Module (100) according to any one of the preceding claims, wherein the longitudinal end (220) of the rotor part (200) is axially slidably mounted in a tubular portion (305) of the stator part (300) which carries at least one annular sealing gasket (306) around this longitudinal end (220).

13. Module (100) according to any one of the preceding claims, wherein the rotor part (200) is a degassing tube and the stator part (300) is mounted downstream of a downstream longitudinal end (220) of the degassing tube.

14. Module (100) according to claim 13, wherein the element (310) is a flame-resistant cartridge.

15. Module (100) according to claim 13 or 14, wherein the degassing tube is mounted coaxially in a turbine shaft, the rotor part (200) being capable of moving or expanding during operation inside this turbine shaft.

16. Aircraft turbomachine, comprising at least one module (100) according to any one of the preceding claims.

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