MODULE FOR AN AIRCRAFT TURBOMACHINE

Abstract

Module (100) for an aircraft turbomachine (1), this module (100) comprising a rotor part (200) movable in rotation about an axis (X), and a stator part (300), the rotor part (200) comprising an external cylindrical surface (210) surrounded by a part of the stator part (300), the rotor part (200) being capable of moving or expanding in operation along the axis (X) which generates axial sliding of the external cylindrical surface (210) inside said part of the stator part (300). According to the invention, the module (100) further comprises a measuring system (400) capable of detecting and measuring these sliding movements, this measuring system (400) comprising a series of annular bands (220) located on said external cylindrical surface (210) and a sensor (310) configured to detect the axial sliding movements of the bands (220). (Shorthand figure: Figure 2)

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] Control of axial clearances of the turbomachine is important and in particular control of axial clearances downstream of the turbomachine, especially to validate low pressure turbine clearances (purges, turbomachine length), and dimensioning of bearing raceways with rolling elements such as rollers or balls, raceways of seals, lengths of abradables of labyrinth seals, non-contact clearances downstream of the engine, etc.

[0004] There are two solutions for measuring these axial clearances. The first involves wear indicators. This solution involves using felt pads at relevant locations determined by analysis and measuring the wear at the end of a testing period. This solution makes it possible to determine the minimum clearance during operation, but not to associate it with the moment of maximum wear.

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

[0006] The present invention provides a simple, effective and economical solution to the aforementioned problems of the prior art. Summary of the invention

[0007] The invention relates to a module for an aircraft turbomachine, this module comprising a rotor part movable about an axis, and a stator part mounted coaxially at least partially around the rotor part, the rotor part having an external cylindrical surface surrounded by a portion of the stator part, the rotor part being capable of moving or expanding in operation along the axis which generates axial sliding of the external cylindrical surface inside said part of the stator piece.

[0008] According to the invention, the module further comprises a measurement system capable of detecting and measuring these sliding movements, this measurement system comprising a series of annular bands which are located on said external cylindrical surface and which are arranged axially next to each other, at least some of the bands having at least one different physical property, and in that the module further comprises a sensor attached to said part and oriented towards the external cylindrical surface, this sensor being configured to detect the axial sliding movements of the bands.

[0009] The module of the invention, and in particular the presence of the measurement system, is simple to implement and allows for real-time measurement of axial play. Compared to existing solutions (notably the solution using X-rays), the invention has the advantage of being less expensive, easier to install, and does not require an isolated environment.

[0010] 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 without contact with the strips; • the sensor is chosen from a capacitive sensor and an optical sensor; • The sensor is oriented radially with respect to said axis and includes a measuring end directed towards the external cylindrical surface; • said at least one physical property is chosen from an electrical property and an optical property; • said at least one physical property is chosen from luminance and electrical conductivity; • the series of bands includes first dielectric bands and second electrically conductive bands which are intercalated between the first bands so that each first band is separated from an adjacent first band by one of the second bands, and each second band is separated from an adjacent second band by one of the first bands; • the first bands are formed by an annular dielectric layer deposited on the external cylindrical surface, and the second bands are formed by the absence of this layer on the external cylindrical surface which is electrically conductive; • The bands have at least two different optical properties, and include first bands with a first optical property and second bands with a second property which are interleaved between the first strips so that each first strip is separated from an adjacent first strip by one of the second strips, and that each second strip is separated from an adjacent second strip by one of the first strips; • the bands all have different optical properties; • it further includes at least one annular sealing gasket mounted between said part and the external cylindrical surface, the sensor being located next to this gasket; • the seal is of the JRS type and / or labyrinth; • it further includes at least one roller bearing mounted between said part and the external cylindrical surface, the sensor being located next to this bearing; • The sensor is connected to an information processing device.

[0011] The invention further relates to an aircraft turbomachine, comprising at least one module as described above. Brief description of the figures

[0012] 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:

[0013] [Fig-1] [Fig.1] is a schematic axial cross-sectional view of a turbomachine aircraft,

[0014] [Fig.2] [Fig.2] is a schematic axial cross-sectional view of part of a module according to the invention forming part of the turbomachine of [Fig.1],

[0015] [Fig. 3a-3c] Figures 3a-3c illustrate variations in axial clearances when the The turbomachine is in operation, during takeoff and engine shutdown, and

[0016] [Fig.4] [Fig.4] is a view similar to [Fig.2] 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 LP shaft 4. The reduction gear 7 is of the epicyclic or planetary type. The turbomachine 1 also includes, for example, an ejection cone 6a located downstream. 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 El, E2 are generally partially delimited by bearing supports. These bearings are lubricated with oil to optimize their operation and dissipate the thermal energy produced. Seals are positioned to ensure the sealing of the enclosures El, E2. The bearings may, in particular, be roller bearings. The bearings and / or seals form the interface between the stators and the rotors.

[0022] The turbomachine 1 also includes a module 100 according to the invention, as illustrated in particular in Figures 2 to 4. Such a module 100 comprises a rotor part 200 that rotates about an axis, here the X-axis. The rotor part 200 is a component of one of the turbomachine rotors mentioned above. The module 100 also includes a stator part 300 mounted coaxially, at least partially, around the rotor part 200. The stator part 300 is a component of one of the turbomachine stators mentioned above.

[0023] The rotor part 200 includes, for example, an external cylindrical surface 210. The external cylindrical surface 210 is in particular surrounded by a portion 305 of the stator part 300. The rotor part 200 is particularly likely to move or expand along the X-axis, especially during the operation of the turbomachine, which can generate, for example, axial sliding (along the X-axis) of the external cylindrical surface 210 inside the portion 305 of the stator part 300. These axial sliding or relative axial displacements of the rotor part 200 with respect to the stator part 300 can be defined as a carriage movement.

[0024] According to the invention, the module 100 further comprises a measuring system 400 capable of detecting and measuring these sliding movements (figures 2 and 3a, 3b, 3c).

[0025] The measuring system 400 comprises, for example, a series of annular bands 220 located on the external cylindrical surface 210 and arranged axially side by side. In other words, the bands 220 are situated one after the other along the X-axis on the external cylindrical surface 210, that is, they are oriented outwards from the rotor part 200. At least some of the bands 220 have at least one different physical property compared to other bands 220. In particular, the bands 220 have a predetermined width.

[0026] The module 100 includes in particular a sensor 310, in particular attached to the part 305 and oriented towards the external cylindrical surface 210. The sensor 310 is therefore located on the stator part 300 opposite the external surface 210 on which the bands 220 are located.

[0027] The sensor 310 is, for example, configured to detect the axial movement of the strips 220. The sensor 310 is specifically configured to cooperate without contact with the strips 220. The sensor 310 is, for example, oriented radially with respect to the X-axis and includes a measuring end 311 directed towards the external cylindrical surface 210. The measuring end 311 is configured to detect the presence and physical properties of the strips 220.

[0028] Thus, since the 220 strips do not all have the same physical properties, the sensor 310 can in particular recognize certain physical properties of some of the 220 strips that pass in front of it following the displacement or expansion of the rotor part 200 on which the 220 strips are located. By recognizing the 220 strip that is in front of it, or that passes in front of it, the sensor 310 thus allows the measuring system 400 to measure in real time the distance of the 220 strips from an origin point along the X axis, that is to say the displacement of the rotor part 200 relative to the stator 300 along the X axis, and therefore the axial clearances of the module 100.

[0029] The bands 220 thus form lines, which the sensor 310 is able to detect during the passage of these lines, i.e. during the sliding of the rotor part 200, thus allowing the relative displacement between the rotor part 200 and the stator part 300 to be determined.

[0030] The sensor 310 is in particular connected to an information processing device 402. It is in particular the information processing device 402 which determines the value of the sliding of the rotor part 200 vis-à-vis the stator as a function of the axial scrolls of the bands 220 detected by the sensor 310.

[0031] In particular, when the turbomachine is running but the aircraft is stationary (Figure 3a), the rotor part 200 moves a first distance and the measuring end 311 of the sensor 310 detects one of the bands 220 located opposite it, allowing the measuring system 400 to deduce the value of this first distance. Furthermore, During aircraft takeoff (Figure 3b), the rotor part 200 moves along a second distance, and the measuring end 311 of sensor 310 detects one of the bands 220 located opposite it, allowing the measuring system 400 to deduce the value of this second distance. Furthermore, when the turbomachine is stationary (Figure 3c), the rotor part 200 moves along a third distance, and the measuring end 311 of sensor 310 detects one of the bands 220 located opposite it, allowing the measuring system 400 to deduce the value of this first distance.

[0032] According to a first embodiment, the physical property that is varied for each band 220 is an electrical property, and in particular the electrical permittivity. The sensor 310 is then, notably, a capacitive sensor 310.

[0033] According to this embodiment, the series of strips 220 comprises, for example, first dielectric strips 221 and, in particular, second electrically conductive strips 222 interleaved between the first strips 221. Each first strip 221 is then separated from an adjacent first strip 221 by one of the second strips 222, and each second strip 222 is separated from an adjacent second strip 222 by one of the first strips 221. Thus, the capacitive sensor 310 detects the number of times there has been a change in physical properties in the strips 220 passing in front of it, that is, the number of times a first dielectric strip 221 has changed to a second electrically conductive strip 222. The first strips 221 are, for example, formed by an annular dielectric layer deposited on the external cylindrical surface 210.The second bands 222 are formed in particular by the absence of this layer on the external cylindrical surface 210, which is electrically conductive. It is understood here that the second bands 222 are formed by parts of the cylindrical surface 210, located in particular between the first bands 221.

[0034] Thus, with the relative displacement of the rotor part 200 with respect to the stator part 300, one moves from a dielectric band 221 to its electrically conductive neighbor 222. The capacitance of the capacitor formed by the measuring system 400 changes (different permittivity), and the signal variation allows the capacitive sensor 310 to detect the band change and the measuring system to deduce the displacement variation. Indeed, at a given axial position, the capacitance of the capacitor formed by the measuring system depends here on the permittivity of the insulator of the corresponding band 220.

[0035] According to a second embodiment of the invention, the physical property that is varied for each band 220 is an optical property, and in particular luminance. The sensor 310 is then, for example, an optical sensor.

[0036] According to this embodiment, the 220 bands have at least two different optical properties. The 220 bands include, for example, first 221 bands having a first optical property and second bands 222 having in particular a second property which are intercalated between the first bands 221. Each first band 221 is in particular separated from an adjacent first band 221 by one of the second bands 222. Each second band 222 is in particular separated from an adjacent second band 222 by one of the first bands 221.

[0037] In the case where the strips 220 have two different optical properties, the first strips 221 having a first optical property and the second strips 222 having a second optical property different from the first, the measuring system 400 of the invention operates similarly to the embodiment shown above, in which the first strips 221 have a first electrical property and the second strips 222 have a second electrical property. In particular, the optical sensor 310 detects the number of changes in optical property as the strips 221, 222 pass in front of the optical sensor 310 during the movements of the rotor part 200.

[0038] According to one embodiment, the 220 bands all have different optical properties. In this latter case, the optical sensor 310 is able to detect exactly which 220 band is in front of it.

[0039] The module 100 includes, for example, at least one annular sealing gasket 330 (Figures 2, 3a, 3b and 3c) mounted between the part 305 of the stator piece 300 and the external cylindrical surface 210. The sensor 310 is located next to this gasket 330. The annular sealing gasket 330 is, for example, of the JRS type and / or labyrinth type.

[0040] The module 100 includes in particular at least one roller bearing 331 ([Fig.4]) mounted between the part 305 of the stator piece and the external cylindrical surface 210. The sensor 310 is in particular located next to the bearing 331.

Claims

Demands

1. Module (100) for an aircraft turbomachine (1), said module (100) comprising a rotor part (200) rotatable about an axis (X), and a stator part (300) mounted coaxially at least partially around the rotor part (200), the rotor part (200) comprising an external cylindrical surface (210) surrounded by a portion (305) of the stator part (300), the rotor part (200) being capable of moving or expanding during operation along the axis (X) which generates axial sliding of the external cylindrical surface (210) within said portion (305) of the stator part (300), characterized in that the module (100) further comprises a measuring system (400) capable of detecting and measuring this sliding, this measuring system (400) comprising a series of annular bands (220) which are located on said external cylindrical surface (210) and which are arranged axially next to each other,at least some of the bands (220) having at least one different physical property, and in that the module (100) further comprises a sensor (310) integral with said part (305) and oriented towards the external cylindrical surface (210), this sensor (310) being configured to detect axial scrolls of the bands (220).

2. Module (100) according to claim 1, wherein the sensor (310) is configured to cooperate without contact with the bands (220).

3. Module (100) according to any one of the preceding claims, wherein the sensor (310) is selected from a capacitive sensor and an optical sensor.

4. Module (100) according to any one of the preceding claims, wherein the sensor (310) is oriented radially with respect to said axis (X) and includes a measuring end (311) directed towards the external cylindrical surface (210).

5. Module (100) according to any one of the preceding claims, wherein said at least one physical property is selected from an electrical property and an optical property.

6. Module (100) according to claim 5, wherein said at least one physical property is selected from luminance and electrical conductivity.

7. Module (100) according to claim 5 or 6, wherein the series of strips comprises first dielectric strips (221) and electrically conductive second strips (222) which are intercalated between the first strips (221) so that each first strip (221) is separated from an adjacent first strip (221) by one of the second strips (222), and that each second strip (222) is separated from an adjacent second strip (222) by one of the first strips (221).

8. Module (100) according to claim 7, wherein the first bands (221) are formed by a dielectric annular layer deposited on the external cylindrical surface (210), and the second bands (222) are formed by the absence of this layer on the external cylindrical surface (210) which is electrically conductive.

9. Module (100) according to claim 5 or 6, wherein the bands (220) have at least two different optical properties, and comprise first bands (221) having a first optical property and second bands (222) having a second property which are intercalated between the first bands (221) such that each first band (221) is separated from an adjacent first band (221) by one of the second bands (222), and each second band (222) is separated from an adjacent second band (222) by one of the first bands (221).

10. Module (100) according to claim 5 or 6, wherein the bands (220) all have different optical properties.

11. Module (100) according to any one of the preceding claims, wherein it further comprises at least one annular sealing gasket (330) mounted between said part (305) and the external cylindrical surface (210), the sensor (310) being located next to this gasket (330).

12. Module (100) according to claim 11, wherein the seal (330) is of the JRS and / or labyrinth type.

13. Module (100) according to any one of claims 1 to 10, wherein it further comprises at least one roller bearing (331) mounted between said part (305) and the external cylindrical surface (210), the sensor (310) being located next to this bearing (331).

14. Module (100) according to any one of the preceding claims, wherein the sensor (310) is connected to an information processing device (402).

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