FR3164977A1 - Maintenance tools for aircraft equipment and associated process - Google Patents

Abstract

A maintenance tool (5) for aircraft equipment comprising a plurality of bladed stages, the aircraft equipment comprising an inner circumferential surface, the maintenance tool (5) comprising: a frame (6), a support member (7) configured to support the aircraft equipment, the support member (7) being mounted to rotate about a principal axis (Z) relative to the frame (6), the frame (6) comprising a cleaning system (8) having at least one cleaning nozzle (9) configured to project a cleaning fluid onto the inner circumferential surface of the aircraft equipment. Figure 4

Description

Maintenance tools for aircraft equipment and associated process

The present invention relates to the field of aircraft maintenance and more particularly to the maintenance of aircraft equipment.

Climate change is a major concern for many legislative and regulatory bodies worldwide. Indeed, various restrictions on carbon emissions have been, are being, or will be adopted by different countries. In particular, an ambitious standard applies to both new types of aircraft and those already in service, requiring the implementation of technological solutions to bring them into compliance with current regulations. Civil aviation has been actively working for several years now to contribute to the fight against climate change.

Technological research efforts have already led to very significant improvements in the environmental performance of aircraft. The Applicant takes into account the factors impacting all phases of design and development in order to obtain less energy-intensive and more environmentally friendly aeronautical components and products whose integration and use in civil aviation have moderate environmental consequences, with the aim of improving the energy efficiency of aircraft.

Consequently, the Applicant is constantly working to reduce its negative climate impact by using methods and operating virtuous development and manufacturing processes that minimize greenhouse gas emissions to the minimum possible in order to reduce the environmental footprint of its activity.

This sustained research and development work focuses on new generations of aircraft engines, the weight reduction of aircraft, particularly through the materials used and lighter on-board equipment, the development of the use of electrical technologies to provide propulsion, and, as essential complements to technological progress, aviation biofuels.

To this end, the invention is the result of technological research aimed at significantly improving aircraft performance and, in this sense, contributes to reducing the environmental impact of aircraft. To this end, the invention aims both to extend the lifespan of an aircraft turbomachine and to limit the aircraft's mass in order to reduce its fuel consumption.

As is well known, an aircraft includes one (or more) turbomachine(s) to enable its movement by accelerating an airflow. For this reason, with reference to the FIG. 1 , the turbomachine 1 includes a propulsion unit 10 mounted on a propulsion shaft 11, which converts the rotational motion into an airflow F which enables the propulsion of the aircraft.

To drive the rotation of the propulsion unit 10, the turbomachine 1 comprises, successively along a longitudinal axis A, a low-pressure compressor 2, a high-pressure compressor 31, a combustion chamber 32, a high-pressure turbine 33, and a low-pressure turbine 4. The high-pressure compressor 31, the combustion chamber 32, and the high-pressure turbine 33 form an assembly known to those skilled in the art as the "high-pressure unit" 3. The low-pressure compressor 2 is configured to receive an incoming airflow, corresponding in this example to a portion of the airflow F from the propulsion unit 10, and compress it to supply the high-pressure compressor 31, which supercompresses it to supply the combustion chamber 32. Combustion in the combustion chamber 32, between a fuel flow and the supercompressed airflow, generates an exhaust airflow that drives the high-pressure turbine 33 and the low-pressure turbine 4. rotation. The low-pressure turbine 4 drives, via the propulsion shaft 11, the low-pressure compressor 2 and the propulsion unit 10.

In practice, with reference to the FIG. 2 The low-pressure turbine 4 comprises, successively along the longitudinal axis A, a plurality of bladed stages, in particular a plurality of rotor wheels 42 and distributors 43. Each rotor wheel 42 has a disc 44 and a plurality of blades, the disc 44 being connected to the drive shaft 11 for its rotation. Each distributor 43, mounted between two rotor wheels 42, comprises a plurality of fixed blades, known as "straighteners," and configured to straighten the airflow from the preceding rotor wheel 42. A housing 41 extends radially around the rotor 42 and stator 43 stages.

To control the temperature in the turbine stages, it is known to circulate an airflow through orifices formed in the discs 44 of the rotor wheels 42. The orifice cross-section is calibrated to ensure a predetermined flow rate of the cold air. In practice, it is necessary to ensure that each orifice is not obstructed to avoid reducing the airflow rate, which would result in insufficient cooling.

However, when the aircraft is in flight, pollution particles (such as sand) are present in the airflow passing through the turbomachine and can be deposited on the turbine components. These pollution particles clog the cooling airflow passages of the 44 discs, leading to the aforementioned drawbacks. Furthermore, the amount of sand deposited is significant, which can substantially increase the turbomachine's mass, thereby increasing the aircraft's fuel consumption and consequently its environmental impact. Therefore, periodic turbine maintenance is necessary, particularly to clear the cooling airflow passages.

It is known to perform water cleaning on a turbine, but these operations are lengthy and tedious. Furthermore, it is difficult to guarantee a high-quality cleaning and complete removal of pollution particles.

The invention aims to eliminate at least some of these drawbacks by providing maintenance tools for aircraft equipment, such as aircraft turbines, that allow for the simple and efficient cleaning of debris and airborne pollution particles. The invention also aims to reduce aircraft weight to limit fuel consumption and thus its environmental impact, while ensuring optimal turbomachine performance.

PRESENTATION OF THE INVENTION

• au moins un bâti,
• au moins un organe de support configuré pour supporter l’équipement d’aéronef, l’organe de support étant monté mobile en rotation autour d’un axe principal par rapport au bâti,
• l’outillage de maintenance étant remarquable en ce que le bâti comprend un système de nettoyage comportant au moins une buse de nettoyage configurée pour injecter un fluide de nettoyage sur la surface circonférentielle intérieure de l’équipement d’aéronef.

The invention relates to a maintenance tool for the maintenance of aircraft equipment comprising a plurality of bladed stages, the aircraft equipment comprising an inner circumferential surface, the maintenance tool comprising:

• at least one building,
• at least one support member configured to support aircraft equipment, the support member being mounted to rotate movably about a main axis relative to the frame,
• The maintenance tooling is remarkable in that the frame includes a cleaning system comprising at least one cleaning nozzle configured to inject a cleaning fluid onto the inner circumferential surface of the aircraft equipment.

Thanks to the cleaning system, the maintenance equipment can remove polluting particles, such as sand, lodged in aircraft equipment and deposited during flight. The integration of a cleaning nozzle onto the frame, opposite which the aircraft equipment support is mounted for rotation, allows for convenient and rapid circumferential cleaning. The cleaning is advantageously uniform for each bladed stage.

Cleaning the equipment ensures that the openings in the rotor wheel discs for cooling airflow are not obstructed, guaranteeing proper airflow and therefore optimal cooling. Aircraft equipment cleaning thus extends the turbomachine's lifespan and reduces the number of components discarded, thereby minimizing the need for parts replacement. Furthermore, removing accumulated pollutants optimizes the turbomachine's performance. The aircraft's weight is also reduced, which lowers fuel consumption and consequently greenhouse gas emissions.

In one embodiment, the maintenance tooling incorporates the features of prior art maintenance tooling, such as the features of a turbine frame equipped with lifting and rotation systems. Furthermore, cleaning can be performed during a pre-scheduled maintenance operation for which the aircraft equipment has already been removed. This advantageously minimizes aircraft downtime.

In a preferred embodiment, the cleaning nozzle is mounted to move along the main axis, allowing the inner circumferential surface to be cleaned at several bladed stages. Different bladed stages can thus be cleaned circumferentially with a compact cleaning system.

According to a preferred design, the cleaning system comprises multiple cleaning nozzles spaced along the main axis, allowing simultaneous cleaning of the inner circumferential surface across several bladed floors. This enables simultaneous circumferential cleaning of multiple bladed floors, resulting in significant time savings.

In one embodiment, the cleaning system includes several mobile cleaning nozzles translating along the main axis, which allows for the successive cleaning of several series of bladed stages.

In one embodiment, the frame comprising a body extending in a plane orthogonal to the main axis, at least one cleaning nozzle of the cleaning system is mounted in the body, allowing simple mounting of the cleaning nozzle.

Alternatively or in addition, the frame includes a central column extending along the main axis, with at least one cleaning nozzle of the cleaning system mounted in the central column. This allows for reliable and efficient positioning of the cleaning nozzle, even for bladed stages located some distance from the support element, thus eliminating, for example, the risk of significant nozzle movement. Central positioning enables circumferential cleaning with consistent fluid pressure. The cleaning is advantageously homogeneous.

In one embodiment, the cleaning system includes a rail formed in the central column and extending along the main axis, the cleaning nozzle being mounted movable in the rail along the main axis, so as to be able to clean different bladed floors.

According to a preferred aspect, the cleaning system includes a rail extending along a radial axis orthogonal to the main axis, the cleaning nozzle is mounted movable in the rail along a radial direction, which allows the distance of the cleaning nozzle to be adapted to each bladed stage.

In one embodiment, the cleaning system comprises a plurality of cleaning nozzles distributed on the frame at different angular positions relative to the main axis, so as to simultaneously clean several angular portions of the inner circumferential surface of the aircraft equipment. This allows for faster cleaning of the entire inner circumferential surface of the bladed equipment.

According to one preferred aspect, the cleaning fluid projected by the cleaning nozzle is a cryogenic fluid, allowing for fast and efficient cryogenic blast cleaning.

Preferably, the cleaning fluid is projected through the cleaning nozzle at a pressure between 1 and 20 MPa, which ensures the removal of polluting particles from the inner circumferential surface.

According to a preferred aspect, the cleaning system includes a filter mounted on the frame and configured to filter out polluting particles detached from the inner circumferential surface during the cleaning of aircraft equipment, allowing for simple and quick cleaning of maintenance tools after use.

Preferably, the cleaning system includes a recovery tank mounted under the frame and configured to collect polluting particles and fluids after the aircraft equipment has been cleaned. The recovery tank allows, in particular, the collection of polluting particles that would not have been captured by the filter, as well as any cleaning liquids that are largely free of polluting particles.

The invention relates to an assembly of aircraft equipment and maintenance tooling as described above for the maintenance of aircraft equipment, the aircraft equipment being fixed on the support element of the maintenance tooling.

• projeter un fluide de nettoyage au travers d’au moins une buse de nettoyage sur la surface circonférentielle intérieure d’au moins un étage aubagé de l’équipement d’aéronef, et
• entrainer en rotation l’organe de support par rapport au bâti de manière à nettoyer au moins une portion angulaire de la surface circonférentielle intérieure d’au moins un étage aubagé de l’équipement d’aéronef.

The invention also relates to a method for cleaning aircraft equipment using the maintenance tooling as described above, the aircraft equipment being mounted on the support member of the frame for a maintenance operation, the method comprising the steps of:

• project a cleaning fluid through at least one cleaning nozzle onto the inner circumferential surface of at least one bladed stage of the aircraft equipment, and
• rotate the support member relative to the frame so as to clean at least an angular portion of the inner circumferential surface of at least one bladed stage of the aircraft equipment.

In one embodiment, when the inner circumferential surface of a first bladed stage is cleaned, the process includes a step of moving the cleaning nozzle along the main axis so as to allow the inner circumferential surface of another bladed stage to be cleaned.

PRESENTATION OF THE FIGURES

The invention will be better understood upon reading the following description, given by way of example, and referring to the following figures, given by way of non-limiting examples, in which identical references are given to similar objects.

There FIG. 1 is a schematic representation of an aircraft turbomachine.

There FIG. 2 is a perspective view of the low-pressure turbine of the turbomachine of the FIG. 1 in which only one canopy floor is represented.

There FIG. 3 is a close-up view of the low-pressure turbine of the turbomachine of the FIG. 1 .

There FIG. 4 is a schematic representation of a maintenance tool for aircraft equipment according to a first embodiment of the invention.

There FIG. 5 is a schematic representation of the maintenance tooling according to a second embodiment of the invention and of the aircraft equipment mounted opposite a cleaning nozzle.

There FIG. 6 is a schematic representation of the maintenance tooling according to a third embodiment of the invention.

There FIG. 7 is a schematic representation of the maintenance tooling according to a fourth embodiment of the invention.

It should be noted that the figures explain the invention in detail for implementing the invention, and these figures can of course be used to better define the invention where appropriate.

DETAILED DESCRIPTION OF THE INVENTION

The invention relates to the maintenance, and in particular the cleaning, of aircraft equipment comprising a plurality of bladed stages. In this example, the invention will be described for the maintenance of a low-pressure turbine of an aircraft turbomachine. It is understood that the invention applies similarly to the maintenance of any aircraft equipment comprising a plurality of bladed stages.

As is known, an aircraft includes one or more gas turbomachines to enable its movement by accelerating an airflow from upstream to downstream. For this reason, with reference to the FIG. 1 , the turbomachine 1 includes a propulsion unit 10 mounted on a propulsion shaft 11, which converts the rotational motion into an airflow F which enables the propulsion of the aircraft.

To drive the rotation of the propulsion unit 10, the turbomachine 1 comprises, successively along a longitudinal axis A, from upstream to downstream, a low-pressure compressor 2, a high-pressure compressor 31, a combustion chamber 32, a high-pressure turbine 33, and a low-pressure turbine 4. The high-pressure compressor 31, the combustion chamber 32, and the high-pressure turbine 33 form an assembly known to those skilled in the art as the "high-pressure unit" 3. The low-pressure compressor 2 is configured to receive an incoming airflow, corresponding in this example to a portion of the airflow F from the propulsion unit 10, and compress it to supply the high-pressure compressor 31, which supercompresses it to supply the combustion chamber 32. Combustion in the combustion chamber 32, between a fuel flow and the supercompressed airflow, generates an exhaust airflow that drives the high-pressure turbine. 33 and the rotating low-pressure turbine 4. The low-pressure turbine 4 drives, via the drive shaft 11, the low-pressure compressor 2 and the propulsion unit 10.

In practice, with reference to Figures 2 and 3, the low-pressure turbine 4 comprises, successively along the longitudinal axis A, a plurality of bladed stages, in particular a plurality of rotor wheels 42 and distributors 43. Each rotor wheel 42 has a disc 44 and a plurality of blades, the disc 44 being connected to the drive shaft 11 to drive it. Each distributor 43, mounted between two rotor wheels 42, comprises a plurality of fixed blades, known as "straighteners," configured to straighten the airflow from the preceding rotor wheel 42. A housing 41 extends radially around the rotor wheels 42 and the distributors 43. As is known, the low-pressure turbine 4 has an annular shape. The protective housing 41 has an inner circumferential surface 45 to which the distributors 43 are connected.

It is known to carry out maintenance operations on the low pressure turbine 4. For this, the turbomachine 1 is removed from the aircraft and the low pressure turbine 4 is isolated to be mounted on a maintenance tool 5.

A maintenance tool 5 according to the invention for the maintenance of the low-pressure turbine 4, shown in the FIG. 4 will now be described. It goes without saying that such maintenance tooling 5 is suitable for the maintenance of other bladed aeronautical equipment.

With reference to the FIG. 4 , the maintenance tooling 5 includes a base 51, for example fixed to the ground and which ensures the stability of the maintenance tooling 5, and a frame 6 connected to the base 51.

The frame 6 extends in a plane (X, Y) and along a principal axis Z orthogonal to the plane (X, Y), so as to form an orthogonal coordinate system (X, Y, Z). More precisely, the frame 6 comprises a body 61 extending in the plane (X, Y), and a column 62, fixedly connected to the body 61, extending along the principal axis Z. The column 62 is configured to extend centrally with respect to the housing 41 of the low-pressure turbine 4 when the latter is mounted on the frame 6, as shown in the figure. FIG. 5 . In practice, when the maintenance tooling 5 is not used and to allow the mounting of the low pressure turbine 4, the main axis Z extends substantially in a vertical direction from bottom to top, as shown in the figures.

Preferably, body 61 has a cylindrical shape to allow maintenance of cylindrical aircraft equipment.

Still referring to the FIG. 4 , the maintenance tooling 5 also includes a support element 7 connected to the body 61 of the frame 6 and configured to support the low pressure turbine 4.

The support member 7 extends radially around the periphery of the body 61 of the frame 6. Preferably, the support member 7 has an annular shape, complementary to the shape of the low pressure turbine 4 and is mounted to rotate freely around the main axis Z relative to the frame 6, to allow the rotation of the low pressure turbine 4 around the main axis Z around the body 61 and the column 62.

According to one aspect of the invention, the maintenance tooling 5 comprises a cleaning system 8 configured to clean the inner circumferential surface 45 of the aircraft equipment, in this example the low-pressure turbine 4. In particular, the cleaning system 8 is configured to clean the inner circumferential surface 45 of the low-pressure turbine 4 of polluting particles deposited during the operation of the turbomachine 1 while the aircraft is in flight. The polluting particles are, for example, sand that is deposited on the bladed stages of the low-pressure turbine 4.

Still referring to the FIG. 4 The cleaning system 8 includes one or more cleaning nozzle(s) 9, configured to inject a cleaning fluid F onto the inner circumferential surface 41 of the low-pressure turbine 4. For this purpose, each cleaning nozzle 9 is connected to a supply channel which is itself connected to a storage tank (not shown) for the cleaning fluid F.

In a first form of realization, represented on the FIG. 4 The cleaning system 8 includes a cleaning nozzle 9 mounted in the body 61 of the frame 6. In this example, the body 61 has a through orifice into which the cleaning nozzle 9 is inserted.

In one embodiment, the cleaning nozzle 9 is slidably mounted in a rail 60 formed in the body 61 of the frame 6. In this example, the rail 60 is formed in a radial direction in the (X, Y) plane which extends from the central column 62 towards the periphery of the body 61. Such mobility allows the cleaning nozzle 9 to reach each bladed stage so that they are all optimally cleaned.

Preferably, the cleaning nozzle 9 is mounted to move in translation along the main axis Z to allow it to reach bladed stages of the low-pressure turbine 4 positioned at different heights defined along the main axis Z. In this example, the translational movement of the cleaning nozzle 9 along the main axis 9 allows it to reach each bladed stage.

A cleaning system 8 comprising a single cleaning nozzle 9 is described; however, it is understood that the cleaning system 8 may alternatively comprise a plurality of cleaning nozzles 9 extending successively radially from the column 62 to the periphery of the body 61 of the frame 6, as shown in the FIG. 6 In this embodiment, each cleaning nozzle 9 preferably has a different height to allow the simultaneous cleaning of several bladed stages of the low-pressure turbine 4. This speeds up the cleaning process.

Alternatively or in addition, always with reference to the FIG. 6 , the cleaning system 8 includes several cleaning nozzles 9 mounted in the body 61 of the frame 6, preferably at different angular positions, so as to simultaneously clean several angular portions of the same bladed stage of the low-pressure turbine 4.

In a second form of realization, with reference to the FIG. 7 The cleaning system 8 includes one or more cleaning nozzle(s) 9 mounted in the column 62 of the frame 6. In this example, the column 62 has a through orifice into which the cleaning nozzle 9 is inserted. Such a central mounting is convenient for routing the supply lines to the cleaning nozzle 9.

In one embodiment, the cleaning nozzle 9 is slidably mounted in a groove 63 formed in the column 62 of the frame 6. In this example, the groove 63 is formed along the main direction Z, to allow the cleaning nozzle 9 to reach bladed stages of the low-pressure turbine 4 positioned at different heights defined along the main axis Z.

Preferably, the cleaning nozzle 9 is mounted to move radially in the (X, Y) plane extending from the central column 62 to the periphery of the body 61. This mobility allows the cleaning nozzle 9 to reach each bladed stage, ensuring optimal cleaning. An operator can thus precisely position the cleaning nozzle 9 to optimally clean a circumferential portion by adjusting its vertical and radial position to achieve the optimal fluid pressure for cleaning.

A single cleaning nozzle 9 mounted in the column 62 is described; however, it is understood that the cleaning system 8 may alternatively comprise a plurality of cleaning nozzles 9 extending successively in the column 62 at different heights along the principal axis Z, as shown in the FIG. 7 This allows for the simultaneous cleaning of several bladed stages of the low-pressure turbine 4.

Alternatively or in addition, always with reference to the FIG. 7 , the cleaning system 8 includes several cleaning nozzles 9 mounted in the column 62 of the frame 6, at different angular positions, so as to simultaneously clean several angular portions of the same bladed stage of the low pressure turbine 4.

It goes without saying that the cleaning system 8 can just as well include one or more cleaning nozzles 9 mounted in the body 61 of the frame 6 and one or more cleaning nozzles 9 mounted in the column 62.

As described previously, to clean the inner circumferential surface 41 of the aircraft equipment, each cleaning nozzle 9 projects a cleaning fluid F shown on the FIG. 6 .

Preferably, the cleaning fluid F is a cryogenic fluid. Accordingly, the cleaning fluid F is sprayed at a temperature of approximately -78.5°C. In this example, the cleaning of the inner circumferential surface 41 of the low-pressure turbine 4 is preferably carried out by cryogenic blasting.

Preferably, the cryogenic fluid F is selected from carbon dioxide pellets. In this example, the cryogenic fluid F is carbon dioxide in its solid state (dry ice), i.e., in the form of chips. In one aspect, the chips have a diameter of 3 mm and a length of 15 mm with a tolerance of 5 to 10%.

Preferably, the cleaning fluid F is projected from the cleaning nozzle 9 under a pressure of between 1 and 20 MPa and at a projection velocity of between 800 and 1000 km/h. Such pressure and projection velocity allow the cleaning fluid F to be generated with kinetic energy, creating an impact that, combined with cryogenic temperatures, facilitates the removal of polluting particles, as will be described in more detail later. By adjusting the gap between the cleaning nozzle 9 and the portion of the internal surface 41 to be cleaned, the cleaning force can be advantageously controlled.

In a preferred form of realization, with reference to the FIG. 6 , the cleaning system 8 includes a filter 81 mounted on the body 61 of the frame 6 and configured to filter polluting particles detached from the inner circumferential surface 41 during the cleaning of the low pressure turbine 4.

Preferably, the cleaning system 8 includes a recovery tank 82 mounted under the frame 6. The recovery tank 82 is preferably mounted under the body 61, so as to collect the polluting particles following the cleaning of the inner circumferential surface 41 of the aircraft equipment 4.

The recovery tank 82, combined with the filter 81, ensures the collection of all polluting particles, with filter 81 providing pre-filtration. Once the majority of polluting particles have been filtered, the cleaning fluids in liquid form can also be collected in the recovery tank 82 after being largely cleaned.

According to a preferred aspect, the body 61 and/or the column 62 comprise a plurality of known maintenance equipment as well as low-pressure turbine rotation systems 4 to perform on the same maintenance tooling 5 different low-pressure turbine maintenance operations 4. Thus, it is not necessary to dismantle and isolate the aircraft equipment only for its cleaning, which represents a significant time saving and limits the downtime of the aircraft on which the turbomachine is mounted.

A cleaning procedure for aircraft equipment using the maintenance tooling 5 described previously will now be described. In this example, the aircraft equipment is a low-pressure turbine 4. The low-pressure turbine 4 has been previously fixed to the support member 7 for maintenance. The cleaning system 8 in this example comprises a single cleaning nozzle 9 mounted in the body 61 of the frame 6 and positioned opposite one of the bladed stages of the low-pressure turbine 4. In this example, the cleaning is carried out by cryogenic blasting.

In a first step, a cleaning fluid F is projected, through the cleaning nozzle 9, in a radial direction onto the inner circumferential surface 41 of the low-pressure turbine 4. More precisely, the cleaning fluid 9 is projected locally onto the inner circumferential surface 41 of one of the bladed stages of the low-pressure turbine 4. In practice, in this example, carbon dioxide chips are projected by a flow of compressed air using a tool commonly referred to as a "blasting machine." The pressure and projection velocity create a cleaning fluid F charged with kinetic energy, which impacts the inner circumferential surface 41. The temperature difference between the cleaning fluid F and the inner circumferential surface 41 causes the polluting particles to detach. Upon impact, the cleaning fluid F transitions from a solid to a gaseous state.

In a second step, the support member 7 is driven in rotation about the main axis Z relative to the frame 6, so as to drive the low pressure turbine 4 in rotation and to clean at least an angular portion of the inner circumferential surface 41 of the bladed stage.

The polluting particles detach and fall under the effect of gravity. In this example, the polluting particles are retained in a filter 81 mounted on the body 61 of the frame 6 or are collected in a recovery tank 82 positioned under the frame 6.

When the entire inner circumferential surface 41 of the first bladed stage is cleaned, the cleaning nozzle 9 is moved, in this example, in a third step, along the principal axis Z to be positioned opposite a second bladed stage. The entire process is then repeated.

It goes without saying that the cleaning system could include several cleaning nozzles 9 to simultaneously clean several bladed stages and/or several angular portions of the same bladed stage of the low-pressure turbine, so as to allow faster cleaning of aircraft equipment.

In one implementation method, the cleaning of the inner circumferential surface 41 of the low-pressure turbine 4 is carried out at the same time as other maintenance operations, allowing for significant time savings, while limiting the downtime of the aircraft whose gas turbomachine has been removed.

Claims (12)

Maintenance tooling (5) for the maintenance of aircraft equipment (4) comprising a plurality of bladed stages, aircraft equipment (4) comprising an internal circumferential surface (45), maintenance tooling (5) comprising:

• at least one frame (6),
• at least one support member (7) configured to support aircraft equipment (4), the support member (7) being mounted to rotate movably about a principal axis (Z) relative to the frame (6),
• the maintenance tooling (5) being characterized in that the frame (6) includes a cleaning system (8) comprising at least one cleaning nozzle (9) configured to project a cleaning fluid (F) onto the inner circumferential surface (41) of the aircraft equipment (4).

Maintenance tooling (5) according to claim 1, in which the cleaning nozzle (9) is mounted movable in translation along the main axis (Z) so as to allow the cleaning of the inner circumferential surface (45) at the level of several bladed stages. Maintenance tooling (5) according to any one of claims 1 to 2, wherein the cleaning system (8) comprises a plurality of cleaning nozzles (9) spaced along the main axis (Z), so as to allow simultaneous cleaning of the inner circumferential surface (45) at several bladed stages. Maintenance tooling (5) according to any one of claims 1 to 3, wherein the frame (6) comprises a central column (62) extending along the main axis (Z), at least one cleaning nozzle (9) of the cleaning system (8) being mounted in the central column (62). Maintenance tooling (5) according to any one of claims 1 to 4, wherein the cleaning system (8) comprises a rail (60) extending along a radial axis (R) orthogonal to the main axis (Z), the cleaning nozzle (9) being movably mounted in the rail (60) along a radial direction. Maintenance tooling (5) according to any one of claims 1 to 5, wherein the cleaning system (8) comprises a plurality of cleaning nozzles (9) distributed on the frame (6) at different angular positions relative to the main axis (Z), so as to simultaneously clean several angular portions of the inner circumferential surface (41) of the aircraft equipment (4). Maintenance tooling (5) according to any one of claims 1 to 6, wherein the cleaning fluid (F) projected by the cleaning nozzle (9) is a cryogenic fluid. Maintenance tooling (5) according to any one of claims 1 to 7, wherein the cleaning fluid (F) is projected by the cleaning nozzle (9) at a pressure between 1 and 20 MPa. Maintenance tooling (5) according to any one of claims 1 to 8, wherein the cleaning system (8) comprises a filter (81) mounted on the frame (6) and configured to filter polluting particles detached from the inner circumferential surface (41) during the cleaning of aircraft equipment (4). Maintenance tooling (5) according to any one of claims 1 to 9, wherein the cleaning system (8) comprises a recovery tank (82) mounted under the frame (6) and configured to recover polluting particles following the cleaning of aircraft equipment (4). Assembly of aircraft equipment (4) and maintenance tooling (5) according to any one of claims 1 to 10 for the maintenance of aircraft equipment (4), the aircraft equipment (4) being fixed on the support member (7) of the maintenance tooling (5). A method for cleaning aircraft equipment (4) using maintenance tools (5) according to any one of claims 1 to 10, the aircraft equipment (4) being mounted on the support member (7) of the frame (6) for a maintenance operation, the method comprising the steps of:

• project a cleaning fluid (F) through at least one cleaning nozzle (9) onto the inner circumferential surface (41) of at least one bladed stage of the aircraft equipment (4),
• rotate the support member (4) relative to the frame (6) so as to clean at least an angular portion of the inner circumferential surface (41) of at least one bladed stage of the aircraft equipment (4).