Equipment for a turbomachine drive system, drive system, turbomachine and associated aircraft

Abstract

Equipment (18) for a drive system (5) of a rotating part of a high-pressure body (4) of a turbomachine (3) for an aircraft (1) is proposed. The drive system includes an accessory relay box (13) having at least one shaft line (14) configured to be mechanically coupled to the rotating part, the equipment (18) having an equipment shaft (18b) configured to be connected to the shaft line (14). A lateral surface (18d) of the equipment includes an opening (25), and the equipment includes a tool shaft (21) having a first end provided with a mechanical interface (22) located opposite the opening (25) and capable of cooperating with an external tool (23) inserted into the opening, the equipment further including transmission means (24) configured to connect the equipment shaft to the second end of the tool shaft to transfer torque between the equipment shaft and the tool shaft.Figure for the abbreviation: Fig 2.

Description

Title of the invention: Equipment for a turbomachine drive system, drive system, turbomachine and associated aircraft technical field

[0001] The invention relates to the drive of an aircraft propulsion engine, and more particularly to equipment for driving an aircraft propulsion engine, and a drive system for a rotating part of a high-pressure body of an aircraft turbomachine comprising such equipment.

[0002] The invention further relates to a propulsion engine comprising a turboprop or turbojet engine comprising such a drive system, and an aircraft comprising such a propulsion engine. Previous techniques

[0003] 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 various states. 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.

[0004] 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.

[0005] 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.

[0006] This sustained research and development work focuses on new generations of aircraft engines, aircraft weight reduction, particularly through the materials used and lighter onboard equipment, and the development of the use of electrical technologies to provide propulsion, and, as essential complements to technological progress, aviation biofuels.

[0007] 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.

[0008] An aircraft includes propulsion engines, each generally comprising a turboprop or a turbojet.

[0009] Each engine includes a turbomachine comprising a high-pressure body including a fixed part and a rotating part equipped with blades, and an accessory relay box coupled to a rotor shaft of the rotating part.

[0010] During maintenance operations, it is necessary to visually check the condition of the rotating part, in particular the rotor blades.

[0011] One end of an endoscope is for example introduced into the turbomachine housing through a dedicated opening and the rotor is driven by the accessory relay box to slowly rotate the rotor in order to spot apparent damage.

[0012] The accessory relay housing includes shaft lines equipped with reducers and connected to the rotor shaft.

[0013] Auxiliary equipment of the turbomachine, including fuel pumps, an alternator, a starter, and means for rotating the rotor, are each connected to a shaft line of the casing.

[0014] Document FR2952121 discloses an example of an embodiment of an accessory relay housing comprising a mechanical interface (“Hand Cranking Pad” in English) disposed on an axial face of the housing.

[0015] The mechanical interface includes a square section end to which a crank can be fitted to slowly rotate the high-pressure body during endoscopic control.

[0016] In the context of new engine developments, and in particular the development of demonstrators prior to future engines in operation, the space located opposite the axial face usually reserved for the implantation of the mechanical interface and the crank is reduced and cluttered by engine components in order in particular to reduce the size of the nacelles supporting the engine.

[0017] It is no longer possible to implant the mechanical interface on the axial face of the accessory relay housing to rotate the high-pressure body during endoscopic control. Description of the invention

[0018] The aim of the invention is to overcome this drawback.

[0019] In view of the foregoing, the invention relates to equipment for a drive system of a rotating part of a high-pressure body of a turbomachine for aircraft.

[0020] The drive system includes an accessory relay housing which has a first mounting surface and at least one shaft line configured to be mechanically coupled to the rotating part, the equipment having a first end surface, a second end surface opposite the first end surface and at least one lateral surface connecting the first and second end surfaces, the equipment further having an equipment shaft configured to be connected to the shaft line, the first end surface being configured to be in contact with the first mounting surface.

[0021] The lateral surface includes an opening and the equipment includes a tool shaft having a first end provided with a mechanical interface located opposite the opening and capable of cooperating with an external tool inserted in the opening, the equipment further including transmission means configured to connect the equipment shaft to a second end of the tool shaft to transfer torque between the equipment shaft and the tool shaft.

[0022] The mechanical interface (“Hand Cranking Pad” in English) is arranged on a lateral surface of the equipment so that an external tool, for example a crank, is attached laterally to the equipment, freeing up space in front of the first mounting face, the external tool allowing the rotating part to be animated by a rotational movement in order in particular to carry out an endoscopic control of the rotating part.

[0023] Preferably, the transmission means comprise a first bevel gear mounted on the equipment shaft and a second bevel gear disposed at the second end of the tooling shaft.

[0024] Advantageously, the equipment shaft is substantially perpendicular to the tooling shaft, the transmission means comprising a spur gear disposed on the tooling shaft and lateral teeth cut on the side of a web integral with the equipment shaft.

[0025] Preferably, the equipment tree is formed by an upstream tree and a downstream tree, the equipment comprising a first disconnection device, the upstream tree connecting the tree line to a first connection of the first disconnection device and the downstream tree connecting a second connection of the disconnection device to the transmission means, the first disconnection device being configured to connect or disconnect the upstream and downstream trees.

[0026] A drive system for a rotating part of a high-pressure body of an aircraft turbomachine is also proposed.

[0027] The drive system includes an accessory relay housing having a first mounting surface and at least one first shaft line configured to be mechanically coupled to the rotating part, and equipment as defined above, the first end surface being in contact with the first mounting surface and the equipment shaft being connected to the first shaft line.

[0028] Preferably, which the accessory relay box includes a second disconnect device configured to connect or disconnect the first shaft line and the equipment shaft.

[0029] Advantageously, the first shaft line includes an output shaft configured to be mechanically coupled to the rotating part, the output shaft being integral with the equipment shaft of the first equipment.

[0030] Preferably, the accessory relay housing further comprises a plurality of shaft lines, and an output shaft configured to be mechanically coupled to the rotating part of the high-pressure body, the output shaft being mechanically coupled to each shaft line among the first shaft line and the plurality of shaft lines via gears, the first shaft line being a shaft line among the shaft lines of the accessory relay housing coupled to the output shaft.

[0031] Also proposed is an aircraft turbomachine comprising a high-pressure body having a rotating part including a propulsion shaft, and a drive system as defined above, the first shaft line being coupled to the propulsion shaft.

[0032] An aircraft comprising at least one turbomachine as defined above is also proposed. Brief description of the drawings

[0033] Other objects, features and advantages of the invention will become apparent from the following description, given solely by way of non-limiting example, and made with reference to the accompanying drawings in which:

[0034] [Fig-1] schematically illustrates an aircraft of the invention;

[0035] [Fig.2] schematically illustrates an example of the realization of a turbomachine according to the invention;

[0036] [Fig.3] schematically illustrates an example of the realization of transmission means according to the invention;

[0037] [Fig.4] schematically illustrates an example of an embodiment of an accessory relay box according to the invention; and

[0038] [Fig.5] schematically illustrates an example of an embodiment of a drive system according to the invention. Detailed description

[0039] Reference is made to [Fig.1] which schematically illustrates an example of an aircraft 1 comprising two propulsion engines, each comprising a turbojet 2.

[0040] Of course, the aircraft may include more than two propulsion engines or a single propulsion engine.

[0041] Alternatively, each propulsion engine includes a turboprop.

[0042] The propulsion engines are identical.

[0043] Each turbojet or turboprop includes a turbomachine 3.

[0044] Fig. 2 schematically illustrates an example of an embodiment of the turbomachine 3.

[0045] The turbomachine 3 comprises a high-pressure body 4 connected to a system drive 5 via a first angle transfer device 6 made from gears for example with conical teeth.

[0046] The high-pressure body 4 comprises a high-pressure compressor 8 and a high-pressure turbine 9 linked in rotation by a common shaft 7 called the high-pressure shaft, and an annular combustion chamber 10 disposed between the compressor 8 and the turbine 9 so that the compressor 8 supplies pressurized air to the combustion chamber 10 to burn a fuel, for example kerosene, injected into the combustion chamber 10.

[0047] The compressor 8, the turbine 9, and the drive shaft form a rotating part of the high-pressure body 4. The gases generated in the combustion chamber 10 drive this rotating part, and also drive a low-pressure turbine (not shown) of a low-pressure body if the turbomachine 3 is of the twin-body type.

[0048] The high-pressure body 4 further includes an internal right-angle gearbox 11 made from cog gears, commonly called an IGB (for "Inlet GearBox"). This gearbox 11 connects the shaft 7 to an input shaft 12, also called a radial shaft, which in turn is connected to an external right-angle gearbox 6 called a TGB (for "Transfer GearBox").

[0049] Alternatively, the internal angle drive device 11 is made from spur gears.

[0050] The drive system 5 includes an accessory gearbox 13 (also called AGB for "accessory gearbox" in English) having three shaft lines 14, 15, 16 and an output shaft 17.

[0051] Each shaft line 14, 15, 16 includes a pinion 14a, 15a, 16a and the output shaft 17 includes a pinion 17a.

[0052] The first shaft line 14 is connected to the output shaft 17 by a gear formed by the pinion 14a of the first shaft line 14 cooperating with the pinion 17a of the output shaft 17.

[0053] The second shaft line 15 is connected to the output shaft 17 by a gear formed by the pinion 15a of the second shaft line 15 cooperating with the pinion 17a of output tree 17.

[0054] The third shaft line 16 is connected to the output shaft 17 by a first gear formed by the pinion 15a of the second shaft line 15 cooperating with the pinion 17a of the output shaft 17 and a second gear formed by the pinion 15a of the second shaft line 15 cooperating with the pinion 16a of the third shaft line 16.

[0055] Of course, the housing 13 can include more or less than three shaft lines.

[0056] The housing 13 has a first mounting surface 13a and a second mounting surface 13b opposite the first mounting face 13a.

[0057] The first mounting face 13a includes at least one opening per shaft line 14, 15, 16 allowing the passage of a shaft.

[0058] The drive system 5 further comprises three pieces of equipment 18, 19, 20.

[0059] The first tree line 14 is connected to a first piece of equipment 18, the second tree line 15 is connected to a second piece of equipment 19 and the third tree line 16 is connected to a third piece of equipment 20.

[0060] Each piece of equipment 18, 19, 20 includes, for example and not limited to, a lubrication pump, a fuel pump or a starter.

[0061] Each piece of equipment 18, 19, 20 is generally cylindrical.

[0062] Each piece of equipment 18, 19, 20 comprises a first end surface 18a, 19a, 20a coming into contact with the first mounting face 13a and fixed to the first mounting face 13a by means of fixing (not shown) comprising for example bolts, so that the housing 13 supports the equipment 18, 19, 20.

[0063] Each piece of equipment 18, 19, 20 further comprises a gear shaft 18b, 19b, 20b connected to the pinion 14a, 15a, 16a the shaft line 14, 15, 16.

[0064] Alternatively, the second mounting face 13b of the housing 13 includes at least one opening so that equipment can be fixed to the second mounting face 13b and connected to a shaft line of the housing 13.

[0065] The first equipment 18 further comprises a second end surface 18c opposite the first end surface 18a, and a lateral surface 18d connecting the first and second end surfaces 18a, 18c.

[0066] The first equipment 18 includes a tool shaft 21 comprising a first end provided with a mechanical interface 22 cooperating with an external tool 23.

[0067] The external tool 23 includes, for example, a crank having a non-circular end fitting into a non-circular bore of the mechanical interface 22.

[0068] The first equipment 18 further includes transmission means 24 connecting the equipment shaft 18b to the second end of the tooling shaft 21 to transfer torque between the equipment shaft 18b and the tooling shaft 21.

[0069] The torque is generated by the manipulation of the external tool 23 inserted into the mechanical interface 22.

[0070] The first equipment 18 further includes an opening 25 located on the lateral surface 18d.

[0071] The mechanical interface 22 is located opposite the opening 25.

[0072] The first equipment 18 includes a first disconnection device 26, and the equipment tree 18b is formed by an upstream tree 27 and a downstream tree 28.

[0073] The upstream tree 27 connects the first tree line 14 to a first connection of the first disconnecting device 26 and the downstream tree 28 connects a second connection of the first disconnecting device 26 to the transmission means 24.

[0074] The first disconnecting device 26 is capable of connecting or disconnecting the upstream and downstream trees 27, 28.

[0075] The transmission means 24 include a first bevel gear 29 mounted on the downstream shaft 28 of the equipment shaft 18b and a second bevel gear 30 disposed at the second end of the tooling shaft 21.

[0076] The mechanical interface 22 (“Hand Cranking Pad” in English) is arranged on a lateral surface 18d of the first equipment 18 so that the external tool 23 is positioned laterally relative to the first equipment 18 and not axially as known from the prior art, thus freeing up space opposite the first mounting face 13b.

[0077] Advantageously, the first equipment 18 and the opening 25 are arranged close to the ground so that when the engine cowlings 3 of the aircraft 1 are opened, the mechanical interface 22 is easily accessible.

[0078] The first shaft line 14 supporting the first equipment 18 is coupled to the output shaft via a single gear formed by the pinion 14a of the first shaft line 14 and the pinion 17a of the output shaft 17.

[0079] The first shaft line 14 is coupled to the output shaft via the minimum number of gears so that the mechanical interface 22 is located as close as possible to the output shaft 17, allowing the number of gear pinions between the tooling shaft 21 and the output shaft 17 to be minimized, so that the sum of the gear tooth backlashes is reduced.

[0080] As the sum of the gear clearances is reduced, the accuracy of the rotation angle of the rotating part of the high-pressure body 4 from a rotation of the external tool 23 is improved, and the latency between the rotation of the external tool 23 and the rotating part of the high-pressure body 4 driven by the rotation of the external tool 23 is reduced.

[0081] The transmission means 24 comprise two bevel gears 29, 30 cooperating to transmit torque such that an angle formed between the equipment shaft 18b and the tool shaft 21 can be equal to 90° or any other angle value compatible with bevel gears and the space available in the equipment 18 to accommodate the transmission means 24.

[0082] The first disconnecting device 26 allows the upstream shaft 27 and the downstream shaft 28 to be disconnected when the aircraft 1 is in flight, increasing the available torque transmitted by the output shaft 17 to drive the second and third pieces of equipment 19, 20 when the aircraft 1 is in flight

[0083] The first disconnecting device 26 allows the upstream shaft 27 and the downstream shaft 28 to be connected during maintenance phases at very low speeds to carry out an endoscopic check and during the first engine revolutions during the engine start and stop phases.

[0084] In addition, since the downstream shaft 28 is not driven in rotation when the aircraft 1 is in flight, and is driven at low speed during maintenance phases and when the engine is in the start-up and shutdown phases, a drip lubrication system is sufficient to lubricate the transmission means 24 and the first equipment 18, reducing the size and complexity of the lubrication system.

[0085] The lubrication system (not shown) lubricates in particular the gears 29, 30 of the transmission means 24 and the bearings (not shown) of the transmission means 24 supporting the equipment and tooling shafts.

[0086] Advantageously, the first equipment 18 is chosen as being an equipment comprising the first disconnection device 26 so that only the transmission means 24, the tool shaft 21 and the opening 25 are added, allowing the sharing of, in particular, the drip-type lubrication system to lubricate the transmission means 24.

[0087] Alternatively, the first equipment 18 does not include the first disconnecting device 26, the equipment shaft 18b being formed of a single shaft connecting the pinion 14a of the first shaft line 14 to the connecting means 24.

[0088] Fig. 3 schematically illustrates another example of transmission means 24.

[0089] The transmission means 24 include a spur gear 35 disposed on the tool shaft 21 and lateral teeth 36 cut on the side of a web 37 integral with the equipment shaft 18b.

[0090] In this embodiment of the transmission means 24, the equipment shaft 18b is substantially perpendicular to the tooling shaft 21 so that the teeth of the spur gear 35 mesh with the lateral teeth 36 cut on the side of a web 37 integral with the equipment shaft 18b.

[0091] The term "substantially" means that the equipment shaft 18b is perpendicular to the tool tree 21 within a few degrees.

[0092] Fig. 4 schematically illustrates another example of the accessory relay housing 13.

[0093] The housing 13 includes a second disconnection device 40 suitable for connecting or disconnecting the first tree line 14 and the equipment tree 18b of the first equipment 18.

[0094] The second disconnecting device 40 allows the first shaft line 14 and the equipment shaft 18b to be disconnected from the first equipment 18 when the aircraft 1 is in flight, and the first shaft line 14 and the equipment shaft 18b to be connected when said shafts are rotating at low speeds during maintenance phases for endoscopic inspection and during the first engine revolutions during engine start and shutdown phases increasing the available torque transmitted by the output shaft 17 to drive the second and third equipment 19, 20 when the aircraft 1 is in flight.

[0095] The integration of the second disconnection device 40 into the housing 13 makes it possible to obtain a more compact drive system 5.

[0096] Fig. 5 schematically illustrates another example of an embodiment of the drive system 5.

[0097] In this example, the output shaft 17 of the housing 17 is fixed to the shaft of the equipment 18b of the first equipment 18.

[0098] Of course, the first tree line 14 can include the second disconnecting device 40 illustrated in [Fig.4].

Claims

Demands

1. Equipment (18) for a drive system (5) of a rotating part of a high-pressure body (4) of a turbomachine (3) for aircraft (1), the drive system comprising an accessory relay box (13) having a first mounting surface (13a) and at least one shaft line (14) configured to be mechanically coupled to the rotating part, the equipment (18) having a first end surface (18a), a second end surface (18c) opposite the first end surface and at least one side surface (18d) connecting the first and second end surfaces (18a, 18c), the equipment further comprising an equipment shaft (18b) configured to be connected to the shaft line (14), the first end surface (18a) being configured to be in contact with the first mounting surface (13a),characterized in that the lateral surface (18d) comprises an opening (25) and the equipment comprises a tool shaft (21) having a first end provided with a mechanical interface (22) located opposite the opening (25) and capable of cooperating with an external tool (23) inserted into the opening, the equipment further comprising transmission means (24) configured to connect the equipment shaft (18b) to a second end of the tool shaft to transfer torque between the equipment shaft and the tool shaft.

2. Equipment according to claim 1, wherein the transmission means (24) comprise a first bevel gear (29) mounted on the equipment shaft (18b) and a second bevel gear (30) disposed at the second end of the tooling shaft (21).

3. Equipment according to claim 1, wherein the equipment shaft (18b) is substantially perpendicular to the tooling shaft (21), the transmission means (24) comprising a spur gear (35) disposed on the tooling shaft (21) and lateral teeth (36) cut on the side of a web (37) integral with the equipment shaft (18b).

4. Equipment according to any one of claims 1 to 3, wherein the equipment shaft (18b) is formed by an upstream shaft (27) and a downstream shaft (28), the equipment (18) comprising a first disconnection device (26), the upstream shaft (27) connecting the shaft line (14) to a first connection of the first disconnection device (26), and the downstream shaft (28) connecting to a second connection of the disconnection device (26) to the transmission means (24), the first disconnection device being configured to connect or disconnect the upstream and downstream trees.

5. Drive system (5) of a rotating part of a high-pressure body (4) of a turbomachine (3) for aircraft (1), the drive system comprising an accessory relay box (13) having a first mounting surface (13a) and at least one first shaft line (14) configured to be mechanically coupled to the rotating part, and equipment (18) according to any one of claims 1 to 4, the first end surface (18a) being in contact with the first mounting surface (13a) and the equipment shaft (18b) being connected to the first shaft line (14).

6. A drive system according to claim 5, wherein the accessory relay housing (13) includes a second disconnecting device (40) configured to connect or disconnect the first shaft line (14) and the equipment shaft (18b).

7. A drive system according to claim 5 or 6, wherein the first shaft line (14) comprises an output shaft (17) configured to be mechanically coupled to the rotating part, the output shaft (17) being integral with the equipment shaft (18b) of the first equipment (18).

8. A drive system according to claim 5 or 6, wherein the accessory relay housing (13) further comprises a plurality of shaft lines (15, 16), and an output shaft (17) configured to be mechanically coupled to the rotating part of the high-pressure body (4), the output shaft (17) being mechanically coupled to each shaft line among the first shaft line (14) and the plurality of shaft lines (15, 16) via gears (14a, 15a, 16a, 17a), the first shaft line (14) being a shaft line among the shaft lines of the accessory relay housing (13) coupled to the output shaft.

9. Turbomachine (3) for aircraft (1) comprising a high-pressure body (4) having a rotating part comprising a drive shaft (7), and a drive system (5) according to any one of claims 5 to 8, the first shaft line (14) being coupled to the drive shaft.

10. Aircraft (1) comprising at least one turbomachine (3) according to claim 9.

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