US20170175753A1 - Turbomachine comprising a means of uncoupling a fan - Google Patents

Turbomachine comprising a means of uncoupling a fan Download PDF

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Publication number
US20170175753A1
US20170175753A1 US15/390,353 US201615390353A US2017175753A1 US 20170175753 A1 US20170175753 A1 US 20170175753A1 US 201615390353 A US201615390353 A US 201615390353A US 2017175753 A1 US2017175753 A1 US 2017175753A1
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United States
Prior art keywords
shaft
fan
uncoupling
reduction device
torque
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Abandoned
Application number
US15/390,353
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English (en)
Inventor
Alexandre Tan-Kim
Julien Fabien Patrick Becoulet
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Filing date
Publication date
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Assigned to SAFRAN AIRCRAFT ENGINES reassignment SAFRAN AIRCRAFT ENGINES NUNC PRO TUNC ASSIGNMENT (SEE DOCUMENT FOR DETAILS). Assignors: BECOULET, JULIEN FABIEN PATRICK, TAN-KIM, Alexandre
Publication of US20170175753A1 publication Critical patent/US20170175753A1/en
Priority to FR1763050A priority Critical patent/FR3061238B1/fr
Priority to US16/728,992 priority patent/US11391290B2/en
Abandoned legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
    • F04D29/053—Shafts
    • F04D29/054—Arrangements for joining or assembling shafts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
    • F01D15/12—Combinations with mechanical gearing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/003—Arrangements for testing or measuring
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/06—Shutting-down
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/107—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission
    • F02C3/113—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission with variable power transmission between rotors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/02—Units comprising pumps and their driving means
    • F04D25/04—Units comprising pumps and their driving means the pump being fluid-driven
    • F04D25/045—Units comprising pumps and their driving means the pump being fluid-driven the pump wheel carrying the fluid driving means, e.g. turbine blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/325—Rotors specially for elastic fluids for axial flow pumps for axial flow fans
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades
    • F04D29/388—Blades characterised by construction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/60—Shafts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/31—Retaining bolts or nuts
    • F05D2260/311—Retaining bolts or nuts of the frangible or shear type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/40—Transmission of power
    • F05D2260/403—Transmission of power through the shape of the drive components
    • F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/40—Transmission of power
    • F05D2260/403—Transmission of power through the shape of the drive components
    • F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing
    • F05D2260/40311—Transmission of power through the shape of the drive components as in toothed gearing of the epicyclical, planetary or differential type
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the field of the present invention is that of aeronautical turbomachines and more particularly that of dual flux turbomachines including a reduction device for driving the fan.
  • turbomachines comprise, starting from the upstream side, one or several compressor modules positioned in series, which compress the air sucked up in an air intake. The air is then introduced into a combustion chamber where it is mixed with fuel and burnt. The combustion gases pass through one or several turbine modules which drive the compressor(s) via associated turbine shafts. The gases are finally ejected either into a nozzle for producing a propelling force either on a free turbine in order to produce power which is recovered on a transmission shaft.
  • Present dual flow turbomachines with a strong dilution rate includes several compressor stages, notably a low pressure (LP) compressor and a high pressure (HP) compressor, crossed by a primary flow.
  • These low pressure (LP) and high pressure (HP) compressors are each driven by an associated respective low pressure (LP) or high pressure (HP) turbine shaft.
  • Upstream from the low pressure (LP) compressor is positioned a wheel including movable blades or vanes of large dimension, or a fan, which feeds both the primary flow crossing the LP and HP compressors and a cold flow, or secondary flow, which is directly directed towards a cold flow nozzle, a so called secondary nozzle.
  • the fan is driven by the rotation shaft of an LP turbine of the LP body and generally rotates at the same speed as it.
  • the fan rotates at a rotational speed of less than that of the LP shaft, notably when the latter is of a very large size, with the purpose of better adapting it aerodynamically.
  • a reduction device is positioned between the turbine shaft LP and a fan shaft, which bears the fan.
  • Such a configuration is notably described in patent applications FR 1,251,655 and 1,251,656 filed on Feb. 23, 2012.
  • the torsion of the shafts may lead to breakages of the shafts in different points of the turbomachine, as this is taught by document EP-2,048,330-A2.
  • Document EP-2,048,330-A2 discloses a turbomachine including a fan shaft and a shaft of a compressor each driven by a turbine shaft via two different coupling paths torqued with the turbine shaft at an intersection laid out at a bearing.
  • the coupling path drives the fan via a reduction device. Both coupling paths are provided so that in the case of an incidental breakage of one of the coupling paths, the turbine remains being charged on the other coupling path in order to avoid excess speeds of the turbine, while a control unit of the turbine may reduce the speed of the turbine.
  • the turbomachine described in this document starts from the fact that a possible mechanical malfunction of the coupling paths may occur, such as for example the one which connects the turbine shaft to the fan.
  • this document does not explicitly specify the nature of this malfunction, which may consist or not in a break, but which is in any case incidental and not predictable.
  • this incidental break then only occurs when the reduction device has already been subject to significant torques and has already likely been damaged.
  • a solution consists of limiting the torsional torque which may pass through the reduction device and the turbine shaft LP in order to avoid blocking the fan.
  • the invention proposes a turbomachine of the type mentioned earlier, characterized in that it includes at least one uncoupling means interposed between the reduction device and the turbine shaft, which is able of uncoupling the reduction device and the turbine shaft in response to exceeding a determined resistant torque exerted by the reduction device on the turbine shaft.
  • the uncoupling is therefore an event provided as a response to the exceeding of a determined resistant torque exerted by the reduction device on the turbine shaft, i.e. conditioned by the exceeding of this resistant torque.
  • the uncoupling means includes at least one fuse connecting element which is interposed between the reduction device and the turbine shaft and which is able to be broken when it is subject to a so called uncoupling resistant torque exerted by the device for reducing speed on the turbine shaft.
  • the fuse element consists of a segment of an input shaft of the reduction device bound to the turbine shaft, said segment being able to be broken when it is subject to a maximum torsional torque corresponding to the uncoupling resistant torque.
  • an input shaft of the reduction device includes a tubular end segment which is coupled with a complementary tubular end segment of the turbine shaft via at least one radial element able to be broken when it is subject to a shear stress corresponding to the resistant uncoupling torque.
  • the radial element includes a pin which is received in a radial orifice of the end segment of the input shaft and in an orifice facing the end segment of the turbine shaft.
  • the reduction device can be coupled to the turbine shaft via a coupling with trapezoidal teeth of the curvic type, including two toothed coupling plates meshing with one another and fastened to one another via screws.
  • these screws are axial fuse screws forming fuse connecting elements of the uncoupling means.
  • the fuse connecting element is able to be broken as soon as it is subject to the determined resistant uncoupling torque corresponding to a resistant torque exerted by the fan on the speed reduction device in the case of loss of at least one blade of a fan driven by said fan shaft.
  • the fuse connecting element is able to be broken as soon as it is subject to a resistant torque which is strictly greater than any torque corresponding to a resistant torque exerted by the fan on the speed reduction device in the case of ingestion of a bird without losing any blade by said fan.
  • the fuse connecting element may be associated with a fan including metal blades.
  • the fuse element is able to be broken as soon as it is subject to an uncoupling torque of 120 to 140% of a normal torque in a maximum speed of the turbomachine.
  • the fuse connecting element may be associated with a fan including blades in a composite material.
  • the melting element is able to be broken as soon as it is subject to an uncoupling torque of 130 to 170% of a normal torque in a maximum speed condition of the turbomachine.
  • the turbomachine according to the invention advantageously includes means for detecting the uncoupling of the reduction device and of the turbine shaft able to control a reduction of speed of the turbine and/or stopping of the turbomachine.
  • the resistant uncoupling torque is greater than 50,000 N ⁇ m, and preferably comprised between 50,000 N ⁇ m and 400,000 N ⁇ m.
  • the turbomachine includes an additional uncoupling means interposed between the reduction device and the fan shaft, which is able to uncouple the reduction device and the fan shaft in response to exceeding a determined resistant torque, called uncoupling torque, exerted by the fan shaft on the reduction device.
  • the additional uncoupling means includes at least one fuse connecting element which is interposed between the reduction device and the fan shaft and which is able to be broken when it is subject to the uncoupling resistant torque exerted by the fan shaft on the reduction device.
  • the fuse element consists of a segment of an output shaft of the reduction device bound to the fan shaft, said segment being able to be broken when it is subject to a maximum torsional torque corresponding to the uncoupling resistant torque.
  • an output shaft of the reduction device includes a tubular end segment which is coupled with a complementary tubular end segment of the fan shaft via at least one radial fuse connecting element able to be broken when it is subject to a shear stress corresponding to the resistant uncoupling torque.
  • the radial element includes a pin which is received in a radial orifice of the end segment of the output shaft and in an orifice facing the end segment of the fan shaft.
  • the reduction device can be coupled to the fan shaft via a coupling with trapezoidal teeth of the curvic type, including two toothed coupling plates with trapezoidal axial teeth meshing with one another and fastened to one another via axial screws.
  • the screws are fuse screws forming the fuse connecting element of the additional uncoupling means.
  • FIG. 1 is an overall view of a turbomachine according to a prior state of the art
  • FIG. 2A is a sectional view of the front portion of a turbomachine according to the invention equipped with a first embodiment of an uncoupling means;
  • FIG. 2B is a detailed view of FIG. 2A ;
  • FIG. 3A is a sectional view of the front portion of a turbomachine according to the invention equipped with a second embodiment of an uncoupling means;
  • FIG. 3B is a detailed view of FIG. 3A .
  • FIG. 4 is a diagram illustrating the resistant torque exerted by the speed reduction device on the turbine shaft versus time during the loss of a blade of the fan.
  • FIG. 5 is a schematic sectional view of the front portion of a turbomachine according to the invention equipped with a second embodiment of an additional uncoupling means;
  • FIG. 6 is a detail view of a first embodiment of the additional uncoupling means
  • FIG. 7 is a detail view of a second embodiment of the additional uncoupling means
  • FIG. 8A is a perspective view of a third embodiment of the uncoupling means or the additional uncoupling means
  • FIG. 8B is a detailed sectional perspective view of a third embodiment of the uncoupling means or the additional uncoupling means prior to uncoupling;
  • FIG. 8C is a detailed sectional view of the third embodiment of the uncoupling means or the additional uncoupling means during uncoupling.
  • FIG. 1 is illustrated a turbomachine such as a turbine engine 10 made according to a prior state of the art.
  • the turbine engine 10 includes, from the upstream side to the downstream side along the gas flow flux “F”, a fan 12 , a low pressure compressor 14 , a high pressure compressor, a combustion chamber, a high pressure turbine and a low pressure turbine (not shown).
  • the fan 12 includes blades 13 .
  • the high pressure compressor and the high pressure turbine are connected through a high pressure shaft and form with it a high pressure body.
  • the low pressure compressor 14 and the low pressure turbine are connected through a low pressure shaft 16 and form with it a low pressure body.
  • the fan 12 as for it is borne by a fan shaft 18 which, in the illustrated example, is bound in rotation to the LP shaft 16 , through a device 20 for reducing the speed of rotation between both shafts 16 , 18 .
  • the fan 12 rotated at a speed of rotation of less than that of the LP shaft 16 , notably when the latter is of a very large size, with the purpose of better adapting it aerodynamically.
  • the HP and LP shafts 16 extend along an axis “A” of rotation of the turbine engine 10 .
  • the turbine engine 10 also comprises, conventionally, a fan case (not shown) which allows channeling of the gases sucked up by the fan 12 towards a vein 22 of a primary flow, which crosses the LP and HP bodies, and a secondary flow vein (not shown) which surrounds a case of the LP and HP bodies and joins up with the primary flow vein in a nozzle (not shown) of the turbine engine.
  • a fan case (not shown) which allows channeling of the gases sucked up by the fan 12 towards a vein 22 of a primary flow, which crosses the LP and HP bodies
  • a secondary flow vein not shown
  • the reduction device 20 is positioned between the fan shaft 18 and the LP shaft 16 .
  • This reduction device for example of the epicycloidal type is illustrated in the schematic form of rectangles only showing its congestion. It is, non-limitingly with respect to the invention, driven by a planetary pinion 24 (shown by the outline of its teeth) borne by an input shaft 26 which is connected in rotation to the LP shaft 16 , the shaft 16 being, only as an example, received without any play by being fitted into the shaft 26 . It also includes a planet carrier 49 (shown by the axis of its planet gears) secured to a case 46 of the turbomachine, and a crown 48 that drives the shaft 18 of the fan 12 .
  • a solution consists of limiting the torsional torque which may pass through the reduction device 20 and the LP turbine shaft 16 , in order to avoid blocking of the fan 12 .
  • the limitation of the torsional torque has another advantage, which is to give the possibility of avoiding over-dimensioning of the members of the reduction device 20 and of the LP turbine shaft 16 able to ensure their resistance to such a torsional torque during exceeding of a determined resistant torque exerted by the speed reduction device 20 on the turbine shaft 16 .
  • the limitation of this torque gives the possibility of avoiding any over-dimensioning of the members of the reduction device 20 and of the low pressure turbine shaft 16 , and therefore alleviating the design of the reduction device 20 and of the LP turbine shaft 16 .
  • the invention proposes a turbomachine of the type described earlier, characterized in that it includes an uncoupling means 28 interposed between the reduction device 20 and the turbine shaft 16 , which is able to uncouple the reduction device 20 from the turbine shaft in response to the exceeding of a determined resistant torque, called uncoupling torque, exerted by the speed reduction device 20 on the turbine shaft 16 .
  • the uncoupling means 28 includes at least one fuse connecting element 30 , 30 ′, 30 ′′ which is interposed between the reduction device 20 and the turbine shaft 16 and which is able to be broken when it is subject to the resistant torque a so called uncoupling torque exerted by the speed reduction device on the turbine shaft, and which notably corresponds to a determined resistant torque exerted by the fan 12 on the speed reduction device 20 , and then transmitted through said speed reduction device.
  • Benefitting from the positioning of at least one fuse connecting element 30 , 30 ′, 30 ′′ between the reduction device 20 and the turbine shaft 16 has several advantages.
  • this positioning of the fuse connecting element 30 , 30 ′, 30 ′′ between the reduction device 20 and the turbine shaft 16 is easy to achieve at the reduction device 20 since the shaft 18 of the fan 12 is supported by two bearings 32 , 34 , and since the shaft 16 of the LP turbine is itself also supported by two bearings, a single bearing 36 of which has been illustrated in FIGS. 2A, 3A .
  • the breaking of the fuse element 30 , 30 ′ therefore has no incidence on the maintaining in rotation of the shaft 16 of the LP turbine or the shaft 18 of the fan 12 .
  • the uncoupling of the reduction device 20 and of the turbine shaft 16 involves a free speed of rotation of the fan 12 after stopping the turbine engine that is greater than that which the same fan 12 would have in a conventional turbine engine wherein the turbine engine would be stopped without uncoupling the fan 12 .
  • the fan 12 is subject to a free speed of rotation or “wind-milling” which allows the turbine engine to only produce a reduced drag.
  • the positioning of the fuse connecting element 30 , 30 ′, 30 ′′ between the reduction device 20 and the turbine shaft 16 allows, as this will be seen later on in the continuation of the present description, protection of the reduction device 20 in the case of excess speed of the shaft 16 of the turbine.
  • the fuse element consists of a segment 30 of the input shaft 26 of the reduction device bound to the shaft 16 of the turbine. This segment 30 is able to be broken when it is subject to a maximum torsional torque corresponding to the determined uncoupling resistant torque exerted by the reduction device 20 on the shaft 16 .
  • the segment may be a tubular segment with reduced thickness “e”, as illustrated in FIG. 2A .
  • This may also be an open-worked segment 30 and/or including areas for initiating the break (not shown).
  • the input shaft 26 of the reduction device includes a tubular end segment 38 which is uncoupled with a complementary tubular end segment 40 of the turbine shaft 16 via at least one radial element 30 , forming the fuse connecting element.
  • This radial element 30 ′ is able to be broken when it is subject to a shear stress corresponding to the resistant uncoupling torque.
  • the radial element 30 ′ forming the fuse element may be conformed according to many embodiments.
  • the radial element 30 ′ consists of a pin, notably a cylindrical pin which is received in a radial orifice 42 of the end segment of the input shaft 26 and into an orifice 44 facing the end segment of the shaft 16 of the turbine.
  • the planetary gear 24 is supported via the satellite-bearer with the output shaft (not shown) of the reduction device 20 .
  • the reduction device 20 is coupled to the turbine shaft 16 via a coupling 17 with trapezoidal teeth of the “curvic” type.
  • a coupling known from the state of the art, is conventionally used in turbomachines to couple trunnions, the juxtaposition of which forms the high-pressure shaft.
  • this coupling 17 is used differently here, since it is inserted between the input shaft 26 of the reduction gear 20 and the turbine shaft 16 .
  • It includes two toothed coupling plates 19 A, 19 B including trapezoidal teeth 21 A, 21 B, whereof the direction of the height of the corresponding trapezoids is oriented parallel to the axial direction, and which mesh with one another.
  • the teeth 21 A, 21 B have inclined planes 27 A, 27 B arranged in contact with one another.
  • the plates 19 A, 19 B are joined to one another by axial screws.
  • a functional clearance J is arranged between the ends of the teeth 21 A and the bottoms of the teeth 21 B to guarantee good contact between the inclined planes 27 A, 27 B.
  • the screws are axial fuse screws 30 ′′ that traverse piercings 23 A, 23 B arranged substantially along an intermediate radius R of the teeth 21 A, 21 B, substantially at the middle of said teeth.
  • the axial fuse screws 30 ′′ each form the fuse connecting element 30 ′′ of the uncoupling means 28 .
  • the screws 30 ′′ are tightened with a determined tightening torque that does not risk causing them to break.
  • FIG. 8C when such a coupling undergoes a torsional torque between its two plates 19 A, 19 B, the trapezoidal teeth 21 A, 21 B, via their inclined faces 27 A, 27 B, convert the forces resulting from the torsional torque into a resultant axial force F between the plates 19 A, 19 B that is exerted in the form of a traction force on the screws 30 ′′.
  • This traction force results in causing the screws 30 ′′ to break at their segments 25 with a smaller diameter.
  • the number of screws 30 ′′ and their diameter depend on the value of the uncoupling torque C D .
  • the input shaft 26 is mounted in a sun gear of this reduction gear via a set of complementary splines similar to the set of splines 54 that was shown as an illustration in FIGS. 2A and 3A .
  • This set of splines more particularly includes splines (not shown) inside the sun gear 24 that receive outer splines (not shown) of the input shaft 26 .
  • the inner splines allow the input shaft 26 to slide in the sun gear 24 .
  • the forces resulting from the torsional torque exerted between the plates 19 A, 19 B cause a resultant axial force between these plates 19 A, 19 B that results in causing their separation.
  • the fuse element 30 , 30 ′, 30 ′′ is calibrated so as to break when respectively the segment 30 , the pin 30 ′, or each screw 30 ′′ is subject to an uncoupling torque corresponding to a resistant torque exerted by the fan on the speed reduction device 20 in the case of loss of at least one blade 13 of the fan driven by said fan shaft 18 , and transmitted by the reduction device 20 .
  • the torque C D is situated in a range from 200% to 300% of the maximum torque to which the turbine shaft 12 is subjected.
  • the determined resistant torque be strictly greater than any torque corresponding to a resistant torque exerted by the fan 12 on the speed reduction device 20 and transmitted through the device 20 , in the case of ingestion of a bird without any loss of a blade by said fan 12 , such an event may produce a tangential force slowing down the fan 12 , but which does not risk damaging the reduction device 20 or blocking the relevant kinematical chain.
  • FIG. 4 comparatively illustrates the transmitted resistant torque “C”, in ordinates, versus the time “t” in abscissas, in the case of break of a blade 13 of the fan.
  • a break of a blade 13 may occur at an instant T R .
  • This break leads to an increase in the resistant torque up to a limiting value C max corresponding to the blocking of the reduce device 20 and of the fan 12 , or more exactly to a risk of blocking according to the specifications of the reduction device, making the latter unable to be used.
  • the maximum torque is tared with a couple C D or uncoupling torque. Consequently, during operation, a break of a blade 13 may also occur at an instant T R which leads to an increase in the resistant torque up to the value C D or uncoupling torque value.
  • the torque decreases then, according to the curve in dotted lines, down to a value C min corresponding to a state of free rotation of the fan 12 .
  • an order of magnitude of the determined transmitted uncoupling torque C D when the fan includes metal blades, is of 120 to 140% of a normal torque in the maximum speed conditions of the turbomachine.
  • an order of magnitude of the determined transmitted uncoupling torque is from 130 to 170% of a normal torque under maximum speed conditions of the turbomachine.
  • the maximum input torque of the input shaft 26 of the reduction gear 20 is comprised between 15,000 and 50,000 N ⁇ m.
  • the maximum output torque of the reduction gear 20 is comprised between 50,000 and 170,000 N ⁇ m.
  • the value of the determined uncoupling torque in all three embodiments of the uncoupling means 28 therefore varies substantially between 50,000 N ⁇ m and 400,000 N ⁇ m.
  • the value of the determined uncoupling torque C D in all three embodiments of the additional uncoupling means 28 ′ therefore varies substantially between 60,000 N ⁇ m and 500,000 N ⁇ m.
  • the turbomachine or turbine engine 10 includes means for detecting uncoupling of the reduction device 20 and of the turbine shaft 16 able to control at least a reduction of speed of the turbine, or even a complete stopping of the turbine engine.
  • this design may advantageously be further improved by adding an additional uncoupling means 28 ′ interposed between the reduction device 20 and the fan 12 shaft 18 , which is able to uncouple the reduction device 20 and the fan shaft 18 in response to exceeding a determined resistant torque C D ′, called uncoupling torque, exerted by the fan shaft 18 on the reduction device 20 .
  • This configuration advantageously makes it possible to ensure total uncoupling of the reduction gear 20 , on the side of the turbine shaft 16 as previously seen, but also on the side of the fan 12 shaft 18 , which makes it possible to prevent any of the internal members of the reduction gear 20 from being subjected to an excessive speed and consequently makes it possible to avoid any risk of blow out of the reduction gear 20 .
  • the reduction gear 20 is also connected to a case 46 of the turbomachine by at least one of its members.
  • a crown 48 of the reduction gear 20 is connected to the case 46 via a flexible link made up of an axially deformable crown support 52 , while a planet carrier of the reduction gear 20 is coupled to this fan shaft 18 and a sun gear is coupled to the turbine shaft 16 via a set of complementary splines 54 .
  • this arrangement is not limiting with respect to the invention and that the elements of the reduction gear could be linked differently to the case 46 , the fan shaft 18 , and the turbine shaft 16 .
  • a crown 48 of the reduction tour 20 could be coupled to the fan shaft 18 , while a planet carrier of the reduction gear 20 would be connected to the case 46 via an axially deformable support, and a sun gear 24 would be coupled to the turbine shaft 16 via a set of splines.
  • FIG. 5 shows the uncoupling means 28 ′ in the form of a coupling with trapezoidal teeth of the “curvic” type, but it will also be understood that this arrangement is not limiting with respect to the invention, and that, as will be seen in the continuation of the present description, the uncoupling means 28 ′ can assume other forms.
  • the additional uncoupling means 28 ′ includes at least one fuse connecting element 31 , 31 ′, 31 ′′ which is interposed between the reduction device 20 and the fan shaft 18 and which is able to be broken when it is subject to the uncoupling resistant torque C D exerted by the fan shaft 18 on the reduction device 20 .
  • the fuse element for example consists of a segment 31 of the fan shaft 18 that is bound to an output shaft 50 of the reduction device 20 .
  • This segment 31 is able to be broken when it is subject to a maximum torsional torque corresponding to the determined uncoupling resistant torque exerted by the reduction device 20 on the shaft 18 .
  • the output shaft 50 of the reduction device 20 and the fan shaft 18 can be fixed to one another using any means known from the state of the art. However, preferably, in this first embodiment, the output shaft 50 of the reduction device 20 and the fan shaft 18 are combined and form a single and same part.
  • the segment may be a tubular segment with reduced thickness “e”, as illustrated in FIG. 6 .
  • This may also be an open-worked segment 31 and/or including areas for initiating the break (not shown).
  • the output shaft 50 of the reduction device includes a tubular end segment 38 which is uncoupled with a complementary tubular end segment 40 of the fan shaft 18 via at least one radial element 31 ′, forming the fuse connecting element.
  • This radial element 31 ′ is able to be broken when it is subject to a shear stress corresponding to the resistant uncoupling torque C D .
  • the radial element 31 ′ forming the fuse element may be conformed according to many embodiments.
  • the radial element 31 ′ consists of a pin, notably a cylindrical pin which is received in a radial orifice 42 of the end segment 38 ′ of the output shaft 50 and into an orifice 44 ′ facing the end segment of the fan shaft 18 .
  • the reduction device 20 is coupled to the fan shaft 18 via a coupling 17 with trapezoidal teeth of the “curvic” type. More particularly, this coupling 17 is inserted between the output shaft 50 of the reduction gear 20 , configured in the form of a flange, and the fan shaft 18 . It includes two toothed coupling plates 19 A, 19 B including trapezoidal teeth 21 A, 21 B, whereof the direction of the height of the corresponding trapezoids is oriented parallel to the axial direction, and which mesh with one another. The teeth 21 A, 21 B have inclined planes 27 A, 27 B arranged in contact with one another. The plates 19 A, 19 B and the shaft 50 are configured in a flange joined to one another by axial screws. It will be understood that alternatively, the plate 19 B could be formed in a single piece with the output shaft 50 configured in a flange.
  • the screws are axial fuse screws 31 ′′ that traverse piercings 23 A, 23 B arranged substantially along an intermediate radius R of the teeth 21 A, 21 B, substantially at the middle of said teeth.
  • the axial fuse screws 31 ′′ each form the fuse connecting element of the uncoupling means 28 ′′.
  • a functional clearance J is arranged between the ends of the teeth 21 A and the bottoms of the teeth 21 B to guarantee good contact between the inclined planes 27 A, 27 B.
  • FIG. 8C when such a coupling undergoes a torsional torque between its two plates 19 A, 19 B, the trapezoidal teeth 21 A, 21 B, via their inclined faces 27 A, 27 B, convert the forces resulting from the torsional torque into a resultant axial force F between the plates 19 A, 19 B that is exerted in the form of a traction force on the screws 31 ′′.
  • This traction force results in causing the screws 31 ′′ to break at their segments 25 having a smaller diameter.
  • the number and diameter of the fuse screws 31 ′′ depends on the value of the uncoupling torque C D .
  • the input shaft 26 is mounted in an input member of this reduction gear 20 via a set 54 of complementary splines inserted between the input shaft 26 of the reduction gear and the input member of the reduction gear.
  • the reduction gear 20 also includes another member fixed to the case 46 with axial mobility, and lastly an axially fixed output member.
  • the reduction gear 20 shown in FIG. 5 includes a sun gear 24 (shown by the outline of its teeth), which receives, via the set of complementary splines 54 , the input shaft 26 of the reduction gear.
  • the reduction gear 20 includes a planet carrier 49 (shown by the outline of the axes of its planet gears) that meshes with the sun gear and with a crown 48 , fixed to the case 46 of the turbomachine via an axially deformable support 52 .
  • the break of the fuse connecting element 31 , 31 ′, 31 ′′ of the uncoupling means 28 ′′ can be provided a minima, once a single blade 13 is lost.
  • This configuration is not limiting with respect to the invention, and the loss of a larger number of blades could be tolerated.
  • the determined resistant torque be strictly greater than any torque corresponding to a resistant torque exerted by the fan 12 on the speed reduction device 20 , in the case of ingestion of a bird without any loss of a blade by said fan 12 , such an event may produce a tangential force slowing down the fan 12 , but which does not risk damaging the reduction device 20 or blocking the relevant kinematical chain. In this case, such an event does not cause the break of the fuse connecting element 31 , 31 ′, 31 ′′.
  • the break is, however, anticipated for an event corresponding to a determined percentage of the maximum torque to which the shaft 18 of the fan 12 is subjected. For example, it is possible to tare the break torque C D to respond to the loss of a blade, as previously seen. In the aforementioned configuration of the turbomachine, this torque C D′ is then situated in a range from 120% to 200% of the maximum torque to which the shaft 18 of the fan 12 is subjected.
  • the torque C D is situated in a range from 200% to 300% of the maximum torque to which the shaft 18 of the fan 12 is subjected.
  • means for detecting uncoupling of the reduction device 20 and the fan shaft 18 by the uncoupling means 28 ′ can be provided to control at least a reduction of speed of the turbine, or even a complete stopping of the turbine engine.
  • the triggering of the break of the fuse connecting element 31 , 31 ′, 31 ′′ of the uncoupling means 28 ′ may or may not be simultaneous with that of the fuse element 30 , 30 ′, 30 ′′ of the uncoupling means 28 .
  • elements 30 , 30 ′, 30 ′′ and 31 , 31 ′, 31 ′′ will be chosen whose strength is tuned so as to offer simultaneous uncoupling of the input shaft 26 and the output shaft 50 of the reduction gear 20 , so as to completely uncouple the reduction gear from the kinematic chain in order to reduce the speed of its internal members as quickly as possible and thus avoid any risk of blow out.
  • the input shaft segment 30 of the reduction device 20 is combined with the segment 31 of the output shaft 50 of the reduction device 20 .
  • the input shaft segment 30 of the reduction device 20 is combined with the radial element 31 ′ inserted between the end segment 40 ′ of the fan shaft 18 and the output shaft 50 of the reduction device 20 .
  • the input shaft segment 30 of the reduction device 20 is combined with the axial fuse screws 31 ′′ of the curvic-type coupling inserted between the output shaft 50 of the reduction gear 20 and the fan shaft 18 .
  • the radial element 30 ′ inserted between the input shaft 26 of the reduction device 20 and the tubular end segment 40 of the turbine shaft 16 is combined with the segment 31 of the output shaft 50 of the reduction device 20 .
  • the radial element 30 ′ inserted between the input shaft 26 of the reduction device 20 and the tubular end segment 40 of the turbine shaft 16 is combined with the radial element 31 ′ inserted between the end segment 40 ′ of the fan shaft 18 and the shaft 50 of the reduction device 20 .
  • the radial element 30 ′ inserted between the input shaft 26 of the reduction device 20 and the tubular end segment 40 of the turbine shaft 16 is combined with the axial fuse screws 31 ′′ of the curvic-type coupling inserted between the output shaft 50 of the reduction device 20 and the fan shaft 18 .
  • the axial fuse screws 30 ′′ of the curvic-type coupling inserted between the input shaft 26 of the reduction gear 20 and the turbine shaft 16 are combined with the segment 31 of the output shaft 50 of the reduction device 20 .
  • the axial fuse screws 30 ′′ of the curvic-type coupling inserted between the input shaft 26 of the reduction device 20 and the turbine shaft 16 are combined with the radial element 31 ′ inserted between the end segment 40 ′ of the fan shaft 18 and the shaft 50 of the reduction device 20 .
  • the axial fuse screws 30 ′′ of the curvic-type coupling inserted between the input shaft 26 of the reduction device 20 and the turbine shaft 16 are combined with the axial fuse screws 31 ′′ of the curvic-type coupling inserted between the output shaft 50 of the reduction device 20 and the fan shaft 18 .
  • the invention therefore provides a safe solution to the risks of excess speed of the kinematic line between a fan and a turbine shaft of a turbomachine, in particular in case of fan blade break of the turbomachine.
  • the invention also gives the possibility, by limiting the torque transmitted to the reduction device 20 , of avoiding any over-dimensioning of the members of the reduction device 20 , the fan shaft 18 , and the low pressure turbine shaft 16 in order to overcome the known risks of increase of said torque in the case of a blade loss.
  • these members no longer need to be over-dimensioned for meeting the high torsional constraints, they may have their dimensioning reduced, which has the consequence of globally alleviating the design of the reduction device 20 , the fan shaft 18 and the LP turbine shaft 16 .

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)
  • Control Of Positive-Displacement Air Blowers (AREA)
US15/390,353 2014-06-25 2016-12-23 Turbomachine comprising a means of uncoupling a fan Abandoned US20170175753A1 (en)

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FR1763050A FR3061238B1 (fr) 2016-12-23 2017-12-22 Turbomachine a reducteur pour un aeronef equipee de moyens fusibles
US16/728,992 US11391290B2 (en) 2014-06-25 2019-12-27 Turbomachine comprising a means of uncoupling a fan

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FR1455939 2014-06-25
FR1455939A FR3022890B1 (fr) 2014-06-25 2014-06-25 Turbomachine comportant un moyen de decouplage d'une soufflante
PCT/FR2015/051614 WO2015197949A1 (fr) 2014-06-25 2015-06-17 Turbomachine comportant un moyen de decouplage d'une soufflante

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BR112016030489A2 (cg-RX-API-DMAC7.html) 2017-08-22
RU2681392C2 (ru) 2019-03-06
US11391290B2 (en) 2022-07-19
RU2017100264A3 (cg-RX-API-DMAC7.html) 2019-01-09
JP6682458B2 (ja) 2020-04-15
US20200149542A1 (en) 2020-05-14
BR112016030489B1 (pt) 2022-12-06
CN106661959A (zh) 2017-05-10
CA2952914C (fr) 2023-02-28
RU2017100264A (ru) 2018-07-25
EP3161270A1 (fr) 2017-05-03
JP2017531116A (ja) 2017-10-19
CA2952914A1 (fr) 2015-12-30
WO2015197949A1 (fr) 2015-12-30
FR3022890A1 (fr) 2016-01-01
FR3022890B1 (fr) 2018-01-05
CN106661959B (zh) 2018-11-13

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