EP2867481B1 - Tourillon de turbomachine comportant une couronne de récupération d'un flux d'huile de lubrification avec une pluralité d'orifices d'évacuation d'huile de lubrification - Google Patents

Tourillon de turbomachine comportant une couronne de récupération d'un flux d'huile de lubrification avec une pluralité d'orifices d'évacuation d'huile de lubrification Download PDF

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Publication number
EP2867481B1
EP2867481B1 EP13733393.6A EP13733393A EP2867481B1 EP 2867481 B1 EP2867481 B1 EP 2867481B1 EP 13733393 A EP13733393 A EP 13733393A EP 2867481 B1 EP2867481 B1 EP 2867481B1
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EP
European Patent Office
Prior art keywords
journal
flow
radially
oil
ring
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP13733393.6A
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German (de)
English (en)
French (fr)
Other versions
EP2867481A1 (fr
Inventor
Eddy Stéphane Joël FONTANEL
Giuliana Elisa ROSSI
Philippe Bouiller
Emmanuel DA COSTA
Julien FOLL
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/18—Lubricating arrangements
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/18—Lubricating arrangements
    • F01D25/183—Sealing means
    • 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
    • F05D2260/60—Fluid transfer
    • F05D2260/602—Drainage
    • F05D2260/6022—Drainage of leakage having past a seal

Definitions

  • the present invention relates to the field of turbomachines, in particular for aircraft, and aims to improve the circulation of lubricating oil and ventilation air in a turbomachine.
  • a turbojet engine comprises a casing 1 in which are mounted one or more rotating bodies via bearings (not shown).
  • a turbojet engine traditionally comprises an upstream compressor part, a combustion chamber and a downstream turbine part, a flow of air F flowing from upstream to downstream in the turbojet engine.
  • Such a turbojet engine is for example known applications FR 2944557 and FR 2934640 from the company SNECMA.
  • Rotating bodies are equipped with radial vanes to allow, on the one hand, to accelerate the flow of air F in the combustion chamber of the turbojet engine and, on the other hand, to recover the energy of the combustion.
  • the turbojet comprises a rotating body comprising a circumferential pin 2 connected upstream to a drum 3 by a bolted connection 4.
  • the drum 3 corresponds to a low pressure shaft of the turbojet engine.
  • Trunnion 2 conventionally comprises a main body 20 extending transversely to the axis of the turbojet engine and annular sealing pieces 5, 6 which are respectively fixed on the upstream and downstream faces of the main body 20 as illustrated in FIG. figure 1 .
  • the annular sealing pieces 5, 6 advantageously comprise sealing strips 50, 60 which cooperate with abradable elements 15, 16 integral with the casing 1 of the turbojet engine in order to form a sealed air stream in which the flow of air flows.
  • the turbojet engine comprises, in a conventional manner, a lubrication circuit.
  • the lubrication circuit is contained in a lubrication chamber which is disposed internally to the air circulation duct.
  • an oil flow H can escape from the lubrication chamber and enter the air stream as shown in the illustration. figure 1 .
  • the oil flow H is sprayed radially to be received in a recovery groove 61 of the journal 2 before being drained upstream to be reintroduced into the lubrication circuit.
  • the recovery ring allows to collect circumferentially any oil flow escaping from a lubrication chamber of the turbomachine.
  • the presence of discharge ports judiciously aligned with the connecting segments prevents the flow of oil is driven downstream by the air flow which is advantageous.
  • Such a journal has a simple structure and can be advantageously installed instead of a pin according to the prior art.
  • At least one connecting segment aligned radially with a discharge orifice of the recovery ring comprises means for guiding a radial oil flow.
  • the guide means are in the form of a radial groove.
  • the guiding means make it possible to channel the flow of oil during its radial displacement so as to prevent it from entering the ventilation holes.
  • a radial groove is simple to implement and allows forming a groove limiting any oil dispersion.
  • the guiding means is in the form of a guide channel so as to prevent circulation of the oil flows near the ventilation holes.
  • the guide channel has a U-shaped section so that the lateral edges of the guide channel block any flow of oil flows to the ventilation holes.
  • the guide channels could be closed and have a circular or flattened section.
  • the guide means preferably a guide channel
  • the connecting segment are attached to the connecting segment to prevent machining of the main body of the pin which could reduce its life.
  • Such an embodiment is advantageous for elongated, preferably oblong, ventilation holes.
  • the guiding means in particular a guiding channel, are integral with the circumferential ring so as to facilitate the assembly of the trunnion and a precise positioning of the guiding means with respect to the evacuation ports of the crown. circumferentially.
  • the trunnion comprises a circumferential groove for recovering the lubricating oil flows radially outside said ventilation orifices.
  • a recovery groove advantageously makes it possible to recover the oil which has passed between the ventilation openings.
  • the recovery groove comprises means for draining the flow of lubricating oil.
  • the drainage means are drainage holes, which preferably open into a lubricating oil drainage circuit.
  • the journal having radial sealing lamellae adapted to cooperate with an abradable element of the casing of the turbomachine, the recovery ring is radially external to said sealing lamellae.
  • any overflow of oil from the sealing strips is projected radially outwardly under the effect of centrifugal forces to be captured by the recovery ring.
  • the recovery ring extends longitudinally to the right of the sealing lamellae.
  • the length of the ring is adapted to collect the oil flow escaping from the sealing strips while being of reduced length to limit its mass.
  • the recovery ring extends longitudinally downstream from the main body of the pin.
  • the trunnion comprises a circumferential circumferential body of U-shaped section so as to define a base in plane contact with the main body, a radially upper branch forming the recovery ring and a radially lower branch on which are formed of radial sealing strips adapted to cooperate with an abradable element of the turbomachine casing.
  • the auxiliary body ensures the collection of possible leakage of lubricating oil.
  • the main body and the auxiliary body are connected together by a plurality of bolted connections so as to facilitate assembly and maintenance.
  • the invention also relates to a turbomachine, in particular for aircraft, comprising a housing and an axial body rotatably mounted in the housing, the rotary body having a journal as previously presented.
  • the turbojet engine comprises an upstream compressor part, a combustion chamber and a downstream turbine part, an air stream F flowing from upstream to downstream in the turbojet engine.
  • the turbojet comprises a low rotary body pressure comprising a circumferential pin 7 extending longitudinally of an axis XX and connected upstream to an axial drum 3 by a plurality of bolted connections 4.
  • the journal 7 comprises a main body 70 which extends substantially longitudinally to the axis XX and an upstream annular sealing piece 5 which is fixed on the upstream face of the main body 70 as illustrated in FIG. figure 2 .
  • the upstream annular sealing member 5 advantageously comprises sealing strips 50 which are adapted to cooperate with abradable elements 15 integral with the casing 1 of the turbojet engine in order to form a sealed air stream in which the air flow F circulates. .
  • the main body 70 of the pin 7 extends substantially in a radial plane and has a plurality of ventilation orifices 71 distributed angularly and circumferentially on the main body 70 so as to allow the flow of the axial air flow F upstream downstream through the trunnion 7 as shown on the Figures 2 to 4 .
  • two consecutive ventilation holes 71 are connected by a connecting segment 72 which extends in a plane substantially transverse to the axis XX of the pin 7.
  • an oil flow H is likely to flow on the face downstream of the pin 7.
  • the main body 70 further comprises a plurality of axial fastening orifices 76 distributed angularly and circumferentially on the main body 70 to allow the passage of fixing screws in order to integrally connect the drum 3 with the trunnion 7 by bolted connections 4.
  • the axial attachment holes 76 of the pin 7 are located radially inside the ventilation holes 71 as shown in FIG. figure 2 .
  • the journal 7 comprises a circumferential auxiliary body 9 of U-shaped section so as to define a base 82 in plane contact with the main body 70, a radially upper branch forming a recovery ring 8 and a radially lower branch 83 on which are formed radial sealing strips 85 adapted to cooperate with an abradable element 16 of the casing 1 of the turbojet engine.
  • the base 82 of the auxiliary body 9 extends radially and comprises a plurality of axial fastening orifices 84 distributed angularly and circumferentially to allow the passage of fixing screws in order to integrally connect the drum 3, the trunnion 7 and the auxiliary body 9 by bolted connections 4.
  • the radially upper branch 8 of the auxiliary body 9 extends longitudinally, that is to say orthogonally to the main body 70, and has a length less than that of the radially lower branch 83.
  • the radially upper branch 8 forms a crown 8 which extends to the right of the sealing strips 85 extending radially outwardly from the radially lower branch 83 to collect any flow oil H escaping via the sealing slats 85 under the effect of centrifugal forces as illustrated in FIG. figure 4 .
  • the recovery ring 8 has a plurality of radial discharge holes 81 to allow the evacuation of a plurality of radial oil flows H outwardly.
  • the discharge orifices 81 are distributed angularly and circumferentially so as to allow homogeneous discharge of the flow of lubricating oil H.
  • each discharge orifice 81 is aligned radially with a connecting segment 72 of the main body 70 so as to allow each oil flow H to be discharged between the air flows F.
  • the number of discharge ports 81 is less than the number of link segments 72, preferably three times smaller.
  • the main body 70 of the pin 7 has a circumferential groove 73 for recovering lubricating oil flows H radially external to said ventilation orifices 71. Once in contact with the walls of the recovery groove 73, the flow of oil The lubricating groove H is less likely to be disturbed by the air flow F. More preferably, the recovery groove 73 comprises drainage means 74 of the lubricating oil flow which are, for example, in the form of radial or oblique holes.
  • At least one connecting segment 72 comprises means for guiding a radial oil flow H so as to allow the flow of oil H to be conveyed from the discharge orifices 81 of the crown. 8 to the recovery groove 73.
  • the guide means are in the form of a radial groove or a radial channel.
  • journal 7 has been shown a journal 7 with a main body 70 independent of the auxiliary body 9 but it goes without saying that the invention also applies to a journal having a main body and an auxiliary body forming a unitary assembly.
  • the journal 7 comprises a main body 70 which extends obliquely to a radial plane and comprises a plurality of ventilation orifices 71 distributed angularly and circumferentially on the main body 70 so as to allow the flow of the axial air flow F from upstream to downstream through the pin 7 as illustrated on the figure 5 .
  • an oil flow H is likely to flow on the upstream face of the pin 5.
  • the ventilation openings 71 are oblong, their length extending radially as illustrated in FIG. figure 6 in order to increase the air flow.
  • the trunnion 7 includes a circumferential auxiliary body 9 having a recovery ring 8 which comprises a plurality of radial discharge holes 81 to allow the evacuation of a plurality of radial oil flows H outwardly as shown in the figure 8 .
  • the discharge orifices 81 are distributed angularly and circumferentially so as to allow homogeneous discharge of the flow of lubricating oil H.
  • each discharge orifice 81 is radially aligned with a connecting segment 72 of the main body 70 so as to allow each oil flow H to be discharged between the air flows F, ie between the ventilation openings 71.
  • the oblong ventilation holes 71 disturb the circulation of the oil flow H on the connecting segments 72, the oil flow H being able to deviate from its direction of radial circulation.
  • At least one connecting segment 72 comprises means for guiding a radial oil flow H in order to avoid any deflection along the oblong ventilation orifices 71.
  • the circumferential auxiliary body 9 comprises a plurality of guide channels 86 which are mounted on the connecting segments 72, opposite, the discharge orifices 81.
  • Each guide channel 86 extends along the connecting segment 72 on which it is intended to be mounted, the cross section of a guide channel preferably has a shape of U so as to prevent any deviation of the flow of oil H during its circulation between consecutive ventilation holes 71, in especially when they are oblong.
  • the discharge orifices 81 open opposite the base of the U guide channels 86 so that the branches of the U prevent any flow of oil flow in the adjacent ventilation holes 71 as illustrated at figure 8 .
  • the guide channels 86 may be closed and have a circular or flattened section.
  • the circumferential ring 8 and the guide channels 86 are joined by welding.
  • the auxiliary body 9 can thus be mounted simply and quickly on the main body 70 of the pin 7.
  • the discharge holes 81 are precisely aligned with the guide channels 86 due to their attachment to the crown. circumferential 8 which is advantageous.
  • guide channels 86 reported on the pin 7 is more advantageous than the formation of channels in the main body 70 of the pin 7 since machining can weaken the structure of the pin 7. Such an embodiment is particularly advantageous when the ventilation holes 71 are elongated.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
  • Lubrication Details And Ventilation Of Internal Combustion Engines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP13733393.6A 2012-06-28 2013-06-12 Tourillon de turbomachine comportant une couronne de récupération d'un flux d'huile de lubrification avec une pluralité d'orifices d'évacuation d'huile de lubrification Active EP2867481B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1256173A FR2992679A1 (fr) 2012-06-28 2012-06-28 Tourillon de turbomachine comportant une couronne de recuperation d'un flux d'huile de lubrification avec une pluralite d'orifices d'evacuation d'huile de lubrification
PCT/FR2013/051377 WO2014001681A1 (fr) 2012-06-28 2013-06-12 Tourillon de turbomachine comportant une couronne de récupération d'un flux d'huile de lubrification avec une pluralité d'orifices d'évacuation d'huile de lubrification

Publications (2)

Publication Number Publication Date
EP2867481A1 EP2867481A1 (fr) 2015-05-06
EP2867481B1 true EP2867481B1 (fr) 2017-03-15

Family

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Application Number Title Priority Date Filing Date
EP13733393.6A Active EP2867481B1 (fr) 2012-06-28 2013-06-12 Tourillon de turbomachine comportant une couronne de récupération d'un flux d'huile de lubrification avec une pluralité d'orifices d'évacuation d'huile de lubrification

Country Status (8)

Country Link
US (1) US9765645B2 (ru)
EP (1) EP2867481B1 (ru)
CN (1) CN104379880B (ru)
BR (1) BR112014031534B1 (ru)
CA (1) CA2876347C (ru)
FR (2) FR2992679A1 (ru)
RU (1) RU2638412C2 (ru)
WO (1) WO2014001681A1 (ru)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3005101B1 (fr) * 2013-04-30 2017-07-28 Snecma Support de palier d'une turbomachine comportant une partie amovible
FR3008738B1 (fr) * 2013-07-16 2015-08-28 Snecma Dispositif de protection contre les fuites d'huile vers les rotors d'une turbine de turbomachine
FR3052487B1 (fr) 2016-06-10 2018-06-15 Safran Aircraft Engines Element tubulaire de rotor a section etoilee pour une turbomachine
FR3096413B1 (fr) * 2019-05-22 2021-05-21 Safran Aircraft Engines Partie d’une turbomachine
FR3101662B1 (fr) * 2019-10-03 2023-04-14 Safran Aircraft Engines Agencement de turbine intégrant une rigole circonférentielle de récupération d’huile
US11459911B2 (en) 2020-10-30 2022-10-04 Raytheon Technologies Corporation Seal air buffer and oil scupper system and method
FR3118989B1 (fr) * 2021-01-21 2023-03-03 Safran Aircraft Engines Couronne de ventilation du support de palier arrière d'une turbomachine d'aéronef

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Also Published As

Publication number Publication date
US9765645B2 (en) 2017-09-19
EP2867481A1 (fr) 2015-05-06
CN104379880A (zh) 2015-02-25
CN104379880B (zh) 2016-05-25
RU2638412C2 (ru) 2017-12-13
BR112014031534B1 (pt) 2021-12-07
CA2876347A1 (fr) 2014-01-03
FR2992679A1 (fr) 2014-01-03
US20150147157A1 (en) 2015-05-28
BR112014031534A2 (pt) 2017-06-27
CA2876347C (fr) 2020-05-12
FR2992680B1 (fr) 2014-07-18
RU2014153555A (ru) 2016-08-20
FR2992680A1 (fr) 2014-01-03
WO2014001681A1 (fr) 2014-01-03

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