WO2013182797A1 - Turbomachine comportant des moyens de fixation amont d'un tube de deshuilage - Google Patents
Turbomachine comportant des moyens de fixation amont d'un tube de deshuilage Download PDFInfo
- Publication number
- WO2013182797A1 WO2013182797A1 PCT/FR2013/051253 FR2013051253W WO2013182797A1 WO 2013182797 A1 WO2013182797 A1 WO 2013182797A1 FR 2013051253 W FR2013051253 W FR 2013051253W WO 2013182797 A1 WO2013182797 A1 WO 2013182797A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- tube
- deoiling
- clutch
- shaft
- upstream
- Prior art date
Links
Classifications
-
- 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
- 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
-
- 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 present invention relates to the field of turbomachines and, more particularly, the attachment of a deoiling tube in an aircraft turbine engine shaft.
- a turbojet engine conventionally comprises at least one rotary shaft on which vanes are mounted to accelerate an upstream flow of air downstream in the turbojet engine body.
- the turbojet engine comprises a compressor part upstream and a turbine part downstream.
- the turbojet engine comprises a structural casing in which the rotary shaft is mounted by means of bearings.
- the turbojet engine has a lubrication circuit for conveying lubricating oil to the bearings.
- the lubricating oil is located in oil enclosures that are kept under pressure.
- the turbojet engine conventionally comprises means for exhausting a flow of air mixed with oil particles, it is called "oiled air flow". Before being able to release the flow of oiled air into the atmosphere, it is de-oiled by introducing it into a deoiling tube mounted internally to the rotary shaft of the turbojet engine.
- FIG. 1 partially represents a sectional view of a low-pressure shaft of a turbojet engine extending along the axial axis XX, the low-pressure shaft 1 comprising an upstream compressor shaft 1 1 and a downstream turbine shaft 12.
- a de-oiling tube 2 is integrally mounted in the shaft 1.
- the de-oiling tube 2 conventionally comprises an upstream portion 21 and a downstream portion 22 which are aligned longitudinally.
- the upstream end of the turbine shaft 12 is mounted internally to the compressor shaft January 1 and is integrally connected thereto by a main nut 3 mounted from upstream and outwardly to the turbine shaft 12.
- This connection by means of the main nut 3 makes it possible to transmit the torque between the turbine shaft 12 and the compressor shaft 1 1.
- the downstream portion 21 of the deoiling tube 2 is mounted internally to the turbine shaft 12 by means of an upstream auxiliary nut 4 which exerts a longitudinal support directed downstream on the de-oiling tube 2.
- the downstream portion 22 of the deoiling tube 2 is mounted downstream in the upstream portion 21 of the deoiling tube 2 as shown in Figure 2B.
- the deoiling tube 2 comprises at the level the connection a mechanical elastic seal so as to achieve a radial blocking of the tube 2 in the shaft 1.
- the downstream end of the tube 2 is locked downstream by a downstream auxiliary nut 6 which allows exert a longitudinal support directed upstream on the de-oiling tube 2, the downstream auxiliary nut 6 being mounted internally to the turbine shaft 12.
- the compressor shaft 1 1 comprises a radial orifice 10 from which is ejected a flow of oiled air H to be driven by a rotating air flow F flowing axially in the tube of de-oiling 2.
- the oiled air stream is vortexed to facilitate de-oiling.
- the upstream assembly means of the deoiling tube 2 form an upstream projecting portion which disturbs the introduction of the oiled air flow H into the de-oiling tube 2.
- the longitudinal distance L between the ejection orifice 10 and the upstream fixing means of the deoiling tube 2 has a preponderant role in the disturbances. When this distance L is small, of the order of 40 mm, the air flow is disturbed.
- the upstream fixing means of the deoiling tube 2 are complex because they require an auxiliary nut upstream and downstream which has disadvantages.
- the invention relates to a turbomachine in which circulates an upstream stream of air downstream, in particular for an aircraft, comprising an axially extending rotary shaft and a deoiling tube mounted integrally and internally to said shaft by upstream fixing means, the upstream fixing means comprise a first internal interconnection extending internally from the shaft, a second interconnection extending externally from the deoiling tube, which is aligned longitudinally with the first clutch and located downstream of the first clutch, and a longitudinal lock anti-rotation lock, extending between the rotary shaft and the deoiling tube, so as to prohibit the rotation of the second clutch of the deoiling tube relative to the first interconnection of the rotary shaft.
- the upstream fastening means according to the invention advantageously make it possible to secure the de-oiling tube to the shaft by blocking on the one hand the axial translation and on the other hand the relative rotation by avoiding the use of a source upstream auxiliary nut. disturbance of the oiled air flow.
- such fastening means have a limited size and are simple to mount.
- the mass of the fastening means is reduced which is an advantage from the point of view of fuel consumption. Thanks to the invention, the distance between the ejection orifice and the upstream fixing means of the de-oiling tube is advantageously increased, which limits the disturbances of the air flow.
- the locking latch comprises an annular body. More preferably, the locking latch comprises at least one axial tongue extending between two consecutive teeth of the first interconnection inside and between two consecutive teeth of the second interconnection outside.
- the tabs advantageously make it possible to block the relative rotation between the shaft and the deoiling tube.
- the upstream fastening means comprise an axial locking ring, mounted between the de-oiling tube and the anti-rotation locking latch, so as to prevent the axial displacement of the locking lock with respect to the 'tree. Thanks to the locking ring, the lock is pressed radially against the shaft which prevents its axial displacement.
- Such a ring is of simple design and can be easily mounted in the constrained state.
- the deoiling tube comprises an annular housing in which is mounted the axial locking ring.
- the locking ring is not protruding from its housing and does not prevent the mounting of the lock between the deoiling tube and the shaft.
- the locking latch comprises an annular groove adapted to be in contact with the axial locking ring and thus guide when it exerts its radial thrust to the outside.
- the axial locking ring is resilient to be mounted prestressed.
- the ring is slit so as to have elastic properties.
- the locking latch comprises at least one radial disassembly orifice adapted to allow the introduction of a disassembly tool from upstream in said disassembly port.
- the turbomachine comprises an annular cover sheet covering the upstream ends of the deoiling tube and the shaft.
- the fastening means do not disturb the flow of oiled air during its introduction into the deoiling tube.
- the invention also relates to a method for fixing a deoiling tube in a rotary shaft of a turbomachine in which circulates an upstream stream of air downstream, in particular for aircraft, the shaft comprising a first internal clutch extending internally, the deoiling tube having a second externally extending interconnection, the method comprising: a step of inserting the deoiling tube into the shaft from upstream,
- the method comprises a step of inserting a locking ring between the shaft and the deoiling tube prior to insertion of the locking bolt.
- Figure 1 is a schematic representation in axial section of mounting a deoiling tube in a shaft of a turbomachine (already commented);
- Figure 2A is a schematic representation in axial section of the upstream attachment means of the deoiling tube according to the prior art (already commented);
- Figure 2B is a schematic representation in axial section of the central support of the deoiling tube (already commented);
- Figure 2C is a schematic representation in axial section of the downstream fixing means of the deoiling tube (already commented);
- FIG. 3 is a schematic representation in axial section of the upstream fixing means of the deoiling tube according to the invention.
- Figure 4 is a schematic representation in axial section close to the upstream fixing means of the deoiling tube of Figure 3;
- Figure 5 is a schematic representation in cutaway perspective of the upstream fastening means of the deoiling tube of Figure 3 without the locking bolt;
- FIG. 6 is a schematic perspective view of the locking latch
- FIG. 7 is a diagrammatic perspective view of the upstream fixing means of the deoiling tube of FIG. 3 with the locking bolt.
- FIG. 3 represents a sectional view of the low-pressure shaft of the turbojet engine extending along the axial axis XX, the low-pressure shaft 1 comprising an upstream compressor shaft 1 1 and a vs
- the compressor shaft 1 1 is in the form of an annular piece which has radially extending deoiling orifices 10.
- a de-oiling orifice 10 makes it possible to eject a flow of oiled air H internally to the compressor shaft 1 1.
- the turbine shaft 12 is in the form of an annular piece of which the upstream end is mounted internally to the compressor shaft January 1 and integrally connected thereto by a main nut 3 mounted from upstream and outwardly to the turbine shaft 12. This connection by means of the nut main 3 makes it possible to transmit the torque between the turbine shaft 12 and the compressor shaft 1 1.
- the lateral dimension of the main nut 3 has been shortened compared to the prior art while retaining the same number of threads to maintain the same degree of fixation.
- the main nut 3 is clamped axially against a radial stop of the compressor shaft January 1 similarly to the prior art.
- the turbojet engine comprises a deoiling tube 7 mounted integrally inside the turbine shaft 12.
- the deoiling tube 7 is in the form of an annular piece extending axially in the turbojet engine along an axis XX.
- the deoiling tube 7 comprises an upstream portion and a downstream portion that are aligned longitudinally.
- the invention relates to the upstream fixing means of the de-oiling tube 7 in the turbine shaft 12 also, the central support means and the downstream fastening means are identical to the prior art as previously described in FIGS. 2C.
- the turbine shaft 12 comprises a first interconnection 13 which extends radially inwardly and is designated by the following interconnection internal.
- a dog clutch is a set of protruding teeth, two consecutive teeth being separated by a space in which can pass a protruding tooth of another interconnection.
- the inner clutch 13 has a plurality of teeth projecting radially inwards and angularly distributed at the inner periphery of the turbine shaft 12 as illustrated in FIGS. 4 and 5.
- the de-oiling tube 7 comprises a second clutch 71 which extends radially outwards and is designated by the following external clutch.
- the outer clutch 71 has a plurality of teeth projecting radially outward and angularly distributed at the outer periphery of the de-oiling tube 7 as shown in Figures 4 and 5.
- the radial distance of the clutch 13, 71 by ratio the axis XX of the turbojet engine is identical so as to prevent a radial displacement of the clutch 13, 71 relative to each other when the teeth of the clutch 13, 71 are aligned longitudinally, that is to say, parallel to the axis XX of the turbojet engine.
- the turbojet engine furthermore comprises a longitudinal anti-rotation locking latch 8 extending between the turbine shaft 12 and the de-oiling tube 7, so as to prevent rotation.
- the locking latch 8 comprises an annular body 80 extending axially along the axis XX in the turbojet engine and three locking tabs 82 extending longitudinally from the body 80 downstream.
- the locking latch 8 could comprise a different number of tongues 82.
- the tongues 82 are angularly distributed around the circumference of the locking latch 8.
- each tongue 82 has the shape of a curved rectangle of so as to be placed between the teeth of the dog clutch 13, 71.
- the locking tabs 82 are adapted to extend between two consecutive teeth of an inner clutch 13 or outer 71 to form an anti -rotation.
- the combination of the clutch 71, 13 and the locking bolt 8 allows to fix the de-oiling tube 7 to the turbine shaft 12 by preventing any rotation and axial displacement.
- the upstream fastening means comprise an axial locking ring 91, mounted between the de-oiling tube 7 and the anti-rotation lock 8, so as to prevent the axial displacement of the de-oiling tube 7 with respect to the lock.
- the axial locking ring 91 is in the form of a split metal ring so as to have elastic properties so that it can be compressed radially.
- the deoiling tube 7 comprises an annular housing 72 located upstream of the outer clutch 71 as illustrated in FIG. 4.
- the annular housing 72 is in the form of a annular groove whose cavity is turned towards the outside and whose radial depth is able to receive completely the axial locking ring 91.
- the locking latch 8 comprises, for its part, an annular groove 81, whose cavity is turned inward, adapted to be in contact with the axial locking ring 91 to limit its radial outward movement.
- the axial locking ring 91 is mounted in the prestressed state between the de-oiling tube 7 and the lock of blocking 8 so that it exerts a radial force on the locking latch 8 in order to press against the turbine shaft 12 and thus prevent its axial displacement.
- the locking bolt 8 has three disassembly lugs 83 which extend longitudinally upstream from its annular body 80.
- the disassembly lugs 83 are angularly distributed around the circumference of the locking bolt 8.
- the locking latch 8 could comprise a different number of disassembly lugs 83.
- Each dismounting lug 83 has a radial disassembly orifice 84 adapted to allow the introduction of a disassembly tool from the upstream in said disassembly port 84, for example, a claw plier as will be detailed later.
- a disassembly tool from the upstream in said disassembly port 84, for example, a claw plier as will be detailed later.
- the disassembly lugs 83 are longitudinally aligned with the locking tabs 82 so that a longitudinal force applied to a dismounting lug 83 is applied directly to a locking tab 82.
- the de-oiling tube 7 comprises an annular groove 73, located upstream of the outer clutch 71, whose cavity is turned inward and whose radial depth is able to receive a complete seal 92 an annular cover plate 10 covering the upstream ends of the deoiling tube 7 and the turbine shaft 12 as shown in Figure 3.
- the seal 92 is in this annular example.
- the cover plate 10 is annular and has a U-shaped section facing downstream so as to provide an aerodynamic profile to the air flowing internally to the shaft 1.
- the radially upper end of the sheet cover 10 is in contact with the lower surface of the compressor shaft 1 1 in order to limit any disruption of the air flow to the connection between the compressor shaft 1 1, the turbine shaft 12 and the fan tube. de-oiling 7.
- the seal 92 makes it possible to prevent air circulation between the sheet 10 and the de-oiling tube 7 as illustrated in FIG. 3.
- the cover plate 10 is slotted so as to facilitate its mounting.
- the de-oiling tube 7 is inserted into the turbine shaft 12 from upstream. Then, the de-oiling tube 7 is oriented angularly so that the second external clutch 71 is not aligned longitudinally with the first internal clutch 13 of the turbine shaft 12. Thus, the de-oiling tube 7 can be moved axially downstream so that the second outer clutch 71 is located downstream of the first inner clutch 13. In fact, the teeth of the second outer clutch 71 can pass into the spaces between two consecutive teeth of the first internal clutch 13.
- the deoiling tube 7 is oriented angularly so that the second clutch 71 is aligned longitudinally with the first clutch 13. Thus, any axial displacement upstream of the deoiling tube 7 is not allowed. Then, the locking ring 91 is introduced under stress into the housing 72 of the de-oiling tube 7 and the lock 0
- the seal 92 is introduced beforehand into the annular groove 73 before the cover plate 10 is placed inside the seal 92. Once placed, the seal 92 prevents any air circulation between the sheet 10 and the de-oiling tube 7.
- the cover plate 10 comprises fastening means to the main nut 3.
- the de-oiling tube 7 is attached downstream by a downstream auxiliary nut which axially constrains the de-oiling tube 7 against the inner clutch 13 of the turbine shaft 12. This axial force is transmitted to the external clutching. 13 which relies on the internal interconnection 71.
- the cover plate 10 is removed and then, with the aid of a claw-type disassembly tool, the locking bolt 8 is gripped by its disassembly holes 84. With the aid of the disassembly tool, an axial force is applied to the disassembly lugs 83 of the latch 8 to forcibly remove the locking latch 8 by opposing the plating force of the locking ring 91. Once the lock lock 8 removed, the locking ring 91 is also out of the turbojet engine. Then, the de-oiling tube 7 is oriented angularly so that the second external clutch 71 is not aligned longitudinally with the first internal clutch 13 of the turbine shaft 12.
- the de-oiling tube 7 can be moved axially upstream, the teeth of the second outer clutch 71 passing in the spaces between two consecutive teeth of the first internal clutch 13.
- the de-oiling tube 7 is then completely out of the turbojet engine.
- the invention has been presented for mounting a deoiling tube in a turbine shaft but it goes without saying that it could be mounted in another type of shaft, for example, a compressor shaft.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Lubrication Of Internal Combustion Engines (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Mechanical Operated Clutches (AREA)
Abstract
Description
Claims
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US14/401,911 US9784130B2 (en) | 2012-06-05 | 2013-06-03 | Turbine engine comprising an upstream attachment means for a de-oiling pipe |
GB1421713.7A GB2517860B (en) | 2012-06-05 | 2013-06-03 | Turbine engine comprising an upstream attachment means for a de-oiling pipe |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1255230A FR2991386B1 (fr) | 2012-06-05 | 2012-06-05 | Turbomachine comportant des moyens de fixation amont d'un tube de deshuilage |
FR1255230 | 2012-06-05 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2013182797A1 true WO2013182797A1 (fr) | 2013-12-12 |
Family
ID=46889207
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2013/051253 WO2013182797A1 (fr) | 2012-06-05 | 2013-06-03 | Turbomachine comportant des moyens de fixation amont d'un tube de deshuilage |
Country Status (4)
Country | Link |
---|---|
US (1) | US9784130B2 (fr) |
FR (1) | FR2991386B1 (fr) |
GB (1) | GB2517860B (fr) |
WO (1) | WO2013182797A1 (fr) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3107717A1 (fr) * | 2020-02-27 | 2021-09-03 | Safran Aircraft Engines | Tube de dégazage pour une turbomachine |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3028781B1 (fr) * | 2014-11-25 | 2016-12-30 | Snecma | Piece pour rotor de turbomachine d'aeronef comprenant une protuberance annulaire usinable pourvue d'un orifice de deshuilage et procede de preparation de celle-ci |
FR3075868B1 (fr) * | 2017-12-22 | 2019-11-15 | Safran Aircraft Engines | Tube de degazage pour une turbomachine d'aeronef a reducteur |
FR3087224B1 (fr) * | 2018-10-10 | 2021-05-21 | Safran Aircraft Engines | Systeme de fixation d'un arbre d'une turbine contrarotative pour une turbomachine d'aeronef |
US11415015B2 (en) | 2019-10-23 | 2022-08-16 | Pratt & Whitney Canada Corp. | Sleeve for oil service tubes |
US11268442B2 (en) * | 2020-07-01 | 2022-03-08 | Raytheon Technologies Corporation | Mid mount sleeve arrangement |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
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US20090134243A1 (en) * | 2007-11-28 | 2009-05-28 | General Electric Company | Air-oil separator |
FR2926604A1 (fr) | 2008-01-23 | 2009-07-24 | Snecma Sa | Centrage d'une piece a l'interieur d'un arbre de rotor dans une turbomachine |
FR2928566A1 (fr) * | 2008-03-12 | 2009-09-18 | Snecma Sa | Deshuileur centrifuge a section de passage variable |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
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US5257903A (en) * | 1991-10-30 | 1993-11-02 | General Electric Company | Low pressure drop radial inflow air-oil separating arrangement and separator employed therein |
US6325381B1 (en) * | 1999-05-04 | 2001-12-04 | System Seals, Inc. | High-pressure rotary seal |
FR2896827B1 (fr) * | 2006-01-27 | 2008-04-25 | Snecma Sa | Assemblage a encombrement radial reduit entre un arbre de turbine et un tourillon d'arbre de compresseur de turbomachine |
US7704029B2 (en) * | 2007-11-19 | 2010-04-27 | Pratt & Whitney Canada Corp. | Arrangement for releasably holding a component in a fixed position on a shaft |
US8092132B2 (en) * | 2008-12-05 | 2012-01-10 | American Axle & Manufacturing, Inc. | Fastener with anti-rotation clip |
US8459954B2 (en) * | 2010-01-19 | 2013-06-11 | United Technologies Corporation | Torsional flexing energy absorbing blade lock |
US8875378B2 (en) * | 2011-11-07 | 2014-11-04 | United Technologies Corporation | Tie bolt employing differential thread |
-
2012
- 2012-06-05 FR FR1255230A patent/FR2991386B1/fr active Active
-
2013
- 2013-06-03 US US14/401,911 patent/US9784130B2/en active Active
- 2013-06-03 WO PCT/FR2013/051253 patent/WO2013182797A1/fr active Application Filing
- 2013-06-03 GB GB1421713.7A patent/GB2517860B/en active Active
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20090134243A1 (en) * | 2007-11-28 | 2009-05-28 | General Electric Company | Air-oil separator |
FR2926604A1 (fr) | 2008-01-23 | 2009-07-24 | Snecma Sa | Centrage d'une piece a l'interieur d'un arbre de rotor dans une turbomachine |
FR2928566A1 (fr) * | 2008-03-12 | 2009-09-18 | Snecma Sa | Deshuileur centrifuge a section de passage variable |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3107717A1 (fr) * | 2020-02-27 | 2021-09-03 | Safran Aircraft Engines | Tube de dégazage pour une turbomachine |
Also Published As
Publication number | Publication date |
---|---|
GB2517860A (en) | 2015-03-04 |
GB201421713D0 (en) | 2015-01-21 |
US9784130B2 (en) | 2017-10-10 |
GB2517860B (en) | 2020-02-19 |
FR2991386A1 (fr) | 2013-12-06 |
FR2991386B1 (fr) | 2014-07-18 |
US20150167495A1 (en) | 2015-06-18 |
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