WO2009144300A1 - Ensemble d'un disque de turbine d'un moteur a turbine a gaz et d'un tourillon support de palier, circuit de refroidissement d'un disque de turbine d'un tel ensemble - Google Patents
Ensemble d'un disque de turbine d'un moteur a turbine a gaz et d'un tourillon support de palier, circuit de refroidissement d'un disque de turbine d'un tel ensemble Download PDFInfo
- Publication number
- WO2009144300A1 WO2009144300A1 PCT/EP2009/056617 EP2009056617W WO2009144300A1 WO 2009144300 A1 WO2009144300 A1 WO 2009144300A1 EP 2009056617 W EP2009056617 W EP 2009056617W WO 2009144300 A1 WO2009144300 A1 WO 2009144300A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- turbine
- openings
- radial annular
- trunnion
- assembly
- 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
- 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
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
- F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc
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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
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
-
- 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
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
- F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
-
- 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
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
-
- 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 dual-body gas turbine engines and, more particularly, the cooling of a high-pressure turbine disk of a dual-body gas turbine engine.
- a front-blower and double-body turbojet engine comprises a low-pressure body, called BP body, and a high-pressure body, called HP body.
- a front-blown double-bladed turbojet engine conventionally comprises, from upstream to downstream, a blower, a LP compressor stage, an HP compressor stage, a combustion chamber, an HP turbine stage and a LP turbine stage.
- the shaft of the body BP is guided in rotation in bearings supported by the fixed structure of the engine while the shaft of the HP body is guided by bearings supported by the BP body, the shafts of the two bodies being concentric.
- turbojet engine During operation of the turbojet engine, a mixture of air and fuel is burned in the combustion chamber of the engine to create the thrust required for the displacement of the aircraft on which the turbojet engine is mounted. After combustion, a gas flow at very high temperature circulates in the HP turbine of the turbojet engine.
- HP turbine disk The elements of the turbine, in particular the HP body turbine disk, hereafter referred to as HP turbine disk, are subjected to very high temperatures. high.
- the engine is provided with cooling circuits in which air, drawn upstream of the HP turbine, flows, upstream and downstream in the turbojet, internally to the HP turbine disk. and externally to the BP tree.
- the HP turbine disk cooling circuit is referred to as the cooling circuit of the turbine disk bore, better known by its English name "Circuit Bore Cooling".
- the HP trunnion includes, inter alia, a ring for mounting the bearing 17 for guiding the HP body on the LP shaft as shown in FIG.
- the HP trunnion 10 is fixed by its upstream end to the HP turbine disk 20, the HP turbine disk 20 comprising a radial annular fixing flange 25 coming into contact with a radial annular portion 15 of the trunnion.
- HP 10 The attachment flange 25 of the HP turbine disk 20 is bolted to the HP journal 10 by longitudinal bolts 2.
- the through openings 11 ventilation of the HP 10 trunnion, allowing the evacuation of the cooling air flow, are provided downstream of the portion of the HP trunnion 10 which is bolted to the HP turbine disk 20.
- the openings ventilation through 11 are formed in a frustoconical portion 12 of the HP 10 trunnion, flared upstream, which is highly mechanically stressed in operation.
- the through openings ventilation 11 are machined obliquely in the frustoconical portion 12 of the HP trunnion 10.
- the ventilation openings 11 are not orthogonal to the surface of the frustoconical portion 12 of the HP trunnion 10.
- These oblique openings 11 are difficult to machine, the frustoconical portion 12 of the HP trunnion 10 being difficult to access by the machining tools.
- the through ventilation openings 11 have sharp edges with concentration of fatigue stresses that are likely to weaken the pin HP 10 during its operation.
- the Applicant proposes an assembly of a turbine disk of a gas turbine engine and a bearing support journal, the turbine disc comprising a radial annular mounting flange integral with a radial annular portion of the trunnion by bolts, the bolts successively passing through fixing bores formed in the radial annular flange for fastening the turbine disk and in the radial annular portion of the trunnion, together characterized by the fact that the radial annular portion of the trunnion comprises air circulation openings, the openings being formed between the fixing bores of the trunnion.
- the flow openings of the cooling air flow are formed on the radial annular portion of the journal between the journal fixing bores. This advantageously allows to distribute the mechanical stresses on said radial annular portion of the pin between the fixing bores and the cooling openings, the level of mechanical stress for each bore and each opening being then lower.
- the mounting flange is easily accessible which facilitates the machining of the discharge openings which can be made at the same time as the fixing bores.
- the frustoconical portion of the trunnion no longer performs a cooling air evacuation function, which advantageously makes it possible to add material to this part in order to increase the mass close to the axis of the trunk. rotation of the pin (which is also the axis of the motor) and thus reduce the fatigue caused by the rotation of the pin.
- the radial annular flange for fixing the turbine disk is in the form of a crenellated radial annular band comprising teeth separated by slots, the turbine mounting bores being formed in the teeth of said crenellated strip.
- the radial annular fixing flange is advantageously castellated to reduce the mass of the turbine while allowing the attachment of the turbine to the trunnion.
- the slots of the radial annular fixing flange are arranged for, during attachment of the turbine to the journal, correspond with the air circulation openings provided on the radial annular portion of the journal.
- the air flow circulates successively between the teeth of the mounting flange of the turbine and in the air circulation openings of the spigot.
- the circulation openings and the fixing bores are arranged circumferentially on the radial annular portion of the journal.
- the mechanical stresses are uniformly distributed around the circumference of the trunnion, avoiding the formation of areas of weakness.
- the trunnion comprises a frustoconical portion, downstream of its radial annular portion, comprising an inner radial portion, close to the axis of rotation, thickened ensuring the mechanical strength of the disk, the weight distribution being thus optimized.
- the part The frustoconical trunnion serves a mechanical reinforcement and limits the impact of the centrifugal forces on the trunnion.
- a sealing disc mounted downstream of the journal, is bolted with the journal and the turbine disc, the sealing disc including circulation openings which are aligned with the circulation openings of the journal.
- the sealing disc advantageously makes it possible to seal while allowing the passage of the cooling air of the turbine disc.
- the passage section of the circulation openings of the sealing disk is adapted to calibrate the flow rate of the flow of air.
- the sealing disc is a lightweight mechanical part that is easy to machine.
- the invention also relates to a cooling circuit of the turbine disk in a gas turbine engine comprising an exhaust passage, downstream of the turbine disk, passing through said openings of an assembly as described above.
- the cooling circuit comprises an upstream passage through a central bore of the turbine disk, upstream of the openings of said assembly.
- the cooling circuit in a dual-body engine comprises a high pressure turbine and a low pressure turbine, the turbine of said assembly being the high pressure turbine .
- the circuit comprises a downstream passage, formed downstream of the openings of said assembly, for partially cooling the low pressure turbine.
- FIG. 1 represents a view in axial section of a turbojet engine comprising a cooling circuit of the turbine disk of a turbojet engine according to the prior art
- FIG. 2 shows an axial sectional view of a turbojet engine comprising a cooling circuit of the turbine disk of a turbojet according to the invention
- FIG. 3 represents a perspective view of a turbine disk and a journal of a turbojet according to the invention, the disk and the journal being partially represented;
- FIG. 4 shows the turbine disk and a portion of the pin of Figure 3;
- FIG. 5 schematically represents, in cross-section, the fastening of the turbine disc to the journal of FIG. 4, seen from upstream to downstream, and
- FIG. 6 partially represents, in perspective, a turbine disc, a trunnion and a labyrinth seal according to a second embodiment of the invention.
- a front-blower and double-body turbojet engine comprises a low-pressure body, called BP body, and a high-pressure body, called HP body.
- the terms “inside” and “outside” are defined radially with respect to the axis of the motor.
- a cylinder extending along the axis of the engine has an inner face facing the axis of the motor and an outer surface opposite to its inner surface.
- the HP turbine stage comprises an HP turbine disk 200 which is mounted integral with an HP pin 100, upstream of the latter.
- the HP 200 turbine disk is in the form of a bladed wheel whose blades extend radially and externally relative to the axis of the motor.
- the HP turbine disk 200 comprises a central bore 201 through which the BP shaft passes.
- the thickness of the HP turbine disk 200 is not uniform, the disk 200 comprising a circumferential bulge near its central opening 201.
- the HP turbine disk 200 comprises centrally an axial extra thickness, mechanical reinforcement, so as to increase the mass of the disk 200 near the axis of the motor and thus reduce the mechanical stresses in operation.
- the HP turbine disk 200 comprises a radial upstream fastening annular flange 240 bolted to a drum associated with a flange 241 for supporting sealing strips and guiding the cooling air of the blades. turbine, the drum being bolted to the HP compressor of the engine.
- the drum makes it possible to transmit to the compressor HP the energy of the combustion of the engine recovered by the turbine disc 200.
- the HP turbine disk 200 includes a downstream radial annular flange 250 for maintaining the downstream HP 100 trunnion.
- the downstream flange 250 is in the form of a crenellated radial annular band 250 comprising teeth 251 separated by crenellations 252 as shown in FIGS. 4 and 5. Thereafter, a slot is defined as the space between two teeth. 251 successive of the crenellated band 250.
- the teeth 251 of the downstream fastening flange 250 (shown in hatched form) extend radially towards the axis of the motor and are directed towards the central bore 201 of the turbine disk 200.
- the trunnion HP 100 is in the form of a part of revolution, substantially flared upstream and extending along the axis of the motor.
- the trunnion HP 100 comprises, from upstream to downstream, a radial annular fixing portion 150, arranged to attach to the flange 250 of the HP turbine disk 200, a frustoconical portion 102 and a longitudinal cylindrical portion 103.
- the longitudinal cylindrical portion 103 of the trunnion HP 100 comprises at its downstream end an external thread intended to receive an outer ring on which is mounted an inter-shaft bearing, this bearing (not shown) allowing the HP turbojet body to be supported by the BP shaft.
- the frustoconical portion 102 of the trunnion HP 100 comprises, for its part, a circumferential radial protruding portion 105, mechanical reinforcement, oriented towards the axis of the motor and for reinforcing the mass of the trunnion HP 100.
- the protruding portion 105 is formed near the axis of the motor to reduce the mechanical stresses in operation, in particular, the stresses resulting from centrifugal forces.
- the frustoconical portion 102 of the HP 100 trunnion comprises radial sealing blades 104, forming labyrinth seal, oriented radially outwardly of the engine and intended to seal between the trunnion HP 100 and a mechanical part mounted externally to the trunnion HP 100.
- the frustoconical portion 102 of the trunnion HP 100 further comprises an inner frustoconical flange 107 secured to a sealing sleeve 400 of the engine shaft BP.
- the sealing sheath 400 is in the form of a cylinder extending axially, externally to the LP shaft of the engine and internally to the turbine disk 200.
- the sealing sheath 400 makes it possible to protect the LP shaft against excessive temperatures.
- An annular cooling air circulation duct of the turbine disk is formed internally to the HP turbine disk 200 and outside the sealing sheath 400. The circulation of the cooling air in the channel is represented by arrows on the turbine disk. Figures 2 and 3.
- the radial annular fixing portion 150 of the pin 100 comprises fixing bores 120 alternating with openings 110 for circulating a flow of cooling air of the turbine disc, hereinafter referred to as ventilation openings 110, the bores 120 and the openings 110 being disposed circumferentially on the radial annular fixing portion 150.
- the bores 120 and the openings 110 are uniformly distributed over the circumference.
- the fixing bores 120 and the ventilation openings 110 of the pin 100 are arranged to correspond respectively to the fixing bores 220 and the slots 252 of the HP 200 turbine disk.
- the bores 120 and the openings 110 of the trunnion 100 advantageously make it possible to reduce the tangential stresses in this area of the trunnion HP 100 by the effect of pitch.
- the fixing bores 120 and the ventilation openings 110 are here circular and have, in this example, the same opening section. It goes without saying that the bores 120 and the openings 110 could have shapes (oblong, rectangular, etc.) and different sections.
- the radial annular fixing portion 150 further comprises radial sealing blades provided at its outer radial end, similar to those formed on the frustoconical portion 102 of the pin 100.
- the downstream face of the downstream mounting flange 250 of the HP 200 turbine disk is brought into surface contact with the upstream face of the annular portion. 150 of the trunnion HP 100.
- the fixing holes 120 of the trunnion 100 are aligned with fixing bores 220 of the HP 200 turbine disc. Due to the alignment of the fixing bores 120, 220, the ventilation openings 110 of the HP trunnion 100 are aligned with the slots 252 of the mounting flange 250 of the HP turbine disk 200. In other words, the ventilation openings 110 of the trunnion 100 HP are aligned with the openings formed between the teeth 251 of the mounting flange. 250 of the HP 200 turbine disk.
- a bolt screw 21 is introduced successively into a fastening bore 120 of the journal 100 and then into the fastening bore 220 of the turbine disc 200 with which it is mounted. aligned. A nut 22 of bolt 20 is then screwed to the end of said screw 21 to secure the attachment. This bolting step is repeated for each fixing bore 120 of the trunnion 100, the turbine disc 200 then being integral with the trunnion HP 100.
- the cooling air can circulate between the bolts 20 for holding the trunnion HP 100.
- the radial annular portion 150 of the trunnion 100 allows the attachment to the turbine disk 200 and the evacuation of the cooling air flow of the turbine disk 200.
- a mixture of air and fuel is burned in the combustion chamber of the engine to create the thrust required for the displacement of the aircraft on which the turbojet engine is mounted.
- a gas flow at very high temperature circulates in the HP turbine of the turbojet engine.
- the HP 200 turbine disk is subjected to very high temperatures.
- an airflow is taken upstream of the turbine disk 200, at the level of the HP compressor, and flows upstream and downstream in the turbojet, internally to the HP 200 turbine disk and externally to the sealing sheath 400.
- the annular cooling air stream takes heat from the turbine disk 200 for cooling and forming a cooling air envelope around the sealing sheath 400, thereby protecting the mechanical parts mounted therein.
- the cooling air After cooling the HP turbine disk 200, the cooling air is discharged through the air circulation passages which are formed between the bolts 20 connecting the HP 100 trunnion to the HP 200 turbine disk as shown in FIG. 2 and 3. Downstream of the airflow openings, the cooling air cools the LP turbine of the dual-body engine. In other words, the cooling air circulates successively between the teeth 251 of the flange downstream mounting 250 of the HP 200 turbine disk and through the ventilation openings 110 formed in the HP 100 trunnion.
- a labyrinth sealing disc 300 is mounted with the HP turbine disc 200 and the HP trunnion 100, the sealing disc 300 being mounted downstream of the HP trunnion 100.
- the labyrinth sealing disc 300 is in the form of a radial annular ring comprising at its outer radial end, ie the farthest from the axis of the motor, radial sealing blades 304 forming a labyrinth seal, and comprising at its inner end, ie the closest to the axis of the engine, a radial annular fixing band 350.
- the radial annular fixing band 350 of the sealing disc 300 comprises fixing bores 320 alternating with ventilation openings 310, the bores 320 and the openings 310 being arranged circumferentially on the radial annular fixing band 350.
- the fixing bores 320 and the ventilation openings 310 of the sealing disc 300 are arranged to correspond with their counterparts on the HP 100 trunnion.
- the face facing downstream of the downstream fastening flange 250 of the HP 200 turbine disk is brought into surface contact with the face facing upstream of the radial annular portion 150 of the trunnion.
- HP 100 the face facing upstream of the fastening strip 350 of the sealing disk 300 is brought into surface contact with the face facing downstream of the radial annular portion 150 of the HP pin 100.
- the fixing bores 120, 220, 320 of the HP turbine disk 200, the HP trunnion 100 and the sealing disk 300 are aligned.
- the openings 110, 310 of the HP trunnion 100 and the sealing disc 300 are aligned with the slots 252 of the fastening flange 250 of the HP turbine disc 200.
- the turbine disc 200, the journal 100 and the sealing disc 300 are then bolted together via the fastening bores 120, 220, 320 which are aligned. After fixing, air circulation passages are formed between the holding bolts 20.
- the passage section of the ventilation openings 310 of the sealing disk 300 is adapted so as to be able to calibrate the flow rate of the cooling air in the central bore 201 of the turbine disk 200.
- the diameter circular ventilation openings 310 of the sealing disc 300 are smaller than the diameter of the circular ventilation openings 110 of the HP 100 trunnion, resulting in a reduction of the cooling air flow in the central bore 201.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Priority Applications (7)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN2009801196717A CN102046922A (zh) | 2008-05-29 | 2009-05-29 | 包括用于燃气涡轮发动机的涡轮盘和支承件支撑轴颈在内的组件、以及用于该组件的涡轮盘的冷却回路 |
BRPI0912114 BRPI0912114B1 (pt) | 2008-05-29 | 2009-05-29 | conjunto de um disco de turbina de um motor de turbina a gás e de um munhão de suporte de mancal e circuito de resfriamento do disco de turbina em um motor de turbina a gás |
JP2011511024A JP5319763B2 (ja) | 2008-05-29 | 2009-05-29 | ガスタービンエンジン用タービンディスクと軸受支持ジャーナルとを含むアセンブリおよび該アセンブリのタービンディスク用冷却回路 |
EP09753955A EP2340358A1 (fr) | 2008-05-29 | 2009-05-29 | Ensemble d'un disque de turbine d'un moteur a turbine a gaz et d'un tourillon support de palier, circuit de refroidissement d'un disque de turbine d'un tel ensemble |
US12/994,785 US8899913B2 (en) | 2008-05-29 | 2009-05-29 | Assembly including a turbine disk for a gas turbine engine and a bearing-supporting journal, and cooling circuit for the turbine disk of such an assembly |
CA2726016A CA2726016C (fr) | 2008-05-29 | 2009-05-29 | Ensemble d'un disque de turbine d'un moteur a turbine a gaz et d'un tourillon support de palier, circuit de refroidissement d'un disque de turbine d'un tel ensemble |
RU2010154117/06A RU2504661C2 (ru) | 2008-05-29 | 2009-05-29 | Узел из диска турбины газотурбинного двигателя и опорной цапфы опорного подшипника, контур охлаждения диска турбины такого узла |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR08/02945 | 2008-05-29 | ||
FR0802945A FR2931873B1 (fr) | 2008-05-29 | 2008-05-29 | Ensemble d'un disque de turbine d'un moteur a turbine a gaz et d'un tourillon support de palier,circuit de refroidissement d'un disque de turbine d'un tel ensemble. |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2009144300A1 true WO2009144300A1 (fr) | 2009-12-03 |
Family
ID=40070588
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2009/056617 WO2009144300A1 (fr) | 2008-05-29 | 2009-05-29 | Ensemble d'un disque de turbine d'un moteur a turbine a gaz et d'un tourillon support de palier, circuit de refroidissement d'un disque de turbine d'un tel ensemble |
Country Status (9)
Country | Link |
---|---|
US (1) | US8899913B2 (fr) |
EP (1) | EP2340358A1 (fr) |
JP (1) | JP5319763B2 (fr) |
CN (1) | CN102046922A (fr) |
BR (1) | BRPI0912114B1 (fr) |
CA (1) | CA2726016C (fr) |
FR (1) | FR2931873B1 (fr) |
RU (1) | RU2504661C2 (fr) |
WO (1) | WO2009144300A1 (fr) |
Cited By (3)
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WO2015075405A1 (fr) * | 2013-11-25 | 2015-05-28 | Snecma | Turbomachine comprenant un fourreau d'arbre et tube de fourreau associe |
WO2021013957A1 (fr) | 2019-07-24 | 2021-01-28 | Safran Aircraft Engines Sas | Turbomachine axiale et étage redresseur à aubes à orientation variable pour turbomachine axiale |
FR3108362A1 (fr) | 2020-03-19 | 2021-09-24 | Safran Aircraft Engines | Etage d’aubes à orientation variable pour une turbomachine axiale comprenant un organe de régulation du débit d’air dépendant de l’orientation des aubes |
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DE102011100221B4 (de) * | 2011-05-02 | 2017-03-09 | MTU Aero Engines AG | Integral beschaufelter Rotorgrundkörper, Verfahren und Strömungsmaschine |
FR2992679A1 (fr) * | 2012-06-28 | 2014-01-03 | Snecma | 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 |
US10001061B2 (en) * | 2014-06-06 | 2018-06-19 | United Technologies Corporation | Cooling system for gas turbine engines |
US10502059B2 (en) | 2015-02-02 | 2019-12-10 | United Technologies Corporation | Alignment tie rod device and method of utilization |
CN104929779B (zh) * | 2015-04-30 | 2016-06-22 | 中国科学院工程热物理研究所 | 轮盘连接结构和具有其的燃气涡轮发动机 |
KR101663306B1 (ko) * | 2015-10-02 | 2016-10-06 | 두산중공업 주식회사 | 가스터빈 디스크 |
CN106677834B (zh) * | 2015-11-05 | 2018-06-08 | 中国航发商用航空发动机有限责任公司 | 连接低压涡轮盘与转子支撑锥臂的螺栓连接结构及方法 |
CN105401981A (zh) * | 2015-12-29 | 2016-03-16 | 中国航空工业集团公司沈阳发动机设计研究所 | 一种高转速低压涡轮转子结构 |
FR3079299B1 (fr) * | 2018-03-22 | 2020-06-05 | Safran Aircraft Engines | Dispositif de mesure des caracteristiques d'un flux d'air |
CN109098773B (zh) * | 2018-08-24 | 2023-07-07 | 哈尔滨电气股份有限公司 | 一种新型的涡轮轮盘变截面螺栓连接结构及其连接方法 |
JP7032279B2 (ja) * | 2018-10-04 | 2022-03-08 | 本田技研工業株式会社 | ガスタービンエンジン |
EP4108898A4 (fr) * | 2020-02-20 | 2024-03-13 | Kawasaki Jukogyo Kabushiki Kaisha | Structure de refroidissement de bride pour un moteur à turbine à gaz |
CN114109511B (zh) * | 2021-11-12 | 2024-06-18 | 中国航发沈阳发动机研究所 | 一种新型盘心连接结构及具有其的双辐板涡轮盘 |
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- 2009-05-29 BR BRPI0912114 patent/BRPI0912114B1/pt active IP Right Grant
- 2009-05-29 CN CN2009801196717A patent/CN102046922A/zh active Pending
- 2009-05-29 EP EP09753955A patent/EP2340358A1/fr active Pending
- 2009-05-29 CA CA2726016A patent/CA2726016C/fr active Active
- 2009-05-29 RU RU2010154117/06A patent/RU2504661C2/ru active
- 2009-05-29 WO PCT/EP2009/056617 patent/WO2009144300A1/fr active Application Filing
- 2009-05-29 JP JP2011511024A patent/JP5319763B2/ja active Active
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Cited By (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2015075405A1 (fr) * | 2013-11-25 | 2015-05-28 | Snecma | Turbomachine comprenant un fourreau d'arbre et tube de fourreau associe |
FR3013766A1 (fr) * | 2013-11-25 | 2015-05-29 | Snecma | Turbomachine comprenant un fourreau d'arbre et tube de fourreau associe |
CN105765167A (zh) * | 2013-11-25 | 2016-07-13 | 斯奈克玛 | 包括轴衬套的涡轮机以及相关的衬套管 |
RU2668507C1 (ru) * | 2013-11-25 | 2018-10-01 | Сафран Эркрафт Энджинз | Турбомашина, содержащая кожух вала, и соответствующая труба кожуха |
US10267154B2 (en) | 2013-11-25 | 2019-04-23 | Safran Aircraft Engines | Turbomachine comprising a shaft sleeve and associated sleeve tube |
CN105765167B (zh) * | 2013-11-25 | 2021-03-02 | 斯奈克玛 | 包括轴衬套的涡轮机以及相关的衬套管 |
WO2021013957A1 (fr) | 2019-07-24 | 2021-01-28 | Safran Aircraft Engines Sas | Turbomachine axiale et étage redresseur à aubes à orientation variable pour turbomachine axiale |
FR3099204A1 (fr) | 2019-07-24 | 2021-01-29 | Safran Aircraft Engines | Etage redresseur de turbomachine avec passage de fuite d’air de refroidissement a section variable suivant orientation des aubes |
CN114144573A (zh) * | 2019-07-24 | 2022-03-04 | 赛峰航空发动机公司 | 涡轮机械整流器级,带有具有根据叶片的取向的可变截面的冷却空气泄漏通道 |
US11952950B2 (en) | 2019-07-24 | 2024-04-09 | Safran Aircraft Engines Sas | Axial turbine engine, and rectifier stage with variable orientation vanes for an axial turbine engine |
FR3108362A1 (fr) | 2020-03-19 | 2021-09-24 | Safran Aircraft Engines | Etage d’aubes à orientation variable pour une turbomachine axiale comprenant un organe de régulation du débit d’air dépendant de l’orientation des aubes |
Also Published As
Publication number | Publication date |
---|---|
RU2504661C2 (ru) | 2014-01-20 |
US8899913B2 (en) | 2014-12-02 |
RU2010154117A (ru) | 2012-07-10 |
CA2726016C (fr) | 2017-06-20 |
CA2726016A1 (fr) | 2009-12-03 |
US20110129336A1 (en) | 2011-06-02 |
CN102046922A (zh) | 2011-05-04 |
JP5319763B2 (ja) | 2013-10-16 |
BRPI0912114B1 (pt) | 2019-12-03 |
EP2340358A1 (fr) | 2011-07-06 |
JP2011522152A (ja) | 2011-07-28 |
BRPI0912114A2 (pt) | 2015-11-03 |
FR2931873B1 (fr) | 2010-08-20 |
FR2931873A1 (fr) | 2009-12-04 |
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