EP1717415B1 - Module de turbine pour moteur à turbine à gaz - Google Patents
Module de turbine pour moteur à turbine à gaz Download PDFInfo
- Publication number
- EP1717415B1 EP1717415B1 EP06113242A EP06113242A EP1717415B1 EP 1717415 B1 EP1717415 B1 EP 1717415B1 EP 06113242 A EP06113242 A EP 06113242A EP 06113242 A EP06113242 A EP 06113242A EP 1717415 B1 EP1717415 B1 EP 1717415B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- module
- compressor
- bolts
- turbine
- flange
- 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
Links
- 238000011144 upstream manufacturing Methods 0.000 claims description 16
- 238000005553 drilling Methods 0.000 claims 3
- 239000007789 gas Substances 0.000 description 7
- 238000007789 sealing Methods 0.000 description 4
- 241000237503 Pectinidae Species 0.000 description 2
- 238000003754 machining Methods 0.000 description 2
- 235000020637 scallop Nutrition 0.000 description 2
- 241000842962 Apoda limacodes Species 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000003292 diminished effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
- 238000010008 shearing Methods 0.000 description 1
Images
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
- F01D5/027—Arrangements for balancing
-
- 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
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2260/00—Function
- F05B2260/30—Retaining components in desired mutual position
- F05B2260/301—Retaining bolts or nuts
-
- 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
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
-
- 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
- F05D2260/34—Balancing of radial or axial forces on regenerative rotors
Definitions
- the present invention relates to the field of gas turbine engines and aims in particular a turbine module, in particular the high pressure module.
- An axial gas turbine engine includes a rotary compressor assembly, supplying a stationary combustion chamber which itself delivers hot gases to a rotating turbine assembly.
- a turbine rotor integral with a compressor rotor forms a body and the motor may comprise one or more bodies, generally two or three rotating at different speeds.
- a dual-body engine comprises a low pressure body LP and an HP high pressure body.
- its architecture is often divided into modules. For example, for the high-pressure body of a double-body engine, all the parts constituting the compressor are arranged in an HP compressor module and all the parts constituting the turbine rotor into an HP turbine module.
- This latter module consists of only rotating parts, for example a turbine disc on which are bolted a labyrinth sealing assembly and a ferrule with upstream assembly flange, and a sealing assembly associated with a downstream bearing. .
- the HP compressor and HP turbine modules are assembled via specific flanges; these flanges transmit the engine torque of the turbine to the compressor.
- the connection by these flanges must be sufficiently resistant to fulfill this function.
- US 5,816,776 for example, describes this state of the art.
- the modules must be provided to the assembly being perfectly balanced in rotation.
- an upstream balancing plan and a downstream balancing plan are provided.
- the balancing plane is that in which balancing weights are available at a distance from the axis and at a given angle.
- the flange that is at the The boundary of the module constitutes an appropriate balancing plan. Balancing weights are therefore available in the area of the boundary flange. This is particularly the case at the boundary between the HP compressor module and the HP turbine module.
- Each module is presented to the assembly being balanced in this way.
- the applicant has therefore set itself the goal of developing a turbine module that satisfies these constraints.
- the gas turbine engine turbine module comprising at least one turbine disk and a disk-shaped component mounted upstream on the turbine disk with respect to the gas flow, said module comprising a means of assembly between the compressor of said engine and the turbine disk, is characterized in that the component, before assembly of the module to the compressor, is pre-assembled to the turbine disk, by bolting to a fastening flange integral with the turbine disk.
- the means for assembling the compressor to the turbine disk comprises said fixing flange.
- the component is disc-shaped with a web between its hub and its periphery, and is mounted to said flange by bolting through first holes in the web, second holes are formed in the web for assembly by bolting from the turbine module to the compressor.
- the component is fixed to said flange by bolts whose number is between 2 and 8 distributed over the circumference.
- the bolts are retained by nuts crimped on the flange, downstream side, together with nuts for assembly of the module to the compressor.
- the fastening bolts of the component more particularly have a specific shaped head which differs from the heads of the fastening bolts of the compressor.
- the component comprises an upstream balancing device disposed on said component independently of the assembly means to the compressor.
- the invention applies in particular to a module whose component is a support disc of labyrinth sealing elements.
- the invention also covers the compressor associated with the module to form a gas turbine engine, comprising a downstream flange for attachment to the module. On this flange housing or passages are formed for the heads of bolts of fixings already in place on the module.
- This module comprises a turbine disk 3, with a hub with axial section increasing in thickness close to the axis, and at the periphery of which are mounted the turbine blades 4. These are housed in axial recesses formed on the rim of the disc.
- a component 5 is mounted on the disc 3 upstream, that is to say on the left in the figure. Upstream and downstream are defined with respect to the flow of gases in the engine.
- the component is here a symmetrical disk of revolution relative to the axis of the machine.
- This disc comprises a hub of increasing thickness towards the axis of the motor, a portion forming a web 51 towards the periphery.
- the disc at its periphery carries radial annular blades 53 forming the rotating portion of labyrinth seals. Their counterpart is not represented.
- the disc 5 is fixed to the disc 3 by bolting to a fastening flange 31 secured to the disc upstream thereof.
- the bolts 7 comprise a head 71, a rod 72 passing through an orifice formed in the web 51 and a bore machined in the flange 31, and cooperate with a nut 73.
- a disc 6 On the downstream side of the module there is a disc 6 with a journal 61 forming a support for a downstream bearing 62.
- the disk is bolted to a downstream mounting flange 33.
- the bolts 64 are fixed all around the disc. It also has sealing elements 63 for a labyrinth seal.
- Disk 6 forms a downstream balancing plane. Balancing weights are fitted with the fixing bolts.
- the module as represented on the figure 1 is pre-assembled ready to be assembled and assembled to a compressor.
- the function of the bolts 7 is to maintain the component 5 integral with the turbine disk during handling.
- the bolts 7 are preferably four in number and equidistant on the circumference. Their number can be between 2 and 8. In fact, you have to take into account the fastening bolts of the compressor to the disc. The bolts 7 do not come to disturb the tiering between the disc 3 and the disc 5.
- FIG. 2 the bolting detail is seen after the turbine module has been attached to a compressor attachment flange 9.
- the latter is not represented.
- the fixing flange 9 is annular and constitutes the downstream boundary of the compressor.
- the figure 2 represents a partial axial section taken along a bolt 7 for fixing the component 5 to the disc 3.
- the figure 3 represents a partial axial section taken along a bolt 8 for fixing the flange 9 to the disk 3.
- the heads 71 of the bolts 7 are engaged in wide scallops of the flange 9 in such a way that they engage the disc of the component 5 directly. These bolts therefore have no effect on the connection of the flange 9.
- Bolts 8 of the figure 3 each participate in fixing the flange 9 to the disc 3.
- the heads 81 bear against the upstream surface of the flange 9 which is held tight against the disk 5 by the nut 83 applied against the downstream face of the flange 31.
- the rod 82 of the bolt 8 passes through the disk of the component 5 and the two flanges 9 and 31.
- annular flange 9 is shown as seen from the upstream side. It comprises notches in the form of scallops to allow it to bypass the heads 71 of the bolts 7, and abut against the disk of the component 5. It also includes holes for the passage of the rods 82 of the bolts 8, whose head 81 comes to bear on the edge of the holes.
- the component 5 has the same holes in the sail 51 capable of passing either the bolts 7 or the bolts 8.
- this type of head while also providing the keying, has the further advantage of avoiding seizing, at the time of the modular disassembly of the compressor and the turbine, the bolts 8. If the bolts 8 remain blocked, the specific heads 81 of the bolts 8 are capable of withstanding a violent over-torque for shearing the shaft 82 of the head 81. In all cases, the modular disassembly is ensured.
- the flange 31 is shown from the downstream side.
- the nuts 73 and 83 are preferably mounted and crimped on site before assembling the parts. It is noted that they have a tongue 731 respectively 831 of rectangular shape so as to ensure mutual locking in rotation. This facilitates the screwing of bolts 7 and 8 during assembly.
- the nuts 73 and 83 crimped on the flange 31 are identical.
- fastening bolts 8 and 7 are in a concrete example of 28 and 4, respectively. It was verified that the 28 bolts could safely secure the attachment of the compressor to the disc. The difference of 4 with respect to an assembly at 32 does not affect. Calculations have demonstrated this in particular for: the passage torque, mechanical stresses, the life of parts, etc ....
- a module comprising this balancing device is represented on the figure 7 .
- the module comprises a flange 10 for hooking the weights on this face.
- the flange 10 is annular with a face perpendicular to the axis of the module, and comprises a plurality of machining for assembling weights.
- the number of machining is preferably equal to that of the number of fins mounted on the turbine disk.
- the figure 7 shows a weight 11 in place held by bolts 111. In this case, the installation of these weights allows the return of the upstream balancing plane rotor HP turbine module. This contributes to one of the delivery conditions of a so-called clean module.
- a module according to the present invention does not degrade the maintenance of the surrounding modules.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0551124A FR2885167B1 (fr) | 2005-04-29 | 2005-04-29 | Module de turbine pour moteur a turbine a gaz |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1717415A1 EP1717415A1 (fr) | 2006-11-02 |
EP1717415B1 true EP1717415B1 (fr) | 2008-06-11 |
Family
ID=35169522
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP06113242A Active EP1717415B1 (fr) | 2005-04-29 | 2006-04-27 | Module de turbine pour moteur à turbine à gaz |
Country Status (9)
Country | Link |
---|---|
US (1) | US7364402B2 (es) |
EP (1) | EP1717415B1 (es) |
CN (1) | CN1854485B (es) |
CA (1) | CA2544784C (es) |
DE (1) | DE602006001430D1 (es) |
ES (1) | ES2310887T3 (es) |
FR (1) | FR2885167B1 (es) |
RU (1) | RU2403401C2 (es) |
UA (1) | UA88281C2 (es) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US11092012B2 (en) | 2017-03-27 | 2021-08-17 | MTU Aero Engines AG | Turbomachine component arrangement |
Families Citing this family (31)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8167547B2 (en) * | 2007-03-05 | 2012-05-01 | United Technologies Corporation | Gas turbine engine with canted pocket and canted knife edge seal |
FR2914008B1 (fr) * | 2007-03-21 | 2009-10-09 | Snecma Sa | Ensemble rotatif d'une soufflante de turbomachine |
FR2921422B1 (fr) * | 2007-09-26 | 2009-12-18 | Snecma | Piece annulaire de turbomachine portant des ecrous a jupe de sertissage |
FR2931873B1 (fr) * | 2008-05-29 | 2010-08-20 | Snecma | 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. |
FR2931869B1 (fr) * | 2008-05-29 | 2014-12-12 | Snecma | Bride annulaire de fixation d'un element de rotor ou de stator |
FR2938292B1 (fr) * | 2008-11-07 | 2010-12-24 | Snecma | Bride annulaire de fixation d'un element de rotor ou de stator dans une turbomachine |
FR2939836B1 (fr) * | 2008-12-12 | 2015-05-15 | Snecma | Joint d'etancheite de plateforme dans un rotor de turbomachine |
FR2946083B1 (fr) * | 2009-05-28 | 2011-06-17 | Snecma | Turbine basse-pression |
FR2974865B1 (fr) * | 2011-05-04 | 2013-07-05 | Snecma | Rotor haute pression pour turbomachine d'aeronef, comprenant des moyens de detrompage associes a des boulons de prefixation de module de turbine |
EP3690211A1 (en) | 2012-10-08 | 2020-08-05 | United Technologies Corporation | Geared turbine engine with relatively lightweight propulsor module |
FR3001515B1 (fr) * | 2013-01-25 | 2015-03-20 | Snecma | Assemblage de masselotte d'equilibrage a un element de rotor |
FR3002585B1 (fr) * | 2013-02-27 | 2016-07-15 | Snecma | Equilibrage d'un ensemble rotatif dans une turbomachine |
WO2014172130A1 (en) * | 2013-04-18 | 2014-10-23 | United Technologies Corporation | Turbine minidisk bumper for gas turbine engine |
EP2824278B1 (de) * | 2013-07-08 | 2018-11-07 | MTU Aero Engines GmbH | Vorrichtung, Schaufel-Vorrichtungs-Verbund, Verfahren sowie Strömungsmaschine |
DE102013216377A1 (de) | 2013-08-19 | 2015-03-12 | Rolls-Royce Deutschland Ltd & Co Kg | Verfahren zum Auswuchten und zur Montage eines Turbinenrotors |
RU2532390C1 (ru) * | 2013-09-10 | 2014-11-10 | Открытое акционерное общество "Авиадвигатель" | Ротор турбины высокого давления |
FR3021066B1 (fr) | 2014-05-19 | 2019-05-10 | Safran Aircraft Engines | Disque de rotor equilibre, et procede d'equilibrage |
EP3081919B1 (de) | 2015-04-16 | 2018-11-21 | Thilo Kraemer | Prüfgerät zum durchführen von härtemessungen |
DE202015101878U1 (de) | 2015-04-16 | 2015-04-30 | Thilo Kraemer | Prüfgerät |
EP3091179B1 (de) * | 2015-05-07 | 2021-06-30 | MTU Aero Engines AG | Rotoranordnung für eine strömungsmaschine und verdichter |
US10533810B2 (en) | 2015-05-20 | 2020-01-14 | Other Lab, Llc | Near-isothermal compressor/expander |
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 |
CN107932060B (zh) * | 2017-11-23 | 2019-03-22 | 中国航发沈阳黎明航空发动机有限责任公司 | 一种控制燃机低压一级涡轮盘磨损的方法 |
FR3078363B1 (fr) * | 2018-02-23 | 2021-02-26 | Safran Aircraft Engines | Anneau mobile d'etancheite |
US11448081B2 (en) | 2019-10-18 | 2022-09-20 | Raytheon Technologies Corporation | Balanced circumferential seal |
CN111485955A (zh) * | 2020-04-16 | 2020-08-04 | 中国航发沈阳发动机研究所 | 一种转子轮盘装配结构 |
US11549373B2 (en) | 2020-12-16 | 2023-01-10 | Raytheon Technologies Corporation | Reduced deflection turbine rotor |
US11578599B2 (en) * | 2021-02-02 | 2023-02-14 | Pratt & Whitney Canada Corp. | Rotor balance assembly |
FR3119647B1 (fr) * | 2021-02-11 | 2023-01-13 | Safran Aircraft Engines | Procédé de réparation d’une bride de rotor de turbomachine |
RU208145U1 (ru) * | 2021-06-07 | 2021-12-06 | Публичное Акционерное Общество "Одк-Сатурн" | Узел ротора турбины высокого давления |
CN114215611B (zh) * | 2021-12-01 | 2023-07-14 | 东方电气集团东方汽轮机有限公司 | 一种燃气轮机透平动叶轴向定位用气封装配体 |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5275534A (en) * | 1991-10-30 | 1994-01-04 | General Electric Company | Turbine disk forward seal assembly |
US5562404A (en) * | 1994-12-23 | 1996-10-08 | United Technologies Corporation | Vaned passage hub treatment for cantilever stator vanes |
FR2744761B1 (fr) * | 1996-02-08 | 1998-03-13 | Snecma | Disque labyrinthe avec raidisseur incorpore pour rotor de turbomachine |
US6893222B2 (en) * | 2003-02-10 | 2005-05-17 | United Technologies Corporation | Turbine balancing |
FR2857419B1 (fr) * | 2003-07-11 | 2005-09-23 | Snecma Moteurs | Liaison amelioree entre disques aubages sur la ligne rotor d'un compresseur |
-
2005
- 2005-04-29 FR FR0551124A patent/FR2885167B1/fr not_active Expired - Fee Related
-
2006
- 2006-04-25 CA CA2544784A patent/CA2544784C/fr active Active
- 2006-04-27 DE DE602006001430T patent/DE602006001430D1/de active Active
- 2006-04-27 ES ES06113242T patent/ES2310887T3/es active Active
- 2006-04-27 EP EP06113242A patent/EP1717415B1/fr active Active
- 2006-04-28 US US11/412,995 patent/US7364402B2/en active Active
- 2006-04-28 UA UAA200604788A patent/UA88281C2/ru unknown
- 2006-04-28 RU RU2006114654/06A patent/RU2403401C2/ru active
- 2006-04-29 CN CN2006100790710A patent/CN1854485B/zh active Active
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US11092012B2 (en) | 2017-03-27 | 2021-08-17 | MTU Aero Engines AG | Turbomachine component arrangement |
Also Published As
Publication number | Publication date |
---|---|
CA2544784C (fr) | 2014-01-28 |
US7364402B2 (en) | 2008-04-29 |
DE602006001430D1 (de) | 2008-07-24 |
RU2403401C2 (ru) | 2010-11-10 |
FR2885167A1 (fr) | 2006-11-03 |
RU2006114654A (ru) | 2007-11-10 |
CA2544784A1 (fr) | 2006-10-29 |
CN1854485A (zh) | 2006-11-01 |
ES2310887T3 (es) | 2009-01-16 |
UA88281C2 (ru) | 2009-10-12 |
CN1854485B (zh) | 2011-05-25 |
FR2885167B1 (fr) | 2007-06-29 |
EP1717415A1 (fr) | 2006-11-02 |
US20070059164A1 (en) | 2007-03-15 |
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