EP1329589A1 - Amenagement de rotor d'une turbomachine - Google Patents
Amenagement de rotor d'une turbomachine Download PDFInfo
- Publication number
- EP1329589A1 EP1329589A1 EP03290117A EP03290117A EP1329589A1 EP 1329589 A1 EP1329589 A1 EP 1329589A1 EP 03290117 A EP03290117 A EP 03290117A EP 03290117 A EP03290117 A EP 03290117A EP 1329589 A1 EP1329589 A1 EP 1329589A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- discs
- flanges
- spacers
- teeth
- arrangement according
- 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.)
- Granted
Links
- 125000006850 spacer group Chemical group 0.000 claims abstract description 29
- 238000009423 ventilation Methods 0.000 claims description 7
- 230000000295 complement effect Effects 0.000 claims description 3
- 238000003491 array Methods 0.000 abstract 1
- 238000010168 coupling process Methods 0.000 abstract 1
- 238000005859 coupling reaction Methods 0.000 abstract 1
- 239000007789 gas Substances 0.000 description 5
- 238000011144 upstream manufacturing Methods 0.000 description 3
- LWZFANDGMFTDAV-BURFUSLBSA-N [(2r)-2-[(2r,3r,4s)-3,4-dihydroxyoxolan-2-yl]-2-hydroxyethyl] dodecanoate Chemical compound CCCCCCCCCCCC(=O)OC[C@@H](O)[C@H]1OC[C@H](O)[C@H]1O LWZFANDGMFTDAV-BURFUSLBSA-N 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 235000011067 sorbitan monolaureate Nutrition 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
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
-
- 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
Definitions
- the subject of this invention is a rotor arrangement of a turbomachine.
- Arrangements of such rotors include often individual disks carrying as many stages of movable blades and joined by spacers whose main role is to establish a seal in delimiting the gas stream.
- the discs are normally provided with extensions to a structure rotor center to which they are fixed by bolting. They also include flanges extending under the spacers and joined together by bolts at their ends. They are so joined directly to neighboring disks, in addition to indirect connection by the central structure of the rotor.
- this arrangement is less rigid than we could have hoped for, which is all the more disappointing as all these means of connection bolted takes a long time to assemble and disassemble and represent a significant weight.
- a rotor arrangement comprising a succession of discs carrying blades joined by spacers, characterized in that two of the discs, at opposite ends of the estate, are provided with junction extensions to a central structure of the rotor, the discs are provided with circular edges, the spacers include flanges placed on ledges, and discs and flanges include complementary networks of teeth interconnection and housing of said teeth around the collars.
- the essential novelty of this arrangement therefore relates to the connection between the discs and the spacers: the spacers are now rigid parts responsible for maintaining the discs intermediaries and provided with means of connecting centering around the rotor axis and stopping at rotation cooperating with complementary means located on these discs. Bolted connections between the discs can therefore disappear, as well as the connections of the intermediate discs to the structure rotor center: the intermediate discs are therefore suspended from the spacers.
- the extensions of the discs extremes are tapered and join each other by mutual fixing flanges.
- the layout according to the invention is then a unitary structure and compact that can be attached to the structure rotor center by a single bolted flange.
- the extreme disc extensions can still be joined by a network of dog teeth and housing said teeth to ensure a more rigid connection directly between the discs extremes.
- the rotor considered here and shown in Figure 1 includes a central structure 1 of a kind indifferent and composed normally, within known turbomachinery, of elements assembled by bolting.
- the arrangement in accordance with the invention carries the general reference 2 and extends around a portion of the central structure 1; its main elements consist of two extreme discs 3 and 4, two intermediate discs 5 and 6 located between the previous, and three spacers 7, 8 and 9 connecting the discs (respectively 3 and 5, 5 and 6, 6 and 4) respectively two by two.
- Discs 3, 4, 5 and 6 are substantially flat, parallel and arranged in succession; they are all meant to carry floors movable blades 10 extending in the gas stream between stages of fixed blades 11.
- Spacers 7, 8 and 9 here carry wipers 12, i.e.
- the extreme discs 3 and 4 are provided, in addition to their normal elements comprising an outer ring 14, an inner crown 15 and a canvas 16 joining the two crowns, from an extension 17 or 18, starting from the crown 15 and extending radially towards the interior, while having a tapered conical shape to converge towards each other;
- the extension 18 of the disc 4 comprises an end ring 19 which commits to a circular span 20 of the extension 17 of disc 3 and stops against a stop face 21 of this extension 17;
- a nut 22 is screwed onto a threaded face 23 of the extension 17 extending behind the bearing surface 20 and retains the ring 19 against the face of stop 21.
- Extension 17 continues to extend towards the center of the rotor, and is joined to the central structure 1 by an arrangement of bolted flanges 25.
- the spacers 7, 8 and 9 are provided with flat flanges 26 and 27 which extend radially inward from their opposite ends. They rest on circular edges axial extension 28 and 29 of discs 3, 4, 5 and 6 who face them.
- the flanges 26 and 27 are provided with housings 30 into which penetrate foot ends 31 of the movable blades 10.
- the arrangement often used to assemble blades mobile to a disc - and which consists of operating grooves 32 passing through the outer ring of the disc in axial or oblique direction and whose section has a bulbous, dovetail-shaped, fir-shaped or similar, opening to the outside of the disc by a neck constricted and holding one foot of a movable blade - is here perfected in that the feet 31 are elongated at part of their cross-section and extend beyond the grooves 32.
- interconnections analogues exist at the junctions between discs 3 to 6 and the spacers 7 to 9; if he is all the same present it can help make the assembly hyperstatic, and we can then advise to delete one of the other interconnections, for example one of those of the central spacer 8.
- the reference 44 designates an air intake duct of ventilation in front of the layout in accordance with the invention, and holes 45 and 46 are provided in the extensions 17 and 18 of the extreme discs 3 and 4 to allow the ventilation air to cool down room 47 inside layout 2, and in particular the intermediate discs 5 and 6 which are there essentially contained.
- Ferrules 33 to 35 include legs 48 which extend radially outwards and penetrate into notches provided in the transfers 28 of the discs. They are thus retained in rotation.
- Figure 3 illustrates a slightly different, where ferrules 33 to 35 likewise disappeared than separate chambers 36 to 38.
- the air flows of ventilation through the grooves 32 flow directly into the gas stream.
- Spacers 7, 8 and 9 are then replaced by spacers 107, 108 and 109 which resemble them but whose collar located upstream (26) is replaced by a flange 126 inverted, extending outward from the main portion of the spacer.
- the flanges 126 continue to be supported on the flanges 28, and include housings 30 of passage of elongated ends of the feet 31 of the blades to establish interconnection links, and they include foot restraint portions against sliding movements.
- the assembly of the arrangement of rotor 2 is very simple to do since it consists of stacking the discs, spacers and ferrules successively and tighten the nut 22 single when the extensions 17 and 19 of the extreme dikes 3 and 4 were joined.
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)
Abstract
Description
- la figure 1 est une vue d'une première réalisation de l'invention,
- la figure 2 est une représentation du mode de liaison des disques aux entretoises,
- et la figure 3 illustre un mode de réalisation légèrement différent de l'invention.
Claims (6)
- Aménagement de rotor comprenant une succession de disques (3, 4, 5, 6) porteurs d'aubes (10) joints par des entretoises (7, 8, 9), caractérisé en ce que deux des disques, à des extrémités opposées de la succession, sont munis de prolongements (17, 18) , en ce que les prolongements (17, 18) sont fuselés et se joignent l'un à l'autre par des brides de fixation mutuelle, les disques sont munis de rebords (28, 29) circulaires, les entretoises comprennent des collerettes (26, 27) posées sur les rebords, et les disques et les collerettes comprennent des réseaux complémentaires de dents de crabotage (31) et de logements (30) desdites dents autour des collerettes (26, 27).
- Aménagement selon la revendication 1, caractérisé en ce que les dents correspondent à des extrémités de pieds des aubes engagés dans des rainures (32) individuelles des disques et traversant les disques, et débordant des rainures.
- Aménagement selon la revendication 3, caractérisé en ce que les prolongements sont aussi joints par un réseau de dents de crabotage (24) et de logements desdites dents.
- Aménagement selon la revendication 4, caractérisé en ce que l'une des entretoises (8) comprend un crabotage à une seule des collerettes.
- Aménagement selon la revendication 2, caractérisé en ce que les collerettes des entretoises sont dirigées vers l'intérieur radialement, et des viroles (33, 34, 35) relient les disques en étant concentriques aux entretoises, les viroles et les entretoises délimitant des chambres de ventilation (36, 37, 38) dans lesquelles les rainures débouchent.
- Aménagement selon l'une quelconque des revendications 1 à 5, caractérisé en ce que les collerettes des entretoises sont dirigées l'une (27) vers l'intérieur et l'autre (26) vers l'extérieur.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR0200522 | 2002-01-17 | ||
| FR0200522A FR2834751B1 (fr) | 2002-01-17 | 2002-01-17 | Amenagement de rotor d'une turbomachine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP1329589A1 true EP1329589A1 (fr) | 2003-07-23 |
| EP1329589B1 EP1329589B1 (fr) | 2006-03-29 |
Family
ID=8871320
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP03290117A Expired - Lifetime EP1329589B1 (fr) | 2002-01-17 | 2003-01-17 | Amenagement de rotor d'une turbomachine |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US7008190B2 (fr) |
| EP (1) | EP1329589B1 (fr) |
| DE (1) | DE60304305T2 (fr) |
| ES (1) | ES2256683T3 (fr) |
| FR (1) | FR2834751B1 (fr) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2012056161A1 (fr) * | 2010-10-28 | 2012-05-03 | Snecma | Ensemble de disques de rotor pour une turbomachine |
| EP2554791A3 (fr) * | 2011-08-03 | 2016-11-09 | United Technologies Corporation | Structure de rotor de turbine à gaz |
Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2875534B1 (fr) † | 2004-09-21 | 2006-12-22 | Snecma Moteurs Sa | Module de turbine pour moteur a turbine a gaz avec rotor comportant un corps monobloc |
| FR2887890B1 (fr) * | 2005-06-30 | 2007-10-12 | Snecma | Composition de materiau abradable, piece thermomecanique ou carter comprenant un revetement et procede de fabrication ou de reparation d'un revetement presentant cette composition |
| FR2895021B1 (fr) * | 2005-12-16 | 2010-09-03 | Snecma | Systeme d'etancheite inter-etages dans une turbomachine |
| FR2914008B1 (fr) * | 2007-03-21 | 2009-10-09 | Snecma Sa | Ensemble rotatif d'une soufflante de turbomachine |
| RU2506428C1 (ru) * | 2012-10-15 | 2014-02-10 | Открытое акционерное общество "Авиадвигатель" | Многоступенчатая газовая силовая турбина |
| RU2506427C1 (ru) * | 2012-11-07 | 2014-02-10 | Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России) | Ротор турбины газотурбинного двигателя |
| RU2534684C1 (ru) * | 2013-11-25 | 2014-12-10 | Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России) | Турбина двухконтурного газотурбинного двигателя |
| US10036278B2 (en) * | 2014-04-11 | 2018-07-31 | United Technologies Corporation | High pressure compressor thermal shield apparatus and system |
| ES2698504T3 (es) * | 2015-07-28 | 2019-02-05 | MTU Aero Engines AG | Turbina de gas |
| US11215056B2 (en) * | 2020-04-09 | 2022-01-04 | Raytheon Technologies Corporation | Thermally isolated rotor systems and methods |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR902004A (fr) * | 1943-02-09 | 1945-08-16 | Tech Studien Ag | Rotor, composé d'éléments de révolution disposés l'un à côté de l'autre et assemblés axialement entre eux par des boulons filetés pour turbomachines, en particulier pour turbines à vapeur et à gaz |
| FR1057171A (fr) * | 1951-04-18 | 1954-03-05 | Bristol Aeroplane Co Ltd | Perfectionnements aux rotors pour compresseurs ou turbines à écoulement axial |
| US2773667A (en) * | 1950-02-08 | 1956-12-11 | Gen Motors Corp | Turbine rotor sealing ring |
| US2825124A (en) * | 1952-02-05 | 1958-03-04 | Gen Motors Corp | Method of making a fabricated rotor |
| FR1201123A (fr) * | 1957-06-14 | 1959-12-28 | Napier & Son Ltd | Rotor pour compresseur axial ou turbine à plusieurs étages |
| FR1201124A (fr) * | 1957-06-14 | 1959-12-28 | Napier & Son Ltd | Rotor à disques supports doubles pour compresseur |
| FR1534718A (fr) * | 1967-02-27 | 1968-08-02 | Snecma | Perfectionnements aux turbo-machines à flux axial |
| US3868197A (en) * | 1973-10-26 | 1975-02-25 | Westinghouse Electric Corp | Spacer rings for a gas turbine rotor |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| BE534314A (fr) * | 1953-12-24 | |||
| US3295825A (en) * | 1965-03-10 | 1967-01-03 | Gen Motors Corp | Multi-stage turbine rotor |
-
2002
- 2002-01-17 FR FR0200522A patent/FR2834751B1/fr not_active Expired - Fee Related
-
2003
- 2003-01-17 DE DE60304305T patent/DE60304305T2/de not_active Expired - Lifetime
- 2003-01-17 ES ES03290117T patent/ES2256683T3/es not_active Expired - Lifetime
- 2003-01-17 EP EP03290117A patent/EP1329589B1/fr not_active Expired - Lifetime
- 2003-01-17 US US10/346,134 patent/US7008190B2/en not_active Expired - Lifetime
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR902004A (fr) * | 1943-02-09 | 1945-08-16 | Tech Studien Ag | Rotor, composé d'éléments de révolution disposés l'un à côté de l'autre et assemblés axialement entre eux par des boulons filetés pour turbomachines, en particulier pour turbines à vapeur et à gaz |
| US2773667A (en) * | 1950-02-08 | 1956-12-11 | Gen Motors Corp | Turbine rotor sealing ring |
| FR1057171A (fr) * | 1951-04-18 | 1954-03-05 | Bristol Aeroplane Co Ltd | Perfectionnements aux rotors pour compresseurs ou turbines à écoulement axial |
| US2825124A (en) * | 1952-02-05 | 1958-03-04 | Gen Motors Corp | Method of making a fabricated rotor |
| FR1201123A (fr) * | 1957-06-14 | 1959-12-28 | Napier & Son Ltd | Rotor pour compresseur axial ou turbine à plusieurs étages |
| FR1201124A (fr) * | 1957-06-14 | 1959-12-28 | Napier & Son Ltd | Rotor à disques supports doubles pour compresseur |
| FR1534718A (fr) * | 1967-02-27 | 1968-08-02 | Snecma | Perfectionnements aux turbo-machines à flux axial |
| US3868197A (en) * | 1973-10-26 | 1975-02-25 | Westinghouse Electric Corp | Spacer rings for a gas turbine rotor |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2012056161A1 (fr) * | 2010-10-28 | 2012-05-03 | Snecma | Ensemble de disques de rotor pour une turbomachine |
| FR2966867A1 (fr) * | 2010-10-28 | 2012-05-04 | Snecma | Ensemble de disques de rotor pour une turbomachine |
| GB2498321A (en) * | 2010-10-28 | 2013-07-10 | Snecma | Set of rotor discs for a turbomachine |
| US9371742B2 (en) | 2010-10-28 | 2016-06-21 | Snecma | Set of rotor disks for a turbine engine |
| GB2498321B (en) * | 2010-10-28 | 2017-07-05 | Snecma | A set of rotor disks for a turbine engine |
| EP2554791A3 (fr) * | 2011-08-03 | 2016-11-09 | United Technologies Corporation | Structure de rotor de turbine à gaz |
Also Published As
| Publication number | Publication date |
|---|---|
| ES2256683T3 (es) | 2006-07-16 |
| DE60304305D1 (de) | 2006-05-18 |
| FR2834751B1 (fr) | 2004-09-10 |
| FR2834751A1 (fr) | 2003-07-18 |
| US7008190B2 (en) | 2006-03-07 |
| EP1329589B1 (fr) | 2006-03-29 |
| US20030133803A1 (en) | 2003-07-17 |
| DE60304305T2 (de) | 2006-12-21 |
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