EP1205637B1 - Ensemble de ventilation d'un anneau de stator - Google Patents
Ensemble de ventilation d'un anneau de stator Download PDFInfo
- Publication number
- EP1205637B1 EP1205637B1 EP01402865A EP01402865A EP1205637B1 EP 1205637 B1 EP1205637 B1 EP 1205637B1 EP 01402865 A EP01402865 A EP 01402865A EP 01402865 A EP01402865 A EP 01402865A EP 1205637 B1 EP1205637 B1 EP 1205637B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- stator ring
- ventilating
- ring
- manifolds
- stator
- 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.)
- Expired - Lifetime
Links
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
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/20—Actively adjusting tip-clearance
- F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
-
- 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
- F05B2230/00—Manufacture
- F05B2230/60—Assembly methods
- F05B2230/604—Assembly methods using positioning or alignment devices for aligning or centering, e.g. pins
- F05B2230/606—Assembly methods using positioning or alignment devices for aligning or centering, e.g. pins using maintaining alignment while permitting differential dilatation
-
- 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
- F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
- F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
Definitions
- Such ventilation assemblies are commonly used in jet engines and consist of ducts branching to several times and whose ends are pierced to blow gas and especially air to a big number of points, judiciously distributed, of the ring.
- Terminal ducts are very often ramps current around the rings, shaped like a circular arc and kissing part of their perimeter. Often too, the gas is blown in the axial direction, on outer ribs of the ring rather than on the ring itself, so that the diameter is controlled by those ribs that are stiffer and govern therefore the deformations of the ring proper.
- the set that will be described here is characterized in that it is easy to manufacture, despite the large number of ducts it usually takes to use, and to assemble to the ring despite the complications that can be dilated differential thermals at different times of operation of the machine.
- the invention thus concerns a set of ventilation of a ring stator consisting of branched ducts comprising supply ducts, distributors and ramps adjacent to the ring and provided with drill holes blowing of gas directed towards the ring, characterized in what ramps are made up of pairs of half-shells comprising a flange and a border surrounding the flange, pairs of half-shells being joined by the borders, the distributors include coil spacers between the ramps and provided with shaped end edges for adjusting on side cheek openings of the flanges.
- a stator ring 1 is associated with a group of 2 ventilation assemblies in accordance with invention, each of which occupies a portion of the circumference of ring 1 and includes a group of ramps 3 parallel and in an arc, a distributor 4 for distributing air from ventilation between all ramps 3 and a duct 5 (shown in FIG. distributor 4.
- the supply ducts 5 come together after one or more others distributors, which are however not shown because they are not the subject of this invention; this one more specifically the end of the sets ventilation 2, that is, their parts which are close to the ring 1 to ventilate.
- each of the ramps 3 is composed of a half-shell left 7 and a half-shell of right 8 of which each of these is assembled to one of these.
- the half-shells 7 and 8 of the two genres each include a flange 9 substantially flat and a border 10 established around the flange 9, the 10 borders of pairs of half-shells 7 and 8 complementary information being put in extension and attached to form a single ramp.
- the half-shells 7 and 8 can be made by a simple operation stamping and the connections between the borders 10 can be performed by welding. This mode of manufacturing is extremely simple and avoids having to to machine tubes to bring them to the shapes and desired dimensions, which would probably be a lot more tedious.
- half-shells of left 7 can usually be built to from the same tool as the right half-shells 8 which are symmetrical to the previous ones by the plane of seal.
- This overall similarity would not exclude some dissimilarities of details.
- half-shells 7 and 8 could be built with borders 10 of different width, so for example to favor the ventilation by the ramps 3 the most wide.
- An example of application of this method appears in Figure 2, where three ramps 3 ventilate two ribs 11, the central ramp being placed between the two ribs 11 and ventilating both, which justify that its width is double.
- cheeks 14 flanges 9 Other openings, wider, carry reference 13 and are executed through cheeks 14 flanges 9, except for an extreme half-shell 10, to form the dispenser 4.
- the cheeks 14 extend laterally from the centers of flanges 9 in this embodiment and their are coplanar.
- the ends of the ramps 3 are closed by continuous sheets welded to them.
- Distributor 4 still includes coils 15 in the form of a short cylinder serving of spacers between the ramps 3 and with the conduit 5. It is often advantageous for are similar, but they can also be different in particular in length. They understand generally edges 16 to engage in the openings 13 ramps 3 to keep them in place, and flanges 17 resting on the ramps 3 to define the spacing of these.
- the distributor 4 is formed when the coils 15 were soldered to 3. However, the distribution duct 5 remains typically separate from the distributor 4 and can slide in the input coil 15, a seal However, the seal 18 is added between them.
- one of the coils 15 comprises plane faces and opposed 19 enclosing the end 20 (here enlarged) of the rib 11 that the corresponding coil 15 overcomes.
- the reduction of the axial clearance between the coil 15 and the enlarged portion of the rib 11 helps to ensure the axial positioning of the distributors 4 on the ring 1. This ensures the axial positioning of the distributor 4, to adjust to the most precise gaps between the ramps 3 and the control rings 11 and master the convective exchanges created by the air-drying of the rings 11.
- the second spool overlaps its ring with axial play, this to allow relative dilations between housings 4 and the casing 1 without generating a connection hyperstatic and unwanted constraints.
- Brackets 22 are connected to one end of the stator ring 1 by fixing bolts 23 and include a wing 24 under one end of the ruler 6; the other end of it is placed on a boss 25 of the stator ring 1.
- Bolts 26 and 27 are screwed to Wing 24 and Boss 25. They are hold the ends of rule 6 on these by compressing springs 28 resting on the ruler 6 by washers 29.
- Such an arrangement has the property of to better control the support effort of the rules 6 on equets 24 and 25. If this effect is excessive, the assembly is rigid and does not allow the thermal breathing.
- rule 6 to which ramps 3 are welded, is provided with wide openings 30 around bolts 26 and 27, so as to be able to move axially and tangentially compared to the stator ring.
- This flexible assembly avoids therefore produce excessive internal stresses in the ventilation set 2, since the ramps 3 have the ability to move over the ring 1 without exerting too much effort.
- the support of one of the coils 15 against the end 20 of the corresponding rib 11 offers also some flexibility in allowing all of ventilation 2 to move to the ends while being recalled back to the stator ring 1 and the bottom of the 21 of the springs 28. This flexibility is valuable in allowing to absorb dilations thermal differentials inevitable with such equipment.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Motor Or Generator Cooling System (AREA)
- Motor Or Generator Frames (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Iron Core Of Rotating Electric Machines (AREA)
Description
- la figure 1 est une vue générale de l'ensemble,
- la figure 2 est une vue d'un distributeur à la ramification d'un conduit,
- la figure 3 expose un mode de support de l'ensemble sur l'anneau,
- et la figure 4 représente un groupe de rampes en coupe près de leur extrémité, ainsi qu'un moyen de maintien sur l'anneau.
Claims (7)
- Ensemble de ventilation (2) d'un anneau (1) de stator, composé de conduits ramifiés comprenant des conduits d'alimentation (5), des distributeurs (4) et des rampes (3) adjacentes à l'anneau et munies de perçages (12) de soufflage de gaz dirigés vers l'anneau, les rampes sont composées de paires de demi-coquilles (7, 8) comprenant un flasque (9) et une bordure (10) entourant le flasque, les paires de demi-coquilles étant jointes par les bordures, caractérisé en ce que les distributeurs comprennent des bobines (15) en entretoises entre les rampes et munies de bords d'extrémité (16) façonnés pour s'ajuster sur des ouvertures (13) de joues (14) latérales des flasques.
- Ensemble de ventilation d'un anneau de stator selon la revendication 1, caractérisé en ce que les demi-coquilles ont des flasques identiques, mais des bordures pouvant avoir des largeurs différentes.
- Ensemble de ventilation d'un anneau de stator selon l'une quelconque des revendications 1 ou 2, caractérisé en ce qu'il comprend des entailles en vé (21) dans des nervures (11) où viennent s'appuyer en s'auto-centrant les bobines (15), assurant ainsi une mise en position parfaite des distributeurs sur l'anneau (1) radialement, tangentiellement et en orientation selon un axe de moteur.
- Ensemble de ventilation d'un anneau de stator selon l'une quelconque des revendications 1 à 3, caractérisé en ce qu'il comprend, sur une des bobines, des surfaces (19) planes, parallèles aux rampes, d'appui sur une nervure (11) de l'anneau (1) de stator et la nervure (11) s'élargit localement pour réduire le jeu axial avec ladite bobine pour assurer le positionnement axial des distributeurs (4) sur l'anneau (1).
- Ensemble de ventilation d'un anneau de stator selon l'une quelconque des revendications 1 à 4, caractérisé en ce qu'il comprend des règles (6) de maintien des rampes vers l'anneau de stator, couvrant les rampes (3) en les croisant et assujetties à l'anneau de stator.
- Ensemble de ventilation d'un anneau de stator selon la revendication 5, caractérisé en ce que les règles de maintien sont assujetties à l'anneau de stator par des liaisons élastiques en direction de l'anneau de stator.
- Ensemble de ventilation d'un anneau de stator selon l'une quelconque des revendications 5 ou 6, caractérisé en ce que les règles de maintien sont assujetties à l'anneau du stator par des liaisons (26, 27) permettant un déplacement de glissement des règles aux extrémités.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0014373 | 2000-11-09 | ||
FR0014373A FR2816352B1 (fr) | 2000-11-09 | 2000-11-09 | Ensemble de ventilation d'un anneau de stator |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1205637A1 EP1205637A1 (fr) | 2002-05-15 |
EP1205637B1 true EP1205637B1 (fr) | 2003-07-09 |
Family
ID=8856230
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP01402865A Expired - Lifetime EP1205637B1 (fr) | 2000-11-09 | 2001-11-08 | Ensemble de ventilation d'un anneau de stator |
Country Status (9)
Country | Link |
---|---|
US (1) | US6896038B2 (fr) |
EP (1) | EP1205637B1 (fr) |
JP (1) | JP3913032B2 (fr) |
CA (1) | CA2361103C (fr) |
DE (1) | DE60100448T2 (fr) |
ES (1) | ES2199921T3 (fr) |
FR (1) | FR2816352B1 (fr) |
RU (1) | RU2276733C2 (fr) |
UA (1) | UA73938C2 (fr) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN107795383A (zh) * | 2016-08-29 | 2018-03-13 | 中国航发商用航空发动机有限责任公司 | 一种燃气轮机冷却气分配系统 |
Families Citing this family (39)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2829525B1 (fr) * | 2001-09-13 | 2004-03-12 | Snecma Moteurs | Assemblage de secteurs d'un distributeur de turbine a un carter |
FR2865237B1 (fr) * | 2004-01-16 | 2006-03-10 | Snecma Moteurs | Perfectionnements apportes aux dispositifs de controle de jeu dans une turbine a gaz |
FR2867806B1 (fr) * | 2004-03-18 | 2006-06-02 | Snecma Moteurs | Dispositif de pilotage de jeu de turbine a gaz a equilibrage des debits d'air |
FR2867805A1 (fr) * | 2004-03-18 | 2005-09-23 | Snecma Moteurs | Stator de turbine haute-pression de turbomachine et procede d'assemblage |
US7503179B2 (en) * | 2005-12-16 | 2009-03-17 | General Electric Company | System and method to exhaust spent cooling air of gas turbine engine active clearance control |
US7597537B2 (en) * | 2005-12-16 | 2009-10-06 | General Electric Company | Thermal control of gas turbine engine rings for active clearance control |
US7785063B2 (en) * | 2006-12-15 | 2010-08-31 | Siemens Energy, Inc. | Tip clearance control |
US7914254B2 (en) * | 2007-02-13 | 2011-03-29 | General Electric Company | Integrated support/thermocouple housing for impingement cooling manifolds and cooling method |
FR2931872B1 (fr) * | 2008-05-28 | 2010-08-20 | Snecma | Turbine haute pression d'une turbomachine avec montage ameliore du boitier de pilotage des jeux radiaux d'aubes mobiles. |
GB0906059D0 (en) * | 2009-04-08 | 2009-05-20 | Rolls Royce Plc | Thermal control system for turbines |
GB2469490B (en) | 2009-04-16 | 2012-03-07 | Rolls Royce Plc | Turbine casing cooling |
GB201013723D0 (en) | 2010-08-17 | 2010-09-29 | Rolls Royce Plc | Manifold mounting arrangement |
FR2977276B1 (fr) * | 2011-06-30 | 2016-12-09 | Snecma | Agencement pour le raccordement d'un conduit a un boitier de distribution d'air |
ITTO20120519A1 (it) | 2012-06-14 | 2013-12-15 | Avio Spa | Turbina a gas per motori aeronautici |
US9341074B2 (en) * | 2012-07-25 | 2016-05-17 | General Electric Company | Active clearance control manifold system |
FR2999642B1 (fr) * | 2012-12-17 | 2018-09-28 | Safran Aircraft Engines | Ensemble statorique dont les bosses comportent des portions en creux ou en saillie |
US10330012B2 (en) * | 2014-02-04 | 2019-06-25 | United Technologies Corporation | Brackets for gas turbine engine components |
RU2567892C1 (ru) * | 2014-06-02 | 2015-11-10 | Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России) | Статор компрессора высокого давления |
US9869196B2 (en) * | 2014-06-24 | 2018-01-16 | General Electric Company | Gas turbine engine spring mounted manifold |
RU2567885C1 (ru) * | 2014-08-08 | 2015-11-10 | Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России) | Статор компрессора |
FR3040429B1 (fr) * | 2015-08-27 | 2019-06-07 | Safran Aircraft Engines | Dispositif de fixation des rampes de refroidissement par jets d'air du carter d'une turbine de turbomachine |
FR3040428B1 (fr) * | 2015-08-27 | 2017-09-01 | Snecma | Dispositif de refroidissement par jets d'air du carter d'une turbine d'une turbomachine |
US10513944B2 (en) * | 2015-12-21 | 2019-12-24 | General Electric Company | Manifold for use in a clearance control system and method of manufacturing |
US10329941B2 (en) * | 2016-05-06 | 2019-06-25 | United Technologies Corporation | Impingement manifold |
FR3058459B1 (fr) * | 2016-11-04 | 2018-11-09 | Safran Aircraft Engines | Dispositif de refroidissement pour une turbine d'une turbomachine |
FR3058460B1 (fr) | 2016-11-08 | 2018-11-09 | Safran Aircraft Engines | Ensemble de raccordement pour le refroidissement d'une turbine de turbomachine |
CN106382136B (zh) * | 2016-11-18 | 2017-07-25 | 中国科学院工程热物理研究所 | 一种跨音速动叶叶顶间隙主动控制装置 |
US10458281B2 (en) * | 2017-06-12 | 2019-10-29 | United Technologies Corporation | Resilient mounting assembly for a turbine engine |
FR3073007B1 (fr) * | 2017-10-27 | 2019-09-27 | Safran Aircraft Engines | Dispositif de maintien d'un tube de refroidissement pour carter de turbomachine |
FR3079874B1 (fr) * | 2018-04-09 | 2020-03-13 | Safran Aircraft Engines | Dispositif de refroidissement pour une turbine d'une turbomachine |
FR3081927B1 (fr) * | 2018-05-30 | 2020-11-20 | Safran Aircraft Engines | Dispositif de refroidissement d'un carter de turbomachine |
FR3082872B1 (fr) * | 2018-06-25 | 2021-06-04 | Safran Aircraft Engines | Dispositif de refroidissement d'un carter de turbomachine |
FR3089560B1 (fr) * | 2018-12-06 | 2021-01-22 | Safran Aircraft Engines | Dispositif de maintien d'un tube de refroidissement pour carter de turbomachine |
FR3089545B1 (fr) * | 2018-12-07 | 2021-01-29 | Safran Aircraft Engines | Dispositif de refroidissement d’un carter de turbine pour une turbomachine |
FR3089544B1 (fr) * | 2018-12-10 | 2021-02-19 | Safran Aircraft Engines | Dispositif de refroidissement d’un carter de turbomachine |
FR3099801B1 (fr) * | 2019-08-09 | 2021-12-03 | Safran Aircraft Engines | Ensemble pour une turbine de turbomachine |
FR3099798B1 (fr) * | 2019-08-09 | 2021-12-03 | Safran Aircraft Engines | Ensemble pour une turbine de turbomachine |
FR3109406B1 (fr) * | 2020-04-17 | 2022-10-07 | Safran Aircraft Engines | Dispositif de refroidissement d’un carter de turbine |
US11788425B2 (en) * | 2021-11-05 | 2023-10-17 | General Electric Company | Gas turbine engine with clearance control system |
Family Cites Families (20)
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DE1601187A1 (de) * | 1967-07-15 | 1972-01-27 | Eberspaecher J | Waermetauscher,vorzugsweise mit innenliegendem Heizraum,insbesondere fuer Kraftfahrzeuge |
US3756020A (en) * | 1972-06-26 | 1973-09-04 | Curtiss Wright Corp | Gas turbine engine and cooling system therefor |
US3818696A (en) * | 1972-10-25 | 1974-06-25 | A Beaufrere | Regenerative air-cooled gas turbine engine |
DE2855055C2 (de) * | 1978-12-20 | 1982-12-16 | Siemens AG, 1000 Berlin und 8000 München | Isolierhülle für ein mit einer Ringwicklung zu bewickelndes Blechpaket |
US4279123A (en) * | 1978-12-20 | 1981-07-21 | United Technologies Corporation | External gas turbine engine cooling for clearance control |
US4773981A (en) * | 1982-07-29 | 1988-09-27 | Stephen Masiuk | Apparatus for improving internal combustion engine efficiency |
US4828403A (en) * | 1987-04-03 | 1989-05-09 | Schwartzman Everett H | Resiliently mounted fluid bearing assembly |
JPH06575Y2 (ja) * | 1988-06-16 | 1994-01-05 | 川崎重工業株式会社 | 内燃機関用マフラー |
US5100291A (en) * | 1990-03-28 | 1992-03-31 | General Electric Company | Impingement manifold |
US5205115A (en) * | 1991-11-04 | 1993-04-27 | General Electric Company | Gas turbine engine case counterflow thermal control |
US5273396A (en) * | 1992-06-22 | 1993-12-28 | General Electric Company | Arrangement for defining improved cooling airflow supply path through clearance control ring and shroud |
US5399066A (en) * | 1993-09-30 | 1995-03-21 | General Electric Company | Integral clearance control impingement manifold and environmental shield |
FR2750451B1 (fr) * | 1996-06-27 | 1998-08-07 | Snecma | Dispositif de soufflage de gaz de reglage de jeux dans une turbomachine |
FR2766517B1 (fr) * | 1997-07-24 | 1999-09-03 | Snecma | Dispositif de ventilation d'un anneau de turbomachine |
FR2800797B1 (fr) * | 1999-11-10 | 2001-12-07 | Snecma | Assemblage d'un anneau bordant une turbine a la structure de turbine |
FR2803871B1 (fr) * | 2000-01-13 | 2002-06-07 | Snecma Moteurs | Agencement de reglage de diametre d'un stator de turbine a gaz |
DE10026355B4 (de) * | 2000-05-27 | 2010-06-17 | Mahle Filtersysteme Gmbh | Schalldämpfende Luftleitung |
FR2817290B1 (fr) * | 2000-11-30 | 2003-02-21 | Snecma Moteurs | Flasque de disque aubage de rotor et agencement correspondant |
FR2819010B1 (fr) * | 2001-01-04 | 2004-05-28 | Snecma Moteurs | Secteur d'entretoise de support d'anneau de stator de la turbine haute pression d'une turbomachine avec rattrapage de jeux |
FR2831918B1 (fr) * | 2001-11-08 | 2004-05-28 | Snecma Moteurs | Stator pour turbomachine |
-
2000
- 2000-11-09 FR FR0014373A patent/FR2816352B1/fr not_active Expired - Fee Related
-
2001
- 2001-10-26 JP JP2001328678A patent/JP3913032B2/ja not_active Expired - Fee Related
- 2001-11-06 CA CA002361103A patent/CA2361103C/fr not_active Expired - Fee Related
- 2001-11-08 UA UA2001117658A patent/UA73938C2/uk unknown
- 2001-11-08 US US09/986,280 patent/US6896038B2/en not_active Expired - Lifetime
- 2001-11-08 DE DE60100448T patent/DE60100448T2/de not_active Expired - Lifetime
- 2001-11-08 ES ES01402865T patent/ES2199921T3/es not_active Expired - Lifetime
- 2001-11-08 RU RU2001130175/06A patent/RU2276733C2/ru not_active IP Right Cessation
- 2001-11-08 EP EP01402865A patent/EP1205637B1/fr not_active Expired - Lifetime
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN107795383A (zh) * | 2016-08-29 | 2018-03-13 | 中国航发商用航空发动机有限责任公司 | 一种燃气轮机冷却气分配系统 |
CN107795383B (zh) * | 2016-08-29 | 2019-08-06 | 中国航发商用航空发动机有限责任公司 | 一种燃气轮机冷却气分配系统 |
Also Published As
Publication number | Publication date |
---|---|
FR2816352A1 (fr) | 2002-05-10 |
ES2199921T3 (es) | 2004-03-01 |
UA73938C2 (uk) | 2005-10-17 |
JP3913032B2 (ja) | 2007-05-09 |
DE60100448D1 (de) | 2003-08-14 |
EP1205637A1 (fr) | 2002-05-15 |
US6896038B2 (en) | 2005-05-24 |
RU2276733C2 (ru) | 2006-05-20 |
US20020053837A1 (en) | 2002-05-09 |
CA2361103C (fr) | 2009-12-29 |
CA2361103A1 (fr) | 2002-05-09 |
DE60100448T2 (de) | 2004-04-15 |
JP2002195007A (ja) | 2002-07-10 |
FR2816352B1 (fr) | 2003-01-31 |
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