EP1205637A1 - Ensemble de ventilation d'un anneau de stator - Google Patents
Ensemble de ventilation d'un anneau de stator Download PDFInfo
- Publication number
- EP1205637A1 EP1205637A1 EP01402865A EP01402865A EP1205637A1 EP 1205637 A1 EP1205637 A1 EP 1205637A1 EP 01402865 A EP01402865 A EP 01402865A EP 01402865 A EP01402865 A EP 01402865A EP 1205637 A1 EP1205637 A1 EP 1205637A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- stator ring
- ramps
- ring
- ventilation assembly
- shells
- 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
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
- This talk deals with a set of ventilation of a stator ring, intended to convey a gas at a determined temperature up to a ring turbomachine stator to adjust its diameter and the game he will do with blade tips of rotor rotating in it.
- Such ventilation assemblies are commonly used in turbojets and consist of multi-branched conduits taken up and the ends of which are provided with holes to blow gas and especially air to a large number of points, judiciously distributed, of the ring.
- Terminal conduits are very often ramps running around the rings, in the shape of an arc of a circle and embracing 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 these ribs which are more rigid and govern therefore the deformations of the ring proper.
- the assembly which will be described here is characterized in that it is easy to manufacture, despite the large number of conduits that are generally required use, and assemble to the ring despite the complications which can arise from dilations differential thermal at different times of machine operation.
- the invention thus relates to a ventilation assembly of a ring stator composed of branched conduits comprising supply lines, distributors and ramps adjacent to the ring and provided with holes blowing of gases directed towards the ring, characterized in what the ramps are made up of pairs of half shells including a flange and a border surrounding the flange, the pairs of half-shells being joined by the edges, the distributors include spool coils between the ramps and fitted with end edges shaped to fit on side cheek openings of the flanges.
- a stator ring 1 is associated with a group of ventilation units 2 conforming to the 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, distributor 4 for distributing air from ventilation between all ramps 3 and a duct supply 5 (visible in Figure 2) connected to the distributor 4.
- supply lines 5 join after one or more others distributors, which are not shown because they are not the subject of this invention; this one relates more specifically to the end of the assemblies ventilation 2, i.e. their parts which are close to ring 1 to be ventilated.
- each of the ramps 3 is composed of a half-shell left 7 and a right half shell 8 of which each of these is assembled to one of these. More precisely, the half-shells 7 and 8 of the two genera each include a flange 9 substantially flat and a border 10 established around the flange 9, the borders 10 of pairs of half-shells 7 and 8 additional being extended and joined to form a single ramp.
- Half-shells 7 and 8 can be made by 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 machine tubes to bring them to shapes and desired dimensions, which would probably be a lot more tedious.
- half-shells of left 7 can generally be built at 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 does not exclude some dissimilarities of details.
- half-shells 7 and 8 could be constructed with borders 10 of different widths, so for example favor ventilation by the 3 most wide.
- An example of application of this process appears in Figure 2, where three ramps 3 ventilate two ribs 11, the central ramp being placed between the two ribs 11 and ventilating them both, which justifies that its width is double.
- the distributor 4 also includes coils 15 in the form of a short cylinder serving spacers between the ramps 3 and with the conduit 5. It is often beneficial that they are similar, but they can also be different in particular in length. They understand generally edges 16 to be engaged in the openings 13 ramps 3 to hold them in place, and flanges 17 pressing on the ramps 3 to define the spacing of these. Distributor 4 is formed when the coils 15 have been soldered to ramps 3. However, the distribution duct 5 remains generally separate from dispenser 4 and can slide in the input coil 15, a seal sealing 18 being added between them, however.
- one of the coils 15 comprises planar faces and opposite 19 enclosing the end 20 (here enlarged) of the rib 11 which the corresponding coil 15 overcomes.
- the reduction in the axial clearance between the coil 15 and the enlarged portion of the rib 11 contributes to ensuring the axial positioning of the distributors 4 on the ring 1.
- the second coil overlaps its ring with axial play, this to allow the relative dilations between the housings 4 and casing 1 without generating a connection hyperstatic and unwanted constraints.
- FIG. 3 shows that the end 20 of this rib 11 has a v-notch 21 in which the central, cylindrical portion of the coil 15 rests in self-centering, which guarantees the distributor 4 against radial movements and tangents to ring 1: perfect positioning radial, tangential and in orientation along the axis of the engine is performed.
- Brackets 22 are linked 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 maintain the ends of rule 6 on them by compressing springs 28 based on rule 6 by washers 29.
- Such an assembly has the property of allow better control of the support effort of rules 6 on equettes 24 and 25. If this effect is excessive, the assembly is rigid and does not allow thermal respiration.
- rule 6 to which ramps 3 are welded, is provided with 30 wide openings around bolts 26 and 27, so that it can be move by sliding axially and tangentially by compared to the stator ring. This flexible mounting avoids therefore to produce excessive internal stresses in ventilation assembly 2, since the ramps 3 have the ability to move above the ring 1 without exerting too much effort. These relative displacements are generally due to thermal expansions differential.
- the support of one of the coils 15 against the end 20 of the corresponding rib 11 offers also some flexibility by allowing all of ventilation 2 to move to the ends, while being recalled towards the stator ring 1 and the bottom of the vé 21 by springs 28. This flexibility is valuable by absorbing expansions inevitable differential thermal 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)
Abstract
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) adjacents à l'anneau et munies de perçages (12) de soufflage de gaz dirigés vers l'anneau, caractérisé en ce que 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, 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 |
---|---|---|---|
FR0014373A FR2816352B1 (fr) | 2000-11-09 | 2000-11-09 | Ensemble de ventilation d'un anneau de stator |
FR0014373 | 2000-11-09 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1205637A1 true EP1205637A1 (fr) | 2002-05-15 |
EP1205637B1 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 (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1577501A1 (fr) * | 2004-03-18 | 2005-09-21 | Snecma | Stator de turbine haute-pression de turbomachine et procédé d'assemblage |
EP1577502A1 (fr) * | 2004-03-18 | 2005-09-21 | Snecma | Dispositif de pilotage de jeu de turbine à gaz à équilibrage des débits d'air |
EP2243931A3 (fr) * | 2009-04-16 | 2013-09-18 | Rolls-Royce plc | Refroidissement de carter de turbine |
ITTO20120519A1 (it) * | 2012-06-14 | 2013-12-15 | Avio Spa | Turbina a gas per motori aeronautici |
FR2999642A1 (fr) * | 2012-12-17 | 2014-06-20 | Snecma | Ensemble statorique dont les bosses comportent des portions en creux ou en saillie |
CN106382136A (zh) * | 2016-11-18 | 2017-02-08 | 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 |
FR3040428A1 (fr) * | 2015-08-27 | 2017-03-03 | Snecma | Dispositif de refroidissement par jets d'air du carter d'une turbine d'une turbomachine |
CN107923259A (zh) * | 2015-08-27 | 2018-04-17 | 赛峰飞机发动机公司 | 用于附接通过空气射流冷却涡轮发动机的涡轮机的外壳的歧管的装置 |
EP3318725A1 (fr) * | 2016-11-08 | 2018-05-09 | Safran Aircraft Engines | Ensemble de raccordement pour le refroidissement d'une turbine de turbomachine |
EP3415724A1 (fr) * | 2017-06-12 | 2018-12-19 | United Technologies Corporation | Ensemble de montage élastique pour un moteur à turbine |
FR3089544A1 (fr) * | 2018-12-10 | 2020-06-12 | Safran Aircraft Engines | Dispositif de refroidissement d’un carter de turbomachine |
FR3099798A1 (fr) * | 2019-08-09 | 2021-02-12 | Safran Aircraft Engines | Ensemble pour une turbine de turbomachine |
FR3099801A1 (fr) * | 2019-08-09 | 2021-02-12 | Safran Aircraft Engines | Ensemble pour une turbine de turbomachine |
WO2021209713A1 (fr) | 2020-04-17 | 2021-10-21 | Safran Aircraft Engines | Dispositif de refroidissement d'un carter de turbine |
Families Citing this family (26)
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 |
US7597537B2 (en) * | 2005-12-16 | 2009-10-06 | General Electric Company | Thermal control of gas turbine engine rings for active clearance control |
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 |
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 |
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 |
US9341074B2 (en) * | 2012-07-25 | 2016-05-17 | General Electric Company | Active clearance control manifold system |
WO2015119754A1 (fr) * | 2014-02-04 | 2015-08-13 | United Technologies Corporation | Supports pour composants de moteur à turbine à gaz |
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 |
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 |
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 |
FR3058459B1 (fr) * | 2016-11-04 | 2018-11-09 | Safran Aircraft Engines | Dispositif de refroidissement pour une turbine d'une turbomachine |
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 |
US11788425B2 (en) * | 2021-11-05 | 2023-10-17 | General Electric Company | Gas turbine engine with clearance control system |
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---|---|---|---|---|
US4279123A (en) * | 1978-12-20 | 1981-07-21 | United Technologies Corporation | External gas turbine engine cooling for clearance control |
US5100291A (en) * | 1990-03-28 | 1992-03-31 | General Electric Company | Impingement manifold |
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 |
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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 |
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 |
US5205115A (en) * | 1991-11-04 | 1993-04-27 | General Electric Company | Gas turbine engine case counterflow thermal control |
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 |
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-
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 DE DE60100448T patent/DE60100448T2/de not_active Expired - Lifetime
- 2001-11-08 ES ES01402865T patent/ES2199921T3/es not_active Expired - Lifetime
- 2001-11-08 UA UA2001117658A patent/UA73938C2/uk unknown
- 2001-11-08 RU RU2001130175/06A patent/RU2276733C2/ru not_active IP Right Cessation
- 2001-11-08 US US09/986,280 patent/US6896038B2/en not_active Expired - Lifetime
- 2001-11-08 EP EP01402865A patent/EP1205637B1/fr not_active Expired - Lifetime
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4279123A (en) * | 1978-12-20 | 1981-07-21 | United Technologies Corporation | External gas turbine engine cooling for clearance control |
US5100291A (en) * | 1990-03-28 | 1992-03-31 | General Electric Company | Impingement manifold |
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 |
Cited By (28)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1577502A1 (fr) * | 2004-03-18 | 2005-09-21 | Snecma | Dispositif de pilotage de jeu de turbine à gaz à équilibrage des débits d'air |
FR2867806A1 (fr) * | 2004-03-18 | 2005-09-23 | 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 |
US7309209B2 (en) | 2004-03-18 | 2007-12-18 | Snecma Moteurs | Device for tuning clearance in a gas turbine, while balancing air flows |
US7360987B2 (en) | 2004-03-18 | 2008-04-22 | Snecma | Stator of a high-pressure turbine of a turbomachine, and a method of assembling it |
EP1577501A1 (fr) * | 2004-03-18 | 2005-09-21 | Snecma | Stator de turbine haute-pression de turbomachine et procédé d'assemblage |
US8668438B2 (en) | 2009-04-16 | 2014-03-11 | Rolls-Royce Plc | Turbine casing cooling |
EP2243931A3 (fr) * | 2009-04-16 | 2013-09-18 | Rolls-Royce plc | Refroidissement de carter de turbine |
WO2013186757A2 (fr) | 2012-06-14 | 2013-12-19 | Avio S.P.A. | Turbine à gaz pour moteurs aéronautiques |
WO2013186757A3 (fr) * | 2012-06-14 | 2014-02-20 | Ge Avio S.R.L. | Turbine à gaz pour moteurs aéronautiques |
ITTO20120519A1 (it) * | 2012-06-14 | 2013-12-15 | Avio Spa | Turbina a gas per motori aeronautici |
US9790810B2 (en) | 2012-06-14 | 2017-10-17 | Ge Avio S.R.L. | Stator casing cooling system |
FR2999642A1 (fr) * | 2012-12-17 | 2014-06-20 | Snecma | Ensemble statorique dont les bosses comportent des portions en creux ou en saillie |
FR3040428A1 (fr) * | 2015-08-27 | 2017-03-03 | Snecma | Dispositif de refroidissement par jets d'air du carter d'une turbine d'une turbomachine |
CN107923259A (zh) * | 2015-08-27 | 2018-04-17 | 赛峰飞机发动机公司 | 用于附接通过空气射流冷却涡轮发动机的涡轮机的外壳的歧管的装置 |
FR3058460A1 (fr) * | 2016-11-08 | 2018-05-11 | Safran Aircraft Engines | Ensemble de raccordement pour le refroidissement d'une turbine de turbomachine |
US11293303B2 (en) | 2016-11-08 | 2022-04-05 | Safran Aircraft Engines | Connecting assembly for cooling the turbine of a turbine engine |
EP3318725A1 (fr) * | 2016-11-08 | 2018-05-09 | 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 |
CN106382136A (zh) * | 2016-11-18 | 2017-02-08 | 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 |
EP3415724A1 (fr) * | 2017-06-12 | 2018-12-19 | United Technologies Corporation | Ensemble de montage élastique pour un moteur à turbine |
FR3089544A1 (fr) * | 2018-12-10 | 2020-06-12 | Safran Aircraft Engines | Dispositif de refroidissement d’un carter de turbomachine |
FR3099798A1 (fr) * | 2019-08-09 | 2021-02-12 | Safran Aircraft Engines | Ensemble pour une turbine de turbomachine |
FR3099801A1 (fr) * | 2019-08-09 | 2021-02-12 | Safran Aircraft Engines | Ensemble pour une turbine de turbomachine |
WO2021028634A1 (fr) * | 2019-08-09 | 2021-02-18 | Safran Aircraft Engines | Ensemble visant à maintenir un boîtier collecteur d'un dispositif de refroidissement de carter d'une turbine de turbomachine |
WO2021209713A1 (fr) | 2020-04-17 | 2021-10-21 | Safran Aircraft Engines | Dispositif de refroidissement d'un carter de turbine |
FR3109406A1 (fr) * | 2020-04-17 | 2021-10-22 | Safran Aircraft Engines | Dispositif de refroidissement d’un carter de turbine |
US11879347B2 (en) | 2020-04-17 | 2024-01-23 | Safran Aircraft Engines | Turbine housing cooling device |
Also Published As
Publication number | Publication date |
---|---|
DE60100448T2 (de) | 2004-04-15 |
JP2002195007A (ja) | 2002-07-10 |
DE60100448D1 (de) | 2003-08-14 |
FR2816352B1 (fr) | 2003-01-31 |
EP1205637B1 (fr) | 2003-07-09 |
RU2276733C2 (ru) | 2006-05-20 |
UA73938C2 (uk) | 2005-10-17 |
FR2816352A1 (fr) | 2002-05-10 |
JP3913032B2 (ja) | 2007-05-09 |
CA2361103C (fr) | 2009-12-29 |
ES2199921T3 (es) | 2004-03-01 |
US20020053837A1 (en) | 2002-05-09 |
CA2361103A1 (fr) | 2002-05-09 |
US6896038B2 (en) | 2005-05-24 |
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