EP0816639B1 - Kühlgaskrümmer für Dichtungsspaltregelung einer Turbomaschine - Google Patents

Kühlgaskrümmer für Dichtungsspaltregelung einer Turbomaschine Download PDF

Info

Publication number
EP0816639B1
EP0816639B1 EP97401486A EP97401486A EP0816639B1 EP 0816639 B1 EP0816639 B1 EP 0816639B1 EP 97401486 A EP97401486 A EP 97401486A EP 97401486 A EP97401486 A EP 97401486A EP 0816639 B1 EP0816639 B1 EP 0816639B1
Authority
EP
European Patent Office
Prior art keywords
gas
blowing device
partitions
chambers
orifices
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
Application number
EP97401486A
Other languages
English (en)
French (fr)
Other versions
EP0816639A1 (de
Inventor
Josette Benoist
Didier Désiré René Pasquiet
Guilaume Henri Chaput
Jean-Claude Christian Taillant
Guy Pierre Queneherve
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA Moteurs SA
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by SNECMA Moteurs SA filed Critical SNECMA Moteurs SA
Publication of EP0816639A1 publication Critical patent/EP0816639A1/de
Application granted granted Critical
Publication of EP0816639B1 publication Critical patent/EP0816639B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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
    • 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
    • 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
    • F01D25/14—Casings modified therefor

Definitions

  • the subject of the invention is a device for gas blowing to adjust the clearance inside of a turbomachine.
  • the clearance adjustment gases therefore do not open directly in the room delimited by the ring in leaving the routing lines, but pass first by a mixer.
  • This mixer is composed of a plurality of rooms in succession, having straight sections analogous and substantially separated by partitions parallel, and the partitions are pierced with orifices always more numerous from one partition to another towards the stator ring. This produces a flow in gas tree from one room to another, so well that they arrive with a great homogeneity of flow and temperature in front of the ring.
  • the orifices may consist of simple drillings operated through partitions of separation of the rooms or in short pipes. In both cases, there is only a pressure drop significantly lower than with devices ordinary pipelines, which generally involve significant disturbances in the flow by large variations in direction or speed.
  • the numbers of orifices can be in geometric progression from one partition to another, by twice as many examples, and they're from preferably distributed in circumferential rows in identical number for all partitions, so that only the angular pitch varies from one partition to another.
  • the rooms can be annular and separated by transverse partitions in the turbomachine and crown: they are then in shape stacked cylinders; or they can be substantially annular but separated by partitions cylindrical and concentric: they are then arranged in concentric cylinders.
  • the orifices between chambers can be replaced by connecting ducts if the rooms are not contiguous.
  • This design applies in peculiar to elongated devices where the chambers face different portions to be ventilated from the ring and are pierced with blowing holes towards these portions.
  • the advantage of having conduits always more numerous between pairs of rooms successive towards the flow of gas from ventilation remains, but the appropriate realization of the invention can be implemented somewhat different from the achievements previously exposed. he it is no longer necessary that the rooms have the same cross section if the gas gradually leaks through the orifices which pierce them: on the contrary favorable that their cross sections decrease by one room to room to maintain speed and almost constant pressure. But it should always that the rooms have the same extent, that is to say the same angular extension in the case normal annular chambers or ring portion.
  • the turbomachine portion shown on the different figures basically includes a fragment of stator 1 which comprises, facing two stages movable blades 2, two rings 3 formed of a skin metallic substantially cylindrical and which carries sealing segments 4, located just in front of the ends movable blades 2, via a ring of fixing 5.
  • a chamber 6 or 106 is provided behind each of the rings 3, and two low walls 7, in one piece with ring 3, also delimit it on the sides in the realization of figure 1.
  • the mixer 8 subject of the invention is of annular shape, closes the outside of one of the rooms 6 and is screwed by its ends longitudinal to two sheets 9 which form extensions of the walls 7.
  • An outer casing ring 10 surrounds and covers the mixer 8. It is however crossed by four gas supply conduits 11 which end in a first chamber 12 of the mixer 8. These conduits 11 are arranged at an angle right around the machine, and only one is shown for that in figure 1.
  • Gas flows enter more precisely through the external wall of the mixer 8 and have first a centripetal direction by leaving ducts 11, before straightening in the first chamber 12 to take an axial direction. They then enter a second chamber 14, then a third chamber 15, before leaving the mixer 8 and go to the first room 6 assigned to ring diameter adjustment 3.
  • Each of these passages is carried out by ever more numerous orifices: while there were four conduits 11, there are eight orifices 16 between the first room 12 and second room 14, sixteen orifices 17 between the second chamber 14 and the third chamber 15 and thirty-two orifices 18 at the exit from third room 15, as seen well on figures 2 to 5 which represent half-circumferences of mixer 8, the rest being identical.
  • the holes 16, 17, 18 are respectively arranged around the machine in a single row, so that their angular pitch is two each time times smaller. This results in a uniformization of the flow and some mixing of the gases which helps to equalize both the flow and the temperature, i.e. thermal expansion produced.
  • the mixer 8 can be formed of two circular sheet metal plates, corresponding substantially to external 13 and internal 19 faces of the chambers 12, 14 and 15 annular and stamped to join at the longitudinal ends and at the partitions 16 and 17, except at the orifices; these sheets include borders end 24 by which they are screwed to sheets 9 integral with the walls 7.
  • FIG. 6 represents a mixer 108 substantially similar but whose structure, as well than those of neighboring rooms, is entirely formed of removable covers.
  • conduits feed here designated by 111, lead to the outer casing 10 and are not joined to the mixer 108.
  • a first cowling 113 forms the face outside, directed towards the outer casing 10, of the mixer 108 and includes an internal border 114 embedded between two flanges of elements 115 and 116 of the stator 101, these elements 115 and 116 being linked respectively to the rings subject to thermal adjustment and to the outer casing 10 to form a partition keep on going.
  • the volume between the outer casing 10 and stator 101, which is occupied by mixer 108, is divided into two substantially concentric parts by this and in particular by the edges 114 and 120, of so that the gases originating from conduits 111 end in the external part of this volume and do not leave it only by crossing four orifices 122 opposite conduits 111 and drilled through the first cowling 113.
  • the third orifices 18 terminate in the other part of the volume containing the mixer 108, in front of one of the walls 7 of one of the bedrooms 6 thermal adjustment.
  • the bedroom 6 is crossed by a low wall 7 to the other by a longitudinal straight gas flow, and it is not closed by the mixer 108, but by a cylindrical partition 123 of a third cowling 124 screwed to the edge 120 of the first cowling 113.
  • the seal between the low walls 7 and the partition cylindrical 123 is provided by seals 125 open section toric metals, which have good elasticity even at high temperatures.
  • Adjacent cowlings can be disposed between the stator 101 and the outer casing 10 to guide the clearance adjustment gases to the second room 106; their shape depends on other arrangements found there.
  • the second chamber 106 can particular be closed by a cover 126 similar to the cylindrical partition 123 and which contributes to crushing other joints 125 with the walls 7.
  • FIG. 7 illustrates another embodiment, which concerns this time more particularly the low walls of the rooms, now designated by the reference 207: these new low walls are hollowed out with a 208 annular groove, so they're divided into two thin skins 209 and 210 which overlap.
  • the orifices, respectively 211 and 212, which pass through each of these skins 209 and 210 are not in extension, which forces the gases to a path in chicane which extends their stay in gorge 208 and improves the heat exchange with the low walls 207 and, indirectly, with the ring 3.
  • the other provisions of the invention are unchanged.
  • FIG. 8 Another remarkable achievement is shown in Figure 8.
  • This mixer 308 is formed of cowlings as in the previous realization, but here gas flow through mixer 308 is not not substantially axial but remains overall centripetal.
  • the mixer 308 is formed of a rollover that could be called laminated, formed of three successive layers 309, 310 and 311 of the casing outside 10 to stator 301, overlapping layers at the ends to isolate two chambers 312 and 313 that the gas passes successively.
  • Concentric chambers 312 and 313 have a form fairly flattened longitudinally which makes it useful, for that flow uniformity occurs, a extended path produced by a chicane arrangement orifices: the orifices 324 and 326 of the layers extremes 309 and 311 are located downstream of the machine, while the holes 325 of the layer intermediate 310 are located upstream.
  • the laminated cover is finished with a first border 315, screwed to the outer casing 10, and by a border opposite taking the form of an angle iron 316 receiving a pressed open section metal O-ring 317 against an opposite circular strip of the outer casing 10.
  • This arrangement again allows the air originating in conduits 11 is forced to pass through the mixer 308 to reach the adjustment chamber thermal 6.
  • the volume between the outer casing 10 and the stator 301 outside the covers 309 to 311 forms two chambers extremes 327 and 328 which also belong to the mixer 308, since the uniformity of the flow is also produced there.
  • cowlings 318 and 319 are still cowlings 318 and 319, generally transverse direction, to isolate the chamber 6 delimited by the ring 3; these cowlings 318 and 319 replace the solution walls previous; they are screwed by one end to the outer casing 10 and the other between the flanges of connection 320 of adjacent elements of stator 301.
  • These connection flanges 320 indeed leave a throat 321 between them in the middle of which introduces a lunule 322 at the end of the cowling additional 318 or 319 respectively, which leaves gas other possibility than entering the throat 321 and go to the bottom of it before leaving it, by circumventing lunula 322 by a movement in hair pin.
  • the advantage achieved by this layout here again is that heat exchange is facilitated, this time by a conduction of the flanges of connection 320 to ring 3.
  • the last variant exposed here concerns a mixing device with which the chambers are provided leak ports that do not communicate with one another bedrooms.
  • This design is useful for mixing devices longer than the previous and each of which rooms is assigned to cooling of a separate area of the machine.
  • a such design is shown in Figures 9 to 13, where the mixing device 400 is present under shape of a ring surrounding a low turbine pressure 401 whose stator 402 must be cooled.
  • mixing device 400 is composed of two sheets 403 and 404 stamped and joined to each other then to enclose chambers 405, 406, 407 and 408 successive circulars and of polygonal section.
  • the mixing device 400 is supplied with gas by a supply line 411 at least: as mounting of the mixing device is easier if it is built in two semicircular parts, we will use two supply lines in total if these semicircular parts remain disjoint when the machine is mounted, and either two conduits only one if these parts are joined together by junction flanges so that rooms 405 to 408 extend over one tower full.
  • the construction with disjoint parts is more simple but not as good because part of the machine is insufficiently cooled at the junctions between the blowing device housings 400, and ventilation irregularities and therefore deformation of the stator 402 can appear from one half to the other of the device 400.
  • Figure 10 shows that the principle of the previous embodiments is retained: if there is only one supply conduit 411 which joined the first chamber 405, there are two conduits 412 joining rooms 405 and 406 and four conduits 413 joining rooms 406 to rooms 407 and 408, the conduits 413 being pierced with lateral orifices 414 crossing the third room 407.
  • This connection design applies to one half blower 400 and is repeated for the other half; others are possible, with numbers of chambers and connecting pipes different, depending on the angular extension of the rooms.
  • Figure 11 shows the mixing device 400 isolated. We see that rooms 405 to 408 have decreasing sections, which is justified by the flow ever weaker gas reaching them and travels; Figures 12 and 13 show that the conduits 412 are much wider than the conduits 413 because of their smaller number and larger flow passing there.
  • Conduits 412 and 413 play perfectly the role of the orifices making the rooms communicate other achievements and are only needed reason for the spacing of the rooms in this production.
  • FIG. 10 represents partitions 414 and 415 which respectively divide the last two rooms 407 and 408 in compartments in each which leads only one of the conduits 413. This provision further promotes equalization of flow rates and ventilation air for each of the rooms.
  • Figure 11 shows one of the flanges 416 of junction with the other semi-circular half of the device mixer 400.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (14)

  1. Kühlgaskrümmer in einem Turbotriebwerk, der sich um mindestens einen Statorring herum erstreckt und mehrere Kammern (12, 14, 15, 312, 313) umfasst, die in Achsrichtung aufeinander folgen, analoge aufrechte Querschnitte aufweisen und durch Trennwände (16, 17, 309, 310, 311) abgegrenzt sind, durch die Öffnungen (11, 16, 17, 18, 111, 324, 325, 326) verlaufen,
       dadurch gekennzeichnet,    dass die Kammern (12, 14, 15, 312, 313) durch die Trennwände hindurch mittels der Öffnungen (16, 17, 324, 325, 326), die in Strömungsrichtung des Gases von einer Trennwand zur nächsten stets zahlreicher sind, miteinander verbunden sind, wobei die Trennwände zwischen den Kammern angeordnete Trennwänden umfassen, die im wesentlichen parallel zueinander angeordnet sind.
  2. Kühlgaskrümmer nach Anspruch 1,
       dadurch gekennzeichnet,    dass die Anzahlen der Öffnungen von einer Trennwand zur nächsten in geometrischer Abstufung vorgesehen sind.
  3. Kühlgaskrümmer nach Anspruch 1,
       dadurch gekennzeichnet,    dass die Öffnungen von einer Trennwand zur nächsten jeweils in doppelter Anzahl vorgesehen sind.
  4. Kühlgaskrümmer nach Anspruch 1,
       dadurch gekennzeichnet,    dass die Kammern (12, 14, 15) ringförmig ausgeführt und durch in dem Triebwerk quer verlaufende und kranzförmig ausgeführte Trennwände voneinander getrennt sind.
  5. Kühlgaskrümmer nach Anspruch 1,
       dadurch gekennzeichnet,    dass die Kammern (327, 312, 313, 328) im wesentlichen ringförmig ausgeführt und durch im wesentlichen zylindrische und konzentrische Trennwände (309, 310, 311) voneinander getrennt sind.
  6. Kühlgaskrümmer nach Anspruch 1,
       dadurch gekennzeichnet,    dass er eine Kammer zur Wärmeeinstellung (6) aufweist, die durch den Ring (3), eine der genannten Trennwände und durch parallele Raumteilerwände (7), die mit dem Ring verbunden sind und sich bis zu dieser Trennwand erstrecken, umgrenzt wird, wobei durch die Raumteilerwände hindurch Auslassöffnungen (20) verlaufen.
  7. Kühlgaskrümmer nach Anspruch 1,
       dadurch gekennzeichnet,    dass der Ring (3) mit Raumteilerwänden (207, 320) verbunden ist, durch die gewundene Öffnungen (208, 211, 212, 321) verlaufen, durch die hindurch das Gas durch die Raumteilerwände gelangt.
  8. Kühlgaskrümmer nach Anspruch 7,
       dadurch gekennzeichnet,    dass die Raumteilerwände von zwei parallelen Häuten (209, 210, 320) gebildet werden, die durch eine Rille (208, 321) voneinander getrennt sind.
  9. Kühlgaskrümmer nach Anspruch 8,
       dadurch gekennzeichnet,    dass die Kammern und die Trennwände aus aufeinandergefügten Hauben bestehen.
  10. Kühlgaskrümmer nach Anspruch 9,
       dadurch gekennzeichnet,    dass Abschnitte (322) der Hauben zumindest in manchen der Rillen (321) in Eingriff sind.
  11. Kühlgaskrümmer in einem Turbotriebwerk, der sich um mindestens einen Statorring herum erstreckt und mehrere Kammern (405, 406, 407) umfasst, die in Achsrichtung parallel angeordnet sind, analoge Ausdehnungen haben, und durch welche Öffnungen (409) zum Statorring hin verlaufen,
       dadurch gekennzeichnet,    dass die Kammern kleiner werdende aufrechte Querschnitte aufweisen und durch Leitungen (412, 413) miteinander verbunden sind, die in Strömungsrichtung des Gases von einer Kammer zur nächsten stets zahlreicher sind.
  12. Kühlgaskrümmer nach Anspruch 11,
       dadurch gekennzeichnet,    dass die Anzahlen der Leitungen von einer Kammerverbindung zur nächsten in geometrischer Abstufung vorgesehen sind.
  13. Kühlgaskrümmer nach Anspruch 12,
       dadurch gekennzeichnet,    dass die Leitungen von einer Kammerverbindung zur nächsten jeweils in doppelter Anzahl vorgesehen sind.
  14. Kühlgaskrümmer nach Anspruch 11,
       dadurch gekennzeichnet,    dass die Kammern in Bereiche unterteilt sind, in die jeweils eine der Leitungen mündet, die zu einer in Strömungsrichtung des Gases vorherigen Kammer führt.
EP97401486A 1996-06-27 1997-06-26 Kühlgaskrümmer für Dichtungsspaltregelung einer Turbomaschine Expired - Lifetime EP0816639B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9607978A FR2750451B1 (fr) 1996-06-27 1996-06-27 Dispositif de soufflage de gaz de reglage de jeux dans une turbomachine
FR9607978 1996-06-27

Publications (2)

Publication Number Publication Date
EP0816639A1 EP0816639A1 (de) 1998-01-07
EP0816639B1 true EP0816639B1 (de) 2002-05-29

Family

ID=9493461

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97401486A Expired - Lifetime EP0816639B1 (de) 1996-06-27 1997-06-26 Kühlgaskrümmer für Dichtungsspaltregelung einer Turbomaschine

Country Status (5)

Country Link
US (1) US5980201A (de)
EP (1) EP0816639B1 (de)
CA (1) CA2209297A1 (de)
DE (1) DE69712831T2 (de)
FR (1) FR2750451B1 (de)

Families Citing this family (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1079068A3 (de) * 1999-08-27 2004-01-07 General Electric Company Verbindungsmuffe für den Kühlkreislauf eines Turbinenrotors
FR2816352B1 (fr) * 2000-11-09 2003-01-31 Snecma Moteurs Ensemble de ventilation d'un anneau de stator
US6454529B1 (en) * 2001-03-23 2002-09-24 General Electric Company Methods and apparatus for maintaining rotor assembly tip clearances
EP1611315B1 (de) * 2003-04-07 2015-07-29 Alstom Technology Ltd Turbomaschine
DE10352089A1 (de) * 2003-11-07 2005-06-09 Alstom Technology Ltd Verfahren zum Betreiben einer Turbomaschine, und Turbomaschine
DE102005035540A1 (de) * 2005-07-29 2007-02-01 Mtu Aero Engines Gmbh Vorrichtung zur aktiven Spaltkontrolle für eine Strömungsmaschine
US7740443B2 (en) * 2006-11-15 2010-06-22 General Electric Company Transpiration clearance control turbine
US8197186B2 (en) * 2007-06-29 2012-06-12 General Electric Company Flange with axially extending holes for gas turbine engine clearance control
US8393855B2 (en) * 2007-06-29 2013-03-12 General Electric Company Flange with axially curved impingement surface for gas turbine engine clearance control
GB2469490B (en) * 2009-04-16 2012-03-07 Rolls Royce Plc Turbine casing cooling
EP2243933A1 (de) * 2009-04-17 2010-10-27 Siemens Aktiengesellschaft Gehäuseteil, insbesondere einer Turbomaschine
US8894359B2 (en) * 2011-12-08 2014-11-25 Siemens Aktiengesellschaft Gas turbine engine with outer case ambient external cooling system
US10094285B2 (en) * 2011-12-08 2018-10-09 Siemens Aktiengesellschaft Gas turbine outer case active ambient cooling including air exhaust into sub-ambient cavity
US9664062B2 (en) * 2011-12-08 2017-05-30 Siemens Energy, Inc. Gas turbine engine with multiple component exhaust diffuser operating in conjunction with an outer case ambient external cooling system
US20130149107A1 (en) * 2011-12-08 2013-06-13 Mrinal Munshi Gas turbine outer case active ambient cooling including air exhaust into a sub-ambient region of exhaust flow
US9085982B2 (en) * 2012-03-19 2015-07-21 Mitsubishi Hitachi Power Systems, Ltd. Gas turbine
JP5868802B2 (ja) * 2012-07-20 2016-02-24 株式会社東芝 タービン
US9598974B2 (en) * 2013-02-25 2017-03-21 Pratt & Whitney Canada Corp. Active turbine or compressor tip clearance control
US9279339B2 (en) 2013-03-13 2016-03-08 Siemens Aktiengesellschaft Turbine engine temperature control system with heating element for a gas turbine engine
DE102015215144B4 (de) * 2015-08-07 2017-11-09 MTU Aero Engines AG Vorrichtung und Verfahren zum Beeinflussen der Temperaturen in Innenringsegmenten einer Gasturbine
FR3041037B1 (fr) * 2015-09-15 2018-08-17 Safran Aircraft Engines Dispositif de ventilation d'un carter de turbine d'une turbomachine
JP6563312B2 (ja) * 2015-11-05 2019-08-21 川崎重工業株式会社 ガスタービンエンジンの抽気構造
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
EP3342991B1 (de) * 2016-12-30 2020-10-14 Ansaldo Energia IP UK Limited Prallplatten für kühlung in einer gasturbine
US10422237B2 (en) * 2017-04-11 2019-09-24 United Technologies Corporation Flow diverter case attachment for gas turbine engine
US10914187B2 (en) * 2017-09-11 2021-02-09 Raytheon Technologies Corporation Active clearance control system and manifold for gas turbine engine
EP3569822A1 (de) * 2018-05-15 2019-11-20 Siemens Aktiengesellschaft Rohrverbindung für eine strömungsmaschine
CN109653813B (zh) * 2018-11-27 2019-08-23 中国航发沈阳发动机研究所 一种变几何涡轮冷气流路结构
FR3096084B1 (fr) * 2019-05-16 2021-04-16 Safran Aircraft Engines Procédé et dispositif d’estimation d’une zone morte d’une vanne de décharge de turbomachine
US11215075B2 (en) * 2019-11-19 2022-01-04 Rolls-Royce North American Technologies Inc. Turbine shroud assembly with flange mounted ceramic matrix composite turbine shroud ring
CN114542287A (zh) * 2022-02-17 2022-05-27 中国航发沈阳发动机研究所 一种降低机匣壁面周向温度不均匀性的引气结构

Family Cites Families (9)

* Cited by examiner, † Cited by third party
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
GB2103294B (en) * 1981-07-11 1984-08-30 Rolls Royce Shroud assembly for a gas turbine engine
US4573865A (en) * 1981-08-31 1986-03-04 General Electric Company Multiple-impingement cooled structure
US4512712A (en) * 1983-08-01 1985-04-23 United Technologies Corporation Turbine stator assembly
GB2236147B (en) * 1989-08-24 1993-05-12 Rolls Royce Plc Gas turbine engine with turbine tip clearance control device and method of operation
US5100291A (en) * 1990-03-28 1992-03-31 General Electric Company Impingement manifold
GB9027986D0 (en) * 1990-12-22 1991-02-13 Rolls Royce Plc Gas turbine engine clearance control
FR2688539A1 (fr) * 1992-03-11 1993-09-17 Snecma Stator de turbomachine comprenant des dispositifs de reglage de jeu entre le stator et les aubes du rotor.
US5399066A (en) * 1993-09-30 1995-03-21 General Electric Company Integral clearance control impingement manifold and environmental shield

Also Published As

Publication number Publication date
CA2209297A1 (fr) 1997-12-27
EP0816639A1 (de) 1998-01-07
FR2750451A1 (fr) 1998-01-02
DE69712831T2 (de) 2003-01-16
DE69712831D1 (de) 2002-07-04
FR2750451B1 (fr) 1998-08-07
US5980201A (en) 1999-11-09

Similar Documents

Publication Publication Date Title
EP0816639B1 (de) Kühlgaskrümmer für Dichtungsspaltregelung einer Turbomaschine
EP1134360B1 (de) Verstellvorrichtung für den Durchmesser des Stators eines Gasturbinenwerks
EP1586743B1 (de) Turbinen-Mantelring
EP0636765B1 (de) Kühlung von Turbinenrotorscheibe
FR2858652A1 (fr) Dispositif de controle de jeu dans une turbine a gaz
EP0176447A1 (de) Vorrichtung für die automatische Regelung des Spiels einer Labyrinthdichtung einer Turbomaschine
EP3587743B1 (de) Vorrichtung zum kühlen eines turbotriebwerkgehäuses
FR2552817A1 (fr) Perfectionnements au refroidissement des rotors de turbines
FR2552164A1 (fr) Disque de compresseur avec accelerateur centripete integre pour l'aspiration d'air dans un dispositif de refroidissement d'une turbine a gaz
WO2021181038A1 (fr) Aube creuse de turbomachine
EP0081405B1 (de) Ringförmige luftgekühlte abreissbare Schaufeldichtung für eine Gasturbine oder einen Kompressor
FR2490721A1 (fr) Turbomachine dont les aubages mobile et fixe sont proteges par une carapace en ceramique
FR2513695A1 (fr) Aube mobile aerodynamiquement profilee et refrigeree pour moteur a turbine a gaz
FR3067405A1 (fr) Turbomachine et procede d'etancheite par soufflage d'air
EP2705219B1 (de) Turbinendüsenleitschaufelanordnung in einer turbomaschine
EP3642538B1 (de) Verbrennungssystem mit konstantem volumen mit einem drehbaren verschlusselement mit segmentierten öffnungen
FR3153108A1 (fr) Système amélioré de refroidissement d’anneau fixe de turbine à gaz
FR3110201A1 (fr) Carter d’échappement de turbomachine
WO2018042116A1 (fr) Procede et dispositif de reglage de jeux entre un rotor et un stator concentrique d'une turbomachine d'aeronef
FR3164245A1 (fr) Carter d’injection d’air de refroidissement d’un disque de rotor d’une turbine comprenant des espaces inter-canaux
FR3148622A1 (fr) Composant de turbomachine, turbomachine l’ayant et procédé de fabrication de celui-ci
WO2021009439A1 (fr) Chambre de combustion de turbomachine a volume constant
WO2024194568A1 (fr) Architecture pour joint d'etancheite de turbomachine
EP4381174A1 (de) Kühlmantel einer hohlen verteilerschaufel
BE511285A (de)

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 19970707

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE FR GB

AKX Designation fees paid

Free format text: DE FR GB

RBV Designated contracting states (corrected)

Designated state(s): DE FR GB

17Q First examination report despatched

Effective date: 20001019

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SNECMA MOTEURS

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REF Corresponds to:

Ref document number: 69712831

Country of ref document: DE

Date of ref document: 20020704

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 20020720

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20030303

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20050524

Year of fee payment: 9

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20050527

Year of fee payment: 9

Ref country code: DE

Payment date: 20050527

Year of fee payment: 9

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20060626

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20070103

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20060626

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20070228

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20060630