EP0651139A1 - Turbomaschine mit Einrichtungnen um das Schaufelspitzenspiel zwischen Rotor und Stator zu Regeln - Google Patents

Turbomaschine mit Einrichtungnen um das Schaufelspitzenspiel zwischen Rotor und Stator zu Regeln Download PDF

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Publication number
EP0651139A1
EP0651139A1 EP94402400A EP94402400A EP0651139A1 EP 0651139 A1 EP0651139 A1 EP 0651139A1 EP 94402400 A EP94402400 A EP 94402400A EP 94402400 A EP94402400 A EP 94402400A EP 0651139 A1 EP0651139 A1 EP 0651139A1
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EP
European Patent Office
Prior art keywords
ring sector
ring
ferrule
casing
turbomachine 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
Application number
EP94402400A
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English (en)
French (fr)
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EP0651139B1 (de
Inventor
Daniel Jean Marey
Fabrice Marois
Gérard Gabriel Miraucourt
Jean-Louis Charbonnel
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
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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.)
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Publication date
Application filed by Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0651139A1 publication Critical patent/EP0651139A1/de
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Publication of EP0651139B1 publication Critical patent/EP0651139B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/26—Double casings; Measures against temperature strain in casings
    • F01D25/265—Vertically split casings; Clamping arrangements therefor
    • 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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings

Definitions

  • the present invention relates to a turbomachine comprising means for controlling the clearances between stator and rotor and, more precisely, between the stator and the top of the moving blades of the rotor.
  • Aircraft engines (particularly those used for propulsion of jet aircraft) must be able to operate under conditions which can vary rapidly. These variations in operating conditions can be runaway from the cold rotor, a throttle stroke, runaway from the hot rotor, or any other operating conditions well known to those skilled in the art.
  • a first means consists in building the ferrules with a coating of soft material at the point in front of which the movable blades pass; thus the possible friction of the end of the movable blades which could occur during a greater expansion of the latter would cause wear of the coating and a reshaping of the stator at this location.
  • stator in such a way that it is possible to circulate gas therein, taken for example from another location of the machine, at a temperature and at a flow rate which produce at will a heating or cooling capable of regulating the expansions of the ferrule and therefore its play with the movable blades.
  • Such a sending of air at variable temperature on the structure of the rectifier support allows, by a variation of the speed of expansion and contraction of the structure, to accommodate different engine operating conditions.
  • FR-2 683 851, FR-2 516 980 and FR-2 482 661 describe turbomachinery whose stators include double-skin casings extending around the rotors on a complete circumference, the heating or cooling air circulating between the two skins of the casing.
  • the shell elements or shell sectors
  • the shell elements are directly linked to the casing. Also, during expansion or contraction of the casing, the shell elements can undergo displacements which harm the circularity of the structure.
  • Document GB-2 115 487 describes stator rings fitted by dovetail in supports.
  • Document FR-2 482 662 describes a segmented stator ring pierced with orifices.
  • turbomachine comprising a stator whose casing of 360 ° circumference and the shell elements are linked by means of a fixed point and sliding bearings ensuring the shell a circumferential flexibility.
  • each ferrule element is made integral with the casing by a fixed point means (10) and at least two sliding support means (11) located on either side of the fixed point means to provide the ferrule member with circumferential flexibility.
  • the turbomachine comprises a support ring housed between the casing and the ferrule and comprising a plurality of circular ring sectors each fixed on the casing by means of fixed point and means d '' sliding supports and having a U-shaped section whose opening is directed towards the ferrule, each ferrule element comprising hooking means able to be introduced into the opening of at least one ring sector to secure said ring sector and the ferrule element.
  • each ring sector comprises an upstream wing and a downstream wing, each of said upstream and downstream wings comprising first recesses open radially towards the ferrule to provide circumferential flexibility to said ring sector.
  • the upstream wing also has second recesses.
  • the turbomachine comprises clamping means in support on either side of each ring sector to ensure that said ring sector is secured to the means for hooking the ferrule element.
  • These tightening means comprise a screw and a conical nut introduced inside the ring sector and able to move apart during the introduction of the screw, the base of said nut then being in abutment on the internal faces of the sector. ring.
  • each ferrule element constitute, with the ends of the upstream and downstream wings of the ring sector in which it is introduced, a dovetail assembly.
  • each fixed point means comprises a screw / nut system ensuring a connection without play of a ring sector with the casing, the nut being introduced inside the ring by the second recess and disposed in abutment on an internal face of the core of the ring sector.
  • the screw can be, for example, introduced into the ring sector with an inclination close to 45 ° relative to the radial direction. It can, according to another example, be introduced radially into the ring sector, the nut then having a conical shape whose base is directed towards the ferrule.
  • the screw is then introduced into the ring sector with a longitudinal inclination at an angle a, and the support pieces comprise a surface inclined at an angle ⁇ relative to the radial direction.
  • the first recesses of the downstream wing are closed by sealing plates.
  • Each ring sector has, around the first recesses, grooves in which the sealing plates are positioned and fitted.
  • Each downstream wing of a ring sector can comprise, at one end, an extension tab and, at another end, a machining ensuring an interlocking with overlapping of said ring sector in the neighboring ring sectors.
  • each sliding support means is positioned astride two ferrule elements to keep them integral with one another.
  • FIG 1 there is shown, in axial section, a high pressure compressor having an outer casing 1 of 360 ° in circumference and means for controlling the clearances according to the first embodiment of the invention.
  • This casing 1 comprises two envelopes (or two skins) concentric, slightly conical, separated by a volume (shown hatched in Figure 1) in which circulates the heating or cooling air.
  • This two-skin housing is of the type described in the document FR-2 683 851 cited above; it will therefore not be described in more detail.
  • This casing 1 surrounds a plurality of shell elements 2 which are substantially conical. These ferrule elements 2 are arranged end to end and assembled by interlocking seals 3 to form a single continuous ferrule and substantially parallel to the casing 1.
  • Each ferrule element 2 carries a stage of stationary vanes 4 of stator, also called rectifier stage.
  • a stage of movable rotor blades 5 extends between each pair of stages of fixed blades 4.
  • the rings 6 according to the first embodiment of the invention are also shown, these rings allowing appreciable displacements of the shell elements 2 as a function of the expansions and contractions of the casing 1.
  • These rings 6 each comprise a plurality of sectors of rings arranged end to end and nested one inside the other to produce continuous rings.
  • each ring 6 has a U-shaped section, the open side of the U being directed towards the ferrule 2.
  • Each ferrule element 2 comprises on its external face, that is to say on the face not carrying the fixed vanes 4, hooking means 9 of the ring 6.
  • these attachment means 9 consist of a dovetail pin 9a capable of being introduced into the opening of the ring 6.
  • the ends of the upstream 7 and downstream 8 wings of the ring 6 form a mortise 9b suitable for receiving the post 9a.
  • the mortise 9b and the tenon 9a thus form a dovetail assembly.
  • Clamping means not shown in this figure 1, ensure a pinching on either side of the wings upstream 7 and downstream 8 of the ring 6 to ensure that said ring 6 is secured to the ferrule 2.
  • Each ring sector 6 is fixed to the casing by means of a fixed point 10 which will be described in more detail through the following figures.
  • Each ring sector is also fixed to the casing by means of sliding supports not shown in this FIG. 1 but described in more detail in the following description.
  • FIG. 2 shows in detail the elements constituting the first embodiment of the control means shown in FIG. 1.
  • FIG. 2 shows the angular distribution of the shell elements 2 and of the ring sectors 6 inside the casing 1.
  • the shell 2 therefore comprises a plurality of shell elements, three of which are shown in FIG. 2 and referenced 2a , 2b and 2c.
  • the ring 6 comprises a plurality of ring sectors, four of which are shown in this FIG. 2 and referenced 6a, 6b, 6c and 6d.
  • each ring sector has a size equivalent to approximately two shell elements.
  • the ring sector 6a comprises two sliding supports 11a and 11b on either side of the fixed point 10a and two sliding supports 11c and 11d at each of its ends.
  • each ring sector has, in fact, a plurality of recesses, namely the recesses 12 only on the upstream wing and the recesses 13 on the upstream wing and on the downstream wing, these recesses ensuring circumferential flexibility at the ring area.
  • the ring sectors 6a, 6b, ... are assembled with the neighboring ring sectors at the center of a recess 12.
  • FIG. 3 represents a perspective view of the ring sector 6a of FIG. 2.
  • This figure therefore shows the ring sector 6a cut at a recess 13, the casing 1 on which the ring sector is fixed 6a, as well as the ferrule 2 with its tenon 9a in dovetail around which fits the ends in dovetail 9b of the upstream wings 7 and downstream 8. More precisely, the ring sector 6a is connected to the casing 1 via the fixed point 10a and several sliding supports, three of which are shown in this figure and referenced 11a, 11b and 11c.
  • FIG. 4 shows, in part A, a portion of the upstream wing 7 of the ring sector 6a and, in part B, a portion of the downstream wing 8 of this same ring sector 6a .
  • part A of FIG. 4 shows the external face of the upstream wing 7 of the ring sector 6a.
  • This part A therefore shows the recesses 12 of the upstream wing 7 as well as the recesses 13 of this same upstream wing 7.
  • these recesses 13 have a radial opening 13a, or radial slot, starting from the internal part of the sector. ring (that is to say the part of smaller diameter) and ending in the recess 13.
  • These radial slots give the ring 6 a circumferential flexibility.
  • the recesses 12, produced in the upstream wing 7, make it possible to reduce the amount of material necessary for the production of this ring; this therefore results in a reduction in the ring.
  • these recesses 12 ensure a reduction in the heat exchanges between the ambient medium and the ring 6.
  • This part A of FIG. 4 also shows the nuts 14 of the clamping means.
  • Part B of FIG. 4 shows the internal face of the downstream wing 8 of the ring sector 6a.
  • This downstream wing 8 comprises the recesses 13 with their radial slots 13a as well as screws 15 which pass through the ring sector right through and are fixed in the nuts 14 of the upstream wing 7.
  • Each screw 15 associated with a nut 14 constitutes the clamping means which ensure the clamping of the ring sector around the dovetail tenon of the ferrule.
  • the sliding support 11a is also shown in this part B of FIG. 4.
  • the screw 18a of the sliding support is inserted into a sole 18b surmounted by a projection pierced with a hole on the wall of which a pitch of screws has been realized.
  • This sole 18b is supported on support pieces 19a and 19b arranged on either side of said hole in the sole 18b. These support pieces 19a and 19b are crossed by the screws 15, which secures said support pieces on the downstream wing 8.
  • An opening 21 is, moreover, made in the core 20 of the ring sector; the sole 18b has, with the projection which surmounts it, a form of "pick" capable of passing partly into the opening 21 of the core 20 of the ring sector 6a so as to be in direct contact with the internal wall of the casing 1.
  • the parties lateral of the sole 18b can therefore slide on these support pieces 19a and 19b thus creating a circumferential clearance of the ring segment 6a relative to the casing 1.
  • this sole 18b is a double-bearing nut.
  • the support pieces 19a and 19b form an angle of approximately 45 ° relative to the downstream wing 8 so as to ensure better sliding of the sole 18b.
  • This part B of FIG. 4 also shows a sealing plate 25 which can be introduced into grooves (or slots) machined around the recesses 13 of the downstream wing 8.
  • These grooves, referenced 26, are shown in dotted lines in the figure because they are produced on the external face of the downstream wing 8.
  • the sealing plate 25 has returns (in dotted lines) capable of being introduced into the grooves 26 to ensure the positioning and fitting of said plates 25 in the downstream wing 8.
  • the positioning of such sealing plates in front of the recesses 13 in the downstream wing 8 of the ring sector 6a is intended to prevent possible reintroductions of downstream gases upstream of the ring.
  • the sealing of the downstream wing of each ring sector is carried out by means of an annular seal 38 bearing on the downstream part of the dovetail assembly.
  • FIG 5 there is shown the clamping means in axial section.
  • these clamping means comprise a screw 15 inserted in the downstream wing 8 of the ring 6 and passing through said ring right through.
  • This screw 15 is fixed in a nut 14 bearing on the external face of the upstream wing 7.
  • FIG 6 there is shown a fixed point in axial section.
  • This fixed point 10 consists of a screw / nut system introduced into the casing 1 and into the ring 6 to secure them. More precisely, this screw / nut system comprises a screw 16a introduced into the casing 1 and into the core 20 of the ring 6 by a breakthrough. A nut 16b introduced into the ring 6 through one of the recesses 12 of the upstream wing 7 secures the screw 16a. The screw 16a thus fixed in the nut 16b secures the ring 6 by its core 20 against the internal wall of the casing 1.
  • the nut 16b is of the tab nut type, the tabs of which are fixed to the ring 6 by the rivets referenced 17a and 17b in FIG. 4.
  • the screw 16a is introduced into the casing 1 and the ring 6 with a longitudinal inclination, the nut 16b having a shape adapted to receive the screw 16a thus inclined while having a solid support against the internal face of the core 20 of the ring 6.
  • the means for hooking the ferrule 2 with the ring 6 consist of a mortise 30b produced in each ferrule element 2 and a tenon 30a produced by the inner ends of the downstream 8 and upstream 7 wings of the ring sectors.
  • the connection without play of each ring sector with the housing 1 is achieved by means of a domed screw 32 inserted radially in the housing 1 and in the ring. This screw is introduced into a nut 34 of conical shape, the base of which, directed towards the ferrule, is in contact with the internal faces of the upstream and downstream wings.
  • a lunule 36 is machined on the external face of each ferrule element.
  • a conical nut 34 is positioned astride two sectors, thus allowing the sectors to slide relative to the rings as a function of thermal variations.
  • This sliding support 11 consists of a screw / nut system in which the nut can move on support parts. More precisely, this screw / nut system comprises a screw 18a inserted in the casing 1 and in the projection of the sole 18b.
  • This sole consists of a base and the projection located in the middle of the base. An opening 21 is made in the core 20 of the ring 6, large enough to allow the passage of the projection of the sole 18b which can thus be in contact with the internal wall of the casing 1.
  • a nut 18c secures the screw 18a in the sole 18b.
  • the base of the sole 18b is supported on two support pieces, of which only the support piece 19a is visible in this figure 8.
  • the projection of the sole 18b passing through the opening 21 of the core 20 and the base of said sole 18b being able to slide on the support pieces, a circumferential clearance of the ring 6 relative to the casing 1 is then possible.
  • Such sliding supports 11 thus allow the movement of the ring 6 and therefore of the shell 2 as a function of thermal variations.
  • the support piece 19a, as well as all the support pieces in the ring 6, are held integral with the ring by the clamping means 14, 15 which pass through the said pieces. supporting parts at their outer ends.
  • FIG. 9 represents a perspective view of the support pieces and of the sole of a sliding support. We therefore see, in this figure 9, the support pieces 19a and 19b having a wall, inclined at 45 ° relative to the radial direction, on which slides the base 18b 'of the sole 18b.
  • Figure 10 shows a perspective view of the joint between two ring sectors 6a and 6b. This joint is made in the middle of an opening 21 machined partly in the core 20 of the ring sector 6a and partly in the core 20 of the ring sector 6b.
  • downstream wing 8 of the ring sector 6b has an extension tab 22b machined in said downstream wing 8; the downstream wing 8 of the ring sector 6a has an extension tab 22a symmetrical to the tab 22b; the legs 22a and 22b being complementary so as to fit into each other.
  • FIGS. 11 to 14 means for controlling the clearances between the stator and the rotor are shown in accordance with a second embodiment of the invention.
  • the means for controlling games in accordance with this second embodiment being mounted on a casing which is substantially identical to that on which the means for controlling the first embodiment are mounted, it was not considered necessary to append another view. of the high pressure compressor. Reference is therefore made to FIG. 1 for the general description of the casing 1 and of the shell elements 2 of the compressor.
  • FIG. 11 therefore shows a partial view of this casing 1 and of the shell 2 made integral by a fixed point and sliding supports. More specifically, this FIG. 11 shows a portion of casing 1 and a ferrule element 2d attached to its two neighboring ferrule elements 2e and 2f.
  • This figure 11 shows, in addition, the means for controlling the clearances between the rotor and the stator.
  • These means consist of a combination of a fixed point 10d and sliding supports 11e and 11f making it possible to make each ferrule element 2d, 2e or 2f integral with the casing 1 while providing it with circumferential flexibility.
  • the ferrule element 2d like all of the compressor ferrule elements is therefore fixed, in its center, to the casing 1 by a fixed point 10d constituted, as for the fixed point in FIG. 6, of a screw system / nut. More specifically, this screw / nut system comprises a screw 16d introduced into the casing 1 by a breakthrough. A nut 16e introduced between the ferrule element 2d and the casing 1 and fixed on said ferrule element 2d ensures the fixing of the screw 16d. The screw 16d thus fixed in the nut 16e ensures a fastening without play of the ferrule element 2d against the internal wall of the casing 1.
  • the nut 16e is of the tab nut type, the tabs of which are fixed to the ferrule element 2d by the rivets.
  • the sliding supports 11f and 11e are located symmetrically with respect to the fixed point 10d. They are above all located each at the junction of two shell elements. This embodiment has the advantage of ensuring that the ferrule 2 is circumferentially flexible relative to the casing 1 obtained by using the clearances between the different ferrule elements 2.
  • the sliding support 11f comprises two screws 40a and 40b introduced into the casing 1 by two separate holes and coming to be fixed in a double floating nut 42.
  • This floating nut 42 comprises a sole 42a having two threaded holes in which the two screws 40a and 40b are screwed.
  • This sole 42a is provided with two lateral sliding tabs 42b and 42c each supported by a respective support piece 44b and 44c.
  • This figure also shows the support parts 44b and 44c each comprising a notch 44a supporting the sliding tabs 42b and 42c.
  • Each of these support pieces is integral with one of the shell elements. They can be attached to it, for example, by stirring.
  • these sliding tabs 42b and 42c have a slightly curved shape at their free end so as to prevent them from dislodging from the notches 44a.
  • the screws of the fixed points, as well as the screws of the supports sliders are positioned at an angle of about 45 ° to the surface of the housing 1.
  • this support 46 is a V in brazed sheet metal on the ferrule element 2f.
  • This support 46 is used for mounting the sliding support.
  • a tool screw 45 is introduced into the hole 42e, that is to say a headless screw shorter than the final screw 40b.
  • This tool screw 45 is therefore introduced into the hole 42e until it is in abutment against the support 46 so as to keep the floating nut 42 fixed relative to the ferrule element.
  • This screw 45 is then embedded in the sole 42a, which makes it possible to position the casing 1 around the shell without being hindered by the presence of the screw heads such as those of the screws 40a and 40b.
  • the screw 40a is introduced into the second hole 42d of the sole 42a to maintain the casing in the chosen position.
  • the tool screw 45 can then be removed and replaced by the final screw 40b.
  • FIG. 14 a second embodiment of the sliding support 11f has been shown, in which the sole 42a is held in a fixed position relative to to the ferrule element 2f by means of a clip 47.
  • This clip 47 is fixed by its end 47 ′ to the radial wall 2f ′ of the ferrule element and partially surrounds the sole 42a so as to keep it fixedly against this wall 2f '.
  • the second technique for mounting the sliding support remains identical to the first technique shown in FIG. 13 and described previously. It will therefore not be described again.
  • the second embodiment of the invention as just described provides circumferential flexibility to the shell by sliding of the shell elements relative to the casing 1 thanks to the sliding supports.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP94402400A 1993-10-27 1994-10-26 Turbomaschine mit Einrichtungnen um das Schaufelspitzenspiel zwischen Rotor und Stator zu Regeln Expired - Lifetime EP0651139B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9312798 1993-10-27
FR9312798A FR2711730B1 (fr) 1993-10-27 1993-10-27 Turbomachine équipée de moyens de pilotage des jeux entre rotor et stator.

Publications (2)

Publication Number Publication Date
EP0651139A1 true EP0651139A1 (de) 1995-05-03
EP0651139B1 EP0651139B1 (de) 1999-01-07

Family

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EP94402400A Expired - Lifetime EP0651139B1 (de) 1993-10-27 1994-10-26 Turbomaschine mit Einrichtungnen um das Schaufelspitzenspiel zwischen Rotor und Stator zu Regeln

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Country Link
US (1) US5616003A (de)
EP (1) EP0651139B1 (de)
DE (1) DE69415765T2 (de)
FR (1) FR2711730B1 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1288444A1 (de) * 2001-08-30 2003-03-05 Snecma Moteurs Befestigung von Statorelementen in einem Turbomaschinengehäuse
EP1944474A3 (de) * 2007-01-03 2009-03-25 United Technologies Corporation Mantelringdichtung einer Gasturbine und entsprechendes Gasturbinentriebwerk

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Publication number Priority date Publication date Assignee Title
DE19938274A1 (de) * 1999-08-12 2001-02-15 Asea Brown Boveri Vorrichtung und Verfahren zur geziehlten Spalteinstellung zwischen Stator- und Rotoranordnung einer Strömungsmaschine
FR2817285B1 (fr) 2000-11-30 2003-06-13 Snecma Moteurs Virole interne de stator
FR2875535B1 (fr) * 2004-09-21 2009-10-30 Snecma Moteurs Sa Module de turbine pour moteur a turbine a gaz
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
ES2705532T3 (es) 2012-10-30 2019-03-25 MTU Aero Engines AG Anillo de turbina y turbomáquina
EP2789804A1 (de) * 2013-04-11 2014-10-15 Alstom Technology Ltd Thermische Hülle für Gasturbine mit verbesserter Haltbarkeit
US20180149030A1 (en) * 2016-11-30 2018-05-31 Rolls-Royce Corporation Turbine shroud with hanger attachment

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FR2482662A1 (fr) * 1980-05-16 1981-11-20 Mtu Muenchen Gmbh Carter exterieur pour compresseur axial ou turbine axiale d'une machine fluidique
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GB2115487A (en) * 1982-02-19 1983-09-07 Gen Electric Double wall compressor casing
US4728257A (en) * 1986-06-18 1988-03-01 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Thermal stress minimized, two component, turbine shroud seal
FR2683851A1 (fr) * 1991-11-20 1993-05-21 Snecma Turbomachine equipee de moyens facilitant le reglage des jeux du stator entree stator et rotor.

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GB137933A (en) * 1919-02-14 1920-01-29 Thomas Macready Down Improvements in and relating to cartridges for sporting and other firearms
DE936900C (de) * 1954-07-16 1955-12-22 Siemens Ag Anordnung zur Befestigung von keramischen Leitschaufeln
GB800098A (en) * 1955-10-31 1958-08-20 Rolls Royce Improvements in or relating to multi-stage axial-flow compressors
FR2695164B1 (fr) * 1992-08-26 1994-11-04 Snecma Turbomachine munie d'un dispositif empêchant une circulation longitudinale de gaz autour des étages d'aubes de redressement.
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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR975879A (fr) * 1948-12-06 1951-03-12 Const Et D Equipements Mecaniq Perfectionnement dans la construction des cylindres pour turbines à gaz
FR1301686A (fr) * 1960-09-28 1962-08-17 Licentia Gmbh Turbine à gaz ou à vapeur du type axial à plusieurs étages
FR1339482A (fr) * 1961-11-28 1963-10-04 Licentia Gmbh Joint de rotor à segments annulaires d'étanchéité radialement mobiles, notammentpour turbo-moteurs
US4131388A (en) * 1977-05-26 1978-12-26 United Technologies Corporation Outer air seal
FR2444801A1 (fr) * 1978-12-20 1980-07-18 United Technologies Corp Structure de support pour le moyen d'etancheite entourant les ailettes du rotor d'un moteur a turbine a gaz
FR2482661A1 (fr) * 1980-05-16 1981-11-20 United Technologies Corp Assemblage directeur d'ecoulement pour une turbine a gaz
FR2482662A1 (fr) * 1980-05-16 1981-11-20 Mtu Muenchen Gmbh Carter exterieur pour compresseur axial ou turbine axiale d'une machine fluidique
FR2516980A1 (fr) * 1981-11-26 1983-05-27 Rolls Royce Carters pour rotors de turbomachines
GB2115487A (en) * 1982-02-19 1983-09-07 Gen Electric Double wall compressor casing
US4728257A (en) * 1986-06-18 1988-03-01 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Thermal stress minimized, two component, turbine shroud seal
FR2683851A1 (fr) * 1991-11-20 1993-05-21 Snecma Turbomachine equipee de moyens facilitant le reglage des jeux du stator entree stator et rotor.

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1288444A1 (de) * 2001-08-30 2003-03-05 Snecma Moteurs Befestigung von Statorelementen in einem Turbomaschinengehäuse
WO2003018962A1 (fr) * 2001-08-30 2003-03-06 Snecma Moteurs Carter de stator de turbomachine
FR2829176A1 (fr) * 2001-08-30 2003-03-07 Snecma Moteurs Carter de stator de turbomachine
US7070387B2 (en) 2001-08-30 2006-07-04 Snecma Moteurs Gas turbine stator housing
EP1944474A3 (de) * 2007-01-03 2009-03-25 United Technologies Corporation Mantelringdichtung einer Gasturbine und entsprechendes Gasturbinentriebwerk
US9039358B2 (en) 2007-01-03 2015-05-26 United Technologies Corporation Replaceable blade outer air seal design

Also Published As

Publication number Publication date
EP0651139B1 (de) 1999-01-07
FR2711730B1 (fr) 1995-12-01
DE69415765D1 (de) 1999-02-18
DE69415765T2 (de) 1999-07-29
FR2711730A1 (fr) 1995-05-05
US5616003A (en) 1997-04-01

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