EP4060165A1 - Gehäuse für kompressor eines turbotriebwerks - Google Patents

Gehäuse für kompressor eines turbotriebwerks Download PDF

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Publication number
EP4060165A1
EP4060165A1 EP22159615.8A EP22159615A EP4060165A1 EP 4060165 A1 EP4060165 A1 EP 4060165A1 EP 22159615 A EP22159615 A EP 22159615A EP 4060165 A1 EP4060165 A1 EP 4060165A1
Authority
EP
European Patent Office
Prior art keywords
ring
platforms
housing
casing
platform
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.)
Pending
Application number
EP22159615.8A
Other languages
English (en)
French (fr)
Inventor
Théo Robin Thomas BOUR
Mathieu Renaud
Sébastien José François Ghislain VACCA
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 Aero Boosters SA
Original Assignee
Safran Aero Boosters 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 Safran Aero Boosters SA filed Critical Safran Aero Boosters SA
Publication of EP4060165A1 publication Critical patent/EP4060165A1/de
Pending 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
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • F04D29/526—Details of the casing section radially opposing blade tips
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/64—Mounting; Assembling; Disassembling of axial pumps
    • F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking

Definitions

  • the invention relates to the design of a turbomachine, in particular an aircraft turbojet or an aircraft turboprop.
  • the invention relates in particular to the casing of a high-speed compressor.
  • the air flow is compressed by alternating rotor blades and stator blades.
  • the stator vanes extend radially inwards from an outer shroud which delimits the passageway of the air flow.
  • the document EP 1 426 559 A1 describes an example of compressor architecture of such a turbomachine.
  • the shroud which holds the stator vanes has flanges upstream and downstream in order to fix it to the upstream casing and to the downstream inter-compressor casing.
  • the shroud forms on the one hand a vector transmitting the axial forces and the torque between the various casings to which it is fixed, and on the other hand it supports the forces undergone by the stator vanes inside the compressor.
  • These two sources of forces generate zones of stress concentration in particular at the level of the anchoring of the blades in the shroud.
  • the usual response to ensure the mechanical strength in these stress zones is to provide additional thicknesses or reinforcement parts and therefore additional weight.
  • the object of the invention is to overcome the drawbacks set out above and in particular to propose a compressor and a lighter/lighter turbomachine without compromising their mechanical strength.
  • the subject of the invention is a compressor casing for an aircraft turbojet equipped with a fan driven by a reduction gear, the casing comprising: an outer shroud made of composite material and possibly formed of several angular shroud segments; and an annular row of platforms fixed to the shroud, each platform supporting one or more stator vane(s); the casing being remarkable in that it comprises a ring, optionally formed of several angular ring segments, and having a layer of abradable material, the ring resting radially on bearing surfaces of the platforms so that no axial force can be transmitted between the ring and the platforms.
  • the ferrule may be one-piece annular, in particular having a taper compatible with the assembly of the various elements to be attached to it.
  • the ferrule can be made up of two half-shells.
  • the composite material can be optimized with denser plies in areas subject to greater mechanical stress.
  • the composite material can be of the unidirectional thermosetting or thermoplastic prepreg type deposited by placement of automatic fibers (“automated fiber placement”, AFP) and consolidated in an autoclave or in a closed mold or alternatively 2D or 3D interlock fabrics consolidated by compression molding -resin transfer (“Resin transfer molding”, RTM).
  • the platforms and the blades can form angular blade sectors with several blades.
  • the layer of abradable material is intended to come face to face with the rotor blade tips of a rotor.
  • the design of the contact interface between the platforms and the ring makes it possible to avoid transmission of an axial force and thus avoids the concentration of stresses at the periphery of the platforms.
  • the platforms of the blades can be welded together or welded to the shell and to the rings.
  • the weld beads generate mechanically heterogeneous zones with a higher stress concentration coefficient (Kt).
  • Kt stress concentration coefficient
  • additional thicknesses or reinforcements are therefore usually provided. welds then lead to the double disadvantage of a surface that is not completely controlled geometrically for guiding the flow of air and of excess weight due to the reinforcement of the structure.
  • the drawbacks associated with the presence of weld beads disappear.
  • this function can be achieved by different designs, in particular rounded, wavy surfaces, having an "S" profile, or being chamfered, or by the interposition of a flexible joint, for example made of silicone .
  • the invention also relates to a platform for fixing one or more stator vane(s) to a turbomachine compressor casing, the platform comprising a housing capable of receiving a fixing element intended for its fixing to a composite shroud, and an upstream bearing surface and/or on a downstream bearing surface, provided with a surface capable of coming into contact with a ring so that no axial force can be transmitted between the ring and the platform.
  • This design has the advantage of “pooling” the fastening elements of the different platforms and therefore of reducing the weight of a turbomachine.
  • the platform comprises two opposite circumferential ends each having a housing portion, such that when two adjacent platforms provided with such housing portions are abutted, the housing portions together form a housing intended to receive a fastening element of the platforms to the shell.
  • the platform comprises a lug arranged on at least the upstream bearing surface and/or the downstream bearing surface, intended to serve as a circumferential stop for a ring.
  • the platform comprises several upstream spans and/or several downstream spans, including one or more external spans and one or more internal spans, preferably arranged in staggered rows seen axially.
  • the invention also relates to a turbomachine comprising a fan driven by a reduction gear, a low-pressure compressor, a high-pressure compressor and an intermediate casing, arranged between the low-pressure compressor and the high-pressure compressor, the turbomachine being remarkable in that the low-pressure compressor has a casing according to one of the embodiments described above.
  • the shroud comprises an upstream flange and a downstream flange, respectively to fix it - directly or not - to an upstream casing and to the intermediate casing, the casing comprising an upstream flange and a downstream flange, fixed to the flanges respective and ensuring continuity of the airflow guiding surface with an upstream ring and a downstream platform.
  • the invention finally relates to a method for assembling a casing according to one of the embodiments set out above or of a turbomachine according to one of the embodiments set out above, the method comprising a step of placing compressor stages in the shroud, optionally by stacking alternately an annular row of platforms and a ring.
  • the method comprises a step of assembling platforms to a first shell half-shell, a step of positioning bladed discs axially between two neighboring annular rows of platforms, a step of assembling platforms to a second half ferrule shell, and finally a step of assembling the second half-shell to the first half-shell.
  • the shell made of composite material and the absence of welding and above all of the reinforcements that it requires saves weight.
  • the rings preferably metallic, can allow passive control by thermal expansion of the clearance between the blade heads and the abradable.
  • An abradable is more easily deposited (or redeposited during maintenance) on these rings.
  • These rings also give rise to a limitation of the carcass deformations of the booster under the thrust of the engine.
  • Another advantage of providing different parts is that it is possible to replace only one of the parts involved in the event of a manufacturing or usage failure rather than scrapping the entire housing.
  • the fact of providing the layer of abradable material on a ring facilitates its deposition in comparison with a deposition of abradable material on a ferrule, which is more restrictive and more cumbersome to handle.
  • the design in two half-shells allows the mounting of a rotor composed of a bladed drum (“blum”) and a one-piece annular shroud can receive one-piece moving wheels (blisks) assembled in a non-permanent manner.
  • the terms “internal” (or “inner”) and “external” (or “outer”) refer to a radial positioning with respect to the axis of rotation of a turbomachine.
  • the axial direction corresponds to the direction along the axis of rotation of the turbomachine.
  • the radial direction is perpendicular to the axis of rotation. Upstream and downstream refer to the main flow direction of the stream in the turbomachine.
  • integral is understood as integral in rotation, and in particular rigidly linked.
  • the term “one-piece” is equivalent to "made from material” and designates different elements made from the same block of material, as opposed to "attached” which means that an element is attached, after its manufacture, to another element.
  • the figures represent the elements schematically, in particular without all of the assembly or sealing elements. Certain dimensions, and in particular the radial thickness of the various parts, are exaggerated in order to facilitate understanding of the figures.
  • the figure 1 schematically represents a turbomachine 2 which comprises a low-pressure compressor 4 and a high-pressure compressor 6, a combustion chamber 8 and two turbines 10.
  • the mechanical power of the turbines 10 sets in motion the two compressors 4 and 6 by means of respective shafts 12, 13.
  • the compressors 4, 6 comprise several rows of rotor blades (or rotor blades) associated with rows of stator blades (or stator blades).
  • the rotation of the rotor 15 around its axis of rotation 14 thus makes it possible to generate an air flow and to gradually compress the latter until it enters the combustion chamber 8.
  • a fan 16 is coupled to the shaft 12 and generates an air flow which is divided into a primary flow 18 and a secondary flow 20 passing through an annular duct (partially shown) along the machine to then join the primary flow at the turbine outlet.
  • Reduction means such as a reducer 17, for example epicyclic, can reduce the speed of rotation of the fan 16 with respect to the associated turbine.
  • An upstream casing 22 provided with support arms (or “struts”) holds the reducer 17 and supports the upstream part of the turbomachine.
  • a compressor casing 24 supports the compressor 4.
  • An inter-compressor casing 5 comprising support arms is arranged between the low-pressure compressor 4 and the high-pressure compressor 6.
  • the various casings are required to support heavy loads.
  • the fan tends to pull the whole plane forward.
  • the casings are mechanical parts which must therefore each support at least part of the thrust generated by the fan.
  • the outer shroud participates in the rigidity of the structure and undergoes a part of these efforts, materialized schematically by the deflection noted F on the figure 1 . Points of stress concentration are also illustrated, in particular in line with the downstream structural arms. By attaching the blades directly to the shroud, these also undergo part of the mechanical stresses of the shroud.
  • the idea of the invention as described below is to dissociate the blades from the efforts of the shroud and thus separate the functions of guiding the flow, attaching the abradable, integrating the casing treatment thereof. .
  • the picture 2 is a sectional view of the compressor 4 in a known turbomachine. A part of the fan 16 can be observed there as well as the nozzle 28 separating the primary 18 and secondary 20 flows.
  • the rotor 15 can comprise several rows of rotor blades 30.
  • the low-pressure compressor 4 comprises at least one straightener which contains an annular row of stator vanes 32 whose purpose is to straighten the flow of air deflected by the rotating vanes.
  • the low-pressure compressor 4 comprises a casing 34.
  • the casing 34 has a generally axisymmetric shape that can incorporate reinforcements, splines or stiffening ribs.
  • the casing 34 comprises a shroud 35 whose axial ends have fixing flanges 36, for example annular fixing flanges 36 for fixing the separation nose 28 and/or for fixing to an intermediate casing 5 of the turbine engine.
  • the stator vanes 32 extend essentially radially from the casing 34 as far as internal shrouds 38.
  • One of the rows of stator vanes 32 can be of variable orientation around its axis 40.
  • the stator vanes 32 are fixed to the casing 34 at the means of platforms 42.
  • a layer of abradable material 44 is generally provided opposite the rotor blades 30.
  • the anchoring zones of the stator blades - the housings (counterbore, "bathtubs") accommodating the platforms 42 - form zones of stress concentrations because they concentrate both the forces collected by the stator vanes induced by the straightening of the air flow 18 and the forces transmitted from the fan 16 or the reducer 17. These zones are therefore generally reinforced with excess thicknesses of material. To that add the weld beads of the platforms 42 to the shell 35. All this has a significant weight.
  • the picture 3 describes a housing 34 according to the invention.
  • the shroud 35 is of generally tubular shape and can be made up of several angular sections such as for example two half-shells, joined in a plane comprising the axis 14.
  • the shroud comprises two flanges 36 for its attachment to an upstream casing (22 on the figure 1 and partially represented on the picture 3 ), and an intermediate casing (5 on the picture 2 ).
  • the ferrule 35 has an outer surface 35.1 and an inner surface 35.2.
  • the stator vanes 32 extend radially inward from the shroud 35.
  • the vanes 32 are fixed to the shroud 35 by means of platforms 42.
  • the platforms 42 can be integral with the vanes 32.
  • the platforms 42 are fixed to the ferrule 35 with means which are described below extending along the axis A.
  • the rotor blades 30 are partially shown. They can come opposite a layer of abradable material 44. The latter is carried by a ring 46.
  • the inner ends of the blades 32 are supported by an inner shroud 38 under which can be attached a layer of abradable material 48 which can cooperate with wipers of a rotor (15 on the figure 2 ).
  • the picture 3 illustrates three compression stages, each formed of a pair of rows of rotor 30 and stator 32 blades. It should be noted that the invention is not limited to this number of compression stages.
  • Flanges 50, 52 can ensure the continuity of the air stream upstream and downstream of these three stages.
  • An enlarged portion of the picture 3 shows in detail the contact between a ring 46 and a platform 42.
  • the platform 42 comprises an outer surface 42.1 which is in contact with the ferrule 35. Sealing can be achieved there by means of a seal such as by example the one illustrated in the document WO 2019/105610 A1 .
  • the internal surface 42.2 of the platform is an air guiding surface.
  • the ring 46 for its part comprises an outer surface 46.1 which can be supported on the ferrule 35 and an inner surface 46.2 which defines an inner groove receiving the layer of abradable material 44.
  • a surface 42.3, 46.3 having an "S" profile provided on the platform 42 as well as on the ring 46 ensures the line contact between the platform 42 and the ring 46.
  • the surface 42.3 is provided on a or several spans 42.4 of the platform 42.
  • the surface 46.3 is provided on a lip 46.4 of the ring 46.
  • the point of contact between the outer surface 46.1 of the ring 46 and the inner surface 35.2 of the ferrule 35 can move, the ring 46 being mounted floating in the ferrule 35.
  • the design of the various surfaces (profiles and clearances ) is suitably chosen to allow expansion of the ring even under the maximum temperature conditions generally admissible in operation.
  • the ring 46 finally has an external groove 46.5 allowing its free deformation without stresses of contact with the ferrule 35.
  • This groove 46.5 also forms a plenum which can be used to integrate a casing treatment.
  • the figure 4 shows a first example of a platform 42, with, at the top an isometric view, in the middle a front view (seen circumferentially) and at the bottom a top view (seen radially).
  • the platform 42 comprises an outer surface 42.1 substantially matching the inner surface 35.2 of the shroud 35, and an inner surface 42.2 from which the blade 32 extends.
  • the platform 42 can be made in one piece with the blade 32.
  • the platform comprises a single bearing surface 42.4 on each axial side, presenting a contact surface 42.3 with the rings 46.
  • the bearing surface is radially on the inside of the platform 42.
  • the ring is thus “stuck” radially between the ferrule and the platform, which makes any means of assembling the ring to the platforms or to the ferrule optional.
  • the span 42.4 is here presented as extending circumferentially over the entirety of the platform 42, alternatively, the span 42.4 can be only on a part of the platform and can therefore present circumferential stop surfaces with the ring (see figure 5 ).
  • a lug 42.4' can be arranged on one and/or the other of the surfaces 42.4, so as to cooperate with a notch of a ring and thus limit or even prevent the circumferential movement of the ring.
  • the ring 46 and its notch 46.6 are partially shown in dotted lines.
  • the platform has two faces at its circumferential ends 42.5, 42.6 which can be partially or completely curved.
  • the continuity of the surface for guiding the air flow is ensured by the continuity of the surfaces of the platforms arranged end-to-end.
  • a housing 42.10 that can receive a lock (or screw) is arranged on the outer face 42.1. It is in this example made of two parts 42.7, 42.8 each at one of the ends 42.5, 42.6 of the platform. These two parts can be substantially cylindrical. One of the parts, preferably on the convex side 42.5, comprises an outer portion with a flat 42.9 which forms a radial stop for the lock. Alternatively, the radial stop can be a cover, attached to the outer face 42.1. By assembling the platforms against each other, the parts 42.7, 42.8 form a substantially cylindrical housing 42.10.
  • Additional housings can also be provided on the platform to receive additional assembly elements.
  • platform 42 may remain as cast.
  • the figure 5 shows a variant for the geometry of the platform 42.
  • several spans 42.4 are arranged on each side of the platform 42.
  • the number of spans 42.4 can be different between one side and the other. Their positions too. In this example, they are arranged in staggered rows, which can facilitate the positioning of the platforms 42 on the ring 46 or vice versa.
  • Two circumferentially adjacent platforms 42 can be identical or different.
  • the surface denoted 42.3' can serve as a circumferential stop for the ring 46, having corresponding indentations to fit into the bearing surfaces 42.4 of the platform 42.
  • the variant of the figure 5 is therefore certainly a platform 42 that is more complex to manufacture, but it can have advantages on the indexing in position of the ring 46.
  • the figure 6 shows two examples of a fastening element 54 whose head 54.1 can penetrate into the housing and the rod 54.2, possibly threaded, can extend through and beyond the ferrule 35.
  • the example on the left shows a screw 54.
  • the head 54.1 is inserted into a half-housing of a platform 42 then an adjacent platform encloses the head 54.1 under the flat 42.9.
  • a nut is then screwed onto the threaded rod 54.2 from the outside.
  • This technique can be repeated for each platform, on two ferrule half-shells 35 (180°), then the half-shells are assembled to one another.
  • the ferrule is annular in one piece, all the platforms of the same annular row are assembled to the ferrule before a ring is stacked on the platforms.
  • the example on the right shows a lock 54.
  • This comprises a head 54.1 which is a radial protrusion of the rod 54.2.
  • the assembly is identical to that carried out with the screw.
  • the lock has a lower weight than the screw although it requires precise angular positioning around the axis A so that the head 54.1 remains well in the housing.
  • the number of compression stages can be adapted to requirements and thus be 1, 2, 3 or 4, or even more.
  • One of the stages may include a row of blades with variable pitch.
  • this row of variable-pitch vanes can come upstream of the casing 34 ( picture 3 of the document WO 2019/105610 A1 ).
  • the invention is not limited thereto.
  • the ring When the ring is formed of several angular segments, these may be in floating contact with each other circumferentially, or be assembled by snap-fastening (tenon/mortise, dovetail, etc.).
  • the assembly of platforms can also be applied to ring segments. This technique can come in addition or as an alternative to the seats and lugs on the platforms now circumferentially and radially the (segments of) rings.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP22159615.8A 2021-03-03 2022-03-02 Gehäuse für kompressor eines turbotriebwerks Pending EP4060165A1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
BE20215154A BE1029166B1 (fr) 2021-03-03 2021-03-03 Carter pour compresseur de turbomachine

Publications (1)

Publication Number Publication Date
EP4060165A1 true EP4060165A1 (de) 2022-09-21

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ID=74859659

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Application Number Title Priority Date Filing Date
EP22159615.8A Pending EP4060165A1 (de) 2021-03-03 2022-03-02 Gehäuse für kompressor eines turbotriebwerks

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EP (1) EP4060165A1 (de)
BE (1) BE1029166B1 (de)

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2994508A (en) 1958-03-04 1961-08-01 Curtiss Wright Corp Lightweight compressor housing construction
US4522559A (en) * 1982-02-19 1985-06-11 General Electric Company Compressor casing
EP1426559A1 (de) 2002-12-03 2004-06-09 Techspace Aero S.A. Innerer Mantelring eines axialen Kompressors
US20100077612A1 (en) * 2008-09-30 2010-04-01 Courtney James Tudor Method of manufacturing a fairing with an integrated seal
EP2202385A1 (de) 2008-12-24 2010-06-30 Techspace Aero S.A. Bearbeitung des Kompressorgehäuses eines Turbotriebwerks, die in der Anlegung einer Ringnut besteht, die eine Wellenbewegung beschreibt, um die Wirbel am Leitschaufelkopf zu kontrollieren
EP2896796A1 (de) * 2014-01-20 2015-07-22 Techspace Aero S.A. Stator einer axialen Strömungsmaschine und zugehörige Strömungsmaschine
WO2019105610A1 (fr) 2017-11-30 2019-06-06 Safran Aero Boosters Sa Ensemble pour turbomachine axiale, turbomachine axiale, procédé d'assemblage et joint d'étanchéité associés
US10577963B2 (en) * 2014-01-20 2020-03-03 United Technologies Corporation Retention clip for a blade outer air seal

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2994508A (en) 1958-03-04 1961-08-01 Curtiss Wright Corp Lightweight compressor housing construction
US4522559A (en) * 1982-02-19 1985-06-11 General Electric Company Compressor casing
EP1426559A1 (de) 2002-12-03 2004-06-09 Techspace Aero S.A. Innerer Mantelring eines axialen Kompressors
US20100077612A1 (en) * 2008-09-30 2010-04-01 Courtney James Tudor Method of manufacturing a fairing with an integrated seal
EP2202385A1 (de) 2008-12-24 2010-06-30 Techspace Aero S.A. Bearbeitung des Kompressorgehäuses eines Turbotriebwerks, die in der Anlegung einer Ringnut besteht, die eine Wellenbewegung beschreibt, um die Wirbel am Leitschaufelkopf zu kontrollieren
EP2896796A1 (de) * 2014-01-20 2015-07-22 Techspace Aero S.A. Stator einer axialen Strömungsmaschine und zugehörige Strömungsmaschine
US10577963B2 (en) * 2014-01-20 2020-03-03 United Technologies Corporation Retention clip for a blade outer air seal
WO2019105610A1 (fr) 2017-11-30 2019-06-06 Safran Aero Boosters Sa Ensemble pour turbomachine axiale, turbomachine axiale, procédé d'assemblage et joint d'étanchéité associés

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BE1029166B1 (fr) 2022-10-03
BE1029166A1 (fr) 2022-09-27

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