EP2808556B1 - Ensemble structurel pour une turbomachine - Google Patents

Ensemble structurel pour une turbomachine Download PDF

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Publication number
EP2808556B1
EP2808556B1 EP14170055.9A EP14170055A EP2808556B1 EP 2808556 B1 EP2808556 B1 EP 2808556B1 EP 14170055 A EP14170055 A EP 14170055A EP 2808556 B1 EP2808556 B1 EP 2808556B1
Authority
EP
European Patent Office
Prior art keywords
fluid
flow path
secondary flow
main flow
duct
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.)
Active
Application number
EP14170055.9A
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German (de)
English (en)
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EP2808556A1 (fr
Inventor
Volker Dr. Gümmer
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.)
Rolls Royce Deutschland Ltd and Co KG
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Rolls Royce Deutschland Ltd and Co KG
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Publication date
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Publication of EP2808556A1 publication Critical patent/EP2808556A1/fr
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Classifications

    • 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
    • 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/685—Inducing localised fluid recirculation in the stator-rotor interface
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F04D27/0215—Arrangements therefor, e.g. bleed or by-pass valves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F04D27/0238—Details or means for fluid reinjection

Definitions

  • the invention relates to a turbomachine with a structural assembly according to the preamble of patent claim 1.
  • turbomachines in particular of fluid flow machines such as fans, compressors, pumps and fans, is limited by the growth and separation of boundary layers in the rotor and stator tip region near the housing or hub wall. In the case of blade rows with a running gap, this leads to high secondary losses and possibly to the occurrence of operational instabilities at higher loads.
  • casing treatments As a countermeasure, it is known to use so-called casing treatments.
  • the simplest form of casing treatments are circumferential grooves of rectangular or parallelogram cross-section, such as in EP 0 754 864 A1 revealed and in the Fig. 1a outlined as an example.
  • Other solutions provide for rows of slots or openings in the housing, the individual slots / openings being oriented substantially in the flow direction and having a slender shape with a small extension viewed in the circumferential direction of the machine.
  • Such solutions are for example in the DE 101 35 003 C1 revealed and in the Fig. 1b outlined as an example.
  • a fluid flow machine which forms at least one secondary flow channel in the area of the blade leading edge in a main flow path boundary, which connects two openings arranged on the main flow path boundary.
  • Each secondary flow channel in each case connects a removal opening with a supply opening provided further upstream.
  • the EP 1 659 293 A2 discloses a structural assembly for a turbomachine having the features of the preamble of claim 1.
  • a support member and a connecting member together form a secondary flow passage.
  • a compressor wheel associated with a bypass is provided, which has two radial grooves and an annular chamber connecting them.
  • the EP 2 639 411 A1 relates to a housing for a turbomachine with an annulus channel, but which explicitly provides valve means for opening and controlling the annulus openings. It is an object of the present invention to provide a turbomachine with a structural subassembly which can efficiently provide secondary flow channels, even those of complex shape, in the region of a main flow path boundary of the turbomachine (ie in the region of the housing or the hub). Here, a spatially compact and robust structural design is to be provided. This object is achieved by a turbomachine with a structural assembly having the features of claim 1. Embodiments of the invention are specified in the subclaims.
  • the structural assembly is formed by at least two interconnected components, namely at least one support member and at least one connecting member, wherein the support member at least partially forms the Hauptströmungspfadberandung and wherein the connecting member forms at least a portion of the secondary flow channel or surrounds.
  • the latter means that the connecting component taken by itself (ie not together with other components) forms or surrounds at least a portion of the secondary flow channel.
  • the connection component completely surrounds at least one subsection of the secondary flow channel such that all wetted surfaces of the secondary flow channel in this subsection are undividedly associated with the connection component.
  • the invention thus contemplates a portion of the main flowpath of a turbomachine, in the region of a free end and a nip row of blades, in which a series of circumferentially distributed secondary flow channels are provided.
  • the course of the secondary flow channels can each be spatially complex.
  • a structural assembly is provided for structurally implementing said secondary flow channels.
  • the invention provides that each secondary flow channel is subdivided into three subsections within a meridian view: a rear subsection which coincides with an opening in the main flow path, a front portion which opens into the main flow path with an opening, and a central portion which connects the two other portions together. It can further be provided that the connection component is connected to the support component substantially on its side facing away from the main flow path.
  • the at least one secondary flow channel has an opening at each of the flow-direction-spaced ends, which opening is formed in the main flow path boundary, so that the secondary flow channel is connected to the main flow path by means of the two openings, wherein in each of the two openings EP 2 639 411 A1 - No valve means for opening and controlling the two openings is arranged.
  • the support member may be formed in embodiments of the invention as an annular housing of a turbomachine, as a half shell housing a turbomachine, an annular manner on the hub of a turbomachine, or semi-annular manner on the hub of a turbomachine.
  • the secondary flow channel is designed as a single-path channel, with a first opening, through which fluid flows into the secondary flow channel, and with a second opening, through which the fluid leaves the secondary flow channel.
  • both sections of the secondary flow channel which open into the main flow path are provided directly in the support component.
  • only a central portion of the secondary flow channel is formed in the connecting member.
  • At least one of the sections of the secondary flow channel which opens into the main flow path is introduced directly into the support component by means of a cutting process, an electrochemical process or a laser process.
  • a further variant of the invention provides that at least one of the sections of a secondary flow channel which opens into the main flow path is at least partially designed as a cylinder with an elliptical or circular cross section in the support component.
  • At least one channel section of the secondary flow channel it may be provided to form at least one connecting piece and / or a web on the side of the support component facing away from the main flow path.
  • at least one secondary flow channel section extends through a web or a neck of the support member, wherein it can further be provided that the at least one web or neck is formed on at least one separate adapter, wherein the adapter is received by the support member, for example is inserted in this.
  • a further variant of the invention provides that the connecting component surrounds a section of the secondary flow channel and connects at least to a secondary flow channel section introduced directly into the support component.
  • a connection of the connecting member to the support member is made for example by a fit, a plug, a clamp, a screw, a weld or a soldering.
  • the connecting member connects both to a first directly introduced into the support member portion and to a second directly introduced into the support member portion, wherein the connecting member forms or encloses a third portion of the secondary flow channel and the connection between the first and second subsections forms.
  • the connecting component is designed as a ring sector and accommodates at least two secondary flow channels.
  • this is the connecting component, for example, formed as a half ring or as a solid ring.
  • a connection of the connecting member to the support member by a fit, a plug, a clamp, a screw, a weld or a soldering is realized.
  • the connecting component is not executed in one piece, but consists of several sub-components, which together are connected. This can provide additional flexibility in the manufacture and assembly of the connection component.
  • the present invention relates generally to structural assemblies for turbomachinery such as turbines, and more particularly to fluid flow machines such as fans, compressors, pumps and fans, in both axial, semi-axial and radial designs.
  • the working medium or fluid may be gaseous or liquid.
  • the turbomachine may include one or more stages each having a rotor and a stator. In some cases, the stage is formed only by a rotor.
  • the rotor of a turbomachine in which a structural assembly according to the invention is used, consists of a number of blades, which are connected to the rotating shaft of the turbomachine and deliver energy to the working fluid in the case of the fluid flow machine.
  • the rotor can be designed with or without shroud on the outer blade end.
  • the stator of a turbomachine in which a structural assembly according to the invention is used, consists of a number of stationary blades, which can be designed on the hub side as the housing side with a fixed or free blade end.
  • the rotor drum and the blading are usually surrounded by a housing. In other cases, z. As in propellers or propellers, no housing exists.
  • a turbomachine in which a structural assembly according to the invention is used, can also have a stator in front of the first rotor, a so-called leading wheel. At least one stator or Vorleitrad - may be rotatably mounted - deviating from an immovable fixation - to change the angle of attack can. An adjustment is made for example by a spindle accessible from outside the annular channel.
  • a turbomachine in which a structural assembly according to the invention is used, have at least one row of adjustable rotors.
  • a turbomachine in which a structural assembly according to the invention is used, have two counterrotating shafts in multiple stages, so that the rotor blade rows change the direction of rotation from stage to stage. There are no stators between successive rotors.
  • a turbomachine in which a structural assembly according to the invention is used, have a bypass configuration such that a single-flow annular channel divides behind a certain row of blades into two concentric annular channels, which in turn each accommodate at least one additional row of blades.
  • turbomachine in which a structural assembly according to the invention is used, it is, for example, a jet engine, in particular a turbofan engine.
  • the structural assembly is formed, for example, in the region of a compressor of a jet engine or turbofan engine.
  • FIG. 3c illustrated example of a structural assembly for a turbomachine is not part of the invention, but a prior art, which facilitates the understanding of the invention.
  • the Fig. 2A shows an arrangement of a blade row 3 with free end and running gap 5 in the meridian plane formed by the axial direction x and the radial direction r.
  • the nip 5 separates the blade tip from a component 2 belonging to the main flow path at the hub or housing of the fluid flow machine.
  • the component 2 forms a main flow path boundary 4 toward the main flow path.
  • the main flow direction in the main flow path is indicated by an arrow A. Upstream and / or downstream of the row of blades 3 with running gap, further rows of blades may be located.
  • a number of secondary flow channels 1 distributed on the circumference are provided in the region of the running gap 5, each of which forms an opening at its ends (feed opening and removal opening).
  • Fig. 2A shows the outline or the projection of a single secondary flow channel 1 in the meridian plane (xr).
  • xr meridian plane
  • each channel 1 has a three-dimensional spatially twisted course, which in the Fig. 2B is shown by way of example.
  • cross-sectional shape of the secondary flow channels 1 in the Fig. 2B merely exemplified as rectangular.
  • the cross section of the secondary flow channels 1 may be formed in other embodiments without corners, in particular circular or elliptical.
  • FIG. 3A shows a structural assembly according to the invention in the region of a row of blades with running gap in the meridian view (xr).
  • the main flow direction is indicated by an arrow A.
  • the blade row is no longer shown in favor of a simpler representation.
  • At least one secondary flow channel 1 is formed, which has two openings 111, 112 in the main flow path boundary and is connected via this to the main flow path.
  • the secondary flow channel 1 is designed as a single-path path with an opening through which fluid flows from the main flow channel into the secondary flow channel and a second opening, through which the fluid leaves the secondary flow channel. Through which of the openings 111, 112 flows fluid and through which the openings 111, 112 fluid flows, depends on the exact positioning of the openings 111, 112 with respect to the blades of the blade row 3 (see. Fig. 2B ).
  • At least one of the secondary flow channels is formed by an arrangement in which a single channel is divided along its course into at least two subchannels, thereby forming a kind of "trouser configuration".
  • an inflow port and a plurality of outflow ports are included, which belong to the secondary flow passage.
  • the support member is designed as a ring housing of a turbomachine or as a half shell housing a turbomachine. With a corresponding arrangement in the hub region, it is, for example, annularly formed on the hub of a turbomachine or semi-annular on the hub of a turbomachine.
  • the support member 21 of FIG. 3A forms on the side facing away from the main flow path a nozzle 211 and spaced therefrom in the flow direction from a web 212, in each of which subregions 12, 13 of the secondary flow channel 1 are formed and which form adjacent to the main flow path in each case one of the openings 111, 112 of the secondary flow channel 1.
  • the connecting component 22 connects the two areas 211, 212 of the support component, so that the secondary flow channel 1 in the illustrated embodiment comprises three sections, a rear section 13, which is formed in the web 212 of the support member 21, a central portion 11 formed in the connecting member 22 is and a front portion 12 which is formed in the neck 211 of the support member 21, wherein the rear and the front portion 13, 12 each open in an opening 112, 111 to the main flow path.
  • the connecting member 22, which forms the central portion 11 of the secondary flow channel 1 is formed by a hose or by a pipe which is connected at their ends to a corresponding surface of the nozzle 212 and the web 211 of the support member, for example by means of a flange connection, not shown.
  • the connection of the connection component 22 to the support component 21 is realized by a fit, a connection, a clamping, a screw connection, a weld or a soldering.
  • FIG. 3A 1 shows an exemplary embodiment in which a structural assembly comprises a support component 21 and a connection component 22, wherein the openings of the secondary flow channel 1 are formed in the support component 11 and the connection component 22 forms a central subsection of the secondary flow channel 1 forms or surrounds.
  • the connecting member 22 is arranged as a line freely in space.
  • FIG. 3B shows an embodiment of a structural assembly in the region of a row of blades with running gap in the meridian view (xr), which is characterized by the embodiment of the FIG. 3A distinguishes that a connecting member 23 is not formed as a freely arranged in space line, but instead as a ring sector.
  • connection component 23 is designed, for example, as a half ring or as a complete solid ring.
  • the connecting component 23 thus constitutes a type of housing shell in which one or more channels 11 are formed, each of which forms a central section of a secondary flow channel 1. It can be provided that due to the possible complexity of the secondary flow channels 1, the connecting component 23 is produced by means of a casting, sintering or print manufacturing process.
  • the FIG. 3C shows an example of a structural assembly in the region of a row of blades with a running gap in the meridian view (xr), in which the secondary flow channel 1 is completely formed in the connecting member 24.
  • the connecting member 24 thus includes portions 241, 242 which adjoin the main flow path and form a portion of the main flow path boundary. In each case one of the openings 111, 112 of the secondary flow channel 1 is formed in the sections 241, 242.
  • connection component 24 is inserted into corresponding openings 213, 214 of the support component 21. Between the regions 241, 242 of the connection component 24, which form the respective openings 111, 112, a partial region 215 of the support component 21 runs in this case.
  • the constructive solutions with regard to FIGS. 3A . 3B . 3C are described, combined with each other.
  • the connecting component 24 of the FIG. 3C consists of three sub-areas, in other words, the connecting member 24 is formed by three connecting part components, wherein the middle sub-component according to the FIG. 3A for example, is designed as a flexible hose, while the other two sub-components which are mounted in the support member 21, can absorb structural forces.
  • the invention is not limited in its embodiment to the embodiments shown above, which are to be understood only as examples.
  • shape and configuration of the secondary flow channels and of the components that make them available can be realized in a different way than illustrated.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (8)

  1. Machine à écoulement avec un sous-ensemble structural qui présente:
    - une bordure de la voie d'écoulement principale (4) qui borde une voie d'écoulement principale d'une machine à écoulement, sachant qu'au moins une rangée d'aubes (3) avec chacune une extrémité d'aube est disposée dans la voie d'écoulement principale, sachant qu'il existe un interstice (5) entre les extrémités des aubes de ladite au moins une rangée d'aubes (3) et la bordure de la voie d'écoulement principale (4) et sachant que les aubes (3) d'une rangée d'aubes et la bordure de la voie d'écoulement principale (4) exécutent un mouvement relatif de rotation les unes par rapport à l'autre, et
    - au moins un canal de flux secondaire (1) qui présente sur chacune des extrémités espacées dans le sens d'écoulement une ouverture (111, 112) qui est formée dans la bordure de la voie d'écoulement principale (4) de telle façon que le canal de flux secondaire (1) est relié à la voie d'écoulement principale au moyen des deux ouvertures (111, 112), sachant qu'aucun dispositif de soupape pour commander l'ouverture et la fermeture des deux ouvertures (111, 112) n'est disposé dans chacune des deux ouvertures (111, 112),
    - sachant que le sous-ensemble structural présente au moins deux composants reliés entre eux, au moins un composant d'appui (21) et au moins un composant de liaison (22, 23), sachant que le composant d'appui (21) forme au moins partiellement la bordure de la voie d'écoulement principale (4), sachant que le composant de liaison (22, 23) forme à lui seul ou entoure au moins une section partielle (11, 12, 13) du canal de flux secondaire (1),
    caractérisée en ce que
    chaque canal de flux secondaire (1) à l'intérieur d'une vue méridienne (x-r) est divisé en trois sections partielles, à savoir une section partielle arrière (13) qui débouche, par une ouverture (112) dans la voie d'écoulement principale, une section partielle avant (12) qui débouche, par une ouverture (111) dans la voie d'écoulement principale et une section partielle centrale (11) qui relie ensemble les deux autres sections partielles (12, 13), sachant que les deux sections partielles (12, 13) du canal de flux secondaire (1), débouchant dans la voie d'écoulement principale sont prévues directement dans le composant d'appui (21).
  2. Machine à écoulement selon une des revendications précédentes, caractérisée en ce que le composant d'appui (21) est conçu sous forme de carter annulaire d'une machine à écoulement, sous forme de carter à demi-coque d'une machine à écoulement, sous forme annulaire sur le moyeu d'une machine à écoulement ou semi-annulaire sur le moyeu d'une machine à écoulement.
  3. Machine à écoulement selon une des revendications précédentes, caractérisée en ce qu'au moins un canal de flux secondaire (1) est formé par une disposition dans laquelle un canal unique se divise le long de son tracé en au moins deux canaux et forme une sorte de « configuration en Y », sachant qu'une ouverture d'entrée et plusieurs ouvertures de sortie appartiennent à un canal de flux secondaire (1) ou dans laquelle au moins deux canaux sont regroupés en un, sachant que plusieurs ouvertures d'entrée et une ouverture de sortie appartiennent à un canal de flux secondaire (1).
  4. Machine à écoulement selon une des revendications précédentes, caractérisée en ce qu'au moins une des sections partielles (12, 13) d'un canal de flux secondaire (1), débouchant dans la voie d'écoulement principale est conçue au moins partiellement sous forme de cylindre avec une section elliptique ou circulaire dans le composant d'appui (21).
  5. Machine à écoulement selon une des revendications précédentes, caractérisée en ce que sur le côté opposé à la voie d'écoulement principale du composant d'appui (21) est prévue au moins une tubulure (212) localement sur la circonférence, pour former ou faire passer au moins une des sections partielles du canal de flux secondaire (12, 13) et/ ou qu'est prévue sur le côté opposé à la voie d'écoulement principale du composant d'appui (21) au moins une nervure (211) s'étendant en continu au moins le long d'une partie de la circonférence, pour former ou faire passer au moins une des sections partielles du canal de flux secondaire (12, 13).
  6. Machine à écoulement selon une des revendications précédentes, caractérisée en ce que le composant de liaison (22, 23) jouxte aussi bien une première section partielle (12) logée directement dans le composant d'appui (21) qu'une seconde section partielle (13) logée directement dans le composant d'appui (21), sachant que le composant de liaison (22, 23) forme ou entoure une troisième section partielle (11) du canal de flux secondaire (1) et forme la liaison entre les premières et secondes sections partielles (12, 13).
  7. Machine à écoulement selon une des revendications précédentes, caractérisée en ce que le composant de liaison (22, 23) abrite seulement un canal de flux secondaire (1) et est disposé au moins partiellement sous forme de conduite, notamment sous forme de tube ou de tuyau librement dans l'espace hors du composant d'appui (21).
  8. Machine à écoulement selon une des revendications n° 1 à n° 6, caractérisée en ce que le composant de liaison (22, 23) est conçu sous forme de secteur d'anneau et abrite au moins deux canaux de flux secondaire (1).
EP14170055.9A 2013-05-31 2014-05-27 Ensemble structurel pour une turbomachine Active EP2808556B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102013210167.8A DE102013210167A1 (de) 2013-05-31 2013-05-31 Strukturbaugruppe für eine Strömungsmaschine

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EP2808556A1 EP2808556A1 (fr) 2014-12-03
EP2808556B1 true EP2808556B1 (fr) 2018-11-14

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US (1) US9822792B2 (fr)
EP (1) EP2808556B1 (fr)
DE (1) DE102013210167A1 (fr)

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EP3177811B1 (fr) * 2014-08-08 2021-07-21 Siemens Energy Global GmbH & Co. KG Compresseur d'une turbine à gaz
US10683076B2 (en) 2017-10-31 2020-06-16 Coflow Jet, LLC Fluid systems that include a co-flow jet
US11293293B2 (en) * 2018-01-22 2022-04-05 Coflow Jet, LLC Turbomachines that include a casing treatment
US10876549B2 (en) 2019-04-05 2020-12-29 Pratt & Whitney Canada Corp. Tandem stators with flow recirculation conduit
GB2600584B (en) 2019-07-23 2024-03-06 Coflow Jet Llc Fluid systems and methods that address flow separation
US11732612B2 (en) * 2021-12-22 2023-08-22 Rolls-Royce North American Technologies Inc. Turbine engine fan track liner with tip injection air recirculation passage

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EP2639411A1 (fr) * 2012-03-12 2013-09-18 MTU Aero Engines GmbH Boîtier de turbomachine avec un système de recirculation de fluide

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US20140356143A1 (en) 2014-12-04
DE102013210167A1 (de) 2014-12-04
US9822792B2 (en) 2017-11-21
EP2808556A1 (fr) 2014-12-03

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