EP2808558A1 - Ensemble structurel pour une turbomachine - Google Patents

Ensemble structurel pour une turbomachine Download PDF

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Publication number
EP2808558A1
EP2808558A1 EP14170065.8A EP14170065A EP2808558A1 EP 2808558 A1 EP2808558 A1 EP 2808558A1 EP 14170065 A EP14170065 A EP 14170065A EP 2808558 A1 EP2808558 A1 EP 2808558A1
Authority
EP
European Patent Office
Prior art keywords
flow path
main flow
support member
plug
secondary flow
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
EP14170065.8A
Other languages
German (de)
English (en)
Other versions
EP2808558B1 (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
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP2808558A1 publication Critical patent/EP2808558A1/fr
Application granted granted Critical
Publication of EP2808558B1 publication Critical patent/EP2808558B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/105—Final actuators by passing part of the fluid
    • 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
    • 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
    • F05D2260/15—Load balancing
    • 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
    • F05D2260/60—Fluid transfer
    • F05D2260/606—Bypassing the fluid
    • 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
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/17—Purpose of the control system to control boundary layer

Definitions

  • the invention relates to a structural assembly for a turbomachine 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 with a rectangular or parallelogram-shaped cross-section, as used, for example, in US Pat EP 0 754 864 A1 are disclosed.
  • 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 disclosed.
  • 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 present invention is based on the object to provide a structural assembly, which efficiently secondary flow channels, including those of complex shape, in the field of Main flow path boundary of a turbomachine (ie in the region of the housing or the hub) can provide.
  • the structural assembly has at least one support member and at least one directly or indirectly connected to the support member, replaceable plug.
  • the neck is directly connected to the support member, e.g. arranged on the circumference of the support member, or the connecting piece is connected to a component connected to the support member and thus indirectly to the support member.
  • the replaceable plug comprises a subsection of a secondary flow channel, the subsection completing at least one further subsection of the secondary flow channel extending outside of the plug in the structural assembly to a secondary flow passage continuous between its openings.
  • the solution according to the invention has the advantage that the secondary flow channel can be interrupted or varied by replacing the plug. Also, in the event of wear, a portion of the secondary flow channel formed in the plug can be replaced in a simple manner. In the plug simultaneously spatially compact and robust three-dimensional structures of a secondary flow channel can be provided.
  • 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 replaceable plug penetrates at least one structural component which overhangs the main flow path and which is the support component or a further component.
  • the support component forms at least part of the main flow path boundary with at least part of its surfaces.
  • the replaceable plug extends in a substantially radial direction relative to the main flow path and forms an end face which forms part of the main flow path boundary. According to one embodiment, at least one of the openings of the secondary flow channel is formed in the end face of the replaceable plug.
  • At least one subsection of a secondary flow channel is realized in the support component, so that at least the support component and the plug accommodate subsections of the secondary flow channel. Further sections can be provided by further components.
  • the support member is formed as an annular housing or as a half-shell housing a turbomachine, or the support member is formed like a ring or half-ring on the hub of a turbomachine.
  • the support member is structurally such that for the purpose of assembly and disassembly of the interchangeable plug from the main flow path side facing a direct access to the interchangeable plug is given, so that the interchangeable plug from the main flow path side facing away from the support member without disassembling others Structural components is replaceable.
  • the structural assembly according to the invention further comprises at least one insert member, wherein in the support member is provided a circumferentially extending recess which receives along the circumference at least one insert member, and wherein each insert member forms part of the surfaces of a part of the Hauptströmungspfaderbandung and at least forms a portion of a secondary flow channel.
  • the insert member is completely penetrated at the periphery of at least one replaceable plug, such that the end face of the replaceable plug forms part of the Hauptströmungspfadberandung. It can also be provided that the replaceable plug penetrates only the insert component and there has a defined seat, wherein the support member is a local Has recess through which the replaceable plug in the insert component is mounted and dismounted. Alternatively, the replaceable plug penetrates both the support member and the insert member.
  • the structural assembly according to the invention further comprises at least one connecting member, wherein the connecting member substantially on the side facing away from the main flow path side of the support member to the support member, and wherein the connecting member forms at least a portion of a secondary flow channel.
  • the support member is completely penetrated at the periphery of at least one replaceable plug such that the end face of the replaceable plug forms part of the main flow path boundary, wherein portions of a secondary flow channel are formed in the support member, in the connection member and in the replaceable plug and complement each other to a continuous secondary flow channel.
  • a further variant of the invention provides that the connecting component is installed in recesses in the support component in the area of at least one end of the secondary flow channel and in this way directly adjoins the main flow path.
  • the connecting component thus also forms an opening-near region of the secondary flow channel.
  • At least one connecting piece may be formed on the side of the support component facing away from the main flow path on the circumference of the support component. Also, on the side facing away from the main flow path side of the support member is at least one, at least along a portion of the circumference continuously extending web for receiving at least one interchangeable plug is formed.
  • the replaceable plug is designed as a multi-part element.
  • an embodiment variant provides that the replaceable plug is subdivided into partial plugs along at least partial sections of the secondary flow channel.
  • a further embodiment provides that the replaceable plug is formed in two parts and provided a fixing top plug and a example with a defined seat Understop comprises, with upper and lower plugs together form the interchangeable plug.
  • the fixation of the interchangeable plug is realized by a fit, a press fit, a plug, a clamp or a screw.
  • the interchangeable plug with implemented portion of a secondary flow channel may be replaced by a blind plug with no channel implemented for the purpose of inhibiting flow through the secondary flow channel.
  • the present invention relates generally to structural assemblies for turbomachines, such as turbines, and to particular 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. A Adjustment takes place 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 in multi-stage have two opposing waves, 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 behind a certain row of blades divides into two concentric annular channels, which in turn accommodate at least one more 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.
  • the invention further relates to a fluid flow machine with a structural assembly according to 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.
  • Within the main flow path belonging to the component 2 is in the region of the running gap 5 a number of the circumference distributed secondary flow channels 1 are provided, which each form an opening at their 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 4 and is connected via this to the main flow path.
  • the secondary flow channel 11 is designed as a single-path path with an opening through which fluid flows from the main flow channel into the secondary flow channel 1 and a second opening, through which the fluid leaves the secondary flow channel 1.
  • 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.
  • at least one of the secondary flow channels is formed by an arrangement in which at least two Channels are merged into a channel, in which case a plurality of inflow and a discharge port to the secondary flow passage.
  • the secondary flow channel 1 is realized in a structural assembly comprising a support member 21, an insert member 22 and a replaceable plug 6.
  • the support member 21 is formed as an annular 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.
  • a recess extending in the circumferential direction is provided, in which at least one insert member 22 is inserted along the circumference.
  • the insert component 21 forms part of its surfaces with a part of the main flow path boundary 4.
  • the replaceable plug 6 extends in a substantially radial direction with respect to the main flow path, penetrating both the support member 21 and the insert member 22.
  • the plug 6 has an end face 60 which forms part of the main flow path boundary 4.
  • the secondary flow channel 1 comprises two subsections 11, 12, wherein one subsection 11 is formed in the insert component 22 and the other subsection 12 is formed in the interchangeable plug 6.
  • the one of the two openings 111, 112 of the secondary flow channel 1 is in the insert member 22 and the other of the openings 111, 112 of the secondary flow channel 1 is in Plug 6 is formed.
  • the insert member 22 is inserted in the axial direction in the corresponding recess in the support member 21.
  • a fixation of the components 21, 22 to each other in the axial direction can be effected by a further component 7.
  • portion 12 of the secondary flow channel 1 is provided by means of internal surfaces of the plug 6, that is not by means of structures formed on the outside of the plug 6.
  • a portion 12 of the secondary flow channel 1 in a replaceable plug 6 is associated with the advantage that it is possible by replacing the plug 6 by a blind plug without integrated channel section, to prevent the flow through the secondary flow channel 1.
  • a flow through a secondary flow channel can be switched on and off.
  • various plugs 6 in which the partial section 12 realized in the stopper 6 is embodied in different ways, in each case complementing the partial section 11 formed in the insert component 22. In this way, the formation of the secondary flow channel 1 and the flow occurring therein can be varied in a simple manner.
  • FIG. 3B shows a further embodiment of a structural assembly in the region of a row of blades with running gap in the meridian view (xr).
  • the embodiment of FIG. 3B differs from the embodiment of FIG. 3A in that the replaceable plug 6 is designed as a multipart element.
  • the plug 6 is divided into two sub-plugs 61, 62, wherein in principle more than two sub-plugs are possible.
  • the plug 6 comprises a fixing top plug 62 and a properly fitted bottom plug 61 Part region 12 of the secondary flow channel 1 in the lower plug 61 is formed.
  • the top plug 62 is fixed by screwing or the like in a corresponding opening of the support member 21, for example.
  • FIG. 3C shows a further embodiment of a structural assembly in the region of a row of blades with running gap in the meridian view (xr).
  • this embodiment is different from the embodiments of FIGS. 3A and 3B provided that the replaceable plug 6 penetrates only the insert member 22 and is fitted in this. A structural member penetrating the plug 6 is thus provided solely by the insert member 22.
  • the support member 21 has a local recess 215, for example in the form of a mounting opening through which the replaceable plug 6 in the insert member 22 can be mounted and dismounted. It can be provided, for example, that the plug 6 has a round cross section and is fixed by means of a thread 63 in its upper part in the insert member 22.
  • the shape and fixation modes of the replaceable plug 6 may be formed in other ways.
  • the Figure 3D shows a further embodiment of a structural assembly in the region of a row of blades with running gap in the meridian view (xr).
  • the replaceable plug 6 penetrates again alone the insert member 22, wherein above the plug 6 in the support member 21, a mounting opening 215 is formed.
  • the plug 6 is designed as a multi-part element with two partial plugs 64, 65, whereby more than two partial plugs can be provided.
  • the subdivision of the plug 6 into two sub-plugs 64, 65 takes place along two sections of the secondary flow channel 1, that is, each of the two sub-plugs 64, 65 accommodates a lower portion 12a, 12b of the portion 12 realized in the plug 6. This is associated with the advantage in that the secondary flow channel 1 can be made more easily accessible, for example, to a production tool.
  • the exchangeable plug 6 may be provided to produce the exchangeable plug 6 by means of a casting, sintering or print production method. This applies to all described embodiments.
  • FIG. 3E shows a further embodiment of a structural assembly in the region of a row of blades with running gap in the meridian view (xr).
  • the secondary flow channel 1 comprises three subsections 11, 12, 13, wherein a subsection is formed in a support member 21, a subsection in a replaceable plug 6, and a subsection in a connection component 23.
  • the support member 21 forms with part of its surfaces a part of the main flow path boundary 4. At the side facing away from the main flow path, it forms a structure 212 for receiving the replaceable plug 6, which is formed in the illustrated embodiment by a cylindrical wall or a nozzle 212. In the wall 212 of the plug 6 is inserted, wherein the end face 60 of the plug 6 is a part of the Hauptströmungspfadberandung 4. In the plug 6, a portion 12 of the secondary flow channel and one of the openings 111 of the secondary flow channel are integrated.
  • the support member 21 further includes on its side facing away from the main flow path side a web 211, in which a first portion 13 of the secondary flow channel is formed. Between the web 211 and the neck or the wall 212 extends the connecting member 22 which extends on the side facing away from the main flow path side of the support member 21 between these portions 211, 212 of the support member 21 and is arranged, for example as a line freely in space.
  • a fixation of the replaceable plug 6 can be realized for example by a fit, a press fit, a plug, a clamp or a screw.
  • the connecting member 11 is attached to the web 211 and the nozzle 212, for example, by a fit, a plug, a clamp, a screw, a weld or a solder.
  • the connecting member 23 is formed such that it is inserted in recesses in the support member 21 in the region of at least one end of the secondary flow channel and in this way has surfaces which form part of the Hauptströmungspfadberandung 4.
  • the connecting piece 211 is formed as part of the connecting component 23.
  • FIGS. 3A to 3E the constructive solutions, with regard to FIGS. 3A to 3E are described, combined with each other.
  • a multipart plug 6 in the embodiment of the FIG. 3E be realized.
  • 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 providing them 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)
EP14170065.8A 2013-05-31 2014-05-27 Ensemble structurel pour une turbomachine Not-in-force EP2808558B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102013210171.6A DE102013210171A1 (de) 2013-05-31 2013-05-31 Strukturbaugruppe für eine Strömungsmaschine

Publications (2)

Publication Number Publication Date
EP2808558A1 true EP2808558A1 (fr) 2014-12-03
EP2808558B1 EP2808558B1 (fr) 2017-12-06

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Application Number Title Priority Date Filing Date
EP14170065.8A Not-in-force EP2808558B1 (fr) 2013-05-31 2014-05-27 Ensemble structurel pour une turbomachine

Country Status (3)

Country Link
US (1) US9587509B2 (fr)
EP (1) EP2808558B1 (fr)
DE (1) DE102013210171A1 (fr)

Families Citing this family (3)

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Publication number Priority date Publication date Assignee Title
DE102018116062A1 (de) * 2018-07-03 2020-01-09 Rolls-Royce Deutschland Ltd & Co Kg Strukturbaugruppe für einen Verdichter einer Strömungsmaschine
US10876549B2 (en) 2019-04-05 2020-12-29 Pratt & Whitney Canada Corp. Tandem stators with flow recirculation conduit
CN113027817A (zh) * 2021-03-12 2021-06-25 西北工业大学 一种轴流压气机自循环机匣的加工方法及其结构

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EP0497574A1 (fr) 1991-01-30 1992-08-05 United Technologies Corporation Virole avec canaux de récirculation pour soufflante
EP0754864A1 (fr) 1995-07-18 1997-01-22 Ebara Corporation Turbomachine
DE10105456A1 (de) * 2001-02-07 2002-08-08 Daimler Chrysler Ag Verdichter, insbesondere für eine Brennkraftmaschine
DE10135003C1 (de) 2001-07-18 2002-10-02 Mtu Aero Engines Gmbh Verdichtergehäusestruktur
US6585479B2 (en) 2001-08-14 2003-07-01 United Technologies Corporation Casing treatment for compressors
DE10330084A1 (de) 2002-08-23 2004-03-04 Mtu Aero Engines Gmbh Rezirkulationsstruktur für Turboverdichter
US20050226717A1 (en) 2004-04-13 2005-10-13 Rolls-Royce Plc Flow control arrangement
EP1659293A2 (fr) * 2004-11-17 2006-05-24 Rolls-Royce Deutschland Ltd & Co KG Turbomachine
EP2108784A2 (fr) * 2008-04-08 2009-10-14 Rolls-Royce Deutschland Ltd & Co KG Turbomachine dotée d'un composant d'injecteur de fluide
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DE102008037154A1 (de) 2008-08-08 2010-02-11 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine
US20120201654A1 (en) * 2009-08-31 2012-08-09 Snecma Turbine engine compressor having air injections

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US9587509B2 (en) 2017-03-07
EP2808558B1 (fr) 2017-12-06
DE102013210171A1 (de) 2014-12-04
US20140363277A1 (en) 2014-12-11

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