EP2110559A2 - Turbomachine avec réinjection de fluide pour influencer la couche limite - Google Patents

Turbomachine avec réinjection de fluide pour influencer la couche limite Download PDF

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Publication number
EP2110559A2
EP2110559A2 EP20090003693 EP09003693A EP2110559A2 EP 2110559 A2 EP2110559 A2 EP 2110559A2 EP 20090003693 EP20090003693 EP 20090003693 EP 09003693 A EP09003693 A EP 09003693A EP 2110559 A2 EP2110559 A2 EP 2110559A2
Authority
EP
European Patent Office
Prior art keywords
point
blade
fluid
profile
flow path
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
EP20090003693
Other languages
German (de)
English (en)
Other versions
EP2110559B1 (fr
EP2110559A3 (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 EP2110559A2 publication Critical patent/EP2110559A2/fr
Publication of EP2110559A3 publication Critical patent/EP2110559A3/fr
Application granted granted Critical
Publication of EP2110559B1 publication Critical patent/EP2110559B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F04D29/66—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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • 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
    • F04D29/542—Bladed diffusers
    • 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
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable 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
    • F04D29/682—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid extraction
    • 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
    • F04D29/684—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid injection
    • 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
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line

Definitions

  • the invention relates to a fluid flow machine according to the features of the preamble of claim 1.
  • the invention relates to a fluid flow machine having a flow path delimited by at least one wall on which at least one row of blades (rotor blades or stator blades) are arranged, with no relative movement between the wall and the blades.
  • the aerodynamic load capacity and the efficiency of fluid flow machines is limited in particular by the growth and separation of boundary layers close to the housing wall.
  • boundary layer control by fluid recycling is thus included in the prior art,
  • the known solutions are only partially effective and very limited in their practicality. This is in part due to the fact that the boundary layer flow phenomena occurring in the sidewall region of fluid flow machines are very complex.
  • the present invention thus relates to blades of fluid flow machines such as fans, compressors, pumps and fans of axial, semi-axial and radial design with gaseous or liquid working medium.
  • the turbomachine may include one or more stages, each having a rotor and a stator, in some cases the stage is merely formed by a rotor.
  • the rotor consists of a number of blades, which are connected to the rotating shaft of the machine and deliver energy to the working fluid.
  • the rotor can be designed with or without shroud on the outer blade end.
  • the stator 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, for. As in propellers or propellers, no housing exists.
  • the machine may also have a stator in front of the first rotor, a so-called leading wheel. At least one stator or leader wheel may be rotatably supported, other than the stationary fixture, to vary the angle of attack. An adjustment is made for example by a spindle accessible from outside the annular channel.
  • the flow machine can have at least one row of adjustable rotors.
  • the turbomachine according to the invention may have two counter-rotating 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.
  • the fluid flow machine can alternatively have a bypass configuration such that the single-flow annular channel divides behind a certain row of blades into two concentric annular channels, which in turn accommodate at least one additional row of blades.
  • the invention relates to a fluid flow machine, with which work is applied to the flow medium.
  • the invention has for its object to provide a fluid flow machine of the type mentioned, which has a simple structure and simple, cost-effective manufacturability improved flow behavior and increased efficiency.
  • the invention thus relates to a scoop row internal, shortest possible fluid return or a fluid return passage through the side wall of the relevant row of blades in the region of a blade end, without a circumferentially extending relative movement between the blade and the main flow path limiting side wall, wherein the removal point in the region of the blade trailing edge or the blade pressure side is provided and the supply point has proximity to the blade suction side.
  • a fluid flow machine is provided with a flow path which is delimited by at least one wall on which at least one row of blades with a fixed connection is arranged.
  • at least one fluid removal opening and at least one fluid supply opening are arranged in the wall in a region of a row of blades, which are connected by at least one fluid return path, wherein the extent of the fluid supply opening in the circumferential direction is less than the distance between two adjacent blades.
  • the fluid return according to the invention gains in particular effectiveness if the flow deflection of the relevant blade row assumes a high degree of more than 35 °.
  • the Fig. 1 shows a schematic representation of a fluid flow machine in the meridian view, here the example of a compressor consisting of an annular channel 2, which is bounded on the inside by a hub contour 3 and the outside by a housing contour 1, and with a number of rotor blade rows 6 and stator blade rows 7 within the annular channel 2 or main flow path is equipped. Between the blade rows 6, 7 exist bladder-free spaces. As shown by the large arrow, the turbomachine flows in from the left.
  • the fluid return according to the invention relates to all areas of the side walls (hub 3 or housing 1) in which a blade end is provided without a relative movement between blade row and adjacent side wall, see marked areas.
  • the Fig. 2 shows different types of fluid recirculation according to the prior art, from blade row to blade row, possibly between blade rows of the same or different type (rotor 6 or stator 7).
  • the Fig. 3 schematically shows another category of fluid recirculation according to the prior art. These relate all to arrangements of rotors 6 with radial gap and relative movement between the rotor 6 and the surrounding Housing 1. Here, air is recirculated from a location above the rotor 6 to a location near the rotor leading edge.
  • the Fig. 4 shows on the left side of the area of a blade end without a circumferential relative movement between the blade and the main flow path defining side wall.
  • the fluid return according to the invention provides for the removal and supply of the fluid in fixed zones of the side wall in the region of the respective same blade row.
  • the right side of the Fig. 4 shows the view ZZ, that is, a section through the row of blades with a view of the side wall and located between two blades blade passage in a plane defined by the circumferential direction u and the meridional direction m plane.
  • the flow of the blade row is from the left.
  • two fluid removal zones are defined, both of which are essentially supported on the profile pressure side: a comprehensive removal zone EA1 in which removal is advantageous and a further restricted removal zone EA2 located within EA1 in which removal is particularly favorable.
  • the Fig. 5 shows how Fig. 4 on the left side, the area of a blade end without a circumferential relative movement between the blade and the side wall delimiting the main flow path.
  • the right side of the Fig. 5 shows the view ZZ, ie the blade passage in the plane defined by the circumferential direction u and the meridional direction m, now with two fluid supply zones, both of which are substantially supported on the profile suction side: a comprehensive supply zone IA1, in which a supply is advantageous and one within IA1 further restricted supply zone IA2, in which a supply is particularly favorable.
  • the Fig. 6 shows a scoop internal fluid return according to the invention.
  • the left image side shows the arrangement in the meridional plane, spanned by the axial coordinate x and the radial coordinate r.
  • a flow path is provided which allows a fluid return from a single opening in the removal zone according to the invention to a single opening in the feed zone according to the invention.
  • the gearbox is shown in dashed lines, as it extends over a portion of the circumference, which is not fully representable in this view. Further features of the fluid recycling can be seen in the right part of the picture. There the arrangement is shown in the view ZZ.
  • Fluid may enter from the main flowpath of the fluid flow machine into an orifice near the tread pressure side of a vane, is directed through a flow channel to the vicinity of the tread suction side of the adjacent vane, and there is supplied to the main flowpath substantially tangential to the sidewall. It is advantageous according to the invention that the removal opening has a larger cross-sectional area than the supply opening and in this way a continuous contraction of the return flow path is possible.
  • Fig. 7 an alternative solution according to the invention for fluid recycling is shown.
  • fluid from the main flow path of the fluid flow machine enters an opening in the vicinity of the profile pressure side of a blade, is guided through a flow channel in the vicinity of the profile suction side of the same blade and fed there substantially tangentially to the side wall of the main flow path.
  • the return flow path and the contour of the airfoil intersect.
  • the center line of the passage between two adjacent blade profiles drawn is the center line of the passage between two adjacent blade profiles drawn.
  • the removal opening there and the supply opening there are arranged on different sides of the passage center line. Furthermore, it is particularly effective according to the invention if the area center of gravity of the fluid supply opening designated CGI is arranged in the meridional flow direction m upstream of the centroid of the fluid removal opening designated CGE. In addition, it is favorable according to the invention if the fluid supply opening is provided at least partially downstream of the leading edge plane LEP. Again, though not in anymore Fig. 7 illustrated, at least one branch of the return flow path for supplying at least one further feed opening exists.
  • the Fig. 8 shows a similar arrangement of fluid recycling as Fig. 7 However, here is a removal not provided in the blade passage, but downstream of the trailing edge.
  • the Fig. 9 shows a similar arrangement of fluid recycling as Fig. 8 but here removal is provided downstream of the trailing edge by means of a chamber extending over the entire circumference of the main flow path, from which individual channels for supplying a plurality of feed openings depart in the further return flow path.
  • the Fig. 10 shows a solution according to the invention for fluid recycling using the example of a rotor with blade platform and blade circumference feet.
  • the rotor blades are mounted in a hub with the hub and blade platform forming a chamber outside the main flowpath.
  • In the blade platform are each a removal opening and a Supply port provided, between which fluid can be replaced by the chamber below the platform.
  • the supply port is formed here as a nozzle projecting into the main flow path.
  • the Fig. 11 shows a solution according to the invention for fluid recycling using the example of a stator with blade platform and blade circumference feet.
  • the stator blades are mounted in a housing with the housing and paddle platform forming a chamber outside of the main flowpath.
  • a removal opening and a supply opening are provided, between which fluid can be replaced by the chamber above the platform.
  • the feed opening is here designed as a nozzle projecting into the main flow path.
  • the Fig. 12 shows a similar arrangement as Fig. 11 However, here is the removal opening formed as a projecting into the main flow path accumulation.
  • the Fig. 13 also shows fluid recirculation on the stator now on both the housing side and the hub side of the main flow path.
  • the stator On the hub side, the stator has an inner cover strip, which performs a rotating relative movement with respect to the rotor drum surrounded by it.
  • a connection of extraction and supply ports can as in the FIGS. 6 to 9 shown to be provided as a number of individual channels, or as shown in FIG Fig. 13 shown, done by means of a circumferentially extending provided within the shroud chamber.
  • the feed opening is here designed as a nozzle projecting into the main flow path, and the removal opening is designed as a congestion inlet projecting into the main flow path.
  • the view YY shows a Blade section facing the shroud and fluid return ports.
  • the Fig. 14 shows a solution according to the invention for a fluid return on the example of a rotatably mounted blade end.
  • This may be a compound of rotor blade and hub, a compound of stator blade and housing or a combination of stator blade and inner shroud.
  • the left part of the picture shows the fluid return in the area of the rotatable blade end.
  • the fluid is passed from the removal opening to the supply opening, bypassing the adjustment axis of the blade. Both openings are exemplified here as flush with the main flow path.
  • the view shown in the right half ZZ (blade section with a view of the main flow path wall and the turntable of the blades) shows a possible course of the return path.
  • the blade profiles are shown here in the design position and would move over the openings during adjustment in partial load operation.
  • the Fig. 15 shows a solution according to the invention for fluid recycling using the example of a variable stator with inner shroud on the hub and rotatable fixation of the blades at both ends.
  • the stator blades are mounted externally in a housing in which a flow chamber is formed, which connects the removal openings with the supply openings.
  • Inside the stator blades are mounted in the shroud, in which also a flow chamber is provided, which connects the discharge openings with the supply openings.
  • Further details of this exemplary arrangement according to the invention shows the view YY in the right half of FIG Fig. 15 ,

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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)
EP09003693.0A 2008-04-18 2009-03-13 Turbomachine avec réinjection de fluide pour influencer la couche limite Active EP2110559B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102008019603A DE102008019603A1 (de) 2008-04-18 2008-04-18 Strömungsmaschine mit schaufelreiheninterner Fluid-Rückführung

Publications (3)

Publication Number Publication Date
EP2110559A2 true EP2110559A2 (fr) 2009-10-21
EP2110559A3 EP2110559A3 (fr) 2015-03-25
EP2110559B1 EP2110559B1 (fr) 2018-12-12

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Family Applications (1)

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EP09003693.0A Active EP2110559B1 (fr) 2008-04-18 2009-03-13 Turbomachine avec réinjection de fluide pour influencer la couche limite

Country Status (3)

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US (1) US8043046B2 (fr)
EP (1) EP2110559B1 (fr)
DE (1) DE102008019603A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2010015241A2 (fr) * 2008-08-04 2010-02-11 Mtu Aero Engines Gmbh Compresseur axial avec grille de compresseur
EP2871368A1 (fr) * 2013-11-12 2015-05-13 MTU Aero Engines GmbH Compresseur de turbine à gaz
US10047619B2 (en) 2013-11-06 2018-08-14 MTU Aero Engines AG Seal configuration for a turbo machine
WO2019034740A1 (fr) * 2017-08-18 2019-02-21 Abb Turbo Systems Ag Diffuseur pour compresseur radial
FR3107917A1 (fr) * 2020-03-04 2021-09-10 Safran Carter de roue mobile pour turbomachine

Families Citing this family (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102008011746A1 (de) * 2008-02-28 2009-09-03 Mtu Aero Engines Gmbh Vorrichtung und Verfahren zur Umleitung eines Leckagestroms
FR2931886B1 (fr) * 2008-05-29 2011-10-14 Snecma Collecteur d'air dans une turbomachine.
DE102008029605A1 (de) * 2008-06-23 2009-12-24 Rolls-Royce Deutschland Ltd & Co Kg Schaufeldeckband mit Durchlass
DE102008060424A1 (de) * 2008-12-04 2010-06-10 Rolls-Royce Deutschland Ltd & Co Kg Strömungsmaschine mit Seitenwand-Grenzschicht-Barriere
US9068507B2 (en) * 2011-11-16 2015-06-30 General Electric Company Compressor having purge circuit and method of purging
CN102556345B (zh) * 2012-01-18 2016-04-13 朱晓义 飞机动力装置
JP6514644B2 (ja) 2013-01-23 2019-05-15 コンセプツ エヌアールイーシー，エルエルシー ターボ機械の隣接する翼要素の流れの場を強制的に結合する構造体および方法、ならびにそれを組み込むターボ機械
DE102013210167A1 (de) * 2013-05-31 2014-12-04 Rolls-Royce Deutschland Ltd & Co Kg Strukturbaugruppe für eine Strömungsmaschine
DE102013210169A1 (de) * 2013-05-31 2014-12-04 Rolls-Royce Deutschland Ltd & Co Kg Strukturbaugruppe für eine Strömungsmaschine
EP2881548B1 (fr) * 2013-12-09 2018-08-15 MTU Aero Engines GmbH Compresseur de turbine à gaz
JP6866019B2 (ja) 2014-06-24 2021-04-28 コンセプツ エヌアールイーシー，エルエルシー ターボ機械の流動制御構造及びその設計方法
DE102015110252A1 (de) * 2015-06-25 2016-12-29 Rolls-Royce Deutschland Ltd & Co Kg Statorvorrichtung für eine Strömungsmaschine mit einer Gehäuseeinrichtung und mehreren Leitschaufeln
DE102015110249A1 (de) * 2015-06-25 2017-01-12 Rolls-Royce Deutschland Ltd & Co Kg Statorvorrichtung für eine Strömungsmaschine mit einer Gehäuseeinrichtung und mehreren Leitschaufeln
DE102015110250A1 (de) * 2015-06-25 2016-12-29 Rolls-Royce Deutschland Ltd & Co Kg Statorvorrichtung für eine Strömungsmaschine mit einer Gehäuseeinrichtung und mehreren Leitschaufeln
US10041500B2 (en) * 2015-12-08 2018-08-07 General Electric Company Venturi effect endwall treatment
CN107150788A (zh) * 2017-04-26 2017-09-12 朱晓义 一种产生更大升力的固定翼飞行器
FR3082558B1 (fr) * 2018-06-15 2021-09-17 Safran Aircraft Engines Distributeur de turbine pour turbomachine, comprenant un systeme passif de reintroduction de gaz de fuite dans une veine d'ecoulement des gaz
FR3084395B1 (fr) * 2018-07-24 2020-10-30 Safran Aircraft Engines Ailettes entrefer pour compresseur de turbomachine
US10876549B2 (en) 2019-04-05 2020-12-29 Pratt & Whitney Canada Corp. Tandem stators with flow recirculation conduit
FR3109959B1 (fr) * 2020-05-06 2022-04-22 Safran Helicopter Engines Compresseur de turbomachine comportant une paroi fixe pourvue d’un traitement de forme
CN116194675A (zh) 2020-08-07 2023-05-30 概创机械设计有限责任公司 用于增强性能的流量控制结构及结合有该流量控制结构的透平机
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
US11946379B2 (en) 2021-12-22 2024-04-02 Rolls-Royce North American Technologies Inc. Turbine engine fan case with manifolded tip injection air recirculation passages
US11702945B2 (en) 2021-12-22 2023-07-18 Rolls-Royce North American Technologies Inc. Turbine engine fan case with tip injection air recirculation passage
FR3133063A1 (fr) * 2022-02-25 2023-09-01 Safran Aircraft Engines Aubage de turbomachine, comprenant une pale et une plateforme qui présente un canal interne d’aspiration et d’éjection de flux

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102004030597A1 (de) 2004-06-24 2006-01-26 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit Aussenradstrahlerzeugung am Stator
EP1382855B1 (fr) 2002-07-20 2006-10-25 Rolls-Royce Deutschland Ltd & Co KG Turbomachine avec système de recirculation de fluide intégré

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH204331A (de) * 1937-02-24 1939-04-30 Rheinmetall Borsig Ag Einrichtung zur Verhinderung der Strahlablösung bei Turboverdichtern.
JPS5254809A (en) * 1975-10-31 1977-05-04 Hitachi Ltd Axial-flow fluid machine construction
EP0497574B1 (fr) * 1991-01-30 1995-09-20 United Technologies Corporation Virole avec canaux de récirculation pour soufflante
US5431533A (en) * 1993-10-15 1995-07-11 United Technologies Corporation Active vaned passage casing treatment
US5474417A (en) * 1994-12-29 1995-12-12 United Technologies Corporation Cast casing treatment for compressor blades
US5607284A (en) * 1994-12-29 1997-03-04 United Technologies Corporation Baffled passage casing treatment for compressor blades
US6220012B1 (en) * 1999-05-10 2001-04-24 General Electric Company Booster recirculation passageway and methods for recirculating air
US6585479B2 (en) * 2001-08-14 2003-07-01 United Technologies Corporation Casing treatment for compressors
ATE325939T1 (de) * 2002-08-23 2006-06-15 Mtu Aero Engines Gmbh Rezirkulationsstruktur für turboverdichter
DE10355240A1 (de) * 2003-11-26 2005-07-07 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit Fluidentnahme
GB2413158B (en) * 2004-04-13 2006-08-16 Rolls Royce Plc Flow control arrangement
DE102004055439A1 (de) * 2004-11-17 2006-05-24 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit dynamischer Strömungsbeeinflussung
DE102007012119A1 (de) * 2007-03-13 2008-09-18 Rolls-Royce Deutschland Ltd & Co Kg Drosselgradabhängige Schaufelverstellung bei Strömungsarbeitsmaschinen

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1382855B1 (fr) 2002-07-20 2006-10-25 Rolls-Royce Deutschland Ltd & Co KG Turbomachine avec système de recirculation de fluide intégré
DE102004030597A1 (de) 2004-06-24 2006-01-26 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit Aussenradstrahlerzeugung am Stator

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2010015241A2 (fr) * 2008-08-04 2010-02-11 Mtu Aero Engines Gmbh Compresseur axial avec grille de compresseur
WO2010015241A3 (fr) * 2008-08-04 2010-04-01 Mtu Aero Engines Gmbh Compresseur axial avec grille de compresseur
US10047619B2 (en) 2013-11-06 2018-08-14 MTU Aero Engines AG Seal configuration for a turbo machine
EP2871368A1 (fr) * 2013-11-12 2015-05-13 MTU Aero Engines GmbH Compresseur de turbine à gaz
US10066633B2 (en) 2013-11-12 2018-09-04 MTU Aero Engines AG Gas turbine compressor bleed channel
WO2019034740A1 (fr) * 2017-08-18 2019-02-21 Abb Turbo Systems Ag Diffuseur pour compresseur radial
US11326619B2 (en) 2017-08-18 2022-05-10 Abb Schweiz Ag Diffuser for a radial compressor
FR3107917A1 (fr) * 2020-03-04 2021-09-10 Safran Carter de roue mobile pour turbomachine

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Publication number Publication date
US20090263233A1 (en) 2009-10-22
EP2110559B1 (fr) 2018-12-12
DE102008019603A1 (de) 2009-10-22
US8043046B2 (en) 2011-10-25
EP2110559A3 (fr) 2015-03-25

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