EP2025945B1 - Machine de traitement des écoulements dotée d'un creux de paroi de canal de ceinture - Google Patents

Machine de traitement des écoulements dotée d'un creux de paroi de canal de ceinture Download PDF

Info

Publication number
EP2025945B1
EP2025945B1 EP08013782.1A EP08013782A EP2025945B1 EP 2025945 B1 EP2025945 B1 EP 2025945B1 EP 08013782 A EP08013782 A EP 08013782A EP 2025945 B1 EP2025945 B1 EP 2025945B1
Authority
EP
European Patent Office
Prior art keywords
recess
fluid
point
flow machine
accordance
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.)
Expired - Fee Related
Application number
EP08013782.1A
Other languages
German (de)
English (en)
Other versions
EP2025945A2 (fr
EP2025945A3 (fr
Inventor
Volker Gümmer
Marius Swoboda
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 EP2025945A2 publication Critical patent/EP2025945A2/fr
Publication of EP2025945A3 publication Critical patent/EP2025945A3/fr
Application granted granted Critical
Publication of EP2025945B1 publication Critical patent/EP2025945B1/fr
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

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
    • F04D29/40—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
    • F04D29/66—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

Definitions

  • the present invention thus relates 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 according to the invention may comprise one or more stages, each with a rotor and a stator.
  • the rotor consists of a number of blades, which are connected to the rotating shaft of the fluid flow machine and energy to the Release working medium.
  • the rotor is designed with a free blade end on the housing.
  • the stator according to the invention consists of a number of fixed blades, which are designed on the housing side with a fixed blade end.
  • the turbomachine in front of the first rotor may have a special form of stator, a so-called leading wheel.
  • At least one stator or Vorleitrad may be rotatably mounted deviating from the immovable fixation in order to change the angle of attack.
  • An adjustment is made for example by a spindle accessible from outside the annular channel.
  • the turbomachine may have at least one row of adjustable rotors.
  • the fluid flow machine can alternatively also have a bypass configuration such that the single-flow annular channel divides behind a specific row of blades into two concentric annular channels, which in turn each comprise at least one further row of blades.
  • Fig. 2 shows examples according to the invention relevant flow machines.
  • the invention relates to the shape of a portion of the annular channel wall and the arrangement and shaping of recesses in said annular channel wall portion in the region of a blade row with free end and running gap of a fluid flow machine.
  • a recirculation structure for turbo compressors is previously known, which shows a circumferential annular chamber.
  • fluid enters around the entire circumference of the annular chamber, is then directed counter to the direction of flow and is conducted between vanes which are scoop-shaped and cause a swirl change of the flow.
  • the flow After flowing through the guide elements, the flow enters an annular region of the annular chamber and flows from there back into the flow path.
  • the present invention has for its object to provide a fluid flow machine of the type mentioned, which has an effective boundary layer influence in the blade tip area while avoiding the disadvantages of the prior art.
  • the Fig. 1 shows, marked by dashed borders, the invention relevant zones, namely areas of the fluid flow machine with free blade ends with running gap.
  • the Figure 3 shows a sketch of a solution according to the invention with at least one recess which is characterized by a partial overlap with the running path of the relevant row of blades. It may also be advantageous to let the recess or the recess group also partially extend into the bladed region of a possibly upstream blade row.
  • the Figure 4 shows a relevant to the invention section of the flow machine, consisting of the portion of a hub or housing assembly with the annular channel wall formed thereby and the blade row located in this area.
  • the configuration may be either a pair of rotor blade rows and a housing assembly, or a pair of stator blade rows and a hub assembly.
  • an optionally upstream arranged row of blades as well as the projected into the illustrated meridian plane outline of the invention Ringkanalwandaus founded.
  • a small arrow indicates the machine axis direction and a thick arrow indicates the main flow direction.
  • the 5a shows a reduced representation of the features Figure 4 , but now with more points and geometrical details.
  • the reference chord length L is defined between the blade tip points A and B. All distances given are in the illustrated meridian plane (plane formed by axial direction x and radial direction r) parallel to the course of the blade tip, ie parallel to the connecting line AB measured.
  • a straight line through the auxiliary points C and D encloses a straight line through the blade tip points A and B the angle alpha.
  • the angle alpha in the indicated directional convention is between -15 ° and 30 °.
  • the front boundary point of the annular channel wall recess E is located at a distance e> 0 in front of the leading edge point A.
  • point E can also be arranged in the bladed region of another row of blades possibly located upstream of the blade row.
  • the rear boundary point of the annular channel wall recess F is at a distance f behind the leading edge point A, where 0.5 L> f> 0.
  • the angle beta is positive in the drawn direction and is given between the straight line through the blade tip points A and B and a tangent to the contour of the annular channel wall recess, at least at one point in the outline of the recess between S and F given in the meridian section minimum 15 ° and maximum 70 °.
  • the angle beta is at least at one point of the outline given in the meridian section of the recess between E and S between 15 ° and 40 °. In this way, a particularly gentle re-entry of the fluid upstream of the blade row is made possible in the main flow path.
  • 5 b shows some possible according to the invention outline shapes of the RingkanalwandausEnglishung.
  • the outline shape can be completely curved or straight.
  • As production technology easily achievable formation of the recess according to the invention is particularly the bottom left and right in 5 b illustrated triangular shape.
  • FIG. 6 shows the view YY, as in Fig. 5a is drawn. Shown here is a pair of rotor blade row and housing, but the following statements also apply to the analogue representable pairing of stator blade row and hub.
  • the figure shows two blade tips in the vicinity of a portion of the housing wall.
  • the annular channel wall (here exemplary housing) has a number of recesses which are arranged distributed in the circumferential direction.
  • the recesses unlike in Figure 6 shown, arranged at different distances in the circumferential direction to each other.
  • the recesses are shown approximately at the position of their maximum penetration depth into the channel wall.
  • the recesses according to the invention have an angle of inclination gamma against the radial direction of the machine.
  • the inclination of the recesses is according to the invention 25 ° ⁇ gamma ⁇ 75 ° and shows accordingly in the direction of the blades moving relative to them.
  • the size of the penetration depth and the choice of shape at the foot of the recess are of minor importance to the present invention and therefore freely selectable.
  • the Fig.7a to 7c each show in the view ZZ a settlement of the circumference of the fluid flow machine in the region of the Ringkanalwandausappelung. Dotted indicate two blades of the relevant row of blades, on which the recess is arranged. Shown are, in partial overlap with the blade row, the openings of an array of recesses on the annular channel wall. According to the invention, the openings in the flow direction of slender nature, ie, the extent in the circumferential direction is smaller than the extent perpendicular thereto.
  • the Fig. 7a shows the alignment of the recess openings in the direction of the machine axis (left half of the picture) and a further arrangement according to the invention, in which the slender openings of the recesses are inclined against the machine axis direction by the angle delta.
  • the angle delta can assume values of up to 35 ° and thus guarantees an opposite staggering of the recess openings and the profiles of the relevant row of blades.
  • Fig. 7b shows two arrangements according to the invention, which are used in the invention differently long and / or differently positioned recesses along the circumference.
  • the Fig. 7c shows two arrangements according to the invention, in which a variation of the width of the recess opening in the longitudinal direction is provided in the invention.

Claims (9)

  1. Machine à écoulement comprenant une voie d'écoulement formée par un carter (1) et un arbre (2) en rotation, dans laquelle sont disposées des rangées d'aubes de rotor (3) et d'aubes de stator (4), caractérisée en ce que dans une zone des bouts des aubes (3, 4) dans une paroi de canal annulaire du carter (1) et/ ou de l'arbre (2) est disposée une rangée d'évidements (5) répartis dans le sens circonférentiel, la section transversale et la position de chaque évidement (5) étant définies comme suit :
    - un point limite E de l'évidement (5) situé en amont dans le sens d'écoulement est à une distance e > 0 du point de bout d'aube avant A,
    - un point limite F de l'évidement (5) situé en aval dans le sens d'écoulement est à une distance f du point de bout d'aube avant A,
    - où : 0,5 L > f > 0,
    - sachant que L est définie comme distance entre les points de bout d'aube A et B,
    - que la paroi de l'évidement (5) comporte un point S qui est situé sur une perpendiculaire à la ligne A-B qui passe par le point S,
    - qu'une droite passant par les points de bout d'aube A et B et une tangente à la paroi de l'évidement (5), au moins à un point de la paroi de l'évidement (5) donnée dans une coupe méridienne entre les points S et F, inscrivent un angle bêta tel que 15° ≤ bêta ≤ 70°,
    - que tous les points sont situés dans un plan méridien défini par une direction axiale x de l'axe (6) de la machine à écoulement et une direction radiale r,
    - que toutes les distances sont mesurées parallèlement à une ligne reliant un point de bout d'aube avant A et un point de bout d'aube arrière B,
    - que deux autres points C et D caractérisent l'allure de la paroi du canal annulaire en amont de l'évidement, C étant à la distance 0,75 L du point de bout d'aube A, et D à la distance 0,25 L du point de bout d'aube A, et
    - que la ligne de jonction A-B inscrit avec la ligne de jonction C-D un angle alpha tel que -15° < alpha < 30°.
  2. Machine à écoulement selon la revendication n° 1, caractérisée en ce que l'angle beta s'élève à 15° ≤ beta ≤ 40°.
  3. Machine à écoulement selon une des revendications n° 1 ou n° 2, caractérisée en ce que le point E se trouve dans la zone aubagée d'une autre rangée d'aubes située en amont des aubes (3, 4) considérées.
  4. Machine à écoulement selon une des revendications n° 1 à n° 3, caractérisée en ce que la forme de la paroi de l'évidement (5) est intégralement curviligne.
  5. Machine à écoulement selon une des revendications n° 1 à n° 3, caractérisée en ce que la forme de la paroi de l'évidement (5) est a une allure rectiligne au moins dans une zone partielle.
  6. Machine à écoulement selon une des revendications n° 1 à n° 5, caractérisée en ce que l'évidement (5) présente par rapport à la direction radiale r de la machine à écoulement un angle d'inclinaison gamma tel que 25° ≤ gamma ≤ 75°.
  7. Machine à écoulement selon une des revendications n° 1 à n° 6, caractérisée en ce qu'une arête longitudinale de l'évidement (5) est inclinée selon un angle delta par rapport à la direction de l'axe de la machine (6), sachant que delta ≤ 35°.
  8. Machine à écoulement selon une des revendications n° 1 à n° 7, caractérisée en ce qu'au moins un évidement (5) présente dans sa section transversale d'ouverture sur la paroi du canal annulaire une largeur ou une extension variante dans le sens circonférentiel.
  9. Machine à écoulement selon une des revendications n° 1 à n° 8, caractérisée en ce qu'en présence de plusieurs évidements (5), deux évidements voisins dans le sens circonférentiel ont différentes positions ou extensions (tant dans le sens axial que circonférentiel).
EP08013782.1A 2007-08-10 2008-07-31 Machine de traitement des écoulements dotée d'un creux de paroi de canal de ceinture Expired - Fee Related EP2025945B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102007037924A DE102007037924A1 (de) 2007-08-10 2007-08-10 Strömungsarbeitsmaschine mit Ringkanalwandausnehmung

Publications (3)

Publication Number Publication Date
EP2025945A2 EP2025945A2 (fr) 2009-02-18
EP2025945A3 EP2025945A3 (fr) 2014-06-25
EP2025945B1 true EP2025945B1 (fr) 2016-04-20

Family

ID=39869927

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08013782.1A Expired - Fee Related EP2025945B1 (fr) 2007-08-10 2008-07-31 Machine de traitement des écoulements dotée d'un creux de paroi de canal de ceinture

Country Status (3)

Country Link
US (1) US8419355B2 (fr)
EP (1) EP2025945B1 (fr)
DE (1) DE102007037924A1 (fr)

Families Citing this family (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102007056953B4 (de) * 2007-11-27 2015-10-22 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit Ringkanalwandausnehmung
FR2940374B1 (fr) * 2008-12-23 2015-02-20 Snecma Carter de compresseur a cavites optimisees.
DE102011107523B4 (de) * 2011-07-15 2016-08-11 MTU Aero Engines AG System zum Einblasen eines Fluids, Verdichter sowie Turbomaschine
FR2989744B1 (fr) * 2012-04-19 2014-06-13 Snecma Carter de compresseur a cavites au calage optimise
FR2989743B1 (fr) * 2012-04-19 2015-08-14 Snecma Carter de compresseur a cavites de longueurs variees
FR2989742B1 (fr) * 2012-04-19 2014-05-09 Snecma Carter de compresseur a cavites a forme amont optimisee
US20140093355A1 (en) * 2012-09-28 2014-04-03 United Technologies Corporation Extended indentation for a fastener within an air flow
US8926276B2 (en) 2013-01-23 2015-01-06 Concepts Eti, Inc. Structures and methods for forcing coupling of flow fields of adjacent bladed elements of turbomachines, and turbomachines incorporating the same
EP2971547B1 (fr) * 2013-03-12 2020-01-01 United Technologies Corporation Stator en porte-à-faux comportant une caractéristique de déclenchement de tourbillon
US9644639B2 (en) * 2014-01-27 2017-05-09 Pratt & Whitney Canada Corp. Shroud treatment for a centrifugal compressor
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
WO2016022138A1 (fr) * 2014-08-08 2016-02-11 Siemens Aktiengesellschaft Compresseur utilisable dans un moteur à turbine à gaz
US10047620B2 (en) * 2014-12-16 2018-08-14 General Electric Company Circumferentially varying axial compressor endwall treatment for controlling leakage flow therein
EP3037674A1 (fr) * 2014-12-22 2016-06-29 Alstom Technology Ltd Moteur et procédé de fonctionnement dudit moteur
JP2016118165A (ja) * 2014-12-22 2016-06-30 株式会社Ihi 軸流機械およびジェットエンジン
CN108506249B (zh) * 2018-04-02 2020-03-10 华能国际电力股份有限公司 一种用于轴流压气机的槽类端壁处理方法
DE102018116062A1 (de) * 2018-07-03 2020-01-09 Rolls-Royce Deutschland Ltd & Co Kg Strukturbaugruppe für einen Verdichter einer Strömungsmaschine
US10914318B2 (en) * 2019-01-10 2021-02-09 General Electric Company Engine casing treatment for reducing circumferentially variable distortion
EP3734081A1 (fr) * 2019-04-30 2020-11-04 Borgwarner Inc. Dispositif de modification de flux pour compresseurs
JP2023536998A (ja) 2020-08-07 2023-08-30 コンセプツ エヌアールイーシー，エルエルシー 性能を向上させるための流量制御構造及び当該流量制御構造を組み込んだターボ機械
CN112832878B (zh) * 2020-12-31 2022-10-25 南昌航空大学 一种涡轮泄漏流控制的非定常机匣处理结构
US20230151825A1 (en) * 2021-11-17 2023-05-18 Pratt & Whitney Canada Corp. Compressor shroud with swept grooves
FR3137940A1 (fr) * 2022-07-15 2024-01-19 Safran Traitement de carter à calage variable par multidisques co-axiaux

Family Cites Families (62)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE889506C (de) 1940-09-25 1953-09-10 Versuchsanstalt Fuer Luftfahrt Stroemungsmaschine mit Grenzschichtabsaugung
GB619722A (en) 1946-12-20 1949-03-14 English Electric Co Ltd Improvements in and relating to boundary layer control in fluid conduits
US2933238A (en) 1954-06-24 1960-04-19 Edward A Stalker Axial flow compressors incorporating boundary layer control
GB799675A (en) 1955-10-13 1958-08-13 Bristol Aeroengines Ltd Improvements in or relating to axial flow gas compressors and turbines
US3066912A (en) 1961-03-28 1962-12-04 Gen Electric Turbine erosion protective device
CH437614A (de) 1963-07-02 1967-11-30 Moravec Zdenek Strömungsmaschine mit verminderter Geräuscherzeugung
GB987625A (en) 1963-10-14 1965-03-31 Rolls Royce Improvements in or relating to axial flow compressors, for example for aircraft gas turbine engines
US3572960A (en) 1969-01-02 1971-03-30 Gen Electric Reduction of sound in gas turbine engines
DE1938132A1 (de) 1969-07-26 1971-01-28 Daimler Benz Ag Leitschaufeln von Axialverdichtern
FR2166494A5 (fr) 1971-12-27 1973-08-17 Onera (Off Nat Aerospatiale)
US3849023A (en) 1973-06-28 1974-11-19 Gen Electric Stator assembly
FR2248732A5 (fr) 1973-10-23 1975-05-16 Onera (Off Nat Aerospatiale)
US4155680A (en) 1977-02-14 1979-05-22 General Electric Company Compressor protection means
GB2017228B (en) * 1977-07-14 1982-05-06 Pratt & Witney Aircraft Of Can Shroud for a turbine rotor
FR2491549B1 (fr) 1980-10-08 1985-07-05 Snecma Dispositif de refroidissement d'une turbine a gaz, par prelevement d'air au niveau du compresseur
US4479755A (en) 1982-04-22 1984-10-30 A/S Kongsberg Vapenfabrikk Compressor boundary layer bleeding system
DE3407945A1 (de) 1984-03-03 1985-09-05 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Verfahren und mittel zur vermeidung der entstehung von titanfeuer
DE3407946A1 (de) 1984-03-03 1985-09-05 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Einrichtung zur verhinderung der ausbreitung von titanfeuer bei turbomaschinen, insbesondere gasturbinen- bzw. gasturbinenstrahltriebwerken
GB2245312B (en) * 1984-06-19 1992-03-25 Rolls Royce Plc Axial flow compressor surge margin improvement
CA1314486C (fr) * 1984-06-19 1993-03-16 Michael John Charles Waterman Methode d'amelioration de la reserve de pompage d'un compresseur a flux axial
US5059093A (en) * 1990-06-07 1991-10-22 United Technologies Corporation Compressor bleed port
US5203162A (en) 1990-09-12 1993-04-20 United Technologies Corporation Compressor bleed manifold for a gas turbine engine
JPH04132899A (ja) 1990-09-25 1992-05-07 Mitsubishi Heavy Ind Ltd 軸流送風機
DE69204861T2 (de) * 1991-01-30 1996-05-23 United Technologies Corp Ventilatorgehäuse mit Rezirculationskanälen.
US5327716A (en) 1992-06-10 1994-07-12 General Electric Company System and method for tailoring rotor tip bleed air
RU2034175C1 (ru) * 1993-03-11 1995-04-30 Центральный институт авиационного моторостроения им.П.И.Баранова Турбокомпрессор
US5431533A (en) 1993-10-15 1995-07-11 United Technologies Corporation Active vaned passage casing treatment
US5480284A (en) 1993-12-20 1996-01-02 General Electric Company Self bleeding rotor blade
US5562404A (en) 1994-12-23 1996-10-08 United Technologies Corporation Vaned passage hub treatment for cantilever stator vanes
US5607284A (en) 1994-12-29 1997-03-04 United Technologies Corporation Baffled passage casing treatment for compressor blades
US5474417A (en) 1994-12-29 1995-12-12 United Technologies Corporation Cast casing treatment for compressor blades
JP3816150B2 (ja) 1995-07-18 2006-08-30 株式会社荏原製作所 遠心流体機械
US5762034A (en) 1996-01-16 1998-06-09 Board Of Trustees Operating Michigan State University Cooling fan shroud
DE19632207A1 (de) 1996-08-09 1998-02-12 Bmw Rolls Royce Gmbh Verfahren zur Verhinderung der laminaren Grenzschicht-Ablösung an Turbomaschinen-Schaufeln
US6109868A (en) 1998-12-07 2000-08-29 General Electric Company Reduced-length high flow interstage air extraction
US6231301B1 (en) 1998-12-10 2001-05-15 United Technologies Corporation Casing treatment for a fluid compressor
US6574965B1 (en) 1998-12-23 2003-06-10 United Technologies Corporation Rotor tip bleed in gas turbine engines
US6290458B1 (en) 1999-09-20 2001-09-18 Hitachi, Ltd. Turbo machines
US6234747B1 (en) 1999-11-15 2001-05-22 General Electric Company Rub resistant compressor stage
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
US6663346B2 (en) 2002-01-17 2003-12-16 United Technologies Corporation Compressor stator inner diameter platform bleed system
EP1478857B1 (fr) * 2002-02-28 2008-04-23 MTU Aero Engines GmbH Compresseur avec moyens de traitement antiblocage d'extremites
DE10233032A1 (de) 2002-07-20 2004-01-29 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit integriertem Fluidzirkulationssystem
GB0216952D0 (en) 2002-07-20 2002-08-28 Rolls Royce Plc Gas turbine engine casing and rotor blade arrangement
DE10330084B4 (de) 2002-08-23 2010-06-10 Mtu Aero Engines Gmbh Rezirkulationsstruktur für Turboverdichter
WO2004018844A1 (fr) * 2002-08-23 2004-03-04 Mtu Aero Engines Gmbh Structure de recirculation d'un turbocompresseur
FR2846034B1 (fr) 2002-10-22 2006-06-23 Snecma Moteurs Carter, compresseur, turbine et turbomoteur a combustion comprenant un tel carter
GB2408546B (en) * 2003-11-25 2006-02-22 Rolls Royce Plc A compressor having casing treatment slots
DE10355240A1 (de) * 2003-11-26 2005-07-07 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit Fluidentnahme
DE10355241A1 (de) * 2003-11-26 2005-06-30 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit Fluidzufuhr
US7097414B2 (en) 2003-12-16 2006-08-29 Pratt & Whitney Rocketdyne, Inc. Inducer tip vortex suppressor
GB2413158B (en) 2004-04-13 2006-08-16 Rolls Royce Plc Flow control arrangement
DE102004030597A1 (de) 2004-06-24 2006-01-26 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit Aussenradstrahlerzeugung am Stator
DE102004043036A1 (de) * 2004-09-06 2006-03-09 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit Fluidentnahme
DE102004055439A1 (de) 2004-11-17 2006-05-24 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit dynamischer Strömungsbeeinflussung
US7861823B2 (en) 2005-11-04 2011-01-04 United Technologies Corporation Duct for reducing shock related noise
GB0600532D0 (en) 2006-01-12 2006-02-22 Rolls Royce Plc A blade and rotor arrangement
EP1862641A1 (fr) 2006-06-02 2007-12-05 Siemens Aktiengesellschaft Canal d'écoulement axial pour turbomachine
US20080044273A1 (en) 2006-08-15 2008-02-21 Syed Arif Khalid Turbomachine with reduced leakage penalties in pressure change and efficiency
FR2912789B1 (fr) 2007-02-21 2009-10-02 Snecma Sa Carter avec traitement de carter, compresseur et turbomachine comportant un tel carter.
US20090160135A1 (en) 2007-12-20 2009-06-25 Gabriele Turini Labyrinth seal with reduced leakage flow by grooves and teeth synergistic action

Also Published As

Publication number Publication date
EP2025945A2 (fr) 2009-02-18
US20090041576A1 (en) 2009-02-12
US8419355B2 (en) 2013-04-16
DE102007037924A1 (de) 2009-02-12
EP2025945A3 (fr) 2014-06-25

Similar Documents

Publication Publication Date Title
EP2025945B1 (fr) Machine de traitement des écoulements dotée d&#39;un creux de paroi de canal de ceinture
EP2096316B1 (fr) Structuration de boîtier pour compresseur axial dans la zone du moyeu
EP1632662B1 (fr) Turbomachine avec soutirage
EP2138727B1 (fr) Bande de recouvrement d&#39;aube dotée d&#39;un passage
EP2108784B1 (fr) Turbomachine dotée d&#39;un composant d&#39;injecteur de fluide
EP2003292B1 (fr) Machine de travail fluidique avec virole d&#39;aube dotée d&#39;un rebord
EP2110559B1 (fr) Turbomachine avec réinjection de fluide pour influencer la couche limite
EP2261463B1 (fr) Turbomachine avec groupe d&#39;étages aubagés
DE102007056953B4 (de) Strömungsarbeitsmaschine mit Ringkanalwandausnehmung
EP0916812B1 (fr) Etage final pour turbine axial
EP2275643B1 (fr) Aube de moteur dotée d&#39;une charge de rebords avant surélevée
EP2143956A2 (fr) Machine de traitement des écoulements dotée d&#39;une rainure sur la trajectoire d&#39;une extrémité d&#39;aube
EP1382855A2 (fr) Turbomachine avec système de recirculation de fluide intégré
EP1657401A2 (fr) Aube de turbomachine avec une augmentation de la longueur des chordes du profil dans ses régions extrêmes
EP1918529A2 (fr) Turbomachine avec aubes statoriques ajustables
DE102008037154A1 (de) Strömungsarbeitsmaschine
EP1609999A2 (fr) Turbo machine
EP2180195A2 (fr) Turbomachine avec contrôle du jeu des aubes
EP2913478B1 (fr) Aubes en tandem d&#39;une turbomachine
EP2947270B1 (fr) Groupe de série d&#39;aubes
EP2226510A2 (fr) Turbomachine de travail dotée d&#39;une arrivée de fluide
EP1998049A2 (fr) Aube de machine de travail d&#39;écoulement doté d&#39;une conception à plusieurs profiles
EP3078804A1 (fr) Agencement virole pour une rangée d&#39;aubes de rotor ou stator et turbine associée
EP1335136B1 (fr) Turbine à gaz ayant un compresseur muni d&#39;un système de guidage du flux traversant le canal d&#39;écoulement du compresseur le long des parois de ce canal
EP3369892B1 (fr) Contournage d&#39;une plate-forme de grille d&#39;aube

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MT NL NO PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA MK RS

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MT NL NO PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA MK RS

RIC1 Information provided on ipc code assigned before grant

Ipc: F04D 29/66 20060101ALI20140520BHEP

Ipc: F04D 29/16 20060101ALI20140520BHEP

Ipc: F04D 27/02 20060101AFI20140520BHEP

Ipc: F04D 29/52 20060101ALI20140520BHEP

17P Request for examination filed

Effective date: 20140716

RBV Designated contracting states (corrected)

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MT NL NO PL PT RO SE SI SK TR

AKX Designation fees paid

Designated state(s): DE FR GB

AXX Extension fees paid

Extension state: AL

Extension state: RS

Extension state: MK

Extension state: BA

17Q First examination report despatched

Effective date: 20150216

REG Reference to a national code

Ref country code: DE

Ref legal event code: R079

Ref document number: 502008014108

Country of ref document: DE

Free format text: PREVIOUS MAIN CLASS: F04D0027020000

Ipc: F04D0029520000

RIC1 Information provided on ipc code assigned before grant

Ipc: F04D 29/52 20060101AFI20150929BHEP

Ipc: F04D 29/68 20060101ALI20150929BHEP

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20151113

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502008014108

Country of ref document: DE

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 9

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502008014108

Country of ref document: DE

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20170123

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 10

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 11

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20190729

Year of fee payment: 12

Ref country code: FR

Payment date: 20190725

Year of fee payment: 12

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20190729

Year of fee payment: 12

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 502008014108

Country of ref document: DE

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502008014108

Country of ref document: DE

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20200731

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200731

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200731

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210202