US3846038A - Fixed blading of axial compressors - Google Patents

Fixed blading of axial compressors Download PDF

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Publication number
US3846038A
US3846038A US00314965A US31496572A US3846038A US 3846038 A US3846038 A US 3846038A US 00314965 A US00314965 A US 00314965A US 31496572 A US31496572 A US 31496572A US 3846038 A US3846038 A US 3846038A
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United States
Prior art keywords
suction opening
fluid
fixed
passage
suction
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Expired - Lifetime
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US00314965A
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English (en)
Inventor
P Carriere
J Leynaert
G Meauze
J Thibert
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Office National dEtudes et de Recherches Aerospatiales ONERA
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Office National dEtudes et de Recherches Aerospatiales ONERA
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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
    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
    • F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S415/00—Rotary kinetic fluid motors or pumps
    • Y10S415/914—Device to control boundary layer

Definitions

  • ABSTRACT Fixed blading for an axial compressor constituted by a succession of blades fixed on at least one annular wall and a method of operating the same. Fluid passing through a passage between adjacent blades is drawn into a suction opening and the pressure at the suction opening is maintained substantially equal to the flow static pressure in the passage.
  • the invention relates to fixed blading for axial compressors, such fixed blading being constituted by arrays of blades each comprising a succession of blades borne by an annular lateral wall, or interposed between two annular lateral walls, this or these annular lateral walls extending transversely between the blades of the array of blades.
  • the present invention also relates to a method of operating such an axial compressor.
  • suctionopenings arranged between two successive blades and connected to aspirating means; these suction openings enabling the reduction of disturbances due to the boundary layer which is developed on this or these annular lateral walls.
  • each suction opening has elongated shape and extends over the whole width of the passage defined by two successive blades, between an under surface region or intrados (side subjected to increased pressure) of a blade situated towards the leading edge and a back surface region or extrados (side subjected to reduced pressure) of the following blade situated at one half or preferably one third of its length, from its leading edge.
  • the suction means are arranged so that the pressure at the level of the suction openings is of the same order of magnitude that is to say substantially equal to the static pressure of the local flow in the passage concerned.
  • the invention further relates to a method for operat- 7 ing such an axial compressor wherein fluid aspired through the passages between adjacent blades is maintained at a pressure substantially equal to the flow static pressure in the passage.
  • FIG. 1 shows a partial diagrammatic perspective view of fixed blading for an axial compressor, constructed in conventional manner, and in which there are shown by various arrows the flow disturbed by the boundary layer which is developed on the annular lateral wall.
  • FIG. 2 shows, under the same conditions, this fixed blading constructed according to the invention and in which the flow represented by the various arrows is perfectly bidimensional.
  • FIG. 3 is a partially developed view of fixed blading constructed according to the invention.
  • FIG. 4 is a diagrammatic section along the line lV-IV of FIG. 3.
  • the fixed blading shown in FIGS. I and 2 is constituted by an array of blades comprising a succession of blades 1 borne by an annular lateral wall 2 on which said blades 1 are fixed by one of their two ends.
  • annular lateral wall 2 For clarity of the drawing there is shown a single annular lateral wall, but the blades can also be interposed between two concentric annular lateral walls.
  • FIG. 1 there is involved conventional fixed blading and the boundary layer which is developed on the annular lateral wall 2 causes disturbances of flow in the passages defined by two successive blades; these disturbances are constituted by detachments and vortexes which create an artificial convergence of the flow into the abovesaid passages.
  • suction opening 3 there is formed in the annular lateral wall 2 or in the two concentric annular lateral walls a suction opening 3 connected to suction means.
  • this suction opening 3 has elongated shape and extends over the whole width of the passage defined by two successive blades, between an under surface region of one blade situated towards its leading edge and a back surface region of the following blade situated at half or preferably one third of its length, from its leading edge.
  • the shape of the suction opening 3 is elongated and oriented parallel to the isobars of the local pressure field and that the arrangement of the suction opening 3 is such that said suction opening 3 occurs in the passage concerned, in a region where the pressure gradients reach maximal values.
  • suction means which will be more explicitly considered below it can be arranged so that the pressure at the level of the suction openings is of the same order of magnitude as the static pressure of the local-flow in the passage concerned.
  • the flow in the fixed blading constructed according to the invention, has a bidimensional character over all of the blades, given that the boundry layer on the annular lateral wall 2 has been trapped and that the detachments and vortexes have been eliminated.
  • FIG. 3 there is shown a partial view of a planar gigg'egtion of the fixed blading shown in perspective in
  • the suction opening 3 has a rounded shape
  • the suction opening 3 has a shape matching the airfoil of the blade. From the constructional point of view, the suction opening 3 can be extended below the latter blade beyond its back surface, the corresponding edge of this suction opening 3 then being bounded by the fraction of the back surface of the blade situated above the said suction opening.
  • FIG. 4 there is shown in axial section the fixed blading of FIG. 3, the rotor of the compressor being denoted by the reference numeral A and the two movable blade assemblies of the compressor, surrounding the fixed blade assembly according to the invention, being denoted by the reference numerals B and B respectively.
  • the suction opening 3 can include an upstream edge 3a perpendicular to the annular lateral wall 2 in which it is formed, and a downstream edge 3b oblique and forming an acute angle with the abovesaid wall. This arrangement facilitates the suction of the boundary layer.
  • suction means they can be of different natures according to the conditions of use of the compressor.
  • suction means can be servocoupled, as regards the value of the flow aspirated, to various characteristics of the compressor.
  • they can be servocoupled to the rotary speed so that the ratio of the flow aspirated to the flow of the stream passing through the compressor remains constant.
  • suction means can, as shown in FIG. 4, comprise a buffer space 13 from which the aspirated fluid is evacuated by means of a restricting device comprising, for example, a fixed constriction 14 and/or a regulating valve '15.
  • This regulating valve 15 can then be governed by a regulator 16 acting as a function, on one hand, of the static pressure of the flow upstream of the fixed blade assembly (which static pressure can be transmitted through an aperture 17 formed in a suitable place of the compressor) and, on the other hand, of the static through the suction opening, said suction means including means for maintaining the pressure in the suction opening substantially equal to the flow static pressure in the said passage.
  • each suction opening comprises an upstream edge perpendicular to the annular lateral wall and an oblique downstream edge forming an acute angle with the abovesaid annular lateral wall.
  • each suction opening comprises a porous or perforated wall arranged to limit the aspirated flow-rate.
  • An aircraft turboreactor axial compressor comprising fixed blading according to claim 1.
  • said suction means including means for maintaining constant the ratio of the flow rate of the fluid aspired through the said suction opening to the flow rate of the fluid flowing through the said passage.
  • said suction means including a regulator device operatively connected to the suction opening to regulate the suction pressure as a function of a particular pressure of the suction pressure (static pressure transmitted by an aperture 18 formed in the buffer space 13).
  • a porous or perforated wall 19 (shown in mixed line in FIG. 4), arranged in the suction opening 3 and limiting the flowrate of aspiration.
  • the flow of fluid aspirated by the group of suction openings 3 can be ejected to the atmosphere, or advantageously be used for other purposes.
  • the fluid sucked into the fixed blade assembly can also be reinjected further upstream into the compressor by means of a suitable device arranged to obtain a blast or parietal effect with a view to reabsorbing possible by a succession of blades fixed on at least one annular wall, each passage between two adjacent blades being provided with a suction opening, suction means associated with said suction opening for aspiring fluid flow passing through the passage.
  • Fixed blading according to claim 1, including means for exhausting to the atmosphere the fluid aspirated through the suction opening.
  • Fixed blading according to claim 1, including means for delivering the fluid aspired through the suction opening to at least one other stage of the compressor situated upstream from said fixed blading for producing thereat a control effect on the boundary layer by a blast effect.
  • said suction opening having an elongated shape extending across the whole width of said passage between an undersurface region of one blade situated towards its leading edge and a back surface region of the following blade situated in the first half of its length from its leading edge.
  • suction opening extends between an undersurface region of a blade situated towards its leading edge and a back surface region of the following blade situated about two thirds of its length from its leading edge.
  • said suction means including a buffer space adjacent the suction opening for receiving the fluid passing therethrough.
  • Fixed blading including an exhaust means for controllably delivering fluid out of said buffer space, and means responsive to the flow static pressure in the passage and to the pressure in the buffer space for controlling the flow rate through the exhaust means.
  • a method of operating an axial compressor of the type constituted by a succession of fixed blades fixed on at least one annular wall of the compressor comprising the steps of:

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US00314965A 1971-12-27 1972-12-14 Fixed blading of axial compressors Expired - Lifetime US3846038A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7146854A FR2166494A5 (de) 1971-12-27 1971-12-27

Publications (1)

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US3846038A true US3846038A (en) 1974-11-05

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US (1) US3846038A (de)
CH (1) CH561844A5 (de)
FR (1) FR2166494A5 (de)
GB (1) GB1408014A (de)

Cited By (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3930742A (en) * 1973-10-23 1976-01-06 Howell Instruments, Inc. Velocity probe for compressor surge control
US3951566A (en) * 1973-12-11 1976-04-20 Electricite De France (Service National) Axial-flow fan with by-pass pipe or pipes
US4082477A (en) * 1974-11-06 1978-04-04 United Turbine Ab & Co. Compressor having two or more stages
US4534701A (en) * 1982-06-29 1985-08-13 Gerhard Wisser Rotor or guide wheel of a turbine engine with shroud ring
US4540335A (en) * 1980-12-02 1985-09-10 Mitsubishi Jukogyo Kabushiki Kaisha Controllable-pitch moving blade type axial fan
US4673330A (en) * 1984-09-21 1987-06-16 Kamyr Ab Method for control of the function of a centrifugal pump
US5020970A (en) * 1989-07-13 1991-06-04 Dresser-Rand Company Fluid-handling, bladed rotor
US5232338A (en) * 1990-09-13 1993-08-03 Gec Alsthom Sa Blade array for turbomachines comprising suction ports in the inner and/or outer wall and turbomachines comprising same
US5431533A (en) * 1993-10-15 1995-07-11 United Technologies Corporation Active vaned passage casing treatment
US6428271B1 (en) 1998-02-26 2002-08-06 Allison Advanced Development Company Compressor endwall bleed system
US6579061B1 (en) * 2001-07-27 2003-06-17 General Electric Company Selective step turbine nozzle
EP1536146A2 (de) 2003-11-26 2005-06-01 Rolls-Royce Deutschland Ltd & Co KG Strömungsarbeitsmaschine mit Fluidentnahme
US20050141990A1 (en) * 2003-11-26 2005-06-30 Volker Guemmer Turbomachine wtih fluid supply
EP1632662A2 (de) 2004-09-06 2006-03-08 Rolls-Royce Deutschland Ltd & Co KG Strömungsarbeitsmaschine mit Fluidentnahme
FR2875866A1 (fr) * 2004-09-30 2006-03-31 Snecma Moteurs Sa Procede de circulation d'air dans un compresseur de turbomachine, agencement de compresseur le mettant en oeuvre , etage de compression et compresseur comportant un tel agencement, et moteur d'aeronef equipe d'un tel compresseur
US20060104805A1 (en) * 2004-06-24 2006-05-18 Volker Gummer Turbomachine with means for the creation of a peripheral jet on the stator
US20060153673A1 (en) * 2004-11-17 2006-07-13 Volker Guemmer Turbomachine exerting dynamic influence on the flow
US20080199306A1 (en) * 2007-02-21 2008-08-21 Snecma Turbomachine casing with treatment, a compressor, and a turbomachine including such a casing
FR2912790A1 (fr) * 2007-02-16 2008-08-22 Snecma Sa Agencement de circuits de prelevement d'air,etage de compresseur le comportant,compresseur les comportant et turboreacteur les comportant
US20090000306A1 (en) * 2006-09-14 2009-01-01 Damle Sachin V Stator assembly including bleed ports for turbine engine compressor
US20090041576A1 (en) * 2007-08-10 2009-02-12 Volker Guemmer Fluid flow machine featuring an annulus duct wall recess
US20090246007A1 (en) * 2008-02-28 2009-10-01 Erik Johann Casing treatment for axial compressors in a hub area
US20100014956A1 (en) * 2008-07-07 2010-01-21 Rolls-Royce Deutschland Ltd & Co Kg Fluid flow machine featuring a groove on a running gap of a blade end
US20100098530A1 (en) * 2008-10-20 2010-04-22 Rolls-Royce Deutschland Ltd & Co Kg Compressor for a gas turbine
US8382422B2 (en) 2008-08-08 2013-02-26 Rolls-Royce Deutschland Ltd & Co Kg Fluid flow machine
US20140093355A1 (en) * 2012-09-28 2014-04-03 United Technologies Corporation Extended indentation for a fastener within an air flow
US8834116B2 (en) 2008-10-21 2014-09-16 Rolls-Royce Deutschland Ltd & Co Kg Fluid flow machine with peripheral energization near the suction side
US20170276141A1 (en) * 2016-03-28 2017-09-28 General Electric Company Compressor bleed systems in turbomachines and methods of extracting compressor airflow
US20190301301A1 (en) * 2018-04-02 2019-10-03 General Electric Company Cooling structure for a turbomachinery component
US20200165969A1 (en) * 2018-11-23 2020-05-28 Pratt & Whitney Canada Corp. Fan assembly having flow recirculation circuit with guide vanes
US11466578B2 (en) 2018-06-15 2022-10-11 Safran Aircraft Engines Turbine nozzle for a turbine engine, comprising a passive system for reintroducing blow-by gas into a gas jet
US11473435B2 (en) 2018-06-15 2022-10-18 Safran Aircraft Engines Turbine vane comprising a passive system for reducing vortex phenomena in an air flow flowing over said vane

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP4195882B2 (ja) * 2003-04-18 2008-12-17 オレグ ナリオトフ 軸流フロー流体機械
FR2958694B1 (fr) 2010-04-07 2014-04-18 Snecma Compresseur de moteur, en particulier de turboreacteur d'aeronef, muni d'un systeme de prelevement d'air
GB201710076D0 (en) * 2017-06-23 2017-08-09 Rolls Royce Plc Secondary flow control

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GB504214A (en) * 1937-02-24 1939-04-21 Rheinmetall Borsig Ag Werk Bor Improvements in and relating to turbo compressors
US2291828A (en) * 1940-05-04 1942-08-04 Westinghouse Electric & Mfg Co Turbine blading
GB619722A (en) * 1946-12-20 1949-03-14 English Electric Co Ltd Improvements in and relating to boundary layer control in fluid conduits
US2656096A (en) * 1946-01-04 1953-10-20 Rateau Soc Centrifugal pump and compressor
US2682363A (en) * 1950-12-08 1954-06-29 Rolls Royce Gas turbine engine
US2720356A (en) * 1952-06-12 1955-10-11 John R Erwin Continuous boundary layer control in compressors

Patent Citations (6)

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Publication number Priority date Publication date Assignee Title
GB504214A (en) * 1937-02-24 1939-04-21 Rheinmetall Borsig Ag Werk Bor Improvements in and relating to turbo compressors
US2291828A (en) * 1940-05-04 1942-08-04 Westinghouse Electric & Mfg Co Turbine blading
US2656096A (en) * 1946-01-04 1953-10-20 Rateau Soc Centrifugal pump and compressor
GB619722A (en) * 1946-12-20 1949-03-14 English Electric Co Ltd Improvements in and relating to boundary layer control in fluid conduits
US2682363A (en) * 1950-12-08 1954-06-29 Rolls Royce Gas turbine engine
US2720356A (en) * 1952-06-12 1955-10-11 John R Erwin Continuous boundary layer control in compressors

Cited By (57)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3930742A (en) * 1973-10-23 1976-01-06 Howell Instruments, Inc. Velocity probe for compressor surge control
US3951566A (en) * 1973-12-11 1976-04-20 Electricite De France (Service National) Axial-flow fan with by-pass pipe or pipes
US4082477A (en) * 1974-11-06 1978-04-04 United Turbine Ab & Co. Compressor having two or more stages
US4540335A (en) * 1980-12-02 1985-09-10 Mitsubishi Jukogyo Kabushiki Kaisha Controllable-pitch moving blade type axial fan
US4534701A (en) * 1982-06-29 1985-08-13 Gerhard Wisser Rotor or guide wheel of a turbine engine with shroud ring
US4673330A (en) * 1984-09-21 1987-06-16 Kamyr Ab Method for control of the function of a centrifugal pump
US5020970A (en) * 1989-07-13 1991-06-04 Dresser-Rand Company Fluid-handling, bladed rotor
US5232338A (en) * 1990-09-13 1993-08-03 Gec Alsthom Sa Blade array for turbomachines comprising suction ports in the inner and/or outer wall and turbomachines comprising same
US5431533A (en) * 1993-10-15 1995-07-11 United Technologies Corporation Active vaned passage casing treatment
US6428271B1 (en) 1998-02-26 2002-08-06 Allison Advanced Development Company Compressor endwall bleed system
US6579061B1 (en) * 2001-07-27 2003-06-17 General Electric Company Selective step turbine nozzle
US20030113206A1 (en) * 2001-07-27 2003-06-19 Heyward John Peter Selective step turbine nozzle
US7364404B2 (en) 2003-11-26 2008-04-29 Rolls-Royce Deutschland Ltd & Co Kg Turbomachine with fluid removal
EP1536146A3 (de) * 2003-11-26 2008-04-02 Rolls-Royce Deutschland Ltd & Co KG Strömungsarbeitsmaschine mit Fluidentnahme
DE10355240A1 (de) * 2003-11-26 2005-07-07 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit Fluidentnahme
US20050238483A1 (en) * 2003-11-26 2005-10-27 Volker Guemmer Turbomachine with fluid removal
EP2226509A3 (de) * 2003-11-26 2011-06-08 Rolls-Royce Deutschland Ltd & Co KG Strömungsarbeitsmaschine mit Fluidzufuhr zur Grenzschichtbeeinflussung
US20050141990A1 (en) * 2003-11-26 2005-06-30 Volker Guemmer Turbomachine wtih fluid supply
EP1536146A2 (de) 2003-11-26 2005-06-01 Rolls-Royce Deutschland Ltd & Co KG Strömungsarbeitsmaschine mit Fluidentnahme
US7387487B2 (en) 2003-11-26 2008-06-17 Rolls-Royce Deutschland Ltd & Co Kg Turbomachine with fluid supply
US7967556B2 (en) * 2004-06-24 2011-06-28 Rolls-Royce Deutschland Ltd & Co Kg Turbomachine with means for the creation of a peripheral jet on the stator
US20060104805A1 (en) * 2004-06-24 2006-05-18 Volker Gummer Turbomachine with means for the creation of a peripheral jet on the stator
US20060051199A1 (en) * 2004-09-06 2006-03-09 Volker Guemmer Turbomachine with fluid removal
US7594793B2 (en) 2004-09-06 2009-09-29 Rolls-Royce Deutschland Ltd & Co Kg Turbomachine with fluid removal
EP1632662A3 (de) * 2004-09-06 2008-10-01 Rolls-Royce Deutschland Ltd & Co KG Strömungsarbeitsmaschine mit Fluidentnahme
EP1632662A2 (de) 2004-09-06 2006-03-08 Rolls-Royce Deutschland Ltd & Co KG Strömungsarbeitsmaschine mit Fluidentnahme
US20060222485A1 (en) * 2004-09-30 2006-10-05 Snecma Method for air circulation in a turbomachine compressor, compressor arrangement using this method, compression stage and compressor incorporating such a arrangement, and aircraft engine equipped with such a compressor
EP1643136A1 (de) * 2004-09-30 2006-04-05 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Verfahren zur Luftzirkulation für Turbokompressoren
FR2875866A1 (fr) * 2004-09-30 2006-03-31 Snecma Moteurs Sa Procede de circulation d'air dans un compresseur de turbomachine, agencement de compresseur le mettant en oeuvre , etage de compression et compresseur comportant un tel agencement, et moteur d'aeronef equipe d'un tel compresseur
US7581920B2 (en) 2004-09-30 2009-09-01 Snecma Method for air circulation in a turbomachine compressor, compressor arrangement using this method, compression stage and compressor incorporating such a arrangement, and aircraft engine equipped with such a compressor
US20060153673A1 (en) * 2004-11-17 2006-07-13 Volker Guemmer Turbomachine exerting dynamic influence on the flow
US8262340B2 (en) 2004-11-17 2012-09-11 Rolls-Royce Deutschland Ltd Co KG Turbomachine exerting dynamic influence on the flow
US20090000306A1 (en) * 2006-09-14 2009-01-01 Damle Sachin V Stator assembly including bleed ports for turbine engine compressor
US8292567B2 (en) * 2006-09-14 2012-10-23 Caterpillar Inc. Stator assembly including bleed ports for turbine engine compressor
EP1959145A3 (de) * 2007-02-16 2010-07-21 Snecma Anordnung von Luftentnahme-Schaltkreisen einer Kompressorstufe
FR2912790A1 (fr) * 2007-02-16 2008-08-22 Snecma Sa Agencement de circuits de prelevement d'air,etage de compresseur le comportant,compresseur les comportant et turboreacteur les comportant
US8147184B2 (en) 2007-02-16 2012-04-03 Snecma Air intake circuit arrangement for high pressure compressor of a turbine engine
US8100629B2 (en) * 2007-02-21 2012-01-24 Snecma Turbomachine casing with treatment, a compressor, and a turbomachine including such a casing
US20080199306A1 (en) * 2007-02-21 2008-08-21 Snecma Turbomachine casing with treatment, a compressor, and a turbomachine including such a casing
US8419355B2 (en) 2007-08-10 2013-04-16 Rolls-Royce Deutschland Ltd & Co Kg Fluid flow machine featuring an annulus duct wall recess
US20090041576A1 (en) * 2007-08-10 2009-02-12 Volker Guemmer Fluid flow machine featuring an annulus duct wall recess
US20090246007A1 (en) * 2008-02-28 2009-10-01 Erik Johann Casing treatment for axial compressors in a hub area
US8251648B2 (en) 2008-02-28 2012-08-28 Rolls-Royce Deutschland Ltd & Co Kg Casing treatment for axial compressors in a hub area
US20100014956A1 (en) * 2008-07-07 2010-01-21 Rolls-Royce Deutschland Ltd & Co Kg Fluid flow machine featuring a groove on a running gap of a blade end
US8257022B2 (en) 2008-07-07 2012-09-04 Rolls-Royce Deutschland Ltd Co KG Fluid flow machine featuring a groove on a running gap of a blade end
US8382422B2 (en) 2008-08-08 2013-02-26 Rolls-Royce Deutschland Ltd & Co Kg Fluid flow machine
US20100098530A1 (en) * 2008-10-20 2010-04-22 Rolls-Royce Deutschland Ltd & Co Kg Compressor for a gas turbine
US8834116B2 (en) 2008-10-21 2014-09-16 Rolls-Royce Deutschland Ltd & Co Kg Fluid flow machine with peripheral energization near the suction side
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Also Published As

Publication number Publication date
FR2166494A5 (de) 1973-08-17
GB1408014A (en) 1975-10-01
CH561844A5 (de) 1975-05-15

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