EP2917590B1 - Assemblage de compression pour turbomachine - Google Patents

Assemblage de compression pour turbomachine Download PDF

Info

Publication number
EP2917590B1
EP2917590B1 EP13795842.7A EP13795842A EP2917590B1 EP 2917590 B1 EP2917590 B1 EP 2917590B1 EP 13795842 A EP13795842 A EP 13795842A EP 2917590 B1 EP2917590 B1 EP 2917590B1
Authority
EP
European Patent Office
Prior art keywords
air
rotation
vanes
duct
grille
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP13795842.7A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP2917590A1 (fr
Inventor
Jean-François Escuret
Pierre Biscay
Guillaume SEVESTRE
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.)
Safran Helicopter Engines SAS
Original Assignee
Safran Helicopter Engines SAS
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 Safran Helicopter Engines SAS filed Critical Safran Helicopter Engines SAS
Priority to PL13795842T priority Critical patent/PL2917590T3/pl
Publication of EP2917590A1 publication Critical patent/EP2917590A1/fr
Application granted granted Critical
Publication of EP2917590B1 publication Critical patent/EP2917590B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

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
    • F01D7/00—Rotors with blades adjustable in operation; Control thereof
    • 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
    • F04D29/544—Blade shapes
    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles

Definitions

  • the invention relates to the field of turbomachines, in particular for aircraft.
  • the invention more particularly relates to a compression assembly for a turbomachine, in particular for a helicopter turbine engine, and a turbomachine equipped with such an assembly.
  • a turbine engine comprises, in known manner, a compression assembly comprising an air inlet duct and at least one air compression stage, or compressor, which comprises at least one mobile compressor wheel on which the duct opens.
  • Such compression assemblies have an aerodynamic stability limit, commonly known as a pumping line, which limits in particular the acceleration capabilities of the turbine engine. At low operating speeds, the aerodynamic stability limit of the compression assembly is related to an aerodynamic overload of the first compression stage, which results in too high incidences of the air flow reaching the first moving wheel.
  • a known solution described in the patent application FR2970508 filed by the Applicant, consists in mounting a gate, said pre-rotation, in the air intake duct of the turbine engine upstream of the first mobile wheel of the compressor to reduce the incidence of the air flow reaching said first moving wheel by orienting it in the direction of rotation of the first moving wheel.
  • Such a pre-rotation grid comprises steerable, variable-pitch inlet guide vanes mounted on a casing and equidistributed in the air intake duct.
  • the setting of the gate that is to say the orientation of the blades, is effected via a control ring and allows to regulate the speed of the air flow at the inlet of the impeller so as to adapt the incidence of airflow reaching the first moving wheel.
  • a known arrangement of such a pre-rotation grid is to arrange the blades of the grid so that the pre-rotation angle of the blades and thus the orientation angle of the airflow is scalable according to the height in the air duct, the airflow orientation angle being defined as the relative deviation of the airflow by a blade of the pre-rotation grid to a given height of the air duct.
  • the angle of orientation of the air flow varies with the radial distance in the air inlet duct relative to the axis of the turbine engine.
  • FIGS 1 to 3 illustrate a diagrammatic cross-sectional view at the head of an arrangement of two blades 10 of a pre-rotation grid 5 and two blades 20 of a compressor moving wheel 15 of the prior art.
  • the consecutive blades 10 of the grid 5 are spaced apart by a distance S1 called "pitch".
  • Each blade 10 has a curved section and defines a rope C1 between the upstream end and the downstream end of the blades 10, that is to say between the leading edge and the trailing edge of the blade 10.
  • pre-rotation angle of the blades 10 of the gate 5 is usually between values of the order of 0 ° at the bottom of the air duct and up to about 15 ° at the top of the air duct (relative to to the axis X'X).
  • the flow of air F entering the grid is then deviated by an angle of orientation ⁇ 1 close to the pre-rotation angle of the blades and between 0 ° to 15 ° according to the height in the air duct with an absolute speed V 1 at the gate exit whose axial component (along the axis X'X) is Vz1.
  • Such calibration of the grid 5 is used for the high operating speeds of the compressor, especially in maximum operating conditions, for example, in the take-off mode in the case of a helicopter turbine engine.
  • the gate 5 is at least partially closed in order to reduce the aerodynamic load and to increase the pumping margin by shifting the compressor pumping line to the low flow rates while shifting the operating line towards the high flow rates, which allows to obtain a large capacity of acceleration of the turbine engine.
  • the control ring (not shown) of the pre-rotation grid 5 is usually set to a value, for example about 65 °, for which the pre-rotation angle of the blades 10 of the grid 5 is between 65 ° and 80 ° depending on the height of the flow in the air duct.
  • the pre-rotation angle of the blades reaches values of the order of 85 ° at the top of the air duct, that is to say that the flow of air is deflected from an orientation angle ⁇ 1 close to about 85 ° by the blades 10 in the highest part of the duct, in particular at the distal end of the blades 10.
  • the air flow at the outlet of the pre-rotation grid 5 at the top of the air duct becomes so low that it can cause an aerodynamic malfunction of the blades 20 of the mobile wheel 15 of the compressor.
  • the air boundary layers no longer hold on the shape of the blade head profiles 20 of the impeller 15, which can lead to aerodynamic detachment within the impeller 15, commonly known as detachment rotating, detrimental to the aerodynamic stability of the compressor, and therefore has a disadvantage.
  • the aim of the invention is to improve the structure of the existing pre-rotation gates by increasing the pre-rotation angle of the blades above 15 ° at the top of the air duct at high operating speed of the turbine engine while avoiding the aerodynamic malfunctions of the blades of the moving wheel at low operating speed of the turbine engine.
  • turbomachine comprising a pre-rotation grid such as exists in the turboshaft engines, turbojets, auxiliary power units.
  • auxiliary power units Auxiliary Power Unit or APU in English
  • land-based turbomachines land-based turbomachines
  • turbochargers turbochargers etc.
  • compressors any type of compressor that is axial, centrifugal, mixed etc.
  • the subject of the invention is a compression assembly for a turbomachine, in particular a turbine engine, according to claim 1.
  • pitch means the distance between two identical points of two blades of the grid arranged consecutively.
  • rope is meant the distance of the segment extending between the upstream end and the downstream end of a blade of the pre-rotation grid, that is to say between the end of the edge of the attack and the end of the trailing edge of a blade of the pre-rotation grid.
  • upstream and downstream is meant in relation to the direction of the flow of air flowing in the turbomachine.
  • the pitch between two consecutive blades is greater than the rope of one of the two blades in the upper part of the air duct, for example at the distal ends of said blades.
  • upper part of the air duct is meant that part of the air duct furthest radially from the longitudinal axis of the turbine engine.
  • at the top of the air duct is meant the distal end of the blade with respect to the longitudinal axis of the turbine engine.
  • lower part of the duct is the portion of the duct closest to the longitudinal axis of the turbine engine.
  • at the bottom of the air duct is meant the proximal end of the blade with respect to the longitudinal axis of the turbine engine.
  • the pitch between the distal ends of two consecutive blades of the pre-rotation grid was equal to or less than the string of a blade of the grid.
  • the ratio of the pitch on the string (S1 / C1) took values between 0.9 and 1.
  • the pitch between two consecutive blades of the gate being greater than the rope of one of the two blades, the blades do not overlap in the closed position of the grid as in the solutions of the prior art, which allows the use of blades whose pre-rotation angle is greater than 15 ° in the upper part of the air duct at high operating speeds of the compressor stage (with very stable open of the pre-rotation grid) while allowing efficient aerodynamic operation of the mobile wheel of the compressor at low speeds (with very closed wedges of the pre-rotation grid).
  • the pre-rotation angle of the blades is greater than 15 ° in the upper part of the air duct, in particular at their distal ends, preferably between 15 ° and 25 °, when the pre-rotation grid is in the open position of operation at high speeds of the compression stage, for example for a setting value of the gate control ring of 0 °.
  • the pre-rotation angle of the blades is between 80 ° and 90 ° in the upper part of the air duct, in particular at their distal ends, when the pre-rotation grid is in the closed position of operating at low speeds of the compression stage, for example for a setting value of the gate control ring of 65 °.
  • the spacing of the blades in the closed position of the grid makes it possible to obtain an axial speed of the air flow greater than the axial velocity of the flux in a assembly of the prior art for the same setting of the control ring of the pre-rotation grid.
  • the spacing of the blades makes it possible to increase the axial speed of the flow of air passing through the pre-rotation grid, in particular with very closed wedges, so as to avoid aerodynamic malfunctions of the blades of the wheel. mobile compressor.
  • the blades of the gate extend radially with respect to the axis of the turbomachine and are configured so that the pre-rotation angle of the blades of the pre-rotation gate changes in the duct. air with radial distance.
  • the blades can be twisted, for example.
  • the pre-rotation angle is approximately equal to 0 ° at the bottom of the air duct, that is to say as close as radially to the axis of the turbine engine, and of the order of 25 ° at the top of the air duct, that is to say at most radially from the axis of the turbine engine, for a setting value of the gate control ring of 0 °.
  • the blade string is constant among the plurality of blades of the pre-rotation grid.
  • the pre-rotation grid is positioned in a radial portion, a bend or an axial portion of the air intake duct.
  • the terms "radial portion” and “axial portion” meaning in relation to the axis of the turbomachine.
  • the blades are arranged equidistributed in the air inlet duct.
  • the pitch between the blades of the grid is constant.
  • the invention also relates to a turbomachine according to claim 7, such as, for example, a turbine engine, particularly for an aircraft such as, for example, a helicopter, comprising an air inlet duct adapted to receive a flow of air.
  • a turbomachine such as, for example, a turbine engine, particularly for an aircraft such as, for example, a helicopter, comprising an air inlet duct adapted to receive a flow of air.
  • air at least one air compression stage comprising at least one mobile compressor wheel on which the duct opens and a pre-rotation grille, positioned in the air intake duct upstream of the mobile compressor wheel for regulating the air speed of said flow at the inlet of the moving wheel and comprising a plurality of variable-pitch blades, the assembly being remarkable in that the pitch between two consecutive blades of the gate is greater than the rope of one of the two blades at a given height, preferably in the upper part, of the air duct.
  • the invention also relates to a method for controlling a pre-rotation grid of a compression assembly, as defined in claim 8, comprising an air intake duct adapted to receive a flow of air, at least one air compression stage comprising at least one mobile compressor wheel on which the duct opens and a pre-rotation grille, positioned in the air intake duct upstream of the mobile compressor wheel for regulating the air speed of said flow at the inlet of the moving wheel and comprising a plurality of variable pitch blades, the method being remarkable in that, the pitch between two consecutive blades of the gate being greater than the rope of one of the two blades at a given height of the air duct, preferably in its upper part in particular at their distal ends, is positioned the blades of the grid at a pre-rotation angle between 80 ° and 90 ° at low speeds of functioning of the compression stage.
  • the invention also relates to a method for controlling a pre-rotation grid of a compression assembly, as defined above, comprising an air intake duct adapted to receive an air flow, at the least one air compression stage comprising at least one mobile compressor wheel on which the duct opens and a pre-rotation grille, positioned in the air inlet duct upstream of the mobile compressor wheel to regulate the air speed of said flow at the inlet of the moving wheel and comprising a plurality of variable-pitch blades, the method being remarkable in that, the pitch between two consecutive blades of the gate being greater than the rope of one of the two blades at a given height of the air duct, preferably in its upper part, particularly at their distal ends, the blades of the grid are positioned at a pre-rotation angle greater than 15 °, preferably between 15 ° and 25 °, to ha Operating modes of the compression stage.
  • the invention further relates to any type of compressor that is axial, centrifugal, mixed etc.
  • the compression assembly of a turbomachine comprises an air intake duct adapted to receive an air flow, an air compression stage comprising a mobile compressor wheel on which the duct opens and a pre-rotation grid.
  • the pre-rotation grid is positioned in the air intake duct upstream of the mobile compressor wheel to straighten the upstream air flow which is directed towards the moving wheel and regulate the speed at the inlet of the wheel mobile.
  • the gate comprises a plurality of variable-pitch blades extending radially with respect to the axis of the turbomachine and arranged in the same transverse plane perpendicular to the axis of the turbomachine.
  • the air enters the air inlet duct, passes through the pre-rotation grid and is conveyed to the compressor impeller.
  • the flow of compressed air by the mobile compressor wheel is then injected into a combustion chamber to be mixed with the fuel and to provide, after combustion, the kinetic energy for rotating one or more turbines.
  • turbomachine may further comprise other compression stages arranged between the first compression stage and the combustion chamber.
  • FIGS. 4 and 5 illustrate in the arrangement of two blades 110 of a pre-rotation grid 105 according to the invention.
  • Control means (not shown) of the grid of pre-rotation 105 allow to orient the blades 110 of the gate 105 according to an opening / closing law of the blades 110 which depends on the rotational speed of the turbomachine.
  • Such a calibration law is set to guarantee a minimum pumping margin between the operating line and the pumping line.
  • the blades 110 of the grid 105 are spaced apart by a pitch S2 and have, between their upstream and downstream end, that is to say between the leading edge and the trailing edge, a curvature defining a rope C2.
  • the pre-rotation gate 105 is arranged upstream, in the overall direction of the air flow F, the blades 120 of the mobile wheel 115 of the compressor.
  • the moving wheel 115 is rotated according to the speed vector U so as to accelerate the flow of air deflected by the pre-rotation grid.
  • the pitch S2 between two consecutive blades 110 of the grid 5 is greater than the rope C2 of the blades 110 of the grid 5 at the top of the air duct so that the blades 110 do not overlap in the closed position of the grid 105.
  • the ratio of the pitch S2 on the chord C2, that is to say the parameter S2 / C2, can take values comprised between 1 and 1.5.
  • pre-rotation angle values of the air flow a2 between 15 ° and 25 ° at the top of the air duct make it possible to significantly reduce the relative speed. W2 air inlet of the impeller 115 and thus very substantially improve the efficiency of the compression stage.
  • the spacing of the blades 110 of the grid 105 allows, despite pre-rotation angle values of the blades between 80 and 90 ° at the top of the air duct, to obtain pre-rotation angles of the air flow a2 lower and thus to maintain an axial velocity Vz2 sufficiently high to avoid aerodynamic malfunctions of the mobile wheel 115 of the compressor at low speeds with very closed wedges of the grid pre-rotation 105.
  • the increase of the pitch S2 compared with the prior art makes it possible to limit the deflection of the flow of air flowing between the leading edge BA of a blade 110 and the trailing edge BF of a blade 110 consecutive from the pre-rotation grid 105.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
EP13795842.7A 2012-11-09 2013-11-07 Assemblage de compression pour turbomachine Active EP2917590B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL13795842T PL2917590T3 (pl) 2012-11-09 2013-11-07 Zespół sprężania do maszyny wirowej

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1260637A FR2998012B1 (fr) 2012-11-09 2012-11-09 Assemblage de compression pour turbomachine
PCT/FR2013/052660 WO2014072642A1 (fr) 2012-11-09 2013-11-07 Assemblage de compression pour turbomachine

Publications (2)

Publication Number Publication Date
EP2917590A1 EP2917590A1 (fr) 2015-09-16
EP2917590B1 true EP2917590B1 (fr) 2019-03-20

Family

ID=47624353

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13795842.7A Active EP2917590B1 (fr) 2012-11-09 2013-11-07 Assemblage de compression pour turbomachine

Country Status (11)

Country Link
US (1) US10352179B2 (enExample)
EP (1) EP2917590B1 (enExample)
JP (1) JP6352284B2 (enExample)
KR (1) KR102197775B1 (enExample)
CN (1) CN104884816B (enExample)
CA (1) CA2887119C (enExample)
FR (1) FR2998012B1 (enExample)
IN (1) IN2015DN03015A (enExample)
PL (1) PL2917590T3 (enExample)
RU (1) RU2651103C2 (enExample)
WO (1) WO2014072642A1 (enExample)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11174916B2 (en) 2019-03-21 2021-11-16 Pratt & Whitney Canada Corp. Aircraft engine reduction gearbox
US11268453B1 (en) 2021-03-17 2022-03-08 Pratt & Whitney Canada Corp. Lubrication system for aircraft engine reduction gearbox

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112796840B (zh) * 2020-12-31 2022-05-20 南昌航空大学 一种节流整流式双级协调涡轮导向器
CN116220913B (zh) * 2023-05-08 2023-08-18 中国航发四川燃气涡轮研究院 一种低损失的发动机预旋供气系统

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4222235A (en) * 1977-07-25 1980-09-16 General Electric Company Variable cycle engine
SU931984A1 (ru) * 1980-12-08 1982-05-30 Всесоюзный Научно-Исследовательский Институт Горной Механики И Технической Кибернетики Им.М.М.Федорова Осевой направл ющий аппарат вентил тора
JP2941319B2 (ja) * 1989-12-01 1999-08-25 三菱重工業株式会社 航空機用軸出力式ガスタービンとその運転方法
JPH04132899A (ja) * 1990-09-25 1992-05-07 Mitsubishi Heavy Ind Ltd 軸流送風機
US5794432A (en) * 1996-08-27 1998-08-18 Diversitech, Inc. Variable pressure and variable air flow turbofan engines
US6508630B2 (en) * 2001-03-30 2003-01-21 General Electric Company Twisted stator vane
GB2405184A (en) * 2003-08-22 2005-02-23 Rolls Royce Plc A gas turbine engine lift fan with tandem inlet guide vanes
DE102008058014A1 (de) * 2008-11-19 2010-05-20 Rolls-Royce Deutschland Ltd & Co Kg Mehrschaufelige Verstellstatoreinheit einer Strömungsarbeitsmaschine
US8123471B2 (en) * 2009-03-11 2012-02-28 General Electric Company Variable stator vane contoured button
CN101737091B (zh) * 2009-12-28 2012-11-14 东方电气集团东方汽轮机有限公司 空冷给水泵汽轮机末级动叶片
CN101716920A (zh) * 2010-02-01 2010-06-02 中国北方车辆研究所 一种特种车辆的进、排气格栅
FR2970508B1 (fr) 2011-01-13 2015-12-11 Turbomeca Assemblage de compression et turbomoteur equipe d'un tel assemblage

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11174916B2 (en) 2019-03-21 2021-11-16 Pratt & Whitney Canada Corp. Aircraft engine reduction gearbox
US11268453B1 (en) 2021-03-17 2022-03-08 Pratt & Whitney Canada Corp. Lubrication system for aircraft engine reduction gearbox
US12392293B2 (en) 2021-03-17 2025-08-19 Pratt & Whitney Canada Corp. Lubrication system for aircraft engine reduction gearbox

Also Published As

Publication number Publication date
RU2651103C2 (ru) 2018-04-18
JP6352284B2 (ja) 2018-07-04
US10352179B2 (en) 2019-07-16
KR102197775B1 (ko) 2021-01-04
FR2998012B1 (fr) 2018-07-13
WO2014072642A1 (fr) 2014-05-15
KR20150082223A (ko) 2015-07-15
US20150275681A1 (en) 2015-10-01
PL2917590T3 (pl) 2019-07-31
IN2015DN03015A (enExample) 2015-10-02
CA2887119A1 (fr) 2014-05-15
CN104884816A (zh) 2015-09-02
EP2917590A1 (fr) 2015-09-16
JP2015535049A (ja) 2015-12-07
CN104884816B (zh) 2017-03-22
FR2998012A1 (fr) 2014-05-16
CA2887119C (fr) 2021-01-19
RU2015115157A (ru) 2017-01-10

Similar Documents

Publication Publication Date Title
EP2895703B1 (fr) Turbomachine comportant une pluralité d'aubes de stator à calage variable montées en amont de la soufflante
EP2715071B1 (fr) Distributeur de turbine radiale à calage variable, en particulier de turbine de source de puissance auxiliaire
EP3325346B1 (fr) Aeronef comprenant un propulseur arriere carene avec stator d'entree a volets mobiles
EP2288813B1 (fr) Injection d'air dans la veine d'un compresseur de turbomachine
EP2438306B1 (fr) Rouet centrifuge de compresseur.
WO2012156640A1 (fr) Procédé de soufflage dans un diffuseur de turbine à gaz et diffuseur correspondant
CA2887119C (fr) Assemblage de compression pour turbomachine
EP2582986B1 (fr) Couplage aérodynamique entre deux rangées annulaires d'aubes fixes dans une turbomachine
EP4508311B1 (fr) Pièce statorique à ailette dans une turbomachine
EP4448941B1 (fr) Turbomachine non carénée comprenant des aubes de stator présentant des cordes différentes
EP2976507B1 (fr) Aube et angle de diedre d'aube
EP4508310B1 (fr) Pièce statorique à ailette dans une turbomachine
FR2970508A1 (fr) Assemblage de compression et turbomoteur equipe d'un tel assemblage
BE1032247B1 (fr) Ensemble statorique de turbomachine comportant des rangées d'aubes en tandem
FR3121170A1 (fr) Aube de roue mobile de turbine de turbomachine
WO2018122538A1 (fr) Moyeu de carter intermédiaire comprenant des canaux de guidage du flux de décharge formés par les ailettes de décharge
FR3027354B1 (fr) Roue a aubes comprenant des percages entre l'intrados et l'extrados de l'aube et moteur associe
FR3162062A1 (fr) Système en tandem d’aubes statoriques comprenant une aube amont à calage variable et une aube aval à calage fixe
EP4582671A1 (fr) Ensemble statorique de turbomachine comportant des rangées d'aubes en tandem
EP4582670A1 (fr) Ensemble statorique de turbomachine comportant des rangées d'aubes en tandem
EP4582672A1 (fr) Ensemble statorique de turbomachine comportant des rangées d'aubes en tandem
FR3156485A1 (fr) Module de turbomachine comprenant des aubes rotoriques a calage variable et des ailettes montees sur un rotor, et turbomachine correspondante
WO2025149725A1 (fr) Ensemble statorique de turbomachine comportant des rangées d'aubes en tandem
FR2998011A1 (fr) Compresseur de turbomachine a deux flux separes
FR3074847A1 (fr) Module de soufflante

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

17P Request for examination filed

Effective date: 20150518

AK Designated contracting states

Kind code of ref document: A1

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

AX Request for extension of the european patent

Extension state: BA ME

DAX Request for extension of the european patent (deleted)
RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SAFRAN HELICOPTER ENGINES

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

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

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20190104

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

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

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

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

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: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602013052659

Country of ref document: DE

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1110847

Country of ref document: AT

Kind code of ref document: T

Effective date: 20190415

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: FRENCH

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20190320

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

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190320

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190620

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190320

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

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

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190320

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190320

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190320

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190620

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190621

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190320

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1110847

Country of ref document: AT

Kind code of ref document: T

Effective date: 20190320

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

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190320

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190320

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190720

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190320

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190320

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190320

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

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190320

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

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190320

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190720

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602013052659

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

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

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190320

26N No opposition filed

Effective date: 20200102

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

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190320

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

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190320

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

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

Ref country code: LI

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

Effective date: 20191130

Ref country code: LU

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

Effective date: 20191107

Ref country code: CH

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

Effective date: 20191130

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190320

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20191130

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

Ref country code: IE

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

Effective date: 20191107

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

Ref country code: BE

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

Effective date: 20191130

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

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190320

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

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190320

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20131107

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

Ref country code: SE

Payment date: 20211020

Year of fee payment: 9

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

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20190320

REG Reference to a national code

Ref country code: SE

Ref legal event code: EUG

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

Ref country code: SE

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

Effective date: 20221108

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

Ref country code: DE

Payment date: 20251118

Year of fee payment: 13

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

Ref country code: GB

Payment date: 20251125

Year of fee payment: 13

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

Ref country code: IT

Payment date: 20251128

Year of fee payment: 13

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

Ref country code: FR

Payment date: 20251125

Year of fee payment: 13

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

Ref country code: CZ

Payment date: 20251024

Year of fee payment: 13

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

Ref country code: PL

Payment date: 20251029

Year of fee payment: 13