[go: up one dir, main page]

EP4582672A1 - Turbomaschinenstatoranordnung mit tandem-schaufelreihen - Google Patents

Turbomaschinenstatoranordnung mit tandem-schaufelreihen Download PDF

Info

Publication number
EP4582672A1
EP4582672A1 EP24305027.5A EP24305027A EP4582672A1 EP 4582672 A1 EP4582672 A1 EP 4582672A1 EP 24305027 A EP24305027 A EP 24305027A EP 4582672 A1 EP4582672 A1 EP 4582672A1
Authority
EP
European Patent Office
Prior art keywords
blade
upstream
downstream
stator assembly
blades
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.)
Pending
Application number
EP24305027.5A
Other languages
English (en)
French (fr)
Inventor
Matteo CAZZOLA
Jérôme Jean-Yves TALBOTEC
Matthieu Pierre Michel Dubosc
Anis Canaan AL RIFAI
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 Aero Boosters SA
Safran Aircraft Engines SAS
Original Assignee
Safran Aero Boosters SA
Safran Aircraft 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 Aero Boosters SA, Safran Aircraft Engines SAS filed Critical Safran Aero Boosters SA
Priority to EP24305027.5A priority Critical patent/EP4582672A1/de
Priority to BE20250003A priority patent/BE1032247B1/fr
Priority to PCT/FR2025/050016 priority patent/WO2025149724A1/fr
Priority to FR2500103A priority patent/FR3158117A1/fr
Publication of EP4582672A1 publication Critical patent/EP4582672A1/de
Pending legal-status Critical Current

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
    • 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
    • F01D5/146—Shape, i.e. outer, aerodynamic form of blades with tandem configuration, split blades or slotted blades
    • 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
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/312—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being parallel to each other
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/314—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being inclined in relation to each other

Definitions

  • the present invention relates to the general field of turbomachines, and more specifically to the field of turbomachine rectifiers or stators, in particular turbomachine compressor rectifiers or stators.
  • climate change is a major concern for many legislative and regulatory bodies around the world. Various states have, are, or will adopt various carbon emission restrictions. In particular, an eager standard applies to both new aircraft types and those already in operation, requiring the implementation of technological solutions to comply with current regulations. For several years now, civil aviation has been mobilizing to contribute to the fight against climate change.
  • the invention aims to at least partially remedy the needs mentioned above and the drawbacks relating to the achievements of the prior art.
  • the invention is the result of technological research aimed at significantly improving aircraft performance and, in this sense, contributes to reducing the environmental impact of aircraft.
  • chord of the upstream blades can be different from the chord of the downstream blades.
  • turbomachine compressor in particular a high pressure compressor or a low pressure compressor, characterized in that it comprises a stator assembly as defined previously.
  • the compressor is a low pressure compressor.
  • the stator assembly belongs to the last compression stage of the compressor.
  • the invention also relates, according to another of its aspects, to a turbomachine, characterized in that it comprises a stator assembly as defined previously or a compressor as defined previously.
  • the turbomachine may comprise a moving wheel and a separation nozzle, arranged downstream of the moving wheel and separating an annular air flow into a primary flow traveling through an internal vein and a secondary flow traveling through an external vein, the stator assembly being arranged in the internal vein upstream of a swan neck shape.
  • turbomachine may comprise a high-pressure compressor arranged downstream of the stator assembly, the swan-neck shape being located in particular between the stator assembly and the high-pressure compressor.
  • FIG. 1 an example of a turbomachine 1 according to the invention is shown in an axial sectional view.
  • stator vanes 22 also called OGV for “outlet guide vanes” in English, is arranged downstream of the rotor 12 to straighten the secondary flow F2.
  • the turbomachine 1 has a separation nozzle 48 for separating the annular flow F into two primary flows F1 and secondary F2.
  • the invention can be applied downstream of any type of flow separation nozzle and is not limited to the separation nozzle 48.
  • the low pressure compression 4 of the turbomachine 1 comprises a final compression stage, as detailed below with reference to the Figure 4 , in which is located a stator assembly 32 according to the invention comprising rows of blades in tandem.
  • stator assembly 32 in accordance with the invention is described below with reference to figures 2 And 3
  • the stator assembly 32 thus has a tandem configuration with two rows or grids of stator blades forming a bi-grid.
  • a first row or grid of upstream stator blades 33 is provided, moderately deflecting and intended to accommodate the flow of the primary flow F1 with a wide range of incidence angle and to provide the second row or grid of downstream stator blades 35 with a supply that is always uniform at any operating point of the turbomachine 1.
  • the second row or grid of stator blades 35 operates at almost single incidence, and completes the deflection without having to manage the incidence variations.
  • THE figures 2 And 3 allow to define design parameters helping to define the geometry of the stator assembly 32, which here forms, and in a non-limiting manner, the stator of the last compression stage of the low pressure compressor 4, also comprising a rotor upstream of the stator.
  • the rotor comprises rotor blades which accelerate the flow of the fluid thanks to the energy transmitted by the transmission shaft while the stator transforms the kinetic energy into pressure thanks to the shape of the stator blades 33, 35.
  • the stator assembly 32 comprises a row of upstream blades 33 and a row of downstream blades 35, extending from a radially internal support 36 to a radially external support 38, as visible in the Figure 2
  • the internal 36 and external 38 supports may be platforms for attachment to a supporting structure.
  • the internal 36 and external 38 supports may also be ferrules describing 360° around the X axis or angular sectors of ferrules describing a few degrees or a few tens of degrees of angle around the X axis.
  • the upstream 33 and downstream 35 blades are carried by a common internal support and by a common external support.
  • the camber of the upstream 33 and downstream 35 stator blades is noted A1 and A2 respectively and is shown in broken lines.
  • the angular pitch between two circumferentially adjacent upstream 33 or downstream 35 blades is noted S as visible on the Figure 3 , and may be identical for both rows of blades 33, 35.
  • Design parameters are advantageously provided for the stator assembly 32 according to the invention. These parameters are determined in particular between 10% and 90% of the radial height H33 of an upstream blade 33 and between 10% and 90% of the radial height H35 of a downstream blade 35.

Landscapes

  • 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)
EP24305027.5A 2024-01-08 2024-01-08 Turbomaschinenstatoranordnung mit tandem-schaufelreihen Pending EP4582672A1 (de)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP24305027.5A EP4582672A1 (de) 2024-01-08 2024-01-08 Turbomaschinenstatoranordnung mit tandem-schaufelreihen
BE20250003A BE1032247B1 (fr) 2024-01-08 2025-01-07 Ensemble statorique de turbomachine comportant des rangées d'aubes en tandem
PCT/FR2025/050016 WO2025149724A1 (fr) 2024-01-08 2025-01-07 Ensemble statorique de turbomachine comportant des rangées d'aubes en tandem
FR2500103A FR3158117A1 (fr) 2024-01-08 2025-01-07 Ensemble statorique de turbomachine comportant des rangées d’aubes en tandem

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP24305027.5A EP4582672A1 (de) 2024-01-08 2024-01-08 Turbomaschinenstatoranordnung mit tandem-schaufelreihen

Publications (1)

Publication Number Publication Date
EP4582672A1 true EP4582672A1 (de) 2025-07-09

Family

ID=90720318

Family Applications (1)

Application Number Title Priority Date Filing Date
EP24305027.5A Pending EP4582672A1 (de) 2024-01-08 2024-01-08 Turbomaschinenstatoranordnung mit tandem-schaufelreihen

Country Status (1)

Country Link
EP (1) EP4582672A1 (de)

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2409002A2 (de) 2009-03-16 2012-01-25 MTU Aero Engines GmbH Tandemschaufelkonstruktion
DE102014203607A1 (de) * 2014-02-27 2015-08-27 Rolls-Royce Deutschland Ltd & Co Kg Schaufelreihengruppe
EP2913480A1 (de) 2014-02-27 2015-09-02 Rolls-Royce Deutschland Ltd & Co KG Tandemschaufel einer Strömungsmaschine
DE102014206217B4 (de) * 2014-04-01 2016-09-15 Deutsches Zentrum für Luft- und Raumfahrt e.V. Verdichtungsgitter für einen Axialverdichter
EP3369891A1 (de) * 2017-03-03 2018-09-05 Rolls-Royce plc Gasturbinenleitschaufeln
DE102018108940A1 (de) 2018-04-16 2019-10-17 Rolls-Royce Deutschland Ltd & Co Kg Turbofantriebwerk für ein Luftfahrzeug
US20200240283A1 (en) 2019-01-24 2020-07-30 MTU Aero Engines AG Guide vane cascade for a turbomachine
WO2023193997A1 (fr) * 2022-04-05 2023-10-12 Safran Aero Boosters Stator tandem

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2409002A2 (de) 2009-03-16 2012-01-25 MTU Aero Engines GmbH Tandemschaufelkonstruktion
DE102014203607A1 (de) * 2014-02-27 2015-08-27 Rolls-Royce Deutschland Ltd & Co Kg Schaufelreihengruppe
EP2913480A1 (de) 2014-02-27 2015-09-02 Rolls-Royce Deutschland Ltd & Co KG Tandemschaufel einer Strömungsmaschine
DE102014206217B4 (de) * 2014-04-01 2016-09-15 Deutsches Zentrum für Luft- und Raumfahrt e.V. Verdichtungsgitter für einen Axialverdichter
EP3369891A1 (de) * 2017-03-03 2018-09-05 Rolls-Royce plc Gasturbinenleitschaufeln
DE102018108940A1 (de) 2018-04-16 2019-10-17 Rolls-Royce Deutschland Ltd & Co Kg Turbofantriebwerk für ein Luftfahrzeug
US20200240283A1 (en) 2019-01-24 2020-07-30 MTU Aero Engines AG Guide vane cascade for a turbomachine
WO2023193997A1 (fr) * 2022-04-05 2023-10-12 Safran Aero Boosters Stator tandem
BE1030421A1 (fr) 2022-04-05 2023-10-27 Safran Aero Boosters Stator tandem

Similar Documents

Publication Publication Date Title
FR3027053B1 (fr) Stator de turbomachine d'aeronef
EP3927945B1 (de) Statorring einer turbomaschine welche statorschaufeln mit unterschidlicher sehnenlänge aufweist
EP4073366B1 (de) Aeronautisches antriebssystem mit niedriger leckrate und verbesserter antriebseffizienz
EP4073369A1 (de) Flugzeugantriebssystem mit verbesserter antriebseffizienz
EP4111062B1 (de) Transonischer turbomaschinenverdichter
BE1032247B1 (fr) Ensemble statorique de turbomachine comportant des rangées d'aubes en tandem
BE1032248B1 (fr) Ensemble statorique de turbomachine comportant des rangées d'aubes en tandem
EP4582672A1 (de) Turbomaschinenstatoranordnung mit tandem-schaufelreihen
EP4582671A1 (de) Turbomaschinenstatoranordnung mit tandem-schaufelreihen
EP4582670A1 (de) Turbomaschinenstatoranordnung mit tandem-schaufelreihen
EP4689356A1 (de) Turbomaschine mit reihen von leitschaufeln und einem diffusor in einem kanal, in dem eine dritte strömung zirkuliert
FR3144840A1 (fr) Système propulsif aéronautique présentant une soufflante dont la tenue mécanique est améliorée
FR3104644A1 (fr) Système propulsif aéronautique à rendement propulsif amélioré
BE1032189B1 (fr) Aube pour compresseur de turbomachine d'aeronef, compresseur, turbomachine
BE1028097B1 (fr) Aube de compresseur de turbomachine, compresseur et turbomachine munis de celle-ci
FR3151628A1 (fr) Soufflante pour propulsion aéronautique
WO2024224017A1 (fr) Aube à calage variable de propulseur aéronautique non-caréné
BE1032707A1 (fr) Aube pour compresseur de turbomachine d'aeronef, compresseur, turbomachine
WO2025114465A1 (fr) Ensemble de turbomachine
WO2025104401A1 (fr) Soufflante pour propulsion aéronautique
FR3162059A1 (fr) Distribution hétérogène de fentes de bord d’attaque
FR3144843A1 (fr) Système propulsif aéronautique présentant une soufflante dont la tenue mécanique est améliorée
FR3160212A1 (fr) Moteur à turbine à gaz avec cadencement relatif de bifurcations
FR3146494A1 (fr) Systeme propulsif aeronautique a soufflante carenee et a fort taux de dilution
WO2025093843A1 (fr) Aube de redresseur avec une fente

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

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

Free format text: STATUS: THE APPLICATION HAS BEEN PUBLISHED

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 ME MK MT NL NO PL PT RO RS SE SI SK SM TR

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

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20251216