EP4582671A1 - Turbomaschinenstatoranordnung mit tandem-schaufelreihen - Google Patents

Turbomaschinenstatoranordnung mit tandem-schaufelreihen Download PDF

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Publication number
EP4582671A1
EP4582671A1 EP24305026.7A EP24305026A EP4582671A1 EP 4582671 A1 EP4582671 A1 EP 4582671A1 EP 24305026 A EP24305026 A EP 24305026A EP 4582671 A1 EP4582671 A1 EP 4582671A1
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
EP24305026.7A
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 EP24305026.7A priority Critical patent/EP4582671A1/de
Priority to PCT/FR2025/050017 priority patent/WO2025149725A1/fr
Priority to FR2500101A priority patent/FR3158118A1/fr
Priority to BE20250004A priority patent/BE1032248A1/fr
Publication of EP4582671A1 publication Critical patent/EP4582671A1/de
Pending legal-status Critical Current

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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 invention thus provides a turbomachine stator assembly comprising successive rows of stator blades in a tandem configuration, a turbomachine compressor comprising such a stator assembly, as well as a turbomachine comprising such a stator assembly or such a compressor.
  • turbomachine modules in order to reduce the size and weight of a turbomachine, it is possible to make the turbomachine modules more compact, and in particular the compressors, especially low pressure ones, by reducing the number of compression stages.
  • this requires driving the rotor faster in rotation.
  • the compressor is then said to be transonic when at least one radially external part of the rotor moves at a speed greater than that of sound.
  • a particularly critical point in this regard is the last compression stage of the compressor, which must imperatively restore a substantially axial flow.
  • a first grid of blades whose purpose is to accommodate a flow with a strong variation in the angle of incidence, is followed by a second grid of blades which is responsible for completing the remaining deviation with an operation always adapted thanks to the work of filtering the incidence of the first grid.
  • 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.
  • the invention aims to propose a turbomachine rectifier or stator configuration making it possible to achieve the necessary flow deflection at all operating points of the turbomachine, and for a wide range of angles of incidence, to axially straighten the upstream flow so as to correctly supply a downstream zone. It thus aims to propose a rectifier or stator design making it possible to improve the compactness of the turbomachine without harming the efficiency, and this over the entire operating range, including transonic, of the turbomachine.
  • the invention it is possible to design a rectifier or stator principle in tandem configuration capable of tolerating a large range of flow incidence and of achieving a large flow deflection, by means of optimizing the design parameters of the rows of blades constituting the stator assembly.
  • the optimization proposed by the invention makes it possible to obtain better performances in terms of aerodynamic losses, residual gyration at the outlet and surge margin.
  • the capacities of the tandem configuration in terms of resistance to incidence and aerodynamic load (high deviation) are improved.
  • the stator assembly according to the invention may further comprise one or more of the following characteristics taken in isolation or in any possible technical combinations.
  • 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.
  • the chord of the upstream 33 and downstream 35 blades which connects the leading edge to the trailing edge, is respectively denoted C 33 and C 35 .
  • the chord C 33 of the upstream 33 blades may be different from the chord C 35 of the downstream 35 blades.
  • the length A0 formed axially between the two rows of upstream 33 and downstream 35 blades is also shown on the figures 2 And 3 .
  • This length A0 can be similar to an axial overlap length when the position of the blades 33, 35 is such that they overlap at least partially, thus providing axial overlap over at least part of their radial height. In the example shown in figures 2 And 3 , the rows of blades 33, 35 do not overlap.
  • the spacing between the trailing edge of an upstream blade 33 and the leading edge of an adjacent downstream blade 35 is quantified by a circumferential spacing length between blades of the tandem, denoted t on the Figure 3 , measured perpendicular to the X axis in a similar way to the measurement of the pitch S between two adjacent blades in the same row.
  • 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.
  • the azimuthal offset Da is chosen such that 0 ⁇ Da ⁇ 0.50, in particular 0.15 ⁇ Da ⁇ 0.35.
  • the incidence protection Pi is chosen such that 0 ⁇ Pi ⁇ 12°, in particular 3° ⁇ Pi ⁇ 9°.
  • the deviation distribution Rd is chosen such that 1.1 ⁇ Rd ⁇ 3.9, notably 1.7 ⁇ Rd ⁇ 3.3.
  • the chord ratio Rc is chosen such that 0.5 ⁇ Rc ⁇ 1.5, notably 0.7 ⁇ Rc ⁇ 1.2.
  • FIG. 4 illustrates an example of possible installation of the stator assembly 32 according to the invention in a turbomachine 1 such as that shown in the Figure 1 , preferably downstream of a flow separator.
  • a rotating or rotor assembly in the form of a mobile wheel 50, in particular a fan, the blades 52 of which extend radially upstream of the primary 44 and secondary 46 annular veins.
  • the stator assembly 32 consisting of an annular row of stator blades 33 and a row of stator blades 35 forming the tandem, is preferably arranged in the primary annular vein 44, in the low-pressure compressor 4 also comprising rotor blades 30, and precedes a swan-neck shape 54 which is arranged upstream of the high pressure compressor 4'.
  • the stator assembly 32 constitutes the last blades 33, 35 of the low pressure compressor 4 and makes it possible to axially straighten the primary flow F1 coming from the upstream stages in order to correctly supply the swan neck 54 located downstream.
  • the low pressure compressor 4 may comprise variable stator vanes, or VSV for "Variable Stator Vanes" in English, and the stator assembly 32 may comprise the only stator vanes of the low pressure compressor 4 which are not variable.
  • the low pressure compressor 4 may comprise between 1 and 4 compression stages, each formed of at least one row or annular grid of rotor vanes directly followed by at least one row or grid of stator vanes.

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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)
EP24305026.7A 2024-01-08 2024-01-08 Turbomaschinenstatoranordnung mit tandem-schaufelreihen Pending EP4582671A1 (de)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP24305026.7A EP4582671A1 (de) 2024-01-08 2024-01-08 Turbomaschinenstatoranordnung mit tandem-schaufelreihen
PCT/FR2025/050017 WO2025149725A1 (fr) 2024-01-08 2025-01-07 Ensemble statorique de turbomachine comportant des rangées d'aubes en tandem
FR2500101A FR3158118A1 (fr) 2024-01-08 2025-01-07 Ensemble statorique de turbomachine comportant des rangées d’aubes en tandem
BE20250004A BE1032248A1 (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
EP24305026.7A EP4582671A1 (de) 2024-01-08 2024-01-08 Turbomaschinenstatoranordnung mit tandem-schaufelreihen

Publications (1)

Publication Number Publication Date
EP4582671A1 true EP4582671A1 (de) 2025-07-09

Family

ID=90721266

Family Applications (1)

Application Number Title Priority Date Filing Date
EP24305026.7A Pending EP4582671A1 (de) 2024-01-08 2024-01-08 Turbomaschinenstatoranordnung mit tandem-schaufelreihen

Country Status (1)

Country Link
EP (1) EP4582671A1 (de)

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
DE102014203604A1 (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
DE102014206217A1 (de) * 2014-04-01 2015-10-01 Deutsches Zentrum für Luft- und Raumfahrt e.V. Verdichtungsgitter für einen Axialverdichter
DE102018108940A1 (de) 2018-04-16 2019-10-17 Rolls-Royce Deutschland Ltd & Co Kg Turbofantriebwerk für ein Luftfahrzeug
CA3057210A1 (en) * 2018-10-05 2020-04-05 Pratt & Whitney Canada Corp. Double row compressor stators
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 (10)

* 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
DE102014203604A1 (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
DE102014206217A1 (de) * 2014-04-01 2015-10-01 Deutsches Zentrum für Luft- und Raumfahrt e.V. Verdichtungsgitter für einen Axialverdichter
DE102018108940A1 (de) 2018-04-16 2019-10-17 Rolls-Royce Deutschland Ltd & Co Kg Turbofantriebwerk für ein Luftfahrzeug
CA3057210A1 (en) * 2018-10-05 2020-04-05 Pratt & Whitney Canada Corp. Double row compressor stators
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

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