WO2015118243A1 - Pale pour une helice de turbomachine, notamment a soufflante non carenee, helice et turbomachine comprenant une telle pale - Google Patents

Pale pour une helice de turbomachine, notamment a soufflante non carenee, helice et turbomachine comprenant une telle pale Download PDF

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Publication number
WO2015118243A1
WO2015118243A1 PCT/FR2015/050158 FR2015050158W WO2015118243A1 WO 2015118243 A1 WO2015118243 A1 WO 2015118243A1 FR 2015050158 W FR2015050158 W FR 2015050158W WO 2015118243 A1 WO2015118243 A1 WO 2015118243A1
Authority
WO
WIPO (PCT)
Prior art keywords
blade
propeller
blades
protrusion
leading edge
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.)
Ceased
Application number
PCT/FR2015/050158
Other languages
English (en)
French (fr)
Inventor
Laurence Francine VION
Rasika FERNANDO
Norman Bruno André JODET
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 Aircraft Engines SAS
Original Assignee
SNECMA 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 SNECMA SAS filed Critical SNECMA SAS
Priority to RU2016130837A priority Critical patent/RU2667555C1/ru
Priority to US15/114,628 priority patent/US10370086B2/en
Priority to CA2936324A priority patent/CA2936324C/fr
Priority to BR112016016467-9A priority patent/BR112016016467B1/pt
Priority to CN201580007583.3A priority patent/CN105980248B/zh
Priority to EP15704355.5A priority patent/EP3102487B1/fr
Publication of WO2015118243A1 publication Critical patent/WO2015118243A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/16—Blades
    • B64C11/18—Aerodynamic features
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/46—Arrangements of, or constructional features peculiar to, multiple propellers
    • B64C11/48—Units of two or more coaxial propellers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/10—Aircraft characterised by the type or position of power plants of gas-turbine type 
    • 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
    • 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
    • F01D5/148—Blades with variable camber, e.g. by ejection of fluid
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D2027/005—Aircraft with an unducted turbofan comprising contra-rotating rotors, e.g. contra-rotating open rotors [CROR]
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
    • 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
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade
    • 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
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • 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
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • F05D2260/961—Preventing, counteracting or reducing vibration or noise by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape
    • 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
    • F05D2270/00—Control
    • F05D2270/60—Control system actuates means
    • F05D2270/62—Electrical actuators
    • 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
    • F05D2270/00—Control
    • F05D2270/60—Control system actuates means
    • F05D2270/64—Hydraulic actuators
    • 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
    • F05D2270/00—Control
    • F05D2270/60—Control system actuates means
    • F05D2270/65—Pneumatic actuators
    • 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

Definitions

  • the The dominant contribution of the radiated noise comes from the interaction lines associated with the downstream propeller which operates in the flow of the upstream propeller, crossing the swirling layers consisting of main wakes and vortices formed by the blades of the upstream propeller (also designated upstream blades).
  • the downstream vortex - marginal vortex interaction dominates the radiated acoustic spectrum for most directivities.
  • the invention is particularly advantageous because it makes it possible to adjust the position of the protuberance on the leading edge of the blade, in particular as a function of the operating conditions. It is thus conceivable that the protuberance of each blade is in a first position (for example low) during take-off of the aircraft comprising a turbomachine equipped with blades according to the invention, whether in a second position (for example intermediate) during the cruise flight of the aircraft, whether it is in a third position (for example higher during the landing of the aircraft, etc.
  • the outgrowth may adopt at least two positions, and preferably several Different positions along the leading edge of the blade Naturally, the excrescences of the blades of the same helix are preferably in the same position for an operating condition.
  • the protuberance and the portion of the leading edge comprising the groove are covered with a flexible membrane fixed to the blade.
  • This membrane may be elastically deformable. It is designed to allow the displacement of the protrusion along the leading edge while locally preserving the aerodynamic surface quality of the profile of the blade. It ensures continuity aerodynamic surface between the zone of the leading edge in which is located the protrusion and the rest of the leading edge, and between this zone and the intrados and extrados of the blade.
  • the membrane is preferably relatively thin (it has for example a thickness of between 1 mm and 5 mm). It can be made for example of polymers covered with erosion-resistant skin.
  • Figure 1 is a schematic longitudinal sectional view of a non-ducted fan turbomachine equipped with upstream blades, according to an embodiment according to the invention.
  • FIG. 1 diagrammatically shows, by way of nonlimiting example, a non-ducted fan turbomachine 1 according to the invention, which comprises, from upstream to downstream, in the direction of flow of the gas (symbolized by the arrow F) inside the longitudinal axis turbomachine LL, a compressor 2, an annular combustion chamber 3, a high pressure turbine 4 and two low pressure turbines 5 and 6 which are counter-rotating, that is, they rotate in two opposite directions about the longitudinal axis LL.
  • a non-ducted fan turbomachine 1 according to the invention, which comprises, from upstream to downstream, in the direction of flow of the gas (symbolized by the arrow F) inside the longitudinal axis turbomachine LL, a compressor 2, an annular combustion chamber 3, a high pressure turbine 4 and two low pressure turbines 5 and 6 which are counter-rotating, that is, they rotate in two opposite directions about the longitudinal axis LL.
  • the invention proposes to equip the blade 1 1 A with means for adjusting the position of the protuberance 16 along its leading edge 17.
  • a membrane 22 preferably flexible and thin, which is intended to match the shape of the protrusion 16 and the leading edge 17 to ensure aerodynamic surface continuity between the protrusion 16 and the rest of the blade and limit the pressure losses during operation.
  • the portion of the membrane 22 covering the protuberance 16 defines a hump that preferably reproduces as closely as possible the shape and dimensions of the protrusion 16.
  • the displacement of the protrusion 16 along the leading edge 17 causes a deformation, preferably elastic, of the membrane 22.
  • the bump defined by the membrane 22 then moves following the protrusion 16.
  • each flight point or each operating condition is defined by a set of several parameters among which the rotational speed of the propeller, the forward speed of the aircraft equipped with this propeller, and the pitch angle of the blades of the propeller.
  • the rotational speed of the propeller the forward speed of the aircraft equipped with this propeller, and the pitch angle of the blades of the propeller.
  • the elements 46 of the protrusion 16 are covered with a membrane 22 which is preferably flexible and thin, which is intended to conform to the shape of the protrusion 16 and the leading edge 17 to ensure aerodynamic surface continuity between the protrusion 16 and the rest of the blade and limit the pressure drops in operation.
  • the portion of the membrane 22 covering the protrusion 16 defines a hump that preferably reproduces as closely as possible the shape and dimensions of the protuberance 16.
  • the deformations of the protrusion 16 along the leading edge 17 cause a deformation, preferably elastic, of the membrane 22.
  • the bump defined by the membrane 22 then moves following the protrusion 16.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
PCT/FR2015/050158 2014-02-05 2015-01-22 Pale pour une helice de turbomachine, notamment a soufflante non carenee, helice et turbomachine comprenant une telle pale Ceased WO2015118243A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
RU2016130837A RU2667555C1 (ru) 2014-02-05 2015-01-22 Лопатка для винта турбомашины, в частности турбовинтовентиляторного двигателя безредукторной схемы, соответствующие винт и турбомашина
US15/114,628 US10370086B2 (en) 2014-02-05 2015-01-22 Blade for a turbine engine propeller, in particular a propfan engine, propeller, and turbine engine comprising such a blade
CA2936324A CA2936324C (fr) 2014-02-05 2015-01-22 Pale pour une helice de turbomachine, notamment a soufflante non carenee, helice et turbomachine correspondantes
BR112016016467-9A BR112016016467B1 (pt) 2014-02-05 2015-01-22 Lâmina para uma hélice de turbomáquina, em particular de ventoinha não carenada, hélice e turbomáquina correspondentes, e, processo de redução das emissões sonoras de uma turbomáquina
CN201580007583.3A CN105980248B (zh) 2014-02-05 2015-01-22 用于涡轮发动机螺旋桨特别是用于桨扇发动机的叶片，包括这样的叶片的螺旋桨和涡轮发动机
EP15704355.5A EP3102487B1 (fr) 2014-02-05 2015-01-22 Pale pour une helice de turbomachine, notamment a soufflante non carenee, helice et turbomachine comprenant une telle pale

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1450874 2014-02-05
FR1450874A FR3017165B1 (fr) 2014-02-05 2014-02-05 Pale pour une helice de turbomachine, notamment a soufflante non carenee, helice et turbomachine correspondantes

Publications (1)

Publication Number Publication Date
WO2015118243A1 true WO2015118243A1 (fr) 2015-08-13

Family

ID=50549129

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/FR2015/050158 Ceased WO2015118243A1 (fr) 2014-02-05 2015-01-22 Pale pour une helice de turbomachine, notamment a soufflante non carenee, helice et turbomachine comprenant une telle pale

Country Status (8)

Country Link
US (1) US10370086B2 (https=)
EP (1) EP3102487B1 (https=)
CN (1) CN105980248B (https=)
BR (1) BR112016016467B1 (https=)
CA (1) CA2936324C (https=)
FR (1) FR3017165B1 (https=)
RU (1) RU2667555C1 (https=)
WO (1) WO2015118243A1 (https=)

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US11192644B2 (en) * 2017-06-16 2021-12-07 Airbus Helicopters Aircraft rotor blade sleeve having a protuberance in its rear zone, and a rotor provided with such a sleeve
CN108953191B (zh) * 2018-07-24 2019-12-17 苏州睿澎诚科技有限公司 能够通过旋转进行扇叶开合的风扇
FR3084693B1 (fr) * 2018-08-03 2020-12-25 Safran Aircraft Engines Turbomachine a helices non carenees
FR3100563B1 (fr) * 2019-09-06 2021-08-06 Safran Aircraft Engines Moyeu polysphérique de turbomachine pour pales à calage variable
US12103702B2 (en) 2019-10-15 2024-10-01 General Electric Company Removeable fuselage shield for an aircraft
US11834196B2 (en) 2019-10-15 2023-12-05 General Electric Company System and method for control for unducted engine
US11506067B2 (en) 2019-10-15 2022-11-22 General Electric Company Gas turbine engine with clutch assembly
US11286795B2 (en) 2019-10-15 2022-03-29 General Electric Company Mount for an airfoil
US11401824B2 (en) 2019-10-15 2022-08-02 General Electric Company Gas turbine engine outlet guide vane assembly
CN112179670B (zh) * 2020-09-29 2021-08-06 西安交通大学 用于测量桨扇空中数据的桨扇试验器
US12410758B2 (en) 2022-01-10 2025-09-09 General Electric Company Three-stream gas turbine engine control
US11858615B2 (en) 2022-01-10 2024-01-02 General Electric Company Rotating airfoil assembly with opening formed therein to eject or to draw air
US12275532B2 (en) 2022-08-15 2025-04-15 General Electric Company Gas turbine engine noise reduction
US12480449B2 (en) 2022-08-22 2025-11-25 General Electric Company Propulsion system including an electric machine for starting a gas turbine engine
US12378887B2 (en) * 2022-11-28 2025-08-05 General Electric Company Airfoil assembly
US12352181B2 (en) 2023-01-30 2025-07-08 General Electric Company Turbine airfoils
US12215596B2 (en) 2023-06-30 2025-02-04 General Electric Company Unducted airfoil assembly
CN117072491B (zh) * 2023-08-14 2026-04-17 中国民用航空飞行学院 一种应用于高负荷压气机叶栅流动控制的涡流发生器

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US20060060721A1 (en) * 2004-03-30 2006-03-23 Phillip Watts Scalloped leading edge advancements
US20060060720A1 (en) * 2004-03-31 2006-03-23 Bogue David R Methods and systems for controlling lower surface shocks
FR2980818A1 (fr) 2011-09-29 2013-04-05 Snecma Pale pour une helice de turbomachine, notamment a soufflante non carenee, helice et turbomachine correspondantes.

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US20060060720A1 (en) * 2004-03-31 2006-03-23 Bogue David R Methods and systems for controlling lower surface shocks
FR2980818A1 (fr) 2011-09-29 2013-04-05 Snecma Pale pour une helice de turbomachine, notamment a soufflante non carenee, helice et turbomachine correspondantes.

Also Published As

Publication number Publication date
CA2936324C (fr) 2021-07-13
BR112016016467B1 (pt) 2022-04-12
RU2667555C1 (ru) 2018-09-21
US20160347440A1 (en) 2016-12-01
US10370086B2 (en) 2019-08-06
FR3017165B1 (fr) 2016-01-22
EP3102487B1 (fr) 2018-04-25
CN105980248A (zh) 2016-09-28
CA2936324A1 (fr) 2015-08-13
FR3017165A1 (fr) 2015-08-07
BR112016016467A2 (https=) 2017-08-08
CN105980248B (zh) 2019-01-08
EP3102487A1 (fr) 2016-12-14

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