EP2880265B1 - Aube mobile de turbine - Google Patents

Aube mobile de turbine Download PDF

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Publication number
EP2880265B1
EP2880265B1 EP13756579.2A EP13756579A EP2880265B1 EP 2880265 B1 EP2880265 B1 EP 2880265B1 EP 13756579 A EP13756579 A EP 13756579A EP 2880265 B1 EP2880265 B1 EP 2880265B1
Authority
EP
European Patent Office
Prior art keywords
blade
low pressure
pressure turbine
stilt
curved portion
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
EP13756579.2A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP2880265A1 (fr
Inventor
Raphaël DUPEYRE
Josserand Bassery
Vincent François BOULAY
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
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 Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP2880265A1 publication Critical patent/EP2880265A1/fr
Application granted granted Critical
Publication of EP2880265B1 publication Critical patent/EP2880265B1/fr
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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
    • 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
    • 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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • 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
    • F05D2240/301—Cross-sectional characteristics
    • 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
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved

Definitions

  • the field of the invention relates to the field of moving blades of a turbomachine low pressure turbine.
  • the invention relates more particularly to a particular arrangement of the foot of a moving blade of low pressure turbine.
  • a moving blade 1 of low pressure turbine is formed by three sets: a lower part called the foot 10, an upper part called the heel 20 and a central part formed by the blade 30.
  • the stilt 11 is an important part of the foot 10 because it provides the mechanical connection between the blade 30 and the foot 10 which is secured to the rotor disk, it is therefore the seat of significant mechanical stress.
  • the low pressure turbine blades have stilts having substantially a rectilinear shape which corresponds to the shape of the upper part of the bulb (ie the upper part of the dovetail).
  • stilts having substantially a rectilinear shape which corresponds to the shape of the upper part of the bulb (ie the upper part of the dovetail).
  • such stilts do not meet the mechanical requirements.
  • stilts called curvilinear stilts, taking the shape or more precisely the profile of the blade, so as to ensure the maximum overlap between the stilt 11 and the blade 30 or more exactly between the profile of the cross section of the stilt 11 and the profile of the cross section of the blade 30.
  • EP0887513A2 discloses a moving blade of the state of the art according to the preamble of claim 1.
  • the invention aims to provide a blade low pressure turbine blade lightened compared to the blades of the state of the art and which allows to withstand the imposed mechanical stresses.
  • the invention proposes a low-pressure turbine blade according to claim 1.
  • the lengths of the different parts are adjusted according to the desired mechanical characteristics.
  • said curvilinear portion is defined so that the cross section of the curvilinear portion is superimposed on the cross section of the base of the blade with an overlap greater than 95%.
  • each of said parts of the stilt has a constant thickness.
  • the invention also relates to a low pressure turbine comprising a plurality of blades according to the invention.
  • the curvilinear portion 15 is located between the two rectilinear portions 14 and 16. Each of the portions 14, 15, 16 having a constant thickness.
  • the geometric shape of the stilt 11 of the blade according to the invention has a curvilinear portion 15 which matches a portion of the profile 35 of the base of the blade 30 of the blade shown in dotted lines on the figure 3 .
  • the base of the blade is the part of the blade connected to the stilt.
  • the two profiles are identical, that is to say that the outer face 18 of this curvilinear portion 15 has the same profile as the extrados 31 of the base of the blade 30 (shown in FIG. figure 1 ) and that the internal face 17 has the same profile as the underside of the base of the blade 30 ( figure 1 ).
  • this portion 15 has the same thickness as the base of the corresponding blade 30 so that the two profiles are found superimposed.
  • the lengths of the different parts 14, 15 and 16 of the stilt 11 may be variable and adapted according to the desired mechanical characteristics. Indeed, it is possible to increase the proportion of the curvilinear portion 15 to the detriment of the rectilinear portions 14, 16 if the foot 10 of the blade must withstand the mechanical constraints imposed. Thus, the different lengths can be modulated and optimized according to the desired weight / strength ratio. For example, the shape of the stilt 11 is determined by successive iterations by means of a CAD model and thermomechanical calculations.
  • the stilt 11 is thus developed so that the curvilinear portion 15 has an overlap with the cross section of the blade 30 of at least 95% and preferably 100%.
  • a total overlap of the order of 65 to 75% between the section of the blade and the section of the stilt allows to obtain sufficient mechanical strength for an application in the field of low pressure turbines while having a gain in mass.
  • the thickness of the stilt profile is constant and equal to 2 mm.
  • the stilt has a recovery rate of 85% with the base of the blade.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP13756579.2A 2012-08-03 2013-07-19 Aube mobile de turbine Active EP2880265B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1257602A FR2994211B1 (fr) 2012-08-03 2012-08-03 Aube mobile de turbine
PCT/FR2013/051748 WO2014020258A1 (fr) 2012-08-03 2013-07-19 Aube mobile de turbine

Publications (2)

Publication Number Publication Date
EP2880265A1 EP2880265A1 (fr) 2015-06-10
EP2880265B1 true EP2880265B1 (fr) 2019-07-17

Family

ID=47427358

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13756579.2A Active EP2880265B1 (fr) 2012-08-03 2013-07-19 Aube mobile de turbine

Country Status (8)

Country Link
US (1) US9920632B2 (zh)
EP (1) EP2880265B1 (zh)
CN (1) CN104520537B (zh)
BR (1) BR112015002350B1 (zh)
CA (1) CA2880829C (zh)
FR (1) FR2994211B1 (zh)
RU (1) RU2642948C2 (zh)
WO (1) WO2014020258A1 (zh)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3017649B1 (fr) * 2014-02-18 2021-10-15 Snecma Aube mobile pour organe de turbomachine
FR3085992B1 (fr) * 2018-09-14 2020-12-11 Safran Aircraft Engines Aube de roue mobile de turbine comportant un pied de forme curviligne
FR3127018A1 (fr) * 2021-09-14 2023-03-17 Safran Aircraft Engines Aube mobile pour turbine de turbomachine, présentant une conception améliorant l’étanchéité des cavités inter-aubes

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2005207300A (ja) * 2004-01-22 2005-08-04 Mitsubishi Heavy Ind Ltd タービン動翼
US20050186074A1 (en) * 2004-02-23 2005-08-25 Mitsubishi Heavy Industries, Ltd. Moving blade and gas turbine using the same

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2056505C1 (ru) * 1992-07-10 1996-03-20 Андреев Валерий Евгеньевич Сопловая лопатка газовой турбины
JPH07310502A (ja) * 1994-05-19 1995-11-28 Toshiba Corp タービン動翼
US5980209A (en) * 1997-06-27 1999-11-09 General Electric Co. Turbine blade with enhanced cooling and profile optimization
US6722851B1 (en) * 2003-03-12 2004-04-20 General Electric Company Internal core profile for a turbine bucket
US6854961B2 (en) * 2003-05-29 2005-02-15 General Electric Company Airfoil shape for a turbine bucket
US6857855B1 (en) * 2003-08-04 2005-02-22 General Electric Company Airfoil shape for a turbine bucket
US7547192B2 (en) * 2005-02-25 2009-06-16 General Electric Company Torque-tuned, integrally-covered bucket and related method
US7300253B2 (en) * 2005-07-25 2007-11-27 Siemens Aktiengesellschaft Gas turbine blade or vane and platform element for a gas turbine blade or vane ring of a gas turbine, supporting structure for securing gas turbine blades or vanes arranged in a ring, gas turbine blade or vane ring and the use of a gas turbine blade or vane ring
US7632072B2 (en) * 2005-12-29 2009-12-15 Rolls-Royce Power Engineering Plc Third stage turbine airfoil
US8727730B2 (en) * 2010-04-06 2014-05-20 General Electric Company Composite turbine bucket assembly

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2005207300A (ja) * 2004-01-22 2005-08-04 Mitsubishi Heavy Ind Ltd タービン動翼
US20050186074A1 (en) * 2004-02-23 2005-08-25 Mitsubishi Heavy Industries, Ltd. Moving blade and gas turbine using the same

Also Published As

Publication number Publication date
BR112015002350B1 (pt) 2021-11-16
CA2880829A1 (fr) 2014-02-06
BR112015002350A2 (pt) 2017-07-04
CN104520537B (zh) 2020-01-17
RU2642948C2 (ru) 2018-01-29
RU2015107176A (ru) 2016-09-27
CA2880829C (fr) 2020-06-09
US9920632B2 (en) 2018-03-20
EP2880265A1 (fr) 2015-06-10
CN104520537A (zh) 2015-04-15
WO2014020258A1 (fr) 2014-02-06
US20150218950A1 (en) 2015-08-06
FR2994211A1 (fr) 2014-02-07
FR2994211B1 (fr) 2018-03-30

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