EP2400160A1 - Leichterer Rotor für Axialkompressor - Google Patents

Leichterer Rotor für Axialkompressor Download PDF

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Publication number
EP2400160A1
EP2400160A1 EP10166959A EP10166959A EP2400160A1 EP 2400160 A1 EP2400160 A1 EP 2400160A1 EP 10166959 A EP10166959 A EP 10166959A EP 10166959 A EP10166959 A EP 10166959A EP 2400160 A1 EP2400160 A1 EP 2400160A1
Authority
EP
European Patent Office
Prior art keywords
rotor
stage according
platform
rotor stage
drum
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.)
Granted
Application number
EP10166959A
Other languages
English (en)
French (fr)
Other versions
EP2400160B1 (de
Inventor
Xavier Wery
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
Original Assignee
Techspace Aero SA
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 Techspace Aero SA filed Critical Techspace Aero SA
Priority to EP20100166959 priority Critical patent/EP2400160B1/de
Priority to US13/165,178 priority patent/US8870543B2/en
Priority to RU2011125136/06A priority patent/RU2011125136A/ru
Priority to CA2743817A priority patent/CA2743817C/en
Priority to CN201110170449A priority patent/CN102297158A/zh
Publication of EP2400160A1 publication Critical patent/EP2400160A1/de
Application granted granted Critical
Publication of EP2400160B1 publication Critical patent/EP2400160B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/322—Blade mountings
    • 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
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • 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
    • F01D5/3053—Fixing blades to rotors; Blade roots ; Blade spacers by means of pins
    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors

Definitions

  • the present invention relates, in the field of turbomachines, to a compressor rotor consisting of a drum and blades mechanically fixed thereon.
  • Axial compressors are well known per se and are used inter alia in turbomachines.
  • These low or high pressure compressors comprise several stages of rotating blades, also called rotor blades, which are separated by rectifier stages which are intended to reposition the velocity vector of the fluid leaving the preceding stage before sending it to the next floor.
  • the rectifier stages consist essentially of fixed vanes, also called stator vanes, connecting an outer ferrule to an inner ferrule, both concentric and delimiting the air flow zone or aerodynamic vein.
  • a compressor drum is a symmetrical hollow body in revolution with respect to its axis of rotation which corresponds to the axis of the turbomachine.
  • the hollow body has a generally oval or ogival shape depending on the shape of the flow.
  • the drum and the rotor blades are generally made of a titanium alloy (TA6V) and the drum has circumferential cavities in which the blade roots are fixed via a system of locks.
  • T6V titanium alloy
  • Such a construction is illustrated in figure 1 of the document EP 1 111 246 B1 .
  • the document GB 1,163,752 presents an alternative to the fastening system with cavities in an axial flow machine rotor.
  • the blade comprises a blade provided with a threaded member which engages in the rotor hub to allow the blade to be fixed to the hub.
  • the present invention aims to provide a solution that makes it possible to overcome the disadvantages of the state of the art.
  • the present invention is more particularly intended to provide a new drum architecture and an original attachment system of the blade to the latter.
  • the present invention also aims to provide a drum rid of its cells and thus aims to provide a new construction of the rotor to reduce consumption in radial and axial clearances.
  • the present invention also aims to achieve a new rotor construction for optimizing the choice of materials of different elements (drum, blade) and therefore a very consistent mass reduction.
  • the present invention relates to a rotor drum rotor compressor stage for axial turbomachine comprising a row of rotor blades each provided with a platform, and a wall generally symmetrical in revolution with respect to the axis of rotation of the turbomachine and forming a hollow body, said wall comprising a web and a support zone raised with respect to the web in a direction facing the outside of the hollow body, said support zone comprising a central part and side walls connecting the central part to the web of the drum, said platform of each of said blades being joined to said central portion by means of one or more fasteners.
  • the present invention also relates to a compressor drum for axial turbomachine comprising at least one rotor stage as described above.
  • the figure 1 is a partial sectional view of a conventional axial compressor drum architecture superimposed on a partial sectional view of an axial compressor drum according to a first preferred embodiment of the invention (profile in gray).
  • the figure 2 represents a three-dimensional view of a preferred variant of the rotor blade according to the invention and the assembly nut.
  • the figure 3 represents a profile view of the attachment of the rotor blade of the figure 2 to the drum according to the first preferred embodiment of the invention.
  • FIG. 1 Two respective views in partial section (upper half) and axial of a compressor drum according to the state of the art 1 and according to the invention 2 (in gray) are superimposed on the figure 1 .
  • the respective drums are intended to fix three stages of rotor blades (not shown).
  • the drums 1.2 comprise a wall 3 generally symmetrical in rotation about an axis of rotation, the wall 3 thus forming a hollow body in the shape of an oval or ogive.
  • the wall 3 comprises a web defining the general shape of the drum.
  • the wall 3 further comprises cells 4 for receiving the roots of the rotor blades.
  • the wall 3 instead of the cells 4 support zones 5.
  • the drums 1,2 also conventionally include wipers 6 disposed between the rotor blade stages and intended to be positioned opposite the abradable inner ferrules (not shown).
  • the support zone 5 of the wall 3 visible to the figures 1 and 3 comprises two side walls 7 and a central portion 8 joining the two side walls 7 and intended to be fixed to the rotor blade 9.
  • the support zone 5 thus forms an annular cavity open towards the inside of the hollow body and raised relative to the neighboring wall 3 forming the veil.
  • the side walls 7 of the support zone 5 are preferably inclined relative to a perpendicular to the axis of rotation (radial direction) and connected to the web by rounded sections.
  • the central portion 8 has on its outer face to the hollow body, a hollow portion 10 and rounded edges 11 connecting it to the side walls 7.
  • the hollow portion 10 serves as housing for the platform 12 of the rotor blade 9, as will be described below, and is preferably provided with a flat bottom.
  • the rounded edges 11 flanking the hollow portion 10 are at the height of the line 13 which delimits the aerodynamic vein (see figure 1 ).
  • the central portion 8 On its inner side, ie on its face facing the hollow body, the central portion 8 also has rounded edges connecting it to the side walls 7 and a projecting portion 14 directed towards the inside of the annular cavity formed by the support zone 5.
  • the projecting portion 14 may be substantially corresponding in shape to that of the hollow portion 10.
  • the projecting portion 14 comprises an area 16 of an additional piece 15, also called sector.
  • the placement area 16 and the area 15 are planar.
  • the central portion 8 is devoid of housing and the platform of the blade covers the entire central portion.
  • the inner face of the central portion may comprise a projecting portion or be devoid of it.
  • the inner face of the central portion is provided with a sector placement area.
  • the investment area is flat and cooperates with a sector also planar.
  • the central portion may comprise on its outer and inner face rounded edges connecting it to the side walls.
  • one or more openings are formed through the thickness of the central portion 8 to allow the attachment of each platform 12 to the central portion 8.
  • or the orifices are formed through the thickness of the hollow portion 10 of the central portion 8.
  • the rotor blade 9 comprises a blade 17 and an attachment platform 12 located in a plane substantially perpendicular to that of the blade.
  • the platform and the blade of the blade are of such dimensions that the platform 12 is housed in the hollow portion 10 while the blade root of the blade rests partially on the edges rounded 11 framing the housing (see figures 2 and 3 ).
  • the platform 12 comprises a flat surface that cooperates with the flat bottom of the hollow portion 10.
  • the platform may, however, take other forms and fit into a housing of complementary shape.
  • the platform covers the entire central portion and is preferably of complementary shape to the latter.
  • the platform 12 is provided with one or more rods (s) intended (s) to be inserted respectively into the or orifices formed through the thickness of the central portion 8 and allowing fixation from the support zone 5 to the platform 12 of the blade by one or more bolted fasteners, one or more lockbolts or one or more rivets.
  • the platform 12 has a threaded rod 18 at its center and is attached to the support zone 5 by a bolted fastener.
  • the platform 12 comprises one or more orifices for later receiving one or more fastening elements respectively (not shown).
  • the platform comprises one or several orifices and one or more rods (not shown).
  • the inner face of the central portion 8 comprises an investment area 16 of an additional piece 15, also called sector.
  • This piece is provided with one or more orifices intended to be placed (s) facing the orifice (s) formed through the thickness of the central portion.
  • the sector makes it possible not to damage the central part of the support zone during the assembly tensioning of the fastening element or elements.
  • the sector 15 serves to take up the compressive stresses when screwing the nut 19 on the threaded rod 18.
  • the sector is placed between the rod and the lockbolt ring and in the case a rivet, it comes to be placed between the stem and the deformed part of the rivet.
  • the rotor blades are, for example, made of a titanium alloy (TA6V) or aluminum MMC (for Metal Matrix Composite).
  • the drum according to the invention is made of an organic matrix composite material or a metallic material such as, for example, a conventional titanium alloy (TA6V).
  • the rotor according to the invention is lighter in its architecture to reduce the mass of the foot of the blade and remove the cells.
  • This new architecture also makes it possible to introduce new materials (composite drum, MMC aluminum blades) that would not be compatible with a conventional design and thus allows even more significant mass reduction.
  • This drum profile makes it possible to bring the veil of the drum closer to the inner vein, thus minimizing the mass of the blade as mentioned above, a mass that the drum must therefore no longer support.
  • This drum profile also makes it possible to free space for the feet of the stator vanes and the inner ferrules.
  • This fastening system makes it possible to guarantee blade positioning in all operating cases, even at low rotational speeds and even at standstill, in contrast to the conventional design where the blades have a positioning latitude generating, in particular, the phenomena of oscillation (rocking), consumer of axial and radial games.
  • the removal of blade rocking and, consequently, the reduction in the consumption of axial games makes it possible to improve the compactness of the booster and therefore the total mass of the engine.
  • the architecture according to the invention also makes it possible to reduce the radial clearance consumptions by the disappearance of the point masses that are the latches and balancing masses thereof used in the conventional architecture with cells and inducing ovalization of the drum.
  • the decrease of the ovalization of the rotor makes it possible to improve the aero performances via a reduction of the radial clearances as well as a reduction of the variation of these on the same floor.
  • composite materials for the drum also makes it possible to minimize the rotating mass of the drum, and consequently to reduce the amount of material required (thickness) thereon.
  • the use of composite materials for the drum also reduces manufacturing costs through a very significant reduction in material requirements, the mass ratio of the part / material purchased is particularly unfavorable in the case of a starting titanium drum a large forged and requiring a lot of machining unlike composite parts.
  • the architecture according to the invention also provides the possibility of lightening the blower system and mainly the blower disk, by reducing the forces on it from the drum, thanks to the lightening of the rotor low pressure.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP20100166959 2010-06-23 2010-06-23 Leichterer Rotor für Axialkompressor Active EP2400160B1 (de)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP20100166959 EP2400160B1 (de) 2010-06-23 2010-06-23 Leichterer Rotor für Axialkompressor
US13/165,178 US8870543B2 (en) 2010-06-23 2011-06-21 Lightened axial compressor rotor
RU2011125136/06A RU2011125136A (ru) 2010-06-23 2011-06-21 Облегченный ротор осевого компрессора
CA2743817A CA2743817C (en) 2010-06-23 2011-06-21 Lightened axial compressor rotor
CN201110170449A CN102297158A (zh) 2010-06-23 2011-06-23 轴流式压缩机的减轻转子

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP20100166959 EP2400160B1 (de) 2010-06-23 2010-06-23 Leichterer Rotor für Axialkompressor

Publications (2)

Publication Number Publication Date
EP2400160A1 true EP2400160A1 (de) 2011-12-28
EP2400160B1 EP2400160B1 (de) 2014-01-01

Family

ID=43014987

Family Applications (1)

Application Number Title Priority Date Filing Date
EP20100166959 Active EP2400160B1 (de) 2010-06-23 2010-06-23 Leichterer Rotor für Axialkompressor

Country Status (5)

Country Link
US (1) US8870543B2 (de)
EP (1) EP2400160B1 (de)
CN (1) CN102297158A (de)
CA (1) CA2743817C (de)
RU (1) RU2011125136A (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2706242A1 (de) * 2012-09-11 2014-03-12 Techspace Aero S.A. Befestigung von Laufradschaufeln auf einer Rotortrommel eines Axialkompressors
WO2015171670A1 (en) * 2014-05-08 2015-11-12 General Electric Company Composite booster spool with separable composite blades
EP3751102A1 (de) 2019-06-11 2020-12-16 Safran Aero Boosters SA Rotor für den kompressor einer rotationsmaschine und zugehöriges fertigungsverfahren

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2762681B1 (de) * 2013-02-04 2017-09-06 Safran Aero Boosters SA Rotortrommel einer axialen Turbomaschine und zugehörige Turbomaschine

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2477954A (en) * 1947-04-01 1949-08-02 Blanc Jacques Jean Louis Gas turbine
US2685405A (en) * 1948-05-03 1954-08-03 Edward A Stalker Axial flow compressor
US2925250A (en) * 1952-05-30 1960-02-16 Power Jets Res & Dev Ltd Blades for compressors, turbines and the like
GB1163752A (en) 1965-11-25 1969-09-10 Edgar Allen Aerex Ltd Improvements in and relating to Axial-Flow Fluid Machines of the Rotary kind
US3609059A (en) * 1969-10-03 1971-09-28 Gen Motors Corp Isothermal wheel
GB2299834A (en) * 1995-04-12 1996-10-16 Rolls Royce Plc Gas turbine engine fan disc
EP1111246B1 (de) 1999-12-21 2003-08-13 Techspace Aero S.A. Steifes Ringteil

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5118257A (en) * 1990-05-25 1992-06-02 Sundstrand Corporation Boot attachment for composite turbine blade, turbine blade and method of making turbine blade
EP1319805A1 (de) * 2001-12-17 2003-06-18 Techspace aero Rotor oder Rototelement für Turbokompressoren

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2477954A (en) * 1947-04-01 1949-08-02 Blanc Jacques Jean Louis Gas turbine
US2685405A (en) * 1948-05-03 1954-08-03 Edward A Stalker Axial flow compressor
US2925250A (en) * 1952-05-30 1960-02-16 Power Jets Res & Dev Ltd Blades for compressors, turbines and the like
GB1163752A (en) 1965-11-25 1969-09-10 Edgar Allen Aerex Ltd Improvements in and relating to Axial-Flow Fluid Machines of the Rotary kind
US3609059A (en) * 1969-10-03 1971-09-28 Gen Motors Corp Isothermal wheel
GB2299834A (en) * 1995-04-12 1996-10-16 Rolls Royce Plc Gas turbine engine fan disc
EP1111246B1 (de) 1999-12-21 2003-08-13 Techspace Aero S.A. Steifes Ringteil

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2706242A1 (de) * 2012-09-11 2014-03-12 Techspace Aero S.A. Befestigung von Laufradschaufeln auf einer Rotortrommel eines Axialkompressors
US9598968B2 (en) 2012-09-11 2017-03-21 Safran Aero Boosters Sa Attaching the blades to the drum of an axial turbocompressor
WO2015171670A1 (en) * 2014-05-08 2015-11-12 General Electric Company Composite booster spool with separable composite blades
US10422340B2 (en) 2014-05-08 2019-09-24 General Electric Company Composite booster spool with separable composite blades
EP3751102A1 (de) 2019-06-11 2020-12-16 Safran Aero Boosters SA Rotor für den kompressor einer rotationsmaschine und zugehöriges fertigungsverfahren
BE1027359A1 (fr) 2019-06-11 2021-01-14 Safran Aero Boosters Sa Rotor hybride à coquille externe rapportée contre la paroi annulaire composite

Also Published As

Publication number Publication date
EP2400160B1 (de) 2014-01-01
CA2743817C (en) 2016-10-25
US8870543B2 (en) 2014-10-28
RU2011125136A (ru) 2012-12-27
US20110318185A1 (en) 2011-12-29
CA2743817A1 (en) 2011-12-23
CN102297158A (zh) 2011-12-28

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