EP1319842A1 - Rotor oder rotierendes Element für Turboverdichter - Google Patents

Rotor oder rotierendes Element für Turboverdichter Download PDF

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Publication number
EP1319842A1
EP1319842A1 EP01870277A EP01870277A EP1319842A1 EP 1319842 A1 EP1319842 A1 EP 1319842A1 EP 01870277 A EP01870277 A EP 01870277A EP 01870277 A EP01870277 A EP 01870277A EP 1319842 A1 EP1319842 A1 EP 1319842A1
Authority
EP
European Patent Office
Prior art keywords
rotor
series
feet
movable blades
crowns
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.)
Withdrawn
Application number
EP01870277A
Other languages
English (en)
French (fr)
Inventor
Dante Benedetto
Jack-Pierre Lauvergnat
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 EP01870277A priority Critical patent/EP1319842A1/de
Publication of EP1319842A1 publication Critical patent/EP1319842A1/de
Withdrawn legal-status Critical Current

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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
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • 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
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
    • 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
    • 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
    • F01D5/3069—Fixing blades to rotors; Blade roots ; Blade spacers between two discs or rings

Definitions

  • the present invention relates to compressors, especially for turbochargers.
  • turbocharger rotors It relates more particularly to turbocharger rotors.
  • Turbochargers are well known in the state of the art and are used in particular for double body engines, turbofans and turbojets.
  • turbochargers which can be low pressure type or high pressure type, are, essentially consisting of a succession of floors rotor blades moving alternately with stages stator of fixed blades (also called stages rectifiers).
  • the blades of the different successive rotor stages of the compressors are fixed on a single element rotor or rotor. At the periphery of said rotor are machined a succession of grooves which allow the embedding of the feet of the moving blades of the different rotor stages.
  • this rotor will include, arranged at its periphery, several annular grooves.
  • the rotor will therefore include, arranged in a first radius in a circular manner, a first groove in which a first will be placed series of movable blades so as to constitute a first rotor stage.
  • the rotor will then include, arranged at a certain distance from the first groove (which corresponds to the width of a rectifier stage), a second groove in which will be arranged a second series of movable blades of so as to constitute a second rotor stage, and so after.
  • the latter is provided with at least one notch or radial opening which allows successive insertion of feet of the series of movable blades.
  • suitable locking means such as locks are used to block the foot of this last moving dawn.
  • These blocking means allow also to avoid any displacement of the feet of the series movable blades within the annular groove.
  • the blocking means and in especially locks, used to immobilize blades in the corresponding grooves cause disturbances in the aerodynamic vein of the fluid, which generates pressure losses and harmful vibrations correct operation of the turbocharger.
  • the present invention aims to remedy the disadvantages stated above of rotors of known turbochargers, providing a rotor of new design intended more particularly for a low pressure compressor and in which the fixing of movable blades in the rotor grooves is simplified and does not no longer requires the use of blocking elements such as locks, disturbance generators.
  • the present invention relates to a rotor or rotor element for a turbocharger, constituting supporting at least one rotor stage of movable blades, in which at least one groove is provided to allow the engagement of the feet of a series of movable blades, characterized in that said rotor or rotor element includes at least two individual crowns comprising at their lateral periphery of the half-profiles which, when juxtaposition of individual crowns, make a full throat in which the feet of a series of moving blades. Each gorge is delimited by lips or edges.
  • Half-profile means a shape which laterally delimits said crown and which makes it possible to recreate a full throat with or without bottom when two crowns are docked or juxtaposed successive.
  • This profile could be formed by the juxtaposition of two half-cells (1/2 per crown juxtaposed) or two half-grooves or simply be under flat shape.
  • the invention relates to a rotor or rotor element for turbocharger with a single rotor stage with a single series of movable blades.
  • the ferrule is essentially annular and is formed by two annular crowns which are juxtaposed.
  • Half-profiles are arranged laterally at the periphery of each of the crowns, so that the half-profiles of a crown are located opposite the half-profiles of the consecutive crown to reconstruct the throat intended for receive the feet of the series of movable blades of the stage rotor.
  • the fixing of the two rotor crowns can be made by any known means suitable and is preferably made removable. In this effect, it can for example be produced by welding, at by means of rivets or by means of screws.
  • a means of fixing the crowns which is removable.
  • the use of a removable fixing means presents the advantage of allowing the replacement of a dawn deteriorated for example.
  • the two consecutive crowns are removably attached to each other by a assembly of bolts and nuts passing through flanges integral with said crowns.
  • the half-profiles of the crown have a shape such that the throat formed by the juxtaposition of the two half-profiles will present a shape complementary to the profile of the feet of the series of movable blades that will be embedded or engaged in said throat.
  • the half-profiles of the crown have the shape of a half-cell, so that the groove formed by the juxtaposition of the two half-profiles has a dovetail profile which will correspond to the profile of the so-called feet of the series of movable blades which will be embedded or engaged in said throat.
  • the half-profiles of the crowns have a flat shape so that the groove formed by the juxtaposition of the two half-profiles present a groove which allows the straight feet or planes of the series of movable blades to be enshrined there.
  • Immobilization of the series of movable blades within a throat can then advantageously be obtained by any suitable means, for example at using a locking screw passing through the rotor.
  • the present invention relates to a rotor for a turbocharger comprising a succession of rotor stages, the rotor being common in this case multi-storey with multiple moving blade series.
  • the turbocharger includes two series movable blades and the rotor comprises a crown intermediate and two end rings.
  • the crown intermediate present on each of its faces half-profiles which correspond to the half-profiles present on each of the end rings so that reconstitute during assembly the two complete grooves for embedding the two sets of movable blades of two successive rotor stages.
  • the invention also relates to a turbocharger comprising a stator and a conforming rotor to the invention, as defined above.
  • the stator comprises one or more stages of fixed blades, alternating with the stages of rotating blades of the rotor.
  • the turbocharger according to the invention can for example being a turbofan, a turbojet or a gas turbine coupled to an alternator for the electricity production.
  • the invention has multiple advantages, both with regard to the construction of the rotors and the operation of turbochargers.
  • the rotor construction is simpler and more economical because it no longer requires expensive machining of grooves complete nor that of corresponding blade supports.
  • it removes the need to practice side openings through the rotor for the passage of blades, which simplifies the construction of the rotor and avoids the presence of high stress areas in the rotor.
  • Born requiring more blade retainer locks on the rotor the invention has the additional advantage of reduce the pressure losses in the fluid flow, reduce vibrations in turbochargers and especially to reduce or eliminate the ovalization of the rotor by operation. All other things being equal by elsewhere, it thus has the advantage of improving the performance of turbochargers and reduce mechanical stresses to which they are subjected.
  • Figure 1 shows a general view of a classic turbocharger.
  • Figure 2 is a cross-sectional view of a part of a rotor according to the state of the art.
  • Figure 3 is an exploded view, in elevation, of a part of a rotor showing the elements of blocking constituted by locks used to fix the last dawn in a gorge according to the state of the art.
  • Figure 4 is a cross-sectional view of a rotor according to an embodiment which combines two forms particular execution of the present invention.
  • the floor of compression of a turbofan is composed of a series of stages rotor 3.3 ', 3 ", ... alternating with a series of stages stator or rectifiers 2,2 '/ 2 ", ...
  • Fig. 1 for each floor, only shows in section that the first blade 70, 70 ', 70 "for each rotor stage or 60, 60 ', 60 "for each stage rectifier or stator.
  • each rotor stage 3.3 ', 3 ", ... includes a series of movable blades 70,71,72, ...
  • each rectifier or stator stage 2,2 ', 2 ", ... includes a series of fixed vanes respectively 60,61,62 ...
  • Each rectifier stage 2,2 ', 2 ", ... includes in addition an inner ferrule respectively 4.4 ', 4 ", ... connected to an outer shroud respectively 5.5 ', 5 ", ... by the series of fixed vanes respectively 60,61,62, ...; 60 ', 61', 62 ', ... or 60 ", 61", 62 “, ... Said ferrules interior 4,4 ', 4 ", ... and said exterior ferrules 5.5 ', 5 ", ... are therefore specific to each of the floors 2.2 ', 2 "rectifiers, ...
  • Such a rotor is shown in Figs. 2 and 3 according to the technological background. It corresponds to a monobloc annular rotor 100, fixed transversely to a disc 15 (intended for example to be coupled to a motor).
  • the rotor 100 is generally made of titanium.
  • the throats 10,10 ', 10 are machined at its periphery and correspond each with a rotor stage 3,3 ', 3 ".
  • the grooves 10,10', 10" are intended to receive the feet 80,81,82, ...; 80 ', 81', 82 ', ... and 80 ", 81", 82 “, ... series successive blades 70,71,72, ...; 70 ', 71', 72 ', ... and 70 ", 71", 72 ", ...
  • the gas When the turbofan is running, the gas first crosses the first rectifier stage 2 of the compressor where its speed vector is repositioned so to be driven by the second rotor rotor stage turning 3 'before reaching the second floor rectifier 2 'to be repositioned again in 3 ", etc. The gas thus undergoes a training cycle repositioning at the end of which its kinetic energy gradually decreases as its pressure increases.
  • Fig. 3 represents a groove 10 in which are successively set the feet 80,81,82, ... 89 of the moving blades 70,71,72, ... 79 of only one rotor stage.
  • the rotor shown in FIG. 4 complies to the present invention. It represents a view of mind in which two rotor stages are shown.
  • the first rotor stage 3 is constituted of a series of movable vanes 70, 71, ... all similar and with a foot 80.81, ... in the form of a dovetail, while the second rotor stage 3 'has blades 70 ', 71', ... all similar and having a foot 80 ', 81', ... straight or flat.
  • the rotor 100 is made up of at least two crowns, and in this case three crowns 20, 21 and 22 intended to achieve the inner ferrule of the different rotor stages 3.3 ′.
  • the intermediate crown 21 present on each from its lateral faces an annular half-profile
  • the end rings 20 and 22 present on a single of their two lateral faces an annular half-profile corresponding to that placed opposite on the crown which it is jusxtaposed.
  • the juxtaposition of these half-profiles will make a full groove 10,10 ' allowing the insertion of the feet 80,81, ... or 80 ', 81', ... series of blades 70, 71, ... or 70 ', 71', ...
  • the crowns 20,21,22 are joined to each other so as to form the rotor 100 completely.
  • the fixing of the various crowns is carried out using any suitable means.
  • profiles of the grooves and therefore the half-profiles constituting them can take forms various and other than those mentioned in the two preferred execution examples. These profiles can be dovetail shape, circular or polygonal. Likewise, the feet of the movable blades can also be shaped dovetail, circular or polygonal, provided that the profile of said feet of said movable blades is complementary and corresponds to that of said grooves.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP01870277A 2001-12-17 2001-12-17 Rotor oder rotierendes Element für Turboverdichter Withdrawn EP1319842A1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP01870277A EP1319842A1 (de) 2001-12-17 2001-12-17 Rotor oder rotierendes Element für Turboverdichter

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP01870277A EP1319842A1 (de) 2001-12-17 2001-12-17 Rotor oder rotierendes Element für Turboverdichter

Publications (1)

Publication Number Publication Date
EP1319842A1 true EP1319842A1 (de) 2003-06-18

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EP01870277A Withdrawn EP1319842A1 (de) 2001-12-17 2001-12-17 Rotor oder rotierendes Element für Turboverdichter

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EP (1) EP1319842A1 (de)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2204541A1 (de) 2008-12-24 2010-07-07 Techspace Aero S.A. Rotorstufe einer einteilig beschaufelten Verdichtertrommel einer axialen Strömungsmaschine und entsprechendes Herstellungsverfahren.
EP2369136A1 (de) * 2010-03-12 2011-09-28 Techspace Aero S.A. Gewichtsreduzierte einteilige Mehrstufentrommel eines Axialverdichters
EP2236757A3 (de) * 2009-03-17 2013-10-23 United Technologies Corporation Geteilte Rotorscheibenanordnung für ein Gasturbinentriebwerk
US20230167745A1 (en) * 2021-11-26 2023-06-01 Ge Avio S.R.L Gas turbine engine including a rotating blade assembly

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR900378A (fr) * 1941-09-08 1945-06-27 Daimler Benz Ag Rotors pour turbo-machines axiales, en particulier pour compresseurs axiaux
DE829970C (de) * 1945-01-03 1952-01-31 Maschf Augsburg Nuernberg Ag Befestigung keramischer Schaufeln in Stahlbauteilen von Kreiselmaschinen
US2738126A (en) * 1950-12-08 1956-03-13 Armstrong Siddeley Motors Ltd Construction of compressor rotors
GB1549070A (en) * 1977-12-12 1979-08-01 Rolls Royce Gas turbine engine compressor rotor construction

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR900378A (fr) * 1941-09-08 1945-06-27 Daimler Benz Ag Rotors pour turbo-machines axiales, en particulier pour compresseurs axiaux
DE829970C (de) * 1945-01-03 1952-01-31 Maschf Augsburg Nuernberg Ag Befestigung keramischer Schaufeln in Stahlbauteilen von Kreiselmaschinen
US2738126A (en) * 1950-12-08 1956-03-13 Armstrong Siddeley Motors Ltd Construction of compressor rotors
GB1549070A (en) * 1977-12-12 1979-08-01 Rolls Royce Gas turbine engine compressor rotor construction

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2204541A1 (de) 2008-12-24 2010-07-07 Techspace Aero S.A. Rotorstufe einer einteilig beschaufelten Verdichtertrommel einer axialen Strömungsmaschine und entsprechendes Herstellungsverfahren.
US8414256B2 (en) 2008-12-24 2013-04-09 Techspace Aero, S.A. One-piece bladed drum of an axial turbomachine compressor
EP2236757A3 (de) * 2009-03-17 2013-10-23 United Technologies Corporation Geteilte Rotorscheibenanordnung für ein Gasturbinentriebwerk
EP2369136A1 (de) * 2010-03-12 2011-09-28 Techspace Aero S.A. Gewichtsreduzierte einteilige Mehrstufentrommel eines Axialverdichters
US8932012B2 (en) 2010-03-12 2015-01-13 Techspace Aero S.A. Reduced monobloc multistage drum of axial compressor
US20230167745A1 (en) * 2021-11-26 2023-06-01 Ge Avio S.R.L Gas turbine engine including a rotating blade assembly

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