EP1319805A1 - Rotor oder Rototelement für Turbokompressoren - Google Patents

Rotor oder Rototelement für Turbokompressoren Download PDF

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Publication number
EP1319805A1
EP1319805A1 EP01870278A EP01870278A EP1319805A1 EP 1319805 A1 EP1319805 A1 EP 1319805A1 EP 01870278 A EP01870278 A EP 01870278A EP 01870278 A EP01870278 A EP 01870278A EP 1319805 A1 EP1319805 A1 EP 1319805A1
Authority
EP
European Patent Office
Prior art keywords
rotor
blades
series
crowns
feet
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Withdrawn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
EP01870278A
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 EP01870278A priority Critical patent/EP1319805A1/de
Priority to US10/323,863 priority patent/US20030143078A1/en
Publication of EP1319805A1 publication Critical patent/EP1319805A1/de
Withdrawn legal-status Critical Current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
    • F01D5/30—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
    • F01D5/3023—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
    • 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

Definitions

  • the present invention relates to compressors, especially to turbochargers.
  • Turbochargers are well known in the state of the art and are used in particular for twin-engine engines, turbofan engines and turbojets.
  • turbochargers which can be low pressure type or high pressure type, are, essentially, consisting of a succession of floors rotor blades alternating with stages stator blades (also called floors) Rectifiers).
  • the series of moving blades of the different rotor stages successive compressors are fixed on one and single rotor element or rotor.
  • At the periphery of the said rotor are machined a succession of grooves that allow the entrenchment of the feet of the blades of different rotor stages.
  • this rotor will comprise, disposed at its periphery, several annular grooves.
  • the rotor will therefore include, arranged in a first radius in a circular manner, a first gorge in which will be arranged a first series of blades to form a first rotor stage.
  • the rotor will then include, arranged at a certain distance from the first gorge (which corresponds to the width of a rectifier stage), a second throat in which will be arranged a second series of blades of to form a second rotor stage, and thus to after.
  • the latter is provided with at least one notch or radial opening which allows the successive insertion of feet of the series of moving blades.
  • blocking means such as locks are used to block the foot of this last dawn moving. These locking means allow also avoid moving the feet of the series of moving blades within the annular groove.
  • the means of blocking, and particular locks, used to immobilize blades in the corresponding grooves cause disturbances of the aerodynamic vein of the fluid, which generates loss of charge and harmful vibrations at smooth operation of the turbocharger.
  • a last major disadvantage of the presence of such blocking devices lies in the ovalization of the rotor after a certain period of operation.
  • This platform or platinum aims to increase the rigidity of the blade / foot set of dawn mobile.
  • the present invention aims to remedy disadvantages stated above of the rotors of known turbochargers, by providing a rotor of new design intended more particularly for a low pressure compressor.
  • the present invention aims to to propose a solution that avoids the problem of double wall created within a drum serving as a rotor and especially in a monobloc type drum or multiblock.
  • the present invention also aims to allow for simplification and simplification of realization of the blades.
  • the present invention aims to propose a solution in which the attachment of the blades in the rotor grooves is simplified and does not require plus the use of blocking elements such as locks generating disturbances.
  • the present invention relates to a rotor or rotor element for a turbocharger, constituting supporting at least one rotor blade stage, in which at least one groove is provided to allow the engagement of the feet of a series of moving blades, characterized in that said blades are not no platform or platinum.
  • the blades are directly connected to a foot, presenting either a dovetail shape, a flat shape. This allows advantageously to eliminate the problem of the presence of a double wall for the aerodynamic vein at the turbocharger operation.
  • the rotor has additional features that still make it possible to improve the present invention in standardizing the aerodynamic vein. For this purpose, we avoid the presence of lateral notches for introducing vanes mobile and therefore locks.
  • said rotor or rotor element includes at least two individual crowns comprising their lateral periphery of the half-profiles which, during the juxtaposition of individual crowns, realize a complete throat in which are engaged the feet of a series of blades. Each gorge is delimited by lips or edges.
  • Half-profile means a form that delimits laterally said crown and which allows recreate a complete gorge with a bottom or not when one docks or juxtaposes two crowns successive.
  • This profile can be constituted in the form of a half-cell or half-groove or in planar form.
  • the invention relates to a rotor or rotor element for a turbocharger comprising a single rotor stage with a single series of blades.
  • the rotor is essentially annular and is formed of two annular crowns which are juxtaposed.
  • Half profiles are arranged laterally on the periphery of each of the crowns, so that the half-profiles of a crown are next to the half-profiles of the consecutive crown to restore the throat intended for receive the feet of the series of moving blades of the floor rotor.
  • the fixation of the two rotor crowns can be achieved by any known means suitable and is preferably made removable. In this Indeed, it can for example be achieved 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 fastening means the advantage of allowing the replacement of a dawn deteriorated for example.
  • the two consecutive crowns are removably attached to one another by a assembly of bolts and nuts passing through flanges integral with said crowns.
  • the half-profiles of the crown have a shape such as the throat formed by the juxtaposition of the two half-profiles will have a shape complementary to the profile of the feet of the series of blades that will be housed or engaged in said throat.
  • the half-profiles of the crown have a shape of half-cells, so that the throat formed by the juxtaposition both half-profiles have a dovetail profile which will correspond to the profile of the so-called shaped feet of the series of blades that will be housed or engaged in said throat.
  • the half-profiles of crowns have a flat shape so that the throat formed by the juxtaposition of the two half-profiles present a groove that allows the rectilinear feet or planes of the series of blades to be housed there.
  • the immobilization of the series of blades within a throat can then be advantageously obtained by any appropriate means, for example to using a locking screw passing through the rotor.
  • this invention relates to a turbocharger rotor comprising a succession of rotor stages, the rotor being common in this case to several floors with several series of blades.
  • the turbocharger includes two series of moving blades and the rotor comprises a crown intermediate and two end crowns.
  • the crown intermediary has on each of its faces half-profiles that correspond to the half-profiles present on each of the end crowns so as to reconstitute during assembly the two complete grooves for the embedding of the two series of blades of two successive rotor stages.
  • the invention also relates to a turbocharger comprising a stator and a rotor compliant to the invention, as defined above.
  • the stator comprises one or more stages of fixed vanes, alternating with the rotor blade stages of the rotor.
  • the turbocharger according to the invention can for example be a turbofan, a turbojet or a gas turbine coupled to an alternator for the electricity production.
  • the invention has many advantages, both with regard to the construction of the rotors and the operation of turbochargers.
  • Rotor construction is simpler and more economical because it no longer imposes expensive machining of grooves complete in the rotor or that of blade supports correspondents.
  • it removes the need to make side openings through the rotor for the passage of the blades, which simplifies the construction of the rotor and avoids the presence of high stress areas in the rotor.
  • the invention has the advantage additional reduction of pressure losses in fluid flow, to reduce vibrations in the turbochargers and especially reduce or remove ovalization of the rotor in operation. All others other things being equal, it presents as well the advantage of improving the efficiency of turbochargers and to reduce the mechanical stresses to which they are subject.
  • This invention also has the advantage to provide a lighter rotor assembly by the presence of a single wall instead of a double wall as in the state of the art.
  • Figure 1 represents 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.
  • FIG. 3 is an exploded view, in elevation, of a part of a rotor showing the elements of blocking constituted by the locks used to secure the last dawn in a throat according to the state of the art.
  • FIG. 4 represents a sectional view cross-section of a rotor according to the state of the art.
  • Figure 5 is a cross-sectional view of a rotor according to an embodiment which combines two forms particular embodiments of the present invention.
  • the floor of compression of a turbofan is conventionally composed of a series of rotor stages 3,3 ', 3 ", ... alternating with a series of stator stages or rectifiers 2,2 ', 2 ", ...
  • the gas When the turbofan is running, the gas first crosses the first stage rectifier 2 of compressor where its velocity vector is repositioned so to be driven by the second rotor stage 3 'of blades rotating before joining the second stage rectifier 2 'to be repositioned in 3 ", etc. Gas undergoes a training cycle - repositioning to the outcome of which its kinetic energy decreases gradually while its pressure increases.
  • Each rotor stage 3,3 ', 3 ", ... comprises a series of blades 70,71,72, ... and each floor rectifier or stator 2.2 ', 2 ", ... includes a series of fixed blades respectively 60,61,62, ...
  • Each stage rectifier 2,2 ', 2 ", ... includes in addition an inner ring respectively 4,4 ', 4 ", ... connected to an outer ring respectively 5,5 ', 5 ", ... by the series of fixed blades respectively 60,61,62, ...; 60 ', 61', 62 ', ... or 60 ", 61", 62 “, ... Said ferrules interior 4,4 ', 4 ", ... and said outer ferrules 5,5 ', 5 “, ... are therefore specific to each floor rectifiers 2,2 ', 2 ", ...
  • FIGS. 2 and 3 Such a rotor is shown in FIGS. 2 and 3 according to the technological background. It corresponds to a one-piece annular rotor 100, fixed transversely to a disk 15 (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 ", grooves 10,10', 10" are intended to receive feet 80,81,82, ...; 80 ', 81', 82 ', ... and 80 ", 81", 82 “, ... series successive blades 70,71,72, ...; 70 ', 71', 72 ', ... and 70 ", 71", 72 “, ...
  • Fig. 3 represents a throat 10 in which are housed successively the feet 80,81,82, ... 89 blades 70,71,72, ... 79 of a single rotor stage.
  • lateral openings 14 are in the throat 10. After the introduction of the last dawn 79, it is fixed by means of one or several locking elements 30,32.
  • Fig. 4 represents the rotor according to the state of the technique in which we have represented for different rotor stages 3,3 ', 3 "series of blades 70.70 ', 70 "made according to the state of the art.
  • These blades are blades having a platform or platen 90,90 ', 90 ".
  • each foot 80,80 'of dawn 70,70 ' is engaged in said groove 10,10', in such a way platform or platinum 90,90 'present at the level of the terminal part of the 70.70 'moving blade above the foot is able to rest on the lips or ledges of said throat.
  • turntables generates the presence of a double wall in the aerodynamic vein, one of the walls being constituted directly by the rotor 100 constituting the support of the different floors rotor and the other wall consisting of the 90,90 'platforms of 70,70' moving blades, ....
  • FIG. 5 a rotor according to the present invention. It represents a frame of mind in which two rotor stages are shown.
  • the first rotor stage 3 is constituted a series of blades 70,71, ... all similar and having a foot 80,81, ... straight or flat, while the second rotor stage 3 'has vanes 70 ', 71', ... all similar and having a foot 80 ', 81', ... shaped like a dovetail.
  • the grooves 10 and 10 'intended to receive the feet first and second stages 3 and 3 ' are formed of different way.
  • the blades mobile devices do not have a platform or platinum, which allows from the rotor profile 100 to generate directly the aerodynamic vein.
  • the various series of blades 70,71, ...; 70 ', 71', ... have a functional part consisting of a pale directly in contact with the corresponding foot 80,81, ...; 80 ', 81', ... without the presence of platforms or platinum extending substantially perpendicular to said dawn.
  • the rotor 100 is consisting of at least two crowns, and in this case of three crowns 20, 21 and 22.
  • the intermediate ring 21 has on each of its lateral faces an annular half-profile 111, 110 ', while the end rings 20 and 22 present on only one of their two lateral faces a half-profile annular 110, respectively 111 'corresponding to that (111, respectively 110 ') disposed opposite on the crown to which he is juxtaposed.
  • the juxtaposition of these half-profiles 110,111; 110 ', 111' will make a throat complete 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 appropriate means.
  • profiles of the throats and therefore the half-profiles constituting them can take forms various and other than those mentioned in both preferred execution examples. These profiles can be of shape dovetail, circular or polygonal. Similarly, the feet of the blades can also be shaped dovetail, circular or polygonal, provided that that the profile of said feet of said 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)
EP01870278A 2001-12-17 2001-12-17 Rotor oder Rototelement für Turbokompressoren Withdrawn EP1319805A1 (de)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP01870278A EP1319805A1 (de) 2001-12-17 2001-12-17 Rotor oder Rototelement für Turbokompressoren
US10/323,863 US20030143078A1 (en) 2001-12-17 2002-12-17 Rotor or rotor element for a turbocompressor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP01870278A EP1319805A1 (de) 2001-12-17 2001-12-17 Rotor oder Rototelement für Turbokompressoren

Publications (1)

Publication Number Publication Date
EP1319805A1 true EP1319805A1 (de) 2003-06-18

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ID=8185070

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01870278A Withdrawn EP1319805A1 (de) 2001-12-17 2001-12-17 Rotor oder Rototelement für Turbokompressoren

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EP (1) EP1319805A1 (de)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ES2254652T3 (es) * 2001-03-05 2006-06-16 Georg Gros Mezcla de revestimiento a base de agua, procedimiento para aplicar una capa de proteccion frente a la corrosion con esta mezcla, base revestida de este modo y su uso.
EP1499687A1 (de) * 2002-04-20 2005-01-26 Chemetall GmbH Gemisch zum aufbringen eines polymeren korrosionsbest ndigen elektrisch schweissbaren berzugs und verfahren zum herstel len dieses berzugs
EP2400160B1 (de) * 2010-06-23 2014-01-01 Techspace Aero S.A. Leichterer Rotor für Axialkompressor
GB201118386D0 (en) 2011-10-25 2011-12-07 Rolls Royce Plc A support ring for a rotary assembly
GB201203303D0 (en) * 2012-02-27 2012-04-11 Rolls Royce Plc Balancing of rotor
US10633986B2 (en) * 2018-08-31 2020-04-28 Rolls-Roye Corporation Platform with axial attachment for blade with circumferential attachment

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE830854C (de) * 1949-10-05 1952-02-07 Maschf Augsburg Nuernberg Ag Keramiklaufschaufel fuer axial durchstroemte Kreiselradmaschinen
GB1375327A (de) * 1971-09-17 1974-11-27
US4135857A (en) * 1977-06-09 1979-01-23 United Technologies Corporation Reduced drag airfoil platforms
US4802824A (en) * 1986-12-17 1989-02-07 Societe Nationale D'etude Et Moteurs D'aviation "S.N.E.C.M.A." Turbine rotor
US5007800A (en) * 1988-10-05 1991-04-16 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Rotor blade fixing for turbomachine rotors
EP1124038A1 (de) * 2000-02-09 2001-08-16 Siemens Aktiengesellschaft Turbinenschaufelanordnung

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE507205A (de) * 1950-12-08
US3455537A (en) * 1967-09-27 1969-07-15 Continental Aviat & Eng Corp Air-cooled turbine rotor self-sustaining shroud plate
CH581783A5 (de) * 1975-01-30 1976-11-15 Bbc Sulzer Turbomaschinen
DE2915201C2 (de) * 1979-04-14 1986-02-27 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Laufrad für Axialströmungsmaschinen, insbesondere Verdichter

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE830854C (de) * 1949-10-05 1952-02-07 Maschf Augsburg Nuernberg Ag Keramiklaufschaufel fuer axial durchstroemte Kreiselradmaschinen
GB1375327A (de) * 1971-09-17 1974-11-27
US4135857A (en) * 1977-06-09 1979-01-23 United Technologies Corporation Reduced drag airfoil platforms
US4802824A (en) * 1986-12-17 1989-02-07 Societe Nationale D'etude Et Moteurs D'aviation "S.N.E.C.M.A." Turbine rotor
US5007800A (en) * 1988-10-05 1991-04-16 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Rotor blade fixing for turbomachine rotors
EP1124038A1 (de) * 2000-02-09 2001-08-16 Siemens Aktiengesellschaft Turbinenschaufelanordnung

Also Published As

Publication number Publication date
US20030143078A1 (en) 2003-07-31

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