EP1678411B1 - Turbomachine et rotor a aubes pour un etage de compression d'une turbomachine - Google Patents

Turbomachine et rotor a aubes pour un etage de compression d'une turbomachine Download PDF

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Publication number
EP1678411B1
EP1678411B1 EP04789909A EP04789909A EP1678411B1 EP 1678411 B1 EP1678411 B1 EP 1678411B1 EP 04789909 A EP04789909 A EP 04789909A EP 04789909 A EP04789909 A EP 04789909A EP 1678411 B1 EP1678411 B1 EP 1678411B1
Authority
EP
European Patent Office
Prior art keywords
rotor
blade
width
blades
blade pitch
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.)
Expired - Fee Related
Application number
EP04789909A
Other languages
German (de)
English (en)
Other versions
EP1678411A1 (fr
Inventor
Richard Scharl
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
MTU Aero Engines AG
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 MTU Aero Engines GmbH, MTU Aero Engines AG filed Critical MTU Aero Engines GmbH
Publication of EP1678411A1 publication Critical patent/EP1678411A1/fr
Application granted granted Critical
Publication of EP1678411B1 publication Critical patent/EP1678411B1/fr
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • 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
    • 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
    • F05D2200/00—Mathematical features
    • F05D2200/30—Mathematical features miscellaneous
    • F05D2200/33—Mathematical features miscellaneous bigger or smaller
    • 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
    • F05D2240/80—Platforms for stationary or moving blades

Definitions

  • the invention relates to a turbomachine, in particular a gas turbine, according to the preamble of claim 7. Furthermore, the invention relates to a rotor for a compressor stage of a turbomachine according to the preamble of patent claim 1.
  • the blades are subjected to high mechanical loads during operation of the rotor or the turbomachine as a result of high rotational speeds, it is important that the blade roots, in particular in the region of a blade neck, have a sufficiently large cross section and thus sufficient strength. Since the width of the Be Schollungsnut must be adapted to the width of the blade roots and further protrude after assembly of the blades in the retaining groove of the rotor no Schaufelfuß in the Be spallungsnut, according to the prior art, the blades have blade roots, the maximum width of the have half blade pitch. Under the blade pitch is to be understood in the circumferential direction of the rotor seen, caused by the circumferential extent of the blades distribution distribution of the blades over the circumference of the rotor.
  • the present invention is based on the problem to provide a novel turbomachine and a novel rotor for a compressor stage of a turbomachine.
  • the width of the blade roots and the width of the or each filling groove in the circumferential direction is greater than half the width of a desired or nominal blade pitch, wherein in the region of the or each filling groove instead of a first number of blades with nominal blade pitch a second number of blades with enlarged blade pitch is positioned, and wherein the first number is greater than the second number.
  • a plurality of filling grooves are evenly distributed over the circumference of the rotor, wherein the width of each filling groove in the circumferential direction is greater than half the width of a desired, nominal blade pitch, wherein in the region of each Be somnllungsnut instead of a first number of blades with nominal Blade pitch a second number of blades with increased blade pitch is positioned, and wherein the first number is greater than the second number.
  • turbomachine according to the invention is characterized by the features of independent claim 7.
  • FIG. 1 shows a section of a rotor 10 of a compressor of a turbomachine, in particular a gas turbine. According to Fig. 1 are in the circumferential direction of the rotor 10 side by side a plurality of blades 11 and 12 respectively.
  • Fig. 1 is a highly schematized representation, so that Fig. 1 only the blade roots 13 and 14 of the blades 11 and 12 shows. Only for two blades 11 in the right edge of the Fig. 1 the blades 15 are indicated the same.
  • the rotor blades 11 and 12 are fixed with their blade roots 13 and 14, respectively, in a retaining groove extending in the circumferential direction of the rotor 10.
  • This retaining groove is in Fig. 1 represented by a designated by the reference numeral 16 line.
  • a Be Schollungsnut 17 is arranged in the area of in Fig. 1 shown peripheral portion of the rotor 10 in the area of in Fig. 1 shown peripheral portion of the rotor 10 in a Be Schollungsnut 17 is arranged. About the Be Schollungsnut 17, the blades 11 and 12 are inserted with their blade roots 13 and 14 in the retaining groove 16. The filling groove 17 is adapted in its width to the width of the blade roots 13 and 14.
  • blades 11 are arranged with a desired, nominal blade pitch and blades 12 with an enlarged blade pitch in the retaining groove 16 of the rotor.
  • the width of the blade roots 13 and 14 of the two types of blades 11, 12 is equal and adapted to the width of the Be colllungsnut 17.
  • a first number of blades 11 is replaced with a desired nominal blade pitch by a second number of blades 12 with increased blade pitch, the first number being greater than the second number.
  • two rotor blades 12 with an enlarged blade pitch are arranged in the region of the filling groove 17 instead of three rotor blades 11 with the desired, nominal blade pitch.
  • section of the rotor 10 is a Be Schollungsnut 17 with positioned in the region of Be Schollungsnut 17 blades 12 shown with respect to the desired, nominal blade pitch enlarged blade pitch. It is within the meaning of the present invention to arrange a plurality of such filling grooves 17 over the circumference of the rotor, the filling grooves 17 being distributed uniformly over the circumference of the rotor 10. For two filling grooves, this would mean that the filling grooves are diametrically opposed. As a result, a symmetry over the circumference of the rotor is ensured, which is in terms of the prevention of imbalances and the avoidance of asymmetric loads on the rotor 10 is advantageous.
  • the platform portion 20 of the enlarged bucket blades 12 is 50% larger than a platform portion 21 of the buckets. In the illustrated embodiment, the platform portion 20 of the enlarged bucket blades 12 is 50% larger than the platform portion 21 of the buckets 11 with nominal blade pitch.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne une turbomachine et un rotor pour une turbomachine. Plusieurs aubes mobiles sont positionnées de façon juxtaposée dans le sens périphérique du rotor, chaque aube mobile présentant une emplanture, chaque aube mobile pouvant être fixée, par l'intermédiaire de cette emplanture, dans une rainure de retenue s'étendant dans le sens périphérique du rotor, chaque aube mobile pouvant être introduite dans cette rainure de retenue par son emplanture à l'aide d'au moins une rainure de remplissage et la largeur de cette rainure de remplissage étant adaptée à la largeur de l'emplanture de l'aube. Selon la présente invention, les emplantures (13, 14) et la ou chaque rainure de remplissage (17) dans le sens périphérique présentent une largeur supérieure à la moitié de la largeur d'un pas nominal souhaité (18), un premier nombre d'aubes mobiles (11) avec le pas nominal souhaité (18) étant remplacé, au niveau de la ou de chaque rainure de remplissage (17), par un second nombre d'aubes mobiles (12) à pas supérieur (19) et ce premier nombre étant supérieur au second.

Claims (7)

  1. Rotor pour un étage de compression d'une turbomachine, en particulier d'une turbine à gaz, comportant plusieurs aubes mobiles positionnées les unes à côté des autres dans la direction périphérique du rotor, dans lequel chaque aube mobile présente un pied d'aube, dans lequel chaque aube mobile peut être fixée au moyen du pied d'aube dans une rainure de fixation s'étendant dans la direction périphérique du rotor, dans lequel chaque aube mobile peut être introduite avec son pied d'aube dans la rainure de fixation via au moins une rainures d'insertion, et dans lequel la largeur de la rainure d'insertion est adaptée à la largeur des pieds d'aube, caractérisé en ce que la largeur des pieds d'aube (13, 14) et la largeur de la ou de chaque rainure d'insertion (17) dans la direction périphérique est plus grande que la moitié de la largeur d'un pas d'aubes nominal souhaité (18), dans lequel, dans la région de la ou de chaque rainure d'insertion (17), un deuxième nombre d'aubes mobiles (12) avec un pas d'aubes accru (19) est positionné à la place d'un premier nombre d'aubes mobiles (11) avec le pas d'aubes nominal, et dans lequel le premier nombre est supérieur au deuxième nombre.
  2. Rotor selon la revendication 1, caractérisé en ce que plusieurs rainures d'insertion (17) sont réparties uniformément sur la périphérie du rotor (10), la largeur de chaque rainure d'insertion (17) dans la direction périphérique est plus grande que la moitié de la largeur d'un pas d'aubes nominal 1 souhaité, dans lequel, dans la région de chaque rainure d'insertion (17), un deuxième nombre d'aubes mobiles (12) avec un pas d'aubes accru est positionné à la place d'un premier nombre d'aubes mobiles (11) avec le pas d'aubes nominal, et dans lequel le premier nombre est supérieur au deuxième nombre.
  3. Rotor selon la revendication 2, caractérisé par deux rainures d'insertion diamétralement opposées.
  4. Rotor selon une ou plusieurs des revendications 1 à 3, caractérisé en ce que, dans la région de la ou de chaque rainure d'insertion, deux aubes mobiles (12) avec un pas d'aubes accru sont positionnées à la place de trois aubes mobiles (11) avec le pas d'aubes nominal.
  5. Rotor selon une ou plusieurs des revendications 1 à 4, caractérisé en ce que les aubes mobiles (12) avec un pas d'aubes accru présentent une zone de plate-forme (20) accrue en direction périphérique par rapport aux aubes mobiles (11) avec le pas d'aubes nominal.
  6. Rotor selon une ou plusieurs des revendications 1 à 5, caractérisé en ce que la largeur de la rainure d'insertion (17) dans la direction périphérique correspond environ à la moitié de la largeur du pas d'aubes accru.
  7. Turbomachine, en particulier turbine à gaz, comportant au moins un étage de compression, avec un rotor par étage de compression, dans laquelle le rotor est un rotor selon l'une quelconque des revendications 1 à 6.
EP04789909A 2003-10-31 2004-10-02 Turbomachine et rotor a aubes pour un etage de compression d'une turbomachine Expired - Fee Related EP1678411B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10351092A DE10351092B4 (de) 2003-10-31 2003-10-31 Turbomaschine und beschaufelter Rotor für eine Verdichterstufe einer Turbomaschine
PCT/DE2004/002192 WO2005045200A1 (fr) 2003-10-31 2004-10-02 Turbomachine et rotor a aubes pour un etage de compression d'une turbomachine

Publications (2)

Publication Number Publication Date
EP1678411A1 EP1678411A1 (fr) 2006-07-12
EP1678411B1 true EP1678411B1 (fr) 2012-08-08

Family

ID=34485188

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04789909A Expired - Fee Related EP1678411B1 (fr) 2003-10-31 2004-10-02 Turbomachine et rotor a aubes pour un etage de compression d'une turbomachine

Country Status (4)

Country Link
US (1) US7399164B2 (fr)
EP (1) EP1678411B1 (fr)
DE (1) DE10351092B4 (fr)
WO (1) WO2005045200A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8608447B2 (en) * 2009-02-19 2013-12-17 Rolls-Royce Corporation Disk for turbine engine

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2002469C3 (de) * 1970-01-21 1978-03-30 Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen Laufschaufelbefestigung in einer schwalbenschwanzförmigen Umfangsnut eines Läufers axial durchströmter Strömungsmaschinen, insbesondere Gasturbinenstrahltriebwerke
US3597112A (en) * 1970-02-02 1971-08-03 Gen Electric Compressor-blade-retaining means
CH678750A5 (fr) * 1989-03-22 1991-10-31 Escher Wyss Ag
US6152698A (en) * 1999-08-02 2000-11-28 General Electric Company Kit of articles and method for assembling articles along a holder distance
GB2364554B (en) * 2000-07-07 2004-04-07 Alstom Power Nv Turbine disc
FR2856728B1 (fr) * 2003-06-27 2005-10-28 Snecma Moteurs Aube de compresseur de turboreacteur

Also Published As

Publication number Publication date
US20070134100A1 (en) 2007-06-14
DE10351092B4 (de) 2013-11-21
EP1678411A1 (fr) 2006-07-12
DE10351092A1 (de) 2005-05-25
WO2005045200A1 (fr) 2005-05-19
US7399164B2 (en) 2008-07-15

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