EP2246575A1 - Agencement d'aube mobile pour un compresseur axial - Google Patents

Agencement d'aube mobile pour un compresseur axial Download PDF

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Publication number
EP2246575A1
EP2246575A1 EP09005894A EP09005894A EP2246575A1 EP 2246575 A1 EP2246575 A1 EP 2246575A1 EP 09005894 A EP09005894 A EP 09005894A EP 09005894 A EP09005894 A EP 09005894A EP 2246575 A1 EP2246575 A1 EP 2246575A1
Authority
EP
European Patent Office
Prior art keywords
blade
recess
securing element
blade assembly
groove
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Withdrawn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
EP09005894A
Other languages
German (de)
English (en)
Inventor
Dirk Wistuba
Dimitri Zelmer
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.)
Siemens AG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Priority to EP09005894A priority Critical patent/EP2246575A1/fr
Publication of EP2246575A1 publication Critical patent/EP2246575A1/fr
Withdrawn legal-status Critical Current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
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor

Definitions

  • the invention relates to a rotor blade assembly, comprising a rotor section for a turbomachine, are distributed on the radially outwardly directed lateral surface at least partially axially extending, laterally open retaining grooves along the circumference and in which inserted via the lateral Garutö réelle each have a blade with its respective blade root is.
  • the protruding ends are bent inwards, so that they clasp the rotor disk on the front side.
  • the blade is secured against displacement along the retaining groove.
  • the object of the invention is therefore to provide a securing device for blades of a turbomachine, by means of which a reliable backup is achieved and moreover requires a particularly small frontal space requirement side of the rotor disk to specify a particular compact turbomachine.
  • the invention is based on the finding that for mounting the blade in the retaining a particularly small lateral space requirement is required if a backup exists in which the ends of the fuse element no longer have to be bent after its installation. To avoid this, however, a departure from the conventional backup concept is required. However, the invention has recognized that, however, the scope of the previous backup concept does not have to be fundamentally abandoned in order to solve the problem.
  • the invention provides that at least one of the ends of the securing element can already be bent before it is mounted in the retaining groove. As a result, at least one of the two lateral spaces can be made extremely compact, which leads to an axially shortened turbomachine.
  • the fuse element and the blades are no longer at the same time, as it were as a pair, inserted into the holding. According to the invention, these are now mounted separately.
  • the securing element is now to bring positively with the groove base in engagement. After the locking plate is positively connected to the groove base, then the blade can be inserted over the still unbent end of the fuse element. Thus, the final securing of the blade can take place, which stops the assembly of the relevant blade.
  • the securing element has two legs, which rest in the securing state in each case on one of the two end faces of the blade root.
  • the legs are no longer on the front sides of the wheel disc, but on the front sides of the blade root. Since the free ends of the legs of the securing element are now directed outward, and no longer, as in the prior art, inwardly, the bending of the legs can now be safely prevented by the centrifugal force acting on the rotor during operation.
  • At least one recess for positive locking is provided in the groove base of the retaining groove.
  • the securing element has a hole corresponding to the respective recess for each recess.
  • the form element is designed as a feather key. The key is thus seated both partially in the recess and partially in the corresponding hole, which prevents the displacement of the securing element along the retaining groove.
  • the feather key thus blocks the displacement of the securing element and thus prevents its relative movement relative to and along the retaining groove.
  • the securing element can now be produced more cheaply, since the introduction of a hole is cheaper than the production of the bead applied there. If a radially outward bias is required for pressing the blade to the retaining groove, this can have a corresponding wall thickness of the securing element be achieved, whereby the gap between bottom and groove bottom is overcompensated.
  • the securing element can also have a contour in its section, which lies opposite the recess, which extends at least partially into the recess.
  • the securing element has a depression produced by deep-drawing, stamping or otherwise, which extends into the recess and blocks the axial displacement. This saves you the additional form element or the feather key.
  • the rotor section, on which the blade is arranged may be formed by a rotor disk or by a shaft collar of the rotor of a turbomachine. More preferably, the blade assembly is used in an axial compressor, particularly for blade rings with relatively small blades, i. Blades with a comparatively short span.
  • FIG. 1 shows in a partially sectioned, partly perspective view of a rotor blade assembly 10 of the rotor of an axial compressor.
  • the rotor blade assembly 10 comprises a rotor section 12, which is part of the rotor of the axial compressor.
  • the rotor section 12 may be formed, for example, as a rotor disk or as a shaft collar of a rotor which is then mainly integral in this section.
  • a retaining groove 16 is shown in section.
  • the section through the retaining groove 16 is chosen so that its principle symmetrical hammer-shaped Schaufelfußkontur is seen in half.
  • Each retaining groove 16 has a slightly arched groove bottom 18, which may however also be flat.
  • the retaining grooves 16 are open on the front side, relative to the rotor section 12, so that a rotor blade 22 can be pushed into the retaining groove 16 via the laterally arranged retaining groove openings 20.
  • FIG. 1 While the blade root 24 of the blade 22 is arranged in the retaining groove 16; an aerodynamically curved airfoil belonging to the blade 22 is in FIG. 1 only partially shown and provided with the reference numeral 25.
  • the blade root 24 has an underside 26 which is only indirectly opposite the groove base 18 of the retaining groove 16, since a securing element 28 is arranged between the groove base 18 and the underside 26.
  • the fuse element 28 is plate-shaped and extends over the entire length of the retaining groove 16 and slightly beyond. It is in accordance with the groove bottom 18, slightly curved or even.
  • the securing element 28 has a first leg 30 protruding beyond the retaining slot opening 20, which is already in the outward direction, ie. in the direction of the airfoil 25 of the blade 22, is bent. A arranged at the other end of the securing element 28 second leg 32 still extends parallel to the groove bottom 18. In the middle between the end faces of the rotor portion 12, a recess 34 is arranged in the groove bottom 18.
  • the recess 34 may be formed, for example, as a bore. According to a first embodiment, that axial portion of the securing element 28, which lies opposite the recess 34, has a hole 36.
  • the hole 36 and the recess 34 are aligned, so that there to form a positive connection there is a mold element 38, designed as a feather key, fitted.
  • the feather key thus sits on the one hand in the recess 34 and on the other hand in the hole 36 and thus prevents a displacement of the securing element 28 along the groove bottom 18.
  • the feather key does not protrude out of the hole in principle.
  • a plurality of pairs of recesses 34 and holes 36 per retaining groove 16 may be distributed between the end faces of the rotor section 12, in each of which a mold element 38 is seated.
  • the feather key is first inserted into the recess 34.
  • the securing element 28 is inserted into the retaining groove 16 such that its hole 36 is closed by the molding element 38.
  • the first leg 30 is already bent outward.
  • the blade 22 can be inserted into the retaining groove 16 by the further-shown on the left side Stirnutö réelleen 20.
  • the second leg 32 with a suitable tool or a suitable auxiliary device to the outside, ie to the lateral surface 14 are bent until it comes to rest on the end face of the blade root 24.
  • the assembly of the blade 22 in the retaining groove 16 is completed. In principle, there are to assemble and secure all blades 22 of a blade ring.
  • a relative movement of the moving blade 22 with respect to the securing element 28 is blocked by the fact that the two legs 30, 32 are placed in the displacement path of the moving blade 22.
  • the two legs 30, 32 thus clasp the blade root 24.
  • a relative movement of the securing element 28 along the longitudinal extent of the retaining groove 16 is not possible, since by means of formed as a feather key element 38 which sits in the hole 36 and in the recess 34 , the fuse element 28 is blocked.
  • FIG. 2 shows an alternative embodiment FIG. 1 with respect to the securing against displacement of the securing element 28 with respect to and along the retaining groove 16.
  • the securing element 28 now has a contour or shape in its section which opposes the recess 34, at least in the recess 34 partially protruding.
  • the mold thus comprises a depression 42, which can be produced, for example, by deep-drawing or stamping. This embodiment can be used several times per retaining groove 16.
  • FIG. 2 shows the inserted blade 22 according to the second embodiment.
  • FIG. 3 shows the top view of the fuse element 28 according to the second embodiment.
  • the lowering 42 is made possible in particular by a hole 44, the edge of which comprises the deep-drawn or lowered contour.
  • a particular advantage of the invention is that the securing element 28 can already be mounted with pre-bent legs 30, which makes the bending of the first leg 30 with the securing element 28 already inserted superfluous. As a result, at the relevant end face of the rotor section 12 no additional Space required for assembly to bend the first leg longer.
  • the invention provides a rotor blade assembly 10 for a rotor section 12 of a turbomachine in which the blades 22 inserted in retaining grooves 16 are each secured by means of a securing element 28 against displacement in the axial direction or along its retaining groove 16, in which the securing element 28 is a positive fit with the groove bottom 18 of the respective retaining groove 16 is engaged.
  • a securing element 28 against displacement in the axial direction or along its retaining groove 16
  • the securing element 28 is a positive fit with the groove bottom 18 of the respective retaining groove 16 is engaged.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP09005894A 2009-04-28 2009-04-28 Agencement d'aube mobile pour un compresseur axial Withdrawn EP2246575A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP09005894A EP2246575A1 (fr) 2009-04-28 2009-04-28 Agencement d'aube mobile pour un compresseur axial

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP09005894A EP2246575A1 (fr) 2009-04-28 2009-04-28 Agencement d'aube mobile pour un compresseur axial

Publications (1)

Publication Number Publication Date
EP2246575A1 true EP2246575A1 (fr) 2010-11-03

Family

ID=41151920

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09005894A Withdrawn EP2246575A1 (fr) 2009-04-28 2009-04-28 Agencement d'aube mobile pour un compresseur axial

Country Status (1)

Country Link
EP (1) EP2246575A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3418498A1 (fr) * 2017-06-22 2018-12-26 Siemens Aktiengesellschaft Segment ressort de precontrainte, rotor et procédé de fabrication associés
CN110296105A (zh) * 2019-08-15 2019-10-01 上海电气燃气轮机有限公司 叶片锁紧结构

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB643914A (en) * 1948-03-08 1950-09-27 Joseph Stanley Hall Improvements in and relating to turbine or like blade securing means
US2641443A (en) * 1951-03-17 1953-06-09 A V Roe Canada Ltd Rotor blade locking
DE1802931U (de) * 1959-08-07 1959-12-24 Entwicklungsbau Pirna Veb Verriegelungsblech fuer mit tannenbaumfuessen versehene laufradschaufeln von gasturbinen u. dgl.
DE10140259C1 (de) * 2001-08-16 2003-01-30 Man B & W Diesel Ag Axialturbine
EP1703078A1 (fr) 2005-03-17 2006-09-20 Siemens Aktiengesellschaft Dispositif et procédé pour sécuriser les pattes de verrouillage dans un compresseur ou une turbine par pliage

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB643914A (en) * 1948-03-08 1950-09-27 Joseph Stanley Hall Improvements in and relating to turbine or like blade securing means
US2641443A (en) * 1951-03-17 1953-06-09 A V Roe Canada Ltd Rotor blade locking
DE1802931U (de) * 1959-08-07 1959-12-24 Entwicklungsbau Pirna Veb Verriegelungsblech fuer mit tannenbaumfuessen versehene laufradschaufeln von gasturbinen u. dgl.
DE10140259C1 (de) * 2001-08-16 2003-01-30 Man B & W Diesel Ag Axialturbine
EP1703078A1 (fr) 2005-03-17 2006-09-20 Siemens Aktiengesellschaft Dispositif et procédé pour sécuriser les pattes de verrouillage dans un compresseur ou une turbine par pliage

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3418498A1 (fr) * 2017-06-22 2018-12-26 Siemens Aktiengesellschaft Segment ressort de precontrainte, rotor et procédé de fabrication associés
CN110296105A (zh) * 2019-08-15 2019-10-01 上海电气燃气轮机有限公司 叶片锁紧结构

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