EP1136654A1 - Aube rotorique de turbine - Google Patents

Aube rotorique de turbine Download PDF

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Publication number
EP1136654A1
EP1136654A1 EP00106142A EP00106142A EP1136654A1 EP 1136654 A1 EP1136654 A1 EP 1136654A1 EP 00106142 A EP00106142 A EP 00106142A EP 00106142 A EP00106142 A EP 00106142A EP 1136654 A1 EP1136654 A1 EP 1136654A1
Authority
EP
European Patent Office
Prior art keywords
blade
turbine
recess
foot
turbine rotor
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Withdrawn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
EP00106142A
Other languages
German (de)
English (en)
Inventor
Peter Dipl.-Ing. Tiemann
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 EP00106142A priority Critical patent/EP1136654A1/fr
Priority to PCT/EP2001/002629 priority patent/WO2001071166A1/fr
Publication of EP1136654A1 publication Critical patent/EP1136654A1/fr
Withdrawn legal-status Critical Current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
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type

Definitions

  • the invention relates to a turbine blade arrangement several offset in the circumferential direction of a turbine disk arranged turbine blades, each with one blade root, which has two long sides and front sides, has longitudinal teeth on its long sides and that in one Turbine disk groove can be inserted lengthways and there by longitudinal teeth, who positively engage his longitudinal teeth, is held radially pull-out.
  • Turbine blade assemblies with grooves in a turbine disc inserted feet are through in their groove areas on the turbine blade when the turbine disc rotates attacking centrifugal forces heavily loaded.
  • To a large contact area to have are the holding devices of the foot in the groove is designed as beveled longitudinal teeth.
  • the centrifugal forces which point radially outwards are caused by the longitudinal teeth of the foot introduced into the longitudinal teeth of the groove. Since the Longitudinal teeth are chamfered by this introduction a force redirection of part of the centrifugal force.
  • the forces introduced are in the front area of the foot very stressful for the groove area, since they rise abruptly there. This results in particular in the lower groove area a heavy load that can lead to cracks.
  • the object of the present invention is therefore a turbine blade arrangement specify that allows turbine blades to be used for helix angles that are larger than have been achieved so far, without the strength of the groove areas to endanger.
  • the object is achieved in that the blade root on its Has a local weakening of material.
  • the invention has the advantage that centrifugal force-induced voltage peaks be intercepted and therefore not in the front End area introduced into the surrounding longitudinal teeth but inside, in the middle of the blade root.
  • This advantage is achieved in that The face is locally weakened. A weakening of materials exists when the surrounding areas are larger Have rigidity, for example in that the Material at the weakening is thinner. So the whole resulting stiffness of this area is reduced. Because when a load is applied, the soft, weakened one is the first Area deformed. The material is no longer like this rigid. This way only a diminished one can be in this area Power transmission to the surrounding groove take place.
  • the normally very rigid end faces of the blade root are due to the proposed arrangement against voltages made more compliant.
  • a material calculation that is easy to calculate and reproducible is given when the blade root on its Front has a recess.
  • the recess softens the Forehead area of the foot against the attacking centrifugal force in that they compress elastically under the application of force leaves. There will be a lesser amount of force in initiated the end region of the groove, and thus a large proportion in the area of the center of the foot.
  • By changing the Shape or dimensions of the recess can be elastic Characteristics of the recess area essential to be influenced.
  • the recess on the front of the The blade root is inserted during the casting Casting core from the outside or subsequently through mechanical processing applicable.
  • the recess has a wedge-shaped notch on the front side of the blade root in the area between that of the axis of the Turbine disk next, opposite longitudinal teeth is, and the recess on a disc axis
  • the end of the blade root is open, can be elastic Bend together the side flanks of the wedge-shaped notch Forces are softly intercepted in this area. It becomes a smaller proportion of the force in the surrounding groove area transfer. The load capacity is thus in one area redirected towards the center of the blade root. This feathery
  • the folding of the wedge-shaped notch is restricted that there are no permanent plastic deformations allowed to. This can be achieved, for example, by that dimensions and shapes of the recess, in particular a certain width and depth are observed, for example of the bucket weight, but also the contact area in depend on the groove and the manufacturing tolerances observed.
  • the recess is in the disc side End area on the front and softest from there towards the center of the blade root with decreasing Width increasingly harder.
  • the maximum notch depth can be moreover in this way easily to a possible Helix angle of the blade root can be adjusted by the Depth increases with increasing helix angle.
  • the recess has a rounded contour, it is ensured that the contact forces are derived more gently can. This prevents the recess for example in the event of changes in force and changes in direction of force Crack tips form, which damage the material to lead.
  • each of the two end faces of the blade root has one local weakening of material, are on both ends, the similar and with a symmetrical design of the blade root would have the same voltage increases, to obtain similar or the same advantageous effects.
  • Coolant can be passed through the blade root and at the same time an efficiency improvement due to a Tilting take place when the blade root has a cavity has, which at the disc axis end of the blade root has access and local material weakening has such a distance from the entrance that under the Operating load of the turbine blade the required stability is guaranteed.
  • Through the access can coolant through the blade root and through it into the blade profile be directed.
  • due to the local weakening of materials the attacking centrifugal force towards the center of the blade root distributed.
  • the strength of the Blade root also given in the forehead area in that a sufficient wall thickness on the front of the blade root is guaranteed despite the local material weakening. It All advantages of the invention can thus be used and at the same time an internal cooling of the blade profile or a weight reduction due to the hollowing out of the Blade base are made.
  • the cavity is offset several at the end of the disc axis has accesses arranged on a longitudinal axis of the foot and the local weakening of material on the front side as well is at least partially on the longitudinal axis of the foot, a Stress distribution in the middle along the longitudinal axis of the foot.
  • the voltage is introduced symmetrically the two flanks of the groove.
  • the forces are evenly on both sides of the groove are distributed, which means that there is also one in the center area possible excessive voltage is avoided.
  • Multiple entrances ensure stabilization in the walls between the accesses, making the force distribution even becomes. In particular, it is sufficient to maintain stability Distance of local material weakening to access, which is closest to the recess.
  • the blade root is star-shaped from the.
  • the groove ends, that encompass the forehead areas of the feet are marked by the forces transferred to them are heavily asymmetrically loaded.
  • This asymmetrical load in the end area poses the resulting bending stresses and the associated stresses Crack nucleation is a limit for the improvement of the cross section due to the inclination of the blade feet
  • the local material weakening according to the invention acts against this especially the recess by itself in this weakened forehead area the material of the foot softer behaves.
  • the turbine blade 2 consists of a Blade profile 10, which is tapered to a parallelogram Bucket platform 11, which borders the completion of the underlying Blade base 3 forms.
  • the blade root 3 has also a parallelogram cross section parallel to the blade platform 11.
  • the platform 11 points relatively to the vertical 14 on an end face 8 of the blade root 3 a helix angle 24.
  • the blade root 3 has parallel to its end face 8 a fir tree-shaped Cross section, the protruding, on the two parallel Long sides 4 of the blade root 3 are parallel to one another longitudinally has longitudinal foot teeth 5 and to a disc axis End 17 of the foot 3 tapers narrower.
  • the longitudinal feet 5 are related to a longitudinal axis of the blade 23 undercuts forming radial bevels.
  • the blade root 3 is formed in a corresponding negative Turbine disk groove 6 with longitudinal foot teeth 5 receiving, lengthways extending cutouts 15 along its long sides 4 inserted and related to the axis of the turbine disk 1 radially secure against extraction by corresponding to the longitudinal teeth of the foot 5 chamfered longitudinal teeth 7 held.
  • the between two blades 2 lying, in cross section parallel to the surface also parallelogram-shaped area 26 of the turbine disc 1 is thus from the two adjacent turbine blades 2 claimed in the opposite direction.
  • the Forces, represented by force vector arrows 30, in the circumferential direction of the turbine disk 1 rise in the central region 28 each other approximately as indicated in Fig.5.
  • the blade root 3 on the face 8 a local weakening of material in Has a shape of a recess 9.
  • the blade root 3 on the face 8 a local weakening of material in Has a shape of a recess 9.
  • the recess 9 In an area 13 am End 17 of the foot 3 on the disc axis side, at which the foot 3 is tapered, is located between the disks closest to the disk Longitudinal teeth 5 have the recess 9 approximately in the center.
  • the recess 9 has a wedge-like shape, which in the direction Platform 11 and tapers towards the other end face 8, rounded flanks 12.
  • the recess 9 is open towards the disc axis end 17 of the foot 3.
  • the recess 9 has its greatest height 27 directly on the end face 8 and falls to the center of the blade root 3 rounded down.
  • FIG. 3a, b, c show parallel to the blade platform 11 Cross sections through the foot area with the recess 9 along the section lines III a, b, c from Fig. 2.
  • the cross sections have a distance from the end 17 on the disc axis side and decreasing maximum as the blade platform 11 approaches Depth 18 on. Likewise increases with distance to the disc axis side End 17 the maximum width 16 of the recess 9 to.
  • the slope of the flanks 12 of the recesses 9 is on adjusted this decrease, but essentially constant.
  • Fig.4 shows a top view II-II on the disc axis side End 17 of the foot 3 from Fig.1.
  • the foot 3 indicates next to the two end faces 8 arranged recesses 9 approximately four similarly elliptically shaped approaches in cross section 19 to an internal cavity, which is not shown is.
  • the entrances 19 are separated from one another by central walls 22. Both the accesses 19 and the recesses 9 lie with their longitudinal dimensions along a longitudinal axis of the foot 21, parallel to the longitudinal sides 4 of the foot 3 in the middle runs between them.
  • the recesses 9 are spaced apart 20 to the neighboring entrances 19. Between the Recess 9 and the adjacent entrance 19 are thus located a wall 31 through which the deflected from the end face 8 Force is introduced into the surrounding groove area. Through the recesses 9, the end faces 8 are in the disc axis side End area 17 softer.
  • the blade profile 10 of the turbine blade can 2 are supplied with coolant.
  • the middle walls 22 reinforce the foot area and ensure sufficient resistance to the load by the attacking centrifugal forces.
  • FIG. 5 shows a plan view of a circumference of a turbine disk 1 with turbine blades inserted in grooves 6 2, a distance 25 between corresponding to each other Have long sides 4.
  • the platforms 11 and with them the Feet have an angle 24 to a perpendicular 14 on the turbine disk end face on.
  • the recess 9 makes the forehead area 8 softer, i.e. so strong forces can no longer given in this area to the surrounding groove areas become. As a result, the maxima of the force distributions reinforced in the direction of the central region 28 of the region 26 moved where large forces without damage even with large ones Angles 24 of over 15 ° can be included.
  • Front area 8 has an elongated recess 9.
  • the Recess 9 is at the disc-side end region 17 of the foot 3 open and extends from the disc-side end region 17 to between the uppermost longitudinal teeth 5. This also means the areas between the middle and the top, opposite each other Longitudinal teeth 5 resilient. Voltage peaks in the forehead area 8 can be even more effectively balanced become.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP00106142A 2000-03-21 2000-03-21 Aube rotorique de turbine Withdrawn EP1136654A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP00106142A EP1136654A1 (fr) 2000-03-21 2000-03-21 Aube rotorique de turbine
PCT/EP2001/002629 WO2001071166A1 (fr) 2000-03-21 2001-03-08 Aube mobile de turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP00106142A EP1136654A1 (fr) 2000-03-21 2000-03-21 Aube rotorique de turbine

Publications (1)

Publication Number Publication Date
EP1136654A1 true EP1136654A1 (fr) 2001-09-26

Family

ID=8168183

Family Applications (1)

Application Number Title Priority Date Filing Date
EP00106142A Withdrawn EP1136654A1 (fr) 2000-03-21 2000-03-21 Aube rotorique de turbine

Country Status (2)

Country Link
EP (1) EP1136654A1 (fr)
WO (1) WO2001071166A1 (fr)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1361340A2 (fr) * 2002-05-06 2003-11-12 General Electric Company Aube de turbine avec encoche sur le pied
FR2903138A1 (fr) * 2006-06-28 2008-01-04 Snecma Sa Aube mobile et disque de rotor de turbomachine, et dispositif d'attache d'une telle aube sur un tel disque
FR2995343A1 (fr) * 2012-09-11 2014-03-14 Snecma Aube de turbine, turbine, et procede de fabrication
GB2529681A (en) * 2014-08-29 2016-03-02 Rolls Royce Plc Gas turbine engine rotor arrangement
EP3098389A1 (fr) * 2015-05-27 2016-11-30 United Technologies Corporation Racine de fixation de pale de ventilateur présentant d'excellentes caractéristiques de réponse
WO2018077589A1 (fr) * 2016-10-26 2018-05-03 Siemens Aktiengesellschaft Ensemble de rotor de turbine et procédé de fabrication d'une pale de rotor de turbine
CN109030012A (zh) * 2018-08-24 2018-12-18 哈尔滨电气股份有限公司 一种带有冷却通道的透平叶根疲劳试验模拟件及试验方法
FR3087479A1 (fr) * 2018-10-23 2020-04-24 Safran Aircraft Engines Aube de turbomachine

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2442968B (en) 2006-10-20 2009-08-19 Rolls Royce Plc A turbomachine rotor blade and a turbomachine rotor
US9777575B2 (en) 2014-01-20 2017-10-03 Honeywell International Inc. Turbine rotor assemblies with improved slot cavities
CN104265377B (zh) * 2014-09-16 2016-01-20 上海金通灵动力科技有限公司 一种降低纵树型轮毂型线处应力的结构

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2643853A (en) * 1948-07-26 1953-06-30 Westinghouse Electric Corp Turbine apparatus
US4480957A (en) * 1983-04-14 1984-11-06 General Electric Company Dynamic response modification and stress reduction in dovetail and blade assembly
US5104290A (en) * 1989-11-09 1992-04-14 Rolls-Royce Plc Bladed rotor with axially extending radially re-entrant features
US5314307A (en) * 1992-12-18 1994-05-24 Alliedsignal Inc. Gas turbine test airfoil
EP0874136A2 (fr) * 1997-04-24 1998-10-28 United Technologies Corporation Aube de soufflante frangible
EP0906514A1 (fr) * 1996-06-21 1999-04-07 Siemens Aktiengesellschaft Rotor pour une turbomachine avec des pales a monter dans des rainures et pales pour un rotor

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2643853A (en) * 1948-07-26 1953-06-30 Westinghouse Electric Corp Turbine apparatus
US4480957A (en) * 1983-04-14 1984-11-06 General Electric Company Dynamic response modification and stress reduction in dovetail and blade assembly
US5104290A (en) * 1989-11-09 1992-04-14 Rolls-Royce Plc Bladed rotor with axially extending radially re-entrant features
US5314307A (en) * 1992-12-18 1994-05-24 Alliedsignal Inc. Gas turbine test airfoil
EP0906514A1 (fr) * 1996-06-21 1999-04-07 Siemens Aktiengesellschaft Rotor pour une turbomachine avec des pales a monter dans des rainures et pales pour un rotor
EP0874136A2 (fr) * 1997-04-24 1998-10-28 United Technologies Corporation Aube de soufflante frangible

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1361340A2 (fr) * 2002-05-06 2003-11-12 General Electric Company Aube de turbine avec encoche sur le pied
EP1361340A3 (fr) * 2002-05-06 2005-08-17 General Electric Company Aube de turbine avec encoche sur le pied
FR2903138A1 (fr) * 2006-06-28 2008-01-04 Snecma Sa Aube mobile et disque de rotor de turbomachine, et dispositif d'attache d'une telle aube sur un tel disque
FR2995343A1 (fr) * 2012-09-11 2014-03-14 Snecma Aube de turbine, turbine, et procede de fabrication
GB2529681B (en) * 2014-08-29 2019-02-20 Rolls Royce Plc Gas turbine engine rotor arrangement
US10119425B2 (en) 2014-08-29 2018-11-06 Rolls-Royce Plc Gas turbine engine rotor arrangement
GB2529681A (en) * 2014-08-29 2016-03-02 Rolls Royce Plc Gas turbine engine rotor arrangement
EP3098389A1 (fr) * 2015-05-27 2016-11-30 United Technologies Corporation Racine de fixation de pale de ventilateur présentant d'excellentes caractéristiques de réponse
US10801515B2 (en) 2015-05-27 2020-10-13 Raytheon Technologies Corporation Fan blade attachment root with improved strain response
US10400784B2 (en) 2015-05-27 2019-09-03 United Technologies Corporation Fan blade attachment root with improved strain response
EP3587737A1 (fr) * 2015-05-27 2020-01-01 United Technologies Corporation Racine de fixation de pale de ventilateur présentant d'excellentes caractéristiques de réponse
US11002285B2 (en) 2015-05-27 2021-05-11 Raytheon Technologies Corporation Fan blade attachment root with improved strain response
WO2018077589A1 (fr) * 2016-10-26 2018-05-03 Siemens Aktiengesellschaft Ensemble de rotor de turbine et procédé de fabrication d'une pale de rotor de turbine
CN109030012A (zh) * 2018-08-24 2018-12-18 哈尔滨电气股份有限公司 一种带有冷却通道的透平叶根疲劳试验模拟件及试验方法
CN109030012B (zh) * 2018-08-24 2024-01-23 哈尔滨电气股份有限公司 一种带有冷却通道的透平叶根疲劳试验模拟件及试验方法
FR3087479A1 (fr) * 2018-10-23 2020-04-24 Safran Aircraft Engines Aube de turbomachine
US11156107B2 (en) 2018-10-23 2021-10-26 Safran Aircraft Engines Turbomachine blade

Also Published As

Publication number Publication date
WO2001071166A1 (fr) 2001-09-27

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