EP1862640A1 - Aube de turbine - Google Patents

Aube de turbine Download PDF

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Publication number
EP1862640A1
EP1862640A1 EP06011253A EP06011253A EP1862640A1 EP 1862640 A1 EP1862640 A1 EP 1862640A1 EP 06011253 A EP06011253 A EP 06011253A EP 06011253 A EP06011253 A EP 06011253A EP 1862640 A1 EP1862640 A1 EP 1862640A1
Authority
EP
European Patent Office
Prior art keywords
blade
turbine blade
shell elements
shell
airfoil
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.)
Granted
Application number
EP06011253A
Other languages
German (de)
English (en)
Other versions
EP1862640B1 (fr
Inventor
Katharina Bergander
Georg Dr. Bostanjoglo
Tobias Dr. Buchal
Winfried Dr. Esser
Dirk Dr. Goldschmidt
Thorsten Koch
Rudolf Küperkoch
Thorsten Mattheis
Jan Münzer
Ralf Müsgen
Matthias Dr. Oechsner
Ursula Pickert
Volker Dr. Vosberg
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 AT06011253T priority Critical patent/ATE459783T1/de
Priority to EP06011253A priority patent/EP1862640B1/fr
Priority to DE502006006333T priority patent/DE502006006333D1/de
Priority to JP2007140112A priority patent/JP4532523B2/ja
Priority to US11/807,387 priority patent/US7832988B2/en
Priority to CN200710108113.3A priority patent/CN101082286B/zh
Priority to RU2007120199/06A priority patent/RU2372493C2/ru
Publication of EP1862640A1 publication Critical patent/EP1862640A1/fr
Application granted granted Critical
Publication of EP1862640B1 publication Critical patent/EP1862640B1/fr
Not-in-force 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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding

Definitions

  • the invention relates to a turbine blade for a gas turbine, comprising a mounting and platform region, at which an at least two opposing shell elements comprising blade with a blade tip connects, which shell elements are connected together as a suction side airfoil wall and as a pressure-side airfoil wall.
  • a disadvantage of the known state of the art is that the bonding connection of the longitudinally slotted airfoil in the region of the blade tip may possibly become detached, and thus the two individual shells may be diverge during operation. This leads to flow losses during operation. In addition, in individual cases there is a risk that the two shell elements completely separate from each other and can cause serious secondary damage in the turbine.
  • a closure insert for a blade tip of a blade known, which is inserted between the two side walls forming the airfoil in the region of the blade tip.
  • the cross-sectionally C-shaped closure insert is seated in two mutually opposite pockets, which are each provided on the inside of the respective airfoil wall.
  • tabs provided on the inner sides, which absorb the centrifugal forces acting on the closure insert.
  • the object of the invention is to provide a turbine blade of the type mentioned, in which the two shell elements are securely connected to each other.
  • the underlying object is achieved by the specification of a generic turbine blade, in which the two shell elements are secured in the region of the blade tip by positive engagement against divergence.
  • the invention is based on the recognition that the connection produced, for example, by means of the bonding process may in individual cases not be sufficient to secure the two shell elements against divergence. It is therefore proposed with the invention that the two shell elements in the region of the blade tip have a form-locking, which the divergence, i. preventing the two shell elements from moving away from one another in the region of the blade tip when the connection is released. Accordingly, with the specified turbine blade a particularly safe operation of a gas turbine can be specified, provided that it is equipped with the turbine blade according to the invention. In addition, the flow losses that occur when divergence of two shell elements, effectively prevented. A deterioration of the efficiency of the gas turbine will therefore not occur for these reasons.
  • the positive connection is formed by a hooking means, which is hooked between the two shell elements with each of the shell elements hooked.
  • the Verhakungsraum is chosen so that a divergence of the two shell elements in the region of the blade tip after production of the positive connection is safely avoided. Consequently, both shell elements each have on their inner side, which in each case opposite their H disclosegasbeetzmaschineten outer side, a hook, each comprising a projection for the blade wall approximately parallel projection.
  • the interlocking means which is preferably formed as a cross-sectionally E-shaped bracket, two opposite clip ends, which are complementary to the provided on the shell elements hooks. Each clip end can engage behind the protrusion provided on the hook, so that a movement of the shell elements away from each other when releasing connection is reliably avoided.
  • the interlocking means may be frictionally engaged with at least one of the shell members, i. soldered or welded, be connected.
  • the interlocking means may be frictionally engaged with at least one of the shell members, i. soldered or welded, be connected.
  • a hooking means which are particularly easy to install, this can also be designed in several parts. This ensures that it can be introduced comparatively easily between the opposing shell elements through the opening formed by these and then positioned.
  • the interlocking means is provided between the two shell members so that, when the turbine blade is formed as a blade, is secured by the arranged on the inner sides of the airfoil walls hooks against a release under centrifugal force.
  • the interlocking means may also be attached as a crown to the blade tip, on which moreover squealer edges may be provided. By means of the squint edges, a particularly small radial gap between the Blade tip and the opposite boundary wall of the gas channel can be achieved.
  • each shell element comprises a hook, which engage each other as a hooking means complementary to each other.
  • a separate component for hooking is not required in this case.
  • One of the two hooks protrudes towards the blade tip, the other of the two hooks towards the blade root.
  • radially offset abutting shell elements are displaced in the radial direction until the blade root and blade tip of both shell elements are each flush with each other and the two hooks engage each other in a form-fitting manner. Subsequently, the two shell elements are permanently and firmly connected.
  • the turbine blade is equipped as a blade with a cross-section hammer- or fir-tree-shaped foot, which is inserted into a corresponding groove for attachment to the rotor of the turbine, and the inserted in the groove blade root secures the entanglement against unwanted loosening, as mounted turbine blade a radial displacement of the two shell elements is not possible.
  • FIG. 10 A modular turbine blade 10 for a preferably stationary gas turbine is shown in FIG.
  • the turbine blade 10 is shown in the form of a blade 12, which has a fastening and platform region 14 for fastening in a groove, not shown, of a rotor disk.
  • the attachment area is designed as a fir tree-shaped or hammer-shaped root in cross-section.
  • Adjoining the fastening and platform region 14 is an aerodynamically profiled airfoil 16, which has a substantially convexly curved suction-side airfoil wall 18 and an opposite, essentially concave, curved pressure-side airfoil wall 20.
  • the two airfoil walls 18, 20 extend along a chord 27 from an upstream leading edge 22 to a downstream trailing edge 24, relative to the hot gas working medium 26 flowing around the airfoil 16 during operation of the gas turbine.
  • the suction-side airfoil wall 18 is formed by a first shell element 28 and the pressure-side airfoil wall 20 by a second shell element 30.
  • the two shell elements 28, 30 are shown in a cross-hatched connection region 32 front edge side and rear edge side by a high-pressure and high-temperature bonding process permanently and firmly connected. Between the two connecting portions 32 is surrounded by the shell elements 28, 30 interior space 34 which extends in the interior of the airfoil 16 from the mounting side end to a blade tip 36.
  • a bracket 40 is provided in this area as a hooking means 39.
  • 2 shows the cross section according to the section line II-II of FIG 1.
  • E-shaped bracket 40 has these two opposite clip ends 54, 56 which are each complementary to the arranged on the shell elements 28, 30 hooks 46, 48 and the projections 50, 52 engage behind a positive fit.
  • the projections 50, 52 extend in the radial direction, preferably inwards. This results in a hooking, in which the clamp 40 is secured in centrifugal force against detachment from the hooks 46, 48.
  • the central region 57 of the E-shaped bracket 40 fills the area between the two projections 50, 52 so that two projecting sealing lips 53 are formed on the blade tip 36. At the same time, the clamp 40 closes the interior space 34 at the blade tip 36, thereby avoiding potentially harmful penetration of hot working medium 26.
  • the two shell elements 28, 30 can not diverge due to the positive connection.
  • the direct abutment of the shell elements 28, 30 between the front edge 22 and the trailing edge 24 in the region of the blade tip 36 is prevented by the then acting as a spacer bracket 40.
  • this can be soldered or welded with at least one of the shell elements 28, 30 pointwise or along the butt weld 58.
  • the interlocking means 39 and / or the hooks 46, 48 may each be divided along the chord 27 into several segments.
  • the multi-part interlocking means 39 can then be mounted particularly simply or the one-piece bracket 40 can then be particularly easily introduced into the interior 34.
  • a radially to be provided externally directed squealer which further improves the sealing effect between the blade tip 36 and an opposite boundary wall during operation.
  • the shell elements 28, 30 can be hooked directly to one another.
  • the solution shown in FIG. 2 is to be modified in such a way that on the one hand the two hooks 46, 48 are extended towards the opposite shell element 30, 28 and on the other hand one of the hooks 46, 48 instead of radially inward, ie. towards the blade root, radially outward, i. towards the blade tip 36 out, so that they can then interlock form-fitting manner. For this case, then no separate component is required as interlocking means 39.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP06011253A 2006-05-31 2006-05-31 Aube de turbine Not-in-force EP1862640B1 (fr)

Priority Applications (7)

Application Number Priority Date Filing Date Title
AT06011253T ATE459783T1 (de) 2006-05-31 2006-05-31 Turbinenschaufel
EP06011253A EP1862640B1 (fr) 2006-05-31 2006-05-31 Aube de turbine
DE502006006333T DE502006006333D1 (de) 2006-05-31 2006-05-31 Turbinenschaufel
JP2007140112A JP4532523B2 (ja) 2006-05-31 2007-05-28 タービン翼
US11/807,387 US7832988B2 (en) 2006-05-31 2007-05-29 Turbine blade
CN200710108113.3A CN101082286B (zh) 2006-05-31 2007-05-30 涡轮叶片
RU2007120199/06A RU2372493C2 (ru) 2006-05-31 2007-05-30 Лопатка турбины и газовая турбина с такой лопаткой

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP06011253A EP1862640B1 (fr) 2006-05-31 2006-05-31 Aube de turbine

Publications (2)

Publication Number Publication Date
EP1862640A1 true EP1862640A1 (fr) 2007-12-05
EP1862640B1 EP1862640B1 (fr) 2010-03-03

Family

ID=36693578

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06011253A Not-in-force EP1862640B1 (fr) 2006-05-31 2006-05-31 Aube de turbine

Country Status (7)

Country Link
US (1) US7832988B2 (fr)
EP (1) EP1862640B1 (fr)
JP (1) JP4532523B2 (fr)
CN (1) CN101082286B (fr)
AT (1) ATE459783T1 (fr)
DE (1) DE502006006333D1 (fr)
RU (1) RU2372493C2 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3023191A1 (fr) * 2014-11-20 2016-05-25 Siemens Aktiengesellschaft Aube de turbine constituée de deux parties

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102008047043A1 (de) * 2008-09-13 2010-03-18 Mtu Aero Engines Gmbh Ersatzteil für eine Gasturbinen-Schaufel einer Gasturbine, Gasturbinen-Schaufel sowie ein Verfahren zur Reparatur einer Gasturbinen-Schaufel
CH700071A1 (de) 2008-12-12 2010-06-15 Alstom Technology Ltd Laufschaufel für eine Gasturbine.
FR3006367B1 (fr) * 2013-05-28 2015-07-03 Snecma Aube creuse, et son procede de fabrication
US9464530B2 (en) * 2014-02-20 2016-10-11 General Electric Company Turbine bucket and method for balancing a tip shroud of a turbine bucket
US11203938B2 (en) 2018-11-08 2021-12-21 General Electric Company Airfoil coupon attachment
US11143033B2 (en) * 2018-11-08 2021-10-12 General Electric Company Turbomachine blade tip attachment

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1087745B (de) * 1959-03-11 1960-08-25 Schilde Maschb Ag Axialschaufelrad
US3899267A (en) 1973-04-27 1975-08-12 Gen Electric Turbomachinery blade tip cap configuration
GB2106997A (en) 1981-10-01 1983-04-20 Rolls Royce Vibration damped rotor blade for a turbomachine
US4411597A (en) 1981-03-20 1983-10-25 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Tip cap for a rotor blade
EP0990771A1 (fr) 1998-09-28 2000-04-05 General Electric Company Aube de turbine avec insert de refroidissement
US6056507A (en) * 1996-08-09 2000-05-02 General Electric Company Article with brazed end plate within an open body end
EP1283325A1 (fr) 2001-08-09 2003-02-12 Siemens Aktiengesellschaft Ailette de turbine et procédé de fabrication d'une ailette de turbine

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US994166A (en) * 1911-02-17 1911-06-06 Arnold Kienast Turbine-blade.
US1829179A (en) * 1929-01-11 1931-10-27 Westinghouse Electric & Mfg Co Method of making turbine blades
US2689107A (en) * 1949-08-13 1954-09-14 United Aircraft Corp Vibration damper for blades and vanes
US2762114A (en) * 1951-08-28 1956-09-11 Gen Motors Corp Method of making sheet metal turbine bucket
US2848192A (en) * 1953-03-12 1958-08-19 Gen Motors Corp Multi-piece hollow turbine bucket
EP1389669B1 (fr) * 2002-08-16 2006-06-07 Siemens Aktiengesellschaft Système de fixation

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1087745B (de) * 1959-03-11 1960-08-25 Schilde Maschb Ag Axialschaufelrad
US3899267A (en) 1973-04-27 1975-08-12 Gen Electric Turbomachinery blade tip cap configuration
US4411597A (en) 1981-03-20 1983-10-25 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Tip cap for a rotor blade
GB2106997A (en) 1981-10-01 1983-04-20 Rolls Royce Vibration damped rotor blade for a turbomachine
US6056507A (en) * 1996-08-09 2000-05-02 General Electric Company Article with brazed end plate within an open body end
EP0990771A1 (fr) 1998-09-28 2000-04-05 General Electric Company Aube de turbine avec insert de refroidissement
EP1283325A1 (fr) 2001-08-09 2003-02-12 Siemens Aktiengesellschaft Ailette de turbine et procédé de fabrication d'une ailette de turbine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3023191A1 (fr) * 2014-11-20 2016-05-25 Siemens Aktiengesellschaft Aube de turbine constituée de deux parties

Also Published As

Publication number Publication date
DE502006006333D1 (de) 2010-04-15
JP2008031985A (ja) 2008-02-14
JP4532523B2 (ja) 2010-08-25
ATE459783T1 (de) 2010-03-15
US7832988B2 (en) 2010-11-16
US20100014980A1 (en) 2010-01-21
EP1862640B1 (fr) 2010-03-03
RU2372493C2 (ru) 2009-11-10
CN101082286A (zh) 2007-12-05
RU2007120199A (ru) 2008-12-10
CN101082286B (zh) 2010-06-23

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