EP3029268A1 - Aube directrice de turbine - Google Patents

Aube directrice de turbine Download PDF

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Publication number
EP3029268A1
EP3029268A1 EP14195679.7A EP14195679A EP3029268A1 EP 3029268 A1 EP3029268 A1 EP 3029268A1 EP 14195679 A EP14195679 A EP 14195679A EP 3029268 A1 EP3029268 A1 EP 3029268A1
Authority
EP
European Patent Office
Prior art keywords
blade
airfoil
turbine
tie rod
side wall
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Withdrawn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
EP14195679.7A
Other languages
German (de)
English (en)
Inventor
Robert Frantzheld
Jacek Grodzki
Holger Hesse
Susanne Kamenzky
Tobias Kähler
Khaled Maiz
Dirk Mertens
Romina Pipke
Eva Scheu
Eric Wiemann
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 EP14195679.7A priority Critical patent/EP3029268A1/fr
Publication of EP3029268A1 publication Critical patent/EP3029268A1/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Withdrawn legal-status Critical Current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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades

Definitions

  • the invention relates to a turbine blade for a gas turbine with a fastening region and an adjoining platform region, which comprises a platform on which a profiled airfoil profiled in cross section is arranged, which terminates at a blade tip. It further relates to a method for producing such a turbine blade.
  • Turbine blades of the above type are used in gas turbines to convert the energy of a hot gas stream into rotary energy. They typically include an airfoil traversed by cavities for guiding cooling air, the cavities extending channelwise along the longitudinal or transverse direction, often the entire area from the platform to the blade tip, and separated by ribs. The ribs thus extend from the pressure side wall to the suction side wall.
  • Turbine blades are currently produced by casting from a single piece and a material. This is usually done by vacuum investment casting. The above-described cavities in the blade are thereby produced with a correspondingly shaped casting core. In the course of further improving the performance of current gas turbines has been found, however, that the turbine blades produced in this process may not meet the current requirements for stability and service life under certain circumstances.
  • the turbine blade has a tie rod, which is arranged such that its tensile force counteracts the centrifugal force occurring during operation of the gas turbine.
  • the invention is based on the consideration that regarding the increase in the power of the gas turbine, the design in particular of the fourth turbine blade stage encounters production limits:
  • the blade should have an internal structure described above and be actively cooled. An extension of the blade necessary to increase the power would lead to a higher weight, which would increase the centrifugal forces, as the blade can withstand their stability. In order to increase the stability of the blade during operation, this should therefore have by their construction on a bias that counteracts the centrifugal forces. This can be achieved by a tie rod, which is correspondingly arranged in the hollow blade so that its tensile force counteracts the centrifugal forces during operation of the gas turbine.
  • the tie rod has a connection between its fixed to the blade end points, which is slightly shorter than the fixation of the end points on the blade itself.
  • the tie rod extends at least between the blade tip and platform region, so it is advantageously arranged so as to extend at least between the blade tip and the platform region with respect to the method.
  • the force of the tie rod acts on the entire area of the blade, which is detected by the centrifugal force.
  • the tie rod can also pass through the entire blade vertically, so that it is attached from the outside of the blade tip and blade root. But it can also be fixed within the blade root and the blade tip.
  • the tie rod comprises a biasing means, by means of which the tie rod is advantageously biased with respect to the method.
  • a biasing device is understood to mean a device by means of which the tensile force or tension of the tie rod can be adjusted. This can be achieved for example via a device arranged in the connection of the tie rod, by means of which the length of the tie rod can be adjusted, for example via a connection with a thread. This allows the tension adjusted set.
  • the airfoil typically includes a pressure sidewall and a suction sidewall. based on its arrangement in the hot gas duct of the turbine.
  • a part of the pressure side wall and / or suction side wall is formed as a separate part connected to the remaining airfoil.
  • this advantageously comprises connecting part of the pressure side wall and / or suction side wall to the remaining airfoil.
  • the airfoil is cast or forged in the casting or forging process as a partially open structure.
  • the tie rod is particularly easy to insert at the desired position in the blade and the tension can be better applied, especially if the blade is open on the pressure and suction side.
  • the open areas of the airfoil can then by means of a sheet o. ⁇ . be closed.
  • At least one rib integral with the rest of the airfoil is arranged between the pressure side wall and the suction side wall.
  • the casting or forging of the airfoil comprises casting at least one rib arranged between the pressure side wall and the suction side wall.
  • the ribs serve as already described at the beginning of the guide of cooling air through the blade. They are forged or cast here with the open structure of the airfoil, creating a stable ribbed structure into which the tie rod can be inserted.
  • the part closing off the open pressure and / or suction side is / are connected in a materially bonded manner to the remaining blade.
  • the part is preferably connected via a welded connection with the remaining blade, d. H.
  • the connection is preferably carried out by means of welding.
  • welding particularly suitable for this purpose is electron beam welding, which permits high welding speeds and is particularly suitable for welding the high-melting steels used for turbine blades.
  • a rotor for a gas turbine advantageously comprises a described turbine blade and / or a turbine blade produced by the described method.
  • a gas turbine advantageously comprises such a rotor.
  • the advantages achieved by the invention are, in particular, that a greater stability of the blade against centrifugal forces is achieved by the arrangement of a tie rod between the blade tip and blade root of a blade with a bias.
  • the blade can be made longer and / or operated at higher speeds. It can also be made heavier and more resistant to high temperatures. All of these effects allow higher performance of the gas turbine.
  • FIG. 1 shows a turbine 100, here a gas turbine, in a longitudinal partial section.
  • a turbine 100 is a turbomachine that converts the internal energy (enthalpy) of a flowing fluid (liquid or gas) into rotational energy and ultimately into mechanical drive energy.
  • the gas turbine 100 has inside a rotatably mounted around a rotation axis 102 (axial direction) rotor 103, which is also referred to as a turbine runner.
  • a rotation axis 102 axial direction
  • rotor 103 which is also referred to as a turbine runner.
  • an intake housing 104 a compressor 105, a toroidal combustion chamber 110, in particular annular combustion chamber 106, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109th
  • the annular combustion chamber 106 communicates with an annular hot gas channel 111.
  • Each Turbine stage 112 is formed of two blade rings.
  • a row 125 of blades 115 is formed in the hot gas channel 111 of a row of guide vanes 115.
  • the vanes 120, 130 are profiled slightly curved, similar to an aircraft wing.
  • the vanes 130 are attached to the stator 143, whereas the blades 120 of a row 125 are mounted on the rotor 103 by means of a turbine disk 133.
  • the rotor blades 120 thus form components of the rotor or rotor 103.
  • Coupled to the rotor 103 is a generator or a working machine (not shown).
  • air 105 is sucked in and compressed by the compressor 105 through the intake housing 104.
  • the compressed air provided at the turbine-side end of the compressor 105 is supplied to the burners 107 where it is mixed with a fuel.
  • the mixture is then burned to form the working fluid 113 in the combustion chamber 110. From there, the working fluid 113 flows along the hot gas passage 111 past the vanes 130 and the blades 120.
  • the components exposed to the hot working medium 113 are subject to thermal loads during operation of the gas turbine 100.
  • the guide vanes 130 and rotor blades 120 of the first turbine stage 112, viewed in the direction of flow of the working medium 113, are subjected to the greatest thermal stress in addition to the heat shield bricks lining the annular combustion chamber 106.
  • the high loads make highly resilient materials necessary.
  • the turbine blades 120, 130 are therefore made of titanium alloys, nickel superalloy, or tungsten-molybdenum alloys.
  • M Fe, Co, Ni, rare earths
  • thermal barrier coating for example ZrO2, Y2O4-ZrO2
  • TBC Thermal Barrier Coating
  • Other measures to make the blades more resistant to heat consist of sophisticated cooling duct systems. This technique is used in both the guide and rotor blades 120, 130.
  • Each vane 130 has a vane foot (also not shown), also referred to as a platform, facing the inner casing 138 of the turbine 108 and a vane head opposite the vane root.
  • the Leitschaufelkopf faces the rotor 103 and fixed to a sealing ring 140 of the stator 143.
  • Each sealing ring 140 encloses the shaft of the rotor 103.
  • each blade 120 has such a blade root, as in the following FIG. 2 is still shown, but ends in a blade tip.
  • FIG. 2 shows the blade 120 in a longitudinal section from the direction of a front view in the direction of FIG. 1
  • the blade 102 of the blade 120 is profiled in the cross section, not shown, similar to an aircraft wing.
  • the airfoil 144 is that portion of the blade 120 which projects into the hot gas passage 111. It ends in a blade tip 150.
  • the platform region 152 and the attachment region 154 adjoin the blade blade region.
  • the already mentioned, transversely oriented platform 156 is arranged, which serves to seal the rotor 103 against the hot gas. This is connected via a rounding with the blade 144.
  • profiles are provided in the attachment region 154, by means of which the rotor blade 120 is fixed to the rotor 103 in a fir tree-like tongue and groove connection.
  • a plurality of radially spaced cooling channels 158 are arranged, which are separated from one another by ribs 160, which are at different radial distances from the axis 102, d. H. extend at different distances from the platform 156 between pressure side wall 146 and suction side wall 148.
  • the ribs 160 may be disposed at other locations or the cooling channels 158 may be oriented in any other directions.
  • a tie rod 162 is additionally arranged in the interior of the rotor blade 120.
  • the tie rod 162 comprises two anchors 164, 166, one armature 164 of which is fastened in the region of the blade tip 150, the other armature 166 in the platform region 152. Both armatures 164, 166 are in the interior of the blade 144 in a form-fitting manner in a groove by a corresponding shaping fixed.
  • the two anchors 164, 166 are firmly connected to each other.
  • the tie rod 162 may also extend through the entire blade 120 and be secured from the outside.
  • the blade 120 is partially cast or forged open with the shown structure of the ribs 160.
  • pressure and suction side wall 146, 148 are open in such a manner that the tie rod 162 in the FIG. 2 after casting or forging can be used.
  • a biasing device 168 is disposed in the connection of the tie rod 162 between the anchors 164, 166. With the biasing device 168, it is possible to adjust the length of the tie rod 162 and thus to shorten the tie rod 162 and thereby create a preload between the blade tip 150 and platform portion 152 over the airfoil 144, which counteracts the centrifugal force during operation of the gas turbine 100.
  • the tie rod 162 may also be formed without pretensioning device 168, but must then already be provided during production with a corresponding undersize, so that the desired preload already arises when inserting the tie rod 162.
  • the open areas of the pressure and suction side wall 146, 148 are closed with sheets that are welded to the open remaining airfoil 144.

Landscapes

  • Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP14195679.7A 2014-12-01 2014-12-01 Aube directrice de turbine Withdrawn EP3029268A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP14195679.7A EP3029268A1 (fr) 2014-12-01 2014-12-01 Aube directrice de turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP14195679.7A EP3029268A1 (fr) 2014-12-01 2014-12-01 Aube directrice de turbine

Publications (1)

Publication Number Publication Date
EP3029268A1 true EP3029268A1 (fr) 2016-06-08

Family

ID=51999341

Family Applications (1)

Application Number Title Priority Date Filing Date
EP14195679.7A Withdrawn EP3029268A1 (fr) 2014-12-01 2014-12-01 Aube directrice de turbine

Country Status (1)

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EP (1) EP3029268A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11536144B2 (en) 2020-09-30 2022-12-27 General Electric Company Rotor blade damping structures
US11739645B2 (en) 2020-09-30 2023-08-29 General Electric Company Vibrational dampening elements

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4314794A (en) * 1979-10-25 1982-02-09 Westinghouse Electric Corp. Transpiration cooled blade for a gas turbine engine
US20060120874A1 (en) * 2004-12-02 2006-06-08 Siemens Westinghouse Power Corp. Stacked lamellate assembly
EP2196624A1 (fr) * 2008-12-12 2010-06-16 Alstom Technology Ltd Aube d'une turbine à gaz
US8142163B1 (en) * 2008-02-01 2012-03-27 Florida Turbine Technologies, Inc. Turbine blade with spar and shell

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4314794A (en) * 1979-10-25 1982-02-09 Westinghouse Electric Corp. Transpiration cooled blade for a gas turbine engine
US20060120874A1 (en) * 2004-12-02 2006-06-08 Siemens Westinghouse Power Corp. Stacked lamellate assembly
US8142163B1 (en) * 2008-02-01 2012-03-27 Florida Turbine Technologies, Inc. Turbine blade with spar and shell
EP2196624A1 (fr) * 2008-12-12 2010-06-16 Alstom Technology Ltd Aube d'une turbine à gaz

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11536144B2 (en) 2020-09-30 2022-12-27 General Electric Company Rotor blade damping structures
US11739645B2 (en) 2020-09-30 2023-08-29 General Electric Company Vibrational dampening elements

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