EP3249158A1 - Aube de turbine et turbomachine axiale - Google Patents

Aube de turbine et turbomachine axiale Download PDF

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Publication number
EP3249158A1
EP3249158A1 EP16170802.9A EP16170802A EP3249158A1 EP 3249158 A1 EP3249158 A1 EP 3249158A1 EP 16170802 A EP16170802 A EP 16170802A EP 3249158 A1 EP3249158 A1 EP 3249158A1
Authority
EP
European Patent Office
Prior art keywords
turbine blade
chambers
chamber
axial flow
cavity
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Withdrawn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
EP16170802.9A
Other languages
German (de)
English (en)
Inventor
Andreas Heselhaus
Marcel SCHLÖSSER
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 EP16170802.9A priority Critical patent/EP3249158A1/fr
Publication of EP3249158A1 publication Critical patent/EP3249158A1/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Withdrawn legal-status Critical Current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
    • 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
    • F01D5/16—Form or construction for counteracting blade vibration
    • 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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • 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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/186—Film cooling
    • 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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • 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
    • F05D2240/81—Cooled platforms

Definitions

  • the invention relates to a turbine blade for an axial flow machine and the axial flow machine with the turbine blade.
  • An axial flow machine such as a gas turbine or a steam turbine, has rows of vanes, the vanes being either vanes mounted on the housing of the axial flow machine or blades mounted on the shaft of the axial flow machine.
  • the blades have a platform in the area of their blade roots which delimit the flow channel in a radial direction of the axial flow machine.
  • the blades may be arranged as compressor blades in a compressor or as turbine blades in a turbine.
  • the platforms of the turbine blades are exposed to a hot gas, for example water vapor or exhaust gases leaving a combustion chamber, which can lead to oxidation of the platforms and thus weakening of the base material of the platforms.
  • a hot gas for example water vapor or exhaust gases leaving a combustion chamber
  • the base material of the platforms is coated with a thermal barrier coating to avoid too high a temperature of the base material.
  • the use of the thermal barrier coating can lead to high temperature gradients in the platform, which can lead to flaking of the thermal barrier coating. The spalling causes the base material to be exposed to the hot gas, which can lead to the oxidation of the base material.
  • the platforms are cooled by providing cooling air holes in the platform that lead to the top and / or sides of the platform.
  • cooling air is passed through the Passage cooling air holes, whereby a cooling of the platform takes place.
  • cooling air bores disadvantageous in the platform warmer and colder areas, which can lead to the formation of mechanical stresses in the platform. These mechanical stresses can in turn lead to the chipping of the thermal barrier coating.
  • the object of the invention is therefore to provide a turbine blade for an axial flow machine and the axial flow machine with the turbine blade, are reduced in the mechanical stresses due to temperature gradients in a platform of the turbine blade.
  • the turbine blade for an axial flow machine comprises an airfoil, a platform and a cavity disposed inside the airfoil, the platform having a support wall to which the airfoil is fixedly mounted and which defines the cavity, at least one within the platform Chamber, which is arranged on the side facing away from the cavity of the support wall, and at least one arranged in the support wall through hole, which connects the cavity fluid-conductively connected to the chamber, so that a during operation of the axial flow in the cavity flowing cooling fluid from the cavity into the Chamber can flow, wherein the sum of the cross sections of the through holes perpendicular to the flow direction of the cooling fluid in the through holes is less than the sum of the cross sections of the chambers perpendicular to the flow direction of the cooling fluid in the chambers.
  • the chambers By providing the chambers, a more uniform cooling of the turbine blade is advantageously possible, as is the case by providing cooling air bores. As a result, during operation of the axial flow machine, the temperature gradients in the platform are low, thereby reducing mechanical stresses in the platform.
  • the support wall is advantageously provided for the airfoil a supporting structure.
  • the airfoil may flutter during operation of the axial flow machine, which is a self-excited vibration of the airfoil. The fluttering leads to a high load on the turbine blade, in particular in the region of the supporting structure. As a result, the slight weakening is especially advantageous in the area of the supporting structure.
  • the sum of the cross sections of the through holes perpendicular to the flow direction of the cooling fluid in the through holes is less than one tenth, in particular less than one twentieth, the sum of the cross sections of the chambers perpendicular to the flow direction of the cooling fluid in the chambers.
  • the flow direction of the cooling fluid in the through hole and in the chamber is preferably directed substantially in the circumferential direction of the axial flow machine.
  • the turbine blade has a blade root which is fixedly mounted on the side of the support wall facing away from the blade leaf. As a result, the blade root is a supporting structure for the supporting wall and thus indirectly a supporting structure for the blade.
  • the support wall preferably extends in the circumferential direction of the axial flow machine in a direction away from the cavity at least as far as the airfoil.
  • the support wall carries the blade particularly stable. It is particularly preferred that the support wall extends in the circumferential direction of the axial flow machine in a direction away from the cavity as far as the airfoil.
  • the support wall carries the blade particularly stable and at the same time the chamber is formed large, whereby a good cooling of the platform is possible.
  • the ratio of the length of the chamber in the circumferential direction of the axial flow machine to the Sum of the length of the chamber in the circumferential direction and the length of the through hole in the circumferential direction of 0.1 to 0.9, in particular from 0.5 to 0.9.
  • a plurality of the chambers are provided juxtaposed in the axial direction of the axial flow machine, and the ratio of the width of one of the chambers in the axial direction to the sum of the length of the one chamber in a circumferential direction of the axial flow and the Length of one of the through holes, which opens into the one chamber, in the circumferential direction is at most 1.
  • Two adjacent chambers are each separated by a partition. By providing the partition results in increased strength of the platform. In the event that only one of the chambers arranged next to one another in the axial direction is provided, the ratio can also be greater than 1.
  • a plurality of the chambers is provided, which is arranged side by side in the axial direction of the axial flow, and the distance of two adjacent chambers of the plurality is smaller than half, in particular smaller than one fifth, than the width of one of the chambers of the plurality. Due to the short distance of the chambers from each other a particularly uniform cooling of the platform is possible.
  • the accumulated widths in the axial direction of the axial flow machine of all the axially adjacent chambers are from 10% to 90%, particularly from 50% to 90%, of the platform width in the axial direction. This allows a good and homogeneous cooling of the platform.
  • the diameter of the through hole is preferably from 0.5 mm to 2 mm. Due to this diameter, only a slight weakening of the support wall occurs. It is preferable that at least one of the chambers on the pressure side of the airfoil and at least one of the chambers on the suction side of the airfoil are provided. This advantageously achieves uniform cooling of the entire platform.
  • the turbine blade preferably has at least one passageway passing through a first wall defining the chamber in an axial direction of the turbomachine at the side facing the airfoil.
  • the cooling fluid may enter the flow channel of the axial flow machine through the passageways and cause film cooling on the surface of the platform facing the flow channel.
  • the axial flow machine according to the invention has at least one of the turbine blades according to the invention.
  • the airfoil 2 has a front edge 6, a trailing edge 7, a blade tip 8, a pressure side 17 and a suction side 18.
  • the turbine blade 1 further has a platform 3, which is arranged on the blade tip 8 facing away from the end of the blade 2, and a blade root 9, which is arranged on the side facing away from the blade 2 of the platform 3.
  • the turbine blade 1 also has a cavity 4, which is arranged in the interior of the blade 2, the platform 3 and the blade root 9.
  • the airfoil 2 has at least one web 5, which connects the pressure side 17 with the suction side 18 and thus causes a stiffening of the airfoil.
  • the platform 3 has a support wall 14 which defines the cavity 4 and on which the blade 2 and the blade root 9 are fixedly mounted.
  • the support wall 14 extends in the radial direction r of the axial flow from the blade 2 to the blade root 9.
  • the platform 3 further comprises at least one arranged within the platform 3 chamber 10, which arranged on the side facing away from the cavity 4 of the support wall 14 is.
  • the support wall 14 is the area of the platform 3, which extends from the cavity 4 to the chamber 10.
  • the platform 3 has at least one through hole 11 arranged in the support wall 14, which connects the cavity 4 to the chamber 10 in a fluid-conducting manner.
  • FIG. 3 it can be seen, at least one of the chambers 10 with the associated through hole 11 on the pressure side 17 of the airfoil 2 and at least one of the chambers 10 is provided with the associated through hole 11 on the suction side of the airfoil 2.
  • FIG. 3 are represented by arrows 12 that during operation of the axial flow machine, a cooling fluid, such as cooling air, flows in the cavity 4 from the blade root 9 toward the blade tip 8.
  • a cooling fluid such as cooling air
  • cooling air holes are provided, through which the cooling fluid can escape from the cavity 4.
  • a portion of the cooling fluid flows from the cavity 4 via the through hole 11 into the chamber 10.
  • the sum of the cross sections of the through holes 11 perpendicular to the flow direction of the cooling fluid in the through holes 11 is less than, in particular less than one tenth than, in particular less than one
  • the flow direction of the cooling fluid in the through hole 11 and in the chamber 10 is directed substantially in the circumferential direction u of the axial flow machine.
  • the blade 2 has on its pressure side 17 immediately adjacent to the platform 3, a first curved portion 15, which protrudes in the circumferential direction u from the remaining pressure side 17.
  • the airfoil 2 has on its suction side 18 immediately adjacent to the platform 3, a second curved portion 16 which protrudes in the circumferential direction u from the remaining suction side 18.
  • the support wall 14 extends in the circumferential direction u of the axial flow in a direction away from the cavity 4 at least as far as the two curved portions 15, 16 of the airfoil 2 extends.
  • FIGS. 1 to 5 show that the platform 3 has a first wall 19 which bounds the chamber 10 in the radial direction r of the axial flow machine.
  • the platform 3 has a second wall 20 which bounds the chamber 10 opposite the first wall 19.
  • the platform 3 has a third wall 21 which bounds the chamber 10 in an axial direction a of the axial flow machine.
  • the platform 3 has a fourth wall 22 which bounds the chamber opposite the third wall 21.
  • the chamber 10 has a rectangular cross-section in the circumferential direction u. It is also possible not to provide the third wall 21 and the fourth wall 22, so that the working fluid can escape from the chamber 10 on both sides in the axial direction. Likewise, it is possible to provide a fifth wall which limits the chamber 10 in the circumferential direction 5 to the support wall 14.
  • FIGS. 1 . 4 and 5 show that the ratio of the length L1 of the chamber 10 in the circumferential direction u of the axial flow machine to the sum L of the length L1 of the chamber in the circumferential direction u and the length L2 of the through-hole 11 in the circumferential direction u is at least 0.5.
  • the ratio of the height s of the chamber in the radial direction r of the axial flow machine to a height h of the platform 3 in the radial direction r is 0.15 to 0.85, preferably 0.25 to 0.4, more preferably substantially 0.33.
  • the summed widths b in the axial direction a of the axial flow machine of all the chambers 10 arranged side by side in the axial direction a is from 50% to 100% of the platform width B in the axial direction a.
  • the diameter of the through hole 11 is from 0.3 mm to 2 mm.
  • the first embodiment according to FIGS. 1 to 3 has a plurality of the chambers 10, which in the axial direction a of the Axial flow machine is arranged side by side.
  • the first embodiment has one of the multiple numbers on the pressure side 17 and one of the multiple numbers on the suction side 18.
  • the second embodiment according to FIG. 4 and the third embodiment according to FIG. 5 each have a single one of the chambers 10 on the pressure side 17 and on the suction side 18.
  • the ratio of the width b of one of the chambers 10 in the axial direction to the sum L of the length L1 of the one chamber in a circumferential direction u of the axial flow machine and the length L2 is one of the through holes 11 opening into the one chamber
  • the distance d of two adjacent chambers 10 of the plurality is smaller than one-fifth, in particular smaller than one-tenth, as the width b of one of the chambers 10 of the plurality.
  • the first embodiment the webs 5, which connect the pressure side 17 with the suction side 18.
  • the arranged within the airfoil 2 cavity 4 is subdivided into subspaces.
  • one of the chambers 10 is provided for each partial space on each pressure side 17 and the suction side 18.
  • at least one of the through holes 10 is provided.
  • the chambers 10 may be arranged in the axial direction a in alignment with the subspaces.
  • the second embodiment according to FIG. 4 differs from the third embodiment according to FIG. 5 in that the chamber 10 of the second embodiment is made shorter in the axial direction a than the chamber 10 of the third embodiment.
  • each of the subspaces is fluidly connected to the chamber 11 via at least one of the through holes 10, whereas in the second embodiment, each of the subspaces is not fluidly connected to the chamber 11 Subspaces connected by means of at least one of the through holes 10 fluidly connected to the chamber 11.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP16170802.9A 2016-05-23 2016-05-23 Aube de turbine et turbomachine axiale Withdrawn EP3249158A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP16170802.9A EP3249158A1 (fr) 2016-05-23 2016-05-23 Aube de turbine et turbomachine axiale

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP16170802.9A EP3249158A1 (fr) 2016-05-23 2016-05-23 Aube de turbine et turbomachine axiale

Publications (1)

Publication Number Publication Date
EP3249158A1 true EP3249158A1 (fr) 2017-11-29

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ID=56068767

Family Applications (1)

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EP16170802.9A Withdrawn EP3249158A1 (fr) 2016-05-23 2016-05-23 Aube de turbine et turbomachine axiale

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EP (1) EP3249158A1 (fr)

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1795703A2 (fr) * 2005-12-08 2007-06-13 General Electric Company Amortisseur pour une plateforme refroidie d'aube de turbine
US8133024B1 (en) * 2009-06-23 2012-03-13 Florida Turbine Technologies, Inc. Turbine blade with root corner cooling
EP2455586A1 (fr) * 2010-11-17 2012-05-23 MTU Aero Engines GmbH Rotor pour une turbomachine comportant des éléments de étanchéité et des amortissement
DE102013109146A1 (de) * 2012-08-31 2014-03-06 General Electric Company Kühlanordnung für den Plattformbereich einer Turbinenlaufschaufel

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1795703A2 (fr) * 2005-12-08 2007-06-13 General Electric Company Amortisseur pour une plateforme refroidie d'aube de turbine
US8133024B1 (en) * 2009-06-23 2012-03-13 Florida Turbine Technologies, Inc. Turbine blade with root corner cooling
EP2455586A1 (fr) * 2010-11-17 2012-05-23 MTU Aero Engines GmbH Rotor pour une turbomachine comportant des éléments de étanchéité et des amortissement
DE102013109146A1 (de) * 2012-08-31 2014-03-06 General Electric Company Kühlanordnung für den Plattformbereich einer Turbinenlaufschaufel

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