EP3232001A1 - Aube rotorique de turbine - Google Patents

Aube rotorique de turbine Download PDF

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Publication number
EP3232001A1
EP3232001A1 EP16165558.4A EP16165558A EP3232001A1 EP 3232001 A1 EP3232001 A1 EP 3232001A1 EP 16165558 A EP16165558 A EP 16165558A EP 3232001 A1 EP3232001 A1 EP 3232001A1
Authority
EP
European Patent Office
Prior art keywords
blade
cooling
platform
transverse edge
inflow
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Withdrawn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
EP16165558.4A
Other languages
German (de)
English (en)
Inventor
Kunyuan Zhou
Horst-Michael Dreher
Matthias Hüls
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 EP16165558.4A priority Critical patent/EP3232001A1/fr
Publication of EP3232001A1 publication Critical patent/EP3232001A1/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Withdrawn legal-status Critical Current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
    • F01D5/18—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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade
    • 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
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid

Definitions

  • the invention relates to a blade according to the preamble of claim 1.
  • a corresponding to the preamble of claim 1 blade is for example from the EP 1 207 268 A1 known.
  • a disadvantage of the known blade is that the inflow-side transverse edge of the platform is impact-cooled laterally of the leading edge of the airfoil. This leads to an uneven temperature load along the transverse edge, wherein in particular of the leading edge of the blade upstream region of the transverse edges is less impact-cooled.
  • the cooling air used for surface cooling of the platform is blown out like a slit. This prevents a uniform cooling air outlet.
  • the object of the invention is therefore to provide a blade of the type mentioned, in which the disadvantages known in the prior art have been eliminated.
  • a rotor blade comprising a fir-tree-shaped blade root, which merges into a substantially rhomboidal or rectangular platform by means of an adjoining blade neck, which on its side facing away from the blade neck has an aerodynamically curved blade with a front edge which can be flowed by a hot gas in terms of the platform the hot gas has an inflow-side transverse edge and a trailing-side transverse edge, and the airfoil has a cooling system with at least one cooling channel extending radially through the blade neck and the platform extending into the airfoil, for cooling by a surface on the blade or shovel side
  • a cooling medium can be supplied to the feed opening, provided that the blade in the region of the platform comprises means for at least partial impingement cooling of the inflow-side transverse edge, which means are fluidically connected to the first cooling channel.
  • the means for impingement cooling of the inflow-side transverse edge of the platform comprises an impingement cooling chamber extending essentially parallel to the transverse edge in the interior of the platform, which is in flow communication with the cooling channel via at least one impingement cooling opening.
  • impingement cooling chamber which extends substantially parallel to the transverse edge, enables large-area cooling of the inflow-side transverse edge.
  • edge used both for the "transverse edge” and for the “leading edge”, is not in the sense of a “corner”, but in the sense of a narrow, but elongated "surface".
  • the means for impingement cooling of the inflow-side transverse edge comprises an impingement cooling space extending in the interior of the platform substantially parallel to the transverse edge, which is connected via at least one impingement cooling opening to an intermediate space which can be supplied with coolant from the cooling passage.
  • a simplified inner structure of the moving blade can be provided, which can be manufactured comparatively easily in the case where the moving blade is manufactured in a casting process.
  • a comparatively long portion of the transverse edge can thereby be impinged with a coolant having a higher pressure.
  • the cooling chamber is adjoined by a further cooling channel, which is provided for convective cooling of the suction-side platform surface which can be overflowed by hot gas.
  • a further cooling channel which is provided for convective cooling of the suction-side platform surface which can be overflowed by hot gas.
  • the impingement cooling space is arranged at least upstream of the leading edge of the front profile with respect to the main flow direction of the hot gas.
  • the local cooling proposed here is of particular advantage, so that the life of a demenschend configured blade is improved compared to the known blade.
  • a sealing arm protrudes in front of the inflow-side transverse edge of the platform.
  • the cooling effect can thus also be extended to the root region of the sealing arm, as a result of which it can withstand higher thermal loads.
  • FIG. 1 shows in perspective view a blade 120 for a turbine, which extends along a longitudinal axis 121 (radial direction).
  • the blade 120 has along the longitudinal axis 121 consecutively on a mounting portion 400, an adjoining paddle platform 403, an airfoil 406 and a blade tip 19.
  • a blade root 183 is formed, which serves for fastening of the rotor blades 120 to a shaft, not shown.
  • the blade root 183 is designed as a Christmas tree.
  • Other configurations, for example as Schwalbenschwanzfuß, are possible.
  • the blade 120 is at least partially hollow and is cooled inside.
  • the rotor blade 120 has, for example, a first coolant inlet area 22 and a second coolant inlet area 25.
  • the blade 120 is flowed around in the axial direction 34 of a hot medium.
  • the hot medium strikes first in the axial direction 34 on a front edge 13 and then flows past the airfoil 406 up to a trailing edge 10.
  • the coolant which penetrates through the first coolant inlet region 22 into a first cooling channel 37, which follows in the axial direction 34 directly behind the leading edge 13, flows in the longitudinal direction 121 up to the blade tip 19.
  • a first cooling channel 37 which follows in the axial direction 34 directly behind the leading edge 13 flows in the longitudinal direction 121 up to the blade tip 19.
  • first outlet opening 40 for the coolant present.
  • this part of the coolant leaves the rotor blade 120.
  • Coolant also flows through the second coolant inlet region 25 into an inner cavity 46, which adjoins the first cooling channel 37 in the axial direction 34.
  • the inner cavity 46 is, for example, meander-shaped, so that part of the coolant flows meander-shaped in the interior of the rotor blade 120 towards the region of the trailing edge 10 and exits there distributed along the trailing edge 10 from the rotor blade 120.
  • a plurality of impact cooling openings 52 are present in a first cooling channel of the meandering region separating wall 49 .
  • the impact cooling holes 52 the coolant flows from the inner cavity 46 in the first cooling channel 37, where it meets the inner wall surface 53 of the leading edge 13 and cools them by means of impingement cooling.
  • the coolant (air and / or steam) flowing through the impingement cooling holes 52 into the first cooling passage 37 may flow together with the coolant flowing through the first coolant input portion 22 has flowed through the first outlet opening 40 to the outside.
  • the first coolant inlet region 22 may also be completely closed, so that coolant only penetrates from the inner cavity 46 into the first cooling channel 37.
  • the blade platform 403 comprises an inflow-side transverse edge 71 and an outflow-side transverse edge 73.
  • An impingement cooling space 75 is provided in the material forming the inflow-side transverse edge 71 of the blade platform 403.
  • the impingement cooling space 75 is in fluid communication with the first cooling passage 37 via a series of further impingement cooling openings 76.
  • part of the coolant flowing in the first cooling channel 37 can be used for impingement cooling of the inflow-side transverse edge 71, the impingement cooling chamber 75 preferably extending approximately over the entire length of the inflow-side transverse edge 71.
  • the cooling medium flowing into the baffle cooling chamber 75 can be drained out of this via openings which are not shown further.
  • FIG. 2 shows the longitudinal direction 121 is a top view of a blade.
  • a gap 77 is arranged between the first cooling channel 37 and the impingement cooling chamber 75, which serves as a distributor space.
  • the intermediate space 77 can be supplied with coolant from the first cooling passage 37 only via a comparatively short cooling air passage 79. This is then supplied via a plurality of impingement cooling openings 76 in the impingement cooling chamber 75.
  • the impingement cooling chamber 75 also extends here in particular over the entire longitudinal extent of the transverse edge 71 of the blade platform 403.
  • a cooling channel section 80 serving for the convective cooling of the platform 403 connects, its mouth 81 in the middle the downstream transverse edge 73 of the platform 403 is arranged.
  • the side view of this blade 120 is in FIG. 3 shown schematically, with insignificant features are hidden for the invention.
  • a sealing arm 74 is also provided, on the outwardly facing surface of which sealing teeth of a labyrinth seal can be arranged in a known manner.
  • the invention thus relates to a blade 120 for a turbine comprising a blade root 183, which merges by means of a subsequent blade neck in a substantially rhomboid- or rectangular platform 403, which on its side facing away from the blade neck an aerodynamically curved blade 406 with a with hot gas flowing in front edge 13, the platform 403 having an upstream transverse edge 71 and a downstream transverse edge 73 with respect to the hot gas and the airfoil 406 cooling its hot gas overflowable surfaces inside a cooling system having at least one radially through the blade neck and the platform 403 has a cooling channel 37 extending into the airfoil 406, to which a cooling medium can be supplied through a feed-side or a blade-side feed opening.
  • the cooling channel in the region of the platform has means for at least partial impingement cooling of the inflow-side transverse edge 71.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP16165558.4A 2016-04-15 2016-04-15 Aube rotorique de turbine Withdrawn EP3232001A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP16165558.4A EP3232001A1 (fr) 2016-04-15 2016-04-15 Aube rotorique de turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP16165558.4A EP3232001A1 (fr) 2016-04-15 2016-04-15 Aube rotorique de turbine

Publications (1)

Publication Number Publication Date
EP3232001A1 true EP3232001A1 (fr) 2017-10-18

Family

ID=55755476

Family Applications (1)

Application Number Title Priority Date Filing Date
EP16165558.4A Withdrawn EP3232001A1 (fr) 2016-04-15 2016-04-15 Aube rotorique de turbine

Country Status (1)

Country Link
EP (1) EP3232001A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110234840A (zh) * 2017-01-31 2019-09-13 西门子股份公司 用于燃气涡轮的涡轮动叶或涡轮静叶
EP3670836A1 (fr) * 2018-12-12 2020-06-24 United Technologies Corporation Plateforme de profil aérodynamique dotée d'orifices de refroidissement
JP7424893B2 (ja) 2019-04-04 2024-01-30 マン・エナジー・ソリューションズ・エスイー ターボ機械の動翼

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3446480A (en) * 1966-12-19 1969-05-27 Gen Motors Corp Turbine rotor
EP1207268A1 (fr) 2000-11-16 2002-05-22 Siemens Aktiengesellschaft Aube de turbine à gaz et procédé de fabrication d'une aube de turbine à gaz
US20070116574A1 (en) * 2005-11-21 2007-05-24 General Electric Company Gas turbine bucket with cooled platform leading edge and method of cooling platform leading edge
US8118554B1 (en) * 2009-06-22 2012-02-21 Florida Turbine Technologies, Inc. Turbine vane with endwall cooling

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3446480A (en) * 1966-12-19 1969-05-27 Gen Motors Corp Turbine rotor
EP1207268A1 (fr) 2000-11-16 2002-05-22 Siemens Aktiengesellschaft Aube de turbine à gaz et procédé de fabrication d'une aube de turbine à gaz
US20070116574A1 (en) * 2005-11-21 2007-05-24 General Electric Company Gas turbine bucket with cooled platform leading edge and method of cooling platform leading edge
US8118554B1 (en) * 2009-06-22 2012-02-21 Florida Turbine Technologies, Inc. Turbine vane with endwall cooling

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110234840A (zh) * 2017-01-31 2019-09-13 西门子股份公司 用于燃气涡轮的涡轮动叶或涡轮静叶
US11053802B2 (en) 2017-01-31 2021-07-06 Siemens Energy Global GmbH & Co. KG Turbine blade or a turbine vane for a gas turbine
EP3670836A1 (fr) * 2018-12-12 2020-06-24 United Technologies Corporation Plateforme de profil aérodynamique dotée d'orifices de refroidissement
US11203939B2 (en) 2018-12-12 2021-12-21 Raytheon Technologies Corporation Airfoil platform with cooling orifices
JP7424893B2 (ja) 2019-04-04 2024-01-30 マン・エナジー・ソリューションズ・エスイー ターボ機械の動翼

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