EP3232004A1 - Aube rotorique pour une turbomachine thermique - Google Patents

Aube rotorique pour une turbomachine thermique Download PDF

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Publication number
EP3232004A1
EP3232004A1 EP16165216.9A EP16165216A EP3232004A1 EP 3232004 A1 EP3232004 A1 EP 3232004A1 EP 16165216 A EP16165216 A EP 16165216A EP 3232004 A1 EP3232004 A1 EP 3232004A1
Authority
EP
European Patent Office
Prior art keywords
blade
squealer
tip
edges
tip surface
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Withdrawn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
EP16165216.9A
Other languages
German (de)
English (en)
Inventor
Bernd Hornung
Frank Schulz
Anne Maria Starke
Eric Thomas
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 EP16165216.9A priority Critical patent/EP3232004A1/fr
Publication of EP3232004A1 publication Critical patent/EP3232004A1/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Withdrawn legal-status Critical Current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
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • F05D2250/294—Three-dimensional machined; miscellaneous grooved
    • 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
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/32—Arrangement of components according to their shape
    • F05D2250/324—Arrangement of components according to their shape divergent

Definitions

  • the invention relates to a blade for a thermal turbomachine according to the preamble of claim 1.
  • a corresponding to the preamble of claim 1 blade is for example from the US 8,708,645 B1 known.
  • the known blade has at its blade tip a virtually closed circumferential squealer in the form of an extension of the airfoil walls of the airfoil. Between the suction-side and the pressure-side rubbing edge, further squealer edges are provided on the blade tip, so that swirl channels are formed between the individual, substantially parallel squealer edges.
  • the disadvantage is that during operation of such a turbine blade wear can occur on the squealer, which can adversely affect the life of the blade and also the efficiency of a gas turbine equipped therewith.
  • the object of the invention is therefore to provide a blade whose blade tip is less susceptible to wear.
  • the generic blade has at least two squealer edges, which are connected to each other at the tip surface side in a common root area.
  • the invention is based on the recognition that by two immediately adjacent squealer edges, the top surface side are connected to each other in a common root area, the wear, in particular when rubbed or by oxidation of the squealer, can be reduced. This is due to the fact that due to the common root area this - when viewing the squealer in cross section - is wider and thus more massive, compared to completely separate squealer edges.
  • cooling air passages which can be fed with cooling air from a cavity arranged in the airfoil open between the two relevant contact edges, which preferably form a V shape.
  • the thus existing between the two squeal, comparatively narrow grooves allow a more direct and immediate flow of the squealer with cooling air.
  • twice the number of sealing surfaces per suction side and per pressure side results from the presence of the total circumferential two rubbing edges with a common root area.
  • a longer duration can be achieved with constant efficiency, which represents a greater benefit for the operator of the gas turbine plant.
  • FIG. 3 shows a schematic representation of a rotor blade 10 for a thermal turbomachine, in particular for a stationary gas turbine, which is known to comprise successively: a blade root 12 for attachment of the blade 10 to a rotatable blade carrier.
  • the blade carrier can be designed, for example, as a welded rotor or as a rotor in disk construction. Both rotor variants are not shown here.
  • the blade 10 comprises an aerodynamically curved freestanding airfoil 14 which extends from a leading edge 16 of a working medium to a trailing edge 18 and transversely thereto from a blade end 20 to a blade tip 22 opposite the blade tip end 20.
  • the blade tip 22 is arranged in a gap-forming manner opposite to an outer wall bounding the flow path of the thermal turbomachine.
  • the blade 10 has an outwardly - thus away from the blade root - pointing tip surface 24 on which at least one of them protruding squealer is provided. Not in the FIG. 3 but in the Figures 1 and 2 these are representing in detail.
  • FIG. 1 shows the blade tip 22 in a perspective view.
  • Both on the pressure side 19 and on the suction side 17 of the blade 14 are provided on the blade tip 22 in each case two squealer edges 26, which merge into one another on the front edge side and the trailing edge side.
  • an outer, closed circumferential first squealer edge 26a and of an inner, also closed circumferential squealer edge 26b be discussed.
  • a half space 31 is enclosed, which opens radially outwards and radially inwardly from a crown bottom 33 (FIGS. Fig. 2 ) is limited.
  • outer squealer edge 26a nor the inner squealer edge 26b must be impermeably closed circumferential can also be configured only partially circumferential.
  • V-shaped groove 27 is present, so that the conceptually to a pair of summarizable outer and inner squealer edges 26a, 26b are also formed substantially V-shaped.
  • the rubbing edges 26 merge into a common root region 28 whose inner end terminates at the tip surface 24 (blade tip side). As a result, the squealer edges 26 have at their outer (free) end 29 a width B which is less than the width W of the root area.
  • Cooling channels 30 can open at the bottom of the groove 27 so that cooling air can flow out of the interior of the blade 10.
  • the outflow of the cooling air serves on the one hand for cooling the immediately adjacent squashing edges 26 and in particular also for cooling the root area 28.
  • the cooling air openings 30 can be provided at a uniform or uneven distance along the circumference or the longitudinal extent of the squealer edges 26. Of the cooling channels 30 are in FIG. 2 only some examples shown.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP16165216.9A 2016-04-14 2016-04-14 Aube rotorique pour une turbomachine thermique Withdrawn EP3232004A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP16165216.9A EP3232004A1 (fr) 2016-04-14 2016-04-14 Aube rotorique pour une turbomachine thermique

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP16165216.9A EP3232004A1 (fr) 2016-04-14 2016-04-14 Aube rotorique pour une turbomachine thermique

Publications (1)

Publication Number Publication Date
EP3232004A1 true EP3232004A1 (fr) 2017-10-18

Family

ID=55754172

Family Applications (1)

Application Number Title Priority Date Filing Date
EP16165216.9A Withdrawn EP3232004A1 (fr) 2016-04-14 2016-04-14 Aube rotorique pour une turbomachine thermique

Country Status (1)

Country Link
EP (1) EP3232004A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2019088992A1 (fr) * 2017-10-31 2019-05-09 Siemens Aktiengesellschaft Aube de turbine avec tranchée pointe
CN112282855A (zh) * 2020-09-27 2021-01-29 哈尔滨工业大学 涡轮叶片

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5660523A (en) * 1992-02-03 1997-08-26 General Electric Company Turbine blade squealer tip peripheral end wall with cooling passage arrangement
US20140044557A1 (en) * 2012-08-09 2014-02-13 General Electric Company Turbine blade and method for cooling the turbine blade
US8708645B1 (en) 2011-10-24 2014-04-29 Florida Turbine Technologies, Inc. Turbine rotor blade with multi-vortex tip cooling channels
US8801377B1 (en) * 2011-08-25 2014-08-12 Florida Turbine Technologies, Inc. Turbine blade with tip cooling and sealing
WO2016071620A1 (fr) * 2014-11-04 2016-05-12 Snecma Aube de turbine avec capuchon d'extrémité

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5660523A (en) * 1992-02-03 1997-08-26 General Electric Company Turbine blade squealer tip peripheral end wall with cooling passage arrangement
US8801377B1 (en) * 2011-08-25 2014-08-12 Florida Turbine Technologies, Inc. Turbine blade with tip cooling and sealing
US8708645B1 (en) 2011-10-24 2014-04-29 Florida Turbine Technologies, Inc. Turbine rotor blade with multi-vortex tip cooling channels
US20140044557A1 (en) * 2012-08-09 2014-02-13 General Electric Company Turbine blade and method for cooling the turbine blade
WO2016071620A1 (fr) * 2014-11-04 2016-05-12 Snecma Aube de turbine avec capuchon d'extrémité

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2019088992A1 (fr) * 2017-10-31 2019-05-09 Siemens Aktiengesellschaft Aube de turbine avec tranchée pointe
JP2021501285A (ja) * 2017-10-31 2021-01-14 シーメンス アクティエンゲゼルシャフト 先端トレンチ付きタービンブレード
US11293288B2 (en) 2017-10-31 2022-04-05 Siemens Energy Global GmbH & Co. KG Turbine blade with tip trench
CN112282855A (zh) * 2020-09-27 2021-01-29 哈尔滨工业大学 涡轮叶片

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