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
  • F01D5/141—Shape, i.e. outer, aerodynamic form
• • 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
  • F05D2220/00—Application
  • F05D2220/30—Application in turbines
  • F05D2220/31—Application in turbines in steam turbines
• • 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
  • F05D2240/10—Stators
  • F05D2240/12—Fluid guiding means, e.g. vanes
• • 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
  • F05D2240/301—Cross-sectional characteristics
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
  • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
  • Y02T50/00—Aeronautics or air transport
  • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
  • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y10S416/00—Fluid reaction surfaces, i.e. impellers
  • Y10S416/02—Formulas of curves
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
  • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y10S416/00—Fluid reaction surfaces, i.e. impellers
  • Y10S416/05—Variable camber or chord length

Definitions

• the present invention relates to a turbomachine blade according to the preamble of claim 1. It further comprises a rotor and a stator of a turbomachine, in particular a steam turbine, and a turbomachine itself, which comprises such blades.
• the split ratio is defined as the distance between two adjacent blades of a blade row with respect to the chord length of the blades. The distance is usually determined in the average section of the grid, and thus results from the defined at the center section radius circumferential length, based on the number of blades of the blade row.
• a larger division ratio initially leads to lower profile losses, because the wetted surface and thus the friction losses occurring in the blade boundary layers decrease.
• An object of the present invention is to provide a new turbomachine blade based on a turbomachinery blade of the type mentioned above. More specifically, a turbomachinery bucket of the type mentioned above is to be specified, which allows a further reduction of the total losses of a blade grid.
• the blade thus has a chord length which is variable over the blade leaf extension.
• the doubt parameter the definition and meaning of which is familiar to the person skilled in the art, is set variably over the longitudinal extent of the blade, such that the losses of the associated blade grid are minimized.
• the doubt parameter is set in such a way that it is greater in the center region of the blade than at the top end or the bottom end.
• the chordal length distribution is sought such that the dimensionless doubt parameter assumes values around 0.9 in the center region to ideally drop to the top end of the airfoil at values around 0.7; in practice, such an idealized distribution will generally not be achieved and instead a reasonable approximation is sought.
• the fus remedyen region of an airfoil is to be understood as meaning the end of the airfoil, with which the airfoil connects to the blade root, with which it is fastened in the rotor or in the stator.
• the head-side region of the airfoil corresponds to the end of the airfoil opposite the foot-side region.
• the head-side end corresponds to the hub-side end of the airfoil, that is to say to the end of the airfoil which, when installed, comes to lie against the hub of a turbomachine.
• the foot end of a vane blade is therefore also the housing-side end.
• the foot-side end is the radially inner, hub-side, end and the head-side end is the radially outer, housing-side, end.
• the described blade is characterized in particular by the fact that the blade has a foot-side chord length at the foot-end, a head-side chord length at the head end, and a chord length which is both smaller than the chord length and smaller than the chord length in a central region of the longitudinal extension the head-side chord length is.
• the airfoil has a maximum chord length, which in one
• the chord length in the middle region of the longitudinal extension at the position of the smallest chord length has values of less than 90%, in particular less than 85% or less than 82% of the maximum chord length.
• the chord length in the middle region of the longitudinal extent at the position of the smallest chord length has values of more than 70%, in particular more than 75% or more than 78% of the maximum chord length.
• the turbomachine blade described here as a turbomachine blade in particular as a turbomachine blade for a deckless blade row, is the foot-side Tendon length less than the head-side chord length; for example, the foot-chord length is less than 95 percent, and in training, more than 90 percent of the chord-side chord length.
• the foot-side chord length of a blade must be the same size or even larger than the head-side chord length must be selected; the latter occurs in particular on blades with shroud elements.
• the root chord length is chosen to be greater than the chord side chord length such that the chord length of the chord is the maximum chord length.
• the head chord length is selected to be less than 95% and / or greater than 90% of the chord side length.
• the airfoil is such that the outflow angle of the airfoil is substantially constant over the entire airfoil longitudinal extent. That is, at each position in the direction of the blade airfoil extension, the skeleton lines of the airfoil profile on the airfoil trailing edge run essentially parallel to one another; the deviations at the different positions in the blade airfoil extension amount to a maximum of 10 ° and in particular to a maximum of 6 ° and in another embodiment even to a maximum of 4 ° or 5 °.
• the profile curvature in one embodiment is greater than in the head-side or foot-side regions, since the aerodynamic load is greater due to the smaller chord length.
• the invention is suitable inter alia for the design of steam turbine blades.
• Turbomachinery blades of the type described above are, for example, suitable as rotor blades for arrangement in a row of blades of a rotor of a turbomachine. They are also suitable as guide vanes for arrangement in a guide vane row of a stator of a turbomachine.
• the invention also includes a turbomachine, in particular a steam turbine, which comprises a rotor with at least one blade row with blades of the type described above, and / or which comprises a stator with at least one row of vanes with blades of the type described above.
• Figure 1 is a schematic representation of a turbomachine
• Figure 2 shows a first example of a non-wound vane of the kind characterized in the claims
• Figure 3 shows a second example of a non-wound vane of the kind characterized in the claims
• FIG. 2 shows an exemplary vane 31.
• the vane includes a blade root 32, a blade platform 33, and an airfoil 34 disposed on the platform.
• the blade is shown without shroud; this is not a limitation.
• the invention can be realized in an analogous manner on a blade with a shroud element.
• the illustrated blade is characterized in that the chord length of the airfoil varies along the blade airfoil extension.
• the chord length s m in the central region of the blade is smaller than the chord length So in the region of the blade root and smaller than the chord length Si in the region of the blade tip 35.
• Airfoil profile 242 in the middle of the airfoil is shorter than the chordal length So of the profile 240 lying in the area of the blade root and the chord length Si of the profile 241 located on the blade tip. From a fluidic point of view, it would also be desirable here if the chord length So Blade foot would be smaller than the chord length Si in the region of the blade tip 25, as shown by way of example.
• the blade airfoil section in the region of the blade root must bear the centrifugal force load of the entire airfoil on one blade. This is accentuated even if a shroud element is arranged on the blade in the head region.

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• Engineering & Computer Science (AREA)
• Physics & Mathematics (AREA)
• Fluid Mechanics (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Turbine Rotor Nozzle Sealing (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)

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Cited By (8)

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Citations (9)

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• 2006
  • 2006-10-11 JP JP2008535014A patent/JP2009511811A/ja active Pending
  • 2006-10-11 WO PCT/EP2006/067250 patent/WO2007042522A1/de not_active Ceased
  • 2006-10-11 DE DE112006002658.5T patent/DE112006002658B4/de active Active
  • 2006-10-11 CN CN2006800464781A patent/CN101326342B/zh active Active
• 2008
  • 2008-04-08 US US12/078,965 patent/US8221065B2/en active Active
• 2012
  • 2012-07-26 JP JP2012166361A patent/JP5420729B2/ja active Active

Patent Citations (9)

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