EP1582696A1 - Aube de compresseur et procédé de construction d'une telle aube - Google Patents

Aube de compresseur et procédé de construction d'une telle aube Download PDF

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Publication number
EP1582696A1
EP1582696A1 EP04007730A EP04007730A EP1582696A1 EP 1582696 A1 EP1582696 A1 EP 1582696A1 EP 04007730 A EP04007730 A EP 04007730A EP 04007730 A EP04007730 A EP 04007730A EP 1582696 A1 EP1582696 A1 EP 1582696A1
Authority
EP
European Patent Office
Prior art keywords
blade
platform
compressor
trailing edge
regions
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Withdrawn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
EP04007730A
Other languages
German (de)
English (en)
Inventor
Christian Dr. Cornelius
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 EP04007730A priority Critical patent/EP1582696A1/fr
Publication of EP1582696A1 publication Critical patent/EP1582696A1/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Withdrawn legal-status Critical Current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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F04D29/544—Blade shapes
    • 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
    • F05D2240/128—Nozzles
    • 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
    • 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
    • F05D2250/70—Shape
    • 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
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved

Definitions

  • the invention relates to a compressor blade according to the The preamble of claim 1, a compressor according to claim 8 and a method of constructing a compressor blade according to the preamble of claim 9.
  • the object of the present invention is to provide a compressor blade and to specify a compressor equipped therewith the particularly good properties in terms of efficiency exhibit.
  • Another object of the invention is the specification of a Method for constructing such a compressor blade.
  • the solution of the former task provides that at least over a part of the blade length in each case the suction side surfaces the platform-near sheet areas so opposite inclined to the adjacent platform surface, that they include a blunt suction side angle.
  • the invention is directed to the conventional stacking the profile cross sections on a straight line.
  • the threading line is modified in the platform-like leaf area in such a way that they are in the direction of the suction side and possibly in the direction of Blade trailing edge is curved.
  • the shape of the airfoil in platform-near leaf area modified so that aerodynamic favorable obtuse angles between the blade suction side and the platform surface arise.
  • the greater diversion will be the risk of lossy ones Detachment of the edge flow decreases, resulting in a significant Extension of the working range of the compressor leads.
  • a gas turbine when it has a compressor, which equipped with the compressor blades according to the invention.
  • a modified in this way compressor blade offers the advantage, especially in flow conditions with large Reynolds numbers and high turbulence levels, especially show low aerodynamic losses.
  • Reynolds number and degree of turbulence are correspondingly the definition in the book "Fluid Mechanics" by Heinz Schade and Ewald Kunz, Verlag Walter De Gruyter, Berlin and New York, 1989, pages 290 and 325, respectively.
  • the flow in the compressor has one from the blade leading edge rising to the blade trailing edge Pressure gradients on which the subsonic velocity the flow is delayed. Therefore, so far the danger of a lossy flow separation, especially in the platform-near Blade trailing edge edge area given is reduced by the design.
  • the blade trailing edge extends in the platform-near leaf areas farther downstream than in the middle leaf areas.
  • the blunt suction side angle between suction side surface and Platform surface can be reached very easily, when the airfoil is twisted in such a way, that the blade trailing edge in the platform near leaf areas towards the middle leaf areas in the direction the suction side is offset.
  • the pressure side surface the platform-near blade areas in the blade trailing edge area a greater curvature than the pressure side surface the middle or platform distant leaf areas. hereby is achieved that a greater deflection by the Airfoil in the edge regions, as e.g. in the radial inside area for blades or in the radially outer lying area for guide vanes is achieved becomes.
  • an angle in the region of the blade trailing edge the pressure side surface of the platform-near Leaf areas inclined to the adjacent platform surface, that they at least in some places an angle include, which is 90 ° or smaller.
  • the airfoil points from the platform surface up to a leaf tip on a leaf height.
  • the present invention is suitable both as a blade as well as trained for vane compressor blades.
  • FIG. 1 shows a section of a compressor with three compressor blades 1, in the compressor ring-shaped around the rotor the compressor (not shown) are arranged and which form a row of guide blades 3 of a compressor stage.
  • the compressor blades 1 are each with their blade root mounted radially on the outside of a guide vane carrier of the compressor (Not shown).
  • the compressor blade 1 has along a blade axis 21 successively the blade root, a platform 19 and a platform 19 transverse to it extending airfoil 7, which in a flow channel 9 of the compressor is arranged.
  • the blade 7 extends from a blade leading edge 11 in Flow direction of the working medium to a blade trailing edge 13.
  • the compressor blade 1 has a concave curved pressure side wall 14 with a pressure side surface 15th and one of the pressure side wall 14 opposite convex curved Suction side wall 16 with a suction side surface 17.
  • the platforms 19 of the compressor blades 1 limit the Flow channel 9 radially outside.
  • the blade axis 21 of the compressor blade 1 agrees with the Radial direction of the rotor of the compressor approximately match.
  • the blade 7 goes from one platform-near leaf area 23 via a middle Blade area 25 in a platform distant sheet area 27 continuously above.
  • a blade skeleton line 30 extends from the blade leading edge 11 to the blade trailing edge 13 transverse to the blade longitudinal axis 21 and runs centrally between the suction side surface 17 and print side surface 15.
  • the suction side angle ⁇ is enclosed by two legs 26a, 26b, both of them in an imaginary way to the vane skeleton line 30 lying perpendicular plane 29 lie.
  • the first Leg 26a is through the section line of the platform surface 33 with the level 29 and the second leg 26 b means a tangent to the suction side surface 17 in the platform Leaf area 23 defined.
  • the tangent of the platform surface 33 at a distance of 5% to 10% the sheet height applied to the suction side surface.
  • the pressure side surface 15 and the suction side surface 17 intersect with each perpendicular to the blade axis 21 Level in a profile cross section 31 of the airfoil 7th
  • the technique becomes the center of gravity of all profile cross sections 31 on a parallel to the blade axis 21st the compressor blade 1 stacked straight line, i. threaded.
  • the profile cross sections 31 change depending on the radial distance to the axis of rotation of the rotor, wherein a platform-proximate blade portion 23 is slightly modified Profile section 31 in comparison to the profile cross sections 31 of the middle and platform distant leaf areas 25, 27 is used.
  • FIG. 2 shows a detailed view of a compressor blade 1 in FIG platform-near leaf area 23 of FIG. 1 according to the state of the technique.
  • the blade trailing edge 13 extends in the middle Blade region 25 substantially parallel to the blade axis 21st and shifts in the platform-near leaf area 23 in the further Course in the direction of the pressure side surface 15, due the construction method described for Fig. 1.
  • the suction side surface 17 closes with the surface 33 the platform 19 of the compressor vane 1 according to the state the technique a sharp suction side angle ⁇ .
  • FIG. 3 A section of the compressor blade according to the invention 1 shows FIG. 3, wherein the compressor blade 1 as a guide vane or formed as a blade of a compressor can be.
  • Analogous to the compressor blade 1 of FIG. 2 are the illustrated parts in Fig. 3 denotes.
  • the compressor blade 1 according to the invention in Fig. 3 is an obtuse angle side angle ⁇ , since the According to the invention modified threading line 37 in the platform Leaf area 23 deviates from the straight line 32.
  • the profile cross sections 31 of the platform-near blade regions 23 are in Fig. 3 with respect to those in Fig. 2 in the direction of Suction side 17 shifted.
  • Fig. 4 shows three profile cross sections of an inventive Compressor blade 1, which by a in the direction of Blade axis 21 was carried out projection of the respective profile cross-section are superimposed.
  • the profile cross section 41 of the middle and the platform distant Leaf area 25, 27 is shown in a solid line.
  • the reference numeral 43 is the profile cross section of the platform Blade portion 23 of a compressor blade 1 according to of the prior art and the profile cross-section of the invention Compressor blade 1 of the platform-near blade area 23 is designated by the reference numeral 45.
  • the profile cross section 45 is opposite the profile cross section 43 shifted according to the arrows 47, as in the platform Leaf section 23, the threading line 37 to the suction side and is deflected to the blade trailing edge 17.
  • the platform-near profile cross-sections 45 at the blade trailing edge 13 more curved than the middle or platform distant Profile cross sections 43, 41.
  • the compressor is equipped with inventive Compressor blades 1 for use in a Gas turbine suitable.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP04007730A 2004-03-30 2004-03-30 Aube de compresseur et procédé de construction d'une telle aube Withdrawn EP1582696A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP04007730A EP1582696A1 (fr) 2004-03-30 2004-03-30 Aube de compresseur et procédé de construction d'une telle aube

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04007730A EP1582696A1 (fr) 2004-03-30 2004-03-30 Aube de compresseur et procédé de construction d'une telle aube

Publications (1)

Publication Number Publication Date
EP1582696A1 true EP1582696A1 (fr) 2005-10-05

Family

ID=34878212

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04007730A Withdrawn EP1582696A1 (fr) 2004-03-30 2004-03-30 Aube de compresseur et procédé de construction d'une telle aube

Country Status (1)

Country Link
EP (1) EP1582696A1 (fr)

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1168599B (de) * 1953-10-29 1964-04-23 United Aircraft Corp Axialverdichter
EP1098092A2 (fr) * 1999-11-05 2001-05-09 General Electric Company Aube statorique
EP1106836A2 (fr) * 1999-12-06 2001-06-13 General Electric Company Aube de compresseur à double courbure
US20030035723A1 (en) * 2001-08-17 2003-02-20 Decker John J. Compressor outlet guide vane and diffuser assembly

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1168599B (de) * 1953-10-29 1964-04-23 United Aircraft Corp Axialverdichter
EP1098092A2 (fr) * 1999-11-05 2001-05-09 General Electric Company Aube statorique
EP1106836A2 (fr) * 1999-12-06 2001-06-13 General Electric Company Aube de compresseur à double courbure
US20030035723A1 (en) * 2001-08-17 2003-02-20 Decker John J. Compressor outlet guide vane and diffuser assembly

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 1996, no. 08 30 August 1996 (1996-08-30) *

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