EP2275643A2 - Aube de moteur dotée d'une charge de rebords avant surélevée - Google Patents

Aube de moteur dotée d'une charge de rebords avant surélevée Download PDF

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Publication number
EP2275643A2
EP2275643A2 EP10005471A EP10005471A EP2275643A2 EP 2275643 A2 EP2275643 A2 EP 2275643A2 EP 10005471 A EP10005471 A EP 10005471A EP 10005471 A EP10005471 A EP 10005471A EP 2275643 A2 EP2275643 A2 EP 2275643A2
Authority
EP
European Patent Office
Prior art keywords
blade
skeleton line
curvature
run length
skeleton
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.)
Granted
Application number
EP10005471A
Other languages
German (de)
English (en)
Other versions
EP2275643B1 (fr
EP2275643A3 (fr
Inventor
Volker Dr. Gümmer
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP2275643A2 publication Critical patent/EP2275643A2/fr
Publication of EP2275643A3 publication Critical patent/EP2275643A3/fr
Application granted granted Critical
Publication of EP2275643B1 publication Critical patent/EP2275643B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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
    • 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

Definitions

  • the invention relates to an engine blade with excessive leading edge load.
  • the invention relates to at least one blade of a fluid flow machine.
  • the blading in question is provided within a main flow path, bounded on the outside by a housing and internally bounded by a hub.
  • a rotor comprises a plurality of rotor blades attached to a rotating shaft and emits energy to the working fluid
  • a stator consists of a plurality of fixed, mostly in the housing mounted stator blades.
  • the invention relates to a rotor with a fixed connection to a rotating hub and a free blade end with a gap on the housing.
  • the invention relates to a stator which has a fixed connection to the edge on the housing side and has a free blade end with a gap to the hub on the hub side.
  • the present invention relates to blades of fluid flow machines such as fans, compressors, pumps and fans in the axial, semi-axial or even radial design.
  • the working medium can be gaseous or liquid.
  • the Fig. 1 1 shows, on the left side, a schematic representation of two blade configurations according to the prior art in the meridian plane formed by the radial direction r and the axial direction x. It is a rotor blade row 4 with a gap on the housing 1 (top), wherein the housing 1 is or in special cases also rotates and the blade row rotates about the machine axis 3. It is also a row of stator blades 5 with a gap on the hub 2 (bottom), wherein the hub 2 rotates about the machine axis 3 or, in special cases, also rests and the row of blades 5 stands.
  • the blade profile cut directly on the running gap of a rotor 4 or stator 5 is designed such that the profile load and thus the profile curvature in the region of the leading edge does not exceed a certain level, because conventional design rules based on considerations of the nature of two-dimensional flows around profiles recommend this.
  • the right side of the Fig. 1 shows different, the prior art corresponding distributions of the skeleton line curvature in the profile section directly on the running gap, shown as a relative curvature ⁇ * over the related run length s * (for definitions see Fig. 3 ).
  • This category includes the so-called CDA (controlled diffusion aerofoils) US 4431376 A , From an aerodynamic point of view, the CDA aims for a moderate profile frontload.
  • CDA controlled diffusion aerofoils
  • the present invention has for its object to provide a rotor or stator blade of the type mentioned, which while avoiding the disadvantages of In the prior art, a very effective influencing of the edge flow is achieved by an excessive skeleton curve curvature in the region of the front edge of the blade profile cuts located near the running gap.
  • the invention can also be represented as follows:
  • the Fig.2 gives a precise definition of the meridional flow lines and the streamline profile sections.
  • the mean meridional flow line 7 is formed by the geometric center of an annular channel 6. If one establishes a normal at each location of the middle streamline 7, one obtains the course of the ring channel width W along the flow path and, on the other hand, a number of normals with whose help further meridional flow lines result with the same relative subdivision in the direction of the channel height.
  • the intersection of a meridional streamline with a blade results in a streamline profile intersection.
  • the respective skeleton line type for a streamline profile intersection is defined in relative representation by means of the relative curvature ⁇ * and the related run length s *, see Figure 3 , The figure shows a streamline profile section of the blade on a meridian flow surface (um plane).
  • the inclination angle ⁇ P and the run length s P covered up to this point are determined in all points of the skeleton line.
  • the Fig. 4a shows a family of inventive crevices near the profile skeleton curves. They are characterized in that the relative skeleton curve curvature ⁇ * always has values greater than or equal to 0.35 for related run lengths of s *> 0.1.
  • Fig. 4a The distribution shown shows the special case according to the invention of a change of the skeleton curve curvature sign.
  • the skeleton line is convexly curved towards the profile suction side in a part of the run length s * and concave in a lower part of the run length s *, as is the case if values of ⁇ *> 1 at least in part of the run length s * are provided.
  • the excessive leakage of the profile leading edge region in the vicinity of the running gap influences the leakage flows occurring at the running gap.
  • values of the relative skeleton curve curvature ⁇ * of greater than or equal to 0.35 or even greater than 0.5 or in special cases greater than or equal to 0.65 or in extreme cases greater than 1.0 already at a relative run length of s * 0.1.
  • a curvature distribution ⁇ * f (s *), the high gradient at the starting point A, starting in the further course of the point B approaches with decreasing gradient.
  • the Fig. 4b shows an also according to the invention Schar of Skelettlinienwölbungsveranderen, which is also suitable for aerodynamically highly loaded profiles.
  • an S-shaped skeleton line curvature distribution results according to the invention, corresponding to FIG Fig. 4b shown crowd.
  • the value ⁇ * C provided at s * 0.9 and thus the position of the point C is restricted.
  • particularly favorable solutions result if ⁇ * C ⁇ * B + 0.75 (1- ⁇ * B ).
  • the skeleton line curvature distribution according to the invention is to be provided in at least one vane stream section in the region between the gap and a vane section at 30% of the main flow path width (0.3 W).
  • Particularly favorable is a providence of the skeleton line curvature distribution according to the invention at least directly at the gap and at least further 5% of the main flow path width W adjoining the gap.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP10005471.7A 2009-07-17 2010-05-26 Aube de moteur dotée d'une charge de rebords avant surélevée Not-in-force EP2275643B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102009033593A DE102009033593A1 (de) 2009-07-17 2009-07-17 Triebwerkschaufel mit überhöhter Vorderkantenbelastung

Publications (3)

Publication Number Publication Date
EP2275643A2 true EP2275643A2 (fr) 2011-01-19
EP2275643A3 EP2275643A3 (fr) 2017-10-04
EP2275643B1 EP2275643B1 (fr) 2018-12-26

Family

ID=42278932

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10005471.7A Not-in-force EP2275643B1 (fr) 2009-07-17 2010-05-26 Aube de moteur dotée d'une charge de rebords avant surélevée

Country Status (3)

Country Link
US (1) US8439646B2 (fr)
EP (1) EP2275643B1 (fr)
DE (1) DE102009033593A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10876412B2 (en) 2017-11-24 2020-12-29 Rolls-Royce Plc Gas turbine engine
US10954798B2 (en) 2017-11-24 2021-03-23 Rolls Royce Plc Gas turbine engine with optimized fan blade geometry
EP3730801A4 (fr) * 2017-12-20 2021-05-05 Ihi Corporation Ventilateur et aube de stator de compresseur

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102113900B (zh) 2010-01-05 2015-07-15 深圳迈瑞生物医疗电子股份有限公司 彩色血流动态帧相关方法和装置
DE102014203605A1 (de) 2014-02-27 2015-08-27 Rolls-Royce Deutschland Ltd & Co Kg Schaufelreihengruppe
JP6468414B2 (ja) * 2014-08-12 2019-02-13 株式会社Ihi 圧縮機静翼、軸流圧縮機、及びガスタービン
US9797267B2 (en) * 2014-12-19 2017-10-24 Siemens Energy, Inc. Turbine airfoil with optimized airfoil element angles
DE102016115868A1 (de) * 2016-08-26 2018-03-01 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit hohem Ausnutzungsgrad
CN109058161B (zh) * 2018-09-27 2023-08-29 美的集团股份有限公司 轴流风轮及空调室外机
IT202000005146A1 (it) * 2020-03-11 2021-09-11 Ge Avio Srl Motore a turbina con profilo aerodinamico avente alta accelerazione e bassa curva di paletta
US12071889B2 (en) 2022-04-05 2024-08-27 General Electric Company Counter-rotating turbine

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4431376A (en) 1980-10-27 1984-02-14 United Technologies Corporation Airfoil shape for arrays of airfoils

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4961686A (en) * 1989-02-17 1990-10-09 General Electric Company F.O.D.-resistant blade
US5167489A (en) * 1991-04-15 1992-12-01 General Electric Company Forward swept rotor blade
US5525038A (en) * 1994-11-04 1996-06-11 United Technologies Corporation Rotor airfoils to control tip leakage flows
FR2797658B1 (fr) * 1999-08-18 2002-08-23 Snecma Aube de turbine a profil ameliore
US7204676B2 (en) * 2004-05-14 2007-04-17 Pratt & Whitney Canada Corp. Fan blade curvature distribution for high core pressure ratio fan
DE102005042115A1 (de) * 2005-09-05 2007-03-08 Rolls-Royce Deutschland Ltd & Co Kg Schaufel einer Strömungsarbeitsmaschine mit blockweise definierter Profilskelettlinie
DE102006055869A1 (de) * 2006-11-23 2008-05-29 Rolls-Royce Deutschland Ltd & Co Kg Schaufelblattdesign für die Lauf- und Leitschaufeln einer Turbomaschine

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4431376A (en) 1980-10-27 1984-02-14 United Technologies Corporation Airfoil shape for arrays of airfoils

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10876412B2 (en) 2017-11-24 2020-12-29 Rolls-Royce Plc Gas turbine engine
US10954798B2 (en) 2017-11-24 2021-03-23 Rolls Royce Plc Gas turbine engine with optimized fan blade geometry
US11346229B2 (en) 2017-11-24 2022-05-31 Rolls-Royce Plc Gas turbine engine with optimized fan blade geometry
EP3730801A4 (fr) * 2017-12-20 2021-05-05 Ihi Corporation Ventilateur et aube de stator de compresseur
US11203945B2 (en) 2017-12-20 2021-12-21 Ihi Corporation Stator vane of fan or compressor

Also Published As

Publication number Publication date
EP2275643B1 (fr) 2018-12-26
EP2275643A3 (fr) 2017-10-04
US8439646B2 (en) 2013-05-14
US20110014057A1 (en) 2011-01-20
DE102009033593A1 (de) 2011-01-20

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