EP1927724A2 - Aube de turbomachine - Google Patents

Aube de turbomachine Download PDF

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Publication number
EP1927724A2
EP1927724A2 EP07120051A EP07120051A EP1927724A2 EP 1927724 A2 EP1927724 A2 EP 1927724A2 EP 07120051 A EP07120051 A EP 07120051A EP 07120051 A EP07120051 A EP 07120051A EP 1927724 A2 EP1927724 A2 EP 1927724A2
Authority
EP
European Patent Office
Prior art keywords
blade
skeleton line
skeleton
chord length
gap
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
EP07120051A
Other languages
German (de)
English (en)
Other versions
EP1927724B1 (fr
EP1927724A3 (fr
Inventor
Carsten Clemen
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 EP1927724A2 publication Critical patent/EP1927724A2/fr
Publication of EP1927724A3 publication Critical patent/EP1927724A3/fr
Application granted granted Critical
Publication of EP1927724B1 publication Critical patent/EP1927724B1/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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—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
    • F05D2250/74—Shape given by a set or table of xyz-coordinates
    • 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 invention relates to the airfoil design of the blades and vanes of a turbomachine, in particular a gas turbine engine, defined by the progression of the skeletal line defined by the skeletal line angle over the chord length and blade height, and the leading edge profile and the blade tip terminating at an air gap.
  • the blade of engine blades is composed under the aspect of a fluidically optimal shape design of a plurality of over the blade blade height threaded individual profiles into a three-dimensional blade shape, the individual profile sections are characterized by a particular skeleton line and a certain material thickness on both sides of the skeleton line.
  • the course of the skeleton line representing a center line in the respective profile section is designed for a minimum profile pressure loss and a maximum working range in the respective blade area.
  • the object of the invention is to design the airfoil profiles of rotor blades and guide vanes of a turbomachine in such a way that the flow disturbances which occur due to the flow disturbances occurring close to the gap, which lead to power losses, are minimized.
  • the gist of the invention is that in a gap-proximate region of up to 30% of the blade height starting from the blade tip, the blade profile cuts are characterized by a specific skeleton line profile defined by the skeleton line angle with respect to the chord length of the blade profile, at which in the vicinity of the gap a uniform pressure distribution along the blade section and thus a stable gap vortex is achieved.
  • the uniform load distribution in the near-gap blade area has lower gap losses, that is, an increase in the power and the stability limit or a reduction in the number of blades and thus the weight at a constant power and ultimately the cost.
  • the dimensionless skeleton line angles for the inventively optimal skeleton line profile for blade profile cuts that fall within the above-mentioned 30% range are in a certain skeletal line angle distribution range that is in one of the chord length (x-axis, in percent) and the dimensionless skeleton line angle ( y-axis) formed coordinate system is arranged, wherein the upper and the lower limit curve of the skeleton line angle distribution are determined by the equations given in claim 1.
  • the dimensionless skeleton line angle results from the relationship given in claim 2.
  • skeleton lines or the corresponding skeleton line angles in the blade profile sections close to the gap lie within the limits defined by the limit curves, the disturbances and losses caused by the gap are greatly reduced.
  • the formation of the skeleton lines according to the invention is not limited to certain leading edge profiles of the blades.
  • Fig. 1 shows a side view of an airfoil 1 with swept course of the leading edge 2 of a blade of the compressor of a gas turbine engine. A plurality of sectional planes distributed over the blade height "h" can be seen. According to the skeleton line 4 (FIG. Fig. 2 ) with in each reference point on both sides of the same material thickness "d" is defined by threading the corresponding blade profile sections 5 in the cutting planes 3, the shape of the airfoil 1.
  • Fig. 4 are - each with the corresponding schematic pressure load - two blade profile cuts 5 in the near-gap region facing each other, namely of a blade according to the prior art (zigzag line hatching) and of a blade according to the invention (slash-hatching).
  • the indicated pressure load is substantially uniform in the blade according to the invention and has the shape of a triangle in the blade according to the prior art, which leads to flow disturbances and losses.

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)
  • Turbine Rotor Nozzle Sealing (AREA)
EP07120051.3A 2006-11-23 2007-11-06 Profil d'aube Not-in-force EP1927724B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102006055869A DE102006055869A1 (de) 2006-11-23 2006-11-23 Schaufelblattdesign für die Lauf- und Leitschaufeln einer Turbomaschine

Publications (3)

Publication Number Publication Date
EP1927724A2 true EP1927724A2 (fr) 2008-06-04
EP1927724A3 EP1927724A3 (fr) 2009-05-20
EP1927724B1 EP1927724B1 (fr) 2015-09-09

Family

ID=38904754

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07120051.3A Not-in-force EP1927724B1 (fr) 2006-11-23 2007-11-06 Profil d'aube

Country Status (3)

Country Link
US (1) US8152473B2 (fr)
EP (1) EP1927724B1 (fr)
DE (1) DE102006055869A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013178914A1 (fr) * 2012-05-31 2013-12-05 Snecma Aube de soufflante pour turboreacteur d'avion a profil cambre en sections de pied
EP2275643A3 (fr) * 2009-07-17 2017-10-04 Rolls-Royce Deutschland Ltd & Co KG Aube de moteur dotée d'une charge de rebords avant surélevée
EP2921648B1 (fr) 2014-03-20 2018-12-26 Ansaldo Energia Switzerland AG Aube de turbine à gaz avec bord d'attaque et bord de fuite courbé
EP3730801A4 (fr) * 2017-12-20 2021-05-05 Ihi Corporation Ventilateur et aube de stator de compresseur
EP3839212A1 (fr) * 2019-12-20 2021-06-23 MTU Aero Engines AG Aube pour une turbomachine

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US8523531B2 (en) * 2009-12-23 2013-09-03 Alstom Technology Ltd Airfoil for a compressor blade
US9291059B2 (en) * 2009-12-23 2016-03-22 Alstom Technology Ltd. Airfoil for a compressor blade
DE102010009615B4 (de) 2010-02-27 2016-11-17 MTU Aero Engines AG Schaufelblatt mit gefädelten Profilschnitten
DE102010027588A1 (de) * 2010-07-19 2012-01-19 Rolls-Royce Deutschland Ltd & Co Kg Fan-Nachleitradschaufel eines Turbofantriebwerks
CN102373971B (zh) * 2010-08-11 2014-06-04 中国科学院工程热物理研究所 轴流透平与单侧径向排汽/气系统一体化气动设计方法
DE102014200644B4 (de) * 2014-01-16 2017-03-02 MTU Aero Engines AG Strangprofil und Verfahren zur Herstellung einer Schaufel eines Nachleitrads, Schaufel eines Nachleitrads, Nachleitrad und Turbomaschine mit solch einem Nachleitrad
WO2015175043A2 (fr) 2014-02-19 2015-11-19 United Technologies Corporation Profil aérodynamique de moteur à turbine à gaz
EP3108101B1 (fr) 2014-02-19 2022-04-20 Raytheon Technologies Corporation Profil aérodynamique de moteur à turbine à gaz
WO2015175052A2 (fr) 2014-02-19 2015-11-19 United Technologies Corporation Profil aérodynamique de turbine à gaz
WO2015126941A1 (fr) 2014-02-19 2015-08-27 United Technologies Corporation Profil aérodynamique de moteur à turbine à gaz
WO2015175044A2 (fr) * 2014-02-19 2015-11-19 United Technologies Corporation Profil aérodynamique de moteur à turbine à gaz
US10570915B2 (en) 2014-02-19 2020-02-25 United Technologies Corporation Gas turbine engine airfoil
EP3108120B1 (fr) 2014-02-19 2021-03-31 Raytheon Technologies Corporation Moteur à turbine à gaz ayant une architecture à engrenages et une structure à aube fixe spécifique
EP3575551B1 (fr) 2014-02-19 2021-10-27 Raytheon Technologies Corporation Surface portante de moteur à turbine à gaz
EP3108105B1 (fr) 2014-02-19 2021-05-12 Raytheon Technologies Corporation Surface portante pour turbine à gaz
US9567858B2 (en) 2014-02-19 2017-02-14 United Technologies Corporation Gas turbine engine airfoil
EP3108123B1 (fr) 2014-02-19 2023-10-04 Raytheon Technologies Corporation Moteur à double flux à engrenage avec aubes de compresseur basse pression
US10570916B2 (en) 2014-02-19 2020-02-25 United Technologies Corporation Gas turbine engine airfoil
WO2015175073A2 (fr) 2014-02-19 2015-11-19 United Technologies Corporation Surface portante de moteur à turbine à gaz
US10465702B2 (en) 2014-02-19 2019-11-05 United Technologies Corporation Gas turbine engine airfoil
EP3108103B1 (fr) 2014-02-19 2023-09-27 Raytheon Technologies Corporation Aube de soufflante pour moteur à turbine à gaz
US9140127B2 (en) 2014-02-19 2015-09-22 United Technologies Corporation Gas turbine engine airfoil
WO2015126454A1 (fr) 2014-02-19 2015-08-27 United Technologies Corporation Surface portante de moteur à turbine à gaz
US10495106B2 (en) 2014-02-19 2019-12-03 United Technologies Corporation Gas turbine engine airfoil
US10584715B2 (en) 2014-02-19 2020-03-10 United Technologies Corporation Gas turbine engine airfoil
EP3108106B1 (fr) 2014-02-19 2022-05-04 Raytheon Technologies Corporation Pale de moteur à turbine à gaz
EP3108100B1 (fr) 2014-02-19 2021-04-14 Raytheon Technologies Corporation Pale de soufflante de moteur à turbine à gaz
EP3985226B1 (fr) 2014-02-19 2024-12-25 RTX Corporation Profil d'aube pour moteur à turbine à gaz
CN105221193B (zh) * 2014-06-12 2017-01-25 中国科学院工程热物理研究所 一种轴流透平与单侧径向排汽/气系统设计方法
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
JP6421091B2 (ja) * 2015-07-30 2018-11-07 三菱日立パワーシステムズ株式会社 軸流圧縮機、それを備えたガスタービン、及び軸流圧縮機の静翼
DE102016115868A1 (de) * 2016-08-26 2018-03-01 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit hohem Ausnutzungsgrad
EP3633207A4 (fr) * 2017-05-24 2021-06-23 IHI Corporation Pale pour ventilateur et compresseur
US10760587B2 (en) 2017-06-06 2020-09-01 Elliott Company Extended sculpted twisted return channel vane arrangement
CN114867944B (zh) 2019-12-09 2024-01-26 Lg电子株式会社 送风机
US11286779B2 (en) * 2020-06-03 2022-03-29 Honeywell International Inc. Characteristic distribution for rotor blade of booster rotor
CN112855284B (zh) * 2021-01-18 2022-11-08 西北工业大学 一种低压涡轮静子叶片波浪前缘的构造方法
CN114973902B (zh) * 2022-04-14 2023-06-23 西北工业大学 一种教学用航空发动机低压涡轮模型及装配方法
CN115288907A (zh) * 2022-08-18 2022-11-04 南通河海大学海洋与近海工程研究院 一种低转速环境友好型轴流式水轮机
GB202216273D0 (en) * 2022-11-02 2022-12-14 Rolls Royce Plc Fan blade for a gas turbine engine
US12366176B2 (en) 2023-08-28 2025-07-22 General Electric Company Rotor system for a turbine engine
BE1032189B1 (fr) 2023-12-01 2025-06-30 Safran Aero Boosters Aube pour compresseur de turbomachine d'aeronef, compresseur, turbomachine
US12509988B2 (en) 2024-06-14 2025-12-30 Pratt & Whitney Canada Corp. Turbine engine airfoil

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Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2275643A3 (fr) * 2009-07-17 2017-10-04 Rolls-Royce Deutschland Ltd & Co KG Aube de moteur dotée d'une charge de rebords avant surélevée
WO2013178914A1 (fr) * 2012-05-31 2013-12-05 Snecma Aube de soufflante pour turboreacteur d'avion a profil cambre en sections de pied
FR2991373A1 (fr) * 2012-05-31 2013-12-06 Snecma Aube de soufflante pour turboreacteur d'avion a profil cambre en sections de pied
US11333164B2 (en) 2012-05-31 2022-05-17 Safran Aircraft Engines Airplane turbojet fan blade of cambered profile in its root sections
EP2921648B1 (fr) 2014-03-20 2018-12-26 Ansaldo Energia Switzerland AG Aube de turbine à gaz avec bord d'attaque et bord de fuite courbé
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
EP3839212A1 (fr) * 2019-12-20 2021-06-23 MTU Aero Engines AG Aube pour une turbomachine
WO2021121458A1 (fr) * 2019-12-20 2021-06-24 MTU Aero Engines AG Aube directrice destinée à une turbomachine
US12180855B2 (en) 2019-12-20 2024-12-31 MTU Aero Engines AG Rotor blade for a turbomachine

Also Published As

Publication number Publication date
US20090226322A1 (en) 2009-09-10
US8152473B2 (en) 2012-04-10
EP1927724B1 (fr) 2015-09-09
DE102006055869A1 (de) 2008-05-29
EP1927724A3 (fr) 2009-05-20

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