EP1624192A1 - Aube de rouet pour compresseur axial - Google Patents

Aube de rouet pour compresseur axial Download PDF

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Publication number
EP1624192A1
EP1624192A1 EP04018728A EP04018728A EP1624192A1 EP 1624192 A1 EP1624192 A1 EP 1624192A1 EP 04018728 A EP04018728 A EP 04018728A EP 04018728 A EP04018728 A EP 04018728A EP 1624192 A1 EP1624192 A1 EP 1624192A1
Authority
EP
European Patent Office
Prior art keywords
compressor
blade
profile
side wall
sealing lip
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Withdrawn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
EP04018728A
Other languages
German (de)
English (en)
Inventor
Christian Dr. Cornelius
Bernhard Küsters
Stephan Mais
Andreas Peters
Achim Schirrmacher
Lutz Stephan
Bernd Van Den Toorn
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 EP04018728A priority Critical patent/EP1624192A1/fr
Priority to US11/659,551 priority patent/US8951008B2/en
Priority to CNB2005800336717A priority patent/CN100523519C/zh
Priority to PCT/EP2005/052848 priority patent/WO2006015899A1/fr
Priority to EP05767976A priority patent/EP1774179B1/fr
Priority to CA2575948A priority patent/CA2575948C/fr
Priority to JP2007524310A priority patent/JP4660547B2/ja
Priority to AT05767976T priority patent/ATE519036T1/de
Priority to MX2007001443A priority patent/MX2007001443A/es
Priority to ES05767976T priority patent/ES2370402T3/es
Priority to PL05767976T priority patent/PL1774179T3/pl
Priority to RU2007108295/06A priority patent/RU2343322C2/ru
Publication of EP1624192A1 publication Critical patent/EP1624192A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • 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
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
    • 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
    • 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
    • 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
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member
    • 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
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making

Definitions

  • the invention relates to a compressor blade for a compressor, which has along a main axis a blade root, a platform region and a subsequent blade profile with a profile tip, which blade profile of a convex suction side wall and the suction side wall opposite concave pressure side wall is formed, which surfaces, based on a flow medium, extending from a leading edge to a trailing edge and between which a profile centerline runs centrally, wherein at the profile tip a transverse to the main axis end face is arranged, on which a sealing lip extends at least partially from the leading edge to the trailing edge.
  • a compressor blade having such a blade profile is known.
  • the free end of the blade profile has an end face on which runs a lip-like rib in the region of the suction side of the blade profile from a leading edge to a trailing edge.
  • the rib of the compressor blade serves as a sealing element in the operation of the compressor to reduce the peak gap losses in the compressor which occur between the blade tip and the confinement of the compressor duct.
  • the object of the invention is therefore to provide a low-cost compressor blade, without reducing the sealing effect of the sealing lip. Moreover, it is an object of the invention to provide a compressor for this purpose.
  • the task related to the compressor blade is achieved by the features of claim 1 and the object directed to the compressor is solved by the features of claim 5.
  • the invention proposes that the sealing lip runs at a distance from the suction side wall and from the pressure side wall along the profile center line.
  • the position of the sealing lip on the profile tip is changed in such a way that error-prone and cost-intensive production steps are eliminated. Due to the newly selected position of the sealing lip their production can be carried out by means of a three-axis milling cutter. In addition, manual post-processing is no longer required.
  • the manufacturing process is shortened because the new sealing lip geometry can be made faster due to its simplicity. Furthermore, the omission of manual post-processing leads to a significantly higher process reliability.
  • the sealing lip has a suction-side side surface and a pressure-side side surface, which run parallel to the main axis, this can be made particularly simple and thus cost-effective.
  • the sealing lip reduces the tip gap losses across the profile tip.
  • the side surfaces of the sealing lip are connected to each other by means of a rubbing surface, which rubbing surface is perpendicular to the radius of the rotor of the compressor.
  • a cylindrical gap can be formed between the housing or hub components and the compressor blade, which reduces the gap losses.
  • the compressor blade according to the invention can be used in the same way advantageous as a blade as well as a vane.
  • the object directed to the compressor is achieved by the features of claim 5.
  • the solution suggests that the compressor is equipped with at least one compressor blade according to one of claims 1 to 4.
  • the advantages of the compressor correspond to the advantages of the compressor blade.
  • FIG. 1 shows a gas turbine 1 with a rotor 5 rotatably mounted about a rotation axis 3.
  • the gas turbine 1 has an intake chamber 7, a compressor 9, a toroidal annular combustion chamber 11 and a turbine unit 13.
  • Both in the compressor 9 and in the turbine unit 13 guide vanes 15 and blades 17 are each arranged in rings.
  • a blade ring 19 is followed by a blade ring 21.
  • the rotor blades 17 are fastened to the rotor 5 by means of rotor disks 23, whereas the stator blades 15 are fixedly mounted on the housing 25.
  • Wreaths 21 of guide vanes 15 are likewise arranged in the turbine unit 13, which, viewed in the direction of the flow medium, is followed by a ring of rotor blades 17.
  • the respective blade profiles of the guide vanes 15 and of the rotor blades 17 extend radially in an annular flow channel 27.
  • air 29 is sucked through the intake manifold 7 and compressed by the compressor.
  • the compressed air is guided to the burners 33, which are provided on a ring lying on the annular combustion chamber 11.
  • the compressed air 29 is mixed with a fuel 35, which mixture in the annular combustion chamber 11 is burned to a hot gas 37.
  • the hot gas 37 flows through the Flow channel 27 of the turbine unit 13 to guide vanes 15 and blades 17 over.
  • the hot gas 37 relaxes on the blades 17 of the turbine unit 13 to perform work.
  • the rotor 5 of the gas turbine 1 is set in a rotational movement, which serves to drive the compressor 9 and to drive a work machine, not shown.
  • the compressor blade 50 has a blade root 55, a platform region 27 with a platform 59 and a blade profile 61 along a main axis 53.
  • the blade profile 61 is flowed around during operation of the compressor 9 of air 29, which the blade profile 61 on a leading edge 63 on and flows from a trailing edge 65.
  • the blade profile 61 is formed by a pressure side wall 67 and a suction side wall 69.
  • a profile center line 71 which has at each point of its course a vertical, which perpendicular 74 both the suction side wall 69 and the pressure side wall 67 intersects.
  • a first distance A between the intersections of the vertical 74 with the profile center line 71 and the pressure side wall 67 with the vertical 74 is identical to a second distance B, which between the intersections of the profile center line 71 with the vertical 74 and the suction side wall 69 with the vertical 74, is present.
  • the blade profile 61 on its side facing away from the platform 59 profile tip 72 on an end face 73 on which a sealing lip 75 is arranged.
  • the sealing lip 75 is narrower than the blade profile 61, extending from the leading edge 63 to the trailing edge 65 and extends along the profile center line 71, ie at a distance between the contour of the suction side wall 69 and the pressure side wall 67th
  • the sealing lip 75 has a first side surface 77 facing the pressure side wall 67 and a second side surface 79 facing the suction side wall 69.
  • the curved side surfaces 77, 79 of the sealing lip 75 are parallel to the main axis 53 and also parallel to the profile center line 71, whereas the suction side wall 69 of the blade profile 61 and the pressure side wall 67 of the blade profile 61 inclined for aerodynamic reasons, i. obliquely, to the main axis 53 run. Compared with a blade of the prior art, a simplified production of the sealing lip 75 can thereby be achieved.
  • a rubbing surface 81 also called squealer edge, connected to each other, which abraded surface 81 is perpendicular to the radius of the rotor 5 of the compressor 9.
  • FIG. 3 shows a detailed view of a squealer according to the invention. It can be clearly seen that the sealing lip 75 runs centrally between the suction side wall 69 and the pressure side wall 67 from the leading edge 63 to the trailing edge 65 with side surfaces 77, 79 aligned parallel to the main axis 53 and the profile center line 71.
  • the new geometry and position of the sealing lip 75 eliminates error-prone and costly manufacturing steps. As a result, both the manufacturing costs and the reject rate of the manufactured compressor blades 50 can be reduced. A deterioration of the top gap losses across the radial gap between the compressor blade 50 and the inner housing does not occur, as well as flow losses due to the insignificantly reduced aerodynamically effective profile surface.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP04018728A 2004-08-06 2004-08-06 Aube de rouet pour compresseur axial Withdrawn EP1624192A1 (fr)

Priority Applications (12)

Application Number Priority Date Filing Date Title
EP04018728A EP1624192A1 (fr) 2004-08-06 2004-08-06 Aube de rouet pour compresseur axial
US11/659,551 US8951008B2 (en) 2004-08-06 2005-06-20 Compressor blade and production and use of a compressor blade
CNB2005800336717A CN100523519C (zh) 2004-08-06 2005-06-20 压气机叶片及压气机叶片的制造和应用
PCT/EP2005/052848 WO2006015899A1 (fr) 2004-08-06 2005-06-20 Aube de compresseur et fabrication et utilisation d'une aube de compresseur
EP05767976A EP1774179B1 (fr) 2004-08-06 2005-06-20 Aube de compresseur
CA2575948A CA2575948C (fr) 2004-08-06 2005-06-20 Aube de compresseur et fabrication et utilisation d'une aube de compresseur
JP2007524310A JP4660547B2 (ja) 2004-08-06 2005-06-20 圧縮機翼とその製造方法並びに圧縮機翼を備えた軸流ガスタービン
AT05767976T ATE519036T1 (de) 2004-08-06 2005-06-20 Verdichterschaufel
MX2007001443A MX2007001443A (es) 2004-08-06 2005-06-20 Alabe para comprensor asi como la produccion y uso en un alabe de compresor.
ES05767976T ES2370402T3 (es) 2004-08-06 2005-06-20 Pala de compresor.
PL05767976T PL1774179T3 (pl) 2004-08-06 2005-06-20 Łopatka sprężarki
RU2007108295/06A RU2343322C2 (ru) 2004-08-06 2005-06-20 Лопатка компрессора, а также способ изготовления и применение лопатки компрессора

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04018728A EP1624192A1 (fr) 2004-08-06 2004-08-06 Aube de rouet pour compresseur axial

Publications (1)

Publication Number Publication Date
EP1624192A1 true EP1624192A1 (fr) 2006-02-08

Family

ID=34926091

Family Applications (2)

Application Number Title Priority Date Filing Date
EP04018728A Withdrawn EP1624192A1 (fr) 2004-08-06 2004-08-06 Aube de rouet pour compresseur axial
EP05767976A Active EP1774179B1 (fr) 2004-08-06 2005-06-20 Aube de compresseur

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP05767976A Active EP1774179B1 (fr) 2004-08-06 2005-06-20 Aube de compresseur

Country Status (11)

Country Link
US (1) US8951008B2 (fr)
EP (2) EP1624192A1 (fr)
JP (1) JP4660547B2 (fr)
CN (1) CN100523519C (fr)
AT (1) ATE519036T1 (fr)
CA (1) CA2575948C (fr)
ES (1) ES2370402T3 (fr)
MX (1) MX2007001443A (fr)
PL (1) PL1774179T3 (fr)
RU (1) RU2343322C2 (fr)
WO (1) WO2006015899A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1930547A2 (fr) * 2006-11-24 2008-06-11 IHI Corporation Aube de compresseur d'une turbine à gaz
CN106271469A (zh) * 2016-08-29 2017-01-04 中航动力股份有限公司 一种细长空心多腔薄壁压气机叶片的加工方法
DE102021130682A1 (de) 2021-11-23 2023-05-25 MTU Aero Engines AG Schaufelblatt für eine Strömungsmaschine
EP2418389B1 (fr) * 2010-08-13 2023-07-05 Ziehl-Abegg Se Hélice pour un ventilateur

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GB0807358D0 (en) * 2008-04-23 2008-05-28 Rolls Royce Plc Fan blade
CN102536897B (zh) * 2010-12-29 2015-04-22 台达电子工业股份有限公司 风扇及其叶轮
FR2972380A1 (fr) 2011-03-11 2012-09-14 Alstom Technology Ltd Procede de fabrication d'un diaphragme de turbine a vapeur
US8790088B2 (en) * 2011-04-20 2014-07-29 General Electric Company Compressor having blade tip features
RU2476729C1 (ru) * 2011-07-29 2013-02-27 Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн") Рабочее колесо осевого компрессора газотурбинного двигателя
EP2798175A4 (fr) * 2011-12-29 2017-08-02 Rolls-Royce North American Technologies, Inc. Moteur à turbine à gaz et aube de turbine
JP5555727B2 (ja) 2012-01-23 2014-07-23 川崎重工業株式会社 軸流圧縮機翼の製造方法
EP2696031B1 (fr) 2012-08-09 2015-10-14 MTU Aero Engines AG Aube pour une turbomachine et turbomachine correspondante
CN103883361B (zh) * 2012-12-20 2016-05-04 中航商用航空发动机有限责任公司 涡轮叶片
CN103925244B (zh) * 2014-04-02 2017-03-15 清华大学 一种用于300mw f级重型燃气轮机的大流量高负荷轴流压气机
US20160238021A1 (en) * 2015-02-16 2016-08-18 United Technologies Corporation Compressor Airfoil
US10934847B2 (en) * 2016-04-14 2021-03-02 Mitsubishi Power, Ltd. Steam turbine rotor blade, steam turbine, and method for manufacturing steam turbine rotor blade
CN111219362A (zh) * 2018-11-27 2020-06-02 中国航发商用航空发动机有限责任公司 轴流压气机叶片、轴流压气机及燃气轮机
CN110076524B (zh) * 2019-04-30 2020-07-31 沈阳透平机械股份有限公司 一种轴流型压缩机静叶流道板的加工方法

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US5363554A (en) * 1991-06-05 1994-11-15 The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kingdom Of Great Britain And Northern Ireland Titanium compressor blade having a wear-resistant portion
GB2310897A (en) * 1993-10-15 1997-09-10 United Technologies Corp Reducing stress on the tips of turbine or compressor blades
US6039531A (en) * 1997-03-04 2000-03-21 Mitsubishi Heavy Industries, Ltd. Gas turbine blade
US6206642B1 (en) * 1998-12-17 2001-03-27 United Technologies Corporation Compressor blade for a gas turbine engine

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JP3137527B2 (ja) * 1994-04-21 2001-02-26 三菱重工業株式会社 ガスタービン動翼チップ冷却装置
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Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5363554A (en) * 1991-06-05 1994-11-15 The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kingdom Of Great Britain And Northern Ireland Titanium compressor blade having a wear-resistant portion
GB2310897A (en) * 1993-10-15 1997-09-10 United Technologies Corp Reducing stress on the tips of turbine or compressor blades
US6039531A (en) * 1997-03-04 2000-03-21 Mitsubishi Heavy Industries, Ltd. Gas turbine blade
US6206642B1 (en) * 1998-12-17 2001-03-27 United Technologies Corporation Compressor blade for a gas turbine engine

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1930547A2 (fr) * 2006-11-24 2008-06-11 IHI Corporation Aube de compresseur d'une turbine à gaz
EP1930547A3 (fr) * 2006-11-24 2010-03-10 IHI Corporation Aube de compresseur d'une turbine à gaz
US8366400B2 (en) 2006-11-24 2013-02-05 Ihi Corporation Compressor rotor
EP2418389B1 (fr) * 2010-08-13 2023-07-05 Ziehl-Abegg Se Hélice pour un ventilateur
CN106271469A (zh) * 2016-08-29 2017-01-04 中航动力股份有限公司 一种细长空心多腔薄壁压气机叶片的加工方法
DE102021130682A1 (de) 2021-11-23 2023-05-25 MTU Aero Engines AG Schaufelblatt für eine Strömungsmaschine
US11697995B2 (en) 2021-11-23 2023-07-11 MTU Aero Engines AG Airfoil for a turbomachine

Also Published As

Publication number Publication date
CA2575948C (fr) 2010-10-19
JP4660547B2 (ja) 2011-03-30
EP1774179A1 (fr) 2007-04-18
CA2575948A1 (fr) 2006-02-16
WO2006015899A1 (fr) 2006-02-16
MX2007001443A (es) 2007-04-19
EP1774179B1 (fr) 2011-08-03
CN101035988A (zh) 2007-09-12
US8951008B2 (en) 2015-02-10
RU2343322C2 (ru) 2009-01-10
CN100523519C (zh) 2009-08-05
ATE519036T1 (de) 2011-08-15
US20110044800A1 (en) 2011-02-24
PL1774179T3 (pl) 2011-12-30
JP2008509316A (ja) 2008-03-27
RU2007108295A (ru) 2008-09-20
ES2370402T3 (es) 2011-12-15

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