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EP1582695A1 - Aube de turbomachine - Google Patents

Aube de turbomachine Download PDF

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Publication number
EP1582695A1
EP1582695A1 EP04007439A EP04007439A EP1582695A1 EP 1582695 A1 EP1582695 A1 EP 1582695A1 EP 04007439 A EP04007439 A EP 04007439A EP 04007439 A EP04007439 A EP 04007439A EP 1582695 A1 EP1582695 A1 EP 1582695A1
Authority
EP
European Patent Office
Prior art keywords
blade
profile
flow channel
height
steam turbine
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Withdrawn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
EP04007439A
Other languages
German (de)
English (en)
Inventor
Manuchehr Dr. Parvizinia
Heinrich Dr. Stüer
Frank Truckenmüller
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to EP04007439A priority Critical patent/EP1582695A1/fr
Publication of EP1582695A1 publication Critical patent/EP1582695A1/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Withdrawn legal-status Critical Current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
    • 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

Definitions

  • the present invention relates to a blade for a Turbomachine, in the flow channel, the blade by means of a fastening area provided at one of its ends is fixed. Furthermore, the invention relates to a gas turbine with a blade according to the invention.
  • the blading of a turbomachine serves to interact with a flowing through the turbomachine Fluid flow to either withdraw energy from the fluid and in a mechanical energy, in particular a rotational movement the rotor shaft of the turbomachine to transform or around the Fluid to supply mechanical energy.
  • a flowing through the turbomachine Fluid flow to either withdraw energy from the fluid and in a mechanical energy, in particular a rotational movement the rotor shaft of the turbomachine to transform or around the Fluid to supply mechanical energy.
  • To the efficiency To increase such machines are getting higher and higher physical Requirements for the materials used in the turbomachine posed. So is currently the example Temperature of a gas flow flowing into a gas turbine at about 1200 ° C. For a good efficiency are in the Usually several arranged axially one after the other in the flow direction Paddle wheels provided, which form the blading.
  • the flow channel of the turbomachine in the axial direction of the changing physical Conditions adapted to the fluid flow so that its cross-section varies over the axial length.
  • the blading is provided so that the axial spaced paddle wheels according to the respective requirements are different from each other. For example, this increases in a steam turbine, the cross-sectional area of the Flow channel in the flow direction, including the blade heights increase the axially spaced paddle wheels.
  • the blade height should be the cross-sectional area largely overflow the flow channel can.
  • the blades have a profile with a predetermined chord length. From design technical As a rule, the chord length is usually constant over the Blade height. One reason is that requirements due to the Strength and frequency tuning must be met. With the commonly selected chord length, the optimal Division ratio can not be achieved. Due to the circular symmetric Construction of the flow channel leads to this Furthermore, to a non-constant division ratio, which by the ratio of the circumference to the product of the number of blades and chord length is given above the blade height.
  • the invention is therefore based on the object, a develop generic blade such that the chord length increases in the upper part of the blade.
  • a generic blade proposed that at least one Area one with increasing distance from the mounting area having increasing chord length.
  • the Profile of the blade at least partially an enlarged Curvature has. This can be achieved that the Blade resistance to bending and vibration excitation can be improved.
  • the profile fluidically at least partially curved backwards. This is particularly advantageous when in the field, in the profile is curved backwards, the flow at supersonic speed flows along the blade along. losses can be further reduced. In addition, a can predeterminable resistance moment in the two main axis directions be achieved.
  • the thickness of the profile the bucket is reduced.
  • the diameter of the maximum in one to the wall of the flow channel essentially parallel section of the profile inscribed circle can be understood. This can be up simple way not only affects a natural frequency of the blade But it can also be a mass-optimized Shovel geometry can be achieved.
  • the blade mass and profile shape over the height of the Shovel provided such that a centrifugal force is largely constant over the height of the blade. In order to make good use of the blade material, the centrifugal force tension should selected in the range of the maximum permissible voltage become.
  • a blade mass distribution is optimized. hereby a further increase in chord length can be achieved.
  • a steam turbine or gas turbine rotatable with one in a flow channel of a housing mounted rotor shaft, rotatably arranged in the flow channel Vanes and blades fixed to a rotor shaft proposed, wherein the gas turbine or steam turbine having a blade according to the invention.
  • the efficiency of the gas or steam turbine can be increased. Operating costs can be reduced.
  • the blade in the low-pressure region of the turbine in particular arranged on the last in the direction of flow Paddle wheel of the rotor shaft.
  • FIG. 1 shows a steam turbine 2 with a housing 3 rotatably mounted rotor shaft 4. On an inner wall of the housing 3, vanes 10 are attached. On the rotor shaft 4 are blades 11 attached. The blades 10, 11 protrude in the flow channel 5 of the steam turbine. 2
  • Fig. 1 of the steam turbine 2 In the right section of Fig. 1 of the steam turbine 2 is located the low pressure part, in the appropriate low pressure blades are mounted. Such a blade of the state of Technique is shown enlarged in Fig. 2.
  • the shovel has in the lower part up to a height 8 of about 60% of Total height on a curved surface 6. In this area takes a chord length 7 of the blade in the upper part of about 60% of the height up to 100% of the amount. About it changes the tendon length only slightly or not at all and the curvature of the surface 6 decreases.
  • Fig. 3 shows a diagram in which on the abscissa 14 the Relative blade height 8% is plotted, whereas on the ordinate 15 the division ratio is indicated.
  • the graph 13 shows the Connection for the low-pressure blade shown in FIG. 2. It can be clearly seen that from a bucket height 8 from about 60% to the maximum height 100% the division ratio the blade in Fig. 1 with increasing height 8 increasingly clear deviates from the optimal division ratio. Result from this the disadvantages mentioned in particular with respect the efficiency.
  • a blade 1 according to the invention is in a perspective view shown in Fig. 4.
  • the blade according to the invention 1 has a slightly increased chord length with increasing Distance from the blade root 16.
  • a scoop of the It is also apparent from the prior art from FIG. 4 that the profile of the blade 1 has an increased curvature.
  • the profile 6 formed fluidically curved backward.
  • the Thickness of the profile 6 of the blade 1 is reduced compared that of a scoop of the prior art.
  • this blade 1 has an optimized blade mass distribution on, so that the centrifugal force tension over the height course the blade within the material is largely constant is.
  • the embodiment shown in the figures is used merely the explanation of the invention and is for this not restrictive. So in particular the type and extent the curvature of the fluidic requirements adapted be, for example, a backward curved blade in the area of a supersonic flow or the like. Also the invention is not limited to steam turbines but of course also in gas turbines, Compressors or the like are used.

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP04007439A 2004-03-26 2004-03-26 Aube de turbomachine Withdrawn EP1582695A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP04007439A EP1582695A1 (fr) 2004-03-26 2004-03-26 Aube de turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04007439A EP1582695A1 (fr) 2004-03-26 2004-03-26 Aube de turbomachine

Publications (1)

Publication Number Publication Date
EP1582695A1 true EP1582695A1 (fr) 2005-10-05

Family

ID=34878182

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04007439A Withdrawn EP1582695A1 (fr) 2004-03-26 2004-03-26 Aube de turbomachine

Country Status (1)

Country Link
EP (1) EP1582695A1 (fr)

Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3108102A4 (fr) * 2014-02-19 2017-02-22 United Technologies Corporation Profil aérodynamique de moteur à turbine à gaz
US9752439B2 (en) 2014-02-19 2017-09-05 United Technologies Corporation Gas turbine engine airfoil
US9777580B2 (en) 2014-02-19 2017-10-03 United Technologies Corporation Gas turbine engine airfoil
US10036257B2 (en) 2014-02-19 2018-07-31 United Technologies Corporation Gas turbine engine airfoil
US10184483B2 (en) 2014-02-19 2019-01-22 United Technologies Corporation Gas turbine engine airfoil
US10309414B2 (en) 2014-02-19 2019-06-04 United Technologies Corporation Gas turbine engine airfoil
US10352331B2 (en) 2014-02-19 2019-07-16 United Technologies Corporation Gas turbine engine airfoil
US10358925B2 (en) 2014-02-19 2019-07-23 United Technologies Corporation Gas turbine engine airfoil
US10370974B2 (en) 2014-02-19 2019-08-06 United Technologies Corporation Gas turbine engine airfoil
US10385866B2 (en) 2014-02-19 2019-08-20 United Technologies Corporation Gas turbine engine airfoil
US10393139B2 (en) 2014-02-19 2019-08-27 United Technologies Corporation Gas turbine engine airfoil
US10422226B2 (en) 2014-02-19 2019-09-24 United Technologies Corporation Gas turbine engine airfoil
US10465702B2 (en) 2014-02-19 2019-11-05 United Technologies Corporation Gas turbine engine airfoil
US10495106B2 (en) 2014-02-19 2019-12-03 United Technologies Corporation Gas turbine engine airfoil
US10502229B2 (en) 2014-02-19 2019-12-10 United Technologies Corporation Gas turbine engine airfoil
US10519971B2 (en) 2014-02-19 2019-12-31 United Technologies Corporation Gas turbine engine airfoil
US10550852B2 (en) 2014-02-19 2020-02-04 United Technologies Corporation Gas turbine engine airfoil
US10557477B2 (en) 2014-02-19 2020-02-11 United Technologies Corporation Gas turbine engine airfoil
US10570916B2 (en) 2014-02-19 2020-02-25 United Technologies Corporation Gas turbine engine airfoil
US10570915B2 (en) 2014-02-19 2020-02-25 United Technologies Corporation Gas turbine engine airfoil
US10584715B2 (en) 2014-02-19 2020-03-10 United Technologies Corporation Gas turbine engine airfoil
US10590775B2 (en) 2014-02-19 2020-03-17 United Technologies Corporation Gas turbine engine airfoil
US10605259B2 (en) 2014-02-19 2020-03-31 United Technologies Corporation Gas turbine engine airfoil
US12270315B2 (en) 2019-07-19 2025-04-08 MTU Aero Engines AG Rotor blade for a turbomachine, associated turbine module, and use thereof

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1536561A (fr) * 1967-08-22 1968-08-16 Gen Electric Ailettes pour compresseur à écoulement axial
FR2053049A1 (fr) * 1969-07-21 1971-04-16 Rolls Royce
CH533466A (de) * 1970-04-02 1973-02-15 Mo Energeticheskij Institut Turboseparator zur Trennung von mehrphasigen Medien und Verwendung des Turboseparators in einer Turbine
US4741667A (en) * 1986-05-28 1988-05-03 United Technologies Corporation Stator vane
US5480285A (en) * 1993-08-23 1996-01-02 Westinghouse Electric Corporation Steam turbine blade
JPH0932501A (ja) * 1995-07-17 1997-02-04 Ishikawajima Harima Heavy Ind Co Ltd 軸流圧縮機動翼
JPH10331791A (ja) * 1997-05-30 1998-12-15 Toshiba Corp 軸流圧縮機用翼およびその翼を適用する軸流圧縮機
EP0957236A1 (fr) * 1998-05-15 1999-11-17 Asea Brown Boveri AG Aubes mobiles pour turbine
EP1111188A2 (fr) * 1999-12-21 2001-06-27 General Electric Company Aube inclinée avec arête amont bombée
EP1225303A2 (fr) * 2001-01-12 2002-07-24 Mitsubishi Heavy Industries, Ltd. Aubes pour turbines à gaz
EP1277966A2 (fr) * 2001-07-18 2003-01-22 General Electric Company Pale dentelée

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1536561A (fr) * 1967-08-22 1968-08-16 Gen Electric Ailettes pour compresseur à écoulement axial
FR2053049A1 (fr) * 1969-07-21 1971-04-16 Rolls Royce
CH533466A (de) * 1970-04-02 1973-02-15 Mo Energeticheskij Institut Turboseparator zur Trennung von mehrphasigen Medien und Verwendung des Turboseparators in einer Turbine
US4741667A (en) * 1986-05-28 1988-05-03 United Technologies Corporation Stator vane
US5480285A (en) * 1993-08-23 1996-01-02 Westinghouse Electric Corporation Steam turbine blade
JPH0932501A (ja) * 1995-07-17 1997-02-04 Ishikawajima Harima Heavy Ind Co Ltd 軸流圧縮機動翼
JPH10331791A (ja) * 1997-05-30 1998-12-15 Toshiba Corp 軸流圧縮機用翼およびその翼を適用する軸流圧縮機
EP0957236A1 (fr) * 1998-05-15 1999-11-17 Asea Brown Boveri AG Aubes mobiles pour turbine
EP1111188A2 (fr) * 1999-12-21 2001-06-27 General Electric Company Aube inclinée avec arête amont bombée
EP1225303A2 (fr) * 2001-01-12 2002-07-24 Mitsubishi Heavy Industries, Ltd. Aubes pour turbines à gaz
EP1277966A2 (fr) * 2001-07-18 2003-01-22 General Electric Company Pale dentelée

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 1997, no. 06 30 June 1997 (1997-06-30) *
PATENT ABSTRACTS OF JAPAN vol. 1999, no. 03 31 March 1999 (1999-03-31) *

Cited By (35)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3108102A4 (fr) * 2014-02-19 2017-02-22 United Technologies Corporation Profil aérodynamique de moteur à turbine à gaz
US9752439B2 (en) 2014-02-19 2017-09-05 United Technologies Corporation Gas turbine engine airfoil
US9777580B2 (en) 2014-02-19 2017-10-03 United Technologies Corporation Gas turbine engine airfoil
US9988908B2 (en) 2014-02-19 2018-06-05 United Technologies Corporation Gas turbine engine airfoil
US10036257B2 (en) 2014-02-19 2018-07-31 United Technologies Corporation Gas turbine engine airfoil
US10184483B2 (en) 2014-02-19 2019-01-22 United Technologies Corporation Gas turbine engine airfoil
US10309414B2 (en) 2014-02-19 2019-06-04 United Technologies Corporation Gas turbine engine airfoil
US10352331B2 (en) 2014-02-19 2019-07-16 United Technologies Corporation Gas turbine engine airfoil
US10358925B2 (en) 2014-02-19 2019-07-23 United Technologies Corporation Gas turbine engine airfoil
US10370974B2 (en) 2014-02-19 2019-08-06 United Technologies Corporation Gas turbine engine airfoil
US10385866B2 (en) 2014-02-19 2019-08-20 United Technologies Corporation Gas turbine engine airfoil
US10393139B2 (en) 2014-02-19 2019-08-27 United Technologies Corporation Gas turbine engine airfoil
US10422226B2 (en) 2014-02-19 2019-09-24 United Technologies Corporation Gas turbine engine airfoil
US10465702B2 (en) 2014-02-19 2019-11-05 United Technologies Corporation Gas turbine engine airfoil
US10495106B2 (en) 2014-02-19 2019-12-03 United Technologies Corporation Gas turbine engine airfoil
US10502229B2 (en) 2014-02-19 2019-12-10 United Technologies Corporation Gas turbine engine airfoil
US10519971B2 (en) 2014-02-19 2019-12-31 United Technologies Corporation Gas turbine engine airfoil
US10550852B2 (en) 2014-02-19 2020-02-04 United Technologies Corporation Gas turbine engine airfoil
US10557477B2 (en) 2014-02-19 2020-02-11 United Technologies Corporation Gas turbine engine airfoil
US10570916B2 (en) 2014-02-19 2020-02-25 United Technologies Corporation Gas turbine engine airfoil
US10570915B2 (en) 2014-02-19 2020-02-25 United Technologies Corporation Gas turbine engine airfoil
US10584715B2 (en) 2014-02-19 2020-03-10 United Technologies Corporation Gas turbine engine airfoil
US10590775B2 (en) 2014-02-19 2020-03-17 United Technologies Corporation Gas turbine engine airfoil
US10605259B2 (en) 2014-02-19 2020-03-31 United Technologies Corporation Gas turbine engine airfoil
US10890195B2 (en) 2014-02-19 2021-01-12 Raytheon Technologies Corporation Gas turbine engine airfoil
US10914315B2 (en) 2014-02-19 2021-02-09 Raytheon Technologies Corporation Gas turbine engine airfoil
US11041507B2 (en) 2014-02-19 2021-06-22 Raytheon Technologies Corporation Gas turbine engine airfoil
US11193496B2 (en) 2014-02-19 2021-12-07 Raytheon Technologies Corporation Gas turbine engine airfoil
US11193497B2 (en) 2014-02-19 2021-12-07 Raytheon Technologies Corporation Gas turbine engine airfoil
US11209013B2 (en) 2014-02-19 2021-12-28 Raytheon Technologies Corporation Gas turbine engine airfoil
US11391294B2 (en) 2014-02-19 2022-07-19 Raytheon Technologies Corporation Gas turbine engine airfoil
US11408436B2 (en) 2014-02-19 2022-08-09 Raytheon Technologies Corporation Gas turbine engine airfoil
US11767856B2 (en) 2014-02-19 2023-09-26 Rtx Corporation Gas turbine engine airfoil
US11867195B2 (en) 2014-02-19 2024-01-09 Rtx Corporation Gas turbine engine airfoil
US12270315B2 (en) 2019-07-19 2025-04-08 MTU Aero Engines AG Rotor blade for a turbomachine, associated turbine module, and use thereof

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