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EP1564374A1 - Aube pour une turbomachine - Google Patents

Aube pour une turbomachine Download PDF

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Publication number
EP1564374A1
EP1564374A1 EP04003172A EP04003172A EP1564374A1 EP 1564374 A1 EP1564374 A1 EP 1564374A1 EP 04003172 A EP04003172 A EP 04003172A EP 04003172 A EP04003172 A EP 04003172A EP 1564374 A1 EP1564374 A1 EP 1564374A1
Authority
EP
European Patent Office
Prior art keywords
airfoil
curved surface
flow medium
viewed
turbomachine
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Withdrawn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
EP04003172A
Other languages
German (de)
English (en)
Inventor
Heinrich Dr. Stüer
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 EP04003172A priority Critical patent/EP1564374A1/fr
Publication of EP1564374A1 publication Critical patent/EP1564374A1/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Withdrawn legal-status Critical Current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
    • F05D2250/71—Shape curved
    • F05D2250/711—Shape curved convex
    • 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
    • F05D2250/712—Shape curved concave

Definitions

  • the invention relates to an airfoil for a Turbomachine, in particular for a low-pressure steam turbine, which is based on a hub of the Turbomachine extends radially outward, from one Flow medium is flowed around while a Overpressure side surface and one facing away from it Has negative pressure side surface.
  • Blades of turbomachinery are highly stressed Components.
  • the last blade in Low-pressure steam turbines are subject to special Flow conditions exceeding the blade height, i. over the extension of the blade starting from the Scar of turbomachine radially outward, change greatly.
  • the blades must therefore be constructed with profiles that withstand these pressures withstand and are optimal in terms of fluid mechanics.
  • Such a known airfoil 10 is flown by a flow medium in a main flow direction 12 and in this case has an overpressure side surface 14 and a vacuum side surface 16 facing away from it. Between the overpressure side surface 14 and the vacuum side surface 16, the so-called nose edge 18 is located at the front of the airfoil 10, onto which the flow of the flow medium occurs and is divided there by the airfoil 10. The two, the airfoil 10 flowing around streams flow behind the airfoil 10 at the end edge 20 together again.
  • a front partial flow 22 flows along the overpressure side surface 14 which, viewed from the flow medium, has a flat, concavely curved surface.
  • a second, rear partial flow 24 flows along the vacuum side surface 16, which, viewed from the flow medium, has a comparatively strongly curved, convex surface.
  • the invention is based on the object, an airfoil to provide the type mentioned, the Massenund Stress distribution especially at high Flow velocities on the airfoil is better than the well-known blades.
  • the object is according to the invention with a generic Airfoil for a turbomachine solved in which the Airfoil at least in the middle region of its radial Extension on its overpressure side surface with one of Fluid medium viewed from concave and a concave adjacently arranged convexly curved surface portion is designed.
  • the invention is based on the recognition that in the Design of the profile of an airfoil next to the Flow behavior of the air flow along the blade Flow medium especially the centrifugal force of the Airfoil itself must be observed.
  • a shovel foot of the airfoil and the profile of the airfoil over the blade foot must have the centrifugal force of the rest Pick up the blade.
  • the mass of the airfoil reduced by placing its profile on the overpressure side surface is hollowed out. The hollow becomes concave arched and an adjacently arranged convex arched Surface section reached.
  • the inventive mass savings may alternatively or in addition also be achieved by the airfoil at least in the middle region of its radial extent its negative pressure side surface with one of the flow medium viewed from concave and one adjacent arranged convex curved surface section designed is.
  • the mass saving is then at the Low side pressure achieved by the top of this said excavation is provided.
  • the said should be concave curved surface section on the overpressure side surface of the airfoil with respect to the flow direction of Flow medium in the front of the Overpressure side surface is arranged.
  • concave and the convex curved Surface section both on the overpressure side surface as also the negative side surface of the airfoil in Circumferential direction of the turbomachine next to each other and be designed adjacent to each other.
  • the concave curved surface section at the Overpressure side surface and / or the negative side surface in a region of the airfoil is formed in the in Flow direction of the flow medium no overlap with If there is an adjacent airfoil, the influence can be be reduced to the profile pressure distribution because itself adjacent profiles or airfoils not or nearly do not influence each other.
  • both the positive pressure side surface and the negative pressure side surface leads to a particularly advantageous shaped airfoil, at least in the middle region of its radial extent has a substantially S-shaped cross-sectional area.
  • Such an S-shape of a profile is especially at transonic profiles of advantage.
  • the invention should Airfoil also in the radially inner region (i.e. Near its blade root) on its overpressure side surface with a view from the flow medium alone concave arched surface and / or on his Low pressure side surface with one from the flow medium considered to be designed solely convex curved surface.
  • the inventive Airfoil in the radially outer region i.e., in the vicinity his blade head or its outer edge or his Randbogens
  • the inventive Airfoil in the radially outer region i.e., in the vicinity his blade head or its outer edge or his Randbogens
  • the overpressure side surface with a from Flow medium viewed from alone convex curved Surface and / or on its negative pressure side surface with one viewed from the flow medium alone concave be designed curved surface.
  • FIG. 2-5 is with three cross sections or profiles and a side view of an embodiment of a Airfoil 10 shown, which of a Flow medium in a main flow direction 12th is flowing and thereby a positive pressure side surface 14 and a negative pressure side surface 16 has.
  • the Airfoil 10 of the prior art of FIG. 1 is in the airfoil 10 according to FIGS. 2-5 the Storming medium at a nose edge 18 of the airfoil 10th divided and flows at an end edge 22 of this again together.
  • the flow medium forms a front Partial flow 22 and a rear partial flow 24th
  • Fig. 5 is the side view of the airfoil 10th its radial longitudinal extent starting from a Foot area 30 in the vicinity of a hub, not shown the associated turbomachine, via a central region 32nd down to a header 34. At the Head portion 34 terminates the airfoil 10 at an outer edge 36 or an edge bow.
  • the profile of the airfoil 10 is in this Header area 34 illustrates.
  • the profile of Airfoil 10 has there on its overpressure side surface 14 a seen from the front partial flow 22 from alone convex curved surface on and is at its Vacuum side surface 16 from the rear partial flow 24 from considered with a single concave curved surface designed.
  • the profile of the airfoil is on its overpressure side surface 14 in the front region on which no overlap with an adjacent blade consists, with a concavely curved surface portion 26th designed, to which an adjacent convex arched Surface section 28 immediately connects.
  • a concavely curved surface portion 26th designed, to which an adjacent convex arched Surface section 28 immediately connects.
  • the vacuum side surface 16 of the profile in Center region 32 in the front region of the airfoil 10th viewed from the rear part of stream 24 from convexly curved Surface portion 28 formed on the rear Area of the airfoil 10 a concave Surface section 26 connects.
  • Fig. 3 are finally still the so-called Mach iso-lines 40 on the profile of the airfoil 10 in the Center area 32 illustrates.
  • the Mach iso lines 40 extend over a wide Area of the pressure side surface 14 and the Vacuum side surface 16 almost perpendicular to these Side surfaces and also almost without curvature.
  • Such Behavior of a front partial flow 22 and a rear Partial flow 24 on an airfoil 10 is aerodynamically particularly favorable.

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP04003172A 2004-02-12 2004-02-12 Aube pour une turbomachine Withdrawn EP1564374A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP04003172A EP1564374A1 (fr) 2004-02-12 2004-02-12 Aube pour une turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04003172A EP1564374A1 (fr) 2004-02-12 2004-02-12 Aube pour une turbomachine

Publications (1)

Publication Number Publication Date
EP1564374A1 true EP1564374A1 (fr) 2005-08-17

Family

ID=34684679

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04003172A Withdrawn EP1564374A1 (fr) 2004-02-12 2004-02-12 Aube pour une turbomachine

Country Status (1)

Country Link
EP (1) EP1564374A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110173459A (zh) * 2019-05-23 2019-08-27 清华大学 叶片及其造型方法和轮机
DE102010038074B4 (de) * 2009-10-23 2020-10-22 General Electric Co. Turbinenschaufelblatt

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB657366A (en) * 1948-02-25 1951-09-19 Westinghouse Electric Int Co Improvements in or relating to fluid pressure apparatus
GB913620A (en) * 1960-02-03 1962-12-19 Szydlowski Joseph Improvements in or relating to axial-flow compressors
US3333817A (en) * 1965-04-01 1967-08-01 Bbc Brown Boveri & Cie Blading structure for axial flow turbo-machines
GB1262182A (en) * 1968-05-12 1972-02-02 Mo Energeticheskij Institut Improvements in or relating to turbine rotor blades
GB2106192A (en) * 1981-09-24 1983-04-07 Rolls Royce Turbomachine blade
US5044885A (en) * 1989-03-01 1991-09-03 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Mobile blade for gas turbine engines providing compensation for bending moments
US6071077A (en) * 1996-04-09 2000-06-06 Rolls-Royce Plc Swept fan blade
EP1152122A2 (fr) * 2000-05-01 2001-11-07 United Technologies Corporation Aube pour une turbomachine
US20030031564A1 (en) * 2001-08-10 2003-02-13 Honda Giken Kogyo Kabushiki Kaisha Stationary vanes for turbines and method for making the same

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB657366A (en) * 1948-02-25 1951-09-19 Westinghouse Electric Int Co Improvements in or relating to fluid pressure apparatus
GB913620A (en) * 1960-02-03 1962-12-19 Szydlowski Joseph Improvements in or relating to axial-flow compressors
US3333817A (en) * 1965-04-01 1967-08-01 Bbc Brown Boveri & Cie Blading structure for axial flow turbo-machines
GB1262182A (en) * 1968-05-12 1972-02-02 Mo Energeticheskij Institut Improvements in or relating to turbine rotor blades
GB2106192A (en) * 1981-09-24 1983-04-07 Rolls Royce Turbomachine blade
US5044885A (en) * 1989-03-01 1991-09-03 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Mobile blade for gas turbine engines providing compensation for bending moments
US6071077A (en) * 1996-04-09 2000-06-06 Rolls-Royce Plc Swept fan blade
EP1152122A2 (fr) * 2000-05-01 2001-11-07 United Technologies Corporation Aube pour une turbomachine
US20030031564A1 (en) * 2001-08-10 2003-02-13 Honda Giken Kogyo Kabushiki Kaisha Stationary vanes for turbines and method for making the same

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102010038074B4 (de) * 2009-10-23 2020-10-22 General Electric Co. Turbinenschaufelblatt
CN110173459A (zh) * 2019-05-23 2019-08-27 清华大学 叶片及其造型方法和轮机

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