EP1371813A1 - Aubage de turbomachine - Google Patents

Aubage de turbomachine Download PDF

Info

Publication number
EP1371813A1
EP1371813A1 EP02405491A EP02405491A EP1371813A1 EP 1371813 A1 EP1371813 A1 EP 1371813A1 EP 02405491 A EP02405491 A EP 02405491A EP 02405491 A EP02405491 A EP 02405491A EP 1371813 A1 EP1371813 A1 EP 1371813A1
Authority
EP
European Patent Office
Prior art keywords
blade
grooves
blades
center axis
extend
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Withdrawn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
EP02405491A
Other languages
German (de)
English (en)
Inventor
Ralf Dr. Greim
Said Dr. Havakechian
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.)
General Electric Switzerland GmbH
Original Assignee
Alstom Schweiz 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 Alstom Schweiz AG filed Critical Alstom Schweiz AG
Priority to EP02405491A priority Critical patent/EP1371813A1/fr
Publication of EP1371813A1 publication Critical patent/EP1371813A1/fr
Withdrawn legal-status Critical Current

Links

Images

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
    • F01D5/145—Means for influencing boundary layers or secondary circulations

Definitions

  • the invention relates to the blades for a turbomachine, such as Example turbines and compressors, and especially the surfaces of the Paddles to optimize the flow conditions.
  • the blades of a turbomachine are in their shape and Surface texture designed so that main or primary flow can flow through the vane channel with as little loss as possible and efficiently.
  • the main flow through a turbomachine is, however, caused by leakage, Secondary and profile losses impaired.
  • Dragage losses are caused by the flow that penetrates between the tip of the blade and the flow channel wall despite the labyrinth structures.
  • Profile losses which are essentially friction losses, are caused by frictional forces on surfaces. In addition to the surface roughness and structure, they also depend on the direction of flow. In addition to the direction of flow, the flow state, namely laminar or turbulent, is also decisive, as is the flow speed (which appears in the known Reynolds number) in order to describe the magnitude of the friction losses caused by surface roughness or structures.
  • a surface can appear aerodynamically smooth, even if it has surface structures, for example if it is parallel to the direction of flow. In the first place, however, the smoother the surface, the lower the friction losses, which is why in today's blade manufacturing practice the blade surfaces are made as smooth as possible.
  • the blades in an intermediate stage a structure of grooves, which according to the Milling processes run parallel to the tip and foot of the blades.
  • These grooves are made by further milling and / or so-called tumbling minimized so that it is as smooth as possible, free of milling grooves and / or roughness Surface, and if possible even a mirror-smooth surface.
  • the Smoothness is particularly the case with short blades with a small height-to-chord ratio and high Reynolds number effective to reduce profile losses. With longer blades with a lower Reynolds number, however, the Profile losses make the surface quality less critical.
  • the blades for a turbomachine are in a blade channel arranged, which is formed by the machine housing and the rotor and a Has blade channel center or blade channel center axis, which is at the level of half radial length of the blades.
  • the blades extend in radial longitudinal direction from a blade root to a blade tip and in axial direction from a blade leading edge to a blade trailing edge and each have a pressure and suction side.
  • each blade has a radially inner and a radially outer one Scoop half.
  • the blades have at least one on their suction side Surface structure with several grooves on it, which extend from one blade edge extend to the tip of the blade, to the blade root or to the other blade edge. There are at least one on the surface of the radially outer blade halves Part of the grooves oriented away from the blade channel center axis and on the Surface of the radially inner blade halves of at least part of the grooves of the blade channel center axis is oriented away.
  • the grooves of the surface structure result in an overall view a fan that is symmetrical with respect to the blade channel center axis, the Viewed in simplified terms, in the meridian plane along the bisector runs between the hub and the housing.
  • the fan starts at one Blade edge in the middle area of the blade, that is in the area of half radial longitudinal extension of the blade, and expands radially inward as well radially outwards.
  • the groove structure serves the vortex-shaped secondary flow, which is connected to the curved surfaces of the blade channel towards the center of the blade suction side flows, by means of a flow resistance and a frictional force counteract. As a result, the vortex flow and thus that of your secondary losses caused reduced.
  • the grooves are ideal for this perpendicular or at the largest possible angle to the direction of the secondary flow oriented.
  • the secondary losses when blading with a surface of this type are compared to the secondary losses with blading with smooth Surfaces reduced.
  • the surface structure according to the invention produces potentially increased profile losses by the groove structure in the primary flow causes additional friction. An overall balance of the various losses however, results in a decrease in primary flow losses.
  • the invention is based on blades for all types of turbomachines to use, such as turbines and compressors High-pressure machines with blades with a low height-to-chord ratio is particularly advantageous. It is on both on blades and on Guide vanes possible.
  • the invention is based on an axial turbomachine blading disclosed. However, it is also analog in the case of radially or diagonally flow Blading possible.
  • the grooves are arranged in such a way that they form a fan as a whole, which begins at the front edge and widens towards the blade root, the blade tip and the rear edge.
  • the grooves therefore extend on the radially outer half of the suction side of a moving blade at least in part from the front edge and away from the blade channel center axis to the blade tip or to the rear edge, and on the radially inner half of the suction side at least partly from the front edge in the direction of the blade channel center axis away to the blade root or to the rear edge.
  • the grooves of the fan on the radially outer half of the suction side extend at least in part from the front edge and away from the blade channel center axis to its blade root or to the rear edge, and on the radially inner half of the suction side at least partly from the front edge in the direction from the blade channel center axis away to the blade tip or to the rear edge.
  • the blades have not only on their suction side, but also on their pressure side Surface structure with the grooves according to the invention. Through this Measure further counteracts eddy formation and secondary losses are further reduced.
  • the surface structure on the suction and pressure sides of the blades forms a fan with the same orientation. That means the fan starts on both Sides of the blades in the center area of the front edge and extends to the rear edge and the blade tip and to the blade root. More precisely, on the suction side and on the pressure side of the blades, in each case on the radially outer blade half, at least some of the grooves extend away from the front edge from the blade channel center axis in the direction of the housing or blade channel wall or to the rear edge. On the radially inner blade half, the grooves extend correspondingly from the front edge and in a direction away from the blade channel center axis in the direction of the hub.
  • the surface structure is formed a fan on the suction side with the same orientation as in the described first variant.
  • the fan is in the Compared to the reverse on the suction side. That means the fan begins in the middle of the trailing edge and widens to the tip of the blade Shovel foot and towards the front edge. This measure has an additional effect the flow that starts from the pressure side and the vortex flow caused contrary.
  • the grooves of the The surface structure is straight.
  • run on the radially outer and inner blade half each have at least some of the grooves parallel to each other. They run on the radially outer and inner half of the blade at an angle away from the channel center axis.
  • each groove runs on the suction and / or Print page at an associated angle with respect to the Scoop channel center axis.
  • the angle of those grooves is that of the radial center closest to the shovel, smallest.
  • the angles of the other grooves are as the distance from the radial center of the blade increases greater.
  • the grooves run along a curved path.
  • the curvature can be either concave or convex with respect to the housing or the hub. In addition to the frictional force that counteracts the secondary flow, such a curvature also causes a pressure gradient to the blade tip or to the blade root, which additionally reduces the secondary flow.
  • the blade surfaces have Area of the radial center of the blades one or more Grooves parallel to the center of the vane channel. More grooves outside of the area with parallel grooves are according to one of the above described versions arranged. That to the blade channel center axis parallel grooves serve an aerodynamically smooth surface and support a low-loss primary flow in this central area.
  • FIG. 1 a shows a plurality of blades 1 of a blading that is on the rotor 2
  • Rotor axis 3 of a turbomachine are arranged. They extend radially from a blade root 4 to a blade tip 5 and axially from one Leading edge 6 to a trailing edge 7.
  • the suction and pressure sides of the Blades 1 are designated 8 and 9, respectively.
  • the arrows 10 indicate that Course of the vortex-shaped secondary flow in the suction side 8 of the Buckets 1 on. In the axial direction there is a helical shape Secondary flow, which affects the main flow 11.
  • Figure 1 b also explains the secondary flow in the blading and in particular the flow 12 and 12 'from the center of a blade pressure side 9 radially outwards or radially inwards to the boundary layer at the curved surfaces 13 of the blade channel flows and in the area of Suction side 8 forms vortex directed towards the middle of the suction side 8.
  • Figure 1c shows a blade channel 30 through the hub 31 and the housing 32 of the turbomachine is formed.
  • Rotor and guide blades 1 are on the rotor fixed with rotor axis 3 or on the housing 32.
  • the blade channel 30 has a defined blade channel center axis 18, which is along the bisector between the hub 31 and the wall of the housing 32 and each on the half radial longitudinal extent of the individual guide and rotor blades 1 runs.
  • Figure 2 shows an embodiment of a blading with an inventive Surface structure.
  • This version and all subsequent versions of Figures 3 to 8 are each shown using the example of blades, they are to be applied accordingly to guide vanes.
  • the surface structure is only on the suction side 8 of the blades 1 is arranged.
  • the surfaces of the printed pages 9 are conventional made smooth.
  • the surface structure has grooves 15 on the radial Outer blade half 16 starting from the front edge 6 in one Extend direction away from the blade center axis 18 and to the trailing edge 7 or lead to the tip of the blade 5.
  • On the radially inner blade half 17 the grooves extend from the leading edge 6 in a direction away from the Blade channel center axis 18 and lead to the rear edge 7 or Blade root 4.
  • the groove structure thus forms a kind of fan, which differs from the Spread the leading edge out to the trailing edge.
  • the grooves also run on each Blade half parallel to each other.
  • FIG. 3 shows an expanded embodiment of the invention, in which the suction sides and the pressure sides of the blades with the inventive Surface structure have been made.
  • the suction side 8 and the pressure side 9 has the same groove structure as described for FIG. 2.
  • the subjects therefore have the same orientation on both sides of the blade.
  • Figure 4 shows a variant of the execution of Figure 3. While in Figure 4 the fan-like groove structure on the suction side 8 in turn from the front edge starting to expand towards the rear edge, it has on the pressure side 9 opposite orientation. There the grooves run from the rear edge on the radially outer blade half 16 in a direction from the Blade channel center axis 18 away from front edge 6 or blade tip 5 out. The grooves 15 run on the radially inner blade half 17 Trailing edge 6 from in a direction away from the blade channel center axis 3 to Blade root 4 or towards the front edge 7.
  • the grooves run in a straight line and parallel to each other.
  • Figures 5 to 8 are several variants of groove structures disclosed, which are applicable to the embodiments of Figures 2 to 4.
  • the orientation of the Expansion of the fan-like groove structure is also possible in reverse, that is starting from the trailing edge and spreading to the leading edge.
  • FIG. 5 shows a variant of the groove structure according to the invention with a straight line Grooves.
  • the grooves 15 in particular each run in a direction assigned to them with respect to the blade channel center axis 18.
  • the grooves 15 start from one Area on the leading edge 6 around the radial blade center 18 and guide on the one hand to the blade tip 5 or trailing edge 7 or on the other hand to Blade base 4 or the rear edge 7.
  • Regarding bucket center 18 the grooves run at ever increasing angles to the blade ends 4,5 or the trailing edge 7.
  • the grooves are in a central area of the blade arranged like a fan as shown in Figure 5, while outside this The grooves parallel to the tip of the blade and the blade root run to each other, as shown in Figure 4.
  • FIG. 6 shows a further variant of the groove structure according to the invention, the Grooves in a central area 19 around the radial center 18 of the blade a plurality of grooves 20 which run parallel to the blade channel center axis 18. Outside of this central region 19 there are further grooves 15 of the type shown in FIG. 5 arranged, which run like a fan and straight.
  • FIG. 7 shows a further groove structure according to the invention, the grooves 21 of which are arranged like a fan, the individual grooves along a curved path.
  • the curvature is in the radially outer one Blade half 16 with respect to the blade tip 5 and in the radially inner one Blade half 17 of the blade root 4 each concave.
  • FIG. 8 shows a groove structure which is similar to that in FIG. 7, the grooves 22 each follow a curved path, the curvature of which with respect to the Blade tip 5 and the blade root 4 are each convex.
  • the curved grooves of FIGS. 7 and 8 are in each Blade half arranged parallel to each other. Furthermore, in one Another variant arranged in the radial center region of the blade grooves run parallel to the tip of the blade, as shown in FIG. 6, and outside of this area curved grooves of the type of FIGS. 7 and 8 arranged.
  • each groove and the distance between adjacent grooves are in accordance with the height-to-chord ratio of the blades customized.
  • the depth of the grooves are large and the distances to choose between the grooves small.
  • the depth should be chosen to be relatively small and the distances relatively large. Furthermore, grooves of different depths and at different distances from one another can also be made on a single blade surface.
  • the surface structure according to the invention is suitable for milled and forged blades.
  • the groove structure is preferably made by milling manufactured.
EP02405491A 2002-06-13 2002-06-13 Aubage de turbomachine Withdrawn EP1371813A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP02405491A EP1371813A1 (fr) 2002-06-13 2002-06-13 Aubage de turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP02405491A EP1371813A1 (fr) 2002-06-13 2002-06-13 Aubage de turbomachine

Publications (1)

Publication Number Publication Date
EP1371813A1 true EP1371813A1 (fr) 2003-12-17

Family

ID=29558480

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02405491A Withdrawn EP1371813A1 (fr) 2002-06-13 2002-06-13 Aubage de turbomachine

Country Status (1)

Country Link
EP (1) EP1371813A1 (fr)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1723311B1 (fr) * 2004-02-28 2010-04-07 MTU Aero Engines GmbH Aube de turbine a gaz
EP2548990A1 (fr) 2011-07-20 2013-01-23 MTU Aero Engines GmbH Procédé de fabrication de composants chargés en courant et composants ainsi fabriqués
WO2013020776A1 (fr) * 2011-08-08 2013-02-14 Siemens Aktiengesellschaft Refroidissement en film d'aubes ou ailettes de turbine
WO2013045629A1 (fr) * 2011-09-29 2013-04-04 Rolls-Royce Deutschland Ltd & Co Kg Pale d'une rangée de pales de rotor ou de stator s'utilisant dans une turbomachine
EP2612991A3 (fr) * 2012-01-03 2014-03-19 General Electric Company Aube de turbine à gaz avec rainure d'écoulement
CN107084000A (zh) * 2016-02-12 2017-08-22 通用电气公司 涡轮机流动路径表面的凸肋
CN107869359A (zh) * 2017-12-01 2018-04-03 无锡宇能选煤机械厂 流线型厚叶片涡轮增压器转子轴
US10539157B2 (en) 2015-04-08 2020-01-21 Horton, Inc. Fan blade surface features

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1545622A (en) * 1975-04-30 1979-05-10 Toyoda Chuo Kenkyusho Kk Axial flow fans
JPS5572602A (en) * 1978-11-24 1980-05-31 Mitsubishi Heavy Ind Ltd Construction of turbine nozzle or blade
JPS5867999A (ja) * 1981-10-16 1983-04-22 Hitachi Ltd 軸流形流体機械における動翼構造
US4907765A (en) * 1985-09-26 1990-03-13 Messerschmitt-Boelkow-Blohm Gmbh Wall with a drag reducing surface and method for making such a wall
WO1998044240A1 (fr) * 1997-04-01 1998-10-08 Siemens Aktiengesellschaft Structure superficielle pour la paroi d'un canal d'ecoulement ou d'une aube de turbine

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1545622A (en) * 1975-04-30 1979-05-10 Toyoda Chuo Kenkyusho Kk Axial flow fans
JPS5572602A (en) * 1978-11-24 1980-05-31 Mitsubishi Heavy Ind Ltd Construction of turbine nozzle or blade
JPS5867999A (ja) * 1981-10-16 1983-04-22 Hitachi Ltd 軸流形流体機械における動翼構造
US4907765A (en) * 1985-09-26 1990-03-13 Messerschmitt-Boelkow-Blohm Gmbh Wall with a drag reducing surface and method for making such a wall
WO1998044240A1 (fr) * 1997-04-01 1998-10-08 Siemens Aktiengesellschaft Structure superficielle pour la paroi d'un canal d'ecoulement ou d'une aube de turbine

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 004, no. 114 (M - 026) 15 August 1980 (1980-08-15) *
PATENT ABSTRACTS OF JAPAN vol. 007, no. 159 (M - 228) 13 July 1983 (1983-07-13) *

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1723311B1 (fr) * 2004-02-28 2010-04-07 MTU Aero Engines GmbH Aube de turbine a gaz
EP2548990A1 (fr) 2011-07-20 2013-01-23 MTU Aero Engines GmbH Procédé de fabrication de composants chargés en courant et composants ainsi fabriqués
WO2013020776A1 (fr) * 2011-08-08 2013-02-14 Siemens Aktiengesellschaft Refroidissement en film d'aubes ou ailettes de turbine
US9771804B2 (en) 2011-08-08 2017-09-26 Siemens Aktiengesellschaft Film cooling of turbine blades or vanes
US9638040B2 (en) 2011-09-29 2017-05-02 Rolls-Royce Deutschland Ltd & Co Kg Blade of a row of rotor blades or stator blades for use in a turbomachine
WO2013045629A1 (fr) * 2011-09-29 2013-04-04 Rolls-Royce Deutschland Ltd & Co Kg Pale d'une rangée de pales de rotor ou de stator s'utilisant dans une turbomachine
US20140248154A1 (en) * 2011-09-29 2014-09-04 Rolls-Royce Deutschland Ltd & Co Kg Blade of a row of rotor blades or stator blades for use in a turbomachine
US9062554B2 (en) 2012-01-03 2015-06-23 General Electric Company Gas turbine nozzle with a flow groove
EP2612991A3 (fr) * 2012-01-03 2014-03-19 General Electric Company Aube de turbine à gaz avec rainure d'écoulement
US10539157B2 (en) 2015-04-08 2020-01-21 Horton, Inc. Fan blade surface features
US10662975B2 (en) 2015-04-08 2020-05-26 Horton, Inc. Fan blade surface features
CN107084000A (zh) * 2016-02-12 2017-08-22 通用电气公司 涡轮机流动路径表面的凸肋
EP3214267A1 (fr) * 2016-02-12 2017-09-06 General Electric Company Riblets pour une surface de trajet d'écoulement d'une turbomachine
US10450867B2 (en) 2016-02-12 2019-10-22 General Electric Company Riblets for a flowpath surface of a turbomachine
CN107869359A (zh) * 2017-12-01 2018-04-03 无锡宇能选煤机械厂 流线型厚叶片涡轮增压器转子轴

Similar Documents

Publication Publication Date Title
EP0972128B1 (fr) Structure superficielle pour la paroi d'un canal d'ecoulement ou d'une aube de turbine
EP2025945B1 (fr) Machine de traitement des écoulements dotée d'un creux de paroi de canal de ceinture
DE60112986T2 (de) Beschaufelung einer Turbomaschine
EP2463480B1 (fr) Aube avec profile hybride
WO2007113149A1 (fr) Aube directrice de turbomachine, notamment de turbine à vapeur
EP2761137B1 (fr) Pale d'une rangée de pales de rotor ou de stator pour une turbomachine
EP2478186B1 (fr) Rotor de turbomachine
CH617493A5 (fr)
EP1717414A1 (fr) Roue de turbine
DE102005042115A1 (de) Schaufel einer Strömungsarbeitsmaschine mit blockweise definierter Profilskelettlinie
EP3988797B1 (fr) Ventilateur axial pourvu de pales de roue d'aérateur réduisant le bruit et pourvues de trous
EP2947270B3 (fr) Groupe de série d'aubes
EP2180195A2 (fr) Turbomachine avec contrôle du jeu des aubes
EP1642005B1 (fr) Aube de turbine
EP2538024A1 (fr) Aube dans une turbomachine
DE60019965T2 (de) Axialturbine für gase
DE102019202356A1 (de) Laufschaufelseitige Dichtungsvorrichtung, stationäre schaufelseitige Dichtungsvorrichtung und Rotationsmaschine
DE102012104240B4 (de) Hybridströmungs-Schaufeldesigns
EP1371813A1 (fr) Aubage de turbomachine
EP2410131A2 (fr) Rotor d'une turbomachine
DE112016000685T5 (de) Turbine und gasturbine
DE60014025T2 (de) Turbomaschinen
EP3428402B1 (fr) Segment d'aube directrice à joint de décharge courbé
EP3181813B1 (fr) Filetage centré d'aubes
EP3431707A1 (fr) Aube, couronne d'aubes, segment de couronne d'aubes et turbomachine

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE TR

AX Request for extension of the european patent

Extension state: AL LT LV MK RO SI

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION HAS BEEN WITHDRAWN

18W Application withdrawn

Effective date: 20040108

REG Reference to a national code

Ref country code: DE

Ref legal event code: 8566