EP1201880A2 - Grilles d'aubes de guidage pour turbomachines - Google Patents

Grilles d'aubes de guidage pour turbomachines Download PDF

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Publication number
EP1201880A2
EP1201880A2 EP01125191A EP01125191A EP1201880A2 EP 1201880 A2 EP1201880 A2 EP 1201880A2 EP 01125191 A EP01125191 A EP 01125191A EP 01125191 A EP01125191 A EP 01125191A EP 1201880 A2 EP1201880 A2 EP 1201880A2
Authority
EP
European Patent Office
Prior art keywords
grille
blades
axial
vane
blade
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
EP01125191A
Other languages
German (de)
English (en)
Other versions
EP1201880B1 (fr
EP1201880A3 (fr
Inventor
Andreas Dr. Fiala
Adam Heisler
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
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 MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Publication of EP1201880A2 publication Critical patent/EP1201880A2/fr
Publication of EP1201880A3 publication Critical patent/EP1201880A3/fr
Application granted granted Critical
Publication of EP1201880B1 publication Critical patent/EP1201880B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • 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
    • 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F04D29/544—Blade shapes

Definitions

  • the invention relates to a vane grille arrangement for turbomachinery in axial flowed through, coaxial design, according to the preamble of claim 1.
  • the patent EP 0 756 667 B1 protects a "clocking" method in which the Caster of a first vane grille through a second vane grille with relative movement on the blade leading edges of a third, fixed relative to the first Blade grids are steered, with a maximum, circumferential deviation between trailing and leading edge of plus / minus 12.5 percent of the blade division should be allowed.
  • the prerequisite for "clocking" is that the same relative system (Stator or rotor) associated, coordinated blade grids have the same blade numbers - With a circumferentially constant blade pitch - have.
  • the object of the invention is a vane grille arrangement with two guide vane grids and to propose a blade grid arranged between them, despite the different blade numbers of the two guide vane grids a fluidically advantageous, relative circumferential positioning of the guide vane grille in the sense of "clocking".
  • the upstream guide vane grille is - despite the constant pitch angle the blades over the circumference - with two different ones, in themselves contiguous or in several separate sectors over the grid circumference Distributed sub-areas, with each blade to their in both areas Neighboring blade is axially offset in a defined manner.
  • the stacking axes are thus located the blades are no longer - as usual - in a common radial plane but on screw surfaces with constant or changing pitch, whereby concrete Bucket points lie on helical lines accordingly.
  • the first section with ⁇ m describes, for example, a "forward screw" the second with ⁇ n a "Reverse screw” connecting ends of the ⁇ m range, or vice versa.
  • the second section is only for feedback of the total, totaled axial misalignment in linear or non-linear Way using ⁇ n while avoiding relevant fluidic disadvantages.
  • the guide vane grille has an oblique outflow with a strong peripheral component have an axial offset between adjacent blades effectively Enlargement or reduction of the flow cross-section on the outlet side.
  • the axial offset ⁇ m is constant and as a function of the blade number ratio of the two guide vane grids selected.
  • the invention leads to a certain asymmetry of the flow and thus the Mass distribution in the circular flow channel cross section. This has among other things the advantage that instabilities and disturbances that occur with symmetrical or periodic Circumstances could spread further, shifted and can be partially prevented. Furthermore, the invention can be targeted certain asymmetries in the inflow are reacted to.
  • clocking effect primarily aimed at with the invention could be due to its Angle limitation, for example, also referred to as “partial clocking” or “sector clocking” become.
  • Preferred embodiments and a dimensioning rule are in the subclaims characterized for the blade grid arrangement according to the main claim.
  • FIGS. 1 and 2 show the vane grille as if it were a flat grille - with no curvature parallel blades - would act, whereby only one concrete profile is given for each blade is.
  • This type of display is much simpler, clearer and easier to understand than a realistic, spatial representation with radial, three-dimensional blades etc.
  • the vane grille arrangement 1 in FIG. 1 is flowed through from left to right, whereby upstream (left) a guide vane grille 2, in the middle a moving vane grille 5 and downstream (right) there is again a guide vane grille 3.
  • the blades 2, 5 and 3 are provided with the reference numerals 6, 9 and 7.
  • the Direction of rotation of the rotor blade grille 5 is underneath it with an upward-pointing indicated by black arrow. Detects above the rotor blade grille 5 a dashed, horizontal double arrow that indicates that the grid can be made axially displaceable to additionally influence the flow to take.
  • the so-called Caster 10 of the guide vane grille 2 In the colors gray and black, the so-called Caster 10 of the guide vane grille 2, the caster 11 of the moving vane grille 5 and the change in caster 10 as it passes through grids 2 and 5, the dotted curves and straight lines represent the paths of the caster 10 in Describe the relation to the stationary stator system.
  • the axial offset according to the invention the blades only affect the upstream guide vane grille 2 and are in Figure 1 not recognizable. Nor can it be seen from FIG. 1 that the guide vane grids 2 and 3 have different blade numbers.
  • FIG. 2 therefore shows a guide vane grille that is comparable to the grille 2 in FIG. 1 4 with blades axially offset according to the invention 8.
  • the pitch angle between all blades 8 is constant, so that the height offset is constant in the figure is. See on the left the specification 2 ⁇ ⁇ ⁇ Z1, which corresponds to the divided by the radius r, i.e. Radius-related radians from bucket to bucket corresponds.
  • the first, second and third blades from above are mutually axial (here horizontal), respectively offset by an amount ⁇ m, the blades continuing to move from top to bottom move to the right, i.e. downstream.
  • the outflow from the guide vane grille 4 runs at an angle ⁇ of approximately 45 ° to the top right, i.e.
  • the bottom blade in Figure 2 is relative to the one above it no longer to the right by ⁇ m, but to the left by an axial offset ⁇ n is.
  • the invention therefore provides for a first partial region T1 of the guide vane grille to be provided with a continuous axial offset ⁇ m, and in one second sub-area T2 to completely reverse the sum of all ⁇ m by means of opposite axial offsets ⁇ n.
  • FIG. 3 shows the course of the axial offset ⁇ ⁇ m, ⁇ n over the circumference U of the guide vane grille, the concrete blade positions are marked with small circles.
  • S curve it can be seen that the axial offset ⁇ n of the blade increases Shovel can change. Which type of curve is cheaper here is, among other things.
  • the blade (small circle) at ordinate 0 is identical to the blade at the ordinate 2 ⁇ ⁇ , since the grid circumference closes here. In the present 16 different blade positions are thus indicated in the diagram. In the In reality, the number of blades will generally be significantly larger.
  • the size ratio the sub-areas T1 and T2 are only exemplary, with T1> T2 to be aimed at is. Since the number of blades Z1 and Z2 are only slightly different in practice, relatively small axial offsets ⁇ m are sufficient for the application of the invention.
  • FIG. 4 shows the course of the axial offset ⁇ m, ⁇ n over the circumference U of a guide vane grille, whose partial areas T1, T2 differ from the embodiment according to FIG 3 not arranged contiguously, but each in four separate ones Sectors T1 ⁇ 4, T2 ⁇ 4 are spread over the grid circumference, making a quadruple periodic course with positive and negative axial offset ⁇ m, ⁇ n results.
  • the division into four sectors is exemplary; it could also be two, three, five or be more sectors.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP01125191A 2000-10-27 2001-10-24 Grilles d'aubes de guidage pour turbomachines Expired - Lifetime EP1201880B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10053361 2000-10-27
DE10053361A DE10053361C1 (de) 2000-10-27 2000-10-27 Schaufelgitteranordnung für Turbomaschinen

Publications (3)

Publication Number Publication Date
EP1201880A2 true EP1201880A2 (fr) 2002-05-02
EP1201880A3 EP1201880A3 (fr) 2003-07-02
EP1201880B1 EP1201880B1 (fr) 2004-09-22

Family

ID=7661316

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01125191A Expired - Lifetime EP1201880B1 (fr) 2000-10-27 2001-10-24 Grilles d'aubes de guidage pour turbomachines

Country Status (5)

Country Link
US (1) US6540478B2 (fr)
EP (1) EP1201880B1 (fr)
AT (1) ATE277277T1 (fr)
CA (1) CA2360395C (fr)
DE (2) DE10053361C1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1724440A1 (fr) * 2005-05-10 2006-11-22 MTU Aero Engines GmbH Procédé pour optimiser l'écoulement dans des turbomachines multi-étages
CN100376765C (zh) * 2005-10-28 2008-03-26 中国科学院工程热物理研究所 一种用于多级叶轮机的三维时序效益最大化方法
CN101457655A (zh) * 2007-12-14 2009-06-17 斯奈克玛 涡轮机多级涡轮的设计方法

Families Citing this family (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2420157B (en) * 2003-05-14 2006-06-28 Rolls Royce Plc A stator vane assembly for a turbomachine
DE10357075B4 (de) 2003-12-06 2006-01-12 Dornier Gmbh Verfahren zur Lärmreduzierung von Turbomaschinen
DE102004059882A1 (de) * 2004-12-10 2006-06-22 Rolls-Royce Deutschland Ltd & Co Kg Magervormischbrenner mit integriertem Stützbrenner
DE102005048982A1 (de) 2005-10-13 2007-04-19 Mtu Aero Engines Gmbh Vorrichtung und Verfahren zum axialen Verschieben eines Turbinenrotors
US8540490B2 (en) * 2008-06-20 2013-09-24 General Electric Company Noise reduction in a turbomachine, and a related method thereof
US20090317237A1 (en) * 2008-06-20 2009-12-24 General Electric Company System and method for reduction of unsteady pressures in turbomachinery
US20100054929A1 (en) * 2008-09-04 2010-03-04 General Electric Company Turbine airfoil clocking
DE102008049358A1 (de) * 2008-09-29 2010-04-01 Mtu Aero Engines Gmbh Axiale Strömungsmaschine mit asymmetrischem Verdichtereintrittsleitgitter
DE102008058014A1 (de) * 2008-11-19 2010-05-20 Rolls-Royce Deutschland Ltd & Co Kg Mehrschaufelige Verstellstatoreinheit einer Strömungsarbeitsmaschine
US8439626B2 (en) * 2008-12-29 2013-05-14 General Electric Company Turbine airfoil clocking
US20130081402A1 (en) * 2011-10-03 2013-04-04 General Electric Company Turbomachine having a gas flow aeromechanic system and method
US20130209216A1 (en) * 2012-02-09 2013-08-15 General Electric Company Turbomachine including flow improvement system
US20140068938A1 (en) * 2012-09-10 2014-03-13 General Electric Company Method of clocking a turbine with skewed wakes
US9435221B2 (en) 2013-08-09 2016-09-06 General Electric Company Turbomachine airfoil positioning
US10519796B2 (en) 2013-09-16 2019-12-31 United Technologies Corporation Variable area turbine vane row assembly
DE102014204346A1 (de) 2014-03-10 2015-09-10 Rolls-Royce Deutschland Ltd & Co Kg Verfahren zur Herstellung eines doppelreihigen Schaufelrads für eine Strömungsmaschine und doppelreihiges Schaufelrad
US10145301B2 (en) 2014-09-23 2018-12-04 Pratt & Whitney Canada Corp. Gas turbine engine inlet
US10378554B2 (en) 2014-09-23 2019-08-13 Pratt & Whitney Canada Corp. Gas turbine engine with partial inlet vane
US9957807B2 (en) 2015-04-23 2018-05-01 Pratt & Whitney Canada Corp. Rotor assembly with scoop
US9938848B2 (en) 2015-04-23 2018-04-10 Pratt & Whitney Canada Corp. Rotor assembly with wear member
US20180010459A1 (en) * 2016-01-11 2018-01-11 United Technologies Corporation Low energy wake stage
US10724540B2 (en) 2016-12-06 2020-07-28 Pratt & Whitney Canada Corp. Stator for a gas turbine engine fan
US10690146B2 (en) 2017-01-05 2020-06-23 Pratt & Whitney Canada Corp. Turbofan nacelle assembly with flow disruptor

Citations (1)

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Publication number Priority date Publication date Assignee Title
EP0756667B1 (fr) 1994-04-19 1998-06-24 United Technologies Corporation Synchronisation des profils d'aubes d'une turbine a gaz

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DE439905C (de) * 1927-01-22 Georg Forner Dr Ing Leitvorrichtung fuer Dampfturbinen
US910266A (en) * 1906-12-17 1909-01-19 Giuseppe Belluzzo Elastic-fluid turbine.
DE433183C (de) * 1924-05-16 1926-08-24 Erste Bruenner Maschinen Fab Schaufeln fuer achsiale Dampf- oder Gasturbinen
DE1033677B (de) * 1957-10-31 1958-07-10 Maschf Augsburg Nuernberg Ag Leitapparat mit im Betrieb verstellbaren Schaufeln fuer Turbinen und Verdichter, besonders fuer Gasturbinen
FR1200484A (fr) * 1958-06-26 1959-12-22 Alsthom Cgee Dispositif de drainage de l'eau dans les turbines à vapeur
US3347520A (en) * 1966-07-12 1967-10-17 Jerzy A Oweczarek Turbomachine blading
CH557468A (de) * 1973-04-30 1974-12-31 Bbc Brown Boveri & Cie Turbine axialer bauart.
SE500471C2 (sv) * 1991-07-09 1994-07-04 Flaekt Ab Ledskeneanordning i en axialfläkt
US6402458B1 (en) * 2000-08-16 2002-06-11 General Electric Company Clock turbine airfoil cooling

Patent Citations (1)

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Publication number Priority date Publication date Assignee Title
EP0756667B1 (fr) 1994-04-19 1998-06-24 United Technologies Corporation Synchronisation des profils d'aubes d'une turbine a gaz

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1724440A1 (fr) * 2005-05-10 2006-11-22 MTU Aero Engines GmbH Procédé pour optimiser l'écoulement dans des turbomachines multi-étages
CN100376765C (zh) * 2005-10-28 2008-03-26 中国科学院工程热物理研究所 一种用于多级叶轮机的三维时序效益最大化方法
CN101457655A (zh) * 2007-12-14 2009-06-17 斯奈克玛 涡轮机多级涡轮的设计方法
EP2071127A1 (fr) * 2007-12-14 2009-06-17 Snecma Procédé de conception d'une turbine multi-étages de turbomachine
FR2925106A1 (fr) * 2007-12-14 2009-06-19 Snecma Sa Procede de conception d'une turbine multi-etages de turbomachine
US8083476B2 (en) 2007-12-14 2011-12-27 Snecma Method of designing a multistage turbine for a turbomachine
CN101457655B (zh) * 2007-12-14 2013-12-25 斯奈克玛 涡轮机多级涡轮的设计方法

Also Published As

Publication number Publication date
CA2360395C (fr) 2010-03-23
EP1201880B1 (fr) 2004-09-22
US6540478B2 (en) 2003-04-01
DE10053361C1 (de) 2002-06-06
CA2360395A1 (fr) 2002-04-27
US20020057966A1 (en) 2002-05-16
ATE277277T1 (de) 2004-10-15
EP1201880A3 (fr) 2003-07-02
DE50103734D1 (de) 2004-10-28

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