EP1724440B1 - Verfahren zur Strömungsoptimierung in mehrstufigen Turbomaschinen - Google Patents
Verfahren zur Strömungsoptimierung in mehrstufigen Turbomaschinen Download PDFInfo
- Publication number
- EP1724440B1 EP1724440B1 EP05010100A EP05010100A EP1724440B1 EP 1724440 B1 EP1724440 B1 EP 1724440B1 EP 05010100 A EP05010100 A EP 05010100A EP 05010100 A EP05010100 A EP 05010100A EP 1724440 B1 EP1724440 B1 EP 1724440B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blade
- ring
- flow
- profiles
- blade ring
- 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.)
- Not-in-force
Links
- 238000000034 method Methods 0.000 title claims description 24
- 238000006073 displacement reaction Methods 0.000 claims description 15
- 239000008186 active pharmaceutical agent Substances 0.000 claims description 8
- 238000005457 optimization Methods 0.000 description 8
- 238000010586 diagram Methods 0.000 description 4
- 239000012530 fluid Substances 0.000 description 3
- 239000000654 additive Substances 0.000 description 2
- 230000000996 additive effect Effects 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 230000004323 axial length Effects 0.000 description 1
- 230000001427 coherent effect Effects 0.000 description 1
- 230000000295 complement effect Effects 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 230000001052 transient effect Effects 0.000 description 1
- 238000003260 vortexing Methods 0.000 description 1
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
- F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
-
- 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
- F05D2270/00—Control
- F05D2270/01—Purpose of the control system
- F05D2270/10—Purpose of the control system to cope with, or avoid, compressor flow instabilities
Definitions
- the invention relates to a method for optimizing flow in multi-stage turbomachines, in which the flow of a third of three successive blade rings is optimized, according to the preamble of claim 1.
- the European Patent EP 0 756 667 B1 protects a generic method of flow optimization in which the relative blade profile positioning between the first and third blade rings is referred to as "clocking".
- clocking The preferred application here is the vane clocking, ie, the first and third vane rings are vane rings, whereas the second vane ring is a blade ring.
- the principle of this method is that the flow paths of the trailing edge of the blade profiles of the first blade ring are determined until entering the third blade ring, and the leading edges of the blade profiles of the third blade ring within a predetermined tolerance angle range (25% of the blade pitch angle) relative to the entry positions of Curbs are positioned.
- Optimal should be a direct / central impact of each caster on the respective leading edge.
- Each caster descends as a contiguous, turbulent stream from the trailing edge of the blade profile of the first blade ring and, as it passes through the second rotating blade ring, is split into separate pieces moving side-by-side on particular webs.
- the number of tracks corresponds to the circumference of the flow area divided by the number of blades of the first blade ring.
- the moving pieces of adjacent wake of the first blade ring move in chronological succession.
- the trailing pieces are averaged over time, so that, computationally, a coherent trailing occurs, which strikes the third blade ring.
- Another simplifying assumption of the patented method is that the flow of the wake by the second blade ring is to take place only on a flow surface and is not taken into account that the caster also arranges radially differently.
- the European Patent EP 1 201 877 B 1 also protects a generic method for flow optimization, which is also illustrated by the example of two relative to each other to be positioned vane rings with a coaxially arranged between them blade ring.
- a generic method for flow optimization which is also illustrated by the example of two relative to each other to be positioned vane rings with a coaxially arranged between them blade ring.
- the size of the entropy is called. However, it is also said that there may be other parameters that vary in size without specifying them. In any case, select one of the identified zones and direct it to the leading edges of the blade profiles of the third blade ring. The at least one non-selected zone may pass in the blade airfoil space. It is acknowledged that it may be necessary to evaluate various parameters. It may also be necessary, for. For example, it is necessary first to guide the zone of greater entropy and then the zone of smaller entropy to the entry edges and thereby to determine computationally / experimentally which measure leads to an increase in efficiency. Basically, this patent teaches a trial-and-error principle that forces the skilled person to take several different measures.
- the object of the present invention is to propose a clear, unambiguous method for flow optimization in multi-stage turbomachinery, which offers a higher probability of success, than the known methods.
- the tolerance angle is ⁇ 10% of the blade pitch angle of the third blade ring.
- FIG. 1 shows in the form of a diagram the qualitative course of the current density pu (y) or in the incompressible limit the course of the velocity u (y) of a flowing, frictional medium in the region of a component surface, such as the surface of a flow-around blade profile.
- the coordinate y is selected at least approximately perpendicular to the flow direction and thus also approximately perpendicular to the component surface flowed around.
- the coordinate y is preferably defined perpendicular to a local tangent of the surface of the blade profile.
- the velocity u (y) at the component surface is "zero".
- the current density pu (y) and the velocity u (y) increase according to the course of a continuous, curved curve up to a value ⁇ e u e (y e ), where y e is the value the speed no longer changes through the viscous boundary layer.
- the value y e corresponds - at least fairly accurately - to the local boundary layer thickness.
- the frictional, curved current density or velocity course is replaced by a friction-free course with a constant current density ⁇ e u e or speed u e .
- the component surface is fictively shifted by the value of the displacement thickness ⁇ * (delta star), ie a blade profile is fictionally thickened accordingly.
- the frictionless flow model the same mass flow must be obtained as for the actual, frictional flow.
- ⁇ * ⁇ 0 y e 1 - ⁇ u y p e ⁇ u e y e d y .
- ⁇ e , u e and y e are the corresponding values at the boundary layer edge.
- ⁇ * is thus the y value whose horizontal line intersects the current density pu (y) in such a way that two equal areas are included below and above the ⁇ * line between it and the velocity curve pu (y).
- These two surfaces are in Fig. 1 hatched diagonally opposite. The surfaces are bounded laterally by the vertical y-axis and a vertical line by ⁇ e u e (y e ).
- the line does not have to be a vertical, but can also be inclined to the y-axis by the change in the outer velocity in the flow outside the boundary layers between the pressure and suction side. See the dashed curves in FIG. 1 , Since ⁇ * changes periodically with periodically arranged blade profiles of the upstream rotating blade ring with the time t, is FIG. 1 as a "snapshot" at a given time in a particular place to look at.
- the time profile of ⁇ * must be determined over at least one period, in each case for the pressure side DS and the suction side SS of the considered blade profile.
- FIG. 2 shows qualitatively the determination of the so-called obstruction V of the displacement thickness for the pressure side ⁇ * DS and the displacement thickness for the suction side ⁇ * SS of a blade profile.
- the courses of the displacement thicknesses are respectively plotted positively above the time axis t. It can be seen that the maxima of ⁇ * DS and ⁇ * SS are different in size (high) and offset in time.
- the time course of the obstruction V results from additive superimposition of the profiles of the displacement thicknesses of ⁇ * DS and ⁇ * SS . Accordingly, the maximum of the obstruction V max is temporally between the time-offset maxima of the displacement thicknesses.
- the maximum of the obstruction V max is presently to be determined in the region of the trailing edge of a blade profile and can alternatively be determined from the distribution perpendicular to the trailing edge N of the blade profile in the region downstream of the trailing edge.
- the local blade profile thickness D is added as a further additive quantity to the displacement thicknesses ⁇ * DS and ⁇ * SS .
- the term "in the area of the trailing edge of a blade profile" is intended to mean that the location for determining the maximum obstruction near the trailing edge can be selected within the airfoil, directly at the trailing edge, or near the trailing edge downstream of the airfoil. Ultimately, it is important that the further path of the maximum of the obstruction is determined correctly.
- FIG. 3a shows a longitudinal section through a bladed flow channel with a static housing 46 and with a rotating hub 47.
- Leitschaufelkränze 48, 50 are arranged with the hub 47 rotate blade rings 49,51.
- curved contour is shown in each case. Within the flow channel, three more curved lines can be seen. These are the intersections of three rotational flow surfaces ⁇ 2 ⁇ ⁇ . ⁇ 6 ⁇ ⁇ and ⁇ 10 ⁇ ⁇ with the selected, axial-radial cutting plane.
- the stream surfaces correspond to the spatial trajectories of selected "fluid particles".
- FIG. 3b shows the implementation of the process principle on the hardware, ie at flow arranged in series blade rings.
- the flow takes place here from left to right, ie from the blade ring 1 to the blade ring 3.
- three adjacent blade rings 1 to 3 are considered, of which the first blade ring 1 and the third blade ring 3 belong to the same unit “stator” or "rotor”
- the second blade ring 2 belongs to the respective complementary unit “rotor” or “stator”.
- the blade rings 1 and 3 belong to the stator, ie be Leitschaufelkränze.
- the blade ring 2 should belong to the rotor, ie be a blade ring.
- the representation according to FIG. 3b For the sake of better clarity, only the blade profiles 18, 19, 20 of the blades 4, 5, 6, 20 are shown on a specific flow surface, ie in a flow area cut.
- the leading edges of the blade profiles 18,19,20 carry the reference numerals 25,26,27, the exit edges the reference numerals 35,36,37.
- the upstream blade profiles 18 generate so-called wake N, ie flow areas with turbulence and at reduced speed in the desired flow direction due to friction.
- each caster N has a circumferential and a meridional component, which in turn can be composed of an axial and a radial component, so that each caster N enters the region of the moving second blade ring 2 and of its successive blade profiles 19 in Separate pieces is divided, which move through the flow channels between the blades 5 and interact with the pressure and suction side boundary layers of the blade profiles 19 in correlation.
- the blade profiles 19 are in the region of the exit edges 36 there to detect periodically occurring maxima of the obstruction V max locally and temporally in the procedure according to FIG FIGS.
- the further path of the respective maximum of the obstruction V max is to be traced into the region of the entry edges 27 of the blade profiles 20 of the third, static blade ring 3.
- the maximum of the obstruction V max should strike an entrance edge 27 within a predetermined tolerance angle ⁇ wt.
- This tolerance angle is for example ⁇ 15% of the blade pitch angle wt of the third blade ring 3, ie it extends on both sides of the leading edge 27 by 15% in the circumferential direction.
- the entire angular range is thus 30% of the blade pitch angle wt of the third blade ring 3. If the measurements or calculations show that the maxima of the obstruction V max actually hit the inlet edges of the third blade ring 3 within the predetermined tolerance angle ⁇ wt, the desired flow optimization has been achieved ,
- the closest measure is likely to be a relative rotation of the blade rings 1 and 3, ie a relative, limited angular movement in the circumferential direction about the longitudinal center axis of the blade rings. After optimization, it must be ensured that the relative positioning during removal and installation or during operation is not unintentionally changeable.
- Another obvious measure is the axial displacement of at least one of the blade rings 1,2,3, but preferably the blade ring 1 relative to the blade ring 2 to move axially. The same effect is achieved by axial displacement of the blade profiles relative to their carrier, ie relative to the disc, the hub, the shroud, etc. This is usually already associated with further structural changes.
- the present optimization method will typically not be limited to only one radial flow area, i. in a stream area intersection, but in several, distributed over the radial extent of the airfoil stream surface sections is performed.
- FIG. 4 shows in axial view on stator trailing edges, the three blades 7,8,9, which emanate from a common foot area, but extend differently over their radial height.
- the blade 7 shown in solid lines runs straight and radially, ie, rather conventionally “threaded”, ie the profile cuts are placed at the same circumferential position at each trailing edge.
- the blade 8 shown in dashed lines runs straight, but with an inclination in the circumferential direction. This is also called “lean”.
- the dot-dashed blade 9 has a curvature in the circumferential direction, a so-called “bow” on. In fact, with such changes, a relative circumferential displacement of the radially superposed profile cuts is achieved.
- FIG. 5 shows a view of two rotor blades 10,11 in the circumferential direction.
- the vane 10 shown in solid lines with the leading edge 28 and the trailing edge 38 has a trapezoidal, more conventional outline.
- the blade 11 shown in dashed lines has an axially curved leading edge and an axially curved exit edge 39 in the same direction. This is also referred to as "axial bow” or “sweep” and causes primarily a relative displacement of the profile sections in the axial direction.
- FIG. 6 shows a view of two blades 12,13 in the circumferential direction.
- the blade 12 shown in solid lines with the inlet edge 30 and the outlet edge 40 corresponds in its trapezoidal, conventional outline of the blade 10 FIG. 5
- the blade 13 shown in dashed lines has the blade root 12 and the blade tip together with the blade 12.
- Their leading edge 31 and their trailing edge 41 are bent in opposite directions outwards, so that a bulbous blade outline is formed. This measure is also referred to as "barreling".
- the axial length of the profile sections is primarily increased, wherein the magnification in the region of the average radial height is most pronounced.
- only another arbitrary profile cut can be common.
- FIG. 7 shows a profile section through two blades 14,15 with the same blade profiles 21,22 in different position.
- the entry edges are designated 32.33, the exit edges 42.43.
- the blade profile 22 shown in dashed lines is intended to be rotated relative to the blade profile 21 shown in solid lines around the threading axis (not reproduced here).
- the leading edge 32 and the trailing edge 42 of the blade 21 are more circumferentially offset than the leading edge 33 and the trailing edge 43 of the blade 22. This measure is also referred to as "twisting". With the rotation, both the inflow and the outflow of such a blade lattice changes directionally.
- FIG. 8 finally shows a profile section through two blades 16,17 with the same inflow and different outflow.
- the two blade profiles 23 and 24 have a common leading edge 34 and a common "nose contour".
- the blade profile 23 shown in solid lines causes by a stronger profile curvature and a stronger flow deflection up to its trailing edge 44.
- the blade profile 24 shown in dashed lines deflects the flow less up to its trailing edge. This measure is also known as "vortexing".
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP05010100A EP1724440B1 (de) | 2005-05-10 | 2005-05-10 | Verfahren zur Strömungsoptimierung in mehrstufigen Turbomaschinen |
ES05010100T ES2310307T3 (es) | 2005-05-10 | 2005-05-10 | Procedimiento para la optimizacion de la corriente en motores de turbopropulsion de varias fases. |
DE502005004938T DE502005004938D1 (de) | 2005-05-10 | 2005-05-10 | Verfahren zur Strömungsoptimierung in mehrstufigen Turbomaschinen |
US11/431,365 US7758297B2 (en) | 2005-05-10 | 2006-05-10 | Method for flow optimization in multi-stage turbine-type machines |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP05010100A EP1724440B1 (de) | 2005-05-10 | 2005-05-10 | Verfahren zur Strömungsoptimierung in mehrstufigen Turbomaschinen |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1724440A1 EP1724440A1 (de) | 2006-11-22 |
EP1724440B1 true EP1724440B1 (de) | 2008-08-06 |
Family
ID=35715003
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP05010100A Not-in-force EP1724440B1 (de) | 2005-05-10 | 2005-05-10 | Verfahren zur Strömungsoptimierung in mehrstufigen Turbomaschinen |
Country Status (4)
Country | Link |
---|---|
US (1) | US7758297B2 (es) |
EP (1) | EP1724440B1 (es) |
DE (1) | DE502005004938D1 (es) |
ES (1) | ES2310307T3 (es) |
Families Citing this family (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7967571B2 (en) * | 2006-11-30 | 2011-06-28 | General Electric Company | Advanced booster rotor blade |
FR2925106B1 (fr) * | 2007-12-14 | 2010-01-22 | Snecma | Procede de conception d'une turbine multi-etages de turbomachine |
US20090317237A1 (en) * | 2008-06-20 | 2009-12-24 | General Electric Company | System and method for reduction of unsteady pressures in turbomachinery |
US8540490B2 (en) * | 2008-06-20 | 2013-09-24 | General Electric Company | Noise reduction in a turbomachine, and a related method thereof |
US8439626B2 (en) * | 2008-12-29 | 2013-05-14 | General Electric Company | Turbine airfoil clocking |
JP5374199B2 (ja) * | 2009-03-19 | 2013-12-25 | 三菱重工業株式会社 | ガスタービン |
JP2011241791A (ja) * | 2010-05-20 | 2011-12-01 | Kawasaki Heavy Ind Ltd | ガスタービンエンジンのタービン |
US10287987B2 (en) | 2010-07-19 | 2019-05-14 | United Technologies Corporation | Noise reducing vane |
US9500085B2 (en) * | 2012-07-23 | 2016-11-22 | General Electric Company | Method for modifying gas turbine performance |
US20140068938A1 (en) * | 2012-09-10 | 2014-03-13 | General Electric Company | Method of clocking a turbine with skewed wakes |
US20140072433A1 (en) * | 2012-09-10 | 2014-03-13 | General Electric Company | Method of clocking a turbine by reshaping the turbine's downstream airfoils |
US9435221B2 (en) | 2013-08-09 | 2016-09-06 | General Electric Company | Turbomachine airfoil positioning |
EP2918777B1 (en) * | 2014-03-11 | 2016-10-26 | United Technologies Corporation | Method for optimizing a vane to reduce noise |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3347520A (en) * | 1966-07-12 | 1967-10-17 | Jerzy A Oweczarek | Turbomachine blading |
JPS54114618A (en) * | 1978-02-28 | 1979-09-06 | Toshiba Corp | Moving and stator blades arranging method of turbine |
US5486091A (en) * | 1994-04-19 | 1996-01-23 | United Technologies Corporation | Gas turbine airfoil clocking |
IT1320722B1 (it) * | 2000-10-23 | 2003-12-10 | Fiatavio Spa | Metodo per il posizionamento di schiere di stadi di una turbina,particolarmente per motori aeronautici. |
DE10053361C1 (de) * | 2000-10-27 | 2002-06-06 | Mtu Aero Engines Gmbh | Schaufelgitteranordnung für Turbomaschinen |
DE10237341A1 (de) * | 2002-08-14 | 2004-02-26 | Siemens Ag | Modell, Berechnung und Anwendung periodisch erzeugter Kantenwirbel im Turbomaschinenbau |
-
2005
- 2005-05-10 DE DE502005004938T patent/DE502005004938D1/de active Active
- 2005-05-10 ES ES05010100T patent/ES2310307T3/es active Active
- 2005-05-10 EP EP05010100A patent/EP1724440B1/de not_active Not-in-force
-
2006
- 2006-05-10 US US11/431,365 patent/US7758297B2/en not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
DE502005004938D1 (de) | 2008-09-18 |
US7758297B2 (en) | 2010-07-20 |
ES2310307T3 (es) | 2009-01-01 |
EP1724440A1 (de) | 2006-11-22 |
US20060257238A1 (en) | 2006-11-16 |
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