WO2008155243A1 - Rangée d'aubes directrices - Google Patents

Rangée d'aubes directrices Download PDF

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Publication number
WO2008155243A1
WO2008155243A1 PCT/EP2008/057103 EP2008057103W WO2008155243A1 WO 2008155243 A1 WO2008155243 A1 WO 2008155243A1 EP 2008057103 W EP2008057103 W EP 2008057103W WO 2008155243 A1 WO2008155243 A1 WO 2008155243A1
Authority
WO
WIPO (PCT)
Prior art keywords
blade
axial
along
row
axιa
Prior art date
Application number
PCT/EP2008/057103
Other languages
German (de)
English (en)
Inventor
Thomas Mokulys
Ralf Greim
Said Havakechian
Ivan William Mcbean
Original Assignee
Alstom Technology Ltd
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 Technology Ltd filed Critical Alstom Technology Ltd
Publication of WO2008155243A1 publication Critical patent/WO2008155243A1/fr

Links

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
    • F01D5/146—Shape, i.e. outer, aerodynamic form of blades with tandem configuration, split blades or slotted blades
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/141—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path
    • F01D17/143—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path the shiftable member being a wall, or part thereof of a radial diffuser
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to a guide vane row for an axial turbomachine, in particular an adaptable vane row for controlling the mass flow of a turbine.
  • variable vane rows are often used to control mass flow and control controlled mass flow rates within the bladed flow path. This measure is used in most cases to regulate the flow through the machine in adaptation to different operating conditions. Adjustable guide blade rows therefore allow an enlargement of the operating range of a turbomachine. They are used, for example, in stationary gas and steam turbines for power generation, as well as in compressors and aircraft engines.
  • the vane row functions as a baffle or throttle as disclosed, for example, in WO 2005/054633.
  • a setting of the first blade row is known, which serves to control the thrust while maintaining the passage cross-section and the air mass flow, as shown for example in US 2003/0059291.
  • Known adjustable vane rows are distinguished according to the manner of geometric adjustment.
  • a first type of adjustable rows of vanes for example in WO 2005/054633, the individual vanes of an axial flow-through stage are radially along each one with respect to the axially positioned machine shaft rotated axis to effect a change in the staggering angle.
  • the adjustment of the vanes requires a mechanical device for each vane and a sufficiently wide radial gap on the housing and shaft to allow a non-contact rotation of the vane.
  • a second type of adjustable vane rows as disclosed for example in EP 808992, the blades of an axial turbine stage are each divided into two axially separated parts. To control the mass flow, a portion of each vane is displaced in the circumferential direction, this being realized for all the vanes by a single mechanical movement in the circumferential direction and by a single rotatable ring device.
  • This second type is mainly used in steam turbines.
  • the radial gap on the housing and shaft is smaller than in the first type.
  • the aerodynamic losses at the radial gap are correspondingly smaller. However, these losses increase due to the step-shaped blade profile caused by the movement of the blade parts on the ring device.
  • the object of the present invention is to provide a guide blade row for an axial-type turbomachine, which provides control of the
  • An airfoil row for an axial-type turbomachine has a number of vanes each having a leading and a trailing edge, each one of which first, arranged upstream and a second, the first part arranged downstream part. Both parts extend over the entire, radial longitudinal extent of the blade, wherein the longitudinal direction of the blade corresponds essentially to the radial direction perpendicular to the shaft axis of the turbomachine.
  • the first part includes the leading edge of the blade and a portion of the pressure and suction sides of the blade. In this case, it extends, measured along the axial chord of the blade, over a larger area along the pressure side than along the suction side.
  • the first part is attached to the stationary inner casing of the turbomachine and therefore immovable.
  • the second part comprises the trailing edge of the blade and also a part of the pressure and suction side. He extends, according to the first part, over a smaller area along the pressure side than along the suction side.
  • the second part is attached to a ring on the inner housing, which is movable in the circumferential direction of the turbomachine.
  • the first part of each vane remains fixed, while the second part of each vane is movable by means of the ring in the circumferential direction between an initial position and an end position defined by contact with the adjacent vane.
  • the reverse case namely that the first part is movable and the second part is fixed, is the subject of this invention.
  • the assignment of the fixed and movable part has no relevance.
  • the ring with the second parts of the blades is circumferentially displaced relative to the initial position, so that a gap has opened between the two parts through which flows a part of the mass flow.
  • the mass flow then passes through this gap between the first part and the second part of each blade as well as through the original channel between the second part of each blade and the first part of the blade adjacent in the blade row.
  • the rotatable ring allows varying the width of this gap, the channel width of the original channel and thus also the distribution of the mass flow through the two channels.
  • the second part of each blade In an end position of the ring, that is at maximum displacement of the ring, the second part of each blade is in contact with the first Part of the blade in the vane row adjacent.
  • the gap between the first and second part is now open to the maximum and has expanded to the actual flow channel, since the original channel is now closed.
  • the entire mass flow now flows through this gap, and no mass flow passes through the original flow path between the second part of the blade and the first part of the adjacent blade.
  • the flow channel width represented by the narrowest cross-section of adjacent blades in the end position is smaller than the original channel width in the initial position.
  • the adjustment of the guide vane row thus makes it possible to regulate the flow cross-section of the mass flow in the manner of a baffle or a throttle valve.
  • the exit angle also varies from the guide row, but only slightly and in an aerodynamically advantageous manner, which is a significant advantage of the invention.
  • the mass flow flowing through the original channel between the second part of each blade and the first part of an adjacent blade at the initial position of the ring undergoes a deflection corresponding to the stagger angle of the blades.
  • the mass flow flowing between the first part and the second part of each blade upon displacement of the ring experiences a deflection which is larger in comparison, resulting in a slightly larger exit angle of the flow.
  • the first and second parts of each blade are inventively designed to aerodynamically form the equivalent of a single blade having a single overall aerodynamic smooth profile (i.e., a profile perpendicular to the longitudinal axis of the blade) in the initial and final positions of the ring. Both parts are also designed to each have an aerodynamic smooth axial profile (i.e., a profile parallel to the shaft axis of the machine) when the ring is displaced as a single piece in the mass flow.
  • the gap formed between the first and second part of each blade also has an aerodynamic smooth profile. This makes it possible for the flow through the gap between the first and second part to experience no or at least minimal losses due to flow separation, since there are no abrupt profile changes or step-shaped profiles.
  • the avoidance of flow separation also has the advantage that the Rotor downstream of the guide vane row according to the invention may be made less robust compared to existing rotors, since this must withstand a less turbulent flow. This allows a cost saving in the turbomachine.
  • the first parts and the second parts of the vane are aerodynamically designed in that their axial profiles are aerodynamically smooth and their end regions, i. their with respect to the mass flow through the blade row front and rear edges are provided with curves.
  • the final shape of the curves and radii is created using standard aerodynamic design criteria.
  • detachment tendencies are taken into account, which e.g. be displayed by a high so-called "Boundary Layer Shape Factor".
  • the axial profiles of the first and second part of each blade as well as the profile of the gap between the first and second part are characterized by the features of a parting surface by each blade.
  • the profile of this separation surface according to the invention extends substantially along a curvature which is the same or similar to the curvature of the suction side of the blade.
  • Both boundary surfaces of the gap between the first and second run according to the separation surface parallel to each other. The gap flow between the first and second part undergoes an exit angle according to these parallel boundary surfaces when leaving the gap.
  • This exit angle is slightly greater than the exit angle of the flow through the original channel between the second part of a blade and the first part of the adjacent blade, since the exit angle of the original channel flow is determined by the curvature of the suction side and the pressure side of the adjacent blade. This generates the slightly stronger deflection of the mass flow through the gap between the first and second part of the blades and thereby the regulation of the inlet angle of the flow to the rotor of the machine.
  • the profile of the parting surface for creating the first and second blade part can be seen in two parts.
  • the first and longer part starts at the pressure side of the blade and extends in the direction of the suction side. It runs along a line that corresponds to the axially displaced profile line of the suction side of the entire bucket.
  • An axial displacement means a displacement parallel to the shaft axis of the machine.
  • the profile of the second and shorter part of the parting surface, which extends from the first part to the suction side has a spline, so that a smooth connection to the suction side is created.
  • the location of the interface i. the extent of the axial displacement of the profile line of the suction side, determined by the end edge of the separation surface on the pressure side of the blade.
  • this end edge lies in a range from 80 to 90% of the axial chord of the blade starting from the front edge of the blade.
  • the end edge of the second part of the separation surface on the suction side, starting from the leading edge of the blade, is in a range of 40-60% of the axial chord.
  • the first and second part of a blade are rounded in the region of the end edges of the parting surface.
  • Rounding the first and upstream portions of the blade at the edge where the interface meets the suction side of the blade has a radius of curvature of a minimum size such that flow along the first and second portions does not separate from the profile surfaces.
  • the radius of curvature also has a maximum size, so that the overall profile of the blade with the first and second part in contact with each other, yet aerodynamically smooth.
  • a rounding at the second and downstream part at the edge where the parting surface meets the suction side of the blade forms the leading edge of the second part.
  • This rounding may have a radius of curvature that is equal to or less than the radius of curvature of the leading edge of the first part.
  • the second part at the edge where the interface meets the pressure side of the blade is also rounded.
  • FIGS. 1 to 6 each show a detail of an adjustable guide vane row of a turbomachine according to the invention, the vane row being transposed into a plane.
  • the figures represent a sequence of different positions of the first and second parts of the blades.
  • FIG. 7 shows an embodiment of a single blade in the guide blade row according to the invention with details of the axial profile of the separating surface between the first and second parts of the blade.
  • the profile shown is exemplary of a so-called cylindrical blade. This is constant over the height, also known under prismatic.
  • the invention is also applicable to blades with a profile of variable height, as well as blades formed e.g. have a lean or sweep or have a variable stagger angle above the height.
  • FIG. 1 shows by way of example two blades 1, 2 of a row of guide blades 3 of an axial turbomachine, each having a first upstream part 4, 5 and a second part 6, 7 arranged downstream of the first part 4, 5.
  • the first parts 4, 5 are fixed to a part 8 of the stationary housing of the turbomachine.
  • the second parts 6, 7 are fastened to a ring 9 which can be moved in the circumferential direction of the machine.
  • the first part 4 of the blade 1 is in contact with the second part 6 thereof.
  • the first upstream part 6 is in contact with the blade second part 7.
  • the characterized by an arrow 10 mass flow through the turbomachine flows through a according to the initial position original flow channel 1 1 with a passage cross-section D first
  • the mass flow 10 is deflected by the guide vane row 3 in this initial position in a direction which is characterized by the angle Ch.
  • Figure 2 shows a first adjustment position of the vane row 3.
  • the second parts 6 and 7 of the first parts 4 and 5 moved away.
  • the passage cross-section or channel width of the flow channel 11 is reduced to D 2 , and it has an additional flow channel 12 formed between the first and second parts through which flows a partial mass flow with the flow direction 13. Due to the curvature of the flow channel 12 of the partial mass flow 13 is directed in a direction with the angle ⁇ 2 .
  • the resulting angle of the total mass flow remains almost unchanged.
  • FIGS. 3 to 6 show further positions of the adjustable guide blade row 3, in each case with increasing displacement of the ring 9 in the tangential direction T.
  • the passage cross-section of the flow channel 11 decreases proportionally, the passage cross-section of the flow channel 12 of the partial mass flow 13 correspondingly increasing.
  • the second part 6 of the blade 1 contacts the first part 5 of the blade 2 adjacent in the guide blade row.
  • the partial mass flow 13 now flows in maximum size through the channel 12, the flow channel 11 being closed and the original mass flow 10 has dropped to zero.
  • the passage cross-section D 3 of the flow channel 12 is in the end position, however, smaller than the passage cross-section D 1 of the original flow channel 11 in the initial position according to FIG 1.
  • each intermediate position and the end position due to the aerodynamic design of the first and second parts of the blades, a low-loss flow of the original mass flow 10 and of the partial mass flow 13 is always guaranteed.
  • This can be achieved by the inventive shape of the parts 4-7, as shown for example in Figure 7.
  • Figure 7 shows the axial profile of a single vane 1 or 2 of the adjustable vane row. It is characterized by a front edge 20, a trailing edge 21, as well as a pressure side 22 and a suction side 23.
  • a parting line with profile line 24 divides the blade profile into a first part 25 and a second part 26, corresponding to parts 4, 5, 6 and 7 in FIGS. 1-6.
  • the dividing line extends from the pressure side 22 of the blade to the suction side 23 of the blade and from the blade root in the radial longitudinal direction of the blade to the blade tip.
  • the dividing line 24 has according to the invention a first section 27 and a second end section 28.
  • the two sections together form a continuous line without sharp creases or corner points and in particular flow gently into the profile lines of the suction side and pressure side.
  • the first portion 27 corresponds to a parallel displacement of a part of the profile line of the suction side 23 in the axial direction A.
  • the end portion 28 has a spline to form a connection from the first portion 27 to the suction side 23 continuously and without sharp corners.
  • the regions E and F of the first part and the points G and H of the second part are designed with curves with specifically selected radii of curvature.
  • the rounding at point E must be chosen to be sufficiently gentle.
  • the radius of curvature Ri is approximately equal to the radius of curvature of the leading edge R LE of the first part 25.
  • the radius of curvature Ri at the point E and the radius of curvature of the leading edge R LE are dependent on the selected basic profile shape and the blade load dependent thereon 0.5 ⁇ RjR LE ⁇ 2.0 is selected.
  • the radius of curvature R 2 is arbitrary, but smaller than the radius of curvature R LE of the leading edge of the first part 25.
  • the radius of curvature at the point G can be chosen arbitrarily large.
  • the rounding at point F can be carried out arbitrarily, as it only minimally influences the flow behavior. LIST OF REFERENCE NUMBERS

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

La présente invention a pour objet des aubes directrices (1, 2) d'une rangée réglable d'aubes directrices (3) d'une turbomachine qui comprennent respectivement une première partie (4, 5) immobile et fixée sur le boîtier et une seconde partie (6, 7) mobile et agencée en aval de la première partie, la seconde partie (6, 7) étant fixée sur un anneau (9) réglable. Selon l'invention, la première et la seconde partie (4-7) de chaque aube directrice (1, 2) est conçue de manière lisse et aérodynamique, de manière à ce que, dans toutes les positions de réglage, des pertes d'écoulement minimales soient engendrées. Les première et seconde parties comprennent une ligne de profil qui correspond à un déplacement parallèle de la ligne de profil du côté aspiration des aubes (1, 2). La rangée réglable d'aubes directrices (3) permet de régler et d'étrangler le débit massique (10, 13) et de régler la déviation (α1, α2) du flux.
PCT/EP2008/057103 2007-06-20 2008-06-06 Rangée d'aubes directrices WO2008155243A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH988/07 2007-06-20
CH9882007 2007-06-20

Publications (1)

Publication Number Publication Date
WO2008155243A1 true WO2008155243A1 (fr) 2008-12-24

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PCT/EP2008/057103 WO2008155243A1 (fr) 2007-06-20 2008-06-06 Rangée d'aubes directrices

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102010054914A1 (de) * 2010-12-17 2012-06-21 Daimler Ag Leiteinrichtung für eine Fluidenergiemaschine, insbesondere für einen Abgasturbolader
WO2014133612A1 (fr) * 2013-02-26 2014-09-04 Bloxham Matthew J Composant d'écoulement à géométrie variable de turbine à gaz
EP3404216A1 (fr) * 2017-05-19 2018-11-21 Rolls-Royce plc Agencement de stator
US11149552B2 (en) 2019-12-13 2021-10-19 General Electric Company Shroud for splitter and rotor airfoils of a fan for a gas turbine engine

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2966332A (en) * 1957-06-20 1960-12-27 Fairchild Engine & Airplane Overspeed control for turbine rotor
DE4238550A1 (de) * 1992-11-14 1994-05-19 Daimler Benz Ag Abgasturbolader für eine Brennkraftmaschine
EP1122407A2 (fr) * 2000-02-02 2001-08-08 Rolls Royce Plc Systeme d' aubes de guidage reglable pour un moteur à turbine à gaz
US20030059291A1 (en) * 2001-09-27 2003-03-27 Koshoffer John Michael Method and apparatus for reducing distortion losses induced to gas turbine engine airflow

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2966332A (en) * 1957-06-20 1960-12-27 Fairchild Engine & Airplane Overspeed control for turbine rotor
DE4238550A1 (de) * 1992-11-14 1994-05-19 Daimler Benz Ag Abgasturbolader für eine Brennkraftmaschine
EP1122407A2 (fr) * 2000-02-02 2001-08-08 Rolls Royce Plc Systeme d' aubes de guidage reglable pour un moteur à turbine à gaz
US20030059291A1 (en) * 2001-09-27 2003-03-27 Koshoffer John Michael Method and apparatus for reducing distortion losses induced to gas turbine engine airflow

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102010054914A1 (de) * 2010-12-17 2012-06-21 Daimler Ag Leiteinrichtung für eine Fluidenergiemaschine, insbesondere für einen Abgasturbolader
WO2014133612A1 (fr) * 2013-02-26 2014-09-04 Bloxham Matthew J Composant d'écoulement à géométrie variable de turbine à gaz
US9617868B2 (en) 2013-02-26 2017-04-11 Rolls-Royce North American Technologies, Inc. Gas turbine engine variable geometry flow component
EP3404216A1 (fr) * 2017-05-19 2018-11-21 Rolls-Royce plc Agencement de stator
US11149552B2 (en) 2019-12-13 2021-10-19 General Electric Company Shroud for splitter and rotor airfoils of a fan for a gas turbine engine

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