US20150030431A1 - Blade ring for an axial turbomachine, and a method for adjusting the maximum flow rate of said blade ring - Google Patents

Blade ring for an axial turbomachine, and a method for adjusting the maximum flow rate of said blade ring Download PDF

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Publication number
US20150030431A1
US20150030431A1 US14/373,818 US201214373818A US2015030431A1 US 20150030431 A1 US20150030431 A1 US 20150030431A1 US 201214373818 A US201214373818 A US 201214373818A US 2015030431 A1 US2015030431 A1 US 2015030431A1
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United States
Prior art keywords
blade
ring
blade ring
flow rate
maximum flow
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.)
Abandoned
Application number
US14/373,818
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English (en)
Inventor
Armin de Lazzer
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
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: DE LAZZER, ARMIN
Publication of US20150030431A1 publication Critical patent/US20150030431A1/en
Abandoned 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
    • 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
    • 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
    • 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
    • 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
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/167—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes of vanes moving in translation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2220/00—Application
    • F05B2220/30—Application in turbines
    • F05B2220/301—Application in turbines in steam turbines
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/31—Application in turbines in steam turbines

Definitions

  • the invention relates to a blade ring for an axial turbomachine, an axial turbomachine having the blade ring and a method for adjusting the maximum flow rate of the blade ring.
  • the maximum process steam mass flow rate which can be fed through the steam turbine is one of the decisive variables in the configuration of the steam turbine and is termed the maximum flow rate of the steam turbine.
  • the guide blade rings of the steam turbine have a multiplicity of guide blades which are arranged evenly distributed around the circumference, blade ducts being formed between the guide blades. Radially, the blade ducts are delimited on the hub side by a hub contour and on the housing side by a housing contour.
  • the maximum flow rate of the steam turbine is decisively influenced by the maximum flow rate of the first guide blade ring, which is substantially determined by the totality of all the effective cross sections of the blade ducts of the first guide blade ring.
  • the maximum flow rate of newly manufactured steam turbines is subject to certain imprecisions on account of manufacturing tolerances and assembly tolerances of components of the steam turbine. Further, the maximum flow rate changes on account of ageing of the components. It is thus often necessary to correct the maximum flow rate of the steam turbine in order to once again be able to operate the steam turbine in the rated state.
  • guide blades which are in operation are exchanged for new guide blades with an improved profile with respect to the maximum flow rate of the steam turbine.
  • all the guide blades of an affected blade ring are exchanged, which is however very laborious and cost-intensive.
  • the trailing edge of the guide blades can be shortened.
  • the maximum flow rate of the guide blade ring can only be increased thereby, and the shortening often leads to worse aerodynamic properties and to lower mechanical strength of the guide blades.
  • the invention is based on an object of providing a blade ring for an axial turbomachine, the axial turbomachine having the blade ring and a method for adjusting the maximum flow rate of the blade ring, with the abovementioned problems being overcome and in particular the maximum flow rate of the axial turbomachine being changeable in a correcting manner.
  • the blade ring according to the invention for an axial turbomachine has an outer face which is arranged on an outer ring and is oriented radially inward, and an inner face which is arranged on an inner ring and is oriented radially outward, which faces are arranged concentrically and parallel with one another and delimit an annular flow duct which tapers in the main flow direction of the axial turbomachine, and at least one adjustment blade which is arranged such that it can be displaced, in the flow duct, parallel to a side line of one of the faces by a guiding device, and which can be secured in a predetermined position on at least one of the rings.
  • a side line is distinguished by the fact that it is arranged on one of the two faces and is directed toward the imaginary tip of the respective face.
  • the diameter of the flow duct decreases in the direction of the tapering of the inner face and of the outer face. If the at least one adjustment blade is displaced in the tapering direction with the aid of the guiding device, its distance in the circumferential direction to the blades which are arranged adjacent thereto in the blade ring decreases, by which the closure of the flow duct, for the fluid flowing through the flow duct, increases and the maximum flow rate of the blade ring decreases accordingly. Similarly, the maximum flow rate can be increased by displacing the at least one adjustment blade, with the aid of the guiding device, counter to the tapering direction. The maximum flow rate of the blade ring can thus advantageously be simply changed by actuating the guiding device.
  • the maximum flow rate of the blade ring changes on account of ageing of components of the axial turbomachine or if the maximum flow rate has to be matched to parameters which themselves are changing, such as a change in process steam mass flow rate. Furthermore, the maximum flow rate can be corrected in order to compensate for manufacturing tolerances or assembly tolerances of a newly manufactured axial turbomachine. It is conceivable that the inner ring is formed as a disk.
  • the outer face and the inner face are preferably conical faces.
  • the outer face and the inner face preferably have, in segments along the respective side line, identical radii of curvature in every cross section perpendicular to the axis of the flow duct such that, when the adjustment blade is displaced, the radial gaps between the adjustment blade and the faces remain constant.
  • each of the cross sections of the outer face and of the inner face is preferably in each case formed, perpendicular to the axis of the flow duct, from a polygon or from a plurality of circle segments which are arranged immediately adjacent to one another.
  • the blade ring is preferably a diagonal stage of the axial turbomachine.
  • the diagonal stage advantageously has the flow duct which is delimited by the two conical faces.
  • the blade ring is preferably a guide blade ring having static, non-rotating guide blades and a static, non-rotating inner face and outer face.
  • the blade ring has a plurality of blades, wherein the blades are, in alternation, the adjustment blades and blades which are securely attached to the outer face and/or to the inner face.
  • Each of the securely attached blades is preferably made in one piece together with the inner ring and the outer ring or in one piece together with a segment of the inner ring and a segment of the outer ring. This advantageously results in high stiffness of the blade ring.
  • the blade ring is advantageously easily accessible for a production tool during production of the blade ring.
  • the guiding device has a sliding groove in the inner ring and/or in the outer ring, and a peg on the radial outer side and/or on the radial inner side of the adjustment blade, wherein the peg engages in the sliding groove.
  • the guiding device preferably has, in at least one of the sliding grooves downstream in the main flow direction of the axial turbomachine, an endstop by which the adjustment blade can be secured in the predetermined position.
  • the adjustment blade is pressed against the endstop by the fluid flowing in the flow duct, thus securing the adjustment blade.
  • the position of the adjustment blade in the flow duct may be defined, for example, by introducing a spacer against the endstop.
  • the spacer can for example be securely attached to the outer ring and/or the inner ring by grub screws and/or welding points.
  • the guiding device is preferably set up such that the at least one adjustment blade can be exchanged for another adjustment blade.
  • the at least one adjustment blade can be exchanged for the other adjustment blade having different aerodynamic properties.
  • the maximum flow rate can be adapted by a suitable swap, in that for example the other adjustment blade has a profile having a shorter or longer chord length.
  • the axial turbomachine according to the invention has the blade ring according to the invention.
  • the maximum flow rate of the axial turbomachine is preferably determined by the maximum flow rate of the blade ring.
  • the method according to the invention for adjusting the maximum flow rate of the blade ring has the following steps: predetermining a setpoint value for the maximum flow rate of the blade ring; determining the actual value of the maximum flow rate of the blade ring; comparing the actual value of the maximum flow rate of the blade ring with the setpoint value for the maximum flow rate of the blade ring; displacing the at least one adjustment blade by the guiding device parallel to the side line such that the setpoint value for the maximum flow rate is the same as the actual value of the maximum flow rate; securing the adjustment blade with the guiding device. If the maximum flow rate of the axial turbomachine is defined by the maximum flow rate of the blade ring, the maximum flow rate of the axial turbomachine can be changed by displacing the at least one adjustment blade.
  • FIGURE shows a longitudinal section through an axial turbomachine having a preferred embodiment of the blade ring according to the invention.
  • an axial turbomachine 1 has a housing 22 , a shaft 21 and a plurality of blade rings 11 to 13 .
  • a fluid 25 can be made to flow within the housing 22 , in a main flow direction 17 .
  • the FIGURE shows a first guide blade ring 11 , a rotor blade ring 12 and a second guide blade ring 13 which are arranged in this order in the main flow direction 17 of the fluid 25 .
  • the first guide blade ring 11 has an outer conical ring 24 which is attached to the housing 22 and has a radially inward-facing conical outer face 2 and, within the outer conical ring 24 , an inner conical ring 23 which has a radially outward-facing conical inner face 3 .
  • the conical outer face 2 and the conical inner face 3 are arranged concentrically with one another, have an identical taper angle 18 , are arranged parallel to each other in every axial section and delimit an annular flow duct 4 .
  • the inner conical ring 23 and the outer conical ring 24 are frusta. It is however also conceivable for the inner conical ring 23 to include its cone tip.
  • the cone axes 26 of the conical outer face 2 and of the conical inner face 3 coincide with the shaft axis 27 .
  • the conical faces 2 , 3 are oriented such that the outer diameter 28 (the figure shows half the outer diameter 28 ) of the flow duct 4 decreases in the main flow direction 17 .
  • the inner conical ring 23 and the outer conical ring 24 are modified such that the conical inner face 3 and the conical outer face 2 have, in segments along the respective side line 6 and along the breadth of the adjustment blade 7 , identical radii of curvature in every cross section perpendicular to the shaft 21 such that, when the adjustment blade 7 is displaced, the radial gaps between the adjustment blade 7 and the conical faces 2 , 3 remain constant.
  • the radii of curvature to be of infinite size, such that each of the cross sections of the conical faces 2 , 3 perpendicular to the shaft 21 in each case forms a polygon, one blade being arranged on each of the straight line segments of the polygon. The length of each of the straight line segments of the polygon becomes shorter downstream in the main flow direction 17 .
  • each of the cross sections perpendicular to the shaft 21 is formed from a plurality of circle segments.
  • the radii of curvature of the circle segments can in this context be either greater or less than the radii of the flow duct 4 . Downstream in the main flow direction 17 , the extent of each of the circle segments becomes shorter, whereas the radius of curvature remains constant in each case.
  • An adjustment blade 7 is arranged within the flow duct 4 and is arranged with its radial outer side 9 on the conical outer face 2 and with its radial inner side 10 on the conical inner face 3 .
  • the adjustment blade 7 has a peg 15 both on its radial inner side 9 and on its radial outer side 10 , the pegs 15 respectively engaging in a sliding groove 14 in the inner conical ring 23 and in the outer conical ring 24 .
  • the sliding grooves 14 are arranged mutually parallel and run in each case along a side line 6 of the conical faces 2 , 3 such that the adjustment blade 7 can be displaced parallel to the side lines 6 .
  • the adjustment blade 7 is displaced in the main flow direction 17 , the distance in the circumferential direction between the adjustment blade 7 and the blades arranged adjacent thereto in the first guide blade ring 11 is reduced, whereby the closure for the fluid 25 in the first guide blade ring 11 increases. As a consequence of the increasing closure, the maximum flow rate of the first guide blade ring 11 is reduced. Conversely, the maximum flow rate can be increased by the adjustment blade 7 being displaced upstream in the main flow direction 17 .
  • the greatest possible displacement path 8 of the adjustment blade 7 is limited by the length of the flow duct 4 in the main flow direction 17 and the length of the sliding grooves 14 . In order to change the maximum flow rate, it is also conceivable that the adjustment blade 7 is replaced by another adjustment blade having a shorter or longer chord length.
  • the sliding grooves 14 and the pegs 15 such as a T-shape or a dovetail.
  • the sliding groove 14 in the conical inner face 3 is limited in the main flow direction 17 by an endstop 29 , i.e. it does not continue as far as the downstream end 5 of the flow duct 4 such that, when the axial turbomachine 1 is in operation, the adjustment blade 7 is pressed against the endstop 29 by the flow of the fluid 25 .
  • spacers 16 are provided in the sliding grooves 14 in order to fix the position of the adjustment blade 7 .
  • the spacers 16 are arranged both on the downstream side of the pegs 15 and on the upstream side of the pegs 15 . It is in principle possible not to provide any spacers 16 on the upstream side as, in operation, the adjustment blade 7 is pressed against the downstream spacers 16 or against the end of the sliding groove 14 . The smallest possible maximum flow rate for the adjustment blade 7 is reached when none of the spacers 16 is provided on the downstream side.
  • All the blades in the first guide blade ring 11 are formed as the adjustment blades 7 and are thus of displaceable design.
  • the blades could alternately be formed as the adjustment blades 7 and securely attached to the conical faces 2 , 3 .
  • the inner conical ring 23 , the outer conical ring 24 and the securely attached blades are made out of a single piece.
  • a securely attached blade is made out of a single piece together with in each case a segment of the inner conical ring 23 and of the outer conical ring 24 and thus the first guide blade ring 11 is composed of a multiplicity of segments.
  • the adjustment blades 7 are equally provided for a rotor blade ring.
  • the inner conical ring 23 is securely connected to the shaft 21 and the adjustment blade 7 is displaceably arranged, by its radial inner side 10 , on the inner conical ring 23 .
  • the inner conical ring 23 and the adjustment blade 7 are thus rotating components of the axial turbomachine 1 .
  • a gap could be provided between the radial outer side 9 of the displaceable blade 7 and the conical outer face 2 .
  • the adjustment blade 7 could also be in engagement, via its radial outer side 9 , with the outer conical ring 24 .
  • the outer conical ring 24 would also be a rotating component.
  • Adjusting the maximum flow rate of the first guide blade ring 11 is performed as follows: predetermining a setpoint value for the maximum flow rate of the blade ring 11 ; determining the actual value of the maximum flow rate of the blade ring 11 ; comparing the actual value of the maximum flow rate of the blade ring 11 with the setpoint value for the maximum flow rate of the blade ring 11 ; displacing the at least one adjustment blade 7 by the guiding device parallel to the side line 6 such that the setpoint value for the maximum flow rate is the same as the actual value of the maximum flow rate; securing the adjustment blade 7 with the guiding device.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US14/373,818 2012-02-02 2012-11-07 Blade ring for an axial turbomachine, and a method for adjusting the maximum flow rate of said blade ring Abandoned US20150030431A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP12153630.4 2012-02-02
EP12153630.4A EP2623717A1 (fr) 2012-02-02 2012-02-02 Couronne d'aube pour une turbomachine axiale et procédé d'ajustement de la capacité de débit massique de la couronne d'aube
PCT/EP2012/071992 WO2013113415A1 (fr) 2012-02-02 2012-11-07 Couronne d'aubes d'une turbomachine axiale et procédé permettant d'ajuster la capacité de débit de la couronne d'aubes

Publications (1)

Publication Number Publication Date
US20150030431A1 true US20150030431A1 (en) 2015-01-29

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Application Number Title Priority Date Filing Date
US14/373,818 Abandoned US20150030431A1 (en) 2012-02-02 2012-11-07 Blade ring for an axial turbomachine, and a method for adjusting the maximum flow rate of said blade ring

Country Status (5)

Country Link
US (1) US20150030431A1 (fr)
EP (2) EP2623717A1 (fr)
JP (1) JP5855768B2 (fr)
CN (1) CN104105844B (fr)
WO (1) WO2013113415A1 (fr)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
IT201700061762A1 (it) * 2017-06-06 2018-12-06 Ansaldo Energia Spa Gruppo statorico per uno stadio di espansione radiale-assiale di turbina a vapore

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US3056258A (en) * 1960-01-26 1962-10-02 Bristol Siddeley Engines Ltd Aircraft propulsion power units
US3233867A (en) * 1963-01-11 1966-02-08 Hitachi Ltd Turbines
FR1380659A (fr) * 1963-10-21 1964-12-04 Steinmueller Gmbh L & C Dispositif pour amener et régler un courant tourbillonnaire
GB1107520A (en) * 1965-11-29 1968-03-27 Bbc Brown Boveri & Cie Expansion compensator for pipelines
US3428243A (en) * 1966-10-20 1969-02-18 Rolls Royce Compressors or turbines for gas turbine engines
US3567331A (en) * 1969-07-25 1971-03-02 Gen Motors Corp Variable vane cascades
GB1378346A (en) * 1971-02-19 1974-12-27 Mtu Muenchen Gmbh Variable stator vane cascade for turbomachines
US3829237A (en) * 1972-06-27 1974-08-13 Nasa Variably positioned guide vanes for aerodynamic choking
US4315714A (en) * 1977-05-09 1982-02-16 Avco Corporation Rotary compressors
US4391564A (en) * 1978-11-27 1983-07-05 Garkusha Anatoly V Exhaust pipe of turbine
US4497171A (en) * 1981-12-22 1985-02-05 The Garrett Corporation Combustion turbine engine
US4579507A (en) * 1981-12-22 1986-04-01 The Garrett Corporation Combustion turbine engine
US4671738A (en) * 1982-10-13 1987-06-09 Rolls-Royce Plc Rotor or stator blades for an axial flow compressor
US4674951A (en) * 1984-09-06 1987-06-23 Societe Nationale D'Etude et de Construction de Meteur D'Aviation (S.N.E.C.M.A.) Ring structure and compressor blow-off arrangement comprising said ring
US5209634A (en) * 1991-02-20 1993-05-11 Owczarek Jerzy A Adjustable guide vane assembly for the exhaust flow passage of a steam turbine
DE4425344A1 (de) * 1994-07-18 1996-01-25 Abb Patent Gmbh Drehschieber mit mindestens einem Axialnadeldrehkranz als drehbewegliches Lagerelement
US6910855B2 (en) * 2000-02-02 2005-06-28 Rolls-Royce Plc Rotary apparatus for a gas turbine engine
US7234917B2 (en) * 2000-02-02 2007-06-26 Rolls-Royce Plc Rotary apparatus for a gas turbine engine
US20100236213A1 (en) * 2006-07-31 2010-09-23 Jan Christopher Schilling Method and apparatus for operating gas turbine engines
US7967571B2 (en) * 2006-11-30 2011-06-28 General Electric Company Advanced booster rotor blade
US20090067981A1 (en) * 2006-12-01 2009-03-12 Parsons Brinckerhoff Limited Flow control device
US20090269187A1 (en) * 2008-04-23 2009-10-29 Rolls-Royce Plc Variable stator vane
US20090297334A1 (en) * 2008-05-27 2009-12-03 Norris James W Gas turbine engine having controllable inlet guide vanes
US20110167791A1 (en) * 2009-09-25 2011-07-14 James Edward Johnson Convertible fan engine
US20110171007A1 (en) * 2009-09-25 2011-07-14 James Edward Johnson Convertible fan system
US20110167784A1 (en) * 2009-09-25 2011-07-14 James Edward Johnson Method of operating a convertible fan engine
US20110247418A1 (en) * 2010-04-08 2011-10-13 General Electric Company System and method for monitoring a compressor

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WO2013113415A1 (fr) 2013-08-08
EP2623717A1 (fr) 2013-08-07
CN104105844A (zh) 2014-10-15
EP2788586B1 (fr) 2016-01-20
CN104105844B (zh) 2016-03-16
JP5855768B2 (ja) 2016-02-09
EP2788586A1 (fr) 2014-10-15
JP2015506439A (ja) 2015-03-02

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