EP1985805B1 - Machine rotative - Google Patents

Machine rotative Download PDF

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Publication number
EP1985805B1
EP1985805B1 EP07008551A EP07008551A EP1985805B1 EP 1985805 B1 EP1985805 B1 EP 1985805B1 EP 07008551 A EP07008551 A EP 07008551A EP 07008551 A EP07008551 A EP 07008551A EP 1985805 B1 EP1985805 B1 EP 1985805B1
Authority
EP
European Patent Office
Prior art keywords
rib
blade
rotor
blades
rotary machine
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
Application number
EP07008551A
Other languages
German (de)
English (en)
Other versions
EP1985805A1 (fr
Inventor
Anders Joelsson
Andrey Shukin
Sergey Shukin
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
Priority to AT07008551T priority Critical patent/ATE504721T1/de
Priority to DE602007013712T priority patent/DE602007013712D1/de
Priority to EP07008551A priority patent/EP1985805B1/fr
Publication of EP1985805A1 publication Critical patent/EP1985805A1/fr
Application granted granted Critical
Publication of EP1985805B1 publication Critical patent/EP1985805B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/181—Two-dimensional patterned ridged
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/183—Two-dimensional patterned zigzag
    • 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
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/314—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being inclined in relation to each other

Definitions

  • This invention relates to a rotary machine comprising at least one rotor and at least one casing, whereby blades are mounted to the rotor and a clearance between the radial outer end of the blades and the radially opposite facing first surface of the casing is provided, whereby the fist surface is provided with at least one radial protrusion, which is extending in circumferential direction of the rotation of the rotor, wherein the blades at the respective first ends are provided with at least one rib, which rib extends in a height radially outwards and has a longitudinal extending along the blade's tip, which forms an angle ⁇ bigger than 0° with the circumferential direction of the rotation of the rotor.
  • the preferred technical field of application of the invention are rotary machines, in particular gas turbines and steam turbines comprising rotating blades mounted to a rotor, which blades do not comprise shrouds. Due to the increasing shortage of fossil energy resources and the growing awareness to emissions, which are affecting the word climate, the efficiency of machines, which are converting the fossil energy resources to mechanical or electrical power, becomes very important. The majority of power plants are still using steam turbines or gas turbines or a combination of these turbines.
  • a typical rotary machine according to the invention comprises blades mounted to a rotor and comprises a stationary casing with a surface facing the blade tips.
  • the rotating blades in general have a blade profile with a pressure side and a suction side and due to the dynamic pressure difference between pressure side and suction side an impulse drives the rotor.
  • the rotating blades do therefore have an optimized angle, which is formed by the rotor axis and the longitudinal extension of the blade profile - also called stagger angle - under which they are mounted to the rotor. This angle optimum depends on the gas, respectively steam conditions, the pressure difference over the entire blading-stage and the orientation of the gas-flow - respectively steam-flow direction before it enters the blading stage.
  • a very complex flow distribution is always established at the blade tip, where the flow through the clearance between the blade tip and the opposing surface of the casing can be considered as a pressure-loss and has direct negative consequences for the efficiency.
  • a similar problem is encountered in the aviation technology where for example winglets are installed at the end of the wings of an airplane to reduce the loss of the pressure difference between the pressure side and the suction side of the wing.
  • shrouds at the tip of the blade which forms together with the other blades of one stage in the assembled condition a closed ring, which itself has a sealing surface, which corresponds to an opposing sealing surface of the casing.
  • Shrouds do have the disadvantage that their mass causes additional tensile stress in the blade due to centrifugal forces resulting from the mass of the shroud under a high rotational speed. Therefore, radially long blades mounted on a large diameter of the rotor cannot be equipped with shrouds due to constraints from the material.
  • US Patent application US 2003/0175116 A1 describes an abradable coating for a gas turbine wall, which might be touched by a blade tip, wherein the tip of the blade is provided with one or two rims enclosing a cavity on the blades tip, wherein the rims might be chamfered.
  • the US patent US 6,155,778 also describes a blade's tip rubbing at the surface of a perforated shroud, wherein the blade's tip is provided with elongated side walls of the blade's airfoil forming lateral rims on the tip.
  • One object of the invention is to overcome the above mentioned problems and disadvantages and to seal the radial clearance between the blade tip and the opposing casing surfaces to obtain a higher efficiency over the total time of operation without decreasing the operational safety.
  • the blades of a rotary machine of the initial mentioned type are provided at the respective first ends with at least one rib respectively fin, which rib extends in the height radially outwards and has a longitudinal extending, which forms an angle ⁇ bigger than (0 with the circumferential direction of the rotation.
  • the rib on the blade tip is orientated in a direction which crosses the direction of the circumferential protrusions. This arrangement causes an unexpected high pressure drop, which results in an exceptional good sealing of the radial clearance between the blades tip and the corresponding casing surface.
  • the pressure drop from the pressure side to the suction side through the radial clearance can be enlarge when the height of the rib is selected in such a way that during operation the rib gets into contact with at least one protrusion at least at the first operations start.
  • One big advantage of the arrangement according to the invention is, that the protrusions of the casing get in contact with the rips of the blades only at a certain point, which minimizes the contact surface and therefore the heat and the forces generated by this rubbing contact.
  • the rib is designed in such a way, that the heat energy and the forces caused by rubbing do not exceed critical limits and therefore do not damage parts of the turbine.
  • the rib is designed strong enough to cope with the pressure difference between suction side and pressure side and that it is not totally destroyed by rubbing.
  • the best sealing effect can be obtained when the height of the rib is designed in such a way, that material abrasion occurs on the rib caused by the circumferential protrusion.
  • the first radial expansion of the rotor is caused by the blades thermal expansion and the rotors disks' radial elongation due to the centrifugal load.
  • the thermal expansion of the shaft is the last step before thermal equilibrium is established due to the shaft's mass.
  • each protrusion only contacts a point of each respective rib, the abrasion occurs mainly at this point of the rib and not at the circumferential protrusion of the casing, which leads to a cut or a recess in the rib at a special axial position of the protrusion. Therefore, the local abrasion of the rib at the blade's tip caused by the circumferential protrusion does always occur at the same position. Hence the circumferential protrusions fit almost exactly in the abrasion recesses of the ribs, which results in an ideal sealing of the radial clearance.
  • the rib can be an inserted seal strip at the tip of the blade but also can be one piece of material with the blade.
  • a characteristic feature of the transition between the blade and the rib is a tapering resulting in a shoulder at least on one side of the rip, respectively the pressure side or the suction side.
  • Preferred embodiment of the invention is given by a rip, which extends along the circumference of parallel to the circumference of the profile of the blade.
  • the form of the rib on the blades tip can be compared to a crown on the blades tip. This comparison especially becomes valid, where the protrusions caused recesses in the rib due to material abrasion resulting from radial contact.
  • rips can be provided on the blades tip.
  • Figure 1 shows a three-dimensional schematic drawing of an arrangement comprising a turbine blade 2 and a surface 1 of a turbine casing 8, which is extending in a circumferential direction 3 indicated by an arrow and which is facing the blade 2 tips 6.
  • This arrangement belongs to a turbine, wherein the blade 2 is mounted to a rotor 7, which is not shown and which rotates around a longitudinal not shown central axis 11 of the rotor.
  • the blades 2 belong to a group of blades 2 which group is not shown in the drawings, and each blade 2 is mounted in a not shown manner to the rotor 7, so that a ring of blades 2 in a circumferential direction of the rotor 7 is arranged around the rotor.
  • the blade has a pressure side 4 and a suction side 5, so that a pressure difference establishes from the pressure side 4 to the suction side 5.
  • the blade 2 faces the surface 1 of the casing 8.
  • the pressure difference between pressure side 4 and suction side 5 leads to a tendency of a fluid or a gas to flow through a clearance 9 between each blade 2 tip 6 and the surface 1 of the casing 8.
  • This flow results in a partial loss of the pressure difference, which drives the rotor 7 in the turbine and therefore this loss results in a loss of turbine efficiency.
  • the radial clearance 9 is designed in a way, which increases the pressure drop from the pressure side 4 to the suction side 5 of the blade 2.
  • the tip 6 of the blade 2 is equipped with a rib 10, which extends in the height radially outwards and has a longitudinal extending, which forms an angle ⁇ with the circumferential direction of the rotation, which angle ⁇ is bigger than 0.
  • Figure 1 shows a preferred embodiment, wherein the rib 10 extends along the circumference 12 of a blade profile 13 at the tip 6 of the blade 2.
  • the form of the rib 10 can be compared to a crown on the top of the tip 6 of the blade 2.
  • the surface 1 is provided with radial protrusions 20, which are extending in circumferential direction 3 of the rotation of the rotor.
  • Figure 2 shows the blades tip 6 as a cross section and as indicated by position B in figure 1 .
  • Figure 2 shows a hollow blade 2 being closed at the blade tip 14 and having trapezium formed ribs 10, which form a crown on the top of the blade 2 tip 6.
  • Figure 3 and 4 show the arrangement of figure 1 during operation.
  • Figure 3 shows an example of an embodiment according to the state of the art, where an abradable coating was applied to the blade 2 and which is wasted away during operation to a certain degree after turbine start, so that the radial clearance 9 is minimized. This coating is worn away during operation totally.
  • Figure 4 shows the design of the blade 2 tip 14 and the surface 1 of the turbine casing 8 according to the invention and during operation.
  • the pressure drop over the clearance 9 is increased due to the rib 10 at the tip 14 of the blade 2, which got into contact with the protrusions of the surface 1 and became abraded at the locations of the protrusions, so that the form of the rib 10 became a negative image of the form of the surface 1 with the protrusions. Since the protrusions have only a point contact to the rib 10 the heat energy generated during the rubbing is low and so are the forces during the rubbing within the first start up of the turbine.
  • Figure 5 and 6 show the arrangement according to the invention before operation and after operation. Before operation the rib 10 did not have contact to the protrusions of the surface 1 and after operation the protrusion of surface 1 abraded locally the rib 10 so that recesses 16 were machined into the rib 10.
  • FIG. 7 and 8 shows a preferred embodiment of the protrusions, which are of a trapezium form (view I).

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Rotary Pumps (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Valve Device For Special Equipments (AREA)
  • Valve-Gear Or Valve Arrangements (AREA)

Claims (8)

  1. Machine rotative comprenant au moins un rotor ( 7 ) et au moins une enveloppe ( 8 ),
    des aubes ( 2 ) étant montées sur le rotor,
    dans laquelle il est prévu un jeu ( 9 ) entre la première extrémité extérieure radialement des aubes ( 2 ) et une première surface ( 1 ) opposée en face s'opposant radialement de l'enveloppe ( 8 ),
    dans laquelle les premières surfaces ( 1 ) sont munies d'au moins une protubérance ( 20 ) radiale qui s'étend dans la direction circonférentielle de la rotation du rotor ( 7 ),
    dans laquelle les premières extrémités respectives des aubes ( 2 ) sont munies d'au moins une nervure ( 10 ),
    cette nervure ( 10 ) s'étendant à une hauteur radialement vers l'extérieur et ayant une étendue longitudinale le long de la pointe de l'aube, qui fait un angle α plus grand que 0° avec la direction circonférentielle de la rotation du rotor, caractérisée en ce que
    la machine rotative, la nervure ( 10 ) et l'aube ( 2 ) sont conçues de manière à ce que, pendant un fonctionnement, la nervure ( 10 ) vienne en contact avec la protubérance ( 20 ) de la surface ( 1 ) et de manière à ce que la nervure ( 10 ) s'abrase aux emplacements des protubérances ( 20 ), cette abrasion donnant une entaille ou une encoche dans la nervure ( 10 ).
  2. Machine rotative suivant la revendication 1,
    caractérisée en ce que
    la hauteur de la nervure ( 10 ) est choisie de manière à ce que, pendant un fonctionnement, la nervure ( 10 ) vienne en contact avec au moins une protubérance ( 20 ), au moins pendant le premier début du fonctionnement.
  3. Machine rotative suivant la revendication 1 ou 2,
    caractérisée en ce que
    la protubérance ( 20 ) est conçue sous la forme d'une bande d'étanchéité.
  4. Machine rotative suivant la revendication 1, 2 ou 3,
    caractérisée en ce que
    la première surface ( 1 ) est munie d'une pluralité de protubérances ( 20 ) radiales qui s'étendent dans la direction circonférentielle de la rotation du rotor.
  5. Machine rotative suivant la revendication 1, 2, 3 ou 4,
    caractérisée par un angle α compris entre 10° et 90°.
  6. Machine rotative suivant l'une des revendications précédentes,
    caractérisée en ce que
    la protubérance ( 20 ) fait, en chaque point de son étendue, un angle α compris entre 10° et 90° avec la nervure ( 10 ).
  7. Machine rotative suivant l'une des revendications précédentes,
    caractérisée en ce que
    la hauteur des nervures ( 10 ) est comprise entre 0,5mm et 3mm.
  8. Machine rotative suivant l'une des revendications précédentes,
    caractérisée en ce que
    la protubérance ( 20 ) a une hauteur comprise entre 0,5mm et 5mm.
EP07008551A 2007-04-26 2007-04-26 Machine rotative Not-in-force EP1985805B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
AT07008551T ATE504721T1 (de) 2007-04-26 2007-04-26 Rotationsmaschine
DE602007013712T DE602007013712D1 (de) 2007-04-26 2007-04-26 Rotationsmaschine
EP07008551A EP1985805B1 (fr) 2007-04-26 2007-04-26 Machine rotative

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP07008551A EP1985805B1 (fr) 2007-04-26 2007-04-26 Machine rotative

Publications (2)

Publication Number Publication Date
EP1985805A1 EP1985805A1 (fr) 2008-10-29
EP1985805B1 true EP1985805B1 (fr) 2011-04-06

Family

ID=38197853

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07008551A Not-in-force EP1985805B1 (fr) 2007-04-26 2007-04-26 Machine rotative

Country Status (3)

Country Link
EP (1) EP1985805B1 (fr)
AT (1) ATE504721T1 (fr)
DE (1) DE602007013712D1 (fr)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009040298A1 (de) * 2009-09-04 2011-03-10 Mtu Aero Engines Gmbh Strömungsmaschine und Verfahren zur Erzeugung eines strukturierten Einlaufbelags
EP2309098A1 (fr) * 2009-09-30 2011-04-13 Siemens Aktiengesellschaft Profil et aube directrice, aube rotorique, turbine à gaz et turbomachine associées
GB2483059A (en) * 2010-08-23 2012-02-29 Rolls Royce Plc An aerofoil blade with a set-back portion
DE102012106090A1 (de) * 2012-07-06 2014-01-09 Ihi Charging Systems International Gmbh Turbine und Turbine für einen Abgasturbolader
US10794211B2 (en) 2016-04-08 2020-10-06 Raytheon Technologies Corporation Seal geometries for reduced leakage in gas turbines and methods of forming

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6155778A (en) * 1998-12-30 2000-12-05 General Electric Company Recessed turbine shroud
FR2832180B1 (fr) * 2001-11-14 2005-02-18 Snecma Moteurs Revetement abradable pour parois de turbines a gaz

Also Published As

Publication number Publication date
ATE504721T1 (de) 2011-04-15
DE602007013712D1 (de) 2011-05-19
EP1985805A1 (fr) 2008-10-29

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