EP1970531A1 - Rotor d'une turbomachine thermique et turbomachine thermique - Google Patents

Rotor d'une turbomachine thermique et turbomachine thermique Download PDF

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Publication number
EP1970531A1
EP1970531A1 EP07005080A EP07005080A EP1970531A1 EP 1970531 A1 EP1970531 A1 EP 1970531A1 EP 07005080 A EP07005080 A EP 07005080A EP 07005080 A EP07005080 A EP 07005080A EP 1970531 A1 EP1970531 A1 EP 1970531A1
Authority
EP
European Patent Office
Prior art keywords
rotor
tie rod
fluid flow
turbine
force
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.)
Withdrawn
Application number
EP07005080A
Other languages
German (de)
English (en)
Inventor
Francois Dr. Benkler
Walter Loch
Oliver Dr. Schneider
Peter-Andreas Schneider
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 EP07005080A priority Critical patent/EP1970531A1/fr
Publication of EP1970531A1 publication Critical patent/EP1970531A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/025—Fixing blade carrying members on shafts
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins

Definitions

  • the invention relates to a rotor of a thermal fluid machine with a number of individual, held together by a tie rod and assembled into a unit rotor parts.
  • the invention further relates to a thermal turbomachine with such a rotor.
  • the thermal turbomachinery includes steam and gas turbines as well as rotary compressors and jet engines. These usually have a rotatably mounted rotor surrounded by a stationary housing.
  • the fixed components of a thermal turbomachine are collectively referred to as a stator. Between the rotor and the stator, a flow channel extending in the axial direction of the turbomachine for a compressible flow medium is arranged.
  • On the rotor usually in the flow channel projecting and combined into groups of blades or rows of blades blades are attached.
  • the blades serve to drive the rotor shaft by momentum transfer from a hot and pressurized flow medium.
  • the thermal energy of the flow medium is thus converted in its relaxation in mechanical energy that can be used for example to drive an electric generator.
  • a compressor unit and a turbine unit are arranged on a common shaft.
  • the compressor also called a compressor, draws in cold ambient air, compresses it and then feeds it to a combustion chamber where it is burned together with an injected fuel.
  • the hot combustion gases eventually flow under high pressure and at high speed into the turbine unit and drive them. Part of the mechanical energy thus generated is used to drive the compressor, the remaining part being available as usable energy.
  • the rotor of a gas turbine is also referred to as a rotor, wherein a high mechanical and thermal stress is exposed.
  • a rotor Mainly due to the high temperature of the working medium and the forces acting on the rotor forces during operation of the gas turbine, the rotor component is heavily stressed. Nevertheless, in order to be able to ensure operational safety on the one hand and to keep the manufacturing costs of the runner within acceptable limits on the other hand, a large number of design options have been proposed in the past.
  • a proposed embodiment of the rotor for example, by the production of a part feasible.
  • a production method is comparatively complicated in the manufacturing process.
  • no order-independent prefabrication and no parallel processing of individual parts is possible, resulting in high production throughput times.
  • a larger axial distance between the impeller discs must be accepted in order to work with the appropriate tools.
  • these production-related relatively large distances between the wheels worsen the rotor dynamics.
  • the rotor can also be composed of individual rotor parts.
  • the rotor parts of the rotor component are mounted on a shaft and optionally shrunk.
  • the individual rotor parts are held together via a tie rod.
  • the tie rod is guided by an axially extending recess in the rotor parts, whereby the rotor parts can be clamped together.
  • the rotor of the gas turbine is arranged at the end by suitable bearings in the housing of the turbine.
  • the frequency u. a. from the distance between the two thrust bearings, d. H. depends on the free-swinging length of the rotor.
  • This frequency shift can lead to impermissibly high vibration amplitudes during operation of the gas turbine, which impair the function of the rotor and can lead to damage to the turbine.
  • the invention is therefore based on the object to provide a rotor of the type mentioned, which ensures safe operation of the gas turbine even with increasing overall length.
  • the oscillation amplitudes of the tie rod should be kept as small as possible, in particular in the region of the central hollow shaft between turbine and compressor discs.
  • At least one rotor part is clamped or coupled to the tie rod.
  • the invention is based on the consideration that just for the achievement of a high stiffness of the rotor, the rotor parts should be connected to the tie rod, the thermally induced different expansions of the rotor components should still be compensated.
  • the fact should be taken into account that due to the increasing demands on the performance of the turbine whose length increases, whereby the natural frequency of the tie rod approaches the operating speed of the gas turbine.
  • the tie rod should be suitably supported for this purpose between its end bearings inside the rotor to increase its rigidity. This is achieved by virtue of the fact that at least one rotor part provided in the middle region of the rotor is braced directly by a suitable device with the tie rod.
  • a lever device is preferably used for deflecting and / or amplifying the necessary pressure forces.
  • the tension between the rotor part and the tie rod is preferably achieved in that by means of the lever device a coupled to the rotor part pressure pin in the radial direction presses on the tie rod.
  • the tie rod may be provided to increase the strength of the connection with a corresponding to the shape of the pressure bolt, the pressure pin associated recess.
  • one or preferably a plurality of rotor parts are clamped to the tie rod.
  • the rotor parts can be provided with a number of such tensioning devices, these preferably being symmetrical about the tie rod are arranged around. In addition to the increased connection strength thus additionally a centering of the tie rod is possible.
  • the lever device is coupled to an adjusting device.
  • deformations in the material, which can be caused by the compressive forces occurring can be corrected in a simple manner.
  • each lever device is coupled to an adjusting device, but also the pressure force adjustment, in particular all belonging to a rotor part lever devices, by only one adjusting device is conceivable.
  • the tie rod could be automatically centered in the runner part.
  • a possible implementation of this variant can be achieved, for example, in that the lever devices of a rotor part are coupled together in a kind of series connection, wherein at least one lever device is coupled to the adjusting device.
  • the adjusting device is designed as a set screw.
  • a trained adjusting device an introduced force can be continuously transmitted to the lever device in a particularly simple manner by the rotational movement of the screw is converted into a linear movement.
  • an exact adjustment of the tie rod is thus made possible via a coupled with the lever device pressure bolt due to the thread translation of the screw. Also, no additional securing of the positioner is necessary during the bracing process due to the self-locking action of the screw.
  • the adjusting screw designed as an adjusting device should be in addition to be provided a screw lock.
  • the set screw is coupled to a spring element. In addition, this ensures that in addition to the positional securing the screw and a vibration damping is realized. Furthermore, thermally induced different expansions between the rotor part and the tie rod can be compensated.
  • the spring element is arranged for the transmission of force between the adjusting screw and the lever device, in particular, the power is transmitted to the lever device, starting from the spring element by means of a pressure bolt.
  • springs such as torsion springs or elastomer springs can be used as spring elements, but particularly preferred is the use of disc springs.
  • the diaphragm spring has a number of advantageous properties compared to other types of springs. For example, this can absorb very large forces even in a small installation space, with their spring characteristic linear or degressive and can be designed progressively by a suitable arrangement.
  • the characteristic of a spring element formed from a number of disc springs can be varied within wide limits by the suitable combination of the single-plate springs.
  • the adjusting device acts by means of centrifugal force on the lever device. That is, the tension of the tie rod with the rotor part takes place in dependence on the rotational speed of the gas turbine by the centrifugal forces occurring during operation of the turbine are transmitted to the lever device.
  • the on the Tie rod to the support acting pressure forces are increased with increasing speed of the rotor component.
  • the lever device is designed as a toggle device.
  • the toggle device is preferably arranged in a recess introduced in the rotor part such that a joint opposite the end is supported on the rotor part, wherein the other end of the toggle device is coupled to the pressure pin.
  • the toggle device is preferably arranged bent in the direction of the adjusting device.
  • a further pressure plate which is interposed between the knee joint and the adjusting device, is provided, wherein the vector of the force acting on the knee joint force preferably points in the direction of the bisector of the enclosed by the two levers of the toggle device angle.
  • the advantages achieved by the invention are in particular that a secure operation of the gas turbine is made possible by the tension of the rotor parts relative to the tie rod with their increasing overall length.
  • the system described in this application for increasing the stiffness of the rotor by the tension of the rotor parts with the tie rod with comparatively little effort can be realized.
  • the thermally induced relative movements between the rotor parts and the tie rod can be compensated particularly well.
  • a cooling necessary due to the high thermal load of the rotor component is ensured by means of a cooling air duct running in the axial direction of the rotor.
  • FIG. 1 A rotor 2 of a gas turbine with a number of individual, held together by a tie rod 4 and assembled into a unit rotor parts 6 is in FIG. 1 shown.
  • the respective rotor parts 6 are on the connection side provided with symmetrically to the central axis M of the rotor 2 extending recesses 8, wherein the resulting contours are formed corresponding to the contours of the respective adjacent rotor part 6, whereby a concentric alignment of the rotor parts 6 to the central axis M is effected.
  • Each of the rotor parts 6 is provided for guiding the tie rod 4 with an axially extending bore 10, wherein the tie rod end is screwed to a rotor part 6 and thus all interposed rotor parts 6 are held together.
  • the introduced into the rotor parts 6 recesses 8 serve to guide a cooling medium for cooling the rotor components by cooling air is supplied via a cooling channel formed between the tie rod 4 and rotor part 6.
  • the cross-sectional view of the rotor 2 according to FIG. 2 shows a in a rotor part 6, for example, a disc or a hollow shaft, integrated into it toggle device 12 in so-called tangential design, which is coupled to a set as an adjusting screw 14 adjusting device 16. Furthermore, the FIG. 2 removable, that for exerting a compressive force on the tie rod 4, a radially mounted in the radial direction pressure pin 18 between the toggle lever device 12 and the tie rod 4 is arranged. In this case, the toggle device 12 is arranged in a recess 20 bent in the direction of the adjusting screw 14, wherein a toggle lever joint opposite end is supported by the inner sides of the recess 20.
  • the adjusting device 16 embodied as an adjusting screw 14, like the toggle lever device 12, is integrated into the rotor part 6 in a suitable manner.
  • the head of the adjusting screw 14 is countersunk in a correspondingly dimensioned recess in the rotor part 6, wherein the adjusting screw 14 via an outgoing from this recess tangentially extending bore by means of spring element 22 and Pressure pin 18 is connected to the joint of the toggle device 12.
  • the case used for the purpose of expansion compensation and damping spring element 22 can be dimensioned and adjusted in a particularly simple manner by the number and arrangement of the plate springs 22 is variable.
  • the pressure force introduced by the adjusting screw 14 is transmitted via the pressure pin 18 to the toggle lever device 12 by means of a spring element 22, which is formed from four plate springs 22 connected in parallel.
  • the thus acting in the tangential direction of the knee joint force causes stretching of the toggle device 12, whereby the zugankerthe mounted pressure pin 18 is pressed radially in the direction of the tie rod 4.
  • the joints of the toggle device 12 opposite ends are rounded.
  • the adjustment accuracy can be adjusted in such a system in a simple manner by the choice of a suitable, provided with a corresponding threaded screw 14.
  • a provision of the screw 14 is prevented during and after the tensioning of the tie rod 4 with the rotor part 6 due to the self-locking effect of the thread.
  • FIG. 3 A cross section of a turbine rotor 2, in whose axially extending bore 10, a tie rod 4 is guided and the rotor part 6 is provided with a centrifugal force-controlled adjusting device 16 also in so-called tangential arrangement is in FIG. 3 shown.
  • the deflection of the force introduced by the adjusting device 16 takes place by means of a knee lever device 12 FIG. 2
  • the compressive force transmitted to the tie rod 4 is advantageously dependent on the rotational speed of the rotor component.
  • the joint of the knee lever device 12 via a pressure plate 18 to a in Axially extending axis 26 rotatably mounted body 24 upstream.
  • this has an effective, preferably a rounded profile.
  • the shape of the base body 24 causes its center of gravity lies outside the axis of rotation 26, so that during operation of the turbine due to the rotational movement of the rotor 2 of the base body 24 counterclockwise performs a tilting movement about its bearing axis 26.
  • the compressive force required for clamping - according to the embodiment FIG. 3 in the tangential direction - transferred to the force side of the knee lever device 12 upstream pressure pin 18, which thus acts analogously to the manner described above on the toggle lever device 12.
  • the force exerted on the knee joint centrifugal force in addition to the speed of the turbine of the dimensions of the body 24 and the position of the axis of rotation is dependent.
  • the force exerted on the tie rod 4 compressive force can be adjusted in dependence on the rotational speed of the turbine.
  • the compressive force generated for tensioning the rotor part 6 with the tie rod 4 can be limited by suitably positioned, not shown here limiting elements within the range of movement of the base body 24 are mounted.
  • the limiting elements may, for example, also be designed as adjusting devices 16.
  • the use of a set screw 14 is possible, which analogous to FIG. 2 may be provided with a spring element 22.
  • FIG. 3 shown in which only the orientation of the effective directions of employment were changed. These embodiments thus correspond to a so-called axial arrangement, since here the loading of the respective knee lever device with compressive force in the axial direction, that is substantially parallel to the central axis M of the tie rod 4, takes place.
  • the tie rod 4 is effectively supported.
  • An example of an arrangement with three such symmetrically arranged around the tie rod 4 devices is in FIG. 6 shown.
  • a substantially unhindered flow through the cooling medium is ensured by the centering of the tie rod 4 achieved thereby.
  • the tie rod 4 can be provided for locking with a contour of the pressure pin 18 corresponding recess, wherein in a particularly preferred embodiment, the pressure pin 18 connection side and their associated recesses have a conical shape in the radial direction.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP07005080A 2007-03-12 2007-03-12 Rotor d'une turbomachine thermique et turbomachine thermique Withdrawn EP1970531A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP07005080A EP1970531A1 (fr) 2007-03-12 2007-03-12 Rotor d'une turbomachine thermique et turbomachine thermique

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP07005080A EP1970531A1 (fr) 2007-03-12 2007-03-12 Rotor d'une turbomachine thermique et turbomachine thermique

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EP1970531A1 true EP1970531A1 (fr) 2008-09-17

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EP07005080A Withdrawn EP1970531A1 (fr) 2007-03-12 2007-03-12 Rotor d'une turbomachine thermique et turbomachine thermique

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ITMI20112019A1 (it) * 2011-11-07 2013-05-08 Ansaldo Energia Spa Apparecchiatura per lo smontaggio di elementi di estremita' di rotori di turbina a gas a tirante centrale

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1282467A (fr) * 1961-03-03 1962-01-19 Austin Motor Co Ltd Dispositif de serrage pour rotors coaxiaux, utilisable notamment sur les turbines à gaz
US3749516A (en) * 1971-10-06 1973-07-31 Carrier Corp Rotor structure for turbo machines
GB2272741A (en) * 1992-11-19 1994-05-25 Gutehoffnungshuette Man Tightening and loosening of the rods of a gas turbine rotor
US5537814A (en) * 1994-09-28 1996-07-23 General Electric Company High pressure gas generator rotor tie rod system for gas turbine engine

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1282467A (fr) * 1961-03-03 1962-01-19 Austin Motor Co Ltd Dispositif de serrage pour rotors coaxiaux, utilisable notamment sur les turbines à gaz
US3749516A (en) * 1971-10-06 1973-07-31 Carrier Corp Rotor structure for turbo machines
GB2272741A (en) * 1992-11-19 1994-05-25 Gutehoffnungshuette Man Tightening and loosening of the rods of a gas turbine rotor
US5537814A (en) * 1994-09-28 1996-07-23 General Electric Company High pressure gas generator rotor tie rod system for gas turbine engine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ITMI20112019A1 (it) * 2011-11-07 2013-05-08 Ansaldo Energia Spa Apparecchiatura per lo smontaggio di elementi di estremita' di rotori di turbina a gas a tirante centrale

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