EP1717419B1 - Méthode et dispositif pour l'adjustement d'un jeu radial d'un compresseur axial dans une turbomachine - Google Patents

Méthode et dispositif pour l'adjustement d'un jeu radial d'un compresseur axial dans une turbomachine Download PDF

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Publication number
EP1717419B1
EP1717419B1 EP05009380A EP05009380A EP1717419B1 EP 1717419 B1 EP1717419 B1 EP 1717419B1 EP 05009380 A EP05009380 A EP 05009380A EP 05009380 A EP05009380 A EP 05009380A EP 1717419 B1 EP1717419 B1 EP 1717419B1
Authority
EP
European Patent Office
Prior art keywords
guide ring
guide
coolant
compressor
gas turbine
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
EP05009380A
Other languages
German (de)
English (en)
Other versions
EP1717419A1 (fr
Inventor
Tobias Dr. Buchal
Gerhard Hülsemann
Mirko Milazar
Dieter Minninger
Michael Neubauer
Harald Nimptsch
Heinrich Pütz
Kang Dr. Qian
Arnd Dr. Reichert
Volker Dr. Vosberg
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
Priority to EP05009380A priority Critical patent/EP1717419B1/fr
Application filed by Siemens AG filed Critical Siemens AG
Priority to DE502005010381T priority patent/DE502005010381D1/de
Priority to AT05009380T priority patent/ATE484652T1/de
Priority to CN2006100752846A priority patent/CN1854468B/zh
Priority to CN201010175874A priority patent/CN101825003A/zh
Priority to JP2006120073A priority patent/JP2006307853A/ja
Priority to US11/413,871 priority patent/US7766611B2/en
Publication of EP1717419A1 publication Critical patent/EP1717419A1/fr
Application granted granted Critical
Publication of EP1717419B1 publication Critical patent/EP1717419B1/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
    • 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
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
    • 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
    • F01D19/00—Starting of machines or engines; Regulating, controlling, or safety means in connection therewith
    • F01D19/02—Starting of machines or engines; Regulating, controlling, or safety means in connection therewith dependent on temperature of component parts, e.g. of turbine-casing

Definitions

  • freestanding guide vanes may also form a radial gap with respect to a rotating conical or cylindrical guide surface arranged on the rotor.
  • the radial gaps are to be made as small as possible. It is known from the aforementioned Offenlegungsschrift to fasten guide rings to a stator by obliquely arranged holding partners to the radial direction and to displace them during operation of the gas turbine due to the thermal material expansion of the guide ring in the direction of the blade ends towards the reduction of the radial gap.
  • a compressor housing with cavities known to prevent the cooling after switching off the compressor or the gas turbine.
  • insulating materials are arranged in the cavities, which are provided between the guide ring and housing outer wall or between the feet of guide vanes and the housing outer wall.
  • the constructive parameters determining the gap dimension are designed for the warm start of a gas turbine in order to cope with the smallest possible operating gap, ie radial gap.
  • the housing cools comparatively quickly with respect to the rotor of the gas turbine.
  • the housing or the guide rings shrink due to their cooling back to their original design size, the initially warm rotor remains initially extended due to the heat stored in it and retarded cools and shrinks.
  • the result is the so-called constricting effect.
  • This situation may cause the radial gap to be reduced and the blades of the rotor to contact or even scratch the housing or guide ring, permanently enlarging or even scooping the radial gap can damage.
  • An increased radial gap leads to increased fuel consumption, damaged blades may require early maintenance with corresponding additional costs.
  • Object of the present invention is to provide a method of the type mentioned, which improves the warm start behavior of the compressor of the turbomachine to increase the availability and at the same time to increase the efficiency.
  • the object of the method is solved by the features of claim 1 and the object directed to the compressor by the features of claim 7.
  • the increase of the radial gap achieved in this way results in a reduction of the described constricting effect and the risk of being scuffed, which significantly improves the warm start behavior of the turbomachine, ie the turbomachine could be started earlier, relative to its previous departure time.
  • the radial gaps no longer need to be dimensioned after the warm start as unfavorable start of operation.
  • the cooling of the warm guide rings increases the radial gap of the non-operating turbomachine.
  • the radial gap increase obtained for this condition can also be partially utilized, rather than improving the warm start, to reduce the radial gaps of one in an idle and cold condition, i. a smaller lying at ambient temperature fluid flow machine, based on a known from the prior art turbomachine.
  • both the rotor and the housing of the continuous-duty turbomachine warm up to a maximum operating temperature. Both housing and rotor expand, so that the risk of constriction no longer exists. Accordingly, the method is particularly advantageous if the admission of the guide ring with coolant is set during the start of the turbomachine. After reaching the maximum operating temperature, the temperature-induced strains of the turbomachine, ie the stator and the Rotor, completed. Consequently, the guide ring also heats up so that it expands and shifts its guide surface in the direction of the scrape edges of the blades, which leads to an efficiency-increasing reduction of the radial gaps. According to the invention this can be used particularly advantageously when the turbomachine is designed as a compressor of a gas turbine, in which the guide rings are usually uncooled during operation.
  • coolant is taken from an external coolant source.
  • coolant in the form of cooling air is usually taken from the compressor. Since the method is used before the start of the gas turbine, this is not possible.
  • an external coolant source such as a separately driven auxiliary compressor or external fan, must be used to provide the coolant for cooling the guide rings prior to the warm start of the gas turbine.
  • Preferred dimensions can be acted upon by the start of the turbomachine of the guide ring with a heating medium.
  • the turbomachine is, for example, a compressor of a gas turbine and the methods known from the prior art, in which material expansions of the guide ring are used for adjusting the radial gap, is applied to the guide ring of a compressor.
  • air or steam can be used as the heating means.
  • FIG. 1 shows an example of a turbomachine, a gas turbine 1 in a longitudinal partial section. It has inside a rotatably mounted about a rotation axis 2 rotor 3, which is also referred to as a turbine runner. Along the rotor 3 successively follow an intake housing 4, a compressor 5, a toroidal annular combustion chamber 6 with a plurality of coaxially arranged burners 7, a turbine unit 8 and the exhaust housing 9.
  • the annular combustion chamber 6 forms a combustion chamber 17 which communicates with an annular flow channel 18.
  • There four successive turbine stages 10 form the turbine unit 8. Each turbine stage 10 and each compressor stage is formed of two blade rings.
  • a compressor stage is formed by a blade row 13 with a ring of guide blade 12 following in the flow direction of the air to be compressed.
  • the blade 15 is radially outside a guide ring 21 and the guide vane 12 radially inward of a guide ring 23 against.
  • the guide rings 21, 23 delimit the flow channel 18 extending in the axial direction of the rotor 3 in the radial direction.
  • the guide rings 21, 23 may be formed from over the circumference adjacent ring segments.
  • FIG. 2 shows the detail II FIG. 1 , a cross section through a guide ring 21 with an opposite blade, after all temperature-induced strains are completed.
  • the blades each have a blade profile 19, which is drop-shaped in cross-section, and has a front edge 20, which can be flowed on by a working medium, and a rear edge 22.
  • a cylindrical or conically extending to the axis of rotation 2 of the gas turbine rotor 3 wall 25 forms part of a rotationally fixed inner housing 27.
  • the wall 25 encloses the annular flow channel 18.
  • In the inner housing 27 and in the Wall 25 is a running in the circumferential direction and in cross-section hammer-shaped groove 29 incorporated, in which the guide ring 21 is arranged.
  • the guide ring 21 surrounds the flow channel 18 coaxial with the axis of rotation 2 of the rotor.
  • an insulating layer 26 may be formed, which shields the guide ring 21 thermally against the wall 25 and insulated so that the wall 25 and the inner housing 27 does not shrink also in the direction of the blade.
  • the guide ring 21 is made of a material which under the action of heat, i. a temperature increase, expands, preferably expands more than the wall 25 and the inner housing 27, i. the guide ring 21 has a greater coefficient of thermal expansion than the wall 25 and the inner housing 27th
  • the guide ring 21 is formed substantially corresponding to the hammer-shaped groove 29 and is directly on the back, or as shown, on the insulating layer 26 on the groove bottom of the groove 29 and the front to a contact surface 50 of the undercut 31, so that the guide ring 21 is fixed.
  • the contact surface 50 determines the radial position of the guide ring 21 and is radially further out (or inside) arranged as the tips of the blades 15 (and vanes 12) opposite guide surface 33rd
  • the flow channel 18 facing the guide surface 33 of the guide ring 21 is the blade 15, in particular their squeal edge 35 opposite. Between the squeal edge 35 of each blade 15 and the guide surface 33, a radial gap 36 is formed. During operation of the gas turbine, the blade rotates 15 under the surface 33 away, this is to illustrate the axis of rotation 2 - not true to scale - indicated.
  • a groove 39 provided with the wall 25 or, if present, the insulating layer 26 extending in the circumferential direction, i. form annular supply channel 41.
  • cooling channels 43 which communicate with the supply channel 41 via radial connection channels 45.
  • the housing After switching off the gas turbine 1, the housing cools faster than the rotor 3, so that the expansions of the housing decrease faster or go back and constrict the still warm and thus more extended rotor 3. This reduces the gap of the radial gap 36.
  • coolant 51 is supplied through the supply channel 49 to the supply channel 41, which passes from there via the connection channels 45 in the cooling channels 43 and the guide ring 21 cools.
  • the coolant 51 absorbs the heat still stored in the guide ring 21 and is then blown through openings, not shown, either in the flow channel 18 or returned to the outside via the return channels also not shown from the inside of the machine.
  • the temperature-induced material expansions of the guide ring 21 go back.
  • the guide surface 33 delimiting the flow channel 16 shifts radially outward into the position 33 '.
  • the radial gap 36 increases by the distance X to 36 ', thereby reducing the risk of rubbing the blades 15 on the guide surface 33 or 33' in the case of warm start. This effect can be used to reduce the time between shutdown and warm start of the gas turbine.
  • the method is particularly effective when the guide ring 21 is insulated from the wall 25.
  • only the guide ring 21 is cooled, and not beyond the wall 25. This leads to a particularly efficient cooling of the guide ring 21 and prevents the wall 25 also moves along the same way. This ensures that only the guide ring 21 takes back its heat-related strains.
  • the housing After or during the start, ie during the starting process of the gas turbine 1, the housing heats up and expands. The housing and the inner housing 27 move radially outward. The risk of rubbing the blades 15 with their squeal edge 35 on the guide surface 33 of the guide rings 21 is reduced, so that after a predetermined period of operation, the cooling of the guide rings 21 can be adjusted.
  • the gas turbine 1 continues to heat up until a temperature distribution that is no longer changing has set in it.
  • the material of the guide ring 21 allows a further increase in temperature, even in place of the coolant 51 during operation of the gas turbine 1, a heating medium through the channels 49, 41, 45 are passed.
  • a further increase in temperature of the guide ring 21 causes an additional expansion in the radial direction, with which the radial gap 36 is further reduced. This leads to an increase in efficiency, since less working fluid - in the compressor 5, the gas to be compressed and in the turbine unit 8, the expanding hot gas 11 - can escape unused by the reduced radial gap 36.
  • the radial gap 36 may not only be formed between a radially outer guide surface 33 and a blade 15, but it may also be between the non-rotating guide vane 12 and arranged on the rotor 3 guide surface 23. Accordingly, wall 25 would be part of the rotor 3, so that the guide ring 23 is opposite a guide vane 12. In this case, the directions of displacement also change from outside to inside.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (10)

  1. Procédé de modification d'un jeu ( 36 ) radial, formé entre un bord ( 35 ) d'attaque d'une aube ( 15 ) et une surface ( 33 ) de guidage qui lui est opposée, d'un compresseur à flux axial d'une turbine à gaz, dans lequel la surface ( 33) de guidage peut être alimentée en un fluide ( 51 ) de refroidissement par un anneau ( 21, 23 ) de guidage formant la surface ( 33 ) de guidage,
    caractérisé en ce que,
    avant le démarrage de la turbomachine, on alimente l'anneau ( 21, 23) de guidage en fluide ( 51 ) de refroidissement.
  2. Procédé suivant la revendication 1,
    dans lequel, pendant le démarrage de la turbine à gaz, on règle l'alimentation de l'anneau ( 21, 23) de guidage en fluide ( 51 ) de refroidissement.
  3. Procédé suivant la revendication 1 ou 2,
    dans lequel on prélève le fluide ( 51 ) de refroidissement d'une source extérieure de fluide de refroidissement.
  4. Procédé suivant l'une des revendications précédentes,
    dans lequel on utilise de l'air ou de l'eau comme fluide ( 51 ) de refroidissement.
  5. Procédé suivant la revendication 2,
    dans lequel, après le démarrage de la turbomachine, on alimente l'anneau ( 21, 23) de guidage en un fluide de chauffage.
  6. Procédé suivant la revendication 5,
    dans lequel on utilise de l'air ou de la vapeur comme fluide de chauffage.
  7. Dispositif pour effectuer le procédé suivant l'une des revendications 1 à 6 comprenant un compresseur ( 5 ) à flux axial d'une turbine à gaz, ayant un dispositif de modification d'un jeu ( 36 ) radial, formé entre un bord ( 35 ) d'attaque d'une aube ( 15 ) et une surface ( 33 ) de guidage qui lui est opposée, du compresseur ( 5 ) à flux axial,
    dans lequel un anneau ( 21, 23 ) formant la surface ( 33 ) de guidage est fixé à une structure ( 25, 27 ) porteuse, caractérisé en ce que
    l'anneau ( 21, 23 ) de guidage peut être alimenté en un fluide ( 51 ) de refroidissement.
  8. Dispositif suivant la revendication 7,
    dans lequel l'anneau ( 21,23 ) est isolé thermiquement par rapport à la structure ( 25, 27 ) porteuse au moyen d'une couche ( 26 ) isolante.
  9. Dispositif suivant la revendication 7 ou 8,
    dans lequel l'anneau ( 21, 23 ) de guidage a un coefficient de dilatation thermique plus grand que celui de la structure ( 25, 27 ) porteuse.
  10. Dispositif suivant la revendication 7, 8 ou 9,
    dans lequel la structure ( 25, 27 ) porteuse a une surface ( 50 ) d'application, à laquelle s'applique un anneau ( 21, 23 ) de guidage et la surface ( 50 ) d'application est disposée radialement plus à l'extérieur ( ou à l'intérieur ) que la surface ( 33 ) de guidage opposée aux bords ( 35 ) d'attaque des aubes ( 15 ) mobiles ( ou des aubes ( 12 ) directrices ).
EP05009380A 2005-04-28 2005-04-28 Méthode et dispositif pour l'adjustement d'un jeu radial d'un compresseur axial dans une turbomachine Not-in-force EP1717419B1 (fr)

Priority Applications (7)

Application Number Priority Date Filing Date Title
DE502005010381T DE502005010381D1 (de) 2005-04-28 2005-04-28 Verfahren und Vorrichtung zur Einstellung eines Radialspaltes eines axial durchströmten Verdichters einer Strömungsmaschine
AT05009380T ATE484652T1 (de) 2005-04-28 2005-04-28 Verfahren und vorrichtung zur einstellung eines radialspaltes eines axial durchströmten verdichters einer strömungsmaschine
EP05009380A EP1717419B1 (fr) 2005-04-28 2005-04-28 Méthode et dispositif pour l'adjustement d'un jeu radial d'un compresseur axial dans une turbomachine
CN201010175874A CN101825003A (zh) 2005-04-28 2006-04-18 用于调节轴流式涡轮机和压缩机的径向间隙的方法
CN2006100752846A CN1854468B (zh) 2005-04-28 2006-04-18 用于调节轴流式涡轮机和压缩机的径向间隙的方法及装置
JP2006120073A JP2006307853A (ja) 2005-04-28 2006-04-25 軸流流体機械におけるラジアル隙間の調整方法と圧縮機
US11/413,871 US7766611B2 (en) 2005-04-28 2006-04-28 Method for setting a radial gap of an axial-throughflow turbomachine and compressor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP05009380A EP1717419B1 (fr) 2005-04-28 2005-04-28 Méthode et dispositif pour l'adjustement d'un jeu radial d'un compresseur axial dans une turbomachine

Publications (2)

Publication Number Publication Date
EP1717419A1 EP1717419A1 (fr) 2006-11-02
EP1717419B1 true EP1717419B1 (fr) 2010-10-13

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ID=35765672

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05009380A Not-in-force EP1717419B1 (fr) 2005-04-28 2005-04-28 Méthode et dispositif pour l'adjustement d'un jeu radial d'un compresseur axial dans une turbomachine

Country Status (6)

Country Link
US (1) US7766611B2 (fr)
EP (1) EP1717419B1 (fr)
JP (1) JP2006307853A (fr)
CN (2) CN101825003A (fr)
AT (1) ATE484652T1 (fr)
DE (1) DE502005010381D1 (fr)

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Also Published As

Publication number Publication date
CN1854468B (zh) 2010-11-10
CN1854468A (zh) 2006-11-01
CN101825003A (zh) 2010-09-08
EP1717419A1 (fr) 2006-11-02
US7766611B2 (en) 2010-08-03
DE502005010381D1 (de) 2010-11-25
US20060245910A1 (en) 2006-11-02
ATE484652T1 (de) 2010-10-15
JP2006307853A (ja) 2006-11-09

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