EP1739285B1 - Aube de turbine refroidie et méthode d'opération d'une turbine à gaz - Google Patents

Aube de turbine refroidie et méthode d'opération d'une turbine à gaz Download PDF

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Publication number
EP1739285B1
EP1739285B1 EP05014377A EP05014377A EP1739285B1 EP 1739285 B1 EP1739285 B1 EP 1739285B1 EP 05014377 A EP05014377 A EP 05014377A EP 05014377 A EP05014377 A EP 05014377A EP 1739285 B1 EP1739285 B1 EP 1739285B1
Authority
EP
European Patent Office
Prior art keywords
gas turbine
guide blade
blade
turbine guide
heating element
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
EP05014377A
Other languages
German (de)
English (en)
Other versions
EP1739285A1 (fr
Inventor
Fathi Ahmad
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 AT05014377T priority Critical patent/ATE446439T1/de
Priority to DE502005008377T priority patent/DE502005008377D1/de
Priority to EP05014377A priority patent/EP1739285B1/fr
Priority to JP2006178356A priority patent/JP2007009911A/ja
Priority to US11/479,183 priority patent/US7465150B2/en
Publication of EP1739285A1 publication Critical patent/EP1739285A1/fr
Priority to US12/269,989 priority patent/US20090074572A1/en
Application granted granted Critical
Publication of EP1739285B1 publication Critical patent/EP1739285B1/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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/10—Heating, e.g. warming-up before starting
    • 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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on 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
    • 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
    • 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
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/321—Application in turbines in gas turbines for a special turbine stage
    • F05D2220/3212—Application in turbines in gas turbines for a special turbine stage the first stage of a turbine
    • 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
    • F05D2260/00—Function
    • F05D2260/85—Starting
    • 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
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/11—Purpose of the control system to prolong engine life
    • F05D2270/114—Purpose of the control system to prolong engine life by limiting mechanical stresses

Definitions

  • the invention relates to a cooled gas turbine guide vane for a gas turbine, comprising a hollow airfoil which comprises an inflow edge, which can be flowed on by a working medium, and which has a leading edge channel extending in the interior of the airfoil along the leading edge for guiding a cooling medium. Furthermore, the invention relates to the use of such a gas turbine guide vane and a method for operating a gas turbine with an aforementioned gas turbine guide vane.
  • a cooled turbine nozzle for a gas turbine is known.
  • the turbine guide vane has a front edge of a vane profile, which can be flowed on by a hot gas.
  • In the interior extends a transverse to the hot gas direction cooling channel.
  • the disassembly of the gas turbine is complex and leads to an undesirable increase in service life. Furthermore, the investigations are time-consuming and expensive, so that it is a general endeavor to reduce the service life of the gas turbine and to increase the life of the components used and used.
  • the object of the invention is therefore to provide a Gasturbinenleitschaufel with increased life.
  • Another object of the invention is the use of such Gasturbinenleitschaufel and the specification of two methods for operating a gas turbine with a gas turbine guide vane to increase their life.
  • the object directed to the gas turbine guide vane is solved by a gas turbine guide vane according to claim 1.
  • the invention proposes that the generic gas turbine vane in the leading edge channel has an electrical heating element which extends approximately completely over the entire length of the leading edge channel.
  • the invention is based on the recognition that particularly strongly rising or falling temperatures - also known as temperature shocks - can cause crack formation in the blade material and promote crack growth, if not accelerate it.
  • the rapid temperature changes each cause thermal stresses in the blade material, which must withstand many such temperature changes and voltage changes. Due to excessive temperature cycling, especially cold starts of the gas turbine, the blade material becomes fatigued. As the temperature changes and changes in voltage progress, cracks may develop and continue to grow. If the cracks exceed a critical length, or if an excessively large number of cracks of uncritical length are present within a unit area, then the component must be replaced.
  • the service life of the gas turbine guide vane is significantly increased by preheating the gas turbine vane to solve the object of the method according to claim 5 before the cold start of the gas turbine.
  • the gas turbine blade in the leading edge channel on a heating element which extends completely over the length of the blade profile.
  • the electrical heating element through which an electric current flows, before the firing of the gas turbine, ie during preheating, heats the gas turbine guide vane initially at room temperature comparatively slowly, so that the temperature-induced thermal stresses in the vane material can be kept correspondingly low.
  • the temperature increase is comparatively slow and not fast or jumpy, as in the previous start ie firing the gas turbine.
  • By firing the Gas turbine is set the heating of the gas turbine vane.
  • the life of the gas turbine vane can be increased if the shutdown of the gas turbine firing, planned or unplanned at a full load shutdown (Trip), the reheating of the gas turbine vane is started. Since the gas turbine guide vane is heated to its maximum permissible operating temperature during operation of the gas turbine, a targeted and controlled lowering of the temperature of the blade material can be achieved with the reheating. As a result, the duration of the temperature decrease is substantially increased compared to the previous, normal cooling of the gas turbine guide vane, so that the material stresses occurring due to the temperature reduction are comparatively low.
  • the gas turbine blades of the first and second turbine stage must withstand the highest operating temperatures, the largest temperature differences also occur in these gas turbine blades.
  • the operating temperatures are in such high temperature ranges, in particular these gas turbine blades are cooled. Therefore, the invention is particularly suitable for cooled gas turbine blades.
  • a particularly uniform heating of the airfoil of the gas turbine guide vane can be achieved when the electrical heating element rests against the channel wall of the leading edge channel or at least partially integrated in the channel wall.
  • This particularly favorable thermal coupling of heating element and duct wall leads to a low-loss heating of the material of the gas turbine guide vane.
  • the heating element is designed as a helical heating coil.
  • the heating coil is known and available at low cost.
  • the supplied heat output during the heating process is increased. This results in preheating to a continuous and steady heating of the blade material to a temperature value whose difference from the operating temperature of the gas turbine guide vane is small compared to the difference of ambient temperature and operating temperature. As a result, the material stresses occurring in the blade material build up slowly and therefore gently. If the firing then starts with the starting of the gas turbine, the remaining temperature increase is low. temperature shocks are thus avoided. It is also possible, with the electric heating element, to keep the gas turbine guide blade "warm” at a holding temperature which is close to the operating temperature in order to achieve a shortened starting phase.
  • the invention can reduce the LCF fatigue of gas turbine vanes, which has a positive effect on their service life and reduces the operating risk of a gas turbine equipped with such gas turbine blades.
  • FIG. 1 shows 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 successive an intake 4, a compressor 5, a toroidal annular combustion chamber 6 with a plurality of rotationally symmetrical to each other arranged burners 7, a turbine unit 8 and an exhaust housing 9.
  • the annular combustion chamber 6 forms a combustion chamber 17, which communicates with an annular hot gas channel 18.
  • FIG. 2 A gas turbine guide vane 30 according to the invention is shown in FIG FIG. 2 shown in a longitudinal section.
  • the gas turbine blade 30 has a blade profile 32 which extends between two platforms 34.
  • the platform 34 forms the radially outer and inner boundary of the hot gas channel 18, in which during operation of the gas turbine, the hot gas 11 flows.
  • the upstream-side leading edge of the blade profile 32 is referred to as the leading edge 36.
  • the blade profile 32 has a blade trailing edge 37, at which the hot gas 11 flows.
  • the blade profile 32 may include a plurality of cavities 38 into which a cooling medium 40, preferably cooling air, supplied through the platforms 34 may flow and cool the cast turbine blade 30.
  • a cooling medium 40 preferably cooling air
  • the common cooling methods such as convection cooling, impingement cooling and / or film cooling and effusion cooling can be used.
  • an electrical heating element 50 is provided in one of the cavities 38, but preferably in the cavity downstream of the leading edge 36, ie in the leading edge channel 40.
  • the heating element 50 extends approximately over the entire length of the leading edge 36, ie from the radially inner platform 34a to the outer platform 34b.
  • the heating element 50 is formed as a helical heating coil 54.
  • FIG. 3 shows a cross section through the gas turbine blade 30 according to the invention according to FIG. 2 ,
  • the helical heating coil 54 is arranged, which can be traversed by the life-prolonging preheating or reheating of the gas turbine guide vane 30 of a controllable electric heating current.
  • the electric heating current induces in the heating coil 54 a thermal radiation which comparatively slowly heats the material of the cast gas turbine nozzle 30, preferably the material of the airfoil 32 and the platform 34, prior to operation of the gas turbine 1 to provide the thermomechanical material stresses in one for the LCF Longevity uncritical scale increase or decay after operation.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Separation By Low-Temperature Treatments (AREA)

Claims (9)

  1. Aube ( 30 ) directrice refroidie pour une turbine ( 1) à gaz,
    ayant un profil ( 32 ) creux qui comprend un bord ( 36 ) d'attaque où peut affluer un fluide de travail et
    un canal ( 40) de bord d'attaque, s'étendant à l'intérieur du profil ( 32 ) de l'aube le long du bord ( 36 ) d'attaque et destiné à conduire un fluide de refroidissement,
    caractérisé
    en ce qu'il est prévu, dans le canal ( 40 ) du bord d'attaque, un élément ( 50 ) électrique de chauffage qui s'étend à peu près complètement sur toute la longueur du canal ( 40) de bord d'attaque.
  2. Aube ( 30 ) directrice pour une turbine à gaz suivant la revendication 1, dans lequel l'élément ( 50 ) électrique de chauffage s'applique à la paroi du canal ( 40 ) de bord d'attaque ou est intégré au moins en partie à la paroi du canal.
  3. Aube ( 30) directrice pour une turbine à gaz suivant la revendication 1 ou 2, dans lequel l'élément ( 50 ) de chauffage est constitué en filament ( 54 ) hélicoïdal de chauffage.
  4. Utilisation d'une aube ( 30) directrice pour une turbine à gaz suivant l'une des revendications 1 à 3 dans une turbine ( 1 ) à gaz fixe.
  5. Procédé pour faire fonctionner une turbine ( 1 ) à gaz ayant une aube ( 30 ) directrice pour une turbine à gaz suivant l'une des revendications 1 à 3,
    caractérisé en ce que
    avant le démarrage à froid de la turbine ( 1 ) à gaz, on préchauffe l'aube ( 30 ) directrice de la turbine à gaz.
  6. Procédé suivant la revendication 5,
    dans lequel, pendant l'opération de chauffage, on augmente la puissance calorifique apportée à l'aube ( 30 ) directrice de turbine à gaz.
  7. Procédé suivant la revendication 5 ou 6,
    dans lequel on règle le chauffage avant ou pendant le démarrage de la turbine ( 1 ) à gaz.
  8. Procédé pour faire fonctionner une turbine ( 1 ) à gaz ayant une aube ( 30 ) directrice pour une turbine à gaz suivant l'une des revendications 1 à 3,
    caractérisé en ce que
    après l'arrêt ( 1 ) de la turbine à gaz, on réchauffe l'aube ( 30 ) directrice de la turbine à gaz.
  9. Procédé suivant la revendication 8,
    dans lequel, pendant l'opération de chauffage, on abaisse la puissance calorifique apportée à l'aube ( 30 ) directrice de la turbine à gaz.
EP05014377A 2005-07-01 2005-07-01 Aube de turbine refroidie et méthode d'opération d'une turbine à gaz Not-in-force EP1739285B1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
AT05014377T ATE446439T1 (de) 2005-07-01 2005-07-01 Gekühlte gasturbinenleitschaufel für eine gasturbine, verwendung einer gasturbinenleitschaufel sowie verfahren zum betreiben einer gasturbine
DE502005008377T DE502005008377D1 (de) 2005-07-01 2005-07-01 Gekühlte Gasturbinenleitschaufel für eine Gasturbine, Verwendung einer Gasturbinenleitschaufel sowie Verfahren zum Betreiben einer Gasturbine
EP05014377A EP1739285B1 (fr) 2005-07-01 2005-07-01 Aube de turbine refroidie et méthode d'opération d'une turbine à gaz
JP2006178356A JP2007009911A (ja) 2005-07-01 2006-06-28 ガスタービンにおける冷却形ガスタービン静翼、ガスタービン静翼の利用およびガスタービンの運転方法
US11/479,183 US7465150B2 (en) 2005-07-01 2006-06-30 Cooled gas turbine guide blade for a gas turbine, use of a gas turbine guide blade and method for operating a gas turbine
US12/269,989 US20090074572A1 (en) 2005-07-01 2008-11-13 Cooled gas turbine guide blade for a gas turbine, use of a gas turbine guide blade and method for operating a gas turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP05014377A EP1739285B1 (fr) 2005-07-01 2005-07-01 Aube de turbine refroidie et méthode d'opération d'une turbine à gaz

Publications (2)

Publication Number Publication Date
EP1739285A1 EP1739285A1 (fr) 2007-01-03
EP1739285B1 true EP1739285B1 (fr) 2009-10-21

Family

ID=34937753

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05014377A Not-in-force EP1739285B1 (fr) 2005-07-01 2005-07-01 Aube de turbine refroidie et méthode d'opération d'une turbine à gaz

Country Status (5)

Country Link
US (2) US7465150B2 (fr)
EP (1) EP1739285B1 (fr)
JP (1) JP2007009911A (fr)
AT (1) ATE446439T1 (fr)
DE (1) DE502005008377D1 (fr)

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US7032290B2 (en) * 2002-03-22 2006-04-25 Asmo Co., Ltd. Manufacturing method for brush holder
US8264096B2 (en) * 2009-03-05 2012-09-11 Tarfin Micu Drive system for use with flowing fluids having gears to support counter-rotative turbines
US8742608B2 (en) 2009-03-05 2014-06-03 Tarfin Micu Drive system for use with flowing fluids
CN102201631A (zh) * 2010-03-26 2011-09-28 富士康(昆山)电脑接插件有限公司 电连接器组件
GB201009264D0 (en) * 2010-06-03 2010-07-21 Rolls Royce Plc Heat transfer arrangement for fluid washed surfaces
FR2970666B1 (fr) * 2011-01-24 2013-01-18 Snecma Procede de perforation d'au moins une paroi d'une chambre de combustion

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Also Published As

Publication number Publication date
JP2007009911A (ja) 2007-01-18
US20070116563A1 (en) 2007-05-24
US20090074572A1 (en) 2009-03-19
EP1739285A1 (fr) 2007-01-03
US7465150B2 (en) 2008-12-16
ATE446439T1 (de) 2009-11-15
DE502005008377D1 (de) 2009-12-03

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