EP1739285A1 - Cooled gas turbine stator vane and method of operation of a gas turbine - Google Patents

Cooled gas turbine stator vane and method of operation of a gas turbine Download PDF

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Publication number
EP1739285A1
EP1739285A1 EP05014377A EP05014377A EP1739285A1 EP 1739285 A1 EP1739285 A1 EP 1739285A1 EP 05014377 A EP05014377 A EP 05014377A EP 05014377 A EP05014377 A EP 05014377A EP 1739285 A1 EP1739285 A1 EP 1739285A1
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EP
European Patent Office
Prior art keywords
gas turbine
guide vane
vane
leading edge
heating element
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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.)
Granted
Application number
EP05014377A
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German (de)
French (fr)
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EP1739285B1 (en
Inventor
Fathi Ahmad
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Siemens AG
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Siemens AG
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Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP05014377A priority Critical patent/EP1739285B1/en
Priority to AT05014377T priority patent/ATE446439T1/en
Priority to DE502005008377T priority patent/DE502005008377D1/en
Priority to JP2006178356A priority patent/JP2007009911A/en
Priority to US11/479,183 priority patent/US7465150B2/en
Publication of EP1739285A1 publication Critical patent/EP1739285A1/en
Priority to US12/269,989 priority patent/US20090074572A1/en
Application granted granted Critical
Publication of EP1739285B1 publication Critical patent/EP1739285B1/en
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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 approachable by a working fluid leading edge and which has a running in the interior of the airfoil along the leading edge leading edge channel 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 is present within a unit area, 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 vane "warm” at a holding temperature which is close to the operating temperature in order to achieve a shortened starting phase.
  • the heat output supplied to the gas turbine vane is steadily lowered to provide a relatively slow lowering of the temperature of the vane material, resulting in reduced thermal expansion and stress.
  • 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.
  • a gas turbine guide vane 30 according to the invention is shown in FIG. 2 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 as shown in FIG 2.
  • the helical heating coil 54 is arranged, which can be traversed for life-prolonging preheating or Nachbeloomung the gas turbine guide vane 30 of a controllable electric heating.
  • 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.

Abstract

A heating element (50) with heating coils is extended over the entire length of the hollow space (38) behind the leading edge (36) of a guide vane profile. The heating element also runs from inside to outside platforms (34a,34b) of the vane profile, and gradually preheats the vane especially at time of cold starting of the gas turbine. Independent claims are included for the following: (1) a use of a gas turbine guide vane; and (2) a method of operating a gas turbine.

Description

Die Erfindung betrifft eine gekühlte Gasturbinenleitschaufel für eine Gasturbine, mit einem hohlen Schaufelblatt, welches eine von einem Arbeitsmedium anströmbare Anströmkante umfasst und welches einen im Inneren des Schaufelprofils entlang der Anströmkante verlaufenden Anströmkantenkanal zur Führung eines Kühlmediums aufweist. Ferner betrifft die Erfindung die Verwendung einer solchen Gasturbinenleitschaufel und ein Verfahren zum Betreiben einer Gasturbine mit einer vorgenannten Gasturbinenleitschaufel.The invention relates to a cooled gas turbine guide vane for a gas turbine, comprising a hollow airfoil, which comprises an approachable by a working fluid leading edge and which has a running in the interior of the airfoil along the leading edge leading edge channel 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.

Aus der EP 1 505 256 A2 ist eine gekühlte Turbinenleitschaufel für eine Gasturbine bekannt. Die Turbinenleitschaufel weist eine von einem Heißgas anströmbare Vorderkante eines Schaufelprofils auf. Im Innern erstreckt sich ein quer zur Heißgasrichtung verlaufender Kühlkanal.From the EP 1 505 256 A2 For example, 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.

Die Berechnung der maximal zulässigen Lebensdauer derartiger Gasturbinenschaufeln, mit der ein störungsfreier und zuverlässiger Betrieb der Gasturbine gewährleistet ist, erfolgt auch unter Berücksichtigung der Ermüdungslebensdauer bezüglich Kurzzeitschwingfestigkeit (Low-Cycle-Fatigue = LCF). Anhand von theoretischen Modellen und unter Annahmen von Randbedingungen wird die LCF-Lebensdauer bestimmt. Nach Erreichen der maximal zulässigen Lebensdauer wird die Gasturbine geöffnet und die Gasturbinenschaufeln werden visuell und maschinell auf Defekte, wie beispielsweise Risse, untersucht. Mit der Untersuchung soll wird festgestellt, ob ihre weitere Verwendung für ein nächstes Betriebsintervall ohne eine Gefährdung des Gasturbinenbetriebs möglich ist.The calculation of the maximum permissible service life of such gas turbine blades, with which a trouble-free and reliable operation of the gas turbine is ensured, is also taking into account the fatigue life with respect to short-term fatigue strength (low-cycle fatigue = LCF). Based on theoretical models and assumptions of boundary conditions, the LCF lifetime is determined. After reaching the maximum allowable life, the gas turbine is opened and the gas turbine blades are visually and mechanically inspected for defects such as cracks. The purpose of the investigation is to determine whether its further use is possible for a next operating interval without endangering gas turbine operation.

Die Zerlegung der Gasturbine ist aufwändig und führt zu einer unerwünschten Erhöhung der Standzeit. Des Weiteren sind die Untersuchungen zeit- und kostenintensiv, so dass es ein allgemeines Bestreben ist, die Standzeiten der Gasturbine zu verringern und die Lebensdauer der verwendeten und eingesetzten Bauteile zu erhöhen.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.

Aufgabe der Erfindung ist daher die Bereitstellung einer Gasturbinenleitschaufel mit erhöhter Lebensdauer. Weitere Aufgabe der Erfindung ist die Verwendung einer solchen Gasturbinenleitschaufel sowie die Angabe zweier Verfahren zum Betreiben einer Gasturbine mit einer Gasturbinenleitschaufel, um deren Lebensdauer zu erhöhen.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.

Gelöst wird die auf die Gasturbinenleitschaufel gerichtete Aufgabe durch eine Gasturbinenleitschaufel gemäß dem Patentanspruch 1. Die Erfindung schlägt vor, dass die gattungsgemäße Gasturbinenleitschaufel im Anströmkantenkanal ein elektrisches Heizelement aufweist, welches sich annähernd vollständig über die gesamte Länge des Anströmkantenkanals erstreckt.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.

Die Erfindung geht von der Erkenntnis aus, dass besonders stark ansteigende bzw. stark abfallende Temperaturen - auch so genannte Temperaturschocks - im Schaufelmaterial Rissentstehung hervorrufen können und Risswachstum begünstigen, wenn nicht sogar beschleunigen. Die schnellen Temperaturänderungen rufen jeweils thermische Spannungen im Schaufelmaterial hervor, welches viele derartiger Temperaturwechsel und Spannungswechsel standhalten muss. Aufgrund von übermäßig vielen Temperaturwechseln, insbesondere Kaltstarts der Gasturbine, ermüdet das Schaufelmaterial. Bei fortschreitender Einwirkung der Temperaturwechsel und Spannungswechsel können Risse entstehen und weiter wachsen. Überschreiten die Risse eine kritische Länge, oder ist innerhalb einer Flächeneinheit eine zu hohe Anzahl an Rissen mit unkritischer Länge vorhanden, so muss das Bauteil ausgetauscht werden.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 is present within a unit area, the component must be replaced.

Diese negativen Anzeigen treten umso häufiger auf, je häufiger das heißgasbeaufschlagte Schaufelmaterial schnellen Temperaturänderungen ausgesetzt ist, und umso größer die jeweils zu widerstehenden Temperaturdifferenzen sind.These negative indications occur more frequently the more frequently the hot gas-loaded blade material is exposed to rapid changes in temperature, and the greater the respective temperature differences to be resisted.

Insbesondere während des Kaltstarts der Gasturbine sowie während des Herunterfahrens der Gasturbine treten die größten Temperaturdifferenzen in den heißgasbeaufschlagten Bauteilen auf.In particular, during the cold start of the gas turbine and during the shutdown of the gas turbine, the largest temperature differences occur in the Heißgasbeaufschlagten components.

Den stärksten negativen Einfluss auf die Lebensdauer der Turbinenschaufel hat jedoch die ungeplante Abschaltung der Gasturbine bei Volllast im kritischen Fehlerfall. Diese als Trip bezeichnete Situation verringert signifikant die Lebensdauer der heißgasbeaufschlagten Bauteile, und somit auch die von Gasturbinenschaufeln, da deren Material in diesen Momenten besonders großen Temperaturgradienten und/oder Temperaturschwankungen standhalten muss.However, the most negative impact on the life of the turbine blade is the unplanned shutdown of the gas turbine at full load in the event of a critical fault. This situation, referred to as trip, significantly reduces the life of the components subjected to hot gas, and thus also of gas turbine blades, since their material must withstand particularly large temperature gradients and / or temperature fluctuations at these moments.

Hier setzt die Erfindung an. In einer vorzugsweise stationären Gasturbine wird die Lebensdauer der Gasturbinenleitschaufel signifikant erhöht, indem zur Lösung der auf das Verfahren gerichteten Aufgabe gemäß Anspruch 5 vor dem Kaltstart der Gasturbine die Gasturbinenleitschaufel vorgeheizt wird. Dazu weist die Gasturbinenschaufel im Anströmkantenkanal ein Heizelement auf, welches sich vollständig über die Länge des Schaufelprofils erstreckt. Das von einem elektrischen Strom durchflossene elektrische Heizelement erwärmt noch vor dem Befeuern der Gasturbine, also während des Vorheizens, die zu Beginn auf Raumtemperatur befindliche Gasturbinenleitschaufel vergleichsweise langsam, so dass die temperaturbedingten thermischen Spannungen im Schaufelmaterial dementsprechend gering gehalten werden können. Der Temperaturanstieg erfolgt vergleichsweise langsam und nicht schnell oder sprunghaft, wie beim bisherigen Starten d.h. Befeuern der Gasturbine. Mit dem Befeuern der Gasturbine wird die Beheizung der Gasturbinenleitschaufel eingestellt.This is where the invention starts. In a preferably stationary gas turbine, 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. For this purpose, 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.

Ebenso kann zur Lösung der auf das Verfahren gerichteten Aufgabe gemäß Anspruch 8 die Lebensdauer der Gasturbinenleitschaufel vergrößert werden, wenn mit dem Abschalten der Befeuerung der Gasturbine, geplant oder ungeplant bei einer Volllastabschaltung (Trip), die Nachheizung der Gasturbinenleitschaufel begonnen wird. Da während des Betriebes der Gasturbine die Gasturbinenleitschaufel auf ihre maximal zulässige Betriebstemperatur aufgeheizt ist, kann mit dem Nachheizen eine gezielte und gesteuerte Absenkung der Temperatur des Schaufelmaterials erreicht werden. Dadurch wird die Temperaturabsenkdauer gegenüber der bisherigen, normalen Auskühlung der Gasturbinenleitschaufel wesentlich verlängert, so dass die aufgrund der Temperaturabsenkung auftretenden Materialspannungen vergleichsweise gering ausfallen.Also, to solve the object of the method according to claim 8, 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.

Aufgrund der bei beiden Verfahren erzielbaren Verminderung von thermischen Spannungen kann im Schaufelmaterial Rissentstehung weiter verzögert und Risswachstums verlangsamt werden, verglichen mit bisherigen Gasturbinenschaufel aus dem Stand der Technik. Die somit materialschonenden Verfahren führen zu einer signifikanten Steigerung der Kurzzeitschwingfestigkeit und zu einer Verlängerung der garantiert fehlerunkritischen Lebensdauer der Gasturbinenleitschaufel. Eine mit den Gasturbinenschaufeln bestückte und/oder nach den Verfahren betriebene Gasturbine kann länger zuverlässig und störungsfrei eingesetzt werden, was sich aufgrund der zeitlich nach hinten verschobenen Kontrolluntersuchungen kostenmindernd auswirkt.Due to the reduction in thermal stresses achievable in both methods, crack generation in the blade material can be further retarded and crack growth slowed as compared to prior gas turbine blade of the prior art. The thus material-sparing processes lead to a significant increase in the short-term fatigue strength and to an extension of the guaranteed fault-non-critical lifetime of the gas turbine guide vane. A equipped with the gas turbine blades and / or operated by the method gas turbine can be used reliably longer and trouble-free, which has a cost-reducing effect due to the postponed backward inspection.

Da die Gasturbinenschaufeln der ersten und zweiten Turbinenstufe den höchsten Betriebstemperaturen standhalten müssen, treten die größten Temperaturdifferenzen auch bei diesen Gasturbinenschaufeln auf. Die Betriebstemperaturen liegen in derart hohen Temperaturbereichen, das insbesondere diese Gasturbinenschaufeln gekühlt werden. Daher ist die Erfindung für gekühlte Gasturbinenschaufeln besonders geeignet. Ungekühlte Gasturbinenschaufeln unterliegen dagegen geringeren Temperaturdifferenzen, so dass der beschriebene Einfluss der Temperaturänderungen zwischen heiß (= Betriebstemperatur des Bauteils) und kalt (= Umgebungstemperatur) geringer ausfällt.Since 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. By contrast, uncooled gas turbine blades are subject to lower temperature differences, so that the described influence of the temperature changes between hot (= operating temperature of the component) and cold (= ambient temperature) is lower.

Vorteilhafte Ausgestaltungen sind in den Unteransprüchen angegeben.Advantageous embodiments are specified in the subclaims.

Eine besonders gleichmäßige Erwärmung des Schaufelblatts der Gasturbinenleitschaufel kann erreicht werden, wenn das elektrische Heizelement an der Kanalwand des Anströmkantenkanals anliegt oder zumindest teilweise in der Kanalwand integriert ist. Diese besonders günstige wärmetechnische Kopplung von Heizelement und Kanalwand führt zu einer verlustarmen Beheizung des Materials der Gasturbinenleitschaufel.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.

Um eine besonders gleichmäßige Verteilung der von dem Heizelement abgestrahlten Wärmeenergie in das Schaufelmaterial zu gewährleisten, ist das Heizelement als schraubenförmige Heizwendel ausgebildet. Die Heizwendel ist bekannt und kostengünstig verfügbar.In order to ensure a particularly uniform distribution of the radiated heat energy from the heating element in the blade material, the heating element is designed as a helical heating coil. The heating coil is known and available at low cost.

Um eine ausreichende Erwärmung der Gasturbinenleitschaufel vor dem Starten der Gasturbine zu erzielen, wird die zugeführte Wärmeleistung während des Heizvorgangs erhöht. Dies führt während des Vorheizens zu einer dauerhaften und stetigen Erwärmung des Schaufelmaterials bis zu einem Temperaturwert, dessen Differenz zur Betriebstemperatur der Gasturbinenleitschaufel klein ist gegenüber der Differenz von Umgebungstemperatur und Betriebstemperatur. Dadurch bauen sich die im Schaufelmaterial auftretenden Materialspannungen langsam und daher materialschonend auf. Wenn anschließend mit dem Starten der Gasturbine die Befeuerung einsetzt, ist der verbleibende Temperaturanstieg gering. Temperaturschocks werden somit vermieden. Auch ist es möglich, mit dem elektrischen Heizelement die Gasturbinenleitschaufel auf einer nahe der Betriebstemperatur liegende Vorhaltetemperatur "warm" zu halten, um eine verkürzte Startphase zu erreichen.In order to achieve sufficient heating of the gas turbine guide vane before starting the gas turbine, 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 vane "warm" at a holding temperature which is close to the operating temperature in order to achieve a shortened starting phase.

Während der Nachheizphase wird die der Gasturbinenleitschaufel zugeführte Wärmeleistung stetig abgesenkt, um eine vergleichsweise langsame Absenkung der Temperatur des Schaufelmaterials herbeizuführen, was zu reduzierten thermischen Materialdehnungen und -spannungen führt.During the post-heating phase, the heat output supplied to the gas turbine vane is steadily lowered to provide a relatively slow lowering of the temperature of the vane material, resulting in reduced thermal expansion and stress.

Insgesamt kann mit der Erfindung die LCF-Ermüdung von Gasturbinenleitschaufeln reduziert werden, was sich positiv auf deren Lebensdauer auswirkt und eine Reduzierung des Betriebsrisikos einer mit solchen Gasturbinenschaufeln ausgerüsteten Gasturbine bewerkstelligt.Overall, 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.

Die Erfindung wird anhand von Figuren erläutert.
Es zeigen:

FIG 1
eine Gasturbine in einem Längsteilschnitt,
FIG 2
eine Gasturbinenleitschaufel mit einer schraubenförmigen Heizwendel und
FIG 3
eine erfindungsgemäße Gasturbinenleitschaufel nach FIG 2 im Querschnitt.
The invention will be explained with reference to figures.
Show it:
FIG. 1
a gas turbine in a longitudinal section,
FIG. 2
a gas turbine vane with a helical heating coil and
FIG. 3
a gas turbine vane according to the invention according to FIG 2 in cross section.

FIG 1 zeigt eine Gasturbine 1 in einem Längsteilschnitt. Sie weist im Inneren einen um eine Rotationsachse 2 drehgelagerten Rotor 3 auf, der auch als Turbinenläufer bezeichnet wird. Entlang des Rotors 3 folgen aufeinander ein Ansauggehäuse 4, ein Verdichter 5, eine torusartige Ringbrennkammer 6 mit mehreren rotationssymmetrisch zueinander angeordneten Brennern 7, eine Turbineneinheit 8 und ein Abgasgehäuse 9. Die Ringbrennkammer 6 bildet einen Verbrennungsraum 17, der mit einem ringförmigen Heißgaskanal 18 kommuniziert. Dort bilden vier hintereinander geschaltete Turbinenstufen 10 die Turbineneinheit 8. Jede Turbinenstufe 10 ist aus zwei Schaufelringen gebildet. In Strömungsrichtung eines in der Ringbrennkammer 6 erzeugten Heißgases 11 gesehen, folgt im Heißgaskanal 18 jeweils einer Leitschaufelreihe 13 eine aus Laufschaufeln 15 gebildete Reihe 14. Die Leitschaufeln 12 sind am Stator befestigt, wohingegen die Laufschaufeln 15 einer Reihe 14 mittels einer Turbinenscheibe am Rotor 3 angebracht sind. An dem Rotor 3 ist ein Generator oder eine Arbeitsmaschine (nicht dargestellt) angekoppelt.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. There form four successive turbine stages 10, the turbine unit 8. Each turbine stage 10 is formed of two blade rings. As seen in the flow direction of a hot gas 11 produced in the annular combustion chamber 6, in the hot gas channel 18 in each case one row of blades 13 followed by a number of rows of blades 14. The vanes 12 are attached to the stator, whereas the blades 15 a row 14 mounted by means of a turbine disk on the rotor 3 are. On the rotor 3, a generator or a working machine (not shown) is coupled.

Eine erfindungsgemäße Gasturbinenleitschaufel 30 ist in FIG 2 in einem Längsschnitt dargestellt. Die Gasturbinenschaufel 30 weist ein Schaufelprofil 32 auf, welches sich zwischen zwei Plattformen 34 erstreckt. Die Plattform 34 bildet die radial äußere und innere Begrenzung des Heißgaskanals 18, in welchem beim Betrieb der Gasturbine das Heißgas 11 strömt. Die anströmseitige Vorderkante des Schaufelprofils 32 wird als Anströmkante 36 bezeichnet. Am gegenüberliegenden Ende weist das Schaufelprofil 32 eine Schaufelhinterkante 37 auf, an der das Heißgas 11 abströmt.A gas turbine guide vane 30 according to the invention is shown in FIG. 2 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. At the opposite end, the blade profile 32 has a blade trailing edge 37, at which the hot gas 11 flows.

Das Schaufelprofil 32 kann mehrere Hohlräume 38 aufweisen, in die ein durch die Plattformen 34 zugeführtes Kühlmedium 40, vorzugsweise Kühlluft, einströmen und die gegossene Turbinenschaufel 30 kühlen kann. Zur Kühlung können die gängigen Kühlmethoden wie Konvektionskühlung, Prallkühlung und/oder Filmkühlung sowie Effusionskühlung eingesetzt werden.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. For cooling, the common cooling methods such as convection cooling, impingement cooling and / or film cooling and effusion cooling can be used.

Um die Gasturbinenleitschaufel 30 vor dem Kaltstart der Gasturbine 1 vorzuheizen, ist in einem der Hohlräume 38, jedoch vorzugsweise in dem Hohlraum, welcher der Anströmkante 36 nachgeordnet ist, d.h. im Anströmkantenkanal 40, ein elektrisches Heizelement 50 vorgesehen. Das Heizelement 50 erstreckt sich annähernd über die vollständige Länge der Anströmkante 36, d.h. von der radial innen liegenden Plattform 34a zur äußeren Plattform 34b.In order to preheat the gas turbine guide vane 30 before the cold start of the gas turbine 1, 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.

Um eine besonders gleichmäßige Erwärmung der Gasturbinenschaufel 30 zu ermöglichen, ist das Heizelement 50 als schraubenförmige Heizwendel 54 ausgebildet.In order to allow a particularly uniform heating of the gas turbine blade 30, the heating element 50 is formed as a helical heating coil 54.

FIG 3 zeigt einen Querschnitt durch die erfindungsgemäße Gasturbinenschaufel 30 gemäß FIG 2. Im Anströmkantenkanal 42 ist die schraubenförmige Heizwendel 54 angeordnet, welche zur lebensdauerverlängernden Vorerwärmung bzw. Nachbeheizung der Gasturbinenleitschaufel 30 von einem regulierbaren elektrischen Heizstrom durchflossen werden kann. Der elektrische Heizstrom ruft in der Heizwendel 54 eine Wärmestrahlung hervor, die das Material der gegossenen Gasturbinenleitschaufel 30, vorzugsweise das Material des Schaufelprofils 32 und der Plattform 34, vor dem Betrieb der Gasturbine 1 vergleichsweise langsam erwärmt, um die thermomechanischen Materialspannungen in einer für die LCF-Lebensdauer unkritischen Größenordnung anwachsen oder nach dem Betrieb abklingen zu lassen.3 shows a cross section through the gas turbine blade 30 according to the invention as shown in FIG 2. In the leading edge channel 42, the helical heating coil 54 is arranged, which can be traversed for life-prolonging preheating or Nachbeheizung the gas turbine guide vane 30 of a controllable electric heating. 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.

Durch die Vorerwärmung bzw. Nachheizung der Gasturbinenleitschaufel 30 können besonders starke in einem vergleichsweise kurzen Zeitintervall auftretende Temperaturschwankungen, so genannte Temperaturschocks, vermieden werden, was zu einer Erhöhung der Kurzzeitschwingfestigkeit führt und die Rissentstehung bzw. das Risswachstum im Schaufelmaterial wirkungsvoll vermindert.By preheating or reheating the gas turbine guide vane 30, particularly high temperature fluctuations occurring in a comparatively short time interval, so-called temperature shocks, can be avoided, which leads to an increase in the short-term vibration resistance and effectively reduces the cracking or crack growth in the vane material.

Claims (9)

Gekühlte Gasturbinenleitschaufel (30) für eine Gasturbine (1),
mit einem hohlem Schaufelprofil (32), welches eine von einem Arbeitsmedium anströmbare Anströmkante (36) umfasst, und
mit einem im Inneren des Schaufelprofils (32) entlang der Anströmkante (36) verlaufenden Anströmkantenkanal (40) zur Führung eines Kühlmediums,
dadurch gekennzeichnet,
dass im Anströmkantenkanal (40) ein elektrisches Heizelement (50) vorgesehen ist, welches sich annähernd vollständig über die gesamte Länge des Anströmkantenkanals (40) erstreckt.Cooled gas turbine guide vanes (30) for a gas turbine (1),
with a hollow blade profile (32), which comprises an approachable by a working medium leading edge (36), and
with a leading edge channel (40) running along the leading edge (36) inside the blade profile (32) for guiding a cooling medium,
characterized,
that an electrical heating element (50) is provided in the leading edge channel (40), which extends approximately completely over the entire length of the Anströmkantenkanals (40). Gasturbinenleitschaufel (30) nach Anspruch 1,
bei der das elektrische Heizelement (50) an der Kanalwand des Anströmkantenkanals (40) anliegt oder zumindest teilweise in der Kanalwand integriert ist.Gas turbine vane (30) according to claim 1,
wherein the electrical heating element (50) on the channel wall of the leading edge channel (40) is present or at least partially integrated in the channel wall. Gasturbinenleitschaufel (30) nach Anspruch 1 oder 2, bei der das Heizelement (50) als schraubenförmige Heizwendel (54) ausgebildet ist.A gas turbine vane (30) according to claim 1 or 2, wherein the heating element (50) is formed as a helical heating coil (54). Verwendung einer Gasturbinenleitschaufel (30) nach einem der Ansprüche 1 bis 3 in einer stationären Gasturbine (1).Use of a gas turbine guide vane (30) according to one of claims 1 to 3 in a stationary gas turbine (1). Verfahren zum Betreiben einer Gasturbine (1) mit einer Gasturbinenleitschaufel (30) nach einem der Anspruch 1 bis 3,
dadurch gekennzeichnet, dass
vor dem Kaltstart der Gasturbine (1) die Gasturbinenleitschaufel (30) vorgeheizt wird.Method for operating a gas turbine (1) with a gas turbine guide blade (30) according to one of claims 1 to 3,
characterized in that
before the cold start of the gas turbine (1), the gas turbine guide vane (30) is preheated. Verfahren nach Anspruch 5,
bei dem während des Heizvorgangs die der Gasturbinenleitschaufel (30) zugeführte Wärmeleistung erhöht wird.Method according to claim 5,
in which during the heating process, the gas turbine guide vane (30) supplied heat output is increased. Verfahren nach Anspruch 5 oder 6,
bei dem die Beheizung vor oder während des Startens der Gasturbine (1) eingestellt wird.Method according to claim 5 or 6,
in which the heating is adjusted before or during the starting of the gas turbine (1). Verfahren zum Betreiben einer Gasturbine (1) mit einer Gasturbinenleitschaufel (30) nach einem der Ansprüche 1 bis 3,
dadurch gekennzeichnet, dass
nach dem Abschalten der Gasturbine (1) die Gasturbinenleitschaufel (30) nachgeheizt wird.Method for operating a gas turbine (1) with a gas turbine guide vane (30) according to one of claims 1 to 3,
characterized in that
after switching off the gas turbine (1), the gas turbine guide vane (30) is reheated. Verfahren nach Anspruch 8,
bei dem während des Heizvorgangs die der Gasturbinenleitschaufel (30) zugeführte Wärmeleistung abgesenkt wird.Method according to claim 8,
in which during the heating process, the gas turbine guide vane (30) supplied heat output is lowered.
EP05014377A 2005-07-01 2005-07-01 Cooled gas turbine stator vane and method of operation of a gas turbine Not-in-force EP1739285B1 (en)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP05014377A EP1739285B1 (en) 2005-07-01 2005-07-01 Cooled gas turbine stator vane and method of operation of a gas turbine
AT05014377T ATE446439T1 (en) 2005-07-01 2005-07-01 COOLED GAS TURBINE GUIDE BLADE FOR A GAS TURBINE, USE OF A GAS TURBINE GUIDE BLADE AND METHOD FOR OPERATING A GAS TURBINE
DE502005008377T DE502005008377D1 (en) 2005-07-01 2005-07-01 A cooled gas turbine nozzle for a gas turbine, use of a gas turbine nozzle and method for operating a gas turbine
JP2006178356A JP2007009911A (en) 2005-07-01 2006-06-28 Cooled type gas turbine stator vane in gas turbine, use of gas turbine stator vane, and method for operation of gas turbine
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 (en) 2005-07-01 2005-07-01 Cooled gas turbine stator vane and method of operation of a gas turbine

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DE502005008377D1 (en) 2009-12-03
JP2007009911A (en) 2007-01-18
ATE446439T1 (en) 2009-11-15
US20090074572A1 (en) 2009-03-19
US20070116563A1 (en) 2007-05-24
US7465150B2 (en) 2008-12-16

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