EP2455584B1 - Gasturbine comprising cooling control means which are made partially of Shape Memory Materials (SMM) - Google Patents
Gasturbine comprising cooling control means which are made partially of Shape Memory Materials (SMM) Download PDFInfo
- Publication number
- EP2455584B1 EP2455584B1 EP11187629.8A EP11187629A EP2455584B1 EP 2455584 B1 EP2455584 B1 EP 2455584B1 EP 11187629 A EP11187629 A EP 11187629A EP 2455584 B1 EP2455584 B1 EP 2455584B1
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- EP
- European Patent Office
- Prior art keywords
- swirl
- flow
- vanes
- temperature
- control means
- 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
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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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
-
- 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
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
-
- 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
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
-
- 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
-
- 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
- F01D25/12—Cooling
-
- 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
- F01D5/08—Heating, heat-insulating or cooling means
-
- 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
- F01D5/187—Convection cooling
-
- 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
- F05D2270/30—Control parameters, e.g. input parameters
- F05D2270/303—Temperature
-
- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/50—Intrinsic material properties or characteristics
- F05D2300/505—Shape memory behaviour
Definitions
- Part of the air is also used for sealing purposes, particularly between the rotating and stationary parts of the gas turbine 10, such as between the stator 28 and the rotor 22 (see the sealing systems 23a, 23b and 23c in FIG Fig. 1 ).
- gaps are rinsed with air which is introduced into the hot-gas channel (see hot-gas main stream 29 in FIG Fig. 1 ) and thus prevents the entry of hot gas and thus a local overheating at this point.
- the invention is characterized in that the swirl vanes are each arranged displaceably in a transversely varying manner in the swirl duct transversely to the flow direction, that adjusting elements are provided from a memory alloy to move the swirl vanes temperature-dependent, and that the displaceable vortex vanes each on the upstream Side are provided with a baffle, which initiates the flowing medium in the spinal canal in the narrowed by the swirl vanes cross-section.
- the adjusting device 43 has a wall-parallel wall element arranged on the side of the blade root of the swirl blade 26 44 with associated baffle 45, which in turn can be moved by adjusting 42 of a memory alloy perpendicular to the wall.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
Die vorliegende Erfindung bezieht sich auf das Gebiet der Energie erzeugenden Maschinen. Sie betrifft eine rotieren Maschine gemäss dem Oberbegriff des Anspruchs 1.The present invention relates to the field of power generating machines. It relates to a rotary machine according to the preamble of claim 1.
In Energie erzeugenden rotierenden Maschinen, wie zum Beispiel Gasturbinen oder Elektro-Generatoren, stellt die erforderliche Kühlung von thermisch stark belasteten Teilen einen wesentlichen physikalischen Parameter dar, der sich auf den gesamten Wirkungsgrad und die Lebensdauer des Systems auswirkt. In den meisten Fällen wird als Kühlmittel Luft eingesetzt; es kann aber auch Dampf, der aus einem Dampferzeuger abgezweigt wird, für denselben Zweck benutzt werden. Die vorliegende Erfindung ist, obwohl sie am Beispiel einer luftgekühlten Gasturbine erläutert wird, nicht auf eine spezielle Kühlungsart beschränkt und kann daher für alle Arten von Kühlmedien eingesetzt werden.In power-generating rotating machinery, such as gas turbines or electric generators, the required cooling of thermally stressed parts is a significant physical parameter that affects the overall efficiency and life of the system. In most cases, air is used as the coolant; but it can also steam, which is diverted from a steam generator, are used for the same purpose. The present invention, although exemplified by an air-cooled Gas turbine is not limited to a specific type of cooling and can therefore be used for all types of cooling media.
In
Ein Teil der Luft wird auch für Dichtungszwecke verwendet, insbesondere zwischen den rotierenden und stationären Teilen der Gasturbine 10, wie zum Beispiel zwischen dem Stator 28 und dem Rotor 22 (siehe die Dichtungssysteme 23a, 23b und 23c in
Es ist allgemein üblich, in diesem Zusammenhang spezielle Einrichtungen zu verwenden, die als in Wirbelkanälen 27 angeordnete Vorwirbeldüsen bezeichnet werden (24 in
Unter Betriebsbedingungen kann die thermische Last auf den heissen Bauteilen der Turbine abnehmen oder zunehmen, je nachdem ob die Gasturbine 10 unter Teillast oder Volllast gefahren wird. Beispielsweise wird eine Reduktion der Ausgangsleistung der Gasturbine üblicherweise durch eine Absenkung der Flammentemperatur in der Brennkammer bewirkt. Abhängig von der nachgefragten Leistung kann die Gasturbine mit Volllast und Teillast betrieben werden, wobei die Volllast den nominalen Betriebsbedingungen entspricht. Die verschiedenen Betriebszustände werden mit veränderbaren Leitschaufeln (Variable Guide Vanes VGV) in den Verdichterstufen gesteuert, die ihren Staffelungswinkel in Abhängigkeit von der gewünschten Ausgangsleistung verändern. Hierdurch ergibt sich ein maximaler oder geringerer Luftmassenstrom bei einer konstanten Drehgeschwindigkeit 21.Under operating conditions, the thermal load on the hot components of the turbine may decrease or increase, depending on whether the
Die Grösse der Strömungsgeschwindigkeit c der Luft hinter in den Wirbelkanälen 27 angeordneten Wirbelschaufeln 26 (siehe
gegeben, wobei Ω die Drehgeschwindigkeit 21 der Turbine und R der mittlere Radius am Auslass der Wirbelkanäle 27 ist (siehe
wobei T die statische Temperatur und Cp die spezifische Wärme bezeichnen.The magnitude of the flow velocity c of the air behind
where Ω is the
where T is the static temperature and C p is the specific heat.
Für eine konstante Drehgeschwindigkeit Ω wird die Teillast durch die veränderbaren Leitschaufeln VGV erreicht, die den Massenstrom im Verdichter 11 reduzieren. Daraufhin nimmt die Luftgeschwindigkeit c hinter der Wirbeleinrichtung (Wirbelschaufeln 26) ab. Schliesslich wird davon auch die resultierende Geschwindigkeit w beeinflusst, was direkte Auswirkungen auf die Metalltemperaturen der rotierenden heissen Teile, wie der Schaufelfüsse 19, der Schaufelhälse 20 und der Plattformen 25, hat. Wird die Metalltemperatur bei konstanter Drehgeschwindigkeit konstant gehalten, unterliegen die entsprechenden mechanischen Komponenten keiner niedrigzyklischen Ermüdung (Low Cycle Fatigue LCF). Dies könnte technisch durch gesteuerte Ventile erreicht werden. Tatsächlich ist jedoch die Wirbeleinrichtung üblicherweise nicht mit Steuerelementen versehen, die den Massenstrom in den Kühldurchgängen 14 beeinflussen können, da diese Region des Rotors 22 und des Stators 28 nur beschränkt zugänglich ist.For a constant rotational speed Ω, the partial load is achieved by the variable guide vanes VGV, which reduce the mass flow in the
Die Steuerung der Kühlluft-Verteilung im Rotor 22, im Stator 28 und in den Turbinenschaufeln 27 ist ein kompliziertes Unterfangen, das zusätzlich erschwert wird durch die Forderung, Rückströmungen zu vermeiden. Daraus folgt, dass eine einfache Drosselung keine gute Lösung darstellt, und dass es von Vorteil ist, eine Steuereinrichtung mit einer aerodynamisch optimierten Gestaltung einzusetzen. Solch eine Einrichtung ist die Vorwirbeldüse 24, die üblicherweise durch eine stationäre Reihe von Schaufelblättern nach Art von Turbinen-Leitschaufeln gebildet wird (Wirbelschaufeln 26 in
Könnte im Bereich der Vorwirbeldüse 24 eine einfache, funktionssichere selbsttätige Regelung des Massenstroms auf einfache Weise verwirklicht werden, liesse sich ohne grossen Aufwand eine besonders effektive Kühlung der entsprechenden Bereiche bei unterschiedlichen Lastzuständen der Turbine verwirklichen.Could in the vortex nozzle 24 a simple, reliable automatic control of the mass flow can be realized in a simple manner, could be realized without great effort, a particularly effective cooling of the corresponding areas at different load conditions of the turbine.
Aus der Druckschrift
Aus der Druckschrift
In beiden Fällen ist der Hauptstrom des Kühlmediums betroffen.In both cases, the main flow of the cooling medium is affected.
Weiterhin offenbart die Druckschrift
Die Druckschrift
Es ist eine Aufgabe der Erfindung, eine rotierende Maschine, insbesondere eine Gasturbine, zu schaffen in welcher durch Steuerung des Kühlmittel-Massenstroms in einem sekundären Kühlbereich (SAF-Secondary Air Flow) die Effizienz der Kühlung und der Wirkungsgrad der Maschine verbessert werden.It is an object of the invention to provide a rotary machine, in particular a gas turbine, in which by controlling the coolant mass flow In a Secondary Air Flow Secondary Airflow (SAF), the efficiency of cooling and the efficiency of the machine can be improved.
Die Aufgabe wird durch die Gesamtheit der Merkmale des Anspruchs 1 gelöst. Die Erfindung geht aus von einer rotierenden Maschine, welche durch ein Kühlmedium, gekühlt wird, welches Kühlmedium in einem Hauptstrom und einem Sekundärstrom durch die Maschine geführt wird, wobei die rotierende Maschine einen Rotor und einen Stator umfasst, der Sekundärstrom des Kühlmediums durch Wirbelkanäle im Stator zu einer Vorwirbeldüse geführt wird und dort aus dem Stator austritt, Steuerungsmittel zur temperaturabhängigen Steuerung des Sekundärstroms in der Vorwirbeldüse angeordnet sind, welche Steuerungsmittel ganz oder teilweise aus einer Gedächtnislegierung bestehen, und wobei in der Vorwirbeldüse Wirbelschaufeln angeordnet sind, und die Steuerungsmittel derart ausgebildet sind, dass der Strömungsquerschnitt der Wirbelkanäle im Bereich der Wirbelschaufeln temperaturabhängig veränderbar ist.The object is solved by the entirety of the features of claim 1. The invention is based on a rotating machine which is cooled by a cooling medium, which cooling medium is passed through the machine in a main flow and a secondary flow, wherein the rotating machine comprises a rotor and a stator, the secondary flow of the cooling medium through swirl ducts in the stator is guided to a Vorwirbeldüse and there exits the stator, control means for temperature-dependent control of the secondary flow are arranged in the Vorwirbeldüse, which control means consist entirely or partially of a memory alloy, and wherein vortex blades are arranged in the Vorwirbeldüse, and the control means are designed such that the flow cross-section of the swirl ducts in the region of the swirl vanes is temperature-dependent changeable.
Die Erfindung ist dadurch gekenntzeichnet, dass die Wirbelschaufeln jeweils in einer den Querschnitt verändernden Weise im Wirbelkanal quer zur Strömungsrichtung verschiebbar angeordnet sind, dass Verstellelemente aus einer Gedächtnislegierung vorgesehen sind, um die Wirbelschaufeln temperaturabhängig zu verschieben, und dass die verschiebbaren Wirbelschaufeln jeweils auf der stromaufwärts gelegenen Seite mit einem Leitblech versehen sind, welches das im Wirbelkanal strömende Medium in den durch die Wirbelschaufeln verengten Querschnitt einleitet.The invention is characterized in that the swirl vanes are each arranged displaceably in a transversely varying manner in the swirl duct transversely to the flow direction, that adjusting elements are provided from a memory alloy to move the swirl vanes temperature-dependent, and that the displaceable vortex vanes each on the upstream Side are provided with a baffle, which initiates the flowing medium in the spinal canal in the narrowed by the swirl vanes cross-section.
Die Erfindung soll nachfolgend anhand von Ausführungsbeispielen im Zusammenhang mit der Zeichnung näher erläutert werden. Es zeigen:
- Fig. 1
- in einem Ausschnitt einen Teil einer Gasturbine mit verschiedenen Wegen für die Verteilung von Kühlluft;
- Fig. 2
- in einem vergrösserten Ausschnitt aus
Fig. 1 die Ausgestaltung des Wirbelkanals; - Fig. 3
- in verschiedenen Ansichten 3a-c die in der Vorwirbeldüse aus
Fig. 1 angeordneten Wirbelschaufeln; - Fig. 4
- in verschiedenen Teilfiguren 4b-f verschiedene Ausführungsbeispiele für eine selbsttätige Regelung des Kühlluft-Massenstroms im Wirbelkanal gegenüber der ungeregelten Anordnung (
Fig. 4a ); - Fig. 5
- in zwei unterschiedlichen Ansichten 5a-b ein weiteres Ausführungsbeispiel für eine selbsttätige Regelung durch Verschwenken der Wirbelschaufeln;
- Fig. 6
- im Schnitt eine weitere Möglichkeit der selbsttätigen Regelung des Kühlluft-Massenstroms im Wirbelkanal durch selbsttätige Veränderung des Austrittsquerschnitts;
- Fig. 7
- in mehreren Teilfiguren 7a-c verschiedene Zustände bei einem Ausführungsbeispiel für eine selbsttätige Steuerung des Austrittsquerschnitts;
- Fig. 8
- in mehreren Teilfiguren 8a-b verschiedene Zustände bei einem anderen Ausführungsbeispiel für eine selbsttätige Steuerung des Austrittsquerschnitts;
- Fig. 9
- eine zu
Fig. 7 vergleichbare Ausgestaltung, bei der die einzelnen Elemente jeweils selbsttätig um eine Achse gedreht werden und - Fig. 10
- eine zu
Fig. 8 vergleichbare Ausgestaltung, bei der die einzelnen Elemente jeweils selbsttätig um eine Achse gedreht werden.
- Fig. 1
- in a section of a part of a gas turbine with different ways for the distribution of cooling air;
- Fig. 2
- in an enlarged section
Fig. 1 the embodiment of the spinal canal; - Fig. 3
- in different views 3a-c in the Vorwirbeldüse
Fig. 1 arranged swirl vanes; - Fig. 4
- in different sub-figures 4b-f different embodiments of an automatic control of the cooling air mass flow in the vortex channel with respect to the unregulated arrangement (
Fig. 4a ); - Fig. 5
- in two different views 5a-b another embodiment of an automatic control by pivoting the swirl vanes;
- Fig. 6
- on average another possibility of automatic control of the cooling air mass flow in the spinal canal by automatically changing the outlet cross section;
- Fig. 7
- in several sub-figures 7a-c different states in an embodiment for an automatic control of the outlet cross section;
- Fig. 8
- in several sub-figures 8a-b different states in another embodiment for an automatic control of the outlet cross section;
- Fig. 9
- one too
Fig. 7 Comparable embodiment in which the individual elements are each automatically rotated about an axis and - Fig. 10
- one too
Fig. 8 comparable embodiment in which the individual elements are each automatically rotated about an axis.
Gemäss einem bevorzugten Ausführungsbeispiel der Erfindung wird die Vorwirbeldüse 24 in einer Gasturbine 10 nach
Hierbei kann ein Schrumpfen, ein Strecken, eine Verdrehung (Torsion) und eine Verbiegung der aus der Gedächtnislegierung bestehenden Teile als Mechanismus für die Reduzierung des Durchflussquerschnitts des ansonsten aus einem Stahl bestehenden, einfachen Systems herangezogen werden.
Im Beispiel der
Im Beispiel der
Im Beispiel der
Im Beispiel der
Im Beispiel der
Ein weiteres Beispiel für einen geeigneten Verstellmechanismus ist in
Eine weitere Möglichkeit besteht darin, gemäss
Besteht die Blende, wie in
Abhängig von der Form des Wirbelkanals 27 kann die Blende aber auch gemäss
Es ist aber auch denkbar, die Anordnung gemäss
Insgesamt beschreibt die vorliegende Erfindung den Einsatz von Gedächtnislegierungen im sekundären Kühlmittelsystem einer rotierenden Maschine zur die Effizienz steigernden Regelung des Kühlmittelverbrauchs in Abhängigkeit vom Lastzustand der Maschine. Die im Ausführungsbeispiel beschriebene Verwirbelung kann unterschiedliche Formen annehmen, die entsprechende Änderungen des Verstellmechanismus erfordern. Der beschriebene selbsttätige Regelungsmechanismus auf der Basis von Gedächtnislegierungen kann auch bei Hitzeschilden eingesetzt werden, um den Kühlmittelverbrauch in Abhängigkeit von der Leistung (der Gasturbine) zu steuern.Overall, the present invention describes the use of memory alloys in the secondary coolant system of a rotating machine for efficiency-increasing control of the coolant consumption as a function of the load condition of the machine. The turbulence described in the embodiment can take different forms that require corresponding changes in the adjustment mechanism. The described self-regulating mechanism based on memory alloys can also be used in heat shields to control the coolant consumption as a function of the power (of the gas turbine).
Die vorgeschlagene Anordnung kann von einer weiteren Absenkung der Kühlmitteltemperatur relativ zur totalen Temperatur im rotierenden Referenzrahmen profitieren. Dies führt zur Möglichkeit, die benötigten Kühlluft-Massenströme weiter zu verringern und damit die Leistung und Effektivität der Gasturbine zu erhöhen.The proposed arrangement may benefit from further lowering the coolant temperature relative to the total temperature in the rotating reference frame. This leads to the possibility to further reduce the required cooling air mass flows and thus to increase the performance and effectiveness of the gas turbine.
Die Gedächtnislegierung kann aus unterschiedlichen metallurgischen Zusammensetzungen verschiedener Elemente bestehen und auch mit unterschiedlichen Technologien hergestellt werden. Eine Veränderung der Temperatur und/oder eine mechanische Veränderung der Maschine startet den Prozess der Geometrieänderung des aus der Gedächtnislegierung bestehenden Bauteils. Im Falle einer abnehmenden Toleranz beim Zusammenbau wird das Schrumpfungsverhalten des Bauteils anstelle einer Dehnung in Betracht gezogen.The memory alloy can consist of different metallurgical compositions of different elements and can also be produced with different technologies. A change in temperature and / or a mechanical change of the machine will start the process of geometry change of the memory alloy component. In the case of decreasing assembly tolerance, the shrinkage behavior of the component is considered instead of elongation.
Obgleich der vorgeschlagene Mechanismus am Beispiel einer Gasturbine erläutert worden ist, kann die Kühlmittelsteuerung auf der Basis von Elementen aus einer Gedächtnislegierung auch in anderen Maschinen eingesetzt werden, wo eine aktive selbsttätige Steuerung des Kühlmittel-Massenstroms benötigt wird.Although the proposed mechanism has been explained using the example of a gas turbine, the memory alloy based coolant control can also be used in other machines where active automatic control of the coolant mass flow is required.
- 1010
- Gasturbinegas turbine
- 1111
- Verdichtercompressor
- 1212
- Verdichterluft-HauptstromCompressor air-mainstream
- 1313
- Sekundärstromsecondary current
- 1414
- KühldurchgangCooling passage
- 1515
- HochtemperaturbereichHigh temperature range
- 1616
- Leitschaufelvane
- 1717
- Laufschaufelblade
- 1818
- LeitschaufelbefestigungLeitschaufelbefestigung
- 1919
- Schaufelfussblade root
- 2020
- Schaufelhalsscoop-neck
- 2121
- Drehgeschwindigkeitrotation speed
- 2222
- Rotorrotor
- 23a-c23a-c
- Dichtungssystemsealing system
- 2424
- VorwirbeldüseVorwirbeldüse
- 2525
- Plattformplatform
- 2626
- Wirbelschaufelswirl vane
- 2727
- Wirbelkanalspinal canal
- 2828
- Statorstator
- 2929
- Heissgas-HauptstromHot gas main stream
- 3131
- Verdichtergehäusecompressor housing
- 3232
- Verdichter-LeitschaufelCompressor vane
- 3333
- Verdichter-LaufschaufelCompressor blade
- 3434
- Maschinenachsemachine axis
- 3535
- Verengungnarrowing
- 3636
- Membranmembrane
- 37,41,4337,41,43
- Verstellvorrichtungadjustment
- 38,4438.44
- Wandelementwall element
- 39,45,4739,45,47
- Leitblechbaffle
- 40,42,4640,42,46
- Verstellelementadjustment
- 4848
- Torsionselementtorsion
- 4949
- Blendecover
- 50,51,53,5550,51,53,55
- Blendenelementdiaphragm element
- 5252
- Ausdehnungexpansion
- 54,5654.56
- Torsionselementtorsion
- FF
- Flächearea
Claims (1)
- Gas turbine which is cooled by means of a cooling medium, which cooling medium is directed through the machine (10) in a main flow (12) and in a secondary flow (13), where the rotating machine (10) comprises a rotor (22) and a stator (28), the secondary flow (13) of the cooling medium is directed through swirl passages (27) in the stator (28) to a pre-swirl nozzle (24) and discharges from the stator (28) there, control means (36 - 56) for the temperature-dependent control of the secondary flow (13) are arranged in the pre-swirl nozzle (24), which control means (36 - 56) consist entirely or partially of a shape-memory alloy, and where swirl vanes (26) are arranged in the pre-swirl nozzle (24), and the control means (36 - 48) are formed in such a way that the flow cross section of the swirl passages (27) can be altered in the region of the swirl vanes (26) in dependence upon temperature, characterized in that the swirl vanes (26) are arranged in each case in a manner in which they can be displaced in the swirl passage (27) transversely to the flow direction and in a way in which they alter the cross section, in that provision is made for adjusting elements (46), consisting of a shape-memory alloy, in order to displace the swirl vanes (26) in dependence upon temperature, and in that the displaceable swirl vanes (26), on the upstream-disposed side, are provided in each case with a baffle plate (47) which directs the medium flowing in the swirl passage (27) into the cross section which is constricted by means of the swirl vanes (26).
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH01947/10A CH704124A1 (en) | 2010-11-19 | 2010-11-19 | Rotating machine, in particular gas turbine. |
Publications (2)
Publication Number | Publication Date |
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EP2455584A1 EP2455584A1 (en) | 2012-05-23 |
EP2455584B1 true EP2455584B1 (en) | 2015-06-17 |
Family
ID=43478440
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP11187629.8A Not-in-force EP2455584B1 (en) | 2010-11-19 | 2011-11-03 | Gasturbine comprising cooling control means which are made partially of Shape Memory Materials (SMM) |
Country Status (4)
Country | Link |
---|---|
US (2) | US9267382B2 (en) |
EP (1) | EP2455584B1 (en) |
JP (1) | JP5933232B2 (en) |
CH (1) | CH704124A1 (en) |
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Publication number | Priority date | Publication date | Assignee | Title |
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US9297310B2 (en) | 2012-10-18 | 2016-03-29 | General Electric Company | Part load performance improvement using deformable bore plugs |
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US10641174B2 (en) | 2017-01-18 | 2020-05-05 | General Electric Company | Rotor shaft cooling |
KR102028591B1 (en) * | 2018-01-08 | 2019-10-04 | 두산중공업 주식회사 | Turbine vane assembly and gas turbine including the same |
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US4296599A (en) * | 1979-03-30 | 1981-10-27 | General Electric Company | Turbine cooling air modulation apparatus |
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DE3542762A1 (en) * | 1985-12-04 | 1987-06-11 | Mtu Muenchen Gmbh | DEVICE FOR CONTROLLING OR CONTROLLING GAS TURBINE ENGINES OR GAS TURBINE JET ENGINES |
FR2604750B1 (en) * | 1986-10-01 | 1988-12-02 | Snecma | TURBOMACHINE PROVIDED WITH AN AUTOMATIC CONTROL DEVICE FOR TURBINE VENTILATION FLOWS |
US5022817A (en) * | 1989-09-12 | 1991-06-11 | Allied-Signal Inc. | Thermostatic control of turbine cooling air |
JPH08296455A (en) | 1995-04-27 | 1996-11-12 | Ishikawajima Harima Heavy Ind Co Ltd | Turbo-engine |
DE19756734A1 (en) * | 1997-12-19 | 1999-06-24 | Bmw Rolls Royce Gmbh | Passive gap system of a gas turbine |
GB2354290B (en) * | 1999-09-18 | 2004-02-25 | Rolls Royce Plc | A cooling air flow control device for a gas turbine engine |
US6468032B2 (en) * | 2000-12-18 | 2002-10-22 | Pratt & Whitney Canada Corp. | Further cooling of pre-swirl flow entering cooled rotor aerofoils |
GB0403198D0 (en) * | 2004-02-13 | 2004-03-17 | Rolls Royce Plc | Casing arrangement |
DE602005005673T2 (en) * | 2005-09-08 | 2009-05-07 | C.R.F. Società Consortile per Azioni, Orbassano | Diaphragm valve with shape memory actuation |
GB0606823D0 (en) * | 2006-04-05 | 2006-05-17 | Rolls Royce Plc | Adjustment assembly |
US20090226327A1 (en) * | 2008-03-07 | 2009-09-10 | Siemens Power Generation, Inc. | Gas Turbine Engine Including Temperature Control Device and Method Using Memory Metal |
US8079803B2 (en) | 2008-06-30 | 2011-12-20 | Mitsubishi Heavy Industries, Ltd. | Gas turbine and cooling air supply structure thereof |
GB0818047D0 (en) | 2008-10-03 | 2008-11-05 | Rolls Royce Plc | Turbine cooling system |
GB0908373D0 (en) * | 2009-05-15 | 2009-06-24 | Rolls Royce Plc | Fluid flow control device |
-
2010
- 2010-11-19 CH CH01947/10A patent/CH704124A1/en not_active Application Discontinuation
-
2011
- 2011-11-03 EP EP11187629.8A patent/EP2455584B1/en not_active Not-in-force
- 2011-11-16 US US13/297,288 patent/US9267382B2/en not_active Expired - Fee Related
- 2011-11-21 JP JP2011253752A patent/JP5933232B2/en not_active Expired - Fee Related
-
2016
- 2016-01-27 US US15/007,542 patent/US20160138410A1/en not_active Abandoned
Also Published As
Publication number | Publication date |
---|---|
EP2455584A1 (en) | 2012-05-23 |
JP5933232B2 (en) | 2016-06-08 |
CH704124A1 (en) | 2012-05-31 |
US20160138410A1 (en) | 2016-05-19 |
JP2012112382A (en) | 2012-06-14 |
US20120128473A1 (en) | 2012-05-24 |
US9267382B2 (en) | 2016-02-23 |
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