EP2148977B1 - Gas turbine - Google Patents

Gas turbine Download PDF

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Publication number
EP2148977B1
EP2148977B1 EP08758019A EP08758019A EP2148977B1 EP 2148977 B1 EP2148977 B1 EP 2148977B1 EP 08758019 A EP08758019 A EP 08758019A EP 08758019 A EP08758019 A EP 08758019A EP 2148977 B1 EP2148977 B1 EP 2148977B1
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EP
European Patent Office
Prior art keywords
rotor
shaft
cooling air
gas turbine
cone
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Not-in-force
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EP08758019A
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German (de)
French (fr)
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EP2148977A2 (en
Inventor
Wilfried Weidmann
Moritz Wirth
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MTU Aero Engines AG
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MTU Aero Engines GmbH
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Publication of EP2148977A2 publication Critical patent/EP2148977A2/en
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    • 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
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc
    • 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
    • F01D25/125—Cooling of bearings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/025—Fixing blade carrying members on shafts

Definitions

  • the invention relates to a gas turbine having a rotor, which comprises a turbine rotor, a shaft and a compressor rotor and in the case of a multi-shaft gas turbine is part of the low-pressure system, wherein the turbine rotor has at least one bladed rotor disk and one from the or a rotor disk to the shaft leading rotor cone, and wherein the downstream end of the shaft is rotatably supported in a bearing with bearing chamber, according to the preamble of claim 1.
  • a gas turbine having a rotor, which comprises a turbine rotor, a shaft and a compressor rotor and in the case of a multi-shaft gas turbine is part of the low-pressure system, wherein the turbine rotor has at least one bladed rotor disk and one from the or a rotor disk to the shaft leading rotor cone, and wherein the downstream end of the shaft is rotatably supported in a bearing with bearing chamber, according to the preamble of claim 1.
  • Such an arrangement
  • Future engine concepts require high-speed low-pressure turbines with high AN 2 , high turbine inlet temperatures and compact, short design to meet the required specifications.
  • CAVITY cavity between the last turbine stage and the turbine exhaust housing (TEC).
  • TEC turbine exhaust housing
  • a conventional low-pressure turbine is, for example, in Fig. 1 shown.
  • the cone of the rotor connection is acted upon on both sides with air at different temperatures.
  • the temperature of the blade cooling air prevails, and behind the shaft connection at the turbine outlet housing (TEC), the temperature of the bearing blockage air. This results in temperature differences with high thermal stresses in the rotor cone and the associated rotor disk.
  • TEC turbine outlet housing
  • the object of the invention is to propose a gas turbine with a rotor comprising a turbine rotor, a shaft and a compressor rotor and in the case of a multi-shaft gas turbine part of the low-pressure system, wherein a thermally balanced design in the region of the turbine rotor and its shaft connection high life is achieved.
  • the shaft in the region of the connection of the rotor cone on a widening with an enlarged inner and outer diameter, at the upstream end openings for the entry of cooling air into the enlarged interior of the shaft, and at the downstream end openings for the escape of cooling air in the space between storage chamber and rotor cone are present.
  • the extended interior of the shaft is sealed against the continuous interior of the shaft with a wall for separating cooling and sealing air. This ensures that the rotor cone and the associated running disk are subjected to cooling air at about the same temperature on both sides in the sense of a thermal compensation. A possibly exiting from the bearing chamber, the cooling air mixed small amount of blocking air at a lower temperature plays no significant role.
  • the turbine rotor 2 in FIG. 1 includes three bladed rotor disks 6, 7 and 8.
  • a rotor cone 10 leads to the associated shaft 12 and is flanged to this.
  • the shaft 12 is rotatably supported at its downstream end in a bearing 14.
  • the bearing 14 is arranged in a bearing chamber 16, which in turn is part of a turbine outlet housing 18.
  • the bearing chamber 16 is non-hermetically sealed by means of two axially spaced seals 41, 42.
  • cooling air 22 flows.
  • sealing air 20 is guided with a relation to the cooling air 22 significantly lower temperature.
  • the sealing air 20 is guided out of the shaft 12 between the seals 41, 42 and flows partly into the bearing chamber 16, partly into the space between the turbine rotor 2 and the turbine outlet housing 18.
  • upstream of the rotor cone 10 and downstream therefrom are different Air temperatures, which leads to thermal stresses and a shortened life of the rotor connection.
  • the solution according to the invention is characterized Fig. 2 by design changes, which lead to a changed air temperature distribution.
  • Fig. 2 From the turbine rotor 1, three running wheels 3, 4 and 5 can be seen. With the rearmost disk 5 a leading to the associated shaft 11 rotor cone 9 is integrally connected.
  • the rotor cone 9 is detachably connected to the shaft 11.
  • the connection 33 (see arrow) is accomplished in the case shown via a toothing 34, two press fits 35, 36, an axial stop 37 and a screw 38.
  • the shaft 11 has in the region of the connection 33 an expansion 27 with an enlarged inner and outer diameter.
  • In the space 23 upstream or outside of the rotor cone 9 and radially outside the shaft 11 is cooling air 21 with elevated temperature.
  • sealing air 19 flows at a lower temperature.
  • cooling air 21 can enter the shaft interior.
  • openings 29 at the downstream end of the widening 27 the same cooling air 21 can again emerge from the shaft interior and enter the space 24 downstream of the rotor cone 9.
  • a separating wall 31, here in the form of a socket is installed.
  • annular interior 26 is only with the spaces 23 and 24 in direct communication.
  • the flow of sealing air 19 is concentrated in the illustrated case by means of a central tube 32 on the outer circumference of the inner space 25, which is not absolutely necessary.
  • the sealing air 19 is known manner via openings 30 out of the shaft between two axially spaced seals 39, 40, here in the form of brush seals, passed. From there, a portion of the sealing air 19 enters the interior of the storage chamber 15 of the bearing 13. The other part of the sealing air 19 enters via the non-hermetic seal 39 in the space 24 and mixes there with cooling air 21. Since the from the openings 29 exiting cooling air flow is considerably greater than the exiting from the seal 39 blocking air flow, deviates the resulting mixing temperature in the space 24 only slightly from the starting temperature of the cooling air 21. This ensures that both sides of the rotor cone 9, the connection 33 and the running disk 5 is about the same temperature.

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

Abstract

A gas turbine having a rotor which includes a turbine rotor, a shaft and a compressor rotor, the turbine rotor having at least one rotor disk and a rotor cone leading from the or a rotor disk to the shaft, the downstream end of the shaft being rotatably supported in a bearing having a bearing chamber, the interior space of the shaft being designed as a flow channel for bearing-chamber sealing air, and the space surrounding the rotor cone upstream of the same being designed as a flow space for cooling air is disclosed. In the region of the rotor connection, the shaft exhibits an expanded portion, at whose upstream end, openings are provided to allow cooling air to enter, and, at whose downstream end, openings are provided to allow cooling air to exit into the space between the bearing chamber and the rotor cone, a wall separating the streams of the cooling air and of the sealing air in the shaft interior from one another.

Description

Die Erfindung betrifft eine Gasturbine mit einem Rotor, der einen Turbinenrotor, eine Welle und einen Verdichterrotor umfasst und im Falle einer mehrwelligen Gasturbine Teil des Niederdrucksystems ist, wobei der Turbinenrotor mindestens eine beschaufelte Laufscheibe und einen von der oder einer Laufscheibe zur Welle führenden Rotorkonus aufweist, und wobei das stromabwärtige Ende der Welle in einem Lager mit Lagerkammer drehbar abgestützt ist, gemäß dem Oberbegriff des Patentanspruchs 1. Eine solche Anordnung ist in der Patentschrift US 2 680 001 A beschrieben.The invention relates to a gas turbine having a rotor, which comprises a turbine rotor, a shaft and a compressor rotor and in the case of a multi-shaft gas turbine is part of the low-pressure system, wherein the turbine rotor has at least one bladed rotor disk and one from the or a rotor disk to the shaft leading rotor cone, and wherein the downstream end of the shaft is rotatably supported in a bearing with bearing chamber, according to the preamble of claim 1. Such an arrangement is in the patent US 2 680 001 A described.

Zukünftige Triebwerkskonzepte benötigen zur Erfüllung der geforderten Spezifikationen schnell laufende Niederdruckturbinen mit hohem AN2, hohen Turbineneintrittstemperaturen und kompakten, kurzen Bauweisen. Zur Vermeidung von Heißgaseinbruch aus dem Hauptstrom, und um den Lagerschub am Festlager des Niederdrucksystems einzustellen, ist es notwendig, den Hohlraum (CAVITY) zwischen der letzten Turbinenstufe und dem Turbinenaustrittsgehäuse (TEC) mit Luft zu beaufschlagen. Zur optimalen Gestaltung dieser Turbinenscheibe ist ein thermisch ausgeglichenes Design (Vermeidung von axialen Temperaturgradienten) erforderlich. Diese Luft wird bei ausgeführten Niederdruckturbinen üblicherweise am Niederdruckverdichter abgezapft und durch die Niederdruckturbinenwelle zur hinteren TEC-Lagerkammer geführt. Diese Luft wird als Sperrluft am Lager und zur Belüftung der hinteren CAVITY verwendet. Bedingt durch die limitierte Sperrlufttemperatur (Ölfeuer, Verkoken etc.) ist die Temperatur dieser Sperrluft deutlich kälter als die Kühlluft, mit welcher die gegenüberliegende Seite der Laufscheibe beaufschlagt wird. Dadurch entsteht ein axialer Temperaturgradient über der Scheibe, welcher eine gewichtsoptimierte Gestaltung der Laufscheibe der Rotoranbindung erschwert. Bedingt durch die für schnelllaufende Triebwerkskonzepte notwendigen, weit nach innen gezogenen Scheibenkörper und die kompakte Bauweise, ist nur ein sehr kurzer Rotorkonus zur Anbindung an der Welle möglich. Durch diese reduzierte Abklinglänge ist die mechanische Auslegung (LCF-Lebensdauer) schwierig. Im Besonderen ist ein starker Temperaturgradient über den Rotorkonus der Wellenanbindung und an der zugehörigen Scheibe nicht mehr akzeptabel.Future engine concepts require high-speed low-pressure turbines with high AN 2 , high turbine inlet temperatures and compact, short design to meet the required specifications. To avoid hot gas intrusion from the main flow and to adjust bearing thrust on the low pressure system's fixed bearing, it is necessary to pressurize the cavity (CAVITY) between the last turbine stage and the turbine exhaust housing (TEC). For optimum design of this turbine disk a thermally balanced design (avoidance of axial temperature gradients) is required. With low pressure turbines running, this air is usually tapped at the low pressure compressor and passed through the low pressure turbine shaft to the rear TEC storage chamber. This air is used as barrier air in the warehouse and for ventilation of the rear CAVITY. Due to the limited sealing air temperature (oil fire, coking, etc.), the temperature of this sealing air is significantly colder than the cooling air, with which the opposite side of the rotor disk is acted upon. This results in an axial temperature gradient across the disc, which complicates a weight-optimized design of the rotor disk rotor connection. Due to the disk bodies required for high-speed engine concepts, which are pulled far inwards, and the compact design, only a very short rotor cone for connection to the shaft is possible. This reduced decay length makes the mechanical design (LCF life) difficult. In particular, a strong temperature gradient across the rotor cone of the shaft connection and on the associated disk is no longer acceptable.

Die Luftführung bei einer konventionellen Niederdruckturbine ist beispielsweise in Fig. 1 dargestellt. Dabei wird der Konus der Rotoranbindung beidseitig mit Luft unterschiedlicher Temperatur beaufschlagt. Vor der Wellenanbindung herrscht die Temperatur der Laufschaufelkühlluft, hinter der Wellenanbindung am Turbinenaustrittsgehäuse (TEC) die Temperatur der Lagersperrluft. Daraus ergeben sich Temperaturunterschiede mit hohen Thermospannungen im Rotorkonus und der zugehörigen Laufscheibe.The air flow in a conventional low-pressure turbine is, for example, in Fig. 1 shown. In this case, the cone of the rotor connection is acted upon on both sides with air at different temperatures. Before the shaft connection, the temperature of the blade cooling air prevails, and behind the shaft connection at the turbine outlet housing (TEC), the temperature of the bearing blockage air. This results in temperature differences with high thermal stresses in the rotor cone and the associated rotor disk.

Demgegenüber besteht die Aufgabe der Erfindung darin, eine Gasturbine mit einem Rotor vorzuschlagen, der einen Turbinenrotor, eine Welle und einen Verdichterrotor umfasst und im Falle einer mehrwelligen Gasturbinen Teil des Niederdrucksystems ist, wobei durch ein thermisch ausgeglichenes Design im Bereich des Turbinenrotors und seiner Wellenanbindung eine hohe Lebensdauer erzielt wird.In contrast, the object of the invention is to propose a gas turbine with a rotor comprising a turbine rotor, a shaft and a compressor rotor and in the case of a multi-shaft gas turbine part of the low-pressure system, wherein a thermally balanced design in the region of the turbine rotor and its shaft connection high life is achieved.

Diese Aufgabe wird durch die im Patentanspruch 1 gekennzeichneten Merkmale gelöst, in Verbindung mit den gattungsbildenden Merkmalen dessen Oberbegriff. Dabei weist die Welle im Bereich der Anbindung des Rotorkonus eine Aufweitung mit einem vergrößerten Innen- und Außendurchmesser auf, an deren stromaufwärtigem Ende Öffnungen für den Eintritt von Kühlluft in den erweiterten Innenraum der Welle, und an deren stromabwärtigem Ende Öffnungen für den Austritt von Kühlluft in den Raum zwischen Lagerkammer und Rotorkonus vorhanden sind. Der erweiterte Innenraum der Welle ist gegenüber den durchgehenden Innenraum der Welle mit einer Wand zur Trennung von Kühl- und Sperrluft abgedichtet. Dadurch wird erreicht, dass der Rotorkonus und die zugehörige Laufscheibe im Sinne eines thermischen Ausgleichs beidseitig mit Kühlluft etwa gleicher Temperatur beaufschlagt werden. Eine ggf. aus der Lagerkammer austretende, der Kühlluft zugemischte kleine Sperrluftmenge mit geringerer Temperatur spielt dabei keine maßgebliche Rolle.This object is achieved by the features characterized in claim 1 features, in conjunction with the generic features of the preamble. In this case, the shaft in the region of the connection of the rotor cone on a widening with an enlarged inner and outer diameter, at the upstream end openings for the entry of cooling air into the enlarged interior of the shaft, and at the downstream end openings for the escape of cooling air in the space between storage chamber and rotor cone are present. The extended interior of the shaft is sealed against the continuous interior of the shaft with a wall for separating cooling and sealing air. This ensures that the rotor cone and the associated running disk are subjected to cooling air at about the same temperature on both sides in the sense of a thermal compensation. A possibly exiting from the bearing chamber, the cooling air mixed small amount of blocking air at a lower temperature plays no significant role.

Bevorzugte Ausgestaltungen der Erfindung sind in den Unteransprüchen gekennzeichnet.Preferred embodiments of the invention are characterized in the subclaims.

Der gattungsbildende Stand der Technik und die Erfindung wird anschließend anhand der Figuren noch näher erläutert. Dabei zeigen in vereinfachter, nicht maßstäblicher Darstellung:

Fig. 1
einen Teillängsschnitt durch einen Turbinenrotor mit Wellenanbindung und Lage- rung mit konventioneller Luftführung,
Fig. 2
einen Teillängsschnitt durch einen Turbinenrotor mit Wellenanbindung, Lagerung und Luftführung gemäß vorliegender Erfindung.
The generic state of the art and the invention will be explained in more detail with reference to FIGS. In a simplified, not to scale representation:
Fig. 1
a partial longitudinal section through a turbine rotor with shaft connection and storage with conventional air duct,
Fig. 2
a partial longitudinal section through a turbine rotor with shaft connection, storage and air duct according to the present invention.

Der Turbinenrotor 2 in Figur 1 umfasst drei beschaufelte Laufscheiben 6, 7 und 8.The turbine rotor 2 in FIG. 1 includes three bladed rotor disks 6, 7 and 8.

Von der mittleren Laufscheibe 7 führt ein Rotorkonus 10 zu der zugehörigen Welle 12 und ist an dieser angeflanscht. Die Welle 12 ist an ihrem stromabwärtigen Ende in einem Lager 14 drehbar abgestützt. Das Lager 14 ist in einer Lagerkammer 16 angeordnet, die wiederum Teil eines Turbinenaustrittsgehäuses 18 ist. Am Welleneintritt ist die Lagerkammer 16 mittels zweier axial beabstandeter Dichtungen 41, 42 nicht-hermetisch abgedichtet. In dem Raum radial außerhalb der Welle 12 und stromaufwärts des Rotorkonus 10 strömt Kühlluft 22. Durch die Verwendung zur Schaufelkühlung im Hochtemperatur- und Hochdruckbereich weist diese eine erhöhte, aber immer noch zu Kühlzwecken geeignete Temperatur auf. Durch das Innere der Welle 12 wird Sperrluft 20 mit einer gegenüber der Kühlluft 22 deutlich niedrigeren Temperatur geführt. Die Sperrluft 20 wird aus der Welle 12 heraus zwischen die Dichtungen 41, 42 geführt und strömt zum Teil in die Lagerkammer 16, zum Teil in den Raum zwischen dem Turbinenrotor 2 und dem Turbinenaustrittsgehäuse 18. Somit liegen stromaufwärts des Rotorkonus 10 und stromabwärts von diesem unterschiedliche Lufttemperaturen vor, was zu Thermospannungen und einer verkürzten Lebensdauer der Rotoranbindung führt.From the central disk 7, a rotor cone 10 leads to the associated shaft 12 and is flanged to this. The shaft 12 is rotatably supported at its downstream end in a bearing 14. The bearing 14 is arranged in a bearing chamber 16, which in turn is part of a turbine outlet housing 18. At the shaft entrance, the bearing chamber 16 is non-hermetically sealed by means of two axially spaced seals 41, 42. In the space radially outward of the shaft 12 and upstream of the rotor cone 10, cooling air 22 flows. By use for blade cooling in the high temperature and high pressure regions, it has an elevated but still suitable temperature for cooling. Through the interior of the shaft 12 sealing air 20 is guided with a relation to the cooling air 22 significantly lower temperature. The sealing air 20 is guided out of the shaft 12 between the seals 41, 42 and flows partly into the bearing chamber 16, partly into the space between the turbine rotor 2 and the turbine outlet housing 18. Thus, upstream of the rotor cone 10 and downstream therefrom are different Air temperatures, which leads to thermal stresses and a shortened life of the rotor connection.

Demgegenüber zeichnet sich die erfindungsgemäße Lösung nach Fig. 2 durch konstruktive Änderungen aus, welche zu einer geänderten Lufttemperaturverteilung führen. Von dem Turbinenrotor 1 sind drei Laufscheiben 3, 4 und 5 erkennbar. Mit der hintersten Laufscheibe 5 ist ein zur zugehörigen Welle 11 führender Rotorkonus 9 integral verbunden. Der Rotorkonus 9 ist mit der Welle 11 lösbar verbunden. Die Anbindung 33 (siehe Pfeil) wird im dargestellten Fall über eine Verzahnung 34, zwei Presssitze 35, 36, einen axialen Anschlag 37 sowie eine Verschraubung 38 bewerkstelligt. Die Welle 11 weist im Bereich der Anbindung 33 eine Aufweitung 27 mit vergrößertem Innen- und Außendurchmesser auf. In dem Raum 23 stromaufwärts bzw. außerhalb des Rotorkonus 9 und radial außerhalb der Welle 11 befindet sich Kühlluft 21 mit erhöhter Temperatur. Im Innenraum 25 der Welle 11 strömt demgegenüber Sperrluft 19 mit niedrigerer Temperatur. Durch Öffnungen 28 am stromaufwärtigen Ende der Aufweitung 27 kann Kühlluft 21 in das Welleninnere eintreten. Durch Öffnungen 29 am stromabwärtigen Ende der Aufweitung 27 kann die selbe Kühlluft 21 wieder aus dem Welleninneren austreten und in den Raum 24 stromabwärts des Rotorkonus 9 eintreten. Damit sich die Sperrluft 19 und die Kühlluft 21 im Welleninneren nicht vermischen, ist eine trennende Wand 31, hier in Form einer Buchse, installiert. Somit steht der zwischen der Wand 31 und der Aufweitung 27 befindliche, ringförmige Innenraum 26 nur mit den Räumen 23 und 24 in direkter Verbindung. Der Strom der Sperrluft 19 wird im dargestellten Fall mittels eines zentrischen Rohres 32 am Außenumfang des Innenraumes 25 konzentriert, was nicht zwingend erforderlich ist. Die Sperrluft 19 wird bekannter Weise über Öffnungen 30 aus der Welle heraus zwischen zwei axial beabstandete Dichtungen 39, 40, hier in Form von Bürstendichtungen, geleitet. Von dort gelangt ein Teil der Sperrluft 19 in das Innere der Lagerkammer 15 des Lagers 13. Der andere Teil der Sperrluft 19 tritt über die nicht-hermetische Dichtung 39 in den Raum 24 ein und mischt sich dort mit Kühlluft 21. Da der aus den Öffnungen 29 austretende Kühlluftstrom erheblich größer als der aus der Dichtung 39 austretende Sperrluftstrom ist, weicht die sich ergebende Mischtemperatur im Raum 24 nur unwesentlich von der Ausgangstemperatur der Kühlluft 21 ab. Dadurch wird erreicht, dass beiderseits des Rotorkonus 9, der Anbindung 33 sowie der Laufscheibe 5 etwa die gleiche Temperatur herrscht. Somit werden Thermospannungen in der erfindungsgemäßen Rotoranbindung auf ein Minimum reduziert, die Lebensdauer wird gegenüber den bekannten Lösungen erheblich erhöht. Der mechanisch höchst kritische Rotorkonus 9 kann ohne Durchbrüche, Bohrungen etc. ausgeführt werden. Die Öffnungen 28 und 29 im Bereich der stabilen Aufweitung 27 der Welle 11 sind demgegenüber unkritisch. Abschließend sei noch erwähnt, dass das Turbinenaustrittsgehäuse 17 in Fig. 2 nur minimal angedeutet ist.In contrast, the solution according to the invention is characterized Fig. 2 by design changes, which lead to a changed air temperature distribution. From the turbine rotor 1, three running wheels 3, 4 and 5 can be seen. With the rearmost disk 5 a leading to the associated shaft 11 rotor cone 9 is integrally connected. The rotor cone 9 is detachably connected to the shaft 11. The connection 33 (see arrow) is accomplished in the case shown via a toothing 34, two press fits 35, 36, an axial stop 37 and a screw 38. The shaft 11 has in the region of the connection 33 an expansion 27 with an enlarged inner and outer diameter. In the space 23 upstream or outside of the rotor cone 9 and radially outside the shaft 11 is cooling air 21 with elevated temperature. In the interior 25 of the shaft 11, in contrast, sealing air 19 flows at a lower temperature. Through openings 28 at the upstream end of the widening 27, cooling air 21 can enter the shaft interior. Through openings 29 at the downstream end of the widening 27, the same cooling air 21 can again emerge from the shaft interior and enter the space 24 downstream of the rotor cone 9. So that the sealing air 19 and the cooling air 21 do not mix in the shaft interior, a separating wall 31, here in the form of a socket, is installed. Thus, located between the wall 31 and the expansion 27, annular interior 26 is only with the spaces 23 and 24 in direct communication. The flow of sealing air 19 is concentrated in the illustrated case by means of a central tube 32 on the outer circumference of the inner space 25, which is not absolutely necessary. The sealing air 19 is known manner via openings 30 out of the shaft between two axially spaced seals 39, 40, here in the form of brush seals, passed. From there, a portion of the sealing air 19 enters the interior of the storage chamber 15 of the bearing 13. The other part of the sealing air 19 enters via the non-hermetic seal 39 in the space 24 and mixes there with cooling air 21. Since the from the openings 29 exiting cooling air flow is considerably greater than the exiting from the seal 39 blocking air flow, deviates the resulting mixing temperature in the space 24 only slightly from the starting temperature of the cooling air 21. This ensures that both sides of the rotor cone 9, the connection 33 and the running disk 5 is about the same temperature. Thus, thermal stresses in the rotor connection according to the invention are reduced to a minimum, the life is significantly increased compared to the known solutions. The mechanically most critical rotor cone 9 can be performed without openings, holes, etc. The openings 28 and 29 in the region of the stable expansion 27 of the shaft 11 are uncritical in contrast. Finally, it should be mentioned that the turbine outlet housing 17 in Fig. 2 only minimally indicated.

Claims (5)

  1. A gas turbine having a rotor which comprises a turbine rotor (1), a shaft (11) and a compressor rotor and, in the case of a multi-shaft gas turbine, is part of the low-pressure system, wherein the turbine rotor (1) has at least one bladed rotor disc (3, 4, 5) and a rotor cone (9) leading from the or one rotor disc (5) to the shaft (11), wherein the downstream end of the shaft (11) is rotatably stayed in a bearing (13) with a bearing chamber (15), wherein the interior space (25) of the shaft (11) is realized as a flow channel for sealing air (19) leading to the bearing chamber (15), and wherein the space (23) surrounding the rotor cone (9) upstream is realized as a flow space for cooling air (21) that is used for rotor-blade cooling, characterised in that the shaft (11) has in the region of the tying (33) of the rotor cone (9) a widened portion (27) with an enlarged inside and outside diameter, provided at whose upstream end there are openings (28) for the entry of cooling air (21) into the widened interior space (26) of the bearing chamber (15) and at whose downstream end there are openings (29) for the exit of cooling air (21) into the space (24) between the bearing chamber (15) and the rotor cone (9), and in that the widened interior space (26) is sealed with respect to the through-going interior space (25) of the shaft (11) by a wall (31) for the separation of the cooling air (21) and the sealing air (19).
  2. A gas turbine according to claim 1, characterised in that the bearing chamber (15) is part of a turbine exit housing (17) that is arranged downstream of the turbine rotor (1).
  3. A gas turbine according to claim 1 or 2, characterised in that a tube (32) for the formation of an annular flow channel for the sealing air (19) is arranged in the interior space (25) of the shaft (11) coaxially with radial spacing.
  4. A gas turbine according to one of claims 1 to 3, characterised in that the flow channel for the sealing air (19) leads through openings (30) in the shaft (11) radially outwards between two axially spaced, non-hermetic seals (39, 40), for example in the form of brush seals, of the bearing chamber (15).
  5. A gas turbine according to one of claims 1 to 4, characterised in that the rotor cone (9) is secured on the widened portion (27) of the shaft (11) by way of a tooth construction (34) that is form-closing in the circumferential direction, by way of press fits (35, 36) arranged axially on both sides of the tooth construction (34), by way of an axial stop (37) and also by way of an axially acting screw connection (38).
EP08758019A 2007-05-18 2008-05-02 Gas turbine Not-in-force EP2148977B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102007023380A DE102007023380A1 (en) 2007-05-18 2007-05-18 gas turbine
PCT/DE2008/000758 WO2008141609A2 (en) 2007-05-18 2008-05-02 Gas turbine

Publications (2)

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EP2148977A2 EP2148977A2 (en) 2010-02-03
EP2148977B1 true EP2148977B1 (en) 2010-08-18

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EP08758019A Not-in-force EP2148977B1 (en) 2007-05-18 2008-05-02 Gas turbine

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US (1) US8388303B2 (en)
EP (1) EP2148977B1 (en)
JP (1) JP5197736B2 (en)
AT (1) ATE478236T1 (en)
DE (2) DE102007023380A1 (en)
ES (1) ES2347303T3 (en)
WO (1) WO2008141609A2 (en)

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US9638056B2 (en) * 2013-03-12 2017-05-02 Rolls-Royce North American Technologies, Inc. Gas turbine engine and active balancing system
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US9371737B2 (en) 2012-02-23 2016-06-21 Mitsubishi Hitachi Power Systems, Ltd. Gas turbine
CN104066954B (en) * 2012-02-23 2016-11-09 三菱日立电力***株式会社 Gas turbine

Also Published As

Publication number Publication date
ES2347303T3 (en) 2010-10-27
JP5197736B2 (en) 2013-05-15
WO2008141609A3 (en) 2009-06-11
EP2148977A2 (en) 2010-02-03
US8388303B2 (en) 2013-03-05
DE102007023380A1 (en) 2008-11-20
WO2008141609A2 (en) 2008-11-27
JP2010527421A (en) 2010-08-12
DE502008001171D1 (en) 2010-09-30
ATE478236T1 (en) 2010-09-15
US20100104418A1 (en) 2010-04-29

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