EP2044293B1 - Gas turbine with a peripheral ring segment comprising a recirculation channel - Google Patents

Gas turbine with a peripheral ring segment comprising a recirculation channel Download PDF

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Publication number
EP2044293B1
EP2044293B1 EP07785646.6A EP07785646A EP2044293B1 EP 2044293 B1 EP2044293 B1 EP 2044293B1 EP 07785646 A EP07785646 A EP 07785646A EP 2044293 B1 EP2044293 B1 EP 2044293B1
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EP
European Patent Office
Prior art keywords
gap
channel
gas turbine
housing
blades
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.)
Expired - Fee Related
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EP07785646.6A
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German (de)
French (fr)
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EP2044293A1 (en
Inventor
Peter Seitz
Roland Huttner
Karl-Heinz Dusel
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MTU Aero Engines AG
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MTU Aero Engines AG
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/10—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using sealing fluid, e.g. steam
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/684—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid injection
    • 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
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/612—Foam

Definitions

  • the invention relates to a gas turbine, in particular a gas turbine aircraft engine, according to the preamble of claim 1.
  • Gas turbines particularly gas turbine aircraft engines, typically include a plurality of rotating blades in the region of a compressor and a turbine and a plurality of fixed vanes, the blades rotating together with a rotor, and the blades and vanes surrounded by a fixed housing.
  • a plurality of rotating blades in the region of a compressor and a turbine and a plurality of fixed vanes, the blades rotating together with a rotor, and the blades and vanes surrounded by a fixed housing.
  • sealing systems include the so-called sealing systems.
  • blades have no shroud, especially in the compressor. Therefore, the radially outer ends of the blades are exposed to so-called rubbing into the fixed housing direct frictional contact with the housing. Such a rubbing of the tips of the blades into the housing is caused by setting a minimum radial gap by manufacturing tolerances. As is removed by the frictional contact of the tips of the blades on the same material, over the entire circumference of the housing and rotor can set an undesirable gap magnification. To avoid this, it is already known from the prior art to armor the ends of the blades with a hard coating or with abrasive particles.
  • housings with inlet lining are known from the prior art, wherein the inlet lining is typically associated with housing-side shroud segments, which serve as a carrier for the inlet lining, Such shroud segments are also referred to as shrouds.
  • a seal assembly which has an inlet lining and a channel.
  • the inlet lining is provided at the height of the gap between the blade and the housing.
  • the channel has an inlet opening at the level of the gap and an outlet opening at the level of the gap.
  • EP 0 992 656 A1 shows a rotor with blades and a surrounding the rotor housing a turbomachine.
  • the blades have blade ends whose surfaces are approximately parallel to an inner wall of the housing.
  • a channel is provided, which opens in front of and behind the blade ends when viewed in the flow direction.
  • the inlet and outlet openings of the channel correspond to the intermediate gaps between the stator and rotor stages.
  • US2005 / 0226717A1 shows a blade which is partially spaced from a housing inner wall in the radial direction.
  • a channel is provided, which, viewed in the flow direction, opens in front of and behind the blade.
  • a negative pressure gradient which causes a backflow through the channel.
  • the present invention is based on the problem of creating a novel gas turbine with reduced aerodynamic gap losses.
  • This problem is solved by a gas turbine according to claim 1.
  • the gas turbine has at least one channel in order to apply a pressure prevailing on the high pressure side of blades of a rotor at a low pressure side thereof in the region of the gap between the radially outer ends of the blades and the housing and thus to prevent flow through the gap.
  • the channel extends at least in sections in serving as a support for the inlet lining, housing-side shroud segment, such that the channel opens on the high pressure side in the region of the shroud segment outside the gap in a flow channel and on the low pressure side in the region of the inlet lining in the gap to be sealed.
  • Fig. 1 shows a highly schematic section of a gas turbine 10 according to the invention in the region of a high-pressure compressor 11, wherein the high-pressure compressor 11 has a rotating rotor, of which in Fig. 1 a blade 12 is shown.
  • the blades 12 of the rotor of the high-pressure compressor 11 are surrounded by a fixed housing 13, wherein the housing 13 are associated with shroud segments 14 which serve, inter alia, as a carrier for an inlet lining 15.
  • Fig. 1 run during operation of the gas turbine radially outer ends 16 of the blades 12 in the inlet lining 15, so that a gap 17 is formed between the inlet lining 15 and the radially outer ends 16 of the blades.
  • a leakage flow from the high pressure side of the blades 12 to the low pressure side of the same form, wherein in the illustration of Fig. 1 the right side of the blades 12 is the high pressure side in which the pressure P H prevails, and the low pressure side is the left side of the blades on which the pressure P L prevails.
  • the gas turbine 10 has at least one channel 18 to the prevailing on the high pressure side of the blades 12 pressure on the low pressure side thereof in the region of the gap to be sealed 17th to apply.
  • the inlet lining 15 is a gas-permeable inlet lining, which preferably has an open-pored structure.
  • the inlet lining 15 is designed as an open-pored metal foam.
  • the in Fig. 1 channel 18 shown extends at least in sections, in which serves as a carrier for the running-in surface 15, housing-side shroud segment 14, the channel 18 on the high pressure side, where the pressure P H prevails in the area of shroud segment 14 in a flow passage of the high pressure compressor 11 of the gas turbine 10 empties.
  • the channel 16 opens in the region of the inlet lining 15 into the gap 17 to be sealed.
  • a cross-section of the or each channel 18 is preferably dimensioned such that an optionally flowing through the respective channel air in the region of the gap 17 to be sealed acts as sealing air.
  • guide elements z. As baffles or guide grille, be integrated to aerodynamically optimally guide the flowing through the channel 18 sealing air.
  • the invention is not limited to use on high pressure compressors.
  • the invention can also be used on other compressors and on turbines.

Description

Die Erfindung betrifft eine Gasturbine, insbesondere ein Gasturbinenflugtriebwerk, gemäß dem Oberbegriff des Anspruchs 1.The invention relates to a gas turbine, in particular a gas turbine aircraft engine, according to the preamble of claim 1.

Gasturbinen, insbesondere Gasturbinenflugtriebwerke, weisen in der Regel im Bereich eines Verdichters und einer Turbine mehrere rotierende Laufschaufeln sowie mehrere feststehende Leitschaufeln auf, wobei die Laufschaufeln zusammen mit einem Rotor rotieren, und wobei die Laufschaufeln sowie die Leitschaufeln von einem feststehenden Gehäuse umgeben sind. Zur Leistungssteigerung ist es von Bedeutung, alle Komponenten und Subsysteme zu optimieren. Hierzu zählen auch die sogenannten Dichtsysteme.Gas turbines, particularly gas turbine aircraft engines, typically include a plurality of rotating blades in the region of a compressor and a turbine and a plurality of fixed vanes, the blades rotating together with a rotor, and the blades and vanes surrounded by a fixed housing. To increase performance, it is important to optimize all components and subsystems. These include the so-called sealing systems.

Besonders problematisch ist die Einhaltung eines minimalen Spalts zwischen den rotierenden Laufschaufeln und dem feststehenden Gehäuse eines Hochdruckverdichters einer Gasturbine. Bei Hochdruckverdichtern treten nämlich hohe absolute Temperaturen sowie Temperaturengradienten auf, was die Spalthaltung der rotierenden Laufschaufeln zum feststehenden Gehäuse erschwert. Dies liegt unter anderem auch darin begründet, dass bei Verdichterlaufschaufeln auf Deckbänder, wie sie üblicherweise bei Turbinenlaufschaufeln verwendet werden, verzichtet wird. Es sind auch Turbinenlaufschaufeln ohne Deckbänder bekannt.Particularly problematic is the maintenance of a minimum gap between the rotating blades and the stationary housing of a high-pressure compressor of a gas turbine. Namely high absolute temperatures and temperature gradients occur in high-pressure compressors, which makes it more difficult for the rotating blades to cling to the stationary housing. This is partly due to the fact that in compressor blades on shrouds, as they are commonly used in turbine blades, is dispensed with. There are also known turbine blades without shrouds.

Wie bereits erwähnt, verfügen Laufschaufeln insbesondere im Verdichter über kein Deckband. Daher sind die radial außen liegenden Enden der Laufschaufeln beim sogenannten Anstreifen in das feststehende Gehäuse einem direkten Reibkontakt mit dem Gehäuse ausgesetzt. Ein solches Anstreifen der Spitzen der Laufschaufeln in das Gehäuse wird bei Einstellung eines minimalen Radialspalts durch Fertigungstoleranzen hervorgerufen. Da durch den Reibkontakt der Spitzen der Laufschaufeln an denselben Material abgetragen wird, kann sich über den gesamten Umfang von Gehäuse und Rotor eine unerwünschte Spaltvergrößerung einstellen. Um dies zu vermeiden ist es aus dem Stand der Technik bereits bekannt, die Enden der Laufschaufeln mit einem harten Belag oder mit abrasiven Partikeln zu panzern.As already mentioned, blades have no shroud, especially in the compressor. Therefore, the radially outer ends of the blades are exposed to so-called rubbing into the fixed housing direct frictional contact with the housing. Such a rubbing of the tips of the blades into the housing is caused by setting a minimum radial gap by manufacturing tolerances. As is removed by the frictional contact of the tips of the blades on the same material, over the entire circumference of the housing and rotor can set an undesirable gap magnification. To avoid this, it is already known from the prior art to armor the ends of the blades with a hard coating or with abrasive particles.

Eine andere Möglichkeit, den Verschleiß an den Spitzen bzw, radial außen liegenden Enden der Laufschaufeln zu vermeiden und für eine optimierte Abdichtung zwischen den Enden bzw. Spitzen der Laufschaufeln und dem feststehenden Gehäuse zu sorgen, besteht in der Beschichtung des Gehäuses mit einem sogenannten Einlaufbelag.Another way to avoid the wear on the tips or, radially outer ends of the blades and to ensure an optimized seal between the tips and tips of the blades and the fixed housing, consists in the coating of the housing with a so-called inlet lining.

Bei einem Materialabtrag an einem Einlaufbelag wird der Radialspalt nicht über den gesamten Umfang vergrößert, sondern in der Regel nur sichelförmig. Gehäuse mit Einlaufbelag sind aus dem Stand der Technik bekannt, wobei der Einlaufbelag typischerweise gehäuseseitigen Mantelringsegmenten zugeordnet ist, die als Träger für den Einlaufbelag dienen, Solche Mantelringsegmente werden auch als Shrouds bezeichnet.In a material removal at an inlet lining of the radial gap is not increased over the entire circumference, but usually only sickle-shaped. Housings with inlet lining are known from the prior art, wherein the inlet lining is typically associated with housing-side shroud segments, which serve as a carrier for the inlet lining, Such shroud segments are also referred to as shrouds.

Wie oben ausgeführt, vergrößert sich auch bei Verwendung eines Einlaufbelags der Spalt zwischen den Spitzen bzw. radial außen liegenden Enden der Laufschaufeln und dem Gehäuse, so dass nach dem Stand der Technik eine aerodynamische Strömung durch diesen Spalt von einer Hochdruckseite der Laufschaufeln zu einer Niederdruckseite derselben nicht gänzlich unterbunden werden kann. Es stellen sich demnach aerodynamische Spaltverluste ein. Dies reduziert den Wirkungsgrad von Gasturbinen.As stated above, even with the use of an inlet lining, the gap between the tips or radially outer ends of the moving blades and the housing increases, so that in the prior art an aerodynamic flow through this gap from a high pressure side of the blades to a low pressure side thereof can not be completely prevented. Accordingly, aerodynamic gap losses occur. This reduces the efficiency of gas turbines.

In der Druckschrift US 5,474,417 ist ein Dichtungssystem für Gasturbinen vorgestellt, das einen Einlaufbelag und einen Kanal aufweist. Der Einlaufbelag befindet sich auf der Höhe des Spalts zwischen dem Gehäuse und der Laufschaufel. Der Kanal weist eine Eintrittsöffnung auf Höhe des Spaltes und eine Austrittsöffnung außerhalb des Spaltes auf.In the publication US 5,474,417 a sealing system for gas turbines is presented, which has an inlet lining and a channel. The inlet lining is at the height of the gap between the housing and the blade. The channel has an inlet opening at the level of the gap and an outlet opening outside the gap.

Die in der Druckschrift EP 0 497 574 A1 ist eine Dichtungsanordnung offenbart, die einen Einlaufbelag und einen Kanal aufweist. Der Einlaufbelag ist auf der Höhe des Spaltes zwischen der Laufschaufel und dem Gehäuse vorgesehen. Der Kanal weist eine Eintrittsöffnung auf der Höhe des Spaltes und eine Austrittsöffnung auf der Höhe des Spaltes auf.The in the publication EP 0 497 574 A1 a seal assembly is disclosed which has an inlet lining and a channel. The inlet lining is provided at the height of the gap between the blade and the housing. The channel has an inlet opening at the level of the gap and an outlet opening at the level of the gap.

EP 0 992 656 A1 zeigt einen Rotor mit Laufschaufeln und ein den Rotor umgebendes Gehäuse einer Strömungsmaschine. Die Laufschaufeln weisen Laufschaufelenden auf, deren Flächen in etwa parallel zu einer Innenwand des Gehäuses verlaufen. In dem Gehäuse ist ein Kanal vorgesehen, der in Strömungsrichtung betrachtet vor und hinter den Laufschaufelenden mündet. Entlang der Laufschaufel liegt ein positiver Druckgradient vor, der eine parallele zur Hauptströmung gerichtete Strömung in dem Kanal bewirkt. Die Ein- und Austrittsöffnungen des Kanals entsprechen den Zwischenspalten zwischen Stator- und Rotorstufen. Durch die spezielle Ausgestaltung des Kanals wird in dem Kanal eine Strömung von der Niederdruckseite zu der Hochdruckseite erzeugt, so dass die dort herrschenden dynamischen Druckverhältnisse in etwa den an den Ein- und Austrittsöffnungen statischen Druckverhältnissen aus der Hauptströmung entsprechen, wodurch Leckageströme reduziert werden. EP 0 992 656 A1 shows a rotor with blades and a surrounding the rotor housing a turbomachine. The blades have blade ends whose surfaces are approximately parallel to an inner wall of the housing. In the housing, a channel is provided, which opens in front of and behind the blade ends when viewed in the flow direction. Along the blade there is a positive pressure gradient which causes a parallel flow to the main flow in the channel. The inlet and outlet openings of the channel correspond to the intermediate gaps between the stator and rotor stages. Due to the special design of the channel, a flow from the low-pressure side to the high-pressure side is generated in the channel, so that the prevailing dynamic pressure conditions correspond approximately to the static pressure conditions at the inlet and outlet openings from the main flow, whereby leakage flows are reduced.

US2005/0226717A1 zeigt eine Laufschaufel, die von einer Gehäuseinnenwand in radialer Richtung teilweise beabstandet angeordnet ist. In der Gehäuseinnenwand ist ein Kanal vorgesehen, der in Strömungsrichtung betrachtet vor und hinter der Laufschaufel mündet. Entlang der Laufschaufel liegt ein negativer Druckgradient vor, der eine Rückströmung durch den Kanal bedingt. US2005 / 0226717A1 shows a blade which is partially spaced from a housing inner wall in the radial direction. In the housing inner wall, a channel is provided, which, viewed in the flow direction, opens in front of and behind the blade. Along the blade there is a negative pressure gradient, which causes a backflow through the channel.

Hiervon ausgehend liegt der vorliegenden Erfindung das Problem zu Grunde, eine neuartige Gasturbine mit verringerten aerodynamischen Spaltverlusten zu schaffen. Dieses Problem wird durch eine Gasturbine gemäß Anspruch 1 gelöst. Erfindungsgemäß weist die Gasturbine mindestens einen Kanal auf, um einen auf der Hochdruckseite von Laufschaufeln eines Rotors herrschenden Druck an einer Niederdruckseite derselben im Bereich des Spalts zwischen den radial außenliegenden Enden der Laufschaufeln und dem Gehäuse anzulegen und so eine Strömung durch den Spalt zu unterbinden. Dabei verläuft der Kanal zumindest abschnittweise in einem als Träger für den Einlaufbelag dienenden, gehäuseseitigen Mantelringsegment, derart, dass der Kanal auf der Hochdruckseite im Bereich des Mantelringsegments außerhalb des Spalts in einen Strömungskanal und auf der Niederdruckseite im Bereich des Einlaufbelags in den abzudichtenden Spalt mündet.On this basis, the present invention is based on the problem of creating a novel gas turbine with reduced aerodynamic gap losses. This problem is solved by a gas turbine according to claim 1. According to the invention, the gas turbine has at least one channel in order to apply a pressure prevailing on the high pressure side of blades of a rotor at a low pressure side thereof in the region of the gap between the radially outer ends of the blades and the housing and thus to prevent flow through the gap. In this case, the channel extends at least in sections in serving as a support for the inlet lining, housing-side shroud segment, such that the channel opens on the high pressure side in the region of the shroud segment outside the gap in a flow channel and on the low pressure side in the region of the inlet lining in the gap to be sealed.

Mit der hier vorliegenden Erfindung können aerodynamische Spaltverluste im Bereich des Spalts zwischen den radial außen liegenden Enden der rotierenden Laufschaufeln und dem Gehäuse, der sich im Betrieb beim Einlaufen der Laufschaufeln in einen Einlaufbelag ausbildet, minimiert werden. Hierdurch wird der Wirkungsgrad von Gasturbinen optimiert.With the present invention, aerodynamic gap losses in the region of the gap between the radially outer ends of the rotating blades and the housing, which forms during operation of the rotor blades in an inlet lining, can be minimized. This optimizes the efficiency of gas turbines.

Bevorzugte Weiterbildungen der Erfindung ergeben sich aus den Unteransprüchen und der nachfolgenden Beschreibung. Ausführungsbeispiele der Erfindung werden, ohne hierauf beschränkt zu sein, an Hand der Zeichnung näher erläutert. Dabei zeigt:

Fig. 1
einen stark schematisierten Ausschnitt aus einer erfindimgemäßen Gasturbine.
Preferred embodiments of the invention will become apparent from the dependent claims and the description below. Embodiments of the invention will be described, without being limited thereto, with reference to the drawings. Showing:
Fig. 1
a highly schematic section of a erfindimgemäßen gas turbine.

Nachfolgend wird die Erfindung unter Bezugnahme auf Fig. 1 in größerem Detail beschrieben.Hereinafter, the invention with reference to Fig. 1 described in more detail.

Fig. 1 zeigt einen stark schematisierten Ausschnitt aus einer erfindungsgemäßen Gasturbine 10 im Bereich eines Hochdruckverdichters 11, wobei der Hochdruckverdichter 11 einen rotierenden Rotor aufweist, von welchem in Fig. 1 eine Laufschaufel 12 gezeigt ist. Die Laufschaufeln 12 des Rotors des Hochdruckverdichters 11 sind von einem feststehenden Gehäuse 13 umgeben, wobei dem Gehäuse 13 Mantelringsegmente 14 zugeordnet sind, die unter anderem als Träger für einen Einlaufbelag 15 dienen. Fig. 1 shows a highly schematic section of a gas turbine 10 according to the invention in the region of a high-pressure compressor 11, wherein the high-pressure compressor 11 has a rotating rotor, of which in Fig. 1 a blade 12 is shown. The blades 12 of the rotor of the high-pressure compressor 11 are surrounded by a fixed housing 13, wherein the housing 13 are associated with shroud segments 14 which serve, inter alia, as a carrier for an inlet lining 15.

Gemäß Fig. 1 laufen im Betrieb der Gasturbine radial außen liegende Enden 16 der Laufschaufeln 12 in den Einlaufbelag 15 ein, so dass sich zwischen dem Einlaufbelag 15 und den radial außen liegenden Enden 16 der Laufschaufeln ein Spalt 17 ausbildet. Durch diesen Spalt 17 kann sich im Betrieb der Gasturbine eine Leckageströmung von der Hochdruckseite der Laufschaufeln 12 zur Niederdruckseite derselben ausbilden, wobei in der Darstellung der Fig. 1 die rechte Seite der Laufschaufeln 12 die Hochdruckseite ist, in welcher der Druck PH herrscht, und wobei die Niederdruckseite die linke Seite der Laufschaufeln ist, an welcher der Druck PL herrscht.According to Fig. 1 run during operation of the gas turbine radially outer ends 16 of the blades 12 in the inlet lining 15, so that a gap 17 is formed between the inlet lining 15 and the radially outer ends 16 of the blades. Through this gap 17 can during operation of the gas turbine, a leakage flow from the high pressure side of the blades 12 to the low pressure side of the same form, wherein in the illustration of Fig. 1 the right side of the blades 12 is the high pressure side in which the pressure P H prevails, and the low pressure side is the left side of the blades on which the pressure P L prevails.

Um nun eine Leckageströmung durch den Spalt 17 zu unterbinden, wird im Sinne der hier vorliegenden Erfindung vorgeschlagen, dass die Gasturbine 10 mindestens einen Kanal 18 aufweist, um den auf der Hochdruckseite der Laufschaufeln 12 herrschenden Druck an der Niederdruckseite derselben im Bereich des abzudichtenden Spalts 17 anzulegen.In order to prevent a leakage flow through the gap 17, it is proposed in the sense of the present invention that the gas turbine 10 has at least one channel 18 to the prevailing on the high pressure side of the blades 12 pressure on the low pressure side thereof in the region of the gap to be sealed 17th to apply.

Hierdurch liegt dann im Bereich des Spalts 17 an der eigentlichen Niederdruckseite desselben in etwa der gleiche Druck an wie an der Hochdruckseite, so dass eine Leckageströmung durch den Spalt 17 und damit den Wirkungsgrad der Gasturbine beeinträchtigende, aerodynamische Spaltverluste effektiv vermieden werden können.As a result, in the region of the gap 17 at the actual low-pressure side thereof, approximately the same pressure is applied as at the high-pressure side, so that a leakage flow through the gap 17 and thus aerodynamic gap losses impairing the efficiency of the gas turbine can be effectively avoided.

Bei dem Einlaufbelag 15 handelt es sich um einen gasdurchlässigen Einlaufbelag, der vorzugsweise eine offenporige Struktur aufweist. Insbesondere ist der Einlaufbelag 15 als offenporiger Metallschaum ausgebildet.The inlet lining 15 is a gas-permeable inlet lining, which preferably has an open-pored structure. In particular, the inlet lining 15 is designed as an open-pored metal foam.

Der in Fig. 1 gezeigte Kanal 18 verläuft zumindest abschnittsweise in dem als Träger für den Einlaufbelag 15 dienenden, gehäuseseitigen Mantelringsegment 14, wobei der Kanal 18 auf der Hochdruckseite, an welcher der Druck PH herrscht, im Bereich des Mantelringsegments 14 in einen Strömungskanal des Hochdruckverdichters 11 der Gasturbine 10 mündet. Auf der Niederdruckseite, an welcher der Druck PL herrscht, mündet der Kanal 16 hingegen im Bereich des Einlaufbelags 15 in den abzudichtenden Spalt 17.The in Fig. 1 channel 18 shown extends at least in sections, in which serves as a carrier for the running-in surface 15, housing-side shroud segment 14, the channel 18 on the high pressure side, where the pressure P H prevails in the area of shroud segment 14 in a flow passage of the high pressure compressor 11 of the gas turbine 10 empties. In contrast, on the low-pressure side, at which the pressure P L prevails, the channel 16 opens in the region of the inlet lining 15 into the gap 17 to be sealed.

Ein Querschnitt des oder jedes Kanals 18 ist vorzugsweise derart bemessen, dass eine gegebenenfalls durch den jeweiligen Kanal strömende Luft im Bereich des abzudichtenden Spalts 17 als Sperrluft wirkt. In den oder jeden Kanal 18 können Leitelemente, z. B. Leitbleche oder Leitgitter, integriert sein, um die durch den Kanal 18 strömende Sperrluft aerodynamisch optimal zu führen.A cross-section of the or each channel 18 is preferably dimensioned such that an optionally flowing through the respective channel air in the region of the gap 17 to be sealed acts as sealing air. In or each channel 18 guide elements, z. As baffles or guide grille, be integrated to aerodynamically optimally guide the flowing through the channel 18 sealing air.

Die Erfindung ist nicht auf den Einsatz an Hochdruckverdichtern beschränkt. Die Erfindung kann auch an anderen Verdichtern und an Turbinen zum Einsatz kommen.The invention is not limited to use on high pressure compressors. The invention can also be used on other compressors and on turbines.

Claims (3)

  1. Gas turbine, in particular gas turbine aircraft engine, comprising at least one compressor, at least one combustion chamber and at least one turbine, the or each compressor and/or the or each turbine comprising a rotor that is surrounded by a stationary housing and comprises rotor blades, and an abradable coating (15) being associated with the housing, characterized in that the gas turbine comprises at least one channel (18) in order to apply pressure, which prevails on a high-pressure side of the rotor blades (12) of a rotor, to a low-pressure side of said rotor blades in the region of a gap (17) between the radially external ends (16) of the rotor blades (12) and the housing (13) and thereby to prevent flow through the gap (17),
    in that the or each channel (18) on the low-pressure side in the region of the abradable coating (15) opens into the gap (17) to be sealed, and
    in that the or each channel (18) extends, at least in portions, in a shroud segment (14) on the housing side, which shroud segment is used as a substrate for the abradable coating (15), such that the channel (18) on the high-pressure side in the region of the shroud segment (14) outside the gap (17) opens into a flow channel.
  2. Gas turbine according to claim 1, characterized in that the abradable coating (15) is gas-permeable and has an open-pored structure.
  3. Gas turbine according to either claim 1 or claim 2, characterized in that the abradable coating (15) in the form of a metal foam.
EP07785646.6A 2006-07-26 2007-07-18 Gas turbine with a peripheral ring segment comprising a recirculation channel Expired - Fee Related EP2044293B1 (en)

Applications Claiming Priority (2)

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DE102006034424A DE102006034424A1 (en) 2006-07-26 2006-07-26 gas turbine
PCT/DE2007/001276 WO2008011864A1 (en) 2006-07-26 2007-07-18 Gas turbine with a peripheral ring segment comprising a recirculation channel

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EP2044293B1 true EP2044293B1 (en) 2018-06-13

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EP (1) EP2044293B1 (en)
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US20090324384A1 (en) 2009-12-31
CA2657190C (en) 2015-06-23
CA2657190A1 (en) 2008-01-31
EP2044293A1 (en) 2009-04-08
US8092148B2 (en) 2012-01-10
DE102006034424A1 (en) 2008-01-31
WO2008011864A1 (en) 2008-01-31

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