EP0261460A2 - Turbo machine with transsonic stages - Google Patents

Turbo machine with transsonic stages Download PDF

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Publication number
EP0261460A2
EP0261460A2 EP87112792A EP87112792A EP0261460A2 EP 0261460 A2 EP0261460 A2 EP 0261460A2 EP 87112792 A EP87112792 A EP 87112792A EP 87112792 A EP87112792 A EP 87112792A EP 0261460 A2 EP0261460 A2 EP 0261460A2
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EP
European Patent Office
Prior art keywords
turbo machine
machine according
flow
impeller
hub
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.)
Granted
Application number
EP87112792A
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German (de)
French (fr)
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EP0261460B1 (en
EP0261460A3 (en
Inventor
Jean Dr. Hourmouziadis
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
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MTU Motoren und Turbinen Union Muenchen GmbH
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Publication of EP0261460A3 publication Critical patent/EP0261460A3/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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • 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
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • 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
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/302—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor characteristics related to shock waves, transonic or supersonic flow

Definitions

  • the invention relates to a turbomachine with stages with transonic flow, in particular a gas turbine with a stationary guide vane.
  • the object of the invention is to achieve the abovementioned which occur in a turbomachine of the type mentioned at the beginning Eliminate disadvantages and in particular to prevent or minimize a circulating flow between the blades in each division on the trailing edge of the inlet grille.
  • the object is achieved in that a compensation device for pressure compensation of pressure gradients resulting from compression surges at the outlet edge of the preliminary grille is provided on the circumference behind the guide grille on the hub and / or housing.
  • the compensating device is preferably designed as at least one calming chamber, which extends over the circumference and is arranged on the hub side and has a circumferential opening towards the subsequent impeller, which is covered with a radially acting sealing flange of the impeller.
  • the sealing flange is expediently designed as a double peripheral seal, each of the two peripheral seals being designed as a labyrinth seal.
  • annular spaces arranged in the housing are formed with a connection to the main flow by means of a blocking element as a throttle point.
  • the annular space is filled with filling material such as metal or mineral wool, fiber, fabric, foam.
  • filling material such as metal or mineral wool, fiber, fabric, foam.
  • one or more compression surges 3 as shown in FIG. 1 occur at the trailing edge 18, particularly when the Mach number M is high. With the division t, these compression surges 3 generate periodic pressure gradients 4 which are many times larger than in the subsonic range.
  • annular spaces 14 there are annular spaces 14 in the area of the housing wall outside of the actual flow channel, then an inflow B into these annular spaces 14 takes place at points of high pressure, and an outflow D at points of low pressure, as can be seen in particular from FIG. 4 is. There is therefore a circulating flow C in each division at the radially outer and inner edge of the flow channel. As a result, the circulating gas at the edge of the Channel disturbs the main flow, increases the losses and deteriorates the efficiency of the gas turbine 1. In addition, the inflow of hot gas into the annular spaces 14 increases the temperature of the components, as a result of which the residual and thus the service life are reduced.
  • the invention proposes a pressure compensation device 2 for compensating the pressure gradients 4 created by compression surges 3 over the circumference behind the impeller 9 on the hub and / or housing 6, as can be seen in particular in FIGS. 5 and 6.
  • a calming chamber 8 which extends in the circumferential direction of the inlet grille 5 at a radially inner point with a circumferential opening to the rear to the subsequent impeller 9, the circumferential opening being covered with a radially oriented sealing flange 10 of the impeller 9 .
  • the sealing flange 10 is fastened to the impeller 9 via an axial flange 11 and provides a labyrinth seal 13 at the radially inner location and a labyrinth seal 12 at the radially outer location of the peripheral opening.
  • the circulating flow C takes place via the upper labyrinth seal 12.
  • the calming chamber 8 there is then a certain pressure compensation in the circumferential direction, which again makes it possible for the inflow of hot gas via the lower one with only a slightly increased back pressure in the interior 7 To prevent labyrinth seal 13.
  • the aforementioned pressure equalization device is found between the stationary and rotating part of the turbine.
  • the annular spaces 14 between standing parts are sealed against the main flow, with the aid of locking members 15, for example in the form of Angle profiles, which form the opening 16 as a throttle point.
  • the annular spaces 14 are filled with filling material 17, such as. B. metal or mineral wool, fiber, fabric, foam. Filling material 17 and locking member 15 nevertheless enable pressure equalization and temperature equalization in the annular space 14.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Bei einer Turbomaschine mit transsonisch durchströmten Stufen, insbesondere Gasturbine (1) mit stationärem Vorleitgitter (5) ist eine Druckausgleichsvorrichtung zum Ausgleich der durch Verdichtungsstöße entstehenden Druckgradienten über dem Umfang hinter dem Vorleitgitter (5) an Nabe und/oder am Gehäuse vorgesehen. Die Druckausgleichsvorrichtung umfaßt insbesondere eine Beruhigungskammer (8) in Nabennähe des Vorleitgitters (5), die mit einem radial ausgerichteten Dichtungsflanch (10) des Laufrades (9) zusammenwirkt.In a turbomachine with stages through which flow is transonic, in particular a gas turbine (1) with a stationary guide grille (5), a pressure compensation device is provided to compensate for the pressure gradients arising from compression surges over the circumference behind the guide grille (5) on the hub and / or on the housing. The pressure compensation device comprises in particular a calming chamber (8) in the vicinity of the hub of the inlet grille (5), which cooperates with a radially oriented sealing flange (10) of the impeller (9).

Description

Die Erfindung betrifft eine Turbomaschine mit transso­nisch durchströmten Stufen, insbesondere eine Gasturbine mit stationärem Vorleitgitter.The invention relates to a turbomachine with stages with transonic flow, in particular a gas turbine with a stationary guide vane.

Bei transsonisch durchströmten Gasturbinen (Einströmge­schwindigkeit beim Leitrad im Unterschallbereich, mitt­lere Ausströmgeschwindigkeit an der Leitradhinterkante im transsonischen Bereich (M > 0.8) stellen sich bei Ab­strömung mit hohen Mach-Zahlen M an der Hinterkante des Leitrads ein oder mehrere Verdichtungsstöße ein. Diese Verdichtungsstöße erzeugen mit der Teilung der Schaufeln periodische Druckgradienten, die um ein Vielfaches größer sind als im Unterschallbereich (M < 0.8).In gas turbines with transonic flow (inflow speed at the stator in the subsonic region, average outflow speed at the stator rear trailing edge in the transonic region (M> 0.8), one or more compression surges occur at the trailing edge of the stator at high Mach numbers M. These compression surges produce with Division of the blades periodic pressure gradients that are many times larger than in the subsonic range (M <0.8).

Befinden sich außerhalb des Strömungskanals der Gastur­bine Hohlräume, so erfolgt an Stellen hohen Drucks ein Einströmen des Gases in die Hohlräume; an Stellen nied­rigen Drucks ein Herausströmen. Es stellt sich in jeder Teilung am radial äußeren und inneren Rand des Strömungs­kanals eine zirkulierende Strömung ein. Diese stört in nachhaltiger Weise die Hauptströmung, erhöht die Verluste und verschlechtert den Wirkungsgrad der Gasturbine. Von Nachteil ist ferner, daß bei einem Einströmen von Heiß­gas in Hohlräume die Temperatur der Bauteile erhöht wird, wodurch die Festigkeit und damit die Lebensdauer verrin­gert wird.If there are cavities outside the flow channel of the gas turbine, the gas flows into the cavities at points of high pressure; leakage at low pressure points. A circulating flow occurs in each division on the radially outer and inner edge of the flow channel. This disturbs the main flow in a sustainable manner, increases losses and deteriorates the efficiency of the gas turbine. Another disadvantage is that when hot gas flows into cavities, the temperature of the components is increased, as a result of which the strength and thus the service life are reduced.

Aufgabe der Erfindung ist es, die bei einer Turbomaschine der eingangs genannten Art auftretenden vorgenannten Nachteile zu beseitigen und insbesondere eine zirkulie­rende Strömung zwischen den Schaufeln in jeder Teilung an der Hinterkante des Vorleitgitters zu verhindern bzw. zu minimieren.The object of the invention is to achieve the abovementioned which occur in a turbomachine of the type mentioned at the beginning Eliminate disadvantages and in particular to prevent or minimize a circulating flow between the blades in each division on the trailing edge of the inlet grille.

Erfindungsgemäß wird die gestellte Aufgabe dadurch ge­löst, daß eine Ausgleichsvorrichtung zum Druckausgleich von durch Verdichtungsstöße an der Austrittskante des Vorleitgitters entstehenden Druckgradienten über dem Um­fang hinter dem Leitgitter an der Nabe und/oder Gehäuse vorgesehen ist.According to the invention, the object is achieved in that a compensation device for pressure compensation of pressure gradients resulting from compression surges at the outlet edge of the preliminary grille is provided on the circumference behind the guide grille on the hub and / or housing.

Dies hat den wesentlichen Vorteil, daß die aufgrund der Verdichtungsstöße auftretenden zirkulierenden Strömungen unterbunden werden, und auf diese Weise sowohl Strömungs­verluste verringert werden, als auch die thermische Be­anspruchung von Bauteilen durch in die Hohlräume eindrin­gendes Heißgas herabgesetzt wird.This has the essential advantage that the circulating flows occurring due to the compression surges are prevented, and in this way both flow losses are reduced and the thermal stress on components is reduced by hot gas penetrating into the cavities.

Die Ausgleichsvorrichtung wird vorzugsweise als zumindest eine über dem Umfang sich erstreckende nabenseitig ange­ordnete Beruhigungskammer ausgestaltet, die zum nachfol­genden Laufrad hin eine Umfangsöffnung aufweist, welche mit einem radial wirkenden Dichtungsflansch des Laufrades abgedeckt ist.The compensating device is preferably designed as at least one calming chamber, which extends over the circumference and is arranged on the hub side and has a circumferential opening towards the subsequent impeller, which is covered with a radially acting sealing flange of the impeller.

Der Dichtungsflansch ist zweckmäßigerweise als doppelte Umfangsdichtung ausgeführt, wobei jede der beiden Umfangs­dichtungen als Labyrinthdichtung ausgebildet ist. Diese Maßnahmen verhindern, daß durch den Spalt zwischen rotie­renden und stehenden Teilen Heißgas in die radial innen liegenden Hohlräume eindringt und eine dadurch entste­hende zirkulierende Strömung die Hauptströmung behindert.The sealing flange is expediently designed as a double peripheral seal, each of the two peripheral seals being designed as a labyrinth seal. These measures prevent hot gas from penetrating into the radially inner cavities through the gap between rotating and standing parts, and a circulating flow which arises as a result hinders the main flow.

Auch können zweckmäßige Maßnahmen an stehenden Teilen zwecks Verhingerung bzw. Minimierung der zirkulierenden Strömung vorgesehen werden. Insbesondere werden im Gehäuse angeordnete Ringräume mit einer Verbindung zur Hauptströ­mung hin mittels eines Sperrgliedes als Drosselstelle ausgebildet.Appropriate measures can also be provided on stationary parts in order to prevent or minimize the circulating flow. In particular, annular spaces arranged in the housing are formed with a connection to the main flow by means of a blocking element as a throttle point.

Der Ringraum wird mit Füllmaterial wie Metall- oder Mine­ralwolle, -faser, -gewebe, -schaum, aufgefüllt. Der lose Verschluß ermöglicht zwar einen Druck- und einen Tempera­turausgleich, verhindert jedoch eine nennenswerte Gas­strömung.The annular space is filled with filling material such as metal or mineral wool, fiber, fabric, foam. The loose closure allows pressure and temperature to be equalized, but prevents significant gas flow.

Die Erfindung wird nachfolgend anhand von Ausführungs­beispielen unter Bezugnahme auf die beigeführten Zeich­nungen mit Erläuterung des Standes der Tecknik näher beschrieben; es zeigen:

  • Fig. 1 zwei benachbarte Leitschaufeln des Leitgitters einer Turbomaschine im Schnitt mit schematischer Darstellung von Verdichtungsstößen an der Hinter­kante,
  • Fig. 2 eine schematische Darstellung des durch die Ver­dichtungsstöße längs A-A der Fig. 1 erzeugten Druckgradienten,
  • Fig. 3 einen Teilaxialschnitt einer Gasturbine mit zir­kulierender Strömung C zwischen Vorleitgitter und Laufrad nach dem Stand der Technik,
  • Fig. 4 die zirkulierende Strömung C gemäß Fig. 3 inner­halb einer Schaufelteilung,
  • Fig. 5 nabenseitige Beruhigungskammer zwischen stehenden und rotierenden Teilen, gesehen in eimen schema­tischen Teilaxialschnitt einer Gasturbine mit Vorleitgitter und Laufrad und
  • Fig. 6 radial außen liegender Ringraum an stehenden Teilen im Bereich des Gehäuses einer Turbine, gesehen in einem Teilaxialschnitt ähnlich der Fig. 5.
The invention is described below with reference to exemplary embodiments with reference to the accompanying drawings with an explanation of the state of Tecknik; show it:
  • 1 two adjacent guide vanes of the guide vane of a turbomachine in section with a schematic representation of compression surges at the rear edge,
  • 2 shows a schematic illustration of the pressure gradient generated by the compression surges along AA of FIG. 1,
  • 3 shows a partial axial section of a gas turbine with a circulating flow C between the guide vane and the impeller according to the prior art,
  • 4 shows the circulating flow C according to FIG. 3 within a blade division,
  • Fig. 5 hub-side calming chamber between standing and rotating parts, seen in a schematic partial axial section of a gas turbine with grille and impeller and
  • 6 radially outer annular space on standing parts in the region of the housing of a turbine, seen in a partial axial section similar to FIG. 5.

In den Fig. 1 bis 4 ist der Effekt der zirkulierenden Strömung C innerhalb einer Teilung t der Schaufeln 19, 20 im Bereich der Schaufelhinterkante 18 nach dem Stand der Technik dargestellt.1 to 4 show the effect of the circulating flow C within a division t of the blades 19, 20 in the region of the blade rear edge 18 according to the prior art.

Bei transsonisch durchströmten Gasturbinen 1 (Schaufel­eintrittsgeschwindigkeit im Unterschallbereich; Schaufel­abströmgeschwindigkeit im transsonischen Bereich) stellen sich bei Abströmung insbesondere bei hohen Mach-Zahlen M an der Hinterkante 18 eine oder mehrere Verdichtungs­stöße 3 gemäß Fig. 1 ein. Diese Verdichtungsstöße 3 er­zeugen mit der Teilung t periodische Druckgradienten 4, die um ein Vielfaches größer sind als im Unterschallbe­reich.In gas turbines 1 through which flow is transonic (blade entry speed in the subsonic range; blade outflow speed in the transonic range), one or more compression surges 3 as shown in FIG. 1 occur at the trailing edge 18, particularly when the Mach number M is high. With the division t, these compression surges 3 generate periodic pressure gradients 4 which are many times larger than in the subsonic range.

Befinden sich beispielsweise gemäß Fig. 3 außerhalb des eingentlichen Strömungskanals Ringräume 14 im Bereich der Gehäusewand, so erfolgt an Stellen hohen Drucks ein Ein­strömen B in diese Ringräume 14 hinein, an Stellen nied­rigen Drucks ein Herausströmen D, wie dies insbesondere der Fig. 4 zu entnehmen ist. Es stellt sich mithin in jeder Teilung am radial äußeren und inneren Rand des Strömungskanals eine zirkulierende Strömung C ein. Dies hat zur Folge, daß das zirkulierende Gas am Rand des Kanals die Hauptströmung stört, die Verluste erhöht und den Wirkungsgrad der Gasturbine 1 verschlechtert. Darüber hinaus erhöht das Einströmen von Heißgas in die Ringräume 14 die Temperatur der Bauteile, wodurch die Restigkeit und damit die Lebensdauer verringert werden.If, for example, according to FIG. 3, there are annular spaces 14 in the area of the housing wall outside of the actual flow channel, then an inflow B into these annular spaces 14 takes place at points of high pressure, and an outflow D at points of low pressure, as can be seen in particular from FIG. 4 is. There is therefore a circulating flow C in each division at the radially outer and inner edge of the flow channel. As a result, the circulating gas at the edge of the Channel disturbs the main flow, increases the losses and deteriorates the efficiency of the gas turbine 1. In addition, the inflow of hot gas into the annular spaces 14 increases the temperature of the components, as a result of which the residual and thus the service life are reduced.

Durch die Erfindung wird eine Druckausgleichsvorrichtung 2 zum Ausgleich der durch Verdichterungsstöße 3 entstehen­den Druckgradienten 4 über dem Umfang hinter dem Laufrad 9 an Nabe und/oder Gehäuse 6 vorgeschlagen, wie dies ins­besondere den Fig. 5 und Fig. 6 zu entnehmen ist.The invention proposes a pressure compensation device 2 for compensating the pressure gradients 4 created by compression surges 3 over the circumference behind the impeller 9 on the hub and / or housing 6, as can be seen in particular in FIGS. 5 and 6.

Die Druckausgleichsvorrichtung 2 gemäß Fig. 5 besteht insbesondere aus einer Beruhigungskammer 8, welche sich in Umfangsrichtung des Vorleitgitters 5 an radial innerer Stelle mit einer Umfangsöffnung nch hinten zum nachfol­genden Laufrad 9 erstreckt, wobei die Umfangsöffnung mit einem radial ausgerichteten Dichtungsflansch 10 des Lauf­rades 9 abgedeckt ist. Der Dichtungsflansch 10 ist am Laufrad 9 über einen Axialflansch 11 befestigt und sieht an radial innerer Stelle eine Labyrinthdichtung 13 und an radial äußerer Stelle der Umfangsöffnung eine Laby­rinthdichtung 12 vor.5 consists in particular of a calming chamber 8, which extends in the circumferential direction of the inlet grille 5 at a radially inner point with a circumferential opening to the rear to the subsequent impeller 9, the circumferential opening being covered with a radially oriented sealing flange 10 of the impeller 9 . The sealing flange 10 is fastened to the impeller 9 via an axial flange 11 and provides a labyrinth seal 13 at the radially inner location and a labyrinth seal 12 at the radially outer location of the peripheral opening.

Die zirkulierende Strömung C nach dem Stand der Technik erfolgt über die obere Labyrinthdichtung 12. In der Be­ruhigungskammer 8 erfolgt dann ein gewisser Druckausgleich in Umfangsrichtung, wodurch es wieder ermöglicht wird, mit einem nur geringfügig erhöhten Gegendruck im Innen­raum 7 das Einströmen von Heißgas über die untere Laby­rinthdichtung 13 zu verhindern. Vorgenannte Druckgleichs­vorrichtung findet sich zwischen stehendem und rotierendem Teil der Turbine.The circulating flow C according to the prior art takes place via the upper labyrinth seal 12. In the calming chamber 8 there is then a certain pressure compensation in the circumferential direction, which again makes it possible for the inflow of hot gas via the lower one with only a slightly increased back pressure in the interior 7 To prevent labyrinth seal 13. The aforementioned pressure equalization device is found between the stationary and rotating part of the turbine.

Un eine zurkulierende Strömung C in stationären Ringräu­men 14 des Gehäuses 6 der Gasturbine 1 zu verhindern, werden die Ringräume 14 zwischen stehenden Teilen, die aus anderen Gründen erforderlich sind, gegen die Haupt­strömung abgedichtet, und zwar mit Hilfe von Sperrglie­dern 15, beispielsweise in Form von Winkelprofilen, welche die Öffnung 16 als Drosselstelle ausbilden. Um den Wider­stand für die zirkulierende Strömung C zu erhöhen, werden die Ringräume 14 mit Füllmaterial 17 gefüllt, wie z. B. Metall- oder Mineralwolle, -faser, -gewebe, -schaum. Füllmaterial 17 und Sperrglied 15 ermöglichen gleichwohl einen Druckausgleich und einen Temperaturausgleich im Ringraum 14.In order to prevent a cumulative flow C in stationary annular spaces 14 of the housing 6 of the gas turbine 1, the annular spaces 14 between standing parts, which are required for other reasons, are sealed against the main flow, with the aid of locking members 15, for example in the form of Angle profiles, which form the opening 16 as a throttle point. In order to increase the resistance to the circulating flow C, the annular spaces 14 are filled with filling material 17, such as. B. metal or mineral wool, fiber, fabric, foam. Filling material 17 and locking member 15 nevertheless enable pressure equalization and temperature equalization in the annular space 14.

Alle in der Beschreibung erwähnten und/oder in der Zeich­nung dargestellten neuen Merkmale für sich oder in sinn­voller Kombination sind erfindungswesentlich, auch so weit sie in den Ansprüchen nicht ausdrücklich beansprucht sind.All of the new features mentioned in the description and / or shown in the drawing, by themselves or in a meaningful combination, are essential to the invention, even to the extent that they are not expressly claimed in the claims.

Claims (6)

1. Turbomaschine mit transsonisch durchströmten Stufen, insbesondere Gasturbine mit stationärem Vorleitgitter, dadurch gekennzeichnet, daß eine Ausgleichsvorrich­tung (2) zum Druckausgleich von durch Verdichtungs­stöße (3) an der Austrittskante des Vorleitgitters entstehenden Druckgradienten (4) über dem Umfang hinter dem Leitgitter (5) an Nabe und/oder Gehäuse (6) vorgesehen ist.1. Turbomachine with stages through which flow is transonic, in particular a gas turbine with a stationary guide vane, characterized in that a compensation device (2) for pressure compensation of pressure gradients (4) at the outlet edge of the guide vane (4) over the circumference behind the guide vane (5) is provided on the hub and / or housing (6). 2. Turbomaschine nach Anspruch 1, dadurch gekennzeichnet, daß die Ausgleichsvorrichtung (2) zumindest eine über dem Umfang sich erstreckende nabenseitig ange­ordnete Beruhigungskammer (8) umfaßt, die zum nach­folgenden Laufrad (9) hin eine Umfangsöffnung auf­weist, welche mit einem radial ausgerichteten Dich­tungsflansch (10) des Laufrades (9) abgedeckt ist.2. Turbo machine according to claim 1, characterized in that the compensating device (2) comprises at least one circumferentially extending hub-side calming chamber (8) which has a peripheral opening towards the subsequent impeller (9), which with a radially aligned sealing flange ( 10) of the impeller (9) is covered. 3. Turbomaschine nach Anspruch 2, dadurch gekennzeichnet, daß der Dichtungsflansch (10) als doppelte Umfangs­dichtung ausgebildet ist.3. Turbo machine according to claim 2, characterized in that the sealing flange (10) is designed as a double peripheral seal. 4. Turbomaschine nach Anspruch 2 oder 3, dadurch gekenn­zeichnet,daß jede der beiden Umfangsdichtungen als Labyrinthdichtung (12 bzw. 13) ausgebildet ist.4. Turbo machine according to claim 2 or 3, characterized in that each of the two circumferential seals is designed as a labyrinth seal (12 or 13). 5. Turbomaschine nach Anspruch 1, dadurch gekennzeichnet daß die Ausgleichsvorrichtung (2) einen im Gehäuse (6) angeordneten Ringraume (14) mit einer Verbindung zur Hauptströmung hin umfaßt, die mittels eines Sperr­gliedes (15) als Drosselstelle ausgebildet ist.5. Turbo machine according to claim 1, characterized in that the compensating device (2) comprises a housing (6) arranged annular spaces (14) with a connection to the main flow, which is designed as a throttle point by means of a blocking member (15). 6. Turbomaschine nach Anspruch 5 oder 6, dadurch gekenn­zeichnet, daä der ringraum (14) mit Füllmateial (17) wie Metall- oder Mineralwolle, -faser, -gewebe, -schaum, gefüllt ist.6. Turbo machine according to claim 5 or 6, characterized in that the annular space (14) is filled with filling material (17) such as metal or mineral wool, fiber, fabric, foam.
EP87112792A 1986-09-20 1987-09-02 Turbo machine with transsonic stages Expired - Lifetime EP0261460B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3632094 1986-09-20
DE19863632094 DE3632094A1 (en) 1986-09-20 1986-09-20 TURBO MACHINE WITH TRANSITIONAL FLOWED STEPS

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EP0261460A2 true EP0261460A2 (en) 1988-03-30
EP0261460A3 EP0261460A3 (en) 1989-11-08
EP0261460B1 EP0261460B1 (en) 1992-06-24

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EP87112792A Expired - Lifetime EP0261460B1 (en) 1986-09-20 1987-09-02 Turbo machine with transsonic stages

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US (1) US4836745A (en)
EP (1) EP0261460B1 (en)
DD (1) DD265444A1 (en)
DE (2) DE3632094A1 (en)

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US5721023A (en) * 1993-12-17 1998-02-24 E. I. Du Pont De Nemours And Company Polyethylene terephthalate articles having desirable adhesion and non-blocking characteristics, and a preparative process therefor

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Also Published As

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DE3632094A1 (en) 1988-03-24
DE3779982D1 (en) 1992-07-30
EP0261460B1 (en) 1992-06-24
DD265444A1 (en) 1989-03-01
US4836745A (en) 1989-06-06
EP0261460A3 (en) 1989-11-08

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