EP0176447B1 - Vorrichtung für die automatische Regelung des Spiels einer Labyrinthdichtung einer Turbomaschine - Google Patents

Vorrichtung für die automatische Regelung des Spiels einer Labyrinthdichtung einer Turbomaschine Download PDF

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Publication number
EP0176447B1
EP0176447B1 EP85401864A EP85401864A EP0176447B1 EP 0176447 B1 EP0176447 B1 EP 0176447B1 EP 85401864 A EP85401864 A EP 85401864A EP 85401864 A EP85401864 A EP 85401864A EP 0176447 B1 EP0176447 B1 EP 0176447B1
Authority
EP
European Patent Office
Prior art keywords
air
wear
stator
labyrinth seal
seal member
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
Application number
EP85401864A
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English (en)
French (fr)
Other versions
EP0176447A1 (de
Inventor
Robert Kervistin
Philippe Jean Lefebvre
Alain François Teissier
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.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0176447A1 publication Critical patent/EP0176447A1/de
Application granted granted Critical
Publication of EP0176447B1 publication Critical patent/EP0176447B1/de
Expired legal-status Critical Current

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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
    • F01D11/02—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
    • 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
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means

Definitions

  • the invention relates to an automatic control device in operation of the clearance of a labyrinth type turbomachine seal.
  • the seals between fixed parts and rotating parts of a turbomachine frequently use labyrinth type seals composed, on the one hand, of elements in the form of wipers, in variable number according to the operating conditions and according to various technological parameters, and, on the other hand, on the fixed part opposite, of an element constituting a wear and sealing lining, called "abradable", that is to say usable by friction during possible contact with a wiper without causing significant damage thereto, this element being carried by an annular support connected to a fixed structure of the turbomachine.
  • Such seals can be arranged for example between different movable stages of compressor or turbine, and fixed parts (or rotating at a different speed) in the vicinity.
  • the wipers are in this case carried by spacers or rings and the lining is fixed on the stator (or on the mobile part rotating at the lowest speed preferably).
  • these seals are arranged between various turbomachine enclosures and are found in particular at the ends of the external enclosure of the combustion chamber housing, d on the one hand, on the side of the compressor outlet and, on the other hand, on the side of the turbine inlet.
  • the proper sealing function of the seal is more complex.
  • pressure balancing between various enclosures of the turbomachine is usually sought.
  • Controlled air circulation is also sought in the enclosures with a view to creating a certain flow of ventilation air which can possibly be used in other areas of the turbomachine and thus it may be desirable to control the air flows with the best precision.
  • FR-A-2 437 544 in the name of the Applicant describes a seal in which the support of the wear packings is surrounded by an annular channel connected, at its downstream end, to an air intake provided in the wall of the combustion chamber housing while its other end opens upstream of the point in the lower pressure air space surrounding the compressor shaft.
  • the adjustment of the circulation flow rate of the cooling air of the seal calls for an adjustable discharge valve controlled by an operating parameter of the turbomachine.
  • Another known device aims to obtain cooling of a labyrinth seal placed downstream of a turbomachine compressor and provides for this purpose passages passing through the stator of the seal through which air is sent between two teeth upstream of the seal rotor.
  • labyrinth seals are placed successively from upstream to downstream in three zones located under the downstream part of a combustion chamber and under an associated turbine distributor.
  • the device described collects the leaks coming from the first two seals and reintroduces this air into the third seal between teeth of the seal rotor from holes passing through the stator of this seal.
  • the invention combines new characteristics with these known elements while avoiding the drawbacks of the previous solutions and by new means obtains interesting results.
  • a rise to full throttle speed by rapid acceleration ensuring minimum clearance between the top of the wipers and the cooperating surface of the wear lining and sealing of the labyrinth seal and also, in the event of a sudden deceleration, to avoid any penetration of the wipers into the wear layer, which would cause, in addition to various mechanical disadvantages (vibratory phenomena, overheating inducing phenomena with divergent effect), the subsequent appearance excessive play clearly detrimental to returns.
  • a minimum of play must even be kept in order to allow that a phase of re-acceleration can follow quickly.
  • the device according to the invention of the aforementioned type is characterized in that the wear and sealing lining is composed of two parts, a first part consisting of a honeycomb and a second part having a smooth surface and a series of holes distributed peripherally and passing through the annular support and the wear and sealing lining, is placed at the level of the separation between the two parts of said lining.
  • the first honeycomb part of the wear and sealing lining is located upstream, relative to the normal direction of gas flow of the turbomachine, from the second part with smooth surface.
  • the first honeycomb part of the wear lining and sealing is located downstream, relative to the normal direction of gas flow of the turbomachine, of the second part with smooth surface.
  • FIG. 1 there is shown schematically, in axial section, under stabilized operating conditions, a portion of a turbomachine comprising an embodiment of the invention.
  • a labyrinth seal according to the invention is disposed between a fixed part and a rotating part of the turbomachine.
  • the rotating part is represented diagrammatically by a rotor part 1.
  • the fixed part comprises a stator element 2 connected in a known manner to the fixed structure of the turbomachine.
  • an annular chamber 3 schematically delimited by two radially spaced internal 4 and external 5 elements and by two axially spaced elements upstream 6 and downstream 7, upstream and downstream being defined with respect to the normal direction of gas flow of the turbomachine.
  • the radially external element 5 comprises one or more air inlet orifices 8. Inside the annular chamber 3, a short distance from the radially internal element 4, is disposed a thin sheet 9 pierced with series of multi-holes 10. This sheet divides the annular chamber 3 into two enclosures, one external 3a comprising the air inlets 8 and the other internal 3b.
  • the internal element 4 of the stator element 2 also constitutes an annular support on the radially internal face of which is fixed a lining 11 for wear and sealing which constitutes an element of the labyrinth seal according to the invention.
  • said wear and sealing lining 11 is composed of two parts, arranged axially and separated by a gap 12, an upstream part 11a and a downstream part 11b.
  • the internal element 4 comprises a series of peripherally distributed holes 12a which constitute air outlet orifices in the annular chamber 3.
  • the upstream part 11 a of the wear and sealing lining 11 consists of a honeycomb and the downstream part 11 Q is a lining of known and commonly used type but necessarily having a smooth surface.
  • the rotor part 1 carries wipers respectively 13 upstream and 14 downstream, the shape and number of which are determined so well known to those skilled in the art depending on the operating parameters of the turbomachine.
  • the device according to the invention which has just been described makes it possible to obtain improved operation by ensuring in all operating conditions of the turbomachine, both in stabilized and transient conditions, a practically constant clearance guaranteeing a controlled value of the air flow rate passing through the labyrinth seal of the turbomachine on which said device is adapted without inadvertent variations being observed, the consequences of which are harmful for the yields or for the life of certain parts, in the leakage rates at the labyrinth seal.
  • the games j1 and j2 may tend to increase.
  • the flow D1 tends to increase, but only according to a very small variation, while the flow D3 increases more quickly in a significant way, this consequently results in an increase in the flow D2 of cooling air.
  • the stator element 2 which causes cooling and therefore a contraction of this stator element 2 and, consequently, the clearances j1 and j2 are restored to their initial value.
  • FIG. 2 represents an embodiment for an application of the invention to a labyrinth seal placed in line with the outlet of a combustion chamber on the radially internal side.
  • the internal jacket of an annular type combustion chamber 22 at 23, an annular envelope defining an enclosure 24 for external ventilation of the combustion chamber.
  • the jacket 21 is connected at its downstream end by a fixing means 25, for example of the bolt-on type, to a radial flange 26 of an internal part of stator vane 27.
  • the casing 23 carries a directed radial flange 28 towards the axis of the machine and to which are fixed by fixing means 29, for example of the bolt type, on the one hand, a radial flange 30 at the end of an annular support 31 and, on the other hand , a radial flange 32 at the end of a multi-perforated annular thin sheet 33.
  • the annular support 31 carries on its radially internal face a wear and sealing lining 34 which comprises two parts arranged axially, an upstream part 34a consisting of a honeycomb and a downstream part 34b having a smooth external surface, these two parts being separated by an interval 34c.
  • the annular support 31 comprises at this interval 34c a series of holes 35.
  • the annular thin sheet 33 is slightly spaced radially outward relative to the support 31 on which it is in radial support at 36 at its downstream end.
  • the support 31 carries a radial flange 37 directed radially outwards and making the connection with the internal part of the stator vane 27.
  • the rotary rotor part comprises a disc 38 carrying in the example shown five wipers 39 cooperating with the wear and sealing lining 34.
  • the internal enclosure is separated by the disc 38 into an upstream enclosure 40 where the air is at pressure P1 and a downstream enclosure 41 where the air is at pressure P2 lower than P1.
  • a space formed between the annular support 31 and the chamber envelope 23 constitutes an annular chamber 42 allowing the ventilation of the annular support 31 and separated into two enclosures 42a and 42b by the annular sheet 33.
  • This thin sheet 33 includes multi-perforations 43 for the impact ventilation of the support 31.
  • An opening 44 made in the envelope 23 ensures the passage of an air flow D2 from the enclosure 24 of the combustion chamber to the chamber 42.
  • FIG. 3 schematically represents a part of a turbomachine similar to that which is represented in FIG. 1 and comprising a second embodiment of the invention.
  • the same references have been kept for identical parts as those which appear in FIG. 1 and reference will be made for more details to the complete description of the device which was made previously with reference to FIG. 1.
  • the wear and seal 111 entering the labyrinth seal is composed of two parts, arranged axially and separated by a gap 12, as before.
  • the upstream part 111_a of the wear and sealing lining 111 has a smooth surface and the downstream part 111 b consists of a honeycomb.
  • the device according to the invention according to the second embodiment which has just been described also makes it possible to ensure, as in the first mode, a practically constant clearance of the labyrinth seal, by guaranteeing a controlled value of the air flow passing through said joint and allowing to obtain the same advantages previously noted.
  • the clearances I 1 and I 2 may tend to decrease.
  • the flow rate D'3 tends to decrease but according to a very small variation whereas the flow rate D'1 decreases more quickly and in a more notable manner, it consequently results in an increase in the flow rate D'2 of air heating of the stator element 2 and therefore a dilation of this stator element 2 and consequently, the clearances I1 and J'2 are restored to their initial value.
  • the effects tending to decrease the games I 1 and I 2 are compensated and canceled and the games I 1 and I 2 are maintained at their objective value determined by the optimal results aimed for in stabilized operation of the turbomachine and it will be the same in all the operating conditions of the turbomachine tending to decrease the clearances i1 and i2.
  • the clearances I and I2 may tend to increase.
  • the flow rate D'3 tends to increase but only according to a very small variation whereas the flow rate D'1 increases more quickly in a significant way, this consequently results in a reduction in the flow rate D'2 d ' air heating of the stator element 2, which causes this stator element 2 to contract and consequently the clearances I 1 and I 2 are restored to their initial value.
  • the effects tending to increase the games I 1 and I 2 are compensated and canceled and the games I 1 and I 2 are again maintained at their objective value and so will be.
  • the device according to the invention also provides, in the second embodiment, a means of automatic correction, in real time, of variations in operation of the games I 1 and I 2 of the labyrinth to keep them at their chosen objective value.
  • FIG. 4 represents the same application of the second embodiment of the invention shown in FIG. 3.
  • the same references have again been kept for identical parts as those appearing in FIG. 2. We will limit our to indicating briefly the features arising from the application of the embodiment of Figure 3 to a labyrinth seal of the kind shown in Figure 2.
  • the identical annular support 31 carries on its radially inner face a wear lining and d seal 134 which has two parts arranged axially, an upstream part 134a having a smooth external surface and a downstream part 134b consisting of a honeycomb, these two parts being separated by a gap 134c. Furthermore, a flow of air D'2 for heating the annular support 31 is taken from the enclosure 24 of the combustion chamber.

Claims (3)

1. Vorrichtung für die automatische Regelung des Spiels einer als Labyrinthdichtung ausgebildeten Dichtung für Turbomaschinen, bei der Elemente (13,14; 39) in Form von Lamellen von einem Rotorteil (1; 38) und eine den Lamellen (13,14; 39) gegenüberliegende Verschleiß- und Dichtungsgarnitur (11; 34; 111; 134) von einer ringförmigen Halterung (4; 31) getragen sind, die den radial inneren Teil des Stators bildet, wobei der Stator eine ringförmige Kammer (3; 42) aufweist, die auf ihrem Außendurchmesser mit Lufteintrittsöffnungen (18; 44) versehen ist, und wobei ein dünnes Blech (9; 33), das mit einer Vielzahl von Löchern (10) versehen ist, im Innern der genannten Kammer (3; 42) in geringem Abstand von der ringförmigen Halterung (4; 31) angeordnet ist, dadurch gekennzeichnet, daß die Verschleiß- und Dichtungsgarnitur (11; 34; 111; 134) aus zwei Teilen (11a, 11b; 34a, 34b; 111a, 111 b; 134a, 134b) zusammengesetzt ist, einem ersten Teil (11a; 34a; 111a; 134a), der aus einem Wabenmuster besteht, und einem zweiten Teil (11b; 34b; 111b; 134b) mit weicher Oberfläche; daß eine Reihe von über den Umfang verteilten Löchern (12a; 35), die die ringförmige Halterung (4; 31) und die Verschleiß- und Dichtungsgarnitur (11; 34; 111; 134) durchdringen, in Höhe des Zwischenraums (12; 34c; 134c) angebracht sind, der die beiden Teile (11 a und 11b; 34a und 34b; 111a und 111b; 134a und 134b) der Garnitur (11; 34; 111; 134) voneinander trennt.
2. Vorrichtung zur automatischen Regelung des Spiels einer Labyrinthdichtung nach Anspruch 1, dadurch gekennzeichnet, daß der als Wabenmuster ausgebildete erste Teil (11a; 34a) der Verschleiß- und Dichtungsgarnitur (11; 34) in Bezug auf die normale Gaszirkulationsrichtung der Turbomaschine stromaufwärts des zweiten Teils (11b; 34b) mit weicher Oberfläche angeordnet ist und daß die genannten Löcher (12a; 35) der Garnitur von der in dem Statorteil der Dichtung vorgesehenen Kammer (3; 42) mit Kühlluft gespeist werden, die kälter ist als die Luft, die die Dichtung von dem stromaufwärtigen auf der Seite der stärkeren Drücke liegenden Endbereich aus direkt durchsetzt.
3. Vorrichtung zur automatischen Regelung des Spiels einer Labyrinthdichtung nach Anspruch 1, dadurch gekennzeichnet, daß der als Wabenmuster ausgebildete erste Teil (111 b; 134b) der Verschleiß- und Dichtungsgarnitur (111; 134) in Bezug auf die normale Gaszirkulationsrichtung der Turbomaschine stromabwärts des zweiten Teils (111a; 134a) mit weicher Oberflüche angeordnet ist und daß die genannten Löcher (12a; 35) der Garnitur (111; 134) von der in dem Statorteil der Dichtung vorgesehenen Kammer (3; 42) mit Kühlluft gespeist werden, die kälter ist als die Luft, die die Dichtung von dem stromaufwärtigen auf der Seite der stärkeren Drücke liegenden Endbereich aus direkt durchsetzt.
EP85401864A 1984-09-27 1985-09-25 Vorrichtung für die automatische Regelung des Spiels einer Labyrinthdichtung einer Turbomaschine Expired EP0176447B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8414819A FR2570764B1 (fr) 1984-09-27 1984-09-27 Dispositif de controle automatique du jeu d'un joint a labyrinthe de turbomachine
FR8414819 1984-09-27

Publications (2)

Publication Number Publication Date
EP0176447A1 EP0176447A1 (de) 1986-04-02
EP0176447B1 true EP0176447B1 (de) 1987-11-04

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EP85401864A Expired EP0176447B1 (de) 1984-09-27 1985-09-25 Vorrichtung für die automatische Regelung des Spiels einer Labyrinthdichtung einer Turbomaschine

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US (1) US4662821A (de)
EP (1) EP0176447B1 (de)
JP (1) JPS6185504A (de)
DE (1) DE3560917D1 (de)
FR (1) FR2570764B1 (de)

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Also Published As

Publication number Publication date
US4662821A (en) 1987-05-05
JPS6185504A (ja) 1986-05-01
JPH0350082B2 (de) 1991-07-31
FR2570764A1 (fr) 1986-03-28
DE3560917D1 (en) 1987-12-10
EP0176447A1 (de) 1986-04-02
FR2570764B1 (fr) 1986-11-28

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