EP0182716B1 - Anstreifring für eine Gasturbine - Google Patents

Anstreifring für eine Gasturbine Download PDF

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Publication number
EP0182716B1
EP0182716B1 EP85402243A EP85402243A EP0182716B1 EP 0182716 B1 EP0182716 B1 EP 0182716B1 EP 85402243 A EP85402243 A EP 85402243A EP 85402243 A EP85402243 A EP 85402243A EP 0182716 B1 EP0182716 B1 EP 0182716B1
Authority
EP
European Patent Office
Prior art keywords
annular support
ring
turbine
annular
temperature
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
EP85402243A
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English (en)
French (fr)
Other versions
EP0182716A1 (de
Inventor
Alain Jacques Emile Guibert
Roland René Mestre
Rémy Paul Charles Ritt
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 EP0182716A1 publication Critical patent/EP0182716A1/de
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Publication of EP0182716B1 publication Critical patent/EP0182716B1/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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator

Definitions

  • the present invention relates to a turbine ring for a gas turbomachine.
  • FR-A-2 540 937, FR-A-2 540 938 and FR-A-2 540 939 as well as FR-A-2 371 575 all describe turbine rings for gas turbomachines, each comprising an annular support, fixed inside the casing of the turbine, and a ring, which is made at least partially of a ceramic and abradable material, and which is fixed inside said annular support.
  • the annular support is made of a metallic material, and, owing to the great difference existing between the respective coefficients of expansion of the metallic materials and of the ceramic materials, the ring of ceramic material must be formed by segments independent of each other, and coupled by their respective ends so as to allow the radius of said ring to follow variations in the radius of the annular support, as a function of the different temperatures that the latter takes for the different operating modes of the turbine , thus avoiding that the ring of ceramic material is subjected to stresses incompatible with the mechanical resistance of the material which constitutes it.
  • FR-A-2 559 834 describes, in its preamble, the numerous drawbacks linked to the use of a ring made of ceramic material, constituted by the juxtaposition of several segments. It is further indicated that these drawbacks can be overcome by also constituting the annular support in a ceramic material, and by making the abradable ring in one piece. In a preferred embodiment of the turbine ring described in this last French patent application, the dimensioning is also such that the annular support exerts, when cold, on the abradable ring, a precompression determined so as to cancel or reverse at normal turbine operating temperature.
  • means are provided for regulating the temperature of the components of the turbine ring, these means comprising for example a circulation of cooling air coming from of the turbine compressor.
  • These cooling means are generally provided so as to act indistinctly on the two main components of the turbine ring, namely its annular support and its or its elements made of abradable ceramic material. Consequently, the temperature gradient between the inner and outer faces of the abradable ring, for example, is very large, and gives rise to stresses in the latter, which can reduce its lifespan.
  • the turbine ring according to the present invention also comprises an annular support, mounted inside the turbine casing, a one-piece ring, made of an abradable ceramic material, mounted inside said annular support, and dimensioned so that the latter applies to said ring, at least when cold, axipetal compression, as well as means for adjusting the temperature of the components of the turbine ring.
  • the turbine ring according to the present invention is characterized in that its internal diameter is adjusted by means of the temperature adjustment means only of the annular support which is metallic so that the annular support exerts an appropriate axipetal compression on the 'ring abradable at all operating speeds, taking into account the temperature of the parts, from the initial assembly in preload of said ring on the annular support.
  • the temperature gradient between the interior and exterior surfaces of the abradable ring is relatively small, which avoids the appearance therein of constraints likely to reduce its lifespan.
  • the temperature gradient in the radial direction, inside the annular support is very important, but, as this support is metallic, it easily collects the thermal stresses which result from it.
  • the means for adjusting the temperature of the annular support are easily controlled, according to the present invention, in particular when they include a circulation of cooling air, coming from the compressor of the turbomachine, for example by automatically controlling the flow rate of the cooling air of said annular support, so that, at all operating modes of the turbine, that is to say both in permanent mode and in various transient modes, the ring of material abradable ceramic is always subjected to an axipetal compression, produced by the annular support, which thus plays the role of a hoop.
  • the particular structure of the turbine ring according to the present invention also offers the following additional advantage: the internal diameter of the abradable ring is adjusted using the means for adjusting the temperature of the annular support, that is to say ie by varying the corresponding cooling air flow and the adjustment of the gap between the ring and the ends of the blades of the corresponding rotor of the turbine is the consequence.
  • the axipetal compression is transmitted by the annular support to the abradable ring, by means of elements with low thermal conduction, with reduced cross section; these elements consist of radial projections from one of the surfaces, facing one another, the annular support and the abradable ring.
  • its annular support can be fitted with gentle friction between two radial flanges, fixed to the internal wall of the turbine casing, and means, comprising pins cooperating with slides, are provided for immobilizing axially and in rotation, and for radially guiding said annular support while maintaining its centering, when the annular support expands or contracts.
  • This arrangement is particularly advantageous insofar as it makes it possible to vary the internal diameter of the abradable ring, and, consequently, its interval with the ends of the rotor blades, between wide limits, for example by varying the flow rate. cooling air, without the geometric position of the ring, relative to the corresponding rotor, ceasing to be defined with the precision necessary to keep said ring and said rotor coaxial.
  • FIG. 1 a part of the casing of a gas turbine has been designated by 1, and by 2A and 2B, two radial flanges, which are fixed to the internal wall of the casing 1 by any suitable means, for example by bolts 3A and 3B. Between the flanges 2A and 2B is mounted a turbine ring 1a. 4 designates the end of a blade of a rotor of the gas turbine under consideration, the other elements of which have not been illustrated.
  • This rotor is surrounded by a one-piece ring, 5, which is made of an abradable ceramic material, which must be chosen as follows: it must withstand temperatures at least equal to 1000 ° C and present conduction and expansion coefficients, lower than those of the materials constituting the other parts of the turbine; it must also have good resistance to erosion under the action of gases at high temperature and be abradable. Different types of abradable ceramic materials are known which meet these requirements and which can be used to form the ring 5 according to the present invention.
  • the outer cylindrical surface of the abradable ring 5 is smooth, and it is in direct contact with the inner surface of a metallic annular support 6, which can be constituted for example by two annular parts , 6a and 6b.
  • the internal part, 6b, of the annular support 6, is in contact with the cylindrical external surface, 5a, of the abradable ring 5, not by a cylindrical surface, but by kinds of pins 6c, whose sum of the cross sections - perpendicular to the axial plane of the figure - is notably less than the area of the external surface 5a of the abradable ring 5.
  • These pins 6c which form radial projections on the internal surface of the metal support 6, facing the outer surface 5a of the abradable ring 5, constitute elements with low thermal conduction, reducing heat exchanges between components 5 and 6.
  • the annular support 6 has, when cold, an inside diameter slightly less than the outside diameter of the abradable ring 5, and it must be previously heated in order to be able to be threaded over the abradable ring 5, which remains cold ; while cooling, the annular support 6 exerts an axipetal compression on the abradable ring 5, like a hoop.
  • the assembly is initially dimensioned taking into account the temperatures at which the parts 5 and 6 are brought to the different speeds, permanent and transient, of the gas turbine, so that the hooping of the ring 5 by the annular support 6, subsists at all the operating regimes of said turbine, that is to say that, both in steady state and in various transient regimes, the annular support 6 does not cease to exert an axipetal compression on the abradable ring 5.
  • an annular distribution chamber, 7, is delimited by the casing 1 of the turbine and by the walls of an annular channel 6d, arranged in the annular support 6, so as to open on its outer surface; cooling air, brought from the compressor - not shown - from the turbine by known means, also not shown, enters the distribution chamber 7 through an opening 8 of the casing 1.
  • cavities, 9a, 9b which communicate with each other by a duct 10, and which are supplied with cooling air, from the distribution chamber 7, by channels 11, closed section, arranged in the annular support 6.
  • this can be formed, as already indicated, by two annular elements, 6a and 6b, the cylindrical connection surface of which passes through the cavities 9a, 9b and through the channel 10; it is therefore in the innermost part, 6B, that the pins 6c are arranged, as well as at least one lug 6e, which engages in a notch of complementary shape of one of the edges of the ring abradable 5, to immobilize the two parts 5 and 6 in rotation relative to each other.
  • the cooling air which has passed through the cavities 9a and 9b, then escapes through exhaust ducts 12, an annular collecting chamber 13 and an opening 14 of the casing 1, to be returned to the secondary flow of the turbine. , or reused for other ventilation (for example BP distributor).
  • the annular support 6 is recessed with gentle friction between the two radial flanges 2A and 2B, which are fixed to the internal wall of the casing 1 of the turbine.
  • at least three slides 15 are arranged in the flange 2A to each radially guide a pin 16, fixed to the corresponding front surface of the annular support 6; similarly, at least three slides 17 are arranged in the left part of the annular support 6, and a pin 18, of corresponding diameter, is fixed to the corresponding surface of the flange 2B and engaged in each slide.
  • the displacements of the annular support 6, and of the abradable ring 5, relative to the flanges 2A and 2B, which are due to expansions or contractions of the parts 5 and 6, are guided radially by the cooperation of the pins such as 16 and 18, with the slides such as 15 and 17, so as to keep the rings 5 and 6 exactly coaxial with the corresponding rotor of the turbine; this is essential for the interval e between the inner, cylindrical surface of the abradable ring 5, on the one hand, and the cylindrical surface swept by the ends of the blades 4 of the turbine rotor, on the other hand, has the same width, appropriate, at all points, both in the axial direction and in the peripheral direction.
  • annular seal 19 is mounted in an annular housing of the flange 2A, to seal between it and the corresponding face of the annular support 6, despite the relative displacements of these two elements in the radial direction.
  • Another annular seal, 20, seals between the cooling air distribution chamber 7, and the collecting chamber 13; this seal 20 is housed in an annular groove of a radial projection 21, arranged on the internal face of the casing 1, opposite a radial projection, 6f, which forms one of the side walls of the channel 6d.
  • the inner surface of the abradable ring 5, facing the ends of the blades 4 of the rotor, is brought for example to a temperature of the order of 1200 ° C; as no means for cooling the abradable ring 5 is provided according to the present invention, its outer surface 5a is then at a temperature in the region of 900 ° C., so that said abradable ring 5 is only subjected to a relatively low thermal gradient, which can generate therein only thermal stresses insufficient to harm the cohesion of the ceramic material which constitutes it.
  • the present invention is not limited to the embodiment described above.
  • the means for axially guiding the radial displacements of the annular support 6, due to its expansions or to its contractions, are capable of various embodiments, different from that previously described.
  • the constitution of the annular support cooling circuit is optional.
  • the number and arrangement of cavities such as 9a and 9b may vary; they are however preferably arranged so as to constitute one or more thermal barriers in the vicinity of the inner surface of the annular support 6.
  • the pins 6c could be in contact with similar pins, arranged in the outer surface of the abradable ring 5; other means could be used to reduce the thermal conduction between parts 5 and 6, for example the interposition of thermal insulators.
  • the pins such as 6c could themselves receive external thermal protection, for example in the form of a projection of magnesium zirconate.
  • Ventilation is provided on the metal / ceramic interface if its temperature exceeds the admissible limit for the material of the hoop.
  • An embodiment of this arrangement is shown in FIG. 2 and in this case the effect of punching the ceramic by the pins is avoided, while ensuring an effective thermal barrier.
  • a conical wall 21, the seal with the ring 1a is ensured by means of a seal 22 is arranged upstream of said ring 1a and channels ventilation air.
  • the radially internal part of the internal part 6b of the annular support 6 comprises a series of circular grooves 23 constituting annular cavities arranged axially and closed on their internal diameter by a ring 24 of small thickness added for example by brazing on the annular support 6.
  • the grooves 23 communicate by axial milling 25.
  • the annular support 6 has on its upstream side face a series of holes 26 through which the ventilation air is brought into the circuit of the grooves 23.
  • a passage 27 is provided at the interface between the annular support 6 and the ring 5 on the downstream side for the evacuation of the air having circulated in the grooves 23.

Claims (6)

1. Anstreifring für eine Gasturbine mit einem im Innern des Turbinengehäuses (1) montierten ringförmigen Träger (6), mit einem einstückigen Ring (5) aus verschleißbarem Keramikmaterial, der innerhalb des genannten ringförmigen Trägers (6) montiert und so bemessen ist, daß letzterer zumindest im kalten Zustand auf den Ring (5) eine axipetale Kompression ausübt, sowie mit Mitteln zur Regelung der Temperatur der Bestandteile des Anstreifrings, dadurch gekennzeichnet, daß der Innendurchmesser des Anstreifrings (1a) mit Hilfe der Mittel zur Regelung der Temperatur einzig des aus Metall bestehenden ringförmigen Trägers (6) derart justiert ist, daß der ringförmige Träger (6) in allen Betriebszuständen unter Berücksichtigung der Temperatur der Teile von der Anfangsmontage an, bei der der genannte Ring (5) auf den ringförmigen Träger (6) unter Vorspannung aufgebracht wird, auf den verschleißbaren Ring (5) eine geeignete axipetale Kompression ausübt.
2. Anstreifring nach Anspruch 1, dadurch gekennzeichnet, daß die Mittel zur Regelung der Temperatur eine Zirkulation von aus dem Verdichter der Turbine stammender Kühlluft umfassen.
3. Anstreifring nach einen der Ansprüche 1 oder 2, dadurch gekennzeichnet, daß die axipetale Kompression von dem ringförmigen Träger (6) über Elemente mit schwacher Wärmeleitung auf den verschleißbaren Ring (5) übertragen wird, wobei diese Elemente einen verringerten Querschnitt aufweisen und aus radialen Vorsprüngen (6c) an einer der einander zugewandten Oberflächen des ringförmigen Trägers (6) oder des verschleißbaren Rings (5) bestehen.
4. Anstreifring nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, daß nur in dem ringförmigen Träger (6) ein Kühlluftkreis vorgesehen ist, der eine ringförmige Verteilerkammer (7) umfaßt, die von dem Turbinengehäuse (1) und einem in dem ringförmigen Träger (6) ausgebildeten ringförmigen Kanal (6d) begrenzt ist, der sich in dessen Außenfläche öffnet, wobei in dem ringförmigen Träger (6) in der Nähe seiner Innenfläche Hohlräume (9a, 9b) vorgesehen sind, sowie Bohrungen (11), die diese Hohlräume (9a, 9b) mit der genannten Verteilerkammer (7) verbinden, und daß wenigstens eine Leitung (12) vorgesehen ist, über die die Luft aus den genannten Hohlräumen (9a, 9b) abführbar ist.
5. Anstreifring nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, daß der ringförmige Träger (6) mit weicher Reibung zwischen zwei radialen Flanschen (2A. 28) eingepaßt ist, die an der Innenwandung des Turbinengehäuses (1) befestigt sind, und daß Mittel vorgesehen sind. die mit Gleitbahnen (15. 17) zusammenwirkende Zapfen (16, 18) umfassen, die den ringförmigen Träger (6) unter Beibehaltung seiner Zentrierung axial und gegen Drehung festlegen und/oder radial führen, wenn er (6) sich ausdehnt oder zusammenzieht.
6. Anstreifring nach einem der Ansprüche 1 oder 2, dadurch gekennzeichnet, daß der ringförmige Träger (6) längs seiner Grenzfläche zu dem verschleißbaren Ring (5) in axialer Richtung verteilte ringförmige Hohlräume aufweist, die aus kreisförmigen Nuten (23) bestehen, die über axiale Fräsnuten (25) miteinander in Verbindung stehen und an ihrem Innendurchmesser von einem eingesetzten Kranz (24) geringer Dicke verschlossen sind, daß in dem stromaufwärtigen Teil des ringförmigen Trägers (6) Bohrungen angebracht sind, die seitlich münden und Ventilationsluft in die Nuten (23) führen, und daß stromabwärts ein Durchgang (27) zur Wegführung der Luft angebracht ist.
EP85402243A 1984-11-22 1985-11-20 Anstreifring für eine Gasturbine Expired EP0182716B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8417775 1984-11-22
FR8417775A FR2574473B1 (fr) 1984-11-22 1984-11-22 Anneau de turbine pour une turbomachine a gaz

Publications (2)

Publication Number Publication Date
EP0182716A1 EP0182716A1 (de) 1986-05-28
EP0182716B1 true EP0182716B1 (de) 1988-07-27

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US (1) US4679981A (de)
EP (1) EP0182716B1 (de)
JP (1) JPS61135905A (de)
DE (1) DE3564006D1 (de)
FR (1) FR2574473B1 (de)

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Publication number Publication date
US4679981A (en) 1987-07-14
JPS61135905A (ja) 1986-06-23
FR2574473A1 (fr) 1986-06-13
JPH0373723B2 (de) 1991-11-22
DE3564006D1 (en) 1988-09-01
FR2574473B1 (fr) 1987-03-20
EP0182716A1 (de) 1986-05-28

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