EP0192556B1 - Turbinengehäuse mit einer Einrichtung, um den Abstand zwischen den Schaufelspitzen und dem Gehäuse einzustellen - Google Patents

Turbinengehäuse mit einer Einrichtung, um den Abstand zwischen den Schaufelspitzen und dem Gehäuse einzustellen Download PDF

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Publication number
EP0192556B1
EP0192556B1 EP86400286A EP86400286A EP0192556B1 EP 0192556 B1 EP0192556 B1 EP 0192556B1 EP 86400286 A EP86400286 A EP 86400286A EP 86400286 A EP86400286 A EP 86400286A EP 0192556 B1 EP0192556 B1 EP 0192556B1
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EP
European Patent Office
Prior art keywords
casing
segments
wall
turbo
clearance
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
EP86400286A
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English (en)
French (fr)
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EP0192556A1 (de
Inventor
Jean-Paul Lagrange
Jean-Max Marie Silhouette
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
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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 EP0192556A1 publication Critical patent/EP0192556A1/de
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Publication of EP0192556B1 publication Critical patent/EP0192556B1/de
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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
    • 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
    • F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion

Definitions

  • the invention relates to a tubormachine casing associated with a device enabling the clearance between said casing and the moving blades of a rotor to be adjusted in operation, automatically.
  • FR-A-2 540 560 describes a sealing device formed by sectors supported by hook elements integral with elastic tongues linked to a ferrule in two parts and supported by hooks fixed to an outer ring having a thermal inertia greater than that of the ferrule so that under the influence of the ventilation air distributed to the device, the sectors during a first transient phase are subjected to a first servo in a radial position to the ferrule and during a second stabilization phase to a second servo to the outer ring .
  • FR-A-2 164 215 describes a stator screen ring comprising at least two parts assembled end to end with chosen linear expansion coefficients and with length used for each such that a predetermined effective linear expansion coefficient is obtained at operating temperatures.
  • a turbomachine casing associated with a device for adjusting the clearance between movable blades and casing according to the invention is remarkable in that said casing is internally lined with a rigid annular wall connected to the casing by connecting means which allow said wall completely free to move in the radial direction according to the expansions / contractions in operation and in that said wall consists of a succession of integral segments in the circumferential direction, each segment being alternately of a type with low thermal inertia and of a type with high thermal inertia so that the radial displacements of said wall adapt in all operating conditions of the turbomachine to the radial displacements of the moving blade heads.
  • the inner wall segments with low thermal inertia are thin, their internal surface is directly in contact with the gases of the vein flowing through the movable blade stage considered, their external and lateral surfaces are coated with a thermally insulating material and the adjacent inner wall segments with high thermal inertia are very thick and coated on all their surfaces with a thermally insulating material.
  • the temperature T of the hot engine gases which pass through a grid of blades such as 1 creates a flow of heat which, passing through the blades, spreads as far as the disk which carries them and causes a radial expansion of the assembly therefore a displacement of the blade heads 1.
  • the radius of gyration R of the blade heads follows a law which can be represented by the relation: linking R to R o , gyratory radius of the blade heads at T o , ambient temperature on the ground, K, being the coefficient of thermal radial expansion of the rotor.
  • each grid of movable blades such as 1 can however be characterized fairly precisely by means of four parameters.
  • the speed of rotation N of the rotor creates a centrifugal force which acts on the whole of the rotor and causes another radial displacement of the blade heads 1.
  • K 2 being the coefficient of centrifugal radial expansion of the rotor.
  • T of the hot engine gases at a given point in the stream is a function of the speed of rotation N of the rotor: where K 3 is the coefficient of proportionality between T and N 2 .
  • radius of gyration R of the movable blades 1 is linked to the temperature of the hot engine gases, at a given point in the vein, by a relationship of simultaneity
  • the evolution of the temperature T of the engine gases is influenced by the fact that the evolution of the speed N is due to a momentary excess or deficit of the flow rate of burned fuel in the combustion chamber in relation to the flow required in stabilized operation.
  • LlTc is the temperature difference due to the excess or deficit of fuel burned
  • T N is the temperature that the turbine gases would have if the speed N were stabilized.
  • the temperature difference il Tc intervenes directly in the evolution of the radius of gyration R due to the temperature T as before.
  • its duration is at most equal to that of the speed transient N, ie 5 to 10 seconds maximum for a simple evolution. Its influence is therefore only appreciable on the expansion of the movable blades 1, that is to say, in the case of a “unitary step” of temperature as above, in connection only with the gain K 1 ' and the time constant 0 '.
  • FIG. 1 represents, in transverse section with respect to the axis of rotation of the turbomachine, a simplified view of an embodiment of the invention.
  • a turbomachine Facing the movable blade heads 1, there is a fixed part of a turbomachine constituted by a stator casing 2 which in the example shown is in two parts 2a, 2b, each having a generally semi-cylindrical shape.
  • Each part, respectively 2a and 2b, carries at its ends flanges, respectively 3a and 4a, 3b and 4b which are assembled by any known means, such as bolting.
  • the casing 2 is internally lined with a rigid wall 5, which in the example shown is also in two parts 5a and 5b.
  • This inner wall 5 consists of a succession of integral segments 6 which are of two different types 6a and 6b, more clearly shown in Figure 2, and arranged alternately.
  • a segment such as 6a is thin, its internal surface 6i is directly in contact with the gases of the vein circulating in the stage of movable blades 1 and its external and lateral surfaces are coated with a layer 7a of a material thermally insulating.
  • These segments 6a of the inner wall 5 therefore very quickly take the temperature of the gases of the vein.
  • An adjacent segment such as 6b is very thick and all of its surfaces are coated with a layer 7b of a thermally insulating material.
  • segments 6b of the inner wall 5 thus have a high thermal inertia and their thermal connection with the outside takes place almost only through their junctions with the adjacent segments 6a. They therefore take the temperature of the vein gases very slowly.
  • the insulating layers 7a and 7b are flexible enough to follow all the thermal expansions / contractions of the interior wall 5.
  • the segments 6a and 6b are in sufficient number so that the initially circular shape of the annular wall is sufficiently well preserved during the expansions / thermal contractions occurring during the operation of the turbomachine.
  • the internal surface of the interior wall 5, both for the segments 6a and for the adjacent segments 6b, can be covered with a layer 8 of abradable material constituting a wear and seal lining susceptible during operation to come into contact with the ends of movable blades 1 without causing damage.
  • This material is determined so as not to create a thermal barrier between the internal surface 6i of the segments 6a of the internal wall 5 and the gases of the vein and not to slow down the thermal expansions / contractions of the internal wall 5.
  • Each part, respectively 5a and 5b, of the inner wall 5 is fixed inside the corresponding part of the casing 2, respectively 2a and 2b, by means of connecting rods 9.
  • a yoke 10 is fixed, for example by screwing, on at least some of the segments 6b of the inner wall 5, at a 7th end of these segments in a radially external zone.
  • a yoke 11 is also fixed, for example by screwing, on the internal surface of the casing 2, in a position circumferentially offset with respect to the associated yoke 10.
  • Each link 9 is provided at its ends with yokes, respectively 9a and 9b which cooperate by means of axes of rotation 10a and 11a with said yokes 10 and 11.
  • links 9 are thus placed in a direction substantially tangential to the inner wall 5 and thus leave the wall 5 free to move radially under the influence of thermal expansion / contraction.
  • an access hole 5c can be made in the interior wall 5, preferably at the level of a thin segment 6a.
  • each end of the inner wall part, respectively 5a and 5b comprises a half-segment respectively 6c or 6d of the very thick type. As shown in more detail in FIGS. 3, 3a and 3b, these half-segments 6c and 6d are joined by their respective end faces by means, for example, of a bolt 12.
  • each of these faces comprises by example a tenon 13 and a mortise 14 arranged in two perpendicular directions and cooperating respectively with a mortise 14a and a tenon 13a of the face of the associated half-segment to very precisely join the two parts 5a and 5b of the inner wall 5.
  • a passage access 15 is provided through the casing 2 to allow the establishment of the bolting 12.
  • the internal wall 5 is placed in a housing constituted by an annular recess 16 formed on the internal face of the casing 2. Under the action of the pressure P of the gases, the internal wall 5 is thus pressed against laterally on the surface 16a of the recess 16 where the pressure P is the lowest.
  • the corresponding lateral surface of the wall 5 is coated with a layer 7b of thermally insulating material, as previously described, which in this zone prevents gas leaks, reduces contact friction and reduces heat exchange between the interior wall 5 e the casing 2.
  • the solution proposed by the invention consists in producing a "thermal model" of the rotor on the stator.
  • an inner wall 5 is produced which, in transient as well as in stabilized regimes, very precisely follows the radial movements of the blades of the rotor, and this by the only thermal effect on this inner wall 5 hot gases that lick it. Because this interior wall 5 is a complete circumference, any peripheral expansion results in a radial expansion of the interior wall 5. This is the principle used.
  • FIG. 5 Certain possible adaptations are shown in FIG. 5 for a segment 106b equivalent to a segment 6b.
  • segments 206b with high thermal inertia radially spaced apart towards the outside.
  • the adjacent segments 206a with low thermal inertia each extend respectively by a part 25.
  • These parts 25 remain without influence on the changes in diameter of the inner wall 5 because they are separated by a slot 26 which can have different shapes , as shown in Figures 6a, straight 6b, oblique, or 6c, bayonet.
  • the ends of the parts 25 are covered by a part 27 which covers the slot 26.
  • each element 105 of internal wall 5 is terminated by two half-segments 306c and 306d of the type with high thermal inertia to facilitate the attachment of the elements to each other.
  • the attachment of the elements to each other can for example be carried out as described above between the two parts 5a and 5b of the inner wall 5, with reference to FIGS. 3, 3a and 3b.
  • the rigidity of the interior wall 5 may be insufficient despite its pressing on a lateral surface 16a of the recess 16 of the casing 2 (see FIG. 4).
  • Figure 8a. are placed on the upstream and downstream lateral edges of the segments 406a of the inner wall 5, two ribs 19 that are thin enough to maintain the thermal performance of the two types of segment. The requested lateral tightness can then be produced on one of these ribs, coming to bear on the lateral surface 16a of the recess 16 of the casing 2 (see FIG. 4).
  • FIG. 8b it is possible, as an alternative, to provide on each lateral edge of a thin segment 506a stiffening elements 20 and 21 attached and fixed to the external wall of the segments 506a.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (10)

1. Gehäuse für ein Turboluftstrahltriebwerk mit einer Vorrichtung zur Einstellung des Spiels zwischen beweglichen Schaufeln und Gehäuse, wobei das Gehäuse (2) doppelwandig ausgeführt ist und innen eine ringförmige feste Wand (5) besitzt, die aus einer Folge von Segmenten (6a, 6b) besteht, die in Umfangsrichtung fest miteinander verbunden sind und nur dem Einfluss der Heizluft des Turboluftstrahltriebwerks ausgesetzt sind, die die Stufe der beweglichen Schaufeln durchströmt, dadurch gekennzeichnet, dass die genannte Wand (5) mit dem Gehäuse (2) über Verbindungsmittel (9 bis 11) verbunden ist, die der Wand (5) jede Bewegungsfreiheit in radialer Richtung entsprechend den im Betrieb auftretenden Ausdehnungen/Kontraktionen belassen, und dass die einzelnen Segmente abwechselnd niedrige und hohe thermische Trägheit haben, derart, dass die radialen Bewegungen der Wand (5) automatisch in allen Betriebszuständen des Turboluftstrahltriebwerks dieselben sind wie diejenigen der Köpfe der beweglichen Schaufeln (1).
2. Gehäuse für ein l'urboluftstrahltriebwerk mit einer Vorrichtung zur Einstellung des Spiels zwischen beweglichen Schaufeln und Gehäuse nach Anspruch 1, dadurch gekennzeichnet, dass die Segmente (6a) der inneren Wand (5) mit niedriger thermischer Trägheit eine geringe Wandstärke haben, dass ihre Innenfläche direkt mit den Gasen der durch die jeweilige Stufe der beweglichen Schaufeln (1 ) zirkulierenden Strömung in Kontakt ist und ihre Aussen- und Seitenflächen mit einem wärmeisolierenden Werkstoff (7a) beschichtet sind, und dass die benachbarten Segmente (6b) der inneren Wand (5) mit hoher thermischer Trägheit grosse Wandstärke haben und auf allen Flächen mit einem wärmeisolierenden Werkstoff (7b) beschichtet und mechanisch und thermisch über eine kleine Fläche mit den benachbarten Segmenten (6a) verbunden sind.
3. Gehäuse für ein Turboluftstrahltriebwerk mit einer Vorrichtung zur Einstellung des Spiels zwischen beweglichen Schaufeln und Gehäuse nach einem der Ansprüche 1 und 2, dadurch gekennzeichnet, dass die innere Wand (5) an der Innenseite des Gehäuses (2) mit Hilfe von in tangentialer Richtung angeordneten Halterungs- Pleuelhebeln (9) befestigt ist, die mit einem Ende (9b) im Innern des Gehäuses und mit dem anderen Ende (9a) zumindest an einigen der Segmente (6a) der inneren Wand (5) mit hoher thermischer Trägheit oder grosser Wandstärke befestigt sind.
4. Gehäuse für ein Turboluftstrahltriebwerk mit einer Vorrichtung zur Einstellung des Spiels zwischen beweglichen Schaufeln und Gehäuse nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass das Gehäuse (2) aus zwei halbzylindrischen Teilen (2a, 2b) besteht, die mit Schraubenbolzen zusammengefügt sind, und dass die innere Wand (5) aus wenigstens zwei Teilen (5a, 5b) besteht, wobei die Verbindung zwischen den beiden Teilen (5a, 5b) zwischen zwei Halbsegmenten (6c, 6d) mit hoher thermischer Trägheit oder grosser Wandstärke erfolgt, deren Kontaktflächen zusammenarbeitende Zentrierzapfen und -zapfenlöcher (13, 13a, 14, 14a) aufweisen und die durch Schraubenbolzen (12) zusammengefügt sind.
5. Gehäuse für ein Turboluftstrahltriebwerk mit einer Vorrichtung zur Einstellung des Spiels zwischen beweglichen Schaufeln und Gehäuse nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die innere Wand (5) in einer Aufnahme angeordnet ist, die von einer ringförmigen Ausnehmung (16) in der Innenseite des Gehäuses (2) gebildet ist, und dass wenigstens eine der Seitenflächen der Wand (5), die sich gegen die korrespondierende Fläche (16a) der Ausnehmung (16) legen kann, mit einer eine Dichtung bildenden Schicht (7b) aus wärmeisolierendem Werkstoff versehen ist.
6. Gehäuse für ein Turboluftstrahltriebwerk mit einer Vorrichtung zur Einstellung des Spiels zwischen beweglichen Schaufeln und Gehäuse nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die radial innen liegende Fläche der inneren Wand (5) mit einer Schicht (8) aus abtragbarem Werkstoff versehen ist, die einen Verschleiss- und Dichtungsbelag bildet.
7. Gehäuse für ein Turboluftstrahltriebwerk mit einer Vorrichtung zur Einstellung des Spiels zwischen beweglichen Schaufeln und Gehäuse nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die in die innere Wand (5) eindringenden Segmente (206a) mit geringer thermischer Trägheit oder kleiner Wandstärke an ihren, bezogen auf die axiale Gaszirkulationsrichtung des Turboluftstrahltriebwerkes, stromaufwärtigen bzw. stromabwärtigen seitlichen Rändern Verstärkungselemente besitzen, die beispielsweise von Rippen (19) gebildet sind.
8. Gehäuse für ein Turboluftstrahltriebwerk mit einer Vorrichtung zur Einstellung des Spiels zwischen beweglichen Schaufeln und Gehäuse nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Segmente (106b) mit hoher thermischer Trägheit oder grosser Wandstärke der inneren Wand (5) innere Unterteilungen (24), hammerartige Endbereiche (22), nicht von wärmeisolierendem Werkstoff bedeckte Zonen (17) und Rippen (18) zur Energieabgabe besitzen, und dass die Verbindungen (23) zwischen diesen Segmenten (106b) und den ihnen benachbarten Segmenten (6a) mit kleiner Wandstärke eng und lang ausgebildet sind.
9. Gehäuse für ein Turboluftstrahltriebwerk mit einer Vorrichtung zur Einstellung des Spiels zwischen beweglichen Schaufeln und Gehäuse nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Segmente (206b) mit hoher thermischer Trägheit oder grosser Wandstärke der inneren Wand (5) in radialer Richtung von den Enden der beweglichen Schaufeln (1) Abstand haben und dass der stetige Verlauf der Innenfläche der Wand (5) durch Teile (25) von Segmenten (406a) mit geringer thermischer Trägheit oder kleiner Wandstärke gegeben ist, die durch einen in der Mitte liegenden Spalt (26) voneinander getrennt sind.
10. Gehäuse für ein Turboluftstrahltriebwerk mit einer Vorrichtung zur Einstellung des Spiels zwischen beweglichen Schaufeln und Gehäuse nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass die Segmente (6a) mit geringer thermischer Trägheit oder kleiner Wandstärke der inneren Wand (5) ein Loch (5c) haben, das einen Zugang für die Befestigung der Halterungs-Pleuelhebel (9) an dem Gehäuse (2) ermöglicht.
EP86400286A 1985-02-13 1986-02-11 Turbinengehäuse mit einer Einrichtung, um den Abstand zwischen den Schaufelspitzen und dem Gehäuse einzustellen Expired EP0192556B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8502022A FR2577281B1 (fr) 1985-02-13 1985-02-13 Carter de turbomachine associe a un dispositif pour ajuster le jeu entre aubes mobiles et carter
FR8502022 1985-02-13

Publications (2)

Publication Number Publication Date
EP0192556A1 EP0192556A1 (de) 1986-08-27
EP0192556B1 true EP0192556B1 (de) 1989-05-24

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EP86400286A Expired EP0192556B1 (de) 1985-02-13 1986-02-11 Turbinengehäuse mit einer Einrichtung, um den Abstand zwischen den Schaufelspitzen und dem Gehäuse einzustellen

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US (1) US4787817A (de)
EP (1) EP0192556B1 (de)
JP (1) JPS61190101A (de)
DE (1) DE3663556D1 (de)
FR (1) FR2577281B1 (de)

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CN112855352B (zh) * 2019-11-28 2022-03-22 中国航发商用航空发动机有限责任公司 高压涡轮实时叶尖间隙的计算方法和控制方法

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JPS61190101A (ja) 1986-08-23
JPH0319883B2 (de) 1991-03-18
FR2577281A1 (fr) 1986-08-14
EP0192556A1 (de) 1986-08-27
FR2577281B1 (fr) 1987-03-20
US4787817A (en) 1988-11-29
DE3663556D1 (en) 1989-06-29

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