EP0263002B1 - Dichtungs- und Sicherungsring für die Schaufeln einer Turbomaschine - Google Patents

Dichtungs- und Sicherungsring für die Schaufeln einer Turbomaschine Download PDF

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Publication number
EP0263002B1
EP0263002B1 EP87401958A EP87401958A EP0263002B1 EP 0263002 B1 EP0263002 B1 EP 0263002B1 EP 87401958 A EP87401958 A EP 87401958A EP 87401958 A EP87401958 A EP 87401958A EP 0263002 B1 EP0263002 B1 EP 0263002B1
Authority
EP
European Patent Office
Prior art keywords
disc
segment
blades
blade
throat
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 - Lifetime
Application number
EP87401958A
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English (en)
French (fr)
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EP0263002A1 (de
Inventor
Jean-Louis Bertrand
Jacky Naudet
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 EP0263002A1 publication Critical patent/EP0263002A1/de
Application granted granted Critical
Publication of EP0263002B1 publication Critical patent/EP0263002B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • 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
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor

Definitions

  • the present invention relates to turbomachine rotors and more particularly to the means for axially locking vanes mounted in axial pinouts of the periphery of the disc.
  • a first problem consists in ensuring the axial locking of each of the blades in the simplest possible but also the safest way possible and so that the easy disassembly of a blade or of the entire stage is also simplified.
  • the second problem is that of the seal between the upstream and the downstream of a disc and arises crucially in the compressors of the turbomachines. Indeed, if the spaces located between the bottom of the disc cavities and the blade roots are not properly masked, large volumes of downstream air can pass under the blade roots and recirculate upstream of the compressor , which decreases the compression ratio thereof and causes the overall efficiency of the turbomachine to drop prohibitively.
  • the pinned blades are locked axially, on one side by a spoiler at the foot of the blade, which ensures locking in one direction, and on the other side by a split elastic segment which is clamped during assembly. to reduce its diameter and introduce it into the bore formed by the teeth of the disc in order to then allow it to relax inside an annular groove formed in the teeth of the disc and in the feet of the blades.
  • the segment is notched so as to enter jointly into a circular slot of the disc and into slots of the spoilers of the blades, then is turned by a half-step so that the full part of the segment comes to lock in said slots. If it provides locking, such a segment has the disadvantage of poorly sealing at the feet of the blades.
  • the object of the invention is to remedy the aforementioned problems by means of a simple device comprising a very small number of parts which simultaneously ensure sealing at the level of the blade roots and the axial locking of the blades on the disc.
  • Another object is to provide a device adaptable to rotor discs of compressors or small diameter turbines such as those existing in aircraft turbomachines such as turbojet engines, turbojet engines with non-faired counter-rotating propellers, called propane, or faired, or in other aviation turbomachines.
  • the subject of the invention is therefore a turbomachine rotor, in particular for an aviation turbomachine comprising at least one disc carrying a set of vanes, the feet of which are mounted in stapled cells on the periphery of the disc along a parallel or slightly inclined axis. relative to a parallel to the longitudinal axis of the engine, the blade roots comprising a means of wedging the blades on the upstream face of the disc and a rear spoiler having a transverse groove radially oriented towards the axis of the disc while the disc has a circular groove radially oriented towards its periphery.
  • the rotor comprises a means of axial locking downstream of the blades on the disc, simultaneously ensuring sealing between the blade roots and the bottom of the cells of the disc, said means for locking downstream of the blades on the disc being constituted by two split segments, the first of which at least cooperates simultaneously with the grooves of the spoilers of the blades and the circular groove of the disc, the first segment having a rectangular notch on its radially external part and the second segment inserted by radial compression having a radial width at least equal to that "1" of the notch of the first segment.
  • Figure 1 are shown by way of example in longitudinal section the first two stages of a high pressure compressor rotor of a turbojet engine.
  • the first stage of the rotor comprises a disc 1 connected by an upstream flange 2 to a medium or low pressure compressor and by a downstream flange 3 from the second stage of the rotor, generally referenced 4, of the HP compressor.
  • Blades 5 having under their platform 6 a foot 7 are slid axially in cells 8 of the disc in a conventional manner.
  • Figure 1 shows that the longitudinal axis of the cells is here slightly inclined relative to a parallel to the longitudinal axis 9 of the engine in a radial plane and this axis could also be slightly inclined relative to the axis 9 in a plane tangential to the periphery of the disc 1.
  • the blade roots 7 have upstream an axial wedging means formed by an upstream spoiler 10 radially oriented towards the axis of symmetry 9, said spoiler coming to bear against the upstream face 11 of the disc 1.
  • the blade also has downstream a spoiler 12 defining between it and the blade root a circular groove 13 whose opening is radially oriented towards the axis of symmetry of the disc.
  • the disc 1 Facing this groove 13 of the blade set up, the disc 1 has a circular groove 14 facing it, that is to say having its opening oriented radially towards the periphery of the disc and machined to a diameter smaller than the diameter machining the bottom of the cells 8.
  • the blade locking and sealing device comprises a first split segment 15 whose radial width "1" is equal to the distance separating the bottoms of the grooves 12 from the blade spoilers and 14 from the disc.
  • the first segment 15 can undergo a slight radial deformation as well as an axial deformation so that the slats of the slot are no longer in the plane containing the segment and when the segment is in this deformed position, it can be put in place in the groove 14 by introducing one of its ends into the groove and then "screwing" circular.
  • the segment 15 completely masks the downstream openings of the cells 8.
  • the segment 15 has a rectangular notch 16 allowing the passage of the downstream spoiler 12 of a blade until the upstream spoiler 10 comes into abutment on the upstream face of the disc.
  • the segment 15 is engaged in the groove 13 of the already mounted blade and the notch 16 is brought in front of the cell 8 of the next blade to be put in place.
  • the same mounting operation is carried out successively for each of the following blades until all the blades are completely installed.
  • the locking device also comprises a second split segment 17 dimensioned in such a way, firstly that its external diameter is equal to that of the bottom of the groove 13 of the blades, secondly that the sum of its thickness and of that of the first segment allows it to be inserted into the groove 13 downstream of the first segment 15 and thirdly that its radial height is at least equal to that "1 '" of the notch 16 of the first segment in order to hide completely this opening, once the second segment 17 in place.
  • the positioning of the second segment is carried out by radial compression, which makes it possible to slide it radially under the downstream spoilers 12 of the blades then by letting it relax to its nominal diameter, to engage it at the bottom of the groove 13.
  • the centrifugation effect of segment 17 during operation of the turbomachine ensures that the segment is held correctly in place.
  • the disassembly of the locking device is carried out by carrying out all the operations in the reverse order to what has just been described.
  • the first segment 15 completely masks the trailing lunules, which without its presence would exist between the feet of the blade 7 and the bottom of the cells 8.
  • the disc shown has on the teeth 18 separating the cells downstream also a spoiler 19 defining a groove which provides continuity between the grooves 13 of the blade spoilers.
  • these teeth 19 spoilers are no longer necessary with the device according to the invention and can be eliminated, which greatly simplifies the machining of the discs and reduces the manufacturing cost.
  • the invention provides a simple solution to the problem of interlocking padded rotor blades, which makes it applicable in particular to small motor rotors.

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

Claims (3)

1. Turbomaschinenrotor, insbesondere Rotor für ein Flugzeug-Turboluftstrahltriebwerk, mit wenigstens einer Scheibe, die einen Satz von Schaufeln trägt, deren Füße in Zellen montiert sind, die längs zur Längsachse des Triebwerks paralleler oder gegenüber dieser Parallelen leicht geneigter Achsen am Umfang der Scheibe herausgearbeitet sind, wobei die Schaufelfüße (7) wenigstens ein Mittel (10) zur Feststellung der Schaufeln an der stromaufwärtigen Seite der Scheibe (1) sowie einen stromabwärtigen Ansatz (12) mit einer radial zur Achse der Scheibe ausgerichteten transversalen Kehle (13) haben und in der Scheibe eine ringförmige Kehle (14) vorgesehen ist, die radial in Richtung auf ihre Peripherie weist, dadurch gekennzeichnet, daß ein stromabwärtig angeordnetes Mittel zur axialen Verriegelung der Schaufel an der Scheibe vorgesehen ist, das gleichzeitig die Abdichtung zwischen den Schaufelfüßen und dem Boden der Zellen (8) der Scheibe gewährleistet, wobei dieses Mittel aus zwei geschlitzten Segmenten (15, 17) besteht, von denen zumindest das erste (15) mit den Kehlen (13) der Ansätze der Schaufeln und der ringförmigen Kehle (14) der Scheibe gleichzeitig zusammenwirkt, daß das in der Kehle (14) der Scheibe angeordnete erste geschlitzte Segment (15) in seinem radial äußeren Teil eine rechteckige Aussparung (16) besitzt, die nacheinander das longitudinale Einführen der einzelnen Schaufeln (5) auf das Segment ermöglicht, daß das zweite geschlitzte Segment (17) eine radiale Elastizität besitzt, die so groß ist, daß es sich durch radiales Zusammendrücken in die von den Ansätzen (12) der Schaufeln gebildete kreisförmige Kehle (13) einführen läßt und sich in dieser Kehle ausdehnen kann, und daß die radiale Breite des zweiten Segments (17) wenigstens so groß ist wie die Breite (1') der Aussparung (16) des ersten Segments (15).
2. Turbomaschinenrotor nach Anspruch 1, bei dem der Durchmesser der ringfömigen Kehle (14) der Scheibe kleiner ist als der Bearbeitungsdurchmesser des Bodens der Zelle (8), dadurch gekennzeichnet, daß die radiale Breite (1) des ersten geschlitzten Segments (15) gleich dem Abstand ist, der die Böden der Kehlen (14, 13) der Scheibe und der Ansätze der Schaufeln voneinander trennt, und daß die Summe der Materialstärken des ersten und des zweiten Segments (15, 17) gleich der Breite der Kehlen (13) der Ansätze der Schaufeln ist.
3. Verfahren zum Montieren der Schaufeln an einer Scheibe des Rotors einer Turbomaschine nach einem der Ansprüche 1 oder 2, dadurch gekennzeichnet,
a) daß man das erste geschlitzte Segment (15) durch axiales Verformen der beiden Wangen seines Schlitzes in die Kehle (14) der stromabwärtigen Seite der Scheibe (1) einführt und das erste Segment (15) in der Kehle (14) dreht,
b) daß man die Aussparung (16) des ersten Segments (15) vor eine Zelle (8) der Scheibe (1) rührt,
c) daß man eine Schaufel (5, 7) in die Zelle (8) einführt, bis sie mit ihrem Festlegungsmittel an der Scheibe (1) zum Anschlag kommt,
d) daß man das erste Segment (15) um eine Schrittweite dreht und die nächste Schaufel (5) montiert und die Schritte (c) und (d) wiederholt, bis alle Schaufeln montiert sind, und
e) daß man das zweite Segment (17) in radialer Richtung zusammendrückt und es durch radiales Ausdehnen in der von den Ansätzen (12) zwischen dem ersten Segment (15) und dem stromabwärtigen Teil der Ansätze (12) gebildeten Kehle (13) der Schaufeln in Stellung bringt.
EP87401958A 1986-09-03 1987-09-02 Dichtungs- und Sicherungsring für die Schaufeln einer Turbomaschine Expired - Lifetime EP0263002B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8612357A FR2603333B1 (fr) 1986-09-03 1986-09-03 Rotor de turbomachine comportant un moyen de verrouillage axial et d'etancheite d'aubes montees dans des brochages axiaux du disque et procede de montage
FR8612357 1986-09-03

Publications (2)

Publication Number Publication Date
EP0263002A1 EP0263002A1 (de) 1988-04-06
EP0263002B1 true EP0263002B1 (de) 1990-04-04

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Application Number Title Priority Date Filing Date
EP87401958A Expired - Lifetime EP0263002B1 (de) 1986-09-03 1987-09-02 Dichtungs- und Sicherungsring für die Schaufeln einer Turbomaschine

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US (1) US4730983A (de)
EP (1) EP0263002B1 (de)
DE (1) DE3762142D1 (de)
FR (1) FR2603333B1 (de)

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US8459954B2 (en) * 2010-01-19 2013-06-11 United Technologies Corporation Torsional flexing energy absorbing blade lock
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US9790803B2 (en) 2013-03-08 2017-10-17 United Technologies Corporation Double split blade lock ring
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Also Published As

Publication number Publication date
US4730983A (en) 1988-03-15
FR2603333B1 (fr) 1990-07-20
DE3762142D1 (de) 1990-05-10
FR2603333A1 (fr) 1988-03-04
EP0263002A1 (de) 1988-04-06

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