EP0115984B1 - Dispositif d'étanchéité d'aubages mobiles de turbomachine - Google Patents

Dispositif d'étanchéité d'aubages mobiles de turbomachine Download PDF

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Publication number
EP0115984B1
EP0115984B1 EP84400155A EP84400155A EP0115984B1 EP 0115984 B1 EP0115984 B1 EP 0115984B1 EP 84400155 A EP84400155 A EP 84400155A EP 84400155 A EP84400155 A EP 84400155A EP 0115984 B1 EP0115984 B1 EP 0115984B1
Authority
EP
European Patent Office
Prior art keywords
sectors
downstream
upstream
turbo
inner ring
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
EP84400155A
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German (de)
English (en)
French (fr)
Other versions
EP0115984A1 (fr
Inventor
Louis François Jumelle
Marcel Robert Soligny
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 EP0115984A1 publication Critical patent/EP0115984A1/fr
Application granted granted Critical
Publication of EP0115984B1 publication Critical patent/EP0115984B1/fr
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
    • 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 turbomachine in which a movable blading sealing device makes it possible to limit in operation to their strict minimum the clearances at the blade tips.
  • blade tip should be understood to mean “radial end of the peripheral heels blades ”, when the blades have such peripheral heels.
  • the ferrule carrying the seal is monolithic, the most obvious solution to obtain both in transient and permanent conditions that this ferrule ensures, at the interior part of its seal, a radius which "follows Without delay, the variations in radius of the blade tips is, as is well known in the prior art, to supply the periphery of the ferrule with a distributor in a homogeneous manner with air taken from one or more compressor stages, said distributor having the function of sending an “adjusted” air flow at any time. This adjustment must in any case be made for the temperature of the air taken off (for example by mixing in suitable proportions of more or less hot air, coming either from different stages of the compressor, or, for at least part of ventilation air, air cooled - or heated - in an exchanger).
  • Such a distributor can obviously be designed, but would be of an extreme complication and of a fairly random reliability (a breakdown of the distributor can in certain cases produce significant damage to the whole of the turbine and / or of the shell).
  • Such a distributor must therefore be capable of a high flow rate. It would therefore be heavy, complex, and ultimately very unreliable.
  • a variant of the invention however provides for the use of a pressure reducer-regulator placed in the air sampling pipe intended for the ventilation of the sealing device, as will be described later. But it will be noted that this regulator is only intended to ensure a pressure, as the operation will be explained later while the mechanisms mentioned above must be adjusted in flow and / or temperature.
  • GB-A-1 484288 relates to a turbomachine in which a sealing device comprises a sealing ring secured to a first ring with low thermal inertia bearing radially in one direction on an axial flange carried by a second outer ring with high thermal inertia.
  • the turbomachine provided with a mobile blading sealing device of the aforementioned type is characterized according to the present invention in that said inner shroud is in two respective parts upstream and downstream, linked by fallen edges of securing tabs secured respectively to the upstream and downstream monolithic parts of the shell, said securing tabs being regularly distributed over the periphery and spaced apart, in that said sectors are supported by elements in the form of hooks integral with elastic elements constituted by elastic tongues interposed in each gap between the securing tongues and respectively linked alternately to the monolithic upstream part and to the downstream part of the inner shell and in that said elastic elements are supported by hooks fixed to said outer ring so that during said transient mechanical acceleration phase, said sectors are subjected to a first servo-control in the radial position to the inner shroud and during said thermal stabilization phase to a second servo-control in the radial position, replaces uant to the first, to the outer ring, the ventilation air being supplied by means of a multiplicity
  • the ventilation conditions of said inner shroud, its coefficient of thermal expansion ⁇ , and the air intake stage are determined so that during a mechanical acceleration phase of the turbomachine from any which speed up to a higher speed, and in particular up to the maximum load of the turbomachine, the thermal expansions of said ferrule "follow" without delay the centrifugal expansion of the disc and of the blades increased, at least in large part, by the thermal expansion of the blades.
  • the expansion coefficient a 2 , the thermal inertia and the ventilation conditions of the outer ring are determined so that during the phase - which can last several minutes - of thermal stabilization of all the elements of the turbomachine, and in particular of the corresponding disc, the thermal expansions of said ring impose on the sectors carrying the seal which are slaved to it during said phase a radial expansion which "follows" the thermal expansion of said disc.
  • the sector support hooks cooperate upstream and downstream with fallen edges of the sectors inserted in the hooks.
  • said elastic tabs enslave the sectors carrying the seal to the expansions of said first ferrule without these tabs deforming themselves during the period when the first servo is effective, and allow the servo of the sectors carrying the seal at the expansions of said second ring, by deformation of these tongues in the elastic domain during the period when the second servo replaces the first.
  • the first ferrule includes heat exchange accelerators (multiple holes traversed by ventilation air, fins, pins, etc.) so that its temperature “follows” practically without delay the temperature of the air of the compressor, the density of these exchange accelerators being determined so that the expansion of the first shell as a function of the time for an acceleration is adjusted to the centrifugal expansion of the disc and of the blades, increased by the thermal expansion of the blades, and their distribution being determined to ensure temperature uniformity at said first shell both longitudinally and peripherally.
  • heat exchange accelerators multiple holes traversed by ventilation air, fins, pins, etc.
  • the turbine casing comprises means for centering the sealing device according to the invention.
  • At least one pressure reducing valve between the air intake pipe to the compressor and a pipe opening into a hole in the turbine casing, comprising an inlet connected by a pipe to a pressure tap located in the downstream part of the external platform of a distributor placed upstream of the mobile blading so that a pressure always very slightly greater than the static pressure at the wall of the gas circulation stream of the turbo-machine is established on the radially outer side of the sectors carrying the seals.
  • This latter arrangement advantageously makes it possible to eliminate the seals provided upstream and downstream of the sectors carrying the seals and thus to eliminate friction which could in certain cases interfere with optimal operation.
  • FIG 1 in which we did not ignore gurer everything related to ventilation, we can see a turbine housing which in the example shown is in three parts, an upstream part 2, a middle part 4, a downstream part 6, the three parts being joined by bolts not shown bringing together radial flanges 8a, 8b and 8c, 8d, said radial flanges also having the role of giving mechanical inertia to the assembly so that it is practically undeformable by ovalization.
  • the upstream part 2 of the casing has a conical extension 10 inwards, in which radial grooves are machined 12.
  • the downstream part 6 of the casing has a conical extension 14 inwards, in which grooves are machined radial 16, similar to the grooves 12, but making them opposite.
  • An outer ring with high inertia 20, comprising for example ribs towards the outside 22, and which can be provided with internal insulation 24, and / or external 26, to give it a suitable response time, also comprises ribs respectively upstream 28 and downstream 30, in which are machined radial grooves 12 'and 16' which cooperate with the radial grooves 12 and 16 to center the ring 20 in the casing.
  • This ring further comprises in its upstream part of the known fixing means for a multiplicity of hooks 32 turned downstream, and in its downstream part of the equivalent fixing means of hooks 34 turned upstream (only the latter elements of attachment being shown). These hooks are used to radially move sectors 84 carrying seals 86 by pressing radially, in the centrifugal direction, directly or by means of shims on longitudinal elements carried by the sectors, as will be described in detail later.
  • the upstream part 2 of the turbine casing comprises, further upstream, a radial flange 40, towards the inside, on which is fixed in a known manner a radial flange 42 towards the outside of an internal ferrule 44 (see FIG. 2).
  • the upstream part comprises, downstream of the radial flange 42, a cylindrical part 46, and in the example shown another radial flange 48, again towards the inside, then an internal ferrule 50 intended mainly to give it inertia.
  • the inner ferrule 50 ends with a radial sealing flange 52.
  • the assembly of the upstream part of the ferrule 44, described above, is monolithic.
  • blades 56 there are regularly spaced and leaving an interval between them blades 56, terminated by an outer fallen edge 58.
  • Each of these is fixed by a bolt nut assembly 60 to a fallen edge 62 of the downstream part of the inner shell 44, this fallen edge 62 is extended by blades 64, similar to the blades 56, which connect the monolithic downstream part of the shell 44 to the upstream part.
  • This monolithic downstream part comprises, from a longitudinal position marked 54b, a cylindrical part 66, similar to the upstream cylindrical part 46 of the ferrule 44, an internal radial flange 68, extended upstream, to give this part downstream monolithic sufficient inertia, by a cylindrical ferrule 70 (similar to 50 but directed upstream), then a radial flange inward 73 (similar to the upstream flange 52), intended to ensure sealing between the sectors and the downstream part of the shell 44.
  • FIG. 3 we will explain schematically how the ventilation works which has not been shown in FIGS. 1 and 2.
  • the air taken from one of the downstream compressor stages arrives in a known manner through holes 100 drilled in the upstream part 2 of the turbine casing and regularly distributed along the periphery of this casing. This ventilation air is distributed, according to arrow A, in the enclosure 102 forming a plenum.
  • downstream part of the ring is ventilated (arrows E ') by a multiplicity of holes also marked 104 drilled in the tongues (of securing or slaving) of the downstream part, in passing, for the part right of Figure 3, around the hooks 34.
  • the ventilation air having traversed the inner ring 44 in the part opposite the sectors passes through downstream stiffeners 90 (see FIG. 1) of the sectors through holes 108 regularly distributed in the enclosure 108 ′ according to arrow F, d 'where it escapes into a downstream enclosure 118 through holes 110 drilled in the downstream monolithic part 66 of the shell 44, according to the arrows F ' .
  • the part of the air circulating between the ring 20 and the ferrule 44 also ventilates the interior of the ring 20, but with a much longer response time, due to the thermal insulation 24.
  • Another part of the ventilation air arriving in the enclosure 102 also ventilates the outside of the ring 20, following the following route: through holes 112, regularly distributed over the conical extension 10, it penetrates according to the arrow G in the enclosure 114 between median casing 4 and ring 20, the external part of this ring 20 and in particular its reinforcement ribs being suitably insulated; this part of the air escapes from the enclosure 114 by holes 116 drilled in the internal conical extension 14 of the downstream casing 6, along arrow H, and it mixes in the enclosure 118 with the ventilation air having followed the path described above (arrows D, E or E ', F, F').
  • substitution action of said second control can be done either directly by pressing the hooks on the end of the fallen edges 92 of the sectors carrying the seals, or, as shown in the accompanying drawings, by indirect support, by l 'Intermediate hooks 78, 82, respectively on the one hand downstream of the tabs 72 and turned upstream and on the other hand upstream of the tabs 74 and turned downstream.
  • the sealing sectors will have a peripheral dimension such that they are controlled both by at least three bearing surfaces of the hooks integral with the inner shell 44 and also by at least three direct or indirect bearing surfaces of the hooks 32 and 34 fixed to the outer shell 20.
  • this control is by only three spans.
  • the hooks 32 (respectively 34) and 82 (respectively 78) can be slightly shifted peripherally which makes it possible to have trapezoidal sectors on four supports close to the four corners of a trapezoid, both when the sectors are slaved to expansion of the ferrule 44 only when they are to that of the ring 20.
  • the radial clearance between the sectors 84 and the internal edge of the angle elements 132 is smaller than under the conditions of stabilized partial speed, which increases the pressure drop between enclosures 134 and 136 when the engine is under heavy load. This corresponds to the direction of variation of the pressure in the vein, since the pressure drop in the moving wheel is greater the greater the engine load, although this favorable effect is partially offset by the leak rate may exist between the angle elements 132 and the elastic elements 72, 74 when these are moved outward during the phases where the second control comes into action.
  • the pressure reducer-regulator 124 provides in the enclosure 134 an extremely reduced overpressure relative to the static pressure at wall, measured by the pressure tap 120. As a result, the flow rate according to the arrow K by the clearance j is reduced to a minimum.
  • a pressure reducer-regulator 124 In FIG. 7 is shown a pressure reducer-regulator 124. It comprises a casing 138 provided with a boss 140 (on the left side of the figure) connected to the static wall pressure tap 120 by the pipe 122 ( see figure 4). It further comprises an air intake boss 142 taken from a downstream stage of the compressor by the pipe 126 (see FIG. 4), for example the last one, and a local expansion 144, terminated by a boss 146, delivering the air at reduced pressure and regulated via a pipe 128 (see FIG. 4) at enclosure 102.
  • a jacket 148 which comprises, opposite the boss 142, a hole 150 communicating with an annular enclosure 152 around the drawer 154 whose function will be described later.
  • the shirt 148 has, in line with the local development 144, a slot 156 intended to regulate the pressure supplying the enclosure 102.
  • the drawer 154 has at its two ends cylindrical surfaces 155 cooperating with the internal part of the shirt 148 for example by carbon segments or seals 158.
  • an oblique hole 160 places the annular enclosure 152 in communication with the enclosure 162 of the reduction-regulator opposite the boss 140.
  • the casing 138 is closed by a cover 164, fixed by known means (for example by screwing) to the casing 138, the seal between the casing 138 and the cover 164 being ensured by a seal 166.
  • the pressure prevailing at 162 on the right side of the slide in the figure is equal to the pressure taken from a downstream stage of the compressor, for example the last one. It is therefore higher than the pressure prevailing in the enclosure 168 on the side of the inlet of static wall pressure 120 through the pipe 122 connected to the boss 140.
  • the static pressure at the wall downstream of the distributor corresponds to the downstream pressure of the compressor, reduced by the pressure drop in the chamber and by the static pressure drop in the upstream distributor of the impeller (or even by the pressure losses of one or more turbine stages upstream if the device is used for one of the turbine wheels BP).
  • the force exerted on the slide 154 to the left equal to the pressure difference between the enclosures 162 and 168 multiplied by the internal section of the jacket is balanced by a spring 170.
  • the operation of the reducer-regulator is as follows. For determined operating conditions (engine load, altitude, flight speed, etc.), the various parameters are determined, in particular the dimensions of the reducer-regulator 124, the dimensions of the slot 156, the diameter and the number of turns of the spring 170, and the pressure drop in the multi-holes 104 so that the pressure prevailing in the enclosure 134 is very slightly greater than the static pressure at the wall upstream of the moving wheel. The corresponding calculation obviously depends on each turbomachine and is within the reach of those skilled in the art.
  • the pressure taken from the compressor is generally itself increased, which is a step in the right direction. It will be assumed in what follows that this increase in pressure is insufficient to completely compensate, taking into account the pressure drops in multi-holes 104, the increase in pressure at the wall of the hot gas stream upstream of the moving wheel. , which is generally the case (in the opposite case, several means can be used: diaphragm on the line 126, change of the sampling stage, modification of the reduction-regulator, in particular of the position of its slot).
  • the reducing-regulator will make it possible to adjust the pressure in the enclosure 134 by the following mechanism: the increase in static pressure at the wall upstream of the moving wheel is detected by the static pressure tap at the wall 120, and is sent to the left face (in FIG. 7) of the drawer 154 of the reduction-regulator 124. As a result, the drawer 154 will move to the right, revealing an additional section of the slot 156 of the jacket 148. The pressure drop in this slot will decrease due to the increase in passage cross-section and an increase in pressure will follow in the enclosure 102 which will be reflected after deduction of the pressure drops by the multi-holes 104, in the enclosure 134.
  • slot 156 By playing on the shape of slot 156, the pressure in enclosure 134 will "follow" the pressure 120, that is to say that it will always remain higher, but by a small amount at the static pressure measured by pressure tap 120. Again this is the s skill of the skilled person who will give the slot 156 the shape to ensure that the pressure in the enclosure 134 "follows” as closely as possible the pressure at the wall of the vein of hot gases, but always remaining slightly higher than the pressure at the wall of the vein.
  • the pressure drop which occurs during the bypassing of the angle elements 132 has the consequence that the pressure in the enclosure 136 is lower than the pressure in the enclosure 134.
  • This pressure drop is in common sense to ensure in the enclosure 134 a pressure not too much higher than the pressure in the stream downstream of the turbine wheel.
  • the pressure drop in the vein is generally greater than the pressure drop between the enclosure 134 and the enclosure 136. It is for this reason that it is preferable to have a clearance i downstream positive but less than clearance j.
  • the holes 110 are in this version increased in number and / or in section relative to the holes 110 of the basic patent. This leads, if we want to collect the flows according to the arrows F 'and H, for example to serve for the cooling of a downstream low-pressure distributor, to decrease in number and / or in section the holes 116, in order to equalize the pressures in the enclosure 118 at a lower level, practically equal to that prevailing in the enclosure 136, this in order to reduce the flow rate according to arrow N, passing through the clearance j ' .
  • two reducers-regulators 124 can be used, one supplying the upstream space 134, via the enclosure 102, the other supplying the downstream space 136 (by a pipe not shown similar to the line 128 but opening directly into the enclosure 136), the latter reducer-regulator being governed by a line similar to line 122 by a static wall pressure tap not shown, similar to the wall tap 120, and mounted at the front of the external platform of the downstream distributor 107 of the turbine wheel.
  • a single reducer-regulator 124 is used, but the latter comprises 2 slots 156, offset peripherally with, of course, a local opening 144 and a connection boss 146 opposite each slot, the first connection boss 146 supplying the enclosure 134 via the enclosure 102 and the multi-holes 104, the second directly supplying the enclosure 136, via a non-re presented, the cross section of the slot supplying the enclosure 136 being, for each position of the drawer, smaller than that of the slot supplying the enclosure 102, in order to take account of the drop in static pressure in the gas stream hot, when the moving wheel passes.

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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)
EP84400155A 1983-02-03 1984-01-25 Dispositif d'étanchéité d'aubages mobiles de turbomachine Expired EP0115984B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8301671 1983-02-03
FR8301671A FR2540560B1 (fr) 1983-02-03 1983-02-03 Dispositif d'etancheite d'aubages mobiles de turbomachine

Publications (2)

Publication Number Publication Date
EP0115984A1 EP0115984A1 (fr) 1984-08-15
EP0115984B1 true EP0115984B1 (fr) 1987-10-28

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EP84400155A Expired EP0115984B1 (fr) 1983-02-03 1984-01-25 Dispositif d'étanchéité d'aubages mobiles de turbomachine

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US (1) US4527385A (enrdf_load_stackoverflow)
EP (1) EP0115984B1 (enrdf_load_stackoverflow)
JP (1) JPS59147802A (enrdf_load_stackoverflow)
DE (1) DE3467017D1 (enrdf_load_stackoverflow)
FR (1) FR2540560B1 (enrdf_load_stackoverflow)

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Also Published As

Publication number Publication date
DE3467017D1 (en) 1987-12-03
FR2540560B1 (fr) 1987-06-12
JPH0377363B2 (enrdf_load_stackoverflow) 1991-12-10
US4527385A (en) 1985-07-09
FR2540560A1 (fr) 1984-08-10
EP0115984A1 (fr) 1984-08-15
JPS59147802A (ja) 1984-08-24

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