EP3070270B1 - Système d'aube pour une turbomachine doté d'un dispositif d'ètanchéité, roue directrice et turbomachine. - Google Patents

Système d'aube pour une turbomachine doté d'un dispositif d'ètanchéité, roue directrice et turbomachine. Download PDF

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Publication number
EP3070270B1
EP3070270B1 EP14192595.8A EP14192595A EP3070270B1 EP 3070270 B1 EP3070270 B1 EP 3070270B1 EP 14192595 A EP14192595 A EP 14192595A EP 3070270 B1 EP3070270 B1 EP 3070270B1
Authority
EP
European Patent Office
Prior art keywords
guide vane
sealing device
vane
slide plate
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.)
Active
Application number
EP14192595.8A
Other languages
German (de)
English (en)
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EP3070270A1 (fr
Inventor
Alexander Böck
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.)
MTU Aero Engines AG
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MTU Aero Engines AG
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Filing date
Publication date
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Publication of EP3070270A1 publication Critical patent/EP3070270A1/fr
Application granted granted Critical
Publication of EP3070270B1 publication Critical patent/EP3070270B1/fr
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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
    • F01D11/001—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
    • 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
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps

Definitions

  • the present invention relates to a rotatable guide vane for a turbomachine, such as a gas turbine or an aircraft engine, with a Sealing device on the radially inner end area of the guide vane according to the preamble of claim 1.
  • the present invention also relates to a guide wheel according to claim 8 and a turbomachine according to claim 9.
  • the efficiency is influenced by various factors and parameters.
  • flow losses as a result of bypass flows outside of the main flow through the impeller and stator blading reduce efficiency.
  • Such bypass flows can be at least reduced in different ways in order to avoid efficiency losses.
  • seals are arranged on blade arrangements of the turbomachine in order to reduce bypass flows.
  • US2013/205800 A1 discloses an example of a vane.
  • An object of the present invention is to provide another rotary vane for a
  • a turbomachine such as a gas turbine or an aircraft engine, which provides a sealing device on the radially inner end region of the guide vane for sealing off leakage flows between the guide vane and an inner ring that can be connected to the guide vane.
  • a corresponding guide wheel and a turbomachine it is the object of the present invention to propose a corresponding guide wheel and a turbomachine.
  • the object of the invention is achieved by a rotatable guide vane with the features of the claim 1 solved. It is also achieved by a stator with the features of claim 8 and a turbomachine with the features of claim 9.
  • a sealing device which is arranged so that it can move with respect to the guide vane.
  • the sealing device is positionable in at least one of an open configuration and a closed configuration for sealing off the leakage flows.
  • a flow cross section for the leakage flow is not or at least not completely closed by the sealing device.
  • the sealing device at least reduces the flow cross section for the leakage flow.
  • the guide wheel according to the invention has at least one guide vane according to the invention.
  • the stator may be a portion of a compressor stage.
  • the guide wheel can be referred to as a vane wheel.
  • the system according to the invention has at least one guide wheel according to the invention.
  • the turbomachine can be a gas turbine or an aircraft engine.
  • the turbomachine is an axial turbomachine, in particular a gas turbine.
  • the gas turbine can be an aircraft engine.
  • a plurality of guide vanes arranged in the circumferential direction of the turbomachine are connected to the inner ring.
  • the guide vanes and the inner ring connected to the guide vanes can be referred to as a guide vane ring or stator or stator ring.
  • the sealing device is positioned in an open arrangement, with an “open arrangement” meaning an open or open flow cross section of a leakage flow which is not or at least not completely closed by the sealing device in this arrangement.
  • the sealing device In this position, the sealing device is not, or not yet, positioned in a way to contain the leakage flow seal or reduce. Only after a movement (translational and/or rotary) from this position, a leakage flow is effectively at least partially reduced,
  • the sealing device is positioned in a closed arrangement for sealing the leakage flows.
  • the sealing device or a section of the sealing device, at least partially closes a flow cross section of a leakage flow.
  • the location or position of the sealing device in the closed configuration is referred to as the hook position in some embodiments of the present invention.
  • the sealing device In the hook position, the sealing device can be moved or shifted until the sealing device rests against one or more hooks as a stop.
  • the hook can be referred to as a stop hook.
  • the sealing device In the hook position, the sealing device can close a gap or a region of a flow cross section of a leakage flow. In the hook position, the sealing device can advantageously at least reduce the leakage flow.
  • the stop hook limits the displacement path of the sealing device.
  • the anchor hook can be referred to as a safety hook.
  • the stop hook can also limit rotations of the sealing device.
  • the fulcrum for limiting the movement of the sealing device by means of rotations can be inside or outside the sealing device. In other words, the sealing device can rotate about the pivot point of the stop hook or hooks.
  • the sealing device or sections of the sealing device are moved by means of the leakage flow.
  • the flow pressure of the leakage flow can be large enough to change the position of the sealing device.
  • This movement of the sealing device can be referred to as pressure controlled movement.
  • the sealing device or at least a portion of the sealing device can be moved solely by the leakage flow.
  • the guide vane is mounted such that it can rotate about a longitudinal axis of the guide vane.
  • the guide vane and/or the sealing device is manufactured using an additive manufacturing method.
  • the additive manufacturing process can be a selective laser melting process (Selective Laser Melting - SLM).
  • the leakage flow in the connection area between the guide vane and the inner ring, which is connected in particular to a seal carrier in a guide wheel can advantageously be at least reduced.
  • a reduction in the leakage flow can increase the efficiency of a turbomachine in which the diffuser is installed.
  • the seal carrier can have an inlet seal or can be connected to an inlet seal.
  • FIG. 1 shows a section of a guide wheel rim 100 in a perspective view according to the prior art.
  • the guide wheel rim 100 has a plurality of guide vanes 200 arranged next to one another in the circumferential direction u.
  • the guide vanes 200 each have outer journals 1, which are connected at the radially outer end to a housing of a turbomachine (in 1 not shown), in particular a gas turbine, are connected.
  • the radially inner end of the outer journal 1 is connected to guide vane profiles 3 .
  • the radially inner ends of the guide vane profiles 3 are connected to an inner ring 7 of the guide wheel rim 100 by means of pins 5 (or pins) (see FIG 2 ).
  • the inner ring 7 is connected to an annular seal carrier 9 .
  • the inner ring 7 and the seal carrier 9 are in particular divided into two semicircular segments which are pushed into one another in the circumferential direction.
  • the seal carrier 9 can be connected to inlet seals or inlet seal segments.
  • FIG. 2 shows a detail 1 in a sectional view with a stator vane platform 11 and the inner ring 7 according to the prior art.
  • the vane 200 is connected to the inner ring 7 by means of the pin 5 and a bushing 13 .
  • the bush 13 is additionally inserted into a bore 15 in the inner ring 7 .
  • the seal carrier 9 and the inner ring 7, both of which are designed in particular as semicircular segments, can be pushed into one another in the circumferential direction u.
  • the segments are secured by means of a securing pin 17 against displacement of the seal carrier 9 and the inner ring 7 (relative to one another).
  • Inlet seals 19 are connected to the seal carrier 9 and are provided to form a sealing gap between sealing tips 21 , for example a rotating shaft 23 .
  • the inlet seals 19 are in particular segmented over the circumference.
  • a leakage flow 25 forms in particular between guide vane platform 11 and inner ring 7 .
  • the leakage flow 25 flows as a result of the pressure drop from the pressure side of the blade profile to the suction side.
  • FIG 3 shows the leakage flow 25 from 2 in perspective view with an adjacent prior art vane 200'.
  • a part of the leakage flow 25' (the leakage flow 25' can be referred to as a blast) can flow from the leakage flow 25 of the guide vane 200 emerging between the guide vane platform 11 and the inner ring 7 in the direction of the leading edge of the adjacent guide vane 200' and thus the oncoming flow of the guide vane 200' disturb. This can lead to a loss of efficiency.
  • Figure 4a shows a sectional view in a plane with the axes circumferential direction u and axial direction a, perpendicular to the radial direction r, a guide vane 300 according to the invention with a sealing device 27 and two stop hooks 29, which are connected to the guide vane 300.
  • the sectional view of Figure 4a is approximately in the middle in the radial direction r at the level of the stator vane platform 11 (see 6 ) arranged.
  • the vane profile 3 (see 6 ) is not visible in this sectional plane, but is sketched in dashed lines to clarify the arrangement of the sealing device 27 .
  • the pin 5 (radially inward of the stator vane platform 11) is also shown in phantom since it is not visible in this sectional view. For example in Figure 6a and 5b the pin 5 is shown.
  • the sealing device 27 is designed as a slide plate 27 in this exemplary embodiment.
  • the section plane shown can move the slide plate 27 in the circumferential direction u and in the axial direction a (displacement path 28), but not in the radial direction r (see 6 ). The movement is limited by the two stop hooks 29 on which the two paragraphs 31 of the slide plate 27 can rest.
  • the position of the slide plate 27 shown in FIG. 4a can be referred to as the assembly position.
  • the slide plate 27 can rotate about a pivot point 33 of the stop hook 29 with a rotation angle 30 .
  • the slide plate 27 is shown in a hooked position 35 with a dashed line representation. In the hook position 35, the maximum displacement path of the slide plate 27 in relation to the starting position (assembly position) is reached.
  • the circle 37 represents the bore 37 in the inner ring 7 for receiving the guide vane platform 11 of the guide vane 300 (see FIG 1 and 2 ).
  • the bore 37 of the inner ring 7 can be or will be offset.
  • the dashed circle 39 represents a maximum displacement of the bore 37 due to wear.
  • the slide plate 27 can at least partially cover or close the gap 41 between the outer boundary 43 of the stator vane platform 11 and the bore 37 and thus a leakage flow 25 (see 3 ), at least partially.
  • an access hole 45 is shown located in the underside (radially inner side) of the stator vane platform 11 .
  • the function of access hole 45 is explained in Figure 4b described.
  • Figure 4b shows the slide plate 27 in a position that is shifted relative to the starting position or starting position (assembly position), in which the gap 41 is partially covered or closed by means of the slide plate 27 .
  • This position can be referred to as the nominal (installed and pressurized) position.
  • the slide plate 27 rests against the bore 37 of the inner ring 7 in the region 47 .
  • the inside Figure 4b upper paragraph 31 of the slide plate 27 rests against the upper stop hook 29 .
  • the lower paragraph 31 not on the lower stop hook 29.
  • the slide plate 27 can be moved from the initial position ( Figure 4a ) to the shifted position ( Figure 4b ) are moved and displaced by means of a flow flowing through the access bore 45 or the pressure force caused by this flow.
  • the direction of the thrust of this flow is represented by arrow 49.
  • Figure 4c shows an alternative, shifted contour 51 (or contour withdrawal) of the slide plate 27. Due to the shifted contour 51, the area 47' of the slide plate 27 that is in contact with the bore of the inner ring 7 also shifts. In the possible alternative contour 51 shown here as an example, the adjacent area 47' (or adjacent point) shifts to Figure 4c downward. Other contour shapes could shift the adjoining area 47' even further down or further up, for example.
  • a displacement of the adjacent area 47' affects the covered or closed area of the gap 41 between the bore 37 (or the worn bore 39) and the outer boundary of the stator vane platform 43.
  • This can be particularly relevant and advantageous if the outflow area of the Leakage outflow 25 (see 3 ) should be covered as precisely as possible, for example in order to optimize the efficiency in a targeted manner.
  • the outflow area of the leakage outflow 25 can be changed and influenced by the rotation of the guide vane 400 according to the invention about its longitudinal axis 14 .
  • the rotation of the guide vane 400 according to the invention or the position of the guide vane profile 3 in relation to its inflow can depend significantly on the flow conditions in the turbomachine, which is influenced, for example, by a full-load or part-load operating state.
  • Figure 5a shows another guide vane 300' according to the invention.
  • the stop hooks 29' are offset (or reversed) from the arrangement of FIGS Fig. 4a-c arranged.
  • the shoulders 31' of the slide plate 27' are also arranged in an offset manner corresponding to the stop hooks 29'.
  • the slide plate 27' is positioned in the home position or mounting position.
  • Figure 5b shows the further guide vane 300' according to the invention Figure 5a in a pressurized (or nominal) position.
  • the slide plate 27' rests in the area 47' on the bore 37'.
  • Figure 6a shows the guide vane 300 according to the invention from FIGS Figure 4a and Figure 4b in a perspective view.
  • a slot 53 can be seen in the stator vane platform 11, in which the slide plate 27 is movably arranged (in the plane with the axial direction a and the circumferential direction u). In the installed position of the slide plate 27, the slide plate 27 is fully integrated in the slot 53 and does not protrude beyond the outer boundary 43 of the vane platform 11.
  • the slide plate 27 in a pressurized position of the slide plate 27, in which a compressive force from the radially inner side of the stator vane platform 11 (in Figure 6a concealed below the guide vane platform 11) on which the slide plate 27 acts, the slide plate 27 can protrude from the slot 53, but not fall out.
  • the slide plate 27 is prevented from falling out by the stop hooks 29 on the guide vane 300 and the shoulders 31 on the slide plate 27 .
  • Figure 6b shows the guide vane 300 according to the invention Figure 6a in a rotated, perspective view seen from radially inside to radially outside.
  • FIG 7a shows the guide vane 300' according to the invention from FIGS Figures 5a and 5b in perspective view.
  • the slide plate 27' protrudes beyond the outer boundary 43' of the stator vane platform 11'. This is the case in particular when the slide plate 27' is pressurized when the guide vane 300' is installed, i.e. the slide plate 27' is moved or displaced outwards as a result of a pressurized flow (in particular a leakage flow) through the access bore 45' been.
  • Figure 7b shows the guide vane 300' according to the invention Figure 7a in a rotated perspective view from radially inward to radially outward with the access bore 45' open.
  • Figure 8a shows three different embodiments of vanes 200, 300, 300 'in an inner ring 7 in perspective views.
  • the guide vane 200 corresponds to the state of the art and was 1 , 2 and 3 described.
  • the vane 300 according to the invention was in the Fig. 4a-c and Fig. 6a,b described, the vane 300 'according to the invention was in the Fig. 5a,b and Fig. 7a,b described.
  • Figure 8b shows two guide vanes 300 according to the invention in a opposite of the Figure 8a changed setting angle.
  • the angle of guide vane 300 around its longitudinal axis is referred to as the setting angle.
  • the guide vane profiles 3 of the guide vanes 300 are in Figure 8b opposite to Figure 8a further aligned in the circumferential direction u.
  • This changed adjustment angle has an influence on the slide plate 27.
  • the slide plate 27 of the guide vane 300 is moved in a direction oblique to the circumferential direction u and to the axial direction a in order to seal the gap 41 (and the leakage flow passing through the gap) by means of the slide plate 27 .
  • the slide plate 27 is aligned in a direction almost parallel to the axis direction a in order to seal the gap 41 .
  • Figure 8c shows the arrangement of the guide vanes 300 according to the invention Figure 8b in another perspective view.
  • the guide vane platform 11 can protrude beyond the surface of the inner ring 7.
  • the constructive configurations of the slide plate 27, the slot 53, the stop hook 29 and the shoulder 31 were designed in such a way that jamming is largely ruled out and the function of the slide plate 27 is ensured. This is achieved in particular by the fact that the stop hooks 29 have different design variants, such as the positioning of the pivot position of the stop hooks 33 (see Figure 4a ), to be executed.
  • the shape of the area of the slide plate 27 protruding beyond the outer boundary 43 of the guide vane platform 11 and/or the positioning (lower position) of the slide plate 27 can be matched to the corresponding contact area 47 (see Figures 4b and 4c ) be designed on the bore of the inner ring 37 in such a way that this contact area 47 still comes about even with maximum adjustment angles and maximum wear of the bore of the inner ring 37 (offset of the inner ring bore).
  • Figure 9a shows a further guide vane 300" according to the invention with a further sealing device 27" and two further stop hooks 29" in a mounting position for mounting the inner ring.
  • the guide vane 300" can be fitted into an inner ring 7 (see Figures 8a to 8c ) can be used or mounted.
  • the inner ring 7 is defined by the circle 37 or bore 37 in Figure 9a implied.
  • the further sealing device 27" is designed as a slide plate 27". Both the slide plate 27" and the two further stop hooks 29" are constructed in such a way that the slide plate 27" as an elastic element can be pushed onto or over the stop hooks 29" and mounted. This assembly process is in the Figures 11a to 11d described in more detail.
  • the other access hole 45 ' in contrast to the previously shown circular access hole 45 in the Figures 4 to 8 , a rounded triangle shape.
  • This triangular shape has a larger cross-sectional shape than the circular cross-sectional shape Flow through of fluid.
  • the pressure force caused by this flow can thus advantageously move the slide plate 27" more easily and better in the operating state or in the case of use and at least partially close the gap 41 towards the inner ring 7.
  • the previously discussed leakage flow 25 can thus be at least partially reduced.
  • Figure 9b shows the guide vane 300" according to the invention Figure 9a in the closed state.
  • the slider 27" closes the gap 41 in certain areas. This area has been selected in terms of design in such a way that a gap flow 25 or leakage flow 25 (see 2 ) on the suction side of the blade profile 3 is at least partially reduced.
  • the slide 27" is displaced as a result of the pressure force of the flow through the access bore 45' in the direction of the displacement path 28 up to the edge of the bore 37 of the inner ring 7.
  • the slider 27" rests with the two paragraphs 31" on the stop hooks 29".
  • this guide vane 300" corresponds to a variant that does not have a pivot point 33 (see Figure 4a ) having.
  • the cutting plane BB is in Figure 10c shown.
  • Figure 10a shows the guide vane 300" according to the invention from FIG Figure 9b in a perspective view.
  • the analogous discussion applies to the slide 27", the stop hook 29" etc Figure 6a .
  • Figure 10b shows the guide vane 300" according to the invention from FIG Figure 9b in another perspective view.
  • the discussion about Figure 6b applies here analogously to the modified design of the slide 27", the stop hook 29" and other modified areas.
  • Figure 10c shows the guide vane 300" according to the invention from FIG Figure 9b as a sectional view BB.
  • the access hole 45' for moving the slide plate 27'' within the vane platform 11 is clearly visible.
  • Figure 11a shows the first step in mounting the slide plate 27" on the stop hooks 29" of the guide vane platform 11'' of the guide vane 300" according to the invention.
  • the slide plate 27" with the upper shoulder 31" is attached to the upper stop hook 29" and hooked in. Then the lower shoulder 31" is first attached or laid to the lower stop hook 29".
  • Figure 11b shows the second step for mounting the slide plate 27" on the guide vane platform 11".
  • the slide plate 27" is moved or pressed in the direction of the arrow 55, so that the lower shoulder 31" can be pushed over the stop hook 29" by means of an elastic deformation of the slide plate 27". This process can be referred to as "clipping in”.
  • 11c shows the third step for assembling the slider plate 27".
  • the slider plate 27" is in the assembled position and the guide vane 300" can be pushed onto the inner ring 7 or connected to it (see Fig Figures 8a to 8c ). In this assembly position, the gap 41 is not yet closed.
  • FIG 11d shows the fourth step for assembling the slide plate 27". This step is no longer part of the actual assembly. In this step, pressure is applied through the access bore 45' (see Figure 10c ) for moving and closing the gap 41, at least in a partial area of the gap 41 (see Figure 9b ). The slide plate 27" then rests against the bore 37 of the inner ring 7. This area is shown as the adjacent area 47" of the slide plate 27".
  • the position of the slide plate 27" can be referred to as the sealing position.

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  • General Engineering & Computer Science (AREA)
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Claims (9)

  1. Aube directrice (300) rotative ajustée pour être reliée à une bague intérieure (7) d'une turbomachine, comportant un dispositif d'étanchéité (27, 27') au niveau de la zone d'extrémité radialement intérieure de l'aube directrice (300) permettant l'étanchéité d'écoulements de fuite (25) entre l'aube directrice (300) et la bague intérieure (7) pouvant être reliée à l'aube directrice (300),
    caractérisée en ce que
    le dispositif d'étanchéité (27, 27') est disposé de manière mobile par rapport à l'aube directrice (300), et le dispositif d'étanchéité (27, 27') peutêtre positionné au moins dans un agencement ouvert ou fermé pour étanchéifier les écoulements de fuite (25), le dispositif d'étanchéité (27, 27'), dans un agencement ouvert, ne fermant pas ou au moins pas complètement une section transversale de passage pour l'écoulement de fuite (25) et, dans l'agencement fermé, réduisant au moins la section transversale de passage pour l'écoulement de fuite (25).
  2. Aube directrice (300) selon la revendication 1, dans laquelle l'aube directrice (300) et/ou le dispositif d'étanchéité (27, 27') présentent au moins un crochet d'arrêt (29, 29') permettant de limiter une course de déplacement (28) et/ou un angle de torsion (30) du dispositif d'étanchéité (27, 27').
  3. Aube directrice (300) selon la revendication 1 ou 2, dans laquelle l'aube directrice (300) est montée rotative autour d'un axe longitudinal (14) de celle-ci.
  4. Aube directrice (300) selon l'une des revendications précédentes, dans laquelle le dispositif d'étanchéité (27, 27') est une plaque ou une tôle coulissante.
  5. Aube directrice (300) selon l'une des revendications précédentes, dans laquelle le dispositif d'étanchéité (27, 27') présente un alésage permettant le passage d'au moins une partie de l'écoulement de fuite (25).
  6. Aube directrice (300) selon l'une des revendications précédentes, dans laquelle le dispositif d'étanchéité (27, 27') et/ou l'aube directrice (300) présentent au moins deux crochets d'arrêt (29, 29'), les crochets d'arrêt (29, 29') étant disposés asymétriques par rapport à un axe central du dispositif d'étanchéité (27, 27') dans une direction de déplacement du dispositif d'étanchéité (27, 27').
  7. Aube directrice (300) selon l'une des revendications précédentes, dans laquelle l'aube directrice (300) et/ou le dispositif d'étanchéité (27, 27') sont fabriqués au moyen d'un procédé de fabrication additive.
  8. Roue directrice (100) comportant au moins une aube directrice (300) et une bague intérieure (7) selon l'une des revendications précédentes.
  9. Turbomachine comportant une roue directrice (100) selon la revendication 8, dans laquelle la turbomachine est une turbine à gaz ou un moteur d'aéronef.
EP14192595.8A 2013-11-12 2014-11-12 Système d'aube pour une turbomachine doté d'un dispositif d'ètanchéité, roue directrice et turbomachine. Active EP3070270B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102013222980.1A DE102013222980A1 (de) 2013-11-12 2013-11-12 Leitschaufel für eine Strömungsmaschine mit einer Dichtungsvorrichtung, Leitrad sowie Strömungsmaschine

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EP3070270A1 EP3070270A1 (fr) 2016-09-21
EP3070270B1 true EP3070270B1 (fr) 2022-03-09

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US (1) US10060278B2 (fr)
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DE102015110252A1 (de) * 2015-06-25 2016-12-29 Rolls-Royce Deutschland Ltd & Co Kg Statorvorrichtung für eine Strömungsmaschine mit einer Gehäuseeinrichtung und mehreren Leitschaufeln
EP3128132B1 (fr) 2015-08-03 2019-03-27 MTU Aero Engines GmbH Élement annulaire d'aube directrice de turbomachine
DE102016207212A1 (de) 2016-04-28 2017-11-02 MTU Aero Engines AG Leitschaufelkranz für eine Strömungsmaschine
US10801343B2 (en) * 2016-12-16 2020-10-13 Pratt & Whitney Canada Corp. Self retaining face seal design for by-pass stator vanes
DE102017211316A1 (de) 2017-07-04 2019-01-10 MTU Aero Engines AG Turbomaschinen-Dichtring
DE102018213983A1 (de) * 2018-08-20 2020-02-20 MTU Aero Engines AG Verstellbare Leitschaufelanordnung, Leitschaufel, Dichtungsträger und Turbomaschine
DE102019218909A1 (de) * 2019-12-04 2021-06-10 MTU Aero Engines AG Strömungsmaschine
DE102020210094A1 (de) 2020-08-10 2022-02-10 MTU Aero Engines AG Verstellbare Leitschaufelanordnung
US11725533B2 (en) * 2020-11-10 2023-08-15 Pratt & Whitney Canada Corp. Variable guide vane assembly and bushing ring therefor
US11814969B2 (en) 2021-07-21 2023-11-14 Pratt & Whitney Canada Corp. Gas turbine engine with low-pressure compressor bypass
US11486265B1 (en) * 2021-07-23 2022-11-01 Pratt & Whitney Canada Corp. Sealing variable guide vanes

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Also Published As

Publication number Publication date
EP3070270A1 (fr) 2016-09-21
DE102013222980A1 (de) 2015-06-11
US10060278B2 (en) 2018-08-28
US20150192025A1 (en) 2015-07-09

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