EP3106672B1 - Gehäuse mit wirbeleinspritzdüsen für kompressor eines axialen turbotriebwerks - Google Patents

Gehäuse mit wirbeleinspritzdüsen für kompressor eines axialen turbotriebwerks Download PDF

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Publication number
EP3106672B1
EP3106672B1 EP16174588.0A EP16174588A EP3106672B1 EP 3106672 B1 EP3106672 B1 EP 3106672B1 EP 16174588 A EP16174588 A EP 16174588A EP 3106672 B1 EP3106672 B1 EP 3106672B1
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EP
European Patent Office
Prior art keywords
vortexes
injection
counter
blades
rotor
Prior art date
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Active
Application number
EP16174588.0A
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English (en)
French (fr)
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EP3106672A1 (de
Inventor
Stéphane Hiernaux
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Safran Aero Boosters SA
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Safran Aero Boosters SA
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Publication of EP3106672A1 publication Critical patent/EP3106672A1/de
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Classifications

    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/685—Inducing localised fluid recirculation in the stator-rotor interface
    • 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
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F04D27/0215—Arrangements therefor, e.g. bleed or by-pass valves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F04D27/0238—Details or means for fluid reinjection
    • 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
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • F04D29/526—Details of the casing section radially opposing blade tips
    • 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
    • F01D11/10—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using sealing fluid, e.g. steam
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/55—Seals

Definitions

  • the invention relates to leakage vortices in turbomachine rotor blade heads. More precisely, the invention deals with a casing for limiting the effect of vortices in blade heads which limit the stability of an axial turbomachine compressor.
  • the invention also proposes a compressor, and an aircraft turbojet engine.
  • An axial turbomachine compressor has alternating rows of rotor vanes and rows of stator vanes.
  • the rotation of the rotor and its blades contributes to gradually compressing the primary flow through the turbomachine.
  • this compression is accompanied by leaks between the rotor blade heads and the housing that surrounds them. Indeed, a mechanical game is necessary at this interface to avoid contacts.
  • the blade heads sweep the inner surface of the housing and the leaks bypass the vane heads forming vortices to the intrados.
  • Each vortex delimits a blocking zone against its blade where the fluid has a small amount of movement.
  • the vortex may gain the leading edge of the next dawn.
  • the flow in the blocking zone can be reversed and the compressor can become unstable.
  • a pumping phenomenon can occur, a crankcase treatment makes it possible to avoid it.
  • the document US2011 / 0299979A1 discloses a turbomachine with a compressor.
  • the compressor has a fixed stator and a movable wheel supporting annular rows of blades.
  • the stator comprises an outer casing surrounding the rotor blades, said casing having annular grooves at the blades. These grooves have varying depths to preserve the stall margin of the compressor. However, the depth and width of each groove increases bladehead leakage, limiting the compression ratio of the compressor. In addition, the performance of the turbomachine is degraded.
  • the document EP2778427A2 discloses a compressor for a turbomachine, comprising a system for recirculating sucked air.
  • the system comprises a plurality of suction ports extending through a collector.
  • An annular suction cavity surrounds the manifold and is in communication with outlet openings of the suction ports.
  • the suction ports allow communication between the main gas flow passage and the annular cavity.
  • the annular cavity includes exit passages with orifices disposed in the manifold.
  • the air is passively drawn through the suction holes, circulates through the annular cavity and is fed back into the main gas flow passage in a second axial position.
  • the effectiveness of this system to stem leaks at the head of dawn remains limited.
  • the quantity of air taken off significantly penalizes the efficiency of the turbomachine.
  • the object of the invention is to solve at least one of the problems posed by the prior art. More precisely, the purpose of the invention is to increase the efficiency of a turbomachine. The invention also aims to push the limit to the stall of a compressor of an axial turbomachine.
  • the object of the invention is an axial turbine engine compressor assembly with the features of claim 1.
  • the vortex generating device comprises orifice injection modules, preferably the casing comprises a plurality of injection modules angularly distributed around the rotor.
  • At least one or each injection module comprises at least one injection orifice arranged upstream of the row of rotor blades.
  • At least one or each injection orifice comprises internal fins configured to generate a vortex from a flow passing through said orifice, optionally at least one or more modules comprise a plurality of orifices. injection with internal fins configured to generate vortexes.
  • At least one or each injection module comprises a set of injection orifices inclined with respect to each other so as to form a vortex from a flow coming from said injection ports of the game
  • At least one or each injection module comprises at least one upstream injection orifice and one downstream injection orifice which are offset axially and / or circumferentially of the casing; said orifices being inclined relative to each other along an axial plane and / or with respect to a plane perpendicular to the axis of rotation of the rotor.
  • At least one or each injection module comprises means for taking air, in particular an air sampling orifice, possibly disposed downstream of the row of blades.
  • At least one or each injection module comprises a pair of channels each connecting an injection orifice upstream of the blades to a sampling orifice downstream of the blades, preferably the channels of each pair. cross.
  • the housing comprises a main internal surface surrounding the blades, at least one or more or each orifices flush with said inner surface.
  • the blades comprise leading edges with external ends, the injection orifices being upstream of the outer ends of the leading edges.
  • the vortex generating device comprises at least one or more channels axially passing through the at least one row of rotor blades.
  • the counter-vortex generating device comprises a block made of material in which at least one or more channels are formed, preferably the block of material extends over the entire axial length of the at least one an annular row of rotor blades.
  • the vortex generating device comprises a collector surrounding the housing, preferably the collector surrounds a space in which the row of blades is inscribed.
  • the assembly comprises control means for generating alternately vortexes according to a frequency which is a function of the speed of rotation of the rotor, the triggering of the generation of a counter-vortex. vortex possibly depending on the proximity of a blade with respect to a generating device.
  • a radial clearance separates the outer ends of the blades of the housing, said clearance possibly surrounding the row of blades, and / or the clearance is an annular clearance.
  • the casing comprises an annular seal, in particular an annular layer of abradable material, the vortex generating device extending upstream downstream from said annular seal and / or surrounding said annular seal.
  • At least one or each injection module comprises at least one channel connecting an injection orifice to a sampling orifice.
  • the assembly comprises several generating devices whose counterwinds rotate in the same direction.
  • At least one or each injection orifice and / or at least one or each sampling orifice forms a passage oriented mainly radially.
  • the main internal surface is the one having the largest extent.
  • the collector is a distributor supplying pressurized air to each vortex generating device.
  • the housing has an inner surface with a generally straight or substantially arcuate profile of revolution, said profile extending axially all along a row of rotor blades.
  • leakage vortices and counter vortices flow downstream.
  • the leakage vortexes rotate helically, the device being configured so that in operation the vortex rotates helically in the direction opposite to the direction of helical rotation of the leakage vortices.
  • the invention also relates to a turbomachine comprising an assembly, remarkable in that the assembly is in accordance with the invention; preferably, the rotor comprises several annular rows of vanes and the assembly comprises a plurality of counter vortex generating devices.
  • the invention also relates to a method for controlling the stability of a turbomachine compressor with the characteristics of claim 12, in particular a low pressure compressor, the compressor comprising an assembly for a turbomachine compressor with the characteristics of the claim 1; remarkable in that the method comprises the generation of the counter vortex generating device to the leakage vortices and rotating in the opposite direction of the leakage vortices in order to limit them, the turbomachine optionally being in accordance with the invention.
  • the generated vortexes are generated in a discontinuous manner, in particular when approaching a leakage vortex.
  • the vortexes generated are injected downstream, in particular towards leakage vortices.
  • the outer ends of the blades have cords inclined relative to the axis of rotation of the rotor, during their generation the vortexes having helical winding axes generally parallel to the inclined cords. outer ends of blades.
  • the assembly is configured for a transonic flow generating a shock at the blades.
  • each object of the invention is also applicable to the other objects of the invention.
  • each object of the invention is combinable with other objects.
  • the invention makes it possible to confine leakage vortices, and possibly to reduce them. Their action is reduced both in terms of space and duration, so that their propagation towards the next dawn is dammed. From then on, each vortex of flight is folded against its reference dawn. The blocking zone is reduced, and is pushed back from the next rotor blade. The stability margin is then increased, and the yield is preserved.
  • the invention makes it possible to maintain a homogeneous clearance between the blade and the casing, which improves the compression ratio of each compression stage.
  • the inner surface of the housing also becomes simpler to achieve since it remains straight, and / or smooth.
  • An embodiment of woven preform composite material remains simple.
  • the use of channels between the orifices makes it possible to form pressure losses, which may be dynamic. By this means, it is possible to control the flow reinjected by the orifices as a function of the upstream-downstream pressure difference of the blades.
  • the vortex generating device can then be adapted to promote the generation of vortex at a predefined regime, and to limit these vortices to another regime. It then becomes easier to design a turbomachine optimized for a nominal speed, while having a self-regulating or passive system.
  • inner or inner and outer or outer refer to a positioning relative to the axis of rotation of an axial turbomachine.
  • the axial direction corresponds to the direction along the axis of rotation of the turbomachine.
  • the figure 1 represents in simplified manner an axial turbomachine. It is in this case a double-flow turbojet engine.
  • the turbojet engine 2 comprises a first compression level, called a low-pressure compressor 4, a second compression level, called a high-pressure compressor 6, a combustion chamber 8 and one or more levels of turbines 10.
  • the mechanical power the turbine 10 transmitted via the central shaft to the rotor 12 sets in motion the two compressors 4 and 6.
  • the latter comprise several rows of rotor blades associated with rows of stator vanes.
  • the rotation of the rotor about its axis of rotation 14 thus makes it possible to generate an air flow and to compress it gradually until it reaches the combustion chamber inlet 8. Reducing means can increase the speed of rotation transmitted. compressors.
  • An inlet fan commonly referred to as fan or blower 16 is coupled to the rotor 12 and generates a flow of air which splits into a primary flow 18 passing through the above mentioned levels of the turbomachine, and a secondary flow 20 passing through an annular duct. (partially shown) along the machine to then join the primary flow at the turbine outlet.
  • the secondary flow can be accelerated to generate a thrust reaction.
  • the primary 18 and secondary 20 streams are annular flows, they are channeled by the casing of the turbomachine.
  • the casing has cylindrical walls or ferrules which can be internal and external.
  • the figure 2 is a sectional view of a compressor of an axial turbomachine such as that of the figure 1 .
  • the compressor may be a low-pressure compressor 4.
  • the rotor 12 comprises several rows of rotor blades 24, 1 occurrence three.
  • the low pressure compressor 4 comprises several rectifiers, in this case four, which each contain a row of stator vanes 26.
  • the rectifiers are associated with the fan 16 or with a row of rotor vanes to straighten the flow of air, so as to convert the speed of the flow into static pressure.
  • the blades stator 26 extend substantially radially from an outer casing 28, and can be fixed and immobilized by means of axes. They are regularly spaced from each other, and have the same angular orientation in the flow. Seals 30, for example abradable, may cover the casing 28 at the level of the rotor vanes 24.
  • the outer casing 28 is provided with counter-vortex generating devices 32, each associated with a row of rotor blades 24.
  • Each vortex is a vortex.
  • one or only certain rows of rotor blades 24 are provided with generating devices 32.
  • the figure 3 sketch a plan view of a compressor section.
  • the compressor can match that of the figure 2 .
  • a rotor blade 24 is axially spaced from an injection port 34.
  • a leakage vortex 36 propagates from the rotor blade head.
  • the device 32 has a vortex injection orifice 34.
  • This vortex 38 rotates in the opposite direction to the direction of rotation of the vortex leak 36 of the blade. When they meet, the leakage vortex 36 is reduced and its effect is countered.
  • the injection orifice 34 may comprise fins 40.
  • the fins 40 may be helical and angularly distributed inside the orifice 34. Their pitch, their spacings, their heights and their lengths make it possible to confer a rotational component on the interior of the orifice 34. a flow passing through the orifice.
  • a vortex just like a vortex is understood as a spiral flow with a winding axis, possibly forming several successive and coherent turns.
  • the air passing through the injection orifice 34 can be taken downstream in the compressor. It can also be from any other place of the turbomachine. Means may allow discontinuous feeding, for example to allow injection of a vortex to a vortex leak.
  • the invention provides a method for combating leakage vortices by opposing vortex 38 which are injected locally and periodically.
  • the figure 4 sketch a generator device 132 against vortex 138 according to a second embodiment of the invention. This figure 4 resumes the numbering of the preceding figures for identical or similar elements, however, the numbering is incremented by 100. Specific numbers are used for the specific elements of this embodiment.
  • the axis of rotation 114 is shown as a marker.
  • Generator device 132 includes a pressurized air manifold 142 and ports for drawing and injecting pressurized air.
  • Collector 142 may form an annular cavity surrounding the rotor blade array 124 and convey air from downstream to upstream.
  • the collector 142 may be delimited by the casing 128, possibly in the form of an outer shell, and / or an outer shell 144 attached to the casing 128.
  • the collector 142 and / or the shell 144 may extend axially all the way through. along the blade bank 124, extending from the leading edge to the trailing edge.
  • the injection ports may be grouped into sets of at least two ports to form a vortex. They can then form an injection module.
  • the generator device 132 has several injection orifices, including an upstream injection orifice 134 and a downstream injection orifice 146. They are in communication with the sampling orifice 148 via the manifold 142. During the passage of a At the vane 124 at the sampling port 148, the pressure increase causes a flow through the manifold 142. This flow enters through the sampling port 148 and out through the injection ports (134; 146). The pressure in the manifold 142 can therefore be oscillating because of the repeated passage of the blades 124.
  • the device 132 can be passive in the sense that it does not require external energy input.
  • the simple passage of a blade 124 is enough to make it operational thanks to the variation of pressure. Reliability and energy saving are optimized.
  • FIG 5 sketching a plan view of a portion of the compressor according to the second embodiment of the invention.
  • An assembly with a rotor portion and a housing portion represented by orifices (134; 146) is illustrated.
  • the axis of rotation 114 is shown as a marker.
  • the upstream injection port 134 and the downstream injection port 146 may overlap axially and / or circumferentially. They can have rectangular shapes. Their offset, the inclinations of their respective output directions favor the birth of a vortex 138. For example, the injected flows are wound on one another, possibly in combination with the primary flow.
  • the figure 6 is an axial section of the housing 128.
  • the section is made along the axis of rotation 114.
  • the orifices (134; 146) may correspond to those drawn on the figure 5 .
  • the injection ports (134; 146) are formed in the thickness of the housing wall 128 radially therethrough. They may be inclined relative to each other, and / or inclined relative to perpendicular lines 149 to the axis of rotation 114 at different angles. By inclination of an orifice, it is possible to consider the direction of the flow which passes through it, and / or the direction of its median axis 150.
  • the upstream orifice 134 may be inclined with respect to a perpendicular 149 to the axis of rotation 114. at an angle of between 30 ° and 50 °.
  • the downstream orifice 146 may be inclined in the same direction, but at a lower angle; for example an angle ⁇ 2 between 25 ° and 45 °
  • the figure 7 is a cross section of the housing 128 at a generator device 132.
  • the cross section is in a plane perpendicular to the axis of rotation.
  • the orifices (134; 146) may correspond to those drawn on the figure 5 and / or figure 6 .
  • the injection ports (134; 146) are inclined without the perpendicular plane. They may be inclined relative to each other, and / or inclined relative to a perpendicular 149 to the axis of rotation 114 at different angles.
  • the upstream orifice 134 is inclined with respect to a perpendicular 149 of an angle ⁇ 1 between 25 ° and 50 ° in the direction opposite to the direction of rotation.
  • the downstream orifice 146 is inclined relative to a perpendicular 149 of an angle ⁇ 2 between 25 ° and 50 ° in the direction of rotation of the rotor.
  • the figure 8 sketch a generator device section 232 according to a third embodiment of the invention. This figure 8 resumes the numbering of the preceding figures for the identical or similar elements, however the numbering is incremented by 200. Specific numbers are used for the elements specific to this embodiment.
  • the axis of rotation 214 is shown as a marker.
  • Generator device 232 may generally be similar to that of the second embodiment of the invention. It further comprises a block of material 252 attached to the collector 242, or at least to the shell 244.
  • the block 252 can be fixed to the housing 228 and have two channels 254 each in communication with the collector 242.
  • the channels (234; ) inject each directed stream into the primary stream.
  • the addition of this block 252 makes it possible to better guide the flows, and thus better to form a vortex 238.
  • the block 252 may be annular or in the shape of an arc of a circle. It can be achieved by additive manufacturing to form canals 254 having complex geometries. Indeed, the curvature and the section of the channels 254 can evolve.
  • FIG 9 Sketch a generator device 332 according to a fourth embodiment of the invention. This figure 9 resumes the numbering of the preceding figures for identical or similar elements, however the numbering is incremented by 300. Specific numbers are used for the elements specific to this embodiment.
  • the injection ports (334; 346) may be generally similar to those of the second and / or third embodiments. Each port (334; 346) may be powered by a dedicated channel 354.
  • the device 332 may comprise several sampling orifices 348, each in fluid communication using a dedicated channel 354. These channels can be formed using pipes, or in a block of material. Channels 354 can intersect. They can be arranged outside the housing 328.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (14)

  1. Baugruppe für einen Kompressor (4; 6) einer axialen Turbomaschine, wobei die Baugruppe umfasst:
    - einen Rotor (12) mit zumindest einer ringförmigen Reihe von Rotorschaufeln (24; 124);
    - ein Statorgehäuse (28; 128; 228; 328), das die Reihe von Rotorschaufeln (24; 124) umgibt;
    wobei die Baugruppe derart konfiguriert ist, dass, wenn die Turbomaschine (2) in Betrieb ist, die Bewegung der Schaufeln (24; 124) Leckagewirbel (36) zwischen dem Gehäuse (28; 128; 228; 328) und den Schaufeln (24; 124) erzeugt;
    gekennzeichnet dadurch, dass
    das Gehäuse (28; 128; 228; 328) eine Erzeugungsvorrichtung (32; 132; 232; 332) von Gegenwirbeln (38; 138; 238) auf dem Niveau der Leckagewirbel (36) umfasst, wobei die Vorrichtung (32; 132; 232; 332) derart konfiguriert ist, dass die Gegenwirbel (38; 138; 238) sich bei Betrieb in eine Richtung drehen, die der Richtung der Drehung der Leckagewirbel (36) entgegengerichtet ist.
  2. Baugruppe gemäß Anspruch 1, gekennzeichnet dadurch, dass die Erzeugungsvorrichtung von Gegenwirbeln (38; 138; 238) Injektionsmodule mit Öffnungen umfasst, wobei das Gehäuse (28; 128; 228; 328) vorzugsweise mehrere Injektionsmodule umfasst, die in Winkelabständen um den Rotor (12) herum verteilt sind.
  3. Baugruppe gemäß Anspruch 2, gekennzeichnet dadurch, dass zumindest eines oder jedes Injektionsmodul zumindest eine Injektionsöffnung (34; 134; 146; 234; 246; 334; 346) umfasst, die stromaufwärts der Reihe von Rotorschaufeln (24; 124) angeordnet ist.
  4. Baugruppe gemäß Anspruch 3, gekennzeichnet dadurch, dass zumindest eine oder jede Injektionsöffnung (34) interne Flügel (40) umfasst, die dazu konfiguriert sind, einen Gegenwirbel (38) zu erzeugen ausgehend von einem Fluss, der die besagte Öffnung (34) durchquert, wobei möglicherweise zumindest eines oder mehrere der Module mehrere Injektionsöffnungen (34) mit internen Flügeln (40) umfasst, die dazu konfiguriert sind, Gegenwirbel (38) zu erzeugen.
  5. Baugruppe gemäß einem der Ansprüche 2 bis 4, gekennzeichnet dadurch, dass zumindest eines oder jedes Injektionsmodul einen Satz Injektionsöffnungen (134; 146; 234; 246; 334; 346) umfasst, die in Bezug zueinander geneigt sind, derart, um einen Gegenwirbel (38; 138; 238) ausgehend von einem Fluss, der von den besagten Injektionsöffnungen des Satzes ausgeht, zu bilden.
  6. Baugruppe gemäß einem der Ansprüche 2 bis 5, gekennzeichnet dadurch, dass zumindest eines oder jedes Injektionsmodul (134; 146; 234; 246; 334; 346) zumindest eine stromaufwärtige Injektionsöffnung (134; 234; 334) und eine stromabwärtige Injektionsöffnung (146; 246; 346) umfasst, die gegeneinander axial und/oder um den Umfang des Gehäuses herum (128; 228; 328) versetzt sind; wobei die besagten Öffnungen (134; 146; 234; 246; 334; 346) in Bezug zueinander in einer axialen Ebene und/oder bezüglich einer Ebene senkrecht zu der Achse der Drehung (114; 214) des Rotors geneigt sind.
  7. Baugruppe gemäß einem der Ansprüche 2 bis 6, gekennzeichnet dadurch, dass zumindest eines oder jedes Injektionsmodul (32; 132; 232; 332) Luftentnahmemittel umfasst, insbesondere eine Luftentnahmeöffnung (148; 348), die möglicherweise stromabwärts der Reihe von Schaufeln (124) angeordnet ist.
  8. Baugruppe gemäß einem der Ansprüche 2 bis 7, gekennzeichnet dadurch, dass zumindest eines oder jedes Injektionsmodul ein Paar von Kanälen (254; 354) aufweist, die jeweils eine Injektionsöffnung (134; 146; 234; 246; 334; 346) stromaufwärts der Schaufeln mit einer Luftentnahmeöffnung (148; 348) stromabwärts der Schaufeln (24; 124) verbinden, wobei die Kanäle (354) von jedem Paar sich vorzugsweise kreuzen.
  9. Baugruppe gemäß einem der Ansprüche 1 bis 8, gekennzeichnet dadurch, dass die Erzeugungsvorrichtung (32; 132; 232; 332) von Gegenwirbeln (38; 138; 238) einen einstückigen Block (252) umfasst, in dem zumindest ein oder mehrere Kanäle (254; 354) geführt sind, wobei der Materialblock (252) sich vorzugsweise über die gesamte axiale Länge der zumindest einen ringförmigen Reihe von Rotorschaufeln (24; 124) erstreckt.
  10. Baugruppe gemäß einem der Ansprüche 1 bis 9, gekennzeichnet dadurch, dass sie Steuermittel zum Erzeugen von Gegenwirbeln (38; 138; 238) in einer alternativen Weise gemäß einer Frequenz umfasst, die eine Funktion der Rotationsgeschwindigkeit des Rotors (12) ist, wobei das Auslösen der Erzeugung eines Gegenwirbels (38; 138; 238) möglicherweise von der Nähe einer Schaufel (24; 124) zu einer Erzeugungsvorrichtung (32; 132; 232; 332) abhängig ist.
  11. Turbomaschine (2) umfassend eine Baugruppe, gekennzeichnet dadurch, dass die Baugruppe gemäß einem der Ansprüche 1 bis 10 ist; wobei vorzugsweise der Rotor (12) mehrere ringförmige Reihen von Schaufeln (24; 124) umfasst und die Baugruppe mehrere Erzeugungsvorrichtungen (32; 132; 232; 332) von Gegenwirbeln (38; 138; 238) aufweist.
  12. Verfahren der Prüfung der Stabilität eines Kompressors (4; 6) einer Turbomaschine (2), insbesondere eines Niederdruckkompressors (4), wobei der Kompressor (4; 6) eine Baugruppe gemäß einem der Ansprüche 1 bis 10 umfasst, wobei das Verfahren die Erzeugung von Gegenwirbeln (28; 138; 238) durch die Erzeugungsvorrichtung (32; 132; 232; 332) von Gegenwirbeln (38; 138; 238) hin zu den Leckagewirbeln (36) und in einer Richtung drehend umfasst, die der Richtung der Drehung der Leckagewirbel (36) entgegengerichtet ist, um sie zu begrenzen.
  13. Verfahren gemäß Anspruch 12, gekennzeichnet dadurch, dass die erzeugten Gegenwirbel (38; 138; 238) diskontinuierlich erzeugt werden, insbesondere bei Annäherung eines Leckagewirbels (36).
  14. Verfahren gemäß einem der Ansprüche 12 oder 13, gekennzeichnet dadurch, dass die erzeugten Gegenwirbel (36) in Richtung stromabwärts injiziert werden, insbesondere hin zu den Leckagewirbeln (36).
EP16174588.0A 2015-06-18 2016-06-15 Gehäuse mit wirbeleinspritzdüsen für kompressor eines axialen turbotriebwerks Active EP3106672B1 (de)

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BE1025077B1 (fr) * 2017-03-22 2018-10-23 Safran Aero Boosters S.A. Capot de turbomachine avec ecran
FR3106653B1 (fr) * 2020-01-23 2022-01-07 Safran Aircraft Engines Ensemble pour une turbomachine
US11608744B2 (en) 2020-07-13 2023-03-21 Honeywell International Inc. System and method for air injection passageway integration and optimization in turbomachinery
CN112065512B (zh) * 2020-08-31 2021-11-16 南京航空航天大学 一种减小间隙泄漏流量的篦齿封严装置

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CN85102135A (zh) * 1985-04-01 1987-01-10 联合工艺公司 有效间隙的控制装置
GB2413158B (en) * 2004-04-13 2006-08-16 Rolls Royce Plc Flow control arrangement
EP1862641A1 (de) * 2006-06-02 2007-12-05 Siemens Aktiengesellschaft Ringförmiger Strömungskanal für eine in Axialrichtung von einem Hauptstrom durchströmbare Strömungsmaschine
DE102008017844A1 (de) * 2008-04-08 2009-10-15 Rolls-Royce Deutschland Ltd & Co Kg Strömungsmaschine mit Fluid-Injektorbaugruppe
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BE1023215B1 (fr) 2016-12-21
EP3106672A1 (de) 2016-12-21
CN106257059B (zh) 2019-07-09
CA2933087A1 (en) 2016-12-18
US20170058687A1 (en) 2017-03-02
RU2016123061A (ru) 2017-12-14
BE1023215A1 (fr) 2016-12-21
CN106257059A (zh) 2016-12-28
US10359054B2 (en) 2019-07-23

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