EP2514975B1 - Flow engine - Google Patents

Flow engine Download PDF

Info

Publication number
EP2514975B1
EP2514975B1 EP12164964.4A EP12164964A EP2514975B1 EP 2514975 B1 EP2514975 B1 EP 2514975B1 EP 12164964 A EP12164964 A EP 12164964A EP 2514975 B1 EP2514975 B1 EP 2514975B1
Authority
EP
European Patent Office
Prior art keywords
annular space
space surface
circumferential
structuring
fluid
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
EP12164964.4A
Other languages
German (de)
French (fr)
Other versions
EP2514975A3 (en
EP2514975A2 (en
Inventor
Erik Johann
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP2514975A2 publication Critical patent/EP2514975A2/en
Publication of EP2514975A3 publication Critical patent/EP2514975A3/en
Application granted granted Critical
Publication of EP2514975B1 publication Critical patent/EP2514975B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/04—Antivibration arrangements
    • F01D25/06—Antivibration arrangements for preventing blade vibration
    • 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
    • F04D29/522—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
    • 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

Definitions

  • the invention relates to a turbomachine.
  • turbomachines are, for example, compressors that are used in jet engines.
  • the blades of compressors tend due to their design and load to a structural vibration excitation.
  • the excitation sources for an undesirable vibration of the blades are of a fluidic nature, wherein the acoustic design of the flow channel can enhance the effect.
  • annulus of the peripheral housing is made substantially smooth, with the rotor moving, for example, with respect to a liner to minimize the annular gap between the tip of the blades and the annulus surface of the housing.
  • the smooth annulus area results in the formation of a stationary splitter vortex at the blade tip which promotes blockage buildup in the blade passage and thereby enhances synchronous (flutter) and non-synchronous blade vibrations.
  • a turbomachine which forms a flow channel between a rotor provided with blades and a peripheral housing.
  • the peripheral housing has a structuring on the inside, which is formed by circumferentially extending grooves. This is intended to influence the boundary layer in the blade tip area.
  • the teaching of claim 1 provides for this purpose to provide a turbomachine having a rotor with a plurality of blades and a peripheral housing surrounding the rotor with a central axis.
  • the peripheral housing or a part connected to this has on the inside an annular space surface which defines an annular space or flow channel of the turbomachine radially outward. It is inventively provided that the annular space surface, at least in a region which peripherally adjacent to a rotor having a circumferentially asymmetric structuring, ie the structuring of the annulus surface is formed circumferentially asymmetric relative to the central axis of the peripheral housing.
  • the annular space surface at least one extending in the circumferential direction portion which provides a symmetrical fracture in an otherwise symmetrical structuring of the annular space surface in the circumferential direction.
  • the annular space surface is symmetrically structured, for example by a periodic sequence of recesses, and this symmetrical structuring is broken in at least one section which extends in the circumferential direction.
  • a recess has a different width or shape than outside the portion that provides the break in symmetry.
  • the considered section is not structured, in particular smooth, while the annular space surface is structured circumferentially symmetrically outside this section.
  • the annulus surface for providing circumferential asymmetry comprises at least one circumferentially extending portion which asymmetrically structures the annulus surface in the circumferential direction, the annulus surface further having at least one symmetric pattern in the circumferential direction.
  • a circumferentially asymmetric structuring is thus superimposed on a circumferentially symmetrical structuring.
  • the flutter stability of the blades is significantly improved. This was demonstrated by the example of compressors in various compressor and engine tests. Due to the improved flutter stability and the working range of a compressor and each compressor stage of the compressor can be extended, and can be increased by suitable choice of the working area of efficiency and weight can be reduced.
  • the circumferentially asymmetric housing contouring according to the invention or the associated advantages may possibly also lead to the number of rotor blades being able to be reduced, which in turn can lead to a lower weight and reduced costs.
  • the non-circumferentially symmetric structuring of the annular space surface also leads to a reduction in the sensitivity of the gap vortex losses with a change in the blade tip gap.
  • the circumferential asymmetry of the structuring of the annular space area required according to the invention represents a greater requirement than the absence of rotational symmetry.
  • a rotational symmetry exists when a rotation around any angle the object represents on itself.
  • a rotational symmetry is already no longer present if the annular space surface is symmetrically structured, for example, has a periodic sequence of elevations and depressions, since for such periodic structuring only rotations by certain angles (corresponding to the period length) reflect the structuring on itself.
  • a circumferential asymmetry is provided, that is, there is no angle other than the 360 ° angle which images the pattern after rotation on itself.
  • a plurality, a symmetry fracture providing sections are formed in the annulus area. However, these are not arranged symmetrically with respect to one another so that they can not be imaged on one another by a rotation at an angle other than 360 °.
  • the annular space surface for providing a circumferential asymmetry on at least one circumferentially extending portion which structurally asymmetric the annular space surface in the circumferential direction, while the annular space surface is otherwise formed smooth in the circumferential direction.
  • the annular space surface is thus basically not structured and rather smooth. Structuring takes place only through the at least one circumferentially extending section. The provision of such a section inherently results in circumferential asymmetry. If several such sections are provided, they are not arranged symmetrically, so that a circumferential asymmetry is likewise provided.
  • the at least one circumferentially extending portion is formed by a recess or depression.
  • the axial extension of the at least one recess is slightly larger than the axial extent of a blade grid of the associated rotor.
  • one or more such recesses or depressions are provided.
  • these are formed circumferentially asymmetrically on the annular space surface, so that overall there is a circumferential asymmetry.
  • the annular space surface to provide a circumferentially asymmetric structuring at least one extending in the circumferential direction portion having a different radius from other sections relative to the central axis.
  • a recess has, for example, the shape of a groove or depression.
  • the structuring of the annulus surface is done in one embodiment by axially aligned structures, for example axially aligned recesses such as e.g. Axial grooves.
  • axially aligned structures for example axially aligned recesses such as e.g. Axial grooves.
  • the structures or recesses are not circumferentially formed circumferentially, but extend over a certain axial length in the axial direction.
  • the axial structures extend in the axial direction at least in the area of the rotor blade grid of the respective rotor, that is to say in the region of the annular space which directly adjoins the rotor blades.
  • the circumferentially asymmetric housing structuring is also provided in axial regions of the peripheral housing, which are located in front of and / or behind a considered blade grid. It may also be provided that each rotor of a considered turbomachine is assigned a different, individual circumferential asymmetry of the housing or its annular space.
  • the structuring of the annular space surface has structures extending in the circumferential direction, for example circumferential grooves which are interrupted, for example, to provide peripheral asymmetry.
  • the peripheral housing itself is circumferentially asymmetric structured, d. H. on the inside of the housing itself asymmetric structures are formed.
  • the peripheral housing is internally connected to a liner or lining ring (liner). Such an insert is often in the area of the front blades of compressors. A circumferentially asymmetric structuring is formed in the insert ring for this case.
  • a structuring of the peripheral housing or of a part connected to the peripheral housing on the inside, such as a deposit ring, is provided, for example, by means of milling or erosion, for example spark erosion, of the housing or of the insert ring.
  • axial structurings such as, for example, axial grooves, can be integrated into the peripheral housing in a simple manner. The additional expense is merely to provide recesses or pockets in the housing or in such separate Einlegeringen.
  • turbomachines such as fans, pumps and fans.
  • the turbomachines can be designed in axial, semi-axial or radial design and basically operated with any gaseous or liquid working medium.
  • the turbomachine according to the invention has at least one rotor which comprises a rotary body with a plurality of rotor blades arranged on the rotary body.
  • a peripheral housing of the turbomachine has on the inside an annular space surface, which is structured circumferentially asymmetric.
  • In training the turbomachine as Compressors each form a rotor and a stator one stage.
  • the circumferentially asymmetric structuring according to the invention can also be realized on a turbomachine which exclusively comprises a rotor.
  • FIG. 1 shows an embodiment of a two-stream jet engine 1, in a conventional manner, a Fansche 10 with a fan as a low-pressure compressor, a medium-pressure compressor 20, a high-pressure compressor 30, a combustion chamber 40, a high-pressure turbine 50, a medium-pressure turbine 60 and a low-pressure turbine 70 on.
  • the Fansche may additionally have booster stages, not shown.
  • the fan constitutes part of the low pressure compressor 10 because its hub near area represents the compressor inlet plane for the jet engine primary flow.
  • the fan stage 10 has a fan housing 15.
  • the fan housing 15 has on the inside an annular space surface 16 which limits a secondary flow channel 4 of the jet engine 1 radially outward.
  • the low-pressure compressor 20 and the high-pressure compressor 30 are surrounded by a peripheral housing 25. This has on the inside an annular space surface 26 which limits the flow channel 3 for the primary flow of the jet engine 1 radially outward. Radially inside the flow channel 3 is connected by corresponding rim surfaces of the rotors and stators of the respective compressor stage or by the hub or with the hub connected elements of the corresponding drive shaft.
  • the flow channel 3 for the primary stream is also referred to as annulus. Accordingly, the surface 26 is an annulus area.
  • the fan stage 10 or the low-pressure compressor has a fan 11, which comprises a rotary body with a plurality of fan blades 12.
  • the fan 11 forms a rotor and the fan blades 12 form blades of the rotor.
  • the medium-pressure compressor 20 rotors 21 (in the FIG. 1 only shown schematically) with a rotary body and blades 22.
  • the rotors 31 each having a rotary body and a Plural on the rotary body arranged blades 32 has (only schematically shown).
  • the high-pressure turbine 50, the medium-pressure turbine 60 and the low-pressure turbine 70 each have stages with a rotor and a stator, wherein the rotor comprises a plurality of rotor blades arranged on a rotary body. To avoid a confusing presentation in the FIG. 1 these rotors are the turbine stages in the FIG. 1 not specified separately.
  • the described components have a common axis of symmetry 2, which represents the central axis for the stators and the housings and the axis of rotation for the rotors of the engine.
  • the present invention provides means that alter the constraints on the inside annulus surface 16, 26, 56 of the respective peripheral housing 15, 25, 55, or associated part, such that the gusset vortex is reduced or completely disappears.
  • circumferentially asymmetric structuring is provided on one or a plurality of the housings 15, 25, 55 or on the inside annular space surface 16, 26, 56, which is described below with reference to FIGS FIGS. 2 to 4 will be explained with reference to two embodiments. In the FIG. 1 the circumferentially asymmetric structuring of the annular space surface 16, 26, 56 can not be seen.
  • jet engine 1 is only one embodiment.
  • the jet engine may also be formed in other ways, for example with a different number of compressor stages and turbine stages and / or as a single-jet engine.
  • the circumferentially asymmetric structuring of the inside annular space surface of a peripheral housing is always considered where a rotor is surrounded by a plurality of blades of a peripheral housing.
  • the in the FIG. 1 shown annular space surfaces 16, 26, 56 are therefore also to be understood only as an example.
  • the FIG. 2 shows a first embodiment of a circumferential asymmetry, which has the inside annular space surface of a peripheral housing 25.
  • the peripheral housing 25 is, for example, the peripheral housing 25 of FIG. 1 .
  • the FIG. 2 shows the peripheral housing 25 in a front-to-rear view in the direction of the central axis 2 of the peripheral housing 25th
  • a liner ring 9 is inserted on the inside.
  • the insert ring 9 has - with respect to the viewing direction of FIG. 2 a front edge 91 and a rear edge 92. Since the insert ring 9 tapers conically towards the rear in the illustrated embodiment, the rear edge 92 has a smaller radial distance from the central axis 2 than the front edge 91.
  • the insert ring 9 forms on its inner side facing the central axis 2 an annular space surface 26a which delimits the adjacent flow channel radially on the outside.
  • the annular space surface is generally formed either by the inside of the housing itself or, if present, by the inside of a deposit ring or other internally mounted part.
  • the insert ring 9 has, apart from a circumferentially extending portion U 6, a symmetrical structuring of the annulus surface 26a, which is provided by a plurality, in the illustrated embodiment by seventy-eight recesses 5, the structure at regular intervals in the circumferential direction of the annular space surface 26a.
  • the recesses 5 each extend in the axial direction and have a length which substantially corresponds to the width of the rotor blades of the associated rotor, not shown.
  • the circumferentially symmetrical housing structuring extends along an axial region of the peripheral housing which peripherally adjoins the associated rotor and which corresponds essentially to the axial extent of the blade lattice of the rotor.
  • the axial recesses 5 may also have a different length, for example, may be shorter, so that they only a fraction of the axial length of the blade lattice of the associated rotor, or may be formed longer, so that they extend into areas of the peripheral housing or of the insert ring, which are located in front of and / or behind the respective blade grid.
  • the axially extending recesses 5 are generated, for example, by internal milling or erosion of the insert ring 9. They can form axial grooves or pockets.
  • structuring according to the recesses 5, if no insert ring 9 is present, can alternatively also be produced on the housing wall of the housing 25 itself.
  • illustrated symmetrical structuring by axial recesses 5 does not extend along the entire circumference of the annular space surface 26a. Rather, a break in symmetry in the form of extending in the circumferential direction U section 6 is provided in which the annular space surface 26 a smooth, that is formed without axial recesses 5. Outside the section 6, the annular space surface 26a is thus structured circumferentially symmetrical, but not in the section 6. The section 6 extends over a defined circumferential angle .DELTA..phi.
  • the structuring of the annular space surface as a whole is without circumferential symmetry, since the structuring can be completely imaged onto itself solely by a rotation through an angle of 360 °.
  • FIG. 2 shown circumferential asymmetry can undergo numerous modifications.
  • a plurality of sections 6 may be provided, in which the annular space surface 26a is not structured.
  • Such portions 6 would be asymmetrically distributed over the circumference, so that the structuring in turn can be imaged on itself only by a rotation through an angle of 360 °.
  • the symmetrical structuring provided by the axial recesses 5 also extends into the section 6, wherein in the section 6, however, an additional circumferentially asymmetric structuring is provided, for example a depression in FIG then the axial recesses 5 are formed.
  • an additional circumferentially asymmetric structuring is provided, for example a depression in FIG then the axial recesses 5 are formed.
  • a symmetrical structuring in the circumferential direction would be superimposed on an asymmetrical structuring in the circumferential direction.
  • a further alternative embodiment provides that only a circumferentially extending section, corresponding to the section 6 of FIG. 2 has at all a structuring, while the annular space surface 26a is formed smooth outside of this section. It would be a reversal of that in the FIG. 2 presented conditions.
  • FIG. 3 shows a perspective view of the inside of a peripheral housing 25, for example, the peripheral housing 25 of FIG. 1 However, but also the peripheral housing 15 or the peripheral housing 55 of the FIG. 1 could be.
  • the peripheral housing 25 forms on the inside an annular space surface 26, which the flow channel 3 (see. FIG. 1 ) bounded radially on the outside.
  • a insert ring 9 ' is arranged on the inside of the peripheral housing 25, on the inside of the peripheral housing 25, a insert ring 9 'is arranged. Where the insert ring 9 'is arranged, its surface 26b facing the flow channel forms the annular space surface of the housing 25.
  • the insert ring 9 ' is concave in a central region 93'. This concave configuration results from the fact that the insert ring 9 'is milled by the blades 22 of the associated rotor.
  • the insert ring 9 ' consists of a comparatively soft material. Such provision of a liner ring 9 'is associated with the advantage of a small annular gap between the blade tip of the blades 22 and the annulus surface 26b.
  • FIG. 4 equals to FIG. 3 , where in the FIG. 4 in addition blades 22 of the associated rotor are shown.
  • a recess 7 is introduced. This is provided, for example, by eroding or milling the insert ring 9 '.
  • the recess 7 may have elongated grooves 71; These arise during the production of the recess 7 and are optional. Outside the recess 7 of the insert ring 9 'is not structured, that is smooth. The recess 7 therefore provides a circumferentially asymmetric structure of the annulus surface 26b.
  • the recess 7 has an axial length x1, which is slightly larger than the axial extent of the portion 93 'of the insert ring 9', which circumferentially adjacent to the blades 22 of the associated rotor.
  • the axial extension x1 of the recess 7 is thus slightly larger than the axial extent of the blade lattice of the associated rotor.
  • the recess 7 further has a length u1 in the circumferential direction U, which corresponds to a circumferential angle ⁇ 1 of the associated circular sector.
  • a plurality of recesses 7 may be formed along the circumference of the insert ring 9 ', wherein such a plurality of recesses are circumferentially arranged asymmetrically.
  • FIG. 5 illustrates the advantages associated with the circumferentially asymmetric design of the annulus area benefits.
  • the circumferential asymetrical design of the annulus area reduces the vibration excitation of blades and thus an improvement in the flutter stability.
  • the compressor pressure ratio is shown as a function of the mass flow.
  • the reference numeral 81 indicates the working line and the point DP indicates a design point under consideration.
  • Reference numeral 82 indicates the stability line, also referred to as the surge line.
  • the map comprises lines 83 of constant speed N.
  • a blade flutter results in a dip in the stability line 82, which in this case is replaced by the flutter line 821.
  • the circumferentially asymmetric structuring according to the invention of the annular space surface results in that the indentation of the stability line 82 is reduced, so that the stability line 82 is replaced by the flutter line 822 in the case of annular space asymmetry.
  • the distance between the flutter line 821 without annular space asymmetry and the flutter line 822 with annular space asymmetry clarifies the advantages associated with the annular space asymmetry according to the invention.
  • the distance between an operating point 81 operating point to the stability line 82 is advantageously increased.
  • the invention is not limited in its embodiment to the embodiments shown above, which are to be understood only as examples.
  • structures may be provided that are configured and arranged in other manners, shapes, and / or locations other than those described in the exemplary embodiments.

Landscapes

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

Description

Die Erfindung betrifft eine Strömungsmaschine. Derartige Strömungsmaschinen sind beispielsweise Verdichter, die in Strahltriebwerken eingesetzt werden.The invention relates to a turbomachine. Such turbomachines are, for example, compressors that are used in jet engines.

Die Laufschaufeln von Verdichtern neigen aufgrund ihrer Bauweise und Belastung zu einer strukturellen Schwingungsanregung. Man unterscheidet dabei zwischen Anregungen aus Schaufelwechselwirkungen ("forced response") und selbstinduziertem Flattern ("flutter"). Dies gilt beispielsweise für Niederdruckverdichter, Mitteldruckverdichter und Hochdruckverdichter eines Strahltriebwerkes, insbesondere für deren Frontlaufschaufeln, einschließlich der Fanstufe eines Strahltriebwerks. Die Anregungsquellen für eine unerwünschte Schwingung der Schaufeln sind strömungstechnischer Natur, wobei die akustische Ausführung des Strömungskanals die Wirkung verstärken kann.The blades of compressors tend due to their design and load to a structural vibration excitation. A distinction is made between suggestions from blade interactions ("forced response") and self-induced flutter ("flutter"). This applies, for example, low-pressure compressor, medium-pressure compressor and high-pressure compressor of a jet engine, in particular for their front blades, including the Fanstufe a jet engine. The excitation sources for an undesirable vibration of the blades are of a fluidic nature, wherein the acoustic design of the flow channel can enhance the effect.

Bei Triebwerksverdichtern sind Ausführungsvarianten bekannt, bei denen der innenseitige Ringraum des Umfangsgehäuses im Wesentlichen glatt ausgeführt ist, wobei der Rotor sich beispielsweise gegenüber einem Einlegering ("liner") bewegt, um den Ringspalt zwischen der Spitze der Laufschaufeln und der Ringraumfläche des Gehäuses zu minimieren. Die glatte Ringraumfläche führt zur Ausbildung eines stationären Spaltwirbels an der Schaufelspitze, der einen Blockageaufbau in der Schaufelpassage fördert und damit synchrone (Flattern) und nicht-synchrone Schaufelschwingungen verstärkt.In engine compressors, embodiments are known in which the inside annulus of the peripheral housing is made substantially smooth, with the rotor moving, for example, with respect to a liner to minimize the annular gap between the tip of the blades and the annulus surface of the housing. The smooth annulus area results in the formation of a stationary splitter vortex at the blade tip which promotes blockage buildup in the blade passage and thereby enhances synchronous (flutter) and non-synchronous blade vibrations.

Es besteht somit die Gefahr, dass insbesondere schnell drehende, schlanke Verdichterschaufeln zu nicht synchronen Schaufelschwingungen oder Schaufelflattern angeregt werden. Gerade dünne Verdichterschaufeln neigen zum Schwingen, da ihre strukturellen Stabilitäts- und Dämpfungseigenschaften relativ gering sind. Dabei ist beispielsweise das so genannte "flutter bite", d. h. eine deutlich reduzierte Flatterstabilität in einem bestimmten Geschwindigkeitsbereich, limitierend bei der Festlegung der Arbeitslinie eines Niederdruckverdichters. Neben den bereits erläuterten Schwingungsanregungen sind durch die nicht-optimale Festlegung der Arbeitslinie Abstriche hinsichtlich Wirkungsgrad und Leistungsdichte gegeben. Der Nachweis ausreichender Flatterstabilität stellt im Übrigen ein sensitives Zulassungskriterium bei Strahltriebwerken dar.There is thus the danger that in particular fast-rotating, slender compressor blades are excited to non-synchronous blade vibrations or blade flutter. Even thin compressor blades tend to vibrate because their structural stability and damping properties are relatively low. Here, for example, the so-called "flutter bite", ie a significantly reduced flutter stability in a certain speed range, limiting in determining the Working line of a low-pressure compressor. In addition to the already described vibration excitations are given by the non-optimal determination of the working line drawbacks in terms of efficiency and power density. In addition, the proof of sufficient flutter stability represents a sensitive approval criterion for jet engines.

Die genannten Probleme ergeben sich in entsprechender Weise auch bei anderen Strömungsmaschinen als Verdichtern, beispielsweise bei Bläsern, Pumpen und Ventilatoren.The problems mentioned arise in a corresponding manner also in other turbomachines as compressors, for example in blowers, pumps and fans.

Aus der DE 10 2007 056 953 A1 ist eine Strömungsmaschine bekannt, die zwischen einem mit Laufschaufeln versehenen Rotor und einem Umfangsgehäuse einen Strömungskanal ausbildet. Das Umfangsgehäuse weist innenseitig eine Strukturierung auf, die durch in Umfangsrichtung verlaufende Nuten gebildet ist. Hierdurch soll die Grenzschicht im Schaufelspitzenbereich beeinflusst werden.From the DE 10 2007 056 953 A1 is a turbomachine is known, which forms a flow channel between a rotor provided with blades and a peripheral housing. The peripheral housing has a structuring on the inside, which is formed by circumferentially extending grooves. This is intended to influence the boundary layer in the blade tip area.

Aus der DE 601 30 577 T2 sind ein Verfahren und eine Vorrichtung zum Verringern von Blattwirbelgeräuschen zwischen Fan und Leiterschaufeln bekanntFrom the DE 601 30 577 T2 For example, a method and apparatus for reducing blade vortex noise between fan and stator blades is known

Es besteht ein Bedarf, Verdichter und andere Strömungsmaschinen bereitzustellen, die sich durch eine verbesserte Flatterstabilität auszeichnen.There is a need to provide compressors and other turbomachines that are characterized by improved flutter stability.

Dieses Problem wird durch die Strömungsmaschine mit den Merkmalen des Anspruchs 1 bzw. durch die Strömungsmaschine mit den Merkmalen des Anspruchs 2 gelöst.This problem is solved by the turbomachine with the features of claim 1 and by the turbomachine with the features of claim 2.

Die Lehre des Anspruchs 1 sieht hierzu vor, eine Strömungsmaschine bereitzustellen, die einen Rotor mit einer Mehrzahl von Laufschaufeln und ein den Rotor umgebendes Umfangsgehäuse mit einer Mittelachse aufweist. Das Umfangsgehäuse oder ein mit diesem verbundenes Teil weist innenseitig eine Ringraumfläche auf, die einen Ringraum bzw. Strömungskanal der Strömungsmaschine radial außen begrenzt. Es ist erfindungsgemäß vorgesehen, dass die Ringraumfläche zumindest in einem Bereich, der umfangsseitig an einen Rotor angrenzt, eine umfangsasymmetrische Strukturierung aufweist, d.h. die Strukturierung der Ringraumfläche ist bezogen auf die Mittelachse des Umfangsgehäuses umfangsasymmetrisch ausgebildet.The teaching of claim 1 provides for this purpose to provide a turbomachine having a rotor with a plurality of blades and a peripheral housing surrounding the rotor with a central axis. The peripheral housing or a part connected to this has on the inside an annular space surface which defines an annular space or flow channel of the turbomachine radially outward. It is inventively provided that the annular space surface, at least in a region which peripherally adjacent to a rotor having a circumferentially asymmetric structuring, ie the structuring of the annulus surface is formed circumferentially asymmetric relative to the central axis of the peripheral housing.

Dabei weist gemäß einer ersten Alternative des Anspruchs 1 die Ringraumfläche mindestens einen sich in Umfangsrichtung erstreckenden Abschnitt auf, der in einer ansonsten symmetrischen Strukturierung der Ringraumfläche in Umfangsrichtung einen Symmetriebruch bereitstellt. Mit anderen Worten ist die Ringraumfläche symmetrisch strukturiert, beispielweise durch eine periodische Abfolge von Aussparungen, und ist diese symmetrische Strukturierung in zumindest einem Abschnitt, der sich in Umfangsrichtung erstreckt, gebrochen. Beispielsweise weist eine Aussparung eine andere Breite oder eine andere Form auf als außerhalb des Abschnitts, der den Symmetriebruch bereitstellt. Auch kann vorgesehen sein, dass der betrachtete Abschnitt nicht strukturiert, insbesondere glatt ausgebildet ist, während die Ringraumfläche außerhalb dieses Abschnittes umfangssymmetrisch strukturiert ist.In this case, according to a first alternative of claim 1, the annular space surface at least one extending in the circumferential direction portion which provides a symmetrical fracture in an otherwise symmetrical structuring of the annular space surface in the circumferential direction. In other words, the annular space surface is symmetrically structured, for example by a periodic sequence of recesses, and this symmetrical structuring is broken in at least one section which extends in the circumferential direction. For example, a recess has a different width or shape than outside the portion that provides the break in symmetry. It can also be provided that the considered section is not structured, in particular smooth, while the annular space surface is structured circumferentially symmetrically outside this section.

Gemäß einer zweiten Alternative des Anspruchs 1 weist die Ringraumfläche zur Bereitstellung einer Umfangsasymmetrie mindestens einen sich in Umfangsrichtung erstreckenden Abschnitt auf, der die Ringraumfläche in Umfangsrichtung asymmetrisch strukturiert, wobei die Ringraumfläche in Umfangsrichtung des Weiteren mindestens eine symmetrische Strukturierung aufweist. Bei dieser Ausführungsvariante wird somit eine umfangsasymmetrische Strukturierung einer umfangssymmetrischen Strukturierung überlagert.According to a second alternative of claim 1, the annulus surface for providing circumferential asymmetry comprises at least one circumferentially extending portion which asymmetrically structures the annulus surface in the circumferential direction, the annulus surface further having at least one symmetric pattern in the circumferential direction. In this embodiment, a circumferentially asymmetric structuring is thus superimposed on a circumferentially symmetrical structuring.

Durch die umfangsasymmetrische Ausbildung der Ringraumfläche wird die Flatterstabilität der Laufschaufeln deutlich verbessert. Dies konnte am Beispiel von Verdichtern in verschiedenen Verdichter- und Triebwerkstests nachgewiesen werden. Durch die verbesserte Flatterstabilität kann auch der Arbeitsbereich eines Verdichters und jeder Verdichterstufe des Verdichters erweitert werden, wobei durch geeignete Wahl des Arbeitsbereichs der Wirkungsgrad gesteigert und Gewicht reduziert werden kann. Die erfindungsgemäße umfangsasymmetrische Gehäusekonturierung bzw. die damit verbundenen Vorteile können ggf. auch dazu führen, dass die Anzahl der Laufschaufeln reduziert werden kann, was wiederum zu einem geringeren Gewicht und reduzierten Kosten führen kann. Die nicht umfangssymmetrische Strukturierung der Ringraumfläche führt des Weiteren zu einer Reduzierung der Sensitivität der Spaltwirbelverluste bei einer Änderung des Schaufelspitzenspaltes.Due to the circumferential asymmetric design of the annular space surface, the flutter stability of the blades is significantly improved. This was demonstrated by the example of compressors in various compressor and engine tests. Due to the improved flutter stability and the working range of a compressor and each compressor stage of the compressor can be extended, and can be increased by suitable choice of the working area of efficiency and weight can be reduced. The circumferentially asymmetric housing contouring according to the invention or the associated advantages may possibly also lead to the number of rotor blades being able to be reduced, which in turn can lead to a lower weight and reduced costs. The non-circumferentially symmetric structuring of the annular space surface also leads to a reduction in the sensitivity of the gap vortex losses with a change in the blade tip gap.

Es wird darauf hingewiesen, dass die erfindungsgemäß verlangte Umfangsasymmetrie der Strukturierung der Ringraumfläche eine stärkere Forderung darstellt als das Fehlen einer Rotationssymmetrie. Eine Rotationssymmetrie liegt vor, wenn eine Drehung um jeden beliebigen Winkel das Objekt auf sich selbst abbildet. Eine Rotationssymmetrie ist bereits dann nicht mehr gegeben, wenn die Ringraumfläche symmetrisch strukturiert ist, beispielsweise eine periodische Abfolge von Erhöhungen und Vertiefungen aufweist, da für eine solche periodische Strukturierung nur Drehungen um bestimmte Winkel (entsprechend der Periodenlänge) die Strukturierung auf sich selbst abbilden. Erfindungsgemäß ist eine Umfangsasymmetrie vorgesehen, d. h., es gibt keinen Winkel außer dem 360°-Winkel, der die Strukturierung nach einer Drehung auf sich selbst abbildet.It should be noted that the circumferential asymmetry of the structuring of the annular space area required according to the invention represents a greater requirement than the absence of rotational symmetry. A rotational symmetry exists when a rotation around any angle the object represents on itself. A rotational symmetry is already no longer present if the annular space surface is symmetrically structured, for example, has a periodic sequence of elevations and depressions, since for such periodic structuring only rotations by certain angles (corresponding to the period length) reflect the structuring on itself. According to the invention, a circumferential asymmetry is provided, that is, there is no angle other than the 360 ° angle which images the pattern after rotation on itself.

Dabei kann auch vorgesehen sein, dass mehrere, einen Symmetriebruch bereitstellende Abschnitte in der Ringraumfläche ausgebildet sind. Diese sind aber zueinander nicht symmetrisch angeordnet, so dass sie nicht durch eine Drehung um einen Winkel ungleich 360° aufeinander abgebildet werden können.It can also be provided that a plurality, a symmetry fracture providing sections are formed in the annulus area. However, these are not arranged symmetrically with respect to one another so that they can not be imaged on one another by a rotation at an angle other than 360 °.

Gemäß Anspruch 2 weist die Ringraumfläche zur Bereitstellung einer Umfangsasymmetrie mindestens einen sich in Umfangsrichtung erstreckenden Abschnitt auf, der die Ringraumfläche in Umfangsrichtung asymmetrisch strukturiert, während die Ringraumfläche ansonsten in Umfangsrichtung glatt ausgebildet ist. Bei dieser Ausführungsvariante ist die Ringraumfläche somit grundsätzlich nicht strukturiert und vielmehr glatt ausgebildet. Eine Strukturierung erfolgt erst durch den mindestens einen sich in Umfangsrichtung erstreckenden Abschnitt. Die Bereitstellung eines solchen Abschnittes führt inhärent zu einer Umfangsasymmetrie. Sofern mehrere solche Abschnitte bereitgestellt werden, sind sie nicht symmetrisch angeordnet, so dass ebenfalls eine Umfangsasymmetrie bereitgestellt wird. Der mindestens eine sich in Umfangsrichtung erstreckenden Abschnitt ist durch eine Aussparung oder Vertiefung gebildet. Die axiale Erstreckung der wenigstens einen Aussparung ist geringfügig größer als die axiale Erstreckung eines Schaufelgitters des zugeordneten Rotors. Dabei sind eine oder mehrere solcher Aussparungen oder Vertiefungen vorgesehen. Im Falle mehrerer Aussparungen oder Vertiefungen sind diese umfangsasymmetrisch an der Ringraumfläche ausgebildet, damit insgesamt eine Umfangsasymmetrie vorliegt.According to claim 2, the annular space surface for providing a circumferential asymmetry on at least one circumferentially extending portion which structurally asymmetric the annular space surface in the circumferential direction, while the annular space surface is otherwise formed smooth in the circumferential direction. In this embodiment, the annular space surface is thus basically not structured and rather smooth. Structuring takes place only through the at least one circumferentially extending section. The provision of such a section inherently results in circumferential asymmetry. If several such sections are provided, they are not arranged symmetrically, so that a circumferential asymmetry is likewise provided. The at least one circumferentially extending portion is formed by a recess or depression. The axial extension of the at least one recess is slightly larger than the axial extent of a blade grid of the associated rotor. In this case, one or more such recesses or depressions are provided. In the case of a plurality of recesses or depressions, these are formed circumferentially asymmetrically on the annular space surface, so that overall there is a circumferential asymmetry.

In einer Ausgestaltung der Erfindung ist vorgesehen, dass die Ringraumfläche zur Bereitstellung einer umfangsasymmetrischen Strukturierung mindestens einen sich in Umfangsrichtung erstreckenden Abschnitt aufweist, der bezogen auf die Mittelachse einen von anderen Abschnitten abweichenden Radius aufweist.In one embodiment of the invention, it is provided that the annular space surface to provide a circumferentially asymmetric structuring at least one extending in the circumferential direction portion having a different radius from other sections relative to the central axis.

Eine Aussparung besitzt beispielsweise die Form einer Nut oder Vertiefung.A recess has, for example, the shape of a groove or depression.

Die Strukturierung der Ringraumfläche erfolgt in einer Ausgestaltung durch axial ausgerichtete Strukturen, beispielsweise axial ausgerichtete Aussparungen wie z.B. Axialnuten. Dies bedeutet, dass die Strukturen bzw. Aussparungen nicht in Umfangsrichtung umlaufend ausgebildet sind, sondern sich über eine bestimmte axiale Länge in axialer Richtung erstrecken. Insbesondere ist dabei vorgesehen, dass sich die axialen Strukturen zumindest im Bereich des Laufschaufelgitters des jeweiligen Rotors in axialer Richtung erstrecken, also in dem Bereich des Ringraums, der unmittelbar an die Laufschaufeln angrenzt. Es kann jedoch ebenfalls vorgesehen sein, dass die umfangsasymmetrische Gehäusestrukturierung auch in axialen Bereichen des Umfangsgehäuses bereitgestellt wird, die vor und/oder hinter einem betrachteten Laufschaufelgitter liegen. Auch kann vorgesehen sein, dass jedem Rotor einer betrachteten Strömungsmaschine eine andere, individuelle Umfangsasymmetrie des Gehäuses bzw. dessen Ringraums zugeordnet ist.The structuring of the annulus surface is done in one embodiment by axially aligned structures, for example axially aligned recesses such as e.g. Axial grooves. This means that the structures or recesses are not circumferentially formed circumferentially, but extend over a certain axial length in the axial direction. In particular, it is provided that the axial structures extend in the axial direction at least in the area of the rotor blade grid of the respective rotor, that is to say in the region of the annular space which directly adjoins the rotor blades. However, it can also be provided that the circumferentially asymmetric housing structuring is also provided in axial regions of the peripheral housing, which are located in front of and / or behind a considered blade grid. It may also be provided that each rotor of a considered turbomachine is assigned a different, individual circumferential asymmetry of the housing or its annular space.

In Ausführungsvarianten der vorliegenden Erfindung kann des weiteren vorgesehen sein, dass die Strukturierung der Ringraumfläche in Umfangsrichtung verlaufende Strukturen aufweist, beispielsweise Umfangsnuten, die zur Bereitstellung einer Umfangsasymmetrie beispielsweise unterbrochen sind.In embodiments of the present invention, it may further be provided that the structuring of the annular space surface has structures extending in the circumferential direction, for example circumferential grooves which are interrupted, for example, to provide peripheral asymmetry.

Die Bereitstellung einer Strukturierung der innenseitigen Ringraumfläche des Umfangsgehäuses kann auf vielfältige Weise erfolgen. In einer Ausführungsvariante ist das Umfangsgehäuse selbst umfangsasymmetrisch strukturiert, d. h. auf der Innenseite des Gehäuses selbst sind asymmetrische Strukturen ausgebildet. Gemäß einer alternativen Ausführungsvariante ist das Umfangsgehäuse innenseitig mit einem Einlegering oder Auskleidungsring verbunden (liner). Ein solcher Einsatz befindet sich häufig im Bereich der Frontlaufschaufeln von Verdichtern. Eine umfangsasymmetrische Strukturierung ist für diesen Fall in dem Einlegering ausgebildet.The provision of a structuring of the inside annular space surface of the peripheral housing can be done in many ways. In one embodiment, the peripheral housing itself is circumferentially asymmetric structured, d. H. on the inside of the housing itself asymmetric structures are formed. According to an alternative embodiment, the peripheral housing is internally connected to a liner or lining ring (liner). Such an insert is often in the area of the front blades of compressors. A circumferentially asymmetric structuring is formed in the insert ring for this case.

Eine Strukturierung des Umfangsgehäuses oder eines mit dem Umfangsgehäuse innenseitig verbundenen Teils wie eines Einlegerings wird beispielsweise mittels eines Ausfräsens oder eines Erodierens, beispielsweise Funkenerodierens, des Gehäuses oder des Einlegerings bereitgestellt. Dabei können insbesondere axiale Strukturierungen wie z.B. Axialnute in einfacher Weise in das Umfangsgehäuse integriert werden. Der zusätzliche Aufwand besteht lediglich darin, Aussparungen oder Taschen im Gehäuse oder in solchen separaten Einlegeringen bereitzustellen.A structuring of the peripheral housing or of a part connected to the peripheral housing on the inside, such as a deposit ring, is provided, for example, by means of milling or erosion, for example spark erosion, of the housing or of the insert ring. In particular, axial structurings, such as, for example, axial grooves, can be integrated into the peripheral housing in a simple manner. The additional expense is merely to provide recesses or pockets in the housing or in such separate Einlegeringen.

Die Erfindung wird nachfolgend unter Bezugnahme auf die Figuren der Zeichnung anhand mehrerer Ausführungsbeispiele näher erläutert. Es zeigen:

  • Figur 1 ein Ausführungsbeispiel eines Strahltriebwerks, wobei mindestens eine Verdichterstufe des Strahltriebwerkes eine umfangsasymmetrische Gehäusestrukturierung aufweist;
  • Figur 2 in einer Ansicht von vorne ein erstes Ausführungsbeispiel einer umfangsasymmetrischen Strukturierung der Ringraumfläche eines mit einem Einlegering versehenen Verdichtergehäuses;
  • Figur 3 in perspektivischer Darstellung ein zweites Ausführungsbeispiel einer umfangsasymmetrischen Strukturierung der Ringraumfläche eines mit einem Einlegering versehenen Verdichtergehäuses, wobei lediglich ein Teilbereich des Umfangsgehäuses dargestellt ist;
  • Figur 4das Ausführungsbeispiel der Figur 3, wobei zusätzlich Laufschaufeln eines Rotors des Verdichters dargestellt sind; und
  • Figur 5ein Verdichterkennfeld, das den Massenstrom durch einen Verdichter in Abhängigkeit vom Verdichterdruckverhältnis zeigt, wobei der Einfluss einer umfangsasymmetrischen Strukturierung der Ringraumfläche auf die Stabilitätslinie des Kennfeldes dargestellt ist.
The invention will be explained in more detail with reference to the figures of the drawing with reference to several embodiments. Show it:
  • FIG. 1 an embodiment of a jet engine, wherein at least one compressor stage of the jet engine has a circumferentially asymmetric housing structuring;
  • FIG. 2 in a front view of a first embodiment of a circumferentially asymmetric structuring of the annular space surface of a bearing housing provided with a compressor housing;
  • FIG. 3 a perspective view of a second embodiment of a circumferentially asymmetric structuring of the annular space surface of a bearing housing provided with a compressor housing, wherein only a portion of the peripheral housing is shown;
  • FIG. 4 the embodiment of FIG. 3 in addition blades of a rotor of the compressor are shown; and
  • FIG. 5 a compressor map showing the mass flow through a compressor as a function of the compressor pressure ratio, the influence of a circumferentially asymmetric structuring of the annulus surface is shown on the stability line of the map.

Die Erfindung wird nachfolgend beispielhaft anhand von Verdichterstufen eines Strahltriebwerks beschrieben. Die Prinzipien der vorliegenden Erfindung gelten jedoch in gleicher Weise wie für andere Strömungsmaschinen wie beispielsweise Bläser, Pumpen und Ventilatoren. Die Strömungsmaschinen können in axialer, halbaxialer oder radialer Bauart ausgeführt sein und grundsätzlich mit einem beliebigen gasförmigen oder flüssigen Arbeitsmedium betrieben werden.The invention will be described below by way of example with reference to compressor stages of a jet engine. However, the principles of the present invention apply in the same way as for other turbomachines such as fans, pumps and fans. The turbomachines can be designed in axial, semi-axial or radial design and basically operated with any gaseous or liquid working medium.

Die erfindungsgemäße Strömungsmaschine weist mindestens einen Rotor auf, der einen Drehkörper mit einer Mehrzahl an dem Drehkörper angeordneter Laufschaufeln umfasst. Ein Umfangsgehäuse der Strömungsmaschine besitzt innenseitig eine Ringraumfläche, die umfangsasymmetrisch strukturiert ist. Bei Ausbildung der Strömungsmaschine als Verdichter bilden jeweils ein Rotor und ein Stator eine Stufe. Hierbei handelt es sich jedoch lediglich um ein Ausführungsbeispiel der vorliegenden Erfindung. Die erfindungsgemäße umfangsasymmetrische Strukturierung kann ebenso an einer Strömungsmaschine realisiert sein, die ausschließlich einen Rotor umfasst.The turbomachine according to the invention has at least one rotor which comprises a rotary body with a plurality of rotor blades arranged on the rotary body. A peripheral housing of the turbomachine has on the inside an annular space surface, which is structured circumferentially asymmetric. In training the turbomachine as Compressors each form a rotor and a stator one stage. However, this is only an embodiment of the present invention. The circumferentially asymmetric structuring according to the invention can also be realized on a turbomachine which exclusively comprises a rotor.

Die Figur 1 zeigt ein Ausführungsbeispiel eines Zweistrom-Strahltriebwerkes 1, das in an sich bekannter Weise eine Fanstufe 10 mit einem Fan als Niedrigdruckverdichter, einen Mitteldruckverdichter 20, einen Hochdruckverdichter 30, eine Brennkammer 40, eine Hochdruckturbine 50, eine Mitteldruckturbine 60 und eine Niederdruckturbine 70 auf. Die Fanstufe kann dabei zusätzlich nicht dargestellte Booster-Stufen aufweisen. Der Fan stellt einen Teil des Niedrigdruckverdichters 10 dar, da sein Nabennahbereich die Verdichtereintrittsebene für den Primärstrom des Strahltriebwerks darstellt.The FIG. 1 shows an embodiment of a two-stream jet engine 1, in a conventional manner, a Fanstufe 10 with a fan as a low-pressure compressor, a medium-pressure compressor 20, a high-pressure compressor 30, a combustion chamber 40, a high-pressure turbine 50, a medium-pressure turbine 60 and a low-pressure turbine 70 on. The Fanstufe may additionally have booster stages, not shown. The fan constitutes part of the low pressure compressor 10 because its hub near area represents the compressor inlet plane for the jet engine primary flow.

Die Fanstufe 10 weist ein Fangehäuse 15. Das Fangehäuse 15 weist innenseitig eine Ringraumfläche 16 auf, die einen Sekundärstromkanal 4 des Strahltriebwerks 1 radial außen begrenzt.The fan stage 10 has a fan housing 15. The fan housing 15 has on the inside an annular space surface 16 which limits a secondary flow channel 4 of the jet engine 1 radially outward.

Der Niederdruckverdichter 20 und der Hochdruckverdichter 30 sind von einem Umfangsgehäuse 25 umgeben. Dieses weist innenseitig eine Ringraumfläche 26 auf, die den Strömungskanal 3 für den Primärstrom des Strahltriebwerks 1 radial außen begrenzt. Radial innen ist der Strömungskanal 3 durch entsprechende Kranzoberflächen der Rotoren und Statoren der jeweiligen Verdichterstufe bzw. durch die Nabe oder mit der Nabe verbundene Elemente der entsprechenden Antriebswelle verbunden. Der Strömungskanal 3 für den Primärstrom wird auch als Ringraum bezeichnet. Dementsprechend stellt die Fläche 26 eine Ringraumfläche dar.The low-pressure compressor 20 and the high-pressure compressor 30 are surrounded by a peripheral housing 25. This has on the inside an annular space surface 26 which limits the flow channel 3 for the primary flow of the jet engine 1 radially outward. Radially inside the flow channel 3 is connected by corresponding rim surfaces of the rotors and stators of the respective compressor stage or by the hub or with the hub connected elements of the corresponding drive shaft. The flow channel 3 for the primary stream is also referred to as annulus. Accordingly, the surface 26 is an annulus area.

Auch im Bereich der Turbinen 50, 60, 70 ist ein Umfangsgehäuse 55 vorgesehen, das eine innenseitige Ringraumfläche 56 ausbildet.Also in the area of the turbines 50, 60, 70, a circumferential housing 55 is provided, which forms an inside annular space surface 56.

Die Fanstufe 10 bzw. der Niederdruckverdichter weist einen Fan 11 auf, der einen Drehkörper mit einer Mehrzahl von Fanschaufeln 12 umfasst. Der Fan 11 bildet einen Rotor und die Fanschaufeln 12 bilden Laufschaufeln des Rotors. Ebenso weist der Mitteldruckverdichter 20 Rotoren 21 (in der Figur 1 nur schematisch dargestellt) mit einem Drehkörper und Laufschaufeln 22 auf. Entsprechendes gilt für den Hochdruckverdichter 30, der Rotoren 31 mit jeweils einem Drehkörper und einer Mehrzahl an dem Drehkörper angeordneter Laufschaufeln 32 aufweist (nur schematisch dargestellt).The fan stage 10 or the low-pressure compressor has a fan 11, which comprises a rotary body with a plurality of fan blades 12. The fan 11 forms a rotor and the fan blades 12 form blades of the rotor. Likewise, the medium-pressure compressor 20 rotors 21 (in the FIG. 1 only shown schematically) with a rotary body and blades 22. The same applies to the high-pressure compressor 30, the rotors 31 each having a rotary body and a Plural on the rotary body arranged blades 32 has (only schematically shown).

In entsprechender Weise weisen die Hochdruckturbine 50, die Mitteldruckturbine 60 und die Niederdruckturbine 70 jeweils Stufen mit einem Rotor und einem Stator auf, wobei der Rotor eine Mehrzahl an einem Drehkörper angeordneter Laufschaufeln umfasst. Zur Vermeidung einer unübersichtlichen Darstellung in der Figur 1 sind diese Rotoren der Turbinenstufen in der Figur 1 nicht gesondert bezeichnet.Similarly, the high-pressure turbine 50, the medium-pressure turbine 60 and the low-pressure turbine 70 each have stages with a rotor and a stator, wherein the rotor comprises a plurality of rotor blades arranged on a rotary body. To avoid a confusing presentation in the FIG. 1 these rotors are the turbine stages in the FIG. 1 not specified separately.

Die beschriebenen Komponenten weisen eine gemeinsame Symmetrieachse 2 auf, die die Mittelachse für die Statoren und die Gehäuse und die Rotationsachse für die Rotoren des Triebwerks darstellt.The described components have a common axis of symmetry 2, which represents the central axis for the stators and the housings and the axis of rotation for the rotors of the engine.

Für sämtliche in der Figur 1 betrachteten Rotoren 11, 21, 31 der Verdichter- und Kompressorstufen 10, 20, 30, 50, 60, 70 gilt, dass eine hohe Flatterstabilität anzustreben ist. Dies gilt in besonderem Maße für die jeweiligen Frontlaufschaufeln der einzelnen Verdichterstufen 10, 20, 30, abgeschwächt jedoch auch für die Laufschaufeln der anderen Rotoren der jeweiligen Verdichterstufen 10, 20, 30. Insbesondere ist die Ausbildung eines Spaltwirbels an der Schaufelspitze der jeweiligen Laufschaufeln 12, 22, 32, der zu einer Schaufelschwingung führt, zu vermeiden oder zu reduzieren. Der Spaltwirbel führt dabei zu einer strömungstechnisch unvorteilhaften Ausprägung für Schaufelflattern.For all in the FIG. 1 considered rotors 11, 21, 31 of the compressor and compressor stages 10, 20, 30, 50, 60, 70 is considered that a high flutter stability is desirable. This is particularly true for the respective front blades of the individual compressor stages 10, 20, 30, but also attenuated for the blades of the other rotors of the respective compressor stages 10, 20, 30. In particular, the formation of a gap vortex at the blade tip of the respective blades 12, 22, 32, which leads to a blade vibration, to avoid or reduce. The gap vortex leads to a fluidically unfavorable expression for blade flutter.

Die vorliegende Erfindung stellt Mittel bereit, die die Randbedingungen an der innenseitigen Ringraumfläche 16, 26, 56 des jeweiligen Umfangsgehäuses 15, 25, 55 oder eines damit verbundenen Teils derart ändern, dass der Spaltwirbel reduziert wird oder vollständig verschwindet. Hierzu ist an einem oder an einer Mehrzahl der Gehäuse 15, 25, 55 bzw. an deren innenseitiger Ringraumfläche 16, 26, 56 eine umfangsasymmetrische Strukturierung vorgesehen, die nachfolgend anhand der Figuren 2 bis 4 anhand zweier Ausführungsbeispiele erläutert wird. In der Figur 1 ist die umfangsasymmetrische Strukturierung der Ringraumfläche 16, 26, 56 nicht zu erkennen.The present invention provides means that alter the constraints on the inside annulus surface 16, 26, 56 of the respective peripheral housing 15, 25, 55, or associated part, such that the gusset vortex is reduced or completely disappears. For this purpose, circumferentially asymmetric structuring is provided on one or a plurality of the housings 15, 25, 55 or on the inside annular space surface 16, 26, 56, which is described below with reference to FIGS FIGS. 2 to 4 will be explained with reference to two embodiments. In the FIG. 1 the circumferentially asymmetric structuring of the annular space surface 16, 26, 56 can not be seen.

Das in der Figur 1 dargestellte Strahltriebwerk 1 stellt lediglich ein Ausführungsbeispiel dar. Das Strahltriebwerk kann auch in anderer Weise, beispielsweise mit einer anderen Anzahl von Verdichterstufen und Turbinenstufen und/oder als Einstromtriebwerk ausgebildet sein. Die nachfolgend erläuterte umfangsasymmetrische Strukturierung der innenseitigen Ringraumfläche eines Umfangsgehäuses kommt immer dort in Betracht, wo ein Rotor mit einer Mehrzahl von Laufschaufeln von einem Umfangsgehäuse umgeben wird. Die in der Figur 1 dargestellten Ringraumflächen 16, 26, 56 sind somit ebenfalls nur beispielhaft zu verstehen.That in the FIG. 1 illustrated jet engine 1 is only one embodiment. The jet engine may also be formed in other ways, for example with a different number of compressor stages and turbine stages and / or as a single-jet engine. The circumferentially asymmetric structuring of the inside annular space surface of a peripheral housing is always considered where a rotor is surrounded by a plurality of blades of a peripheral housing. The in the FIG. 1 shown annular space surfaces 16, 26, 56 are therefore also to be understood only as an example.

Die Figur 2 zeigt ein erstes Ausführungsbeispiel für eine Umfangsasymmetrie, die die innenseitige Ringraumfläche eines Umfangsgehäuses 25 aufweist. Bei dem Umfangsgehäuse 25 handelt es sich beispielsweise um das Umfangsgehäuse 25 der Figur 1. Die Figur 2 zeigt das Umfangsgehäuse 25 in einer Ansicht von vorne nach hinten in Richtung der Mittelachse 2 des Umfangsgehäuses 25.The FIG. 2 shows a first embodiment of a circumferential asymmetry, which has the inside annular space surface of a peripheral housing 25. The peripheral housing 25 is, for example, the peripheral housing 25 of FIG. 1 , The FIG. 2 shows the peripheral housing 25 in a front-to-rear view in the direction of the central axis 2 of the peripheral housing 25th

In das Umfangsgehäuse 25 ist innenseitig ein Einlegering 9 eingebracht. Der Einlegering 9 weist - bezogen auf die Betrachtungsrichtung der Figur 2 - eine vordere Kante 91 und eine hintere Kante 92 auf. Da der Einlegering 9 sich im dargestellten Ausführungsbeispiel konisch nach hinten verjüngt, weist die hintere Kante 92 einen geringeren radialen Abstand zur Mittelachse 2 auf als die vordere Kante 91.In the peripheral housing 25, a liner ring 9 is inserted on the inside. The insert ring 9 has - with respect to the viewing direction of FIG. 2 a front edge 91 and a rear edge 92. Since the insert ring 9 tapers conically towards the rear in the illustrated embodiment, the rear edge 92 has a smaller radial distance from the central axis 2 than the front edge 91.

Der Einlegering 9 bildet an seiner der Mittelachse 2 zugewandten Innenseite eine Ringraumfläche 26a aus, die den angrenzenden Strömungskanal radial außen begrenzt. Die Ringraumfläche wird allgemein entweder durch die Innenseite des Gehäuses selbst oder, sofern vorhanden, durch die Innenseite eines Einlegerings oder eines anderen innenseitig angebrachten Teils gebildet.The insert ring 9 forms on its inner side facing the central axis 2 an annular space surface 26a which delimits the adjacent flow channel radially on the outside. The annular space surface is generally formed either by the inside of the housing itself or, if present, by the inside of a deposit ring or other internally mounted part.

Der Einlegering 9 weist, abgesehen von einem sich in Umfangsrichtung U erstreckenden Abschnitt 6, eine symmetrische Strukturierung der Ringraumfläche 26a auf, die durch eine Mehrzahl, im dargestellten Ausführungsbeispiel durch achtundsiebzig Aussparungen 5 bereitgestellt wird, die in regelmäßigem Abstand in Umfangsrichtung die Ringraumfläche 26a strukturieren. Die Aussparungen 5 verlaufen jeweils in axialer Richtung und weisen eine Länge auf, die im Wesentlichen der Breite der Laufschaufeln des zugehörigen, nicht dargestellten Rotors entsprechen. Mit anderen Worten erstreckt sich die umfangssymmetrische Gehäusestrukturierung entlang eines axialen Bereichs des Umfangsgehäuses, der umfangsseitig an dem zugehörigen Rotor angrenzt und der im Wesentlichen der axialen Erstreckung des Schaufelgitters des Rotors entspricht.The insert ring 9 has, apart from a circumferentially extending portion U 6, a symmetrical structuring of the annulus surface 26a, which is provided by a plurality, in the illustrated embodiment by seventy-eight recesses 5, the structure at regular intervals in the circumferential direction of the annular space surface 26a. The recesses 5 each extend in the axial direction and have a length which substantially corresponds to the width of the rotor blades of the associated rotor, not shown. In other words, the circumferentially symmetrical housing structuring extends along an axial region of the peripheral housing which peripherally adjoins the associated rotor and which corresponds essentially to the axial extent of the blade lattice of the rotor.

Allerdings wird darauf hingewiesen, dass die axialen Aussparungen 5 auch eine andere Länge aufweisen können, beispielsweise kürzer ausgebildet sein können, so dass sie nur einem Bruchteil der axialen Länge des Schaufelgitters des zugehörigen Rotors entsprechen, oder länger ausgebildet sein können, so dass sie sich in Bereiche des Umfangsgehäuses bzw. des Einlegerings erstrecken, die vor und/oder hinter dem jeweiligen Schaufelgitter liegen.However, it should be noted that the axial recesses 5 may also have a different length, for example, may be shorter, so that they only a fraction of the axial length of the blade lattice of the associated rotor, or may be formed longer, so that they extend into areas of the peripheral housing or of the insert ring, which are located in front of and / or behind the respective blade grid.

Die axial verlaufenden Aussparungen 5 werden beispielsweise durch innenseitiges Fräsen oder Erodieren des Einlegerings 9 erzeugt. Sie können Axialnuten oder Taschen bilden.The axially extending recesses 5 are generated, for example, by internal milling or erosion of the insert ring 9. They can form axial grooves or pockets.

Es wird darauf hingewiesen, dass eine Strukturierung entsprechend den Aussparungen 5, sofern kein Einlegering 9 vorhanden ist, alternativ auch an der Gehäusewandung des Gehäuses 25 selbst erzeugt werden kann.It should be noted that structuring according to the recesses 5, if no insert ring 9 is present, can alternatively also be produced on the housing wall of the housing 25 itself.

Die in der Figur 2 dargestellte symmetrische Strukturierung durch axiale Aussparungen 5 verläuft allerdings nicht entlang des gesamten Umfangs der Ringraumfläche 26a. Vielmehr ist ein Symmetriebruch in Form des sich in Umfangsrichtung U erstreckenden Abschnitts 6 bereitgestellt, in dem die Ringraumfläche 26a glatt, d. h. ohne axiale Aussparungen 5 ausgebildet ist. Außerhalb des Abschnitts 6 ist die Ringraumfläche 26a somit umfangssymmetrisch strukturiert, nicht jedoch in dem Abschnitt 6. Der Abschnitt 6 erstreckt sich dabei über einen definierten Umfangswinkel Δϕ.The in the FIG. 2 However, illustrated symmetrical structuring by axial recesses 5 does not extend along the entire circumference of the annular space surface 26a. Rather, a break in symmetry in the form of extending in the circumferential direction U section 6 is provided in which the annular space surface 26 a smooth, that is formed without axial recesses 5. Outside the section 6, the annular space surface 26a is thus structured circumferentially symmetrical, but not in the section 6. The section 6 extends over a defined circumferential angle .DELTA..phi.

Durch den nicht strukturierten Bereich 6 ist die Strukturierung der Ringraumfläche insgesamt ohne Umfangssymmetrie, da die Strukturierung insgesamt ausschließlich durch eine Drehung um einen Winkel von 360° auf sich selbst abgebildet werden kann.Due to the non-structured region 6, the structuring of the annular space surface as a whole is without circumferential symmetry, since the structuring can be completely imaged onto itself solely by a rotation through an angle of 360 °.

Die in der Figur 2 dargestellte Umfangsasymmetrie kann zahlreiche Abwandlungen erfahren. Beispielsweise können in einer ersten alternativen Ausgestaltung mehrere Abschnitte 6 vorgesehen sein, in denen die Ringraumfläche 26a nicht strukturiert ist. Solche Abschnitte 6 würden dabei asymmetrisch über den Umfang verteilt sein, so dass die Strukturierung wiederum nur durch eine Drehung um einen Winkel von 360° auf sich selbst abgebildet werden kann.The in the FIG. 2 shown circumferential asymmetry can undergo numerous modifications. For example, in a first alternative embodiment, a plurality of sections 6 may be provided, in which the annular space surface 26a is not structured. Such portions 6 would be asymmetrically distributed over the circumference, so that the structuring in turn can be imaged on itself only by a rotation through an angle of 360 °.

In einem zweiten alternativen Ausgestaltung kann vorgesehen sein, dass sich die durch die axialen Aussparungen 5 bereitgestellte symmetrische Strukturierung auch in den Abschnitt 6 erstreckt, wobei in dem Abschnitt 6 dann aber eine zusätzliche umfangsasymmetrische Strukturierung vorgesehen ist, beispielsweise eine Vertiefung, in der dann die axialen Aussparungen 5 ausgebildet sind. Für diesen Fall wäre einer symmetrischen Strukturierung in Umfangsrichtung eine asymmetrische Strukturierung in Umfangsrichtung überlagert.
Eine weitere alternative Ausgestaltung sieht vor, dass ausschließlich ein in Umfangsrichtung verlaufender Abschnitt, entsprechend dem Abschnitt 6 der Figur 2, überhaupt eine Strukturierung aufweist, während die Ringraumfläche 26a außerhalb dieses Abschnitts glatt ausgebildet ist. Es läge insofern eine Umkehrung der in der Figur 2 dargestellten Verhältnisse vor.In a second alternative embodiment it can be provided that the symmetrical structuring provided by the axial recesses 5 also extends into the section 6, wherein in the section 6, however, an additional circumferentially asymmetric structuring is provided, for example a depression in FIG then the axial recesses 5 are formed. For this case, a symmetrical structuring in the circumferential direction would be superimposed on an asymmetrical structuring in the circumferential direction.
A further alternative embodiment provides that only a circumferentially extending section, corresponding to the section 6 of FIG. 2 has at all a structuring, while the annular space surface 26a is formed smooth outside of this section. It would be a reversal of that in the FIG. 2 presented conditions.

Ein Ausführungsbeispiel einer solchen Ausführungsvariante ist in den Figuren 3 und 4 dargestellt. Die Figur 3 zeigt eine perspektivische Ansicht auf die Innenseite eines Umfangsgehäuses 25, das beispielsweise dem Umfangsgehäuse 25 der Figur 1 entspricht, jedoch ebenfalls das Umfangsgehäuse 15 oder das Umfangsgehäuse 55 der Figur 1 sein könnte. Das Umfangsgehäuse 25 bildet innenseitig eine Ringraumfläche 26 aus, die den Strömungskanal 3 (vgl. Figur 1) radial außen begrenzt. An der Innenseite des Umfangsgehäuses 25 ist ein Einlegering 9' angeordnet. Dort, wo der Einlegering 9' angeordnet ist, bildet dessen dem Strömungskanal zugewandte Oberfläche 26b die Ringraumfläche des Gehäuses 25.An embodiment of such a variant is in the FIGS. 3 and 4 shown. The FIG. 3 shows a perspective view of the inside of a peripheral housing 25, for example, the peripheral housing 25 of FIG. 1 However, but also the peripheral housing 15 or the peripheral housing 55 of the FIG. 1 could be. The peripheral housing 25 forms on the inside an annular space surface 26, which the flow channel 3 (see. FIG. 1 ) bounded radially on the outside. On the inside of the peripheral housing 25, a insert ring 9 'is arranged. Where the insert ring 9 'is arranged, its surface 26b facing the flow channel forms the annular space surface of the housing 25.

Der Einlegering 9' ist in einem mittigen Bereich 93' konkav ausgebildet. Diese konkave Ausbildung entsteht dadurch, dass der Einlegering 9' durch die Laufschaufeln 22 des zugeordneten Rotors ausgefräst ist. Der Einlegering 9' besteht dabei aus einem vergleichsweise weichen Material. Eine solche Bereitstellung eines Einlegerings 9' ist mit dem Vorteil eines geringen Ringspalts zwischen der Schaufelspitze der Laufschaufeln 22 und der Ringraumfläche 26b verbunden.The insert ring 9 'is concave in a central region 93'. This concave configuration results from the fact that the insert ring 9 'is milled by the blades 22 of the associated rotor. The insert ring 9 'consists of a comparatively soft material. Such provision of a liner ring 9 'is associated with the advantage of a small annular gap between the blade tip of the blades 22 and the annulus surface 26b.

Die Figur 4 entspricht der Figur 3, wobei in der Figur 4 zusätzlich Laufschaufeln 22 des zugeordneten Rotors dargestellt sind.The FIG. 4 equals to FIG. 3 , where in the FIG. 4 in addition blades 22 of the associated rotor are shown.

Es ist in den Einlegering 9' eine Aussparung 7 eingebracht. Diese wird beispielsweise durch Erodieren oder Fräsen des Einlegerings 9' bereitgestellt. Die Aussparung 7 kann längliche Rillen 71 aufweisen; diese entstehen bei der Herstellung der Aussparung 7 und sind optional. Außerhalb der Aussparung 7 ist der Einlegering 9' nicht strukturiert, d. h. glatt ausgeführt. Die Aussparung 7 stellt daher eine umfangsasymmetrische Struktur der Ringraumfläche 26b bereit.It is in the insert ring 9 'a recess 7 is introduced. This is provided, for example, by eroding or milling the insert ring 9 '. The recess 7 may have elongated grooves 71; These arise during the production of the recess 7 and are optional. Outside the recess 7 of the insert ring 9 'is not structured, that is smooth. The recess 7 therefore provides a circumferentially asymmetric structure of the annulus surface 26b.

Die Aussparung 7 weist eine axiale Länge x1 auf, die geringfügig größer als die axiale Erstreckung des Bereichs 93' des Einlegerings 9', der umfangsseitig an die Laufschaufeln 22 des zugeordneten Rotors angrenzt. Die axiale Erstreckung x1 der Aussparung 7 ist somit geringfügig größer als die axiale Erstreckung des Schaufelgitters des zugeordneten Rotors.The recess 7 has an axial length x1, which is slightly larger than the axial extent of the portion 93 'of the insert ring 9', which circumferentially adjacent to the blades 22 of the associated rotor. The axial extension x1 of the recess 7 is thus slightly larger than the axial extent of the blade lattice of the associated rotor.

Die Aussparung 7 weist des Weiteren eine Länge u1 in Umfangsrichtung U auf, die einem Umfangswinkel Δϕ1 des zugehörigen Kreissektors entspricht.The recess 7 further has a length u1 in the circumferential direction U, which corresponds to a circumferential angle Δφ1 of the associated circular sector.

Auch im Ausführungsbeispiel der Figuren 3 und 4 können mehrere Aussparungen 7 entlang des Umfangs des Einlegerings 9' ausgebildet sein, wobei solche mehrere Aussparungen umfangsasymmetrisch angeordnet sind.Also in the embodiment of FIGS. 3 and 4 a plurality of recesses 7 may be formed along the circumference of the insert ring 9 ', wherein such a plurality of recesses are circumferentially arranged asymmetrically.

Die Figur 5 verdeutlicht die mit der umfangsasymmetrischen Ausbildung der Ringraumfläche verbundenen Vorteile. Die umfangsasymmetrische Ausbildung der Ringraumfläche vermindert die Schwingungsanregung von Laufschaufeln und damit eine Verbesserung der Flatterstabilität. In der Figur 5 ist das Verdichterdruckverhältnis in Abhängigkeit vom Massenstrom dargestellt. Das Bezugszeichen 81 gibt die Arbeitslinie an und der Punkt DP einen betrachteten Auslegungspunkt. Das Bezugszeichen 82 gibt die Stabilitätslinie, auch als Pumpgrenze bezeichnet, an. Das Kennfelder umfasst Linien 83 mit konstanter Drehzahl N.The FIG. 5 illustrates the advantages associated with the circumferentially asymmetric design of the annulus area benefits. The circumferential asymetrical design of the annulus area reduces the vibration excitation of blades and thus an improvement in the flutter stability. In the FIG. 5 the compressor pressure ratio is shown as a function of the mass flow. The reference numeral 81 indicates the working line and the point DP indicates a design point under consideration. Reference numeral 82 indicates the stability line, also referred to as the surge line. The map comprises lines 83 of constant speed N.

Nach links wird der Kennfeldbereich durch die Stabilitätslinie 82 begrenzt. Liegt ein aktueller Betriebspunkt jenseits der Stabilitätslinie, so kommt es zum Strömungsabriss.To the left of the map area is limited by the stability line 82. If a current operating point lies beyond the stability line, the result is a stall.

Ein Schaufelflattern führt zu einer Eindellung der Stabilitätslinie 82, die für diesen Fall durch die Flatterlinie 821 ersetzt wird. Die erfindungsgemäße umfangsasymmetrische Strukturierung der Ringraumfläche führt dazu, dass die Eindellung der Stabilitätslinie 82 reduziert wird, so dass die Stabilitätslinie 82 durch die Flatterlinie 822 bei Ringraumasymmetrie ersetzt wird. Der Abstand zwischen der Flatterlinie 821 ohne Ringraumasymmetrie und der Flatterlinie 822 mit Ringraumasymmetrie verdeutlicht die mit der erfindungsgemäßen Ringraumasymmetrie verbundenen Vorteile. Der Abstand eines auf der Arbeitslinie 81 liegenden Betriebspunktes zur Stabilitätslinie 82 wird vorteilhafterweise erhöht.A blade flutter results in a dip in the stability line 82, which in this case is replaced by the flutter line 821. The circumferentially asymmetric structuring according to the invention of the annular space surface results in that the indentation of the stability line 82 is reduced, so that the stability line 82 is replaced by the flutter line 822 in the case of annular space asymmetry. The distance between the flutter line 821 without annular space asymmetry and the flutter line 822 with annular space asymmetry clarifies the advantages associated with the annular space asymmetry according to the invention. The distance between an operating point 81 operating point to the stability line 82 is advantageously increased.

Die Erfindung beschränkt sich in ihrer Ausgestaltung nicht auf die vorstehend dargestellten Ausführungsbeispiele, die lediglich beispielhaft zu verstehen sind. Beispielsweise können zur Bereitstellung einer Umfangsasymmetrie der Ringraumfläche Strukturen bereitgestellt werden, die in anderer Weise, mit anderen Formen und/oder an anderer Stelle als in den Ausführungsbeispielen beschrieben ausgebildet und angeordnet sind.The invention is not limited in its embodiment to the embodiments shown above, which are to be understood only as examples. For example, to provide circumferential asymmetry of the annulus surface, structures may be provided that are configured and arranged in other manners, shapes, and / or locations other than those described in the exemplary embodiments.

Claims (11)

  1. Fluid-flow machine, featuring:
    - at least one rotor (11, 21, 31) including a rotary element with a plurality of rotor blades (12, 22, 32) arranged on the rotary element, and
    - a circumferential casing (15, 25) having a central axis (2) and surrounding the rotor (11, 21, 31),
    - with the circumferential casing (15, 25) or a part (9, 9') connected thereto having an annular space surface (16, 26, 26a, 26b) on the inside which delimits a flow duct (3, 4) of the fluid-flow machine radially outwards, and
    - with the annular space surface (16, 26, 26a, 26b) having a structuring at least in one area adjoining a rotor (11, 21, 31) on the circumferential side,
    characterized in that
    at least one structuring (6, 7) of the annular space surface (16, 26, 26a, 26b) is, relative to the central axis (2) of the circumferential casing (15, 25), given a circumferentially asymmetrical design, and that
    - the annular space surface (26a) has at least one section (6) extending in the circumferential direction (U), which section in an otherwise symmetrical structuring (5) of the annular space surface (26a) provides a symmetry break in the circumferential direction (U),
    or
    - the annular space surface (16, 26, 26a, 26b) has at least one section extending in the circumferential direction (U), which section structures the annular space surface (16, 26, 26a, 26b) asymmetrically in the circumferential direction (U), and the annular space surface (16, 26, 26a, 26b) furthermore features at least one symmetrical structuring in the circumferential direction (U).
  2. Fluid-flow machine, featuring:
    - at least one rotor (11, 21, 31) including a rotary element with a plurality of rotor blades (12, 22, 32) arranged on the rotary element, and
    - a circumferential casing (15, 25) having a central axis (2) and surrounding the rotor (11, 21, 31),
    - with the circumferential casing (15, 25) or a part (9, 9') connected thereto having an annular space surface (16, 26, 26a, 26b) on the inside which delimits a flow duct (3, 4) of the fluid-flow machine radially outwards, and
    - with the annular space surface (16, 26, 26a, 26b) having a structuring at least in one area adjoining a rotor (11, 21, 31) on the circumferential side,
    characterized in that
    at least one structuring (6, 7) of the annular space surface (16, 26, 26a, 26b) is, relative to the central axis (2) of the circumferential casing (15, 25), given a circumferentially asymmetrical design, and that the annular space surface (26b) has at least one section (7) extending in the circumferential direction (U), which section structures the annular space surface (26b) asymmetrically in the circumferential direction (U), while the annular space surface (26b) is otherwise designed smooth in the circumferential direction (U), where the at least one section (7) extending in the circumferential direction (U) provides a circumferential asymmetry and is formed by a recess, where the annular space surface (26b) has exactly one recess (7) or several recesses, which are provided circumferentially asymmetrically in the annular space surface, and where the axial extension (x1) of the recess (7) is slightly larger than the axial extension of a blade cascade of the associated rotor.
  3. Fluid-flow machine in accordance with one of the preceding Claims, characterized in that the annular space surface (16, 26, 26a, 26b) has at least one section (6, 7) extending in the circumferential direction (U), the radius of which differs from that of the other sections with reference to the central axis (2).
  4. Fluid-flow machine in accordance with Claim 2, characterized in that the recess (7) in a section in a plane perpendicular to the central axis (2) is given a bent or rectangularly shaped design.
  5. Fluid-flow machine in accordance with one of the preceding Claims, characterized in that the structuring of the annular space surface includes structures (5, 6, 7) that extend over a defined length in the axial direction.
  6. Fluid-flow machine in accordance with one of the preceding Claims, characterized in that the circumferential casing (15, 25) itself is given a circumferentially asymmetrical structure.
  7. Fluid-flow machine in accordance with one of the preceding Claims, characterized in that a liner (9, 9') connected on the inside to the circumferential casing (15, 25) is given a circumferentially asymmetrical structure.
  8. Fluid-flow machine in accordance with one of the preceding Claims, characterized in that a structuring of the circumferential casing (15, 25) or of a part (9, 9') connected to the circumferential casing (15, 25) is provided by at least one recess (7) milled out or eroded in the casing (15, 25) or the part (9, 9').
  9. Fluid-flow machine in accordance with one of the preceding Claims, characterized in that the circumferentially asymmetrical casing structuring (6, 7) is provided in each case in the area of the blade cascade of a rotor (11, 21, 31).
  10. Fluid-flow machine in accordance with one of the preceding Claims, characterized in that a circumferentially asymmetrical casing structuring (6, 7) is also provided in axial areas of the circumferential casing (15, 25) or a part (9, 9') connected thereto, said areas being located in front of and/ or behind an adjacent blade cascade.
  11. Fluid-flow machine in accordance with one of the preceding Claims, characterized in that the fluid-flow machine is a compressor (10, 20, 30) designed and intended to be used in a jet engine (1).
EP12164964.4A 2011-04-20 2012-04-20 Flow engine Active EP2514975B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102011007767A DE102011007767A1 (en) 2011-04-20 2011-04-20 flow machine

Publications (3)

Publication Number Publication Date
EP2514975A2 EP2514975A2 (en) 2012-10-24
EP2514975A3 EP2514975A3 (en) 2014-06-11
EP2514975B1 true EP2514975B1 (en) 2017-08-02

Family

ID=46000967

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12164964.4A Active EP2514975B1 (en) 2011-04-20 2012-04-20 Flow engine

Country Status (3)

Country Link
US (1) US9816528B2 (en)
EP (1) EP2514975B1 (en)
DE (1) DE102011007767A1 (en)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9267386B2 (en) 2012-06-29 2016-02-23 United Technologies Corporation Fairing assembly
EP2885506B8 (en) 2012-08-17 2021-03-31 Raytheon Technologies Corporation Contoured flowpath surface
US10344711B2 (en) * 2016-01-11 2019-07-09 Rolls-Royce Corporation System and method of alleviating blade flutter
US10465539B2 (en) * 2017-08-04 2019-11-05 Pratt & Whitney Canada Corp. Rotor casing
DE102018116062A1 (en) * 2018-07-03 2020-01-09 Rolls-Royce Deutschland Ltd & Co Kg Structure assembly for a compressor of a turbomachine
CN116464675B (en) * 2023-06-20 2023-09-01 河北拓顺医疗科技有限公司 Shock-absorbing noise reduction device for ventilator built-in fan

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE60130577T2 (en) * 2000-11-21 2008-06-26 Pratt & Whitney Canada Corp., Longueuil REDUCTION OF LEAF WHEEL NOISE BETWEEN FAN AND LEAD SHOVEL

Family Cites Families (45)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3890060A (en) * 1974-02-15 1975-06-17 Gen Electric Acoustic duct with asymmetric acoustical treatment
JPS6318799Y2 (en) * 1980-12-02 1988-05-26
GB2090334B (en) * 1980-12-29 1983-11-16 Rolls Royce Damping flutter of ducted fans
CA1314486C (en) * 1984-06-19 1993-03-16 Michael John Charles Waterman Axial flow compressor surge margin improvement
GB2245312B (en) 1984-06-19 1992-03-25 Rolls Royce Plc Axial flow compressor surge margin improvement
US5067876A (en) 1990-03-29 1991-11-26 General Electric Company Gas turbine bladed disk
GB2281356B (en) 1993-08-20 1997-01-29 Rolls Royce Plc Gas turbine engine turbine
EP0774050B1 (en) * 1994-06-14 1999-03-10 United Technologies Corporation Interrupted circumferential groove stator structure
US5562404A (en) 1994-12-23 1996-10-08 United Technologies Corporation Vaned passage hub treatment for cantilever stator vanes
US5725353A (en) 1996-12-04 1998-03-10 United Technologies Corporation Turbine engine rotor disk
DE19650656C1 (en) 1996-12-06 1998-06-10 Mtu Muenchen Gmbh Turbo machine with transonic compressor stage
GB9823840D0 (en) 1998-10-30 1998-12-23 Rolls Royce Plc Bladed ducting for turbomachinery
US6290458B1 (en) * 1999-09-20 2001-09-18 Hitachi, Ltd. Turbo machines
US6511294B1 (en) 1999-09-23 2003-01-28 General Electric Company Reduced-stress compressor blisk flowpath
US6561761B1 (en) 2000-02-18 2003-05-13 General Electric Company Fluted compressor flowpath
US6471474B1 (en) 2000-10-20 2002-10-29 General Electric Company Method and apparatus for reducing rotor assembly circumferential rim stress
US6478545B2 (en) 2001-03-07 2002-11-12 General Electric Company Fluted blisk
JP3872966B2 (en) * 2001-06-29 2007-01-24 株式会社日立プラントテクノロジー Axial fluid machine
US6969232B2 (en) 2002-10-23 2005-11-29 United Technologies Corporation Flow directing device
GB2408546B (en) * 2003-11-25 2006-02-22 Rolls Royce Plc A compressor having casing treatment slots
US7690890B2 (en) 2004-09-24 2010-04-06 Ishikawajima-Harima Heavy Industries Co. Ltd. Wall configuration of axial-flow machine, and gas turbine engine
US7134842B2 (en) 2004-12-24 2006-11-14 General Electric Company Scalloped surface turbine stage
US7220100B2 (en) 2005-04-14 2007-05-22 General Electric Company Crescentic ramp turbine stage
GB0518628D0 (en) 2005-09-13 2005-10-19 Rolls Royce Plc Axial compressor blading
US7861823B2 (en) 2005-11-04 2011-01-04 United Technologies Corporation Duct for reducing shock related noise
GB0600532D0 (en) * 2006-01-12 2006-02-22 Rolls Royce Plc A blade and rotor arrangement
US7465155B2 (en) 2006-02-27 2008-12-16 Honeywell International Inc. Non-axisymmetric end wall contouring for a turbomachine blade row
US7874794B2 (en) 2006-03-21 2011-01-25 General Electric Company Blade row for a rotary machine and method of fabricating same
US7887297B2 (en) 2006-05-02 2011-02-15 United Technologies Corporation Airfoil array with an endwall protrusion and components of the array
US7909570B2 (en) 2006-08-25 2011-03-22 Pratt & Whitney Canada Corp. Interturbine duct with integrated baffle and seal
DE102006048933A1 (en) * 2006-10-17 2008-04-24 Mtu Aero Engines Gmbh Arrangement for influencing the flow
FR2912789B1 (en) * 2007-02-21 2009-10-02 Snecma Sa CARTER WITH CARTER TREATMENT, COMPRESSOR AND TURBOMACHINE COMPRISING SUCH A CARTER.
JP5283855B2 (en) 2007-03-29 2013-09-04 株式会社Ｉｈｉ Turbomachine wall and turbomachine
DE102007020025A1 (en) 2007-04-27 2008-10-30 Honda Motor Co., Ltd. Shape of a gas channel in an axial flow gas turbine engine
DE102007056953B4 (en) 2007-11-27 2015-10-22 Rolls-Royce Deutschland Ltd & Co Kg Turbomachine with Ringkanalwandausnehmung
JP4400686B2 (en) 2008-01-07 2010-01-20 ダイキン工業株式会社 Propeller fan
DE102008011644A1 (en) 2008-02-28 2009-09-03 Rolls-Royce Deutschland Ltd & Co Kg Housing structuring for axial compressor in the hub area
FR2928174B1 (en) 2008-02-28 2011-05-06 Snecma DAWN WITH NON AXISYMETRIC PLATFORM: HOLLOW AND BOSS ON EXTRADOS.
DE102008021053A1 (en) 2008-04-26 2009-10-29 Mtu Aero Engines Gmbh Reformed flow path of an axial flow machine to reduce secondary flow
DE102008031982A1 (en) * 2008-07-07 2010-01-14 Rolls-Royce Deutschland Ltd & Co Kg Turbomachine with groove at a trough of a blade end
DE102008052401A1 (en) 2008-10-21 2010-04-22 Rolls-Royce Deutschland Ltd & Co Kg Turbine working machine with running column feeder
US8439643B2 (en) 2009-08-20 2013-05-14 General Electric Company Biformal platform turbine blade
FR2950942B1 (en) 2009-10-02 2013-08-02 Snecma ROTOR OF A TURBOMACHINE COMPRESSOR WITH OPTIMIZED INTERNAL END WALL
US8684684B2 (en) 2010-08-31 2014-04-01 General Electric Company Turbine assembly with end-wall-contoured airfoils and preferenttial clocking
US8678740B2 (en) * 2011-02-07 2014-03-25 United Technologies Corporation Turbomachine flow path having circumferentially varying outer periphery

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE60130577T2 (en) * 2000-11-21 2008-06-26 Pratt & Whitney Canada Corp., Longueuil REDUCTION OF LEAF WHEEL NOISE BETWEEN FAN AND LEAD SHOVEL

Also Published As

Publication number Publication date
US9816528B2 (en) 2017-11-14
EP2514975A3 (en) 2014-06-11
EP2514975A2 (en) 2012-10-24
DE102011007767A1 (en) 2012-10-25
US20120269619A1 (en) 2012-10-25

Similar Documents

Publication Publication Date Title
EP2514975B1 (en) Flow engine
EP2242931B1 (en) Circulation structure for a turbo compressor
DE102011054589B4 (en) Rotary machine with spacers to control fluid dynamics
EP3408503B1 (en) Turbomachinery with bladed diffuser
DE102007037924A1 (en) Turbomachine with Ringkanalwandausnehmung
EP2761137B1 (en) Blade of a row of rotor blades or stator blades for use in a turbomachine
EP2921716B1 (en) stator blade GROUP
DE102013109203A1 (en) Vertebra-disrupting sealing teeth for a sealing arrangement
DE102014219821A1 (en) Return step
EP2294286B1 (en) Rotor with shrouded blades of a turbomachine
EP3161325A1 (en) Diffuser for a radial compressor
EP3682092B1 (en) Exhaust gas turbine with a diffusser
EP3428393B1 (en) Rotor of a turbomachine
EP2913481B1 (en) Tandem blades of a turbo-machine
EP2597257B1 (en) Blades
DE112015005131T5 (en) Cooling structure for turbine, and gas turbine
DE102006060694B4 (en) Rotor and stator blade arrangement for a gas turbine engine
DE102014203604A1 (en) Blade row group
EP3088743B1 (en) Side-channel vacuum pump stage with a stripper that is slanted on the suction side
EP2921715A1 (en) Stator blade group
DE102016219815A1 (en) Blade assembly with ring-shaped or disk-shaped blade carrier and radially inner stiffening structure
EP1953340B1 (en) Flow machine and rotor shovel for a flow machine
EP1711689B1 (en) Sealing arrangement
EP3650709A1 (en) Bladed diffuser assembly for a radial compressor
DE102016105957A1 (en) Fan housing and engine assembly with fan housing

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

RIC1 Information provided on ipc code assigned before grant

Ipc: F04D 29/68 20060101ALI20140506BHEP

Ipc: F04D 29/52 20060101ALI20140506BHEP

Ipc: F04D 29/16 20060101ALI20140506BHEP

Ipc: F04D 29/66 20060101AFI20140506BHEP

Ipc: F01D 25/04 20060101ALI20140506BHEP

17P Request for examination filed

Effective date: 20141210

RBV Designated contracting states (corrected)

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

17Q First examination report despatched

Effective date: 20151026

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20170313

RIN1 Information on inventor provided before grant (corrected)

Inventor name: JOHANN, ERIK

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAJ Information related to disapproval of communication of intention to grant by the applicant or resumption of examination proceedings by the epo deleted

Free format text: ORIGINAL CODE: EPIDOSDIGR1

GRAL Information related to payment of fee for publishing/printing deleted

Free format text: ORIGINAL CODE: EPIDOSDIGR3

GRAR Information related to intention to grant a patent recorded

Free format text: ORIGINAL CODE: EPIDOSNIGR71

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

INTC Intention to grant announced (deleted)
AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

INTG Intention to grant announced

Effective date: 20170627

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

Ref country code: AT

Ref legal event code: REF

Ref document number: 914812

Country of ref document: AT

Kind code of ref document: T

Effective date: 20170815

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502012010889

Country of ref document: DE

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20170802

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171102

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171102

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171202

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20171103

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 7

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502012010889

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20180503

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20180430

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180420

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180430

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180430

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180430

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180420

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 914812

Country of ref document: AT

Kind code of ref document: T

Effective date: 20180420

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180420

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20120420

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170802

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170802

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20200429

Year of fee payment: 9

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20210420

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210420

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20230528

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20240429

Year of fee payment: 13

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20240430

Year of fee payment: 13