EP3140548A1 - Rotor, en particulier pour une machine à canal latéral - Google Patents

Rotor, en particulier pour une machine à canal latéral

Info

Publication number
EP3140548A1
EP3140548A1 EP15712837.2A EP15712837A EP3140548A1 EP 3140548 A1 EP3140548 A1 EP 3140548A1 EP 15712837 A EP15712837 A EP 15712837A EP 3140548 A1 EP3140548 A1 EP 3140548A1
Authority
EP
European Patent Office
Prior art keywords
impeller
wall
radius
dimension
blade
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.)
Granted
Application number
EP15712837.2A
Other languages
German (de)
English (en)
Other versions
EP3140548B1 (fr
Inventor
Lars Buchholz
Antje Gennat
Ulli Kriebel
Henryk WANIEK
Achim Von Kathen
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.)
Gebr Becker GmbH
Original Assignee
Gebr Becker GmbH
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 Gebr Becker GmbH filed Critical Gebr Becker GmbH
Publication of EP3140548A1 publication Critical patent/EP3140548A1/fr
Application granted granted Critical
Publication of EP3140548B1 publication Critical patent/EP3140548B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F04D5/00—Pumps with circumferential or transverse flow
    • F04D5/002—Regenerative pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D23/00—Other rotary non-positive-displacement pumps
    • F04D23/008—Regenerative pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/18—Rotors
    • F04D29/188—Rotors specially for regenerative pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps

Definitions

  • Impeller in particular for a side channel machine
  • the invention relates to an impeller, in particular for a side channel machine such as a side channel compressor or a sokanalvakuumpumpe aufwei- send distributed in Umf angsraum arranged, formed by a respective blade wall blades which in a plan view of the impeller, in which plan view is a geometric impeller impeller Rotation axis punctiform forms, open vane chambers form, wherein a blade wall in plan view at a first radius relative to the geometric impeller-impeller axis of rotation begins, which first radius of half or more of a second radius corresponds to the second radius of a peripheral edge of the radius Impeller determined and wherein the first radius dimension determines a radially inner boundary wall of the blade chamber, wherein further comprises a blade wall has an exposed upper end edge, which enters radially inward in accordance with the inner boundary wall and ends in the plan view radially outward, wherein between an inlet point of the terminal edge in the inner boundary wall and the radially outer end of a mental connection
  • An impeller of the type in question is known for example from DE 102005008388 AI.
  • the invention has for its object, an impeller of the type in question advantageous to further develop in particular with regard to improved efficiency.
  • a possible solution to the problem is given according to a first inventive idea in an impeller, in which it is geared to that the largest Offset amount equal to 0.1 times or more the difference of the first and second radius dimensions.
  • turbomachines have at least one annular working space with a substantially circular cross section, in which an impeller with blading, ie blades and blade chambers lying between them, is rotatably received in the impeller circumferential direction.
  • the unfilled, possibly on both impeller sides adjacent to the blading cross section of the working space forms a side channel, which is interrupted at the periphery by the so-called breaker.
  • a fluid to be compressed for example, gas or liquid
  • the fluid flows through the inlet into the side channel and is carried along by the blades of the impeller. In their flow chambers, the fluid is forced outwards due to the centrifugal force and compressed there.
  • the inflow fluid forces the compressed fluid out of the blades into the side channel where it is directed radially inward and reenters the impeller blading.
  • the fluid passes from the side channel impeller end side through a radially inner chamber inlet region in the flow space bounded by the blade chambers and after Flow through the vane chamber through a radially outer Kammerauslass Symposium in the side channel back. This so-called circulation is repeated several times, so that the fluid can be compressed in several stages to the outlet.
  • the largest offset dimension preferably corresponds to 0.1 to 0.6 times, possibly even more, the difference between the first and second radius dimensions.
  • the largest offset dimension can also correspond to about one third of the difference of the first and second radius measure.
  • the end edge of a blade wall preferably also extends radially outward substantially in the direction of the impeller-impeller axis of rotation. This results in a corresponding radially outer peripheral edge, which extends substantially perpendicular to the end edge of the blade wall.
  • the peripheral edge may, for example, extend in a range of +/- 5 ° perpendicular to the trailing edge.
  • this radially outer peripheral edge determines the extent of the larger radius of the impeller, at least in a radially outwardly open configuration, in which open the vane chambers radially outward. In this case, the blades end freely radially outward.
  • the blade wall can pass radially outward into a peripheral end wall.
  • the vane chamber formed is limited in relation to a cross section through the chamber bottom and the inner and outer boundary wall or in the circumferential direction successive vane walls and preferably only in the region of a through the end edges of the
  • the mental connecting line between the inlet point of the terminal edge in the inner boundary wall and the radially outer end may, with respect to the plan view, extend so that it is parallel to a Radialen emanating from the geometric impeller axis of rotation.
  • the line of connection with the radial may include an acute angle of, for example, 0.05 to 15 °. It is preferred that the connecting line extends in extension in the direction of the geometric impeller rotation axis at a distance from the geometric impeller rotation axis.
  • the vertical distance dimension of the connection line to the geometric impeller rotation axis is given by the length of a perpendicular to the connection line, which perpendicular cuts the geometric impeller rotation axis.
  • the vertical distance dimension may be formed in the range of -40% to 40% of the outer radius dimension.
  • the distance measure may be formed in the range of -40% to + 40% of the radius difference between inner and outer radius.
  • There may be both a "lead" of the radially outer end of the end wall opposite the inlet point in the inner boundary wall as well as a "lag". Seen from said inlet point radially outward can therefore be formed leading in the direction of rotation at a given direction of rotation so the radially outer end of the end wall as well as against the direction of rotation lagging.
  • the radially outer end of the terminal edge may include an acute angle of up to 90 ° with the connecting line or a radial passing through the radially outer end (starting from the axis of rotation). Preferred is an acute angle of 50 to 75 °, for example 70 °.
  • the acute angle refers on an inlet section of the terminal edge in the outer wall.
  • the radially outer end of the trailing edge preferably enters tangentially into a circular line connecting the radially outer ends of all trailing edges, or, more preferably, into the radially outer end wall, such that the prescribed acute angle is between one through the intersection of the trailing edge and adjusts an idealized, ie, averaged, line of the terminating wall and the connecting line.
  • the acute angle refers to the angle between the straight line and the connecting line.
  • the terminal edge may at least partially be composed of straight sections. It may be provided a straight section, but in addition also a plurality of successively arranged straight sections, such as two, three, four or even ten straight sections. These straight sections extend over the shortest distance between a respective straight section beginning and a straight section end. Such a straight section can then continue into a curved section. An area between two straight sections may be formed by a curved area.
  • the end edge between the inner and outer radius can also be curved continuously.
  • Preference is here an uninterrupted Krüm- mung between the inner and outer radius, which curvature of several, for example, two, three, four or ten successively arranged curvature sections composed.
  • One or more curved sections may be circularly curved and follow a radius. In the case of several or all of a radius following curvature sections, these may have different radii, wherein in a plurality of curvature sections a plurality of curvature sections may also have the same radii.
  • the trailing edge essentially follows a radius line, so that over the extension length of the trailing edge, a constant, possibly a deviation of, for example, +/- 5% of the relevant radius dimension exhibiting radius sets.
  • the radius of the terminating edge is preferably removed from a circle center, which lies in relation to a distance to the geometric impeller axis of rotation between the first and the second radius.
  • the center of the circle is preferably located within a vane chamber, moreover preferably in a vane chamber following in the circumferential direction of the vane wall having the end edge.
  • the center of the circle can lie in the upstream vane chamber viewed in the direction of rotation of the impeller.
  • the circle center is located on or adjacent to a radius line of the geometric impeller axis of rotation, which radius line runs centrally between the first and the second radius.
  • the first and the second Radi measure dimension facing end portions of the end edge can extend curved.
  • the radius of this end edge of the terminating edge which preferably runs tangentially into the radially inner boundary wall and possibly into the radially outer end wall and more preferably extends in the form of a circular segment, may be smaller or larger than a radius dimension, for example following a radius line.
  • the radius of the outer end regions of the terminal edge preferably corresponds to a 0.5 to
  • the blade wall can, starting from the end edge in the direction of the geometric impeller axis of rotation or in the direction of a
  • the wall thickness of the blade wall near or at the transition to the chamber bottom may correspond to 2 to 4 times, more preferably 3 times the wall thickness in the region of the end edge.
  • the increase in the wall thickness may be different with respect to the circumferential direction.
  • the blade wall edges may be parallel to the geometric impeller axis of rotation extending straight lines include different acute angles. Based on the above-described straight line, the angle of a blade wall edge can have 1 to 10 °, while the angle of the opposite blade wall edge to the straight line is 11 to 30 °.
  • the acute angle of the blade edge against the direction of rotation is preferably greater than the acute angle of the blade wall edge in the direction of rotation. There may be a ratio between these different angles from 1: 3 to 1:10.
  • the blade wall can be viewed convex in the direction of rotation.
  • the blade wall curved in the ground plan opens in the direction of rotation.
  • the chamber bottom may extend in a cross-section in the connecting line or parallel thereto in a circle or ellipse.
  • the circular shape has a radius that remains constant over the extension length of the chamber bottom in cross section. Also, a curvature with different radii can be provided over the Er extension length.
  • the chamber bottom for example following a circular or elliptical line, can run into an upper edge of the inner end wall.
  • the greatest depth of the chamber bottom preferably corresponds to 0.25 to
  • the depth corresponds to half the radius difference.
  • the depth is in this case measured starting from a (possibly largest) height of the terminal edge in the direction of the axis of rotation.
  • the radial velocity is increased in operation in addition to the known solutions during pressure buildup in addition to the peripheral speed.
  • the pressure build-up is improved.
  • the suggested solution the possibility of a radially outwardly closed impeller, whereby a two-stage operation can be realized with only one impeller.
  • the ranges and / or ranges of values or multiple ranges given above also include all intermediate values, in particular in 1/10-steps of the respective dimension, if appropriate also without dimensions.
  • the specification 0.1 to 0.5 times also includes the disclosure of 0.11 to 0.5, 0.1 to 0.49, 0.12 to 0.5 0.12 to 0.9, 0.12 to 0.48, 0.1 to 0.48, etc., the disclosure of 15 to 40% also the disclosure of 15.1 up to 40%, 15 to 39.9%, 15.1 to 39.9%, 15.2 to 40%, 15.2 to 39.9%, 15.2 to 39.8%, 15 to 39.8 % etc., the disclosure of 60 ° to 89 ° also the disclosure of 60.1 ° to 89 °, 60 ° to 88.9 °, 60.2 ° to 89 °, 60.2 ° to 88.9 °, 60,2 ° to 88,8 °, 60 ° to 88,8 ° etc.
  • This disclosure may on the one hand to delimit
  • Fig. 1 is an impeller in plan view
  • FIG. 2 shows the section along the line II-II in Figure 1;
  • Fig. 3 is the bottom view of the impeller;
  • FIG. 4 shows the enlargement of region IV in FIG. 1, relating to a first embodiment of a blade wall
  • FIG. 5 is an illustration corresponding to FIG. 4, relating to an alternative embodiment of the blade wall
  • FIG. 8 shows a sectional view according to FIG. 7, but relating to a further embodiment of the blade wall
  • FIG. 9 shows a representation corresponding to FIG. 6 with respect to a further embodiment
  • Fig. 10 is a further, corresponding to Figure 6 representation in a further embodiment.
  • an impeller 1 is shown and described, in particular for a side channel machine, such as a side channel compressor or a side channel vacuum pump.
  • the impeller 1 has a center located in the hub 2 with a through hole 3, which serves for fastening the impeller 1 to a drive shaft, not shown, a side channel machine. Distributed uniformly in the circumferential direction, the impeller 1 has vane chambers 4 which are open towards a top opening plane E with reference to FIG. These are viewed in the circumferential direction laterally bounded by blades 5 forming blade walls. 6
  • the blades 5 as well as the blade chambers 4 are formed in a radially outer region of the impeller 1.
  • the blades 5, optionally with the exception of one end wall, as explained below, form the radially outer boundary of the impeller 1.
  • FIGS. 1 to 9 relate to an impeller 1 for forming a two-stage side channel machine. Accordingly, with respect to a plane parallel to the opening plane E center plane which intersects the geometric impeller rotation axis x perpendicular, formed on both sides of the median plane blades 5 to form vane chambers 4.
  • the blade chambers 4 are bounded by an inner peripheral boundary wall 7. This ends with respect to a cross-section to form a boundary wall edge 8 in the opening plane E.
  • a final wall 10 is formed circumferentially. These also extend, for example according to FIG. 6, into the opening plane E, forming an end wall edge 11 running in the opening plane E.
  • the inner boundary wall 7 runs along a first, inner radius ri.
  • This radius ri preferably relates to a radial inner edge of the boundary wall 7 and corresponds in the illustrated embodiment. Examples of preferred two thirds of a radius r 2 of a radially outer edge of the end wall 10th
  • Thirty to forty-five blades 5, for example thirty-five blades 5, may be provided evenly distributed over the circumference.
  • Each vane wall 6 has an exposed upper end edge 12 extending in the opening plane E.
  • This end edge 12 runs radially inward into the inner boundary wall, in particular into the boundary wall edge 8, and terminates radially outward in the peripheral edge 9, in particular in the end wall edge 11 of the end wall 10.
  • a conceptual connecting line V can be drawn (compare, for example, FIG. 4).
  • the connecting line V in this case runs in the opening plane E or in a plane parallel thereto.
  • each blade wall 6 is perpendicular to the connecting line V with different offset a.
  • the largest offset a preferably results in the middle between the radially inner Boundary wall 7 and the radially outer end wall 10 and the peripheral edge edge 9th
  • the offset a corresponds in the illustrated embodiments about one third of the difference measure c of the second radius r 2 and the first radius ri ri.
  • the blade walls 6 of the embodiment illustrated in FIGS. 1 to 4 are designed so that their terminal edges 12 essentially follow a radius line.
  • the radius r 3 - relative to the radius center point facing inner peripheral edge of the terminal edge - is removed from a circle center P which is located in a direction of rotation d upstream vane chamber 4 or in the upstream vane chamber 4 of the vane chamber 4 separating blade wall 6.
  • the ends of the terminal edge 12 preferably extend tangentially in the facing boundary wall 7 or end wall 10.
  • the end sections of the terminal edge 12 can be opposite to one another
  • the radius r 3 changed radius be provided, in particular with a comparatively smaller radius whose circle center is located in the blade chamber 4 bounded by the described blade wall 6.
  • the circle center P of the radius r 3 can lie on the radius of the blade chamber 4 in the radial direction between the boundary wall 7 and end wall 10 radius line r 4 .
  • the circle center P is in the radial direction to the geometric impeller axis of rotation x by a dimension z with respect to the radius line offset radially outward.
  • the measure z corresponds to about one tenth to one fifth of the difference measure c.
  • the blade wall 6, in particular the terminal edge 12 at least partially composed of straight sections 13, each taking different acute angle to a radial in plan view according to Figure 5.
  • the straight sections 13 are arranged in total so that overall results in a direction of rotation d of the impeller 1 convex course.
  • an end edge 12 designed in this way can tangentially enter into the boundary wall 7 and into the peripheral edge 9 or into the end wall 10 with a radius line.
  • the radially outer end of the terminal edge 12, optionally a tangent T passing through the intersection of the terminal edge 12 and the end wall 10, may preferably include an acute angle ⁇ of about 70 ° with the connecting line V (see FIG. 4).
  • the radially outer end of the terminating edge 12 is provided by a curvature edge line of the terminating edge 12 in the case of a planar configuration of the terminating edge 12, as is preferred and also given for the exemplary embodiments.
  • the connecting line V extends in an extension in the direction of the geometric impeller rotation axis x at a distance b (see FIG. 1, for example) to the geometric impeller rotation axis x, which corresponds to a perpendicular distance measure b of about one twentieth to one fifteenth of the outer radius r2 ,
  • the vane walls 6 arranged one behind the other in the direction of rotation d and the inner boundary wall 7 and, in one embodiment, also the void wall 10 resulting radially outward bottom 14 extends in a cross section, in which cross section, the impeller axis of rotation x represents a line, circular section (see Figure 6).
  • the circle center of the circle bottom describing the chamber 14 is preferably within the opening plane E.
  • this circular line preferably also extends radially outward into the end edge 11 extending in the opening plane E.
  • the chamber bottom 14 may be formed in the form of a half rectangle with rounded corners 15 as shown in Figure 9.
  • Chamber bottom 14 is in this case preferably formed parallel to the opening plane E. From the regions of the rounded corners 15 facing away from the chamber bottom 14, wall sections extend into the opening plane E, which wall sections run parallel to the impeller rotation axis x or enclose an acute angle thereto.
  • the greatest depth u of a blade chamber 4 considered in the direction of the impeller rotation axis-removed from the opening plane E-can correspond to 0.5 times the difference measure c between the second radius dimension r 2 and the first radius dimension ri.
  • FIG. 8 With reference to a cross section through a blade wall 6 as shown in Figure 7 it can be seen that the blade wall 6, starting from the opening plane E and thus from the end edge 12, starting in the direction of the chamber bottom 14 increases in the wall thickness w. Thus, in the transition to the chamber bottom 14, a wall thickness w is indicated, which corresponds approximately to 3 times the wall thickness w in the region of the end edge 12. With reference to a, in the cross section, the end edge 12 centrally passing, parallel to the impeller axis of rotation x extending straight close the blade wall edges 16, in particular in the region of the radius line r 4 equal acute angle to the line. An alternative embodiment is shown in FIG. 8.
  • the blade wall edges 16 with the straight line different acute angle.
  • ßi for example, 15 to 30, in particular about 20 ° to the line
  • ß 2 an acute angle ß 2 to the straight line of, for example 2 to 5 °.
  • the blade chambers 4 may also be designed to be open radially outwards.
  • the blade wall 6, which ends radially free on the outside, in this case extends radially outward in the direction of the impeller rotation axis d and determines the dimension of the second radius dimension r 2 .
  • An impeller which is characterized in that the end edge 12 of a blade wall 6 extends radially outward also in the direction of the impeller rotation axis x and determines the measure of the second radius dimension r 2 .
  • An impeller which is characterized in that the blade wall 6 passes radially outward into a peripheral end wall 10 and that an outer edge of the end wall 10 determines the second radius dimension r 2 .
  • An impeller characterized in that the connecting line V extends in extension in the direction of the geometric impeller rotation axis x with a vertical distance b to the geometric impeller rotation axis x.
  • An impeller characterized in that the radially outer end of the terminal edge 12, optionally a tangent T passing through the intersection of the terminal edge 12 and the end wall 10, subtends an acute angle ⁇ of up to 90 ° with the connecting line V.
  • An impeller which is characterized in that the end edge 12 is composed at least partially of straight sections 13.
  • An impeller characterized in that the trailing edge 12 between the first ri and the second radius r 2 is continuously curved.
  • An impeller characterized in that the end edge 12 substantially follows a radius line.
  • An impeller which is characterized in that a radius r 3 of the terminal edge 12 is removed from a circle center P, which lies in a circumferentially following vane chamber 4.
  • An impeller which is characterized in that the blade wall 6, starting from the end edge 12, increases in the direction of the geometric impeller rotation axis x with respect to a wall thickness w.
  • An impeller characterized in that the increase of the wall thickness w with respect to the circumferential direction is different.
  • An impeller characterized in that, with respect to a cross section of the blade wall 6 between the inner inlet point and the outer end, for example in a middle between the first radius dimension ri and the second radius dimension r 2 , vane wall edges 16 with a parallel to the geometric Impeller axis of rotation x extending lines include different acute angle ß.
  • An impeller which is characterized in that the acute angle ßi of the blade wall edge 16 against the direction of rotation is greater than the pointed Angle ß 2 of the blade wall edge 16 in the direction of rotation.
  • An impeller which is characterized in that a blade wall 6 in the direction of rotation d is convex.
  • An impeller which is characterized in that a chamber bottom 14 of a blade chamber 4 in a cross section in the connecting line V or parallel to it runs in a circle or elliptical, in any case radially inwardly the circle or elliptical line extends into an upper edge of the inner end wall 10.
  • An impeller characterized in that a maximum depth u of a chamber bottom 14 corresponds to 0.25 to 0.75 times the radius difference c.

Landscapes

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

Abstract

L'invention concerne un rotor (1), en particulier pour une machine à canal latéral, présentant des aubes (5) disposées de façon répartie dans la direction circonférentielle, formées chacune par une paroi d'aube (6), qui forment des chambres d'aube (4) ouvertes en vue de dessus du rotor (1), dans lequel une paroi d'aube (6) commence, en vue de dessus, à une première mesure de rayon (r1) par rapport à l'axe de rotation géométrique du rotor (x), ladite valeur de rayon (r2) correspondant à la moitié ou plus d'une seconde mesure de rayon (r2), ladite mesure de rayon (r2) déterminant un bord périphérique (9) du rotor (1) et la mesure de rayon (r2) déterminant une paroi de limitation (7) interne radiale de la chambre d'aube (4), dans lequel en outre une paroi d'aube (6) présente un bord terminal supérieur détaché, qui pénètre dans la paroi de limitation (7) interne de façon correspondante radialement vers l'intérieur et se termine radialement vers l'extérieur en vue de dessus, dans lequel une ligne de liaison (V), mentale, peut être tracée entre un point d'entrée du bord terminal dans la paroi de limitation interne (7) et une extrémité externe radiale du bord terminal (12) et le bord terminal s'étend perpendiculairement à la ligne de liaison (V) avec des mesures de départ différentes, une mesure de départ maximale étant donnée. Selon une amélioration avantageuse, en particulier en ce qui concerne un degré d'efficacité amélioré, selon l'invention la mesure de départ correspond à 0,1 fois ou plus la différence de la seconde (r2) et de la première (r1) mesure de rayon.
EP15712837.2A 2014-05-08 2015-03-19 Rotor pour turbomachine régénératrice Active EP3140548B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102014106440.2A DE102014106440A1 (de) 2014-05-08 2014-05-08 Laufrad, insbesondere für eine Seitenkanalmaschine
PCT/EP2015/055775 WO2015169496A1 (fr) 2014-05-08 2015-03-19 Rotor, en particulier pour une machine à canal latéral

Publications (2)

Publication Number Publication Date
EP3140548A1 true EP3140548A1 (fr) 2017-03-15
EP3140548B1 EP3140548B1 (fr) 2023-05-03

Family

ID=52774195

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15712837.2A Active EP3140548B1 (fr) 2014-05-08 2015-03-19 Rotor pour turbomachine régénératrice

Country Status (8)

Country Link
US (1) US10378543B2 (fr)
EP (1) EP3140548B1 (fr)
JP (1) JP2017515042A (fr)
KR (1) KR20170005841A (fr)
CN (1) CN106460851B (fr)
DE (1) DE102014106440A1 (fr)
TW (1) TWI648471B (fr)
WO (1) WO2015169496A1 (fr)

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Also Published As

Publication number Publication date
JP2017515042A (ja) 2017-06-08
CN106460851B (zh) 2020-03-17
US10378543B2 (en) 2019-08-13
EP3140548B1 (fr) 2023-05-03
US20170051753A1 (en) 2017-02-23
TW201600730A (zh) 2016-01-01
KR20170005841A (ko) 2017-01-16
TWI648471B (zh) 2019-01-21
CN106460851A (zh) 2017-02-22
WO2015169496A1 (fr) 2015-11-12
DE102014106440A1 (de) 2015-11-12

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