EP0741247A2 - Anneau de commande - Google Patents

Anneau de commande Download PDF

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Publication number
EP0741247A2
EP0741247A2 EP96106866A EP96106866A EP0741247A2 EP 0741247 A2 EP0741247 A2 EP 0741247A2 EP 96106866 A EP96106866 A EP 96106866A EP 96106866 A EP96106866 A EP 96106866A EP 0741247 A2 EP0741247 A2 EP 0741247A2
Authority
EP
European Patent Office
Prior art keywords
ring
compressor
adjusting ring
adjusting
thermal expansion
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
EP96106866A
Other languages
German (de)
English (en)
Other versions
EP0741247B1 (fr
EP0741247A3 (fr
Inventor
Frank Kocian
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.)
Deutsches Zentrum fuer Luft und Raumfahrt eV
Original Assignee
Deutsches Zentrum fuer Luft und Raumfahrt eV
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 Deutsches Zentrum fuer Luft und Raumfahrt eV filed Critical Deutsches Zentrum fuer Luft und Raumfahrt eV
Publication of EP0741247A2 publication Critical patent/EP0741247A2/fr
Publication of EP0741247A3 publication Critical patent/EP0741247A3/fr
Application granted granted Critical
Publication of EP0741247B1 publication Critical patent/EP0741247B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T403/00—Joints and connections
    • Y10T403/21—Utilizing thermal characteristic, e.g., expansion or contraction, etc.
    • Y10T403/217—Members having different coefficients of expansion

Definitions

  • the present invention relates to an adjusting ring for synchronously changing the angle of attack of guide vanes of a compressor, which has several bearing points for mounting on a housing of the compressor.
  • Such adjusting rings are used, in particular in aeronautical engineering, to adapt the compressor to different operating conditions by adjusting the guide vanes, so as to enable optimal operation of the compressor under different requirement profiles.
  • the invention was therefore based on the object of providing an adjusting ring which can be made at least partially from materials with a low coefficient of thermal expansion and is nevertheless temperature-compatible with a metallic compressor housing.
  • the adjusting ring comprises curved ring segments arranged between two adjacent bearing points, the curvature of which decreases as the temperature of the ring segments increases, so that the bearing points between the ring segments in the radial direction to the outside be moved.
  • the concept according to the invention has the advantage that by changing the geometry of the adjusting ring, the bearing points of the same are displaced far enough in the radial direction to prevent the adjusting ring from shrinking on the compressor housing.
  • a homogeneous thermal expansion of the adjusting ring is not necessary for the thermal expansion compatibility between the adjusting ring and the compressor housing, so that the adjusting ring with the required structural stiffness can be made at least partially from non-metallic materials with a very small, vanishing or even negative coefficient of thermal expansion and sufficient stiffness.
  • the element carried comprises a material with greater thermal expansion than that of the material of the carrier, it is to be provided that the curvature of the ring or tube segments increases with an increase in temperature, so that the bearing points are displaced radially inwards.
  • the adjusting ring advantageously comprises at least three ring segments in order to obtain a sufficient number of bearing points for the mounting of the adjusting ring on the compressor housing.
  • the geometry change effect decreases with an increasing number of ring segments into which the adjusting ring is divided, while the manufacturing costs of the adjusting ring increase, so that it is advantageous if the adjusting ring comprises at most 16 ring segments.
  • Embodiments of the adjusting ring with six to ten ring segments are particularly preferred.
  • the curvature of the ring segments when the temperature rises can advantageously be achieved in that the ring segments each have a peripheral part arranged on the outside of the adjusting ring, which has a first coefficient of thermal expansion in the circumferential direction of the adjusting ring, and a beam arranged on the inside of the adjusting ring, which has a second coefficient of thermal expansion in Has circumferential direction of the adjusting ring, wherein the second coefficient of thermal expansion is greater than the first coefficient of thermal expansion and the peripheral part and the beams of each ring segment are fixed to one another in such a way that the curvature of the ring segments decreases as the temperature of the ring segments increases.
  • the required change in the geometry of the adjusting ring is brought about here by an effect similar to the bimetal effect known from temperature measuring strips when the temperature of the ring segments rises.
  • At least the peripheral parts of the ring segments can be made from a non-metallic material.
  • the beams In order to increase the curvature of the ring segments when the temperature rises, the beams would have to be arranged on the outside instead of on the inside of the adjusting ring.
  • peripheral parts consist at least partially of a fiber composite material.
  • This composite material can be, for example, a carbon fiber composite material or glass fiber composite material.
  • the fibers of the fiber composite material are aligned essentially in the circumferential direction of the adjusting ring.
  • a particularly high rigidity and strength of the adjusting ring is achieved in the circumferential direction.
  • any material that has a significantly greater coefficient of thermal expansion than the material of the peripheral parts in particular also a fiber composite material with a corresponding coefficient of thermal expansion, can be used as the material for the beams.
  • an embodiment of the adjusting ring is particularly preferred in which the beams are at least partially made of aluminum, in particular an aluminum powder alloy.
  • each ring segment of the adjusting ring can be manufactured as individual parts and can only be joined together when the adjusting ring is assembled.
  • peripheral parts of a plurality of adjacent ring segments are formed in one piece with one another.
  • peripheral parts of the ring segments are designed as two peripheral half rings, since in this way an advantageous compromise between assembly and manufacturing costs is achieved.
  • peripheral parts of all ring segments are formed in one piece with one another.
  • a further embodiment of the invention relates to a compressor with a compressor housing, guide vanes and an adjusting ring for synchronously changing the angle of attack of the guide vanes, in which the adjusting ring is an adjusting ring according to one of claims 1 to 12.
  • the compressor comprises sliding shoes on which the adjusting ring is mounted and which each have a sliding surface for sliding on the compressor housing.
  • sliding shoes can also advantageously consist of a fiber composite material in order to achieve a weight saving.
  • the compressor housing comprises adjusting ring carriers, each of which has a sliding surface.
  • the compressor comprises both sliding shoes and adjusting ring carriers, the sliding surfaces of the sliding shoes being able to slide on the sliding surfaces of the adjusting ring carriers.
  • the adjusting ring carrier advantageously consists of a fiber composite material in order to save further weight.
  • the adjusting ring supports In a preferred embodiment of the adjusting ring supports, they have a layer structure in which dense fabric layers and less dense spacing layers follow one another in an axial direction of the compressor. Cavities contained in the spacing layers reduce the weight of the adjusting ring carrier in a particularly effective manner.
  • the fabric layers have a negative coefficient of thermal expansion in the radial direction of the compressor.
  • the adjusting ring carriers shorten when the temperature rises in the radial direction of the compressor and thus partially compensate for the expansion of the compressor housing.
  • a smaller displacement of the support points of the adjustment ring in the radial direction is sufficient to ensure thermal expansion compatibility between the adjustment ring and the compressor housing.
  • a particularly large negative coefficient of thermal expansion of the fabric layers in the radial direction can be achieved if the fabric layers are fibers which are oriented at an angle of approximately plus 30 ° to the radial direction of the compressor and fibers which are at an angle of approximately minus 30 ° are aligned against the radial direction of the compressor.
  • a thermal insulation layer is arranged between the compressor housing and each of the adjusting ring carriers.
  • the thermal expansion coefficients of the circumferential parts and beams of the ring segments are matched to one another and to the length and curvature of the ring segments in such a way that the support points of the adjusting ring are displaced radially outward by the same distance as the adjusting ring carrier when the temperature rises.
  • This allows the game to run during an operating cycle (Heating to operating temperature and cooling of the compressor) at the bearing points of the adjusting ring can be kept small, so that the position of the adjusting ring is precisely defined and the angle of attack of the guide vanes of the compressor can be set exactly.
  • it is necessary that the effective specific thermal expansion of the adjusting ring at the bearing points is greater than the specific thermal expansion of the compressor housing, since the adjusting ring has a lower temperature than the compressor housing in the operating state.
  • An adjusting ring 10 according to the invention shown in FIG. 1 of a compressor designated as a whole by 11 comprises several, for example eight, substantially circular arc-shaped ring segments 12, of which two adjacent ring segments 12 are shown enlarged in FIG. 2.
  • Each of the ring segments 12 comprises a circumferential part 14 in the form of a circular ring section arranged on the outside of the adjusting ring 10 and one on the inside of the circumferential part 14, for example on four contact surfaces 16, fixed beam 18, which projects from the inside of the peripheral part 14 to an axis 20 of the adjusting ring 10.
  • the peripheral parts 14 are made of such a material that they have a small, vanishing or even negative coefficient of thermal expansion along the circumferential direction of the adjusting ring 10.
  • peripheral parts 14 can be produced, for example, by producing the peripheral parts 14 from a carbon fiber composite material, the carbon fibers being aligned parallel to the peripheral direction of the adjusting ring 10. In this case, the coefficient of thermal expansion for the expansion along the circumference of the ring disappears practically completely.
  • the peripheral parts 14 can also be produced from a glass fiber composite material.
  • the coefficient of thermal expansion for the expansion along the circumference of the ring is clearly in the positive range, but is still only around half the coefficient of thermal expansion of the metallic compressor housing.
  • FIGS. 1 to 5 In the exemplary embodiment of the adjusting ring according to the invention shown in FIGS. 1 to 5, four adjacent circumferential parts 14 are each formed integrally with one another and form a circumferential half ring 22.
  • the two circumferential half rings 22 thus created are at two connection points 24 (of which only one in FIG. 1) can be seen) fixed to one another and thus form a complete, closed circumferential ring 26.
  • Each of the beams 18 has essentially the shape of a section of a hollow ring profile with a rectangular cross section, the side wall of the profile facing the respective peripheral part 14 having the same height as the peripheral part 14 and being flush with the same.
  • Each beam 18 is chamfered at both ends and has, for example, three recesses 28 arranged between the bearing surfaces 16 to save weight.
  • Each beam 18 has in the area of each of its, for example four, support surfaces 16 each a radial through bore 30, which is aligned with a corresponding radial through bore 32 in the associated peripheral part 14, as shown in FIG. 3.
  • an internally threaded threaded insert 34 is arranged, into which a hollow cylindrical guide bushing 36 is screwed, which guides the through holes 30 and 32 in the beam 18 or penetrates in the associated peripheral part 14 and carries at its outer end in the radial direction a ring 38 which rests on the outside of the peripheral part 14.
  • the beams 18 are fixed to the associated peripheral parts 14 by the guide bushes 36 in connection with a threaded insert 34 in each case.
  • the beams 18 are made of a material that has a high coefficient of thermal expansion at least in the circumferential direction of the adjusting ring 10.
  • an aluminum powder alloy can be used, which moreover ensures sufficient bending stiffness of the ring segments 12 even at high temperatures.
  • the through bores 32 in the peripheral parts 14 are arranged equidistantly from one another along the circumference of the peripheral parts 14.
  • a further radial through-hole 40 is provided in the circumferential ring 26, which is at the same distance from the adjacent through-holes 32 as two directly adjacent through-holes 32 .
  • an essentially cuboid bearing block 42 is arranged on the inside of the circumferential ring 26 in such a way that a threaded hole 44 penetrating the center of the bearing block 42 in the radial direction of the compressor 11 is aligned with the through hole 40 in the circumferential ring 26, as shown in FIG. 4.
  • each support block 42 has two projections 45, which protrude in opposite directions from the support block 42 in the circumferential direction of the adjusting ring 10 and bear against both the inside of a circumferential part 14 and a respective beam 18.
  • a hollow cylindrical guide bushing 36 which is provided with an external thread, is screwed into the threaded bore 44 and passes through the through bore 40 in the circumferential ring 26 and rests with its ring 38 on the outside of the circumferential ring 26.
  • the area of the bearing block 42 lying inside in the radial direction is guided in a substantially cuboid recess 46 of a sliding block 48 so that it can be moved in the radial direction with little play.
  • the adjusting ring 10 is supported on the sliding block 48 on the outer surfaces of the bearing blocks 42 aligned in the radial direction of the compressor.
  • the support blocks 42 thus represent support points of the adjusting ring 10.
  • a concave sliding surface 50 of the sliding block 48 facing away from the support block 42 and lying in the radial direction has the shape of a cutout from an annular surface, is provided with a sliding coating and lies on a correspondingly curved convex sliding surface 52 of an adjusting ring carrier referred to as a centralizer 54. Since the amount and direction of the curvatures of the concave sliding surface 50 of the sliding block 48 on the one hand and the convex sliding surface 52 of the centralizer 54 coincide with one another, each sliding block 48 can slide on the associated centralizer 54 in the circumferential direction of the adjusting ring 10.
  • Each centralizer 54 has an upper and a lower, each substantially trapezoidal guide plate 56, between which the beams 18 of the ring segments 12 adjacent to the respective centralizer 54 at one Movement of the adjusting ring 10 are performed along its circumference.
  • the clear distance between the two guide plates 56 of each centralizer is slightly larger than the height of the beams 18.
  • each of the centralizers 54 has a stepped, central radial through-bore 58, which comprises a further section 60 lying on the outside in the radial direction and a narrower section 62 on the inside in the radial direction.
  • the narrower section 62 of the stepped through-bore 58 opens onto a base surface 64 of the centralizer 54 which lies in the radial direction and which rests on an essentially cuboidal insulation block 66 which is in turn supported by a substantially hollow cylindrical compressor housing 68 arranged coaxially to the adjusting ring 10 .
  • the centralizer 54 is penetrated perpendicularly to the guide plates 56 by a further through hole 69 which intersects the stepped through hole 58 and into which a cylindrical pin 70 is inserted such that a central radial through hole thereof is aligned with the narrower section 62 of the stepped through hole 58.
  • Each centralizer 54 is screwed into a radial threaded hole 72 in the compressor housing 68 by means of a screw 71 which passes through the through hole in the pin 70, the narrower section 62 of the stepped through hole 58 and a through hole aligned therewith in the insulation block 66, and with its head on it Pin 70 is applied.
  • a good force coupling into the centralizer 54 is achieved by the pin 70.
  • the centralizers 54 can be made of carbon fiber composite material so that they have a low positive, a vanishing or a negative coefficient of thermal expansion.
  • FIG. 5 A layer structure of the centralizer material which is advantageous in order to achieve a negative coefficient of thermal expansion in the radial direction and a low weight is shown in FIG. 5.
  • dense fabric layers 73 and less dense spacer layers 74 which comprise webs 75 of spacer fabric oriented transversely to the fabric layers 73, follow one another in the axial direction of the compressor.
  • the fabric layers 73 comprise fibers which are arranged at an angle of approximately plus 30 ° with respect to the radial direction of the compressor and fibers which are oriented at an angle of approximately minus 30 ° with respect to the radial direction of the compressor in order to maximize the amount to obtain negative thermal expansion coefficients of the centralizer 54 in the radial direction of the compressor.
  • the radial direction of the compressor is represented by the arrow 73a and the directions in which the fibers of the fabric layers 73 are aligned by the arrows 73b and 73c.
  • the insulation blocks 66 can be made of a high-temperature-resistant plastic that has a high thermal resistance, so that the amount of heat transferred from the compressor housing 68 during operation of the compressor via the centralizer 54 to the adjusting ring 10 and thus the thermal load on the adjusting ring 10 is kept as low as possible .
  • each of the guide vanes 78 has an adjusting shaft 80 which projects outward in the radial direction, each of which penetrates a radial through bore 82 in the compressor housing 68 and a bearing bushing 84 which is arranged on the outer wall of the compressor housing 68 and is coaxial with the adjusting shaft 80 and is rotationally fixed at its free end is connected to an adjustment arm 86 aligned perpendicular to the axis of the adjustment shaft 80.
  • each of the adjustment arms 86 carries a pivot pin 88 which projects inwards in the radial direction and which is mounted in each of the guide bushings 36 of the circumferential ring 26. This creates an articulated connection between the adjusting ring 10 on the one hand and the guide vane grille 76 on the other hand.
  • the beams 18 of the adjusting ring 10 are arranged centrally between two adjacent centralizers 54, and the adjusting arms 86 are aligned parallel to the axis 20 of the adjusting ring 10 and the compressor housing 68.
  • the guide vanes 78 are aligned against the axis 20 at a rest angle of incidence.
  • the adjusting ring 10 is rotated clockwise from above by a movement mechanism (not shown) along its circumference relative to the compressor housing 68, the pivot pins 88 in the guide bushes 36 follow this movement of the adjusting ring 10, as a result of which the adjusting arms 86 assume an oblique position relative to the Take axis 20.
  • the adjusting shafts 80 which are non-rotatably connected to the adjusting arms 86, correspondingly rotate counterclockwise when viewed in the radial direction. This in turn reduces the angle of attack between the guide vanes 78 and the axis 20 of the adjusting ring 10 and the compressor housing 68.
  • the angle of attack of the guide vanes 78 of the compressor can be synchronously adapted to the respective operating conditions. Due to the circumferential ring 26 made of carbon fiber composite material, the adjusting ring 10 has high rigidity and strength in the circumferential direction, while the beams 18 made of aluminum ensure a high bending rigidity of the adjusting ring 10.
  • the operating temperature of the compressor is significantly above room temperature.
  • the compressor housing 68 therefore expands until the operating temperature is reached, as a result of which the centralizers 54 arranged on the circumference of the compressor housing 68 and the sliding shoes 48 resting on the convex sliding surfaces 52 of the centralizers 54 are displaced radially outward.
  • the support points for the support blocks 42 forming the adjusting ring 10 must move outward by a corresponding distance in the radial direction in order to prevent the sliding shoes 48 from being pressed too strongly against the convex sliding surfaces 52 of the centralizers 54, so that the concave sliding surfaces 50 slide off on the convex sliding surfaces 52 and thus a rotation of the adjusting ring 10 in the circumferential direction is made difficult or even impossible.
  • the required thermal expansion compatibility is achieved by the interaction of the beams 18 with a comparatively large thermal expansion coefficient in the circumferential direction of the adjusting ring 10 with the peripheral parts 14, which have a small or vanishing thermal expansion coefficient in the circumferential direction.
  • FIG. 6 shows a highly schematic and simplified top view of the adjusting ring 10 according to the invention, which is composed of eight ring segments 12, two adjacent ring segments 12 each adjoining one another at a bearing point 90.
  • the eight ring segments 12 each essentially have the shape of an eighth circle with a radius R 1 . Consequently, the adjusting ring 10 at this temperature is a circle with the radius R 1 , from the center 92 of which the bearing points 90 are each at a distance R 1 .
  • FIG. 7 shows the highly schematic adjustment ring 10 from FIG. 6 at an operating temperature that is significantly above the idle temperature.
  • the ring segments 12 are less curved at the operating temperature. In order to clarify the curvature of the ring segments 12, these are shown in FIG. 7 as straight sections, which is greatly exaggerated, but most clearly shows the significant geometry change effect.
  • the adjusting ring 10 no longer corresponds to an exact circle with a radius R 1 , but instead the adjusting ring 10 is deformed into an octagon, the corners of which are formed by the bearing points 90 between the ring segments 12.
  • the bearing points 90 are displaced radially outward by substantially the same amount as the sliding shoes 48, which makes the thermal expansion compatibility between the adjusting ring 10 and the compressor housing 68 is ensured.
  • the adjusting ring 10 can easily be rotated with respect to the compressor housing 68 along its circumference along its periphery by sliding the concave sliding surfaces 50 of the sliding shoes 48 on the convex sliding surfaces 52 of the centralizers 54 both at the rest temperature and at the maximum operating temperature and at all temperatures in between , so that an exactly synchronous change of the angle of attack of the guide vanes 78 is possible in every operating state.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Rotary Pumps (AREA)
EP96106866A 1995-05-04 1996-05-01 Anneau de commande Expired - Lifetime EP0741247B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19516382A DE19516382A1 (de) 1995-05-04 1995-05-04 Verstellring
DE19516382 1995-05-04

Publications (3)

Publication Number Publication Date
EP0741247A2 true EP0741247A2 (fr) 1996-11-06
EP0741247A3 EP0741247A3 (fr) 1998-05-20
EP0741247B1 EP0741247B1 (fr) 2003-02-26

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ID=7761078

Family Applications (1)

Application Number Title Priority Date Filing Date
EP96106866A Expired - Lifetime EP0741247B1 (fr) 1995-05-04 1996-05-01 Anneau de commande

Country Status (4)

Country Link
US (1) US5700129A (fr)
EP (1) EP0741247B1 (fr)
JP (1) JP2703750B2 (fr)
DE (2) DE19516382A1 (fr)

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EP1696134A2 (fr) 2005-02-25 2006-08-30 Snecma Dispositif de réglage du centrage d'un anneau de synchronisation de commande d'aubes pivotantes de turbomachine
EP2107217A1 (fr) * 2008-03-31 2009-10-07 Siemens Aktiengesellschaft Ensemble d'anneau de commande pour boîtier de compresseur axial
EP2481892A3 (fr) * 2011-02-01 2013-12-18 United Technologies Corporation Ecarteur d'anneau de synchronisation de turbine à gaz
DE102017124339A1 (de) 2017-10-18 2019-04-18 Deutsches Zentrum für Luft- und Raumfahrt e.V. Verstellring, Verdichter und Verfahren zum Betreiben eines Verstellrings

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US20140064912A1 (en) * 2012-08-29 2014-03-06 General Electric Company Systems and Methods to Control Variable Stator Vanes in Gas Turbine Engines
US9932851B2 (en) 2013-12-30 2018-04-03 Rolls-Royce North American Technologies, Inc. Active synchronizing ring
DE102016122639A1 (de) * 2016-11-23 2018-05-24 Rolls-Royce Deutschland Ltd & Co Kg Leitschaufelbaugruppe mit Ausgleichseinrichtung
FR3063779B1 (fr) * 2017-03-07 2022-11-04 Safran Aircraft Engines Anneau de commande de calage d'un etage d'aube d'un stator
CN107023511A (zh) * 2017-05-19 2017-08-08 象州县科学技术情报研究所 一种叶片可调式离心风机叶轮
FR3082562B1 (fr) 2018-06-19 2020-06-12 Safran Aircraft Engines Anneau de commande de portes de decharge pour une turbomachine d'aeronef et turbomachine le comportant
CN109129250B (zh) * 2018-10-18 2020-05-19 北京动力机械研究所 一种涡轮发动机导向器流通能力调节工装
US11255214B2 (en) * 2019-11-04 2022-02-22 Raytheon Technologies Corporation Negative thermal expansion compressor case for improved tip clearance
JP7431640B2 (ja) * 2020-03-31 2024-02-15 川崎重工業株式会社 ガスタービンエンジンのユニゾンリング
CN119825754A (zh) * 2025-01-24 2025-04-15 中国航空发动机研究院 一种基于金属扶正器的分布式压气机静叶电驱调节机构

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Cited By (7)

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Publication number Priority date Publication date Assignee Title
EP1696134A2 (fr) 2005-02-25 2006-08-30 Snecma Dispositif de réglage du centrage d'un anneau de synchronisation de commande d'aubes pivotantes de turbomachine
EP1696134A3 (fr) * 2005-02-25 2012-11-14 Snecma Dispositif de réglage du centrage d'un anneau de synchronisation de commande d'aubes pivotantes de turbomachine
EP2107217A1 (fr) * 2008-03-31 2009-10-07 Siemens Aktiengesellschaft Ensemble d'anneau de commande pour boîtier de compresseur axial
WO2009121665A1 (fr) * 2008-03-31 2009-10-08 Siemens Aktiengesellschaft Ensemble anneau de conjugaison pour carter de compresseur axial
US8123472B2 (en) 2008-03-31 2012-02-28 Siemens Aktiengesellschaft Unison ring assembly for an axial compressor casing
EP2481892A3 (fr) * 2011-02-01 2013-12-18 United Technologies Corporation Ecarteur d'anneau de synchronisation de turbine à gaz
DE102017124339A1 (de) 2017-10-18 2019-04-18 Deutsches Zentrum für Luft- und Raumfahrt e.V. Verstellring, Verdichter und Verfahren zum Betreiben eines Verstellrings

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JP2703750B2 (ja) 1998-01-26
US5700129A (en) 1997-12-23
JPH08312593A (ja) 1996-11-26
DE59610160D1 (de) 2003-04-03
DE19516382A1 (de) 1996-11-07
EP0741247B1 (fr) 2003-02-26
EP0741247A3 (fr) 1998-05-20

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