EP3954875B1 - Aube directrice, étage de compresseur pour une turbine à gaz, turbomachine et procédé pour exploiter une turbomachine - Google Patents

Aube directrice, étage de compresseur pour une turbine à gaz, turbomachine et procédé pour exploiter une turbomachine Download PDF

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Publication number
EP3954875B1
EP3954875B1 EP21187375.7A EP21187375A EP3954875B1 EP 3954875 B1 EP3954875 B1 EP 3954875B1 EP 21187375 A EP21187375 A EP 21187375A EP 3954875 B1 EP3954875 B1 EP 3954875B1
Authority
EP
European Patent Office
Prior art keywords
section
guide vane
profile
airfoil
axis
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
EP21187375.7A
Other languages
German (de)
English (en)
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EP3954875A2 (fr
EP3954875A3 (fr
Inventor
Sergio Elorza Gomez
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines AG
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 MTU Aero Engines AG filed Critical MTU Aero Engines AG
Publication of EP3954875A2 publication Critical patent/EP3954875A2/fr
Publication of EP3954875A3 publication Critical patent/EP3954875A3/fr
Application granted granted Critical
Publication of EP3954875B1 publication Critical patent/EP3954875B1/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00—Axial-flow pumps
    • F04D19/02—Multi-stage pumps
    • F04D19/022—Multi-stage pumps with concentric rows of vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • F01D17/165—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for radial flow, i.e. the vanes turning around axes which are essentially parallel 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
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F04D29/544—Blade shapes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps

Definitions

  • the present invention relates to a guide vane, a compressor stage for a gas turbine and a turbomachine, in particular a gas turbine, with the guide vane and a method for operating the turbomachine, in particular a gas turbine.
  • An object of an embodiment of the present invention is to provide an improved guide vane and/or to improve the operation of a turbomachine, in particular a gas turbine.
  • Claims 8 and 9 protect a compressor stage for a gas turbine or a turbomachine, in particular a gas turbine, with one or more guide vanes described here.
  • Advantageous embodiments of the invention are the subject of the subclaims.
  • a guide vane has an airfoil, which in turn has a first airfoil section and a second airfoil section, wherein the first airfoil section is reversibly rotatable, preferably rotatably mounted, about an axis of rotation from a first position to a second position relative to the second airfoil section.
  • the rotation axis forms an angle of no more than 15° with a radial direction; in a further development, it extends in the radial direction. This allows particularly advantageous adjustment kinematics to be implemented in one embodiment.
  • an axial direction is parallel to a rotating or (main) machine axis of a turbomachine, in particular a gas turbine, for which or in which the guide vane is provided or arranged or used in one embodiment
  • a circumferential direction in one embodiment is a direction of rotation about this rotating or (main) machine axis
  • a radial direction is a direction perpendicular to the axial and circumferential direction or a direction (axis) that perpendicularly intersects the rotating or (main) machine axis.
  • a flow direction is a direction of an intended or designed flow and/or a direction from a leading to a trailing edge of the guide vane or its blade and/or parallel to the rotating or
  • a leading edge is accordingly an upstream edge or edge closer to an inlet
  • a trailing edge is accordingly a downstream edge or edge closer to an outlet.
  • a most upstream point of an intersection of a blade or its first or second blade section with a cylinder is around the rotation or
  • radially successive profile (sections) which are threaded along the threading axis in one embodiment define or form the blade or its outer contour and corresponding elements of these profile (sections) as profile (sections) form the first blade section or its outer contour and other elements of these profile (sections) as profile (sections) form the second blade section or its outer contour.
  • Profile and profile section can in particular be synonymous.
  • the axis of rotation is arranged outside a profile section of the first blade section. In one embodiment, the axis of rotation is arranged outside the blade.
  • an adjustment of the guide vane can be realized which is particularly advantageous aerodynamically and/or mechanically, and in one embodiment, low-loss, compact, simple and/or reliable.
  • the rotatable first blade section can be arranged upstream in a flow direction and the second blade section can be arranged downstream of the first blade section in a flow direction.
  • variations in an angle of attack or incidence can advantageously be at least partially compensated, and in one embodiment, pressure losses and/or efficiency losses usually associated with such a variation can be reduced.
  • the rotatable first blade section can be arranged downstream in a flow direction and the second blade section can be arranged upstream of the first blade section in a flow direction. This allows the outflow condition to be advantageously varied.
  • this makes it possible to reduce the negative effect of a leakage (back)flow between the first and second blade section, in particular the risk of this flow separating from the suction side of the second blade section.
  • the first blade section is separated from the second blade section by a gap, in particular a contact gap or gap in which the first and second blade sections contact each other, or a free gap or gap in which the first and second blade sections do not contact each other, or the first and second blade sections are unconnected.
  • the first blade section is arranged on, in one embodiment on, at least one platform, in particular a turntable, which can rotate about the axis of rotation and is rotatably mounted in one embodiment, in one embodiment on or on two radially opposite platforms or turntables, between which the first blade section is then arranged.
  • the first blade section is connected or integrally formed with the or one or both platforms or turntables in a way that is detachable in a non-destructive manner, in particular frictionally and/or positively, or in a non-destructive manner, in particular with a material fit.
  • the first blade section is arranged on the edge of the or one or both platforms or turntables.
  • a distance to the axis of rotation along the first contour section of the first blade section varies by at most 10%, in particular by at most 5%, in one embodiment by at most 1%, in particular the first contour section can thus be a segment of a (first) circle around the axis of rotation.
  • a distance to the axis of rotation along the second contour section of the first blade section varies by at most 10%, in particular by at most 5%, in one embodiment by at most 1%, in particular the second contour section can thus be a segment of a circle, in particular the first circle, around the axis of rotation.
  • a distance to the axis of rotation along the pressure-side contour section of the second blade section varies by at most 10%, in particular by at most 5%, in one embodiment by at most 1%, in particular the pressure-side contour section can thus be a segment of a circle around the axis of rotation, in particular concentric with the first circle.
  • the first blade section has a conical or cylindrical region which has the first and second contour section(s), and/or the second blade section has a conical or cylindrical region, in particular one which is congruent therewith, which has the pressure-side contour section(s).
  • the guide vane has a seal, in one embodiment elastic and/or contacting, in one embodiment a lip or brush seal, which reduces a gap width between regions of the first and second blade section that are opposite one another in the first and/or second position or is provided for this purpose, in particular is designed or used.
  • the seal can be provided in particular on the second blade section, in particular on the pressure-side contour section of the second blade section, and/or on the first blade section, in particular on the first and/or second contour section of the first blade section.
  • the axis of rotation is arranged on the side of the pressure side of the blade or to the side of the pressure side of the blade.
  • the axis of rotation is arranged downstream of a leading edge of the second blade section.
  • the axis of rotation is arranged upstream of a trailing edge of the second blade section.
  • the axis of rotation in the at least one profile section of the blade is arranged outside the profile (section) of the second blade section. In one embodiment, the axis of rotation is arranged outside the second blade section.
  • an adjustment of the guide vane can be realized which is particularly advantageous aerodynamically and/or mechanically, and in one embodiment, low-loss, compact, simple and/or reliable.
  • the guide vane has an outer shroud, which in one embodiment is arranged radially outward from the blade, and/or an inner shroud, which in one embodiment is arranged radially inward from the blade.
  • the first blade section is mounted on the outer shroud, in one embodiment via the or one of the platforms, so as to be rotatable about the axis of rotation.
  • the first blade section is mounted on the inner shroud, in one embodiment, via the other of the platforms, so as to be rotatable about the axis of rotation.
  • the second blade section is arranged fixedly, in particular rotationally fixed, in one embodiment, on the outer shroud, in one embodiment it can be detached non-destructively, in particular frictionally and/or positively, or it can not be detached non-destructively, in particular materially, connected or formed integrally with the outer shroud.
  • the second blade section is arranged fixedly, in particular rotationally fixed, in one embodiment, on the inner shroud, in one embodiment it can be detached non-destructively, in particular frictionally and/or positively, or it can not be detached non-destructively, in particular materially, connected or formed integrally with the inner shroud.
  • an adjustment of the guide vane can be realized which is particularly advantageous aerodynamically and/or mechanically, and in one embodiment, low-loss, compact, simple and/or reliable.
  • the present invention is particularly suitable for gas turbines and in particular their compressor stages and/or outlet guide vanes and is used accordingly in an embodiment for this purpose, particularly preferably as or in a compressor stage outlet guide vane (blade) of a gas turbine, in particular an aircraft engine gas turbine, or is employed therein, without, however, being restricted thereto.
  • a compressor stage outlet guide vane blade of a gas turbine, in particular an aircraft engine gas turbine, or is employed therein, without, however, being restricted thereto.
  • the first vane section(s) thereof is/are adjusted or rotated, in one embodiment synchronously, from the first to the second position.
  • an axial distance between a leading edge of the first blade section and a trailing edge of the second blade section of the guide vane(s) in the second position or an axial extension of the guide vane(s) in the second position is shorter than in the first position. Additionally or alternatively, in one embodiment, a distance in the circumferential direction between a leading edge of the first blade section and a leading or trailing edge or suction side of the second blade section of the guide vane(s) in the second position or an axial extension of the guide vane(s) in the second position is shorter than in the first position.
  • the first blade section of the guide vane or the first blade sections of the guide vanes is/are adjusted or rotated into the second position in or for operation at an operating point with a suction-side angle of attack and/or into the first position in or for operation at an operating point with a pressure-side angle of attack.
  • this makes it possible to improve the operation of the turbomachine, in particular the gas turbine, and in particular its efficiency.
  • the first blade section is adjustable or rotatable, preferably continuously, in positions between the first and second positions and/or beyond the first and/or second positions.
  • Fig.1 shows a profile section of an airfoil of a guide vane according to an embodiment of the present invention in a first position.
  • the blade has an upstream first blade section 10 which in the profile section of the Fig.1 a profile (section) 11 with a suction side 12, and a in a flow direction (from left to right in Fig.1 ) second blade section 20, which in the profile section of the Fig.1 has a profile (section) 21.
  • the second blade section 20 is fixedly arranged on an outer shroud 30.
  • the first blade section 10 is separated from the second blade section by a gap S in which a seal 22 is arranged on the second blade section 20, which reduces the gap width, at least substantially, to zero.
  • the first and second blade sections can contact each other, and a free gap can also be formed between them.
  • the first blade section 10 is arranged on a platform 40 which can be rotated about an axis of rotation D and is mounted on the outer shroud 30 via this platform 40 so that it can rotate about the axis of rotation D.
  • a platform 40 which can be rotated about an axis of rotation D and is mounted on the outer shroud 30 via this platform 40 so that it can rotate about the axis of rotation D.
  • Fig.1 At the radial (perpendicular to the plane of the drawing of the Fig.1 ) opposite and therefore in Fig.1
  • the guide vane which is not visible, it can be arranged in an analogous manner on an inner shroud or it can also be designed without an inner shroud.
  • the rotation axis D is on the side of the pressure side (bottom in Fig.1 ) and in the profile section of the Fig.1 outside the profile 11 of the first blade section 10, downstream of a leading edge 23, upstream of a trailing edge 24 and outside the profile 21 of the second blade section 20.
  • the suction side 12 of the profile 11 of the first blade section 10 has a first contour section 12A and a second contour section 12B adjoining it upstream, the profile 21 of the second blade section 20 has a pressure-side contour section 21A.
  • the first contour section 12A covers the pressure-side contour section 21A in the circumferential direction (vertically in Fig.1 ).
  • the first blade section 10 is rotated about the axis of rotation D in the direction shown in Fig.2 shown second position is adjusted or rotated.
  • the second contour section 12B now covers the pressure-side contour section 21A in the circumferential direction (the first contour section 12A covers another (pressure-side) contour section of the profile (section) 21 of the second blade section 20).
  • the second contour section 12B takes the place of the first contour section 12A relative to the second blade section 20.
  • the first blade section 10 is rotated about the axis of rotation D back to the position shown in Fig.1 The first position shown is adjusted back or rotated.
  • the first and second contour sections 12A, 12B are, at least essentially, circular segments of the same circle
  • the pressure-side contour section 21A is, at least essentially, a circular segment of a concentric circle, so that the distances r, R to the axis of rotation D along these contour sections are, at least substantially, constant.
  • Fig.3 shows the profile section of the Fig.1 , where a point P2 is marked, which is located in one upstream twentieth of the suction side (top in Fig.3 ) of the second blade section 20 or profile (section) 21, ie a suction-side point in the area or near the leading edge 23.
  • suction-side tangent T2 at point P2 (to the suction side of the second blade section 20 or profile (section) 21) and the suction-side tangent T1 at point P1 (to the suction side of the first blade section 10 or profile (section) 11) as well as the angle ⁇ between these two tangents T1, T2, which is more than 20°, are shown.

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

Claims (10)

  1. Aube directrice, l'aube présentant une pale d'aube comportant une première partie de pale d'aube (10) et une seconde partie de pale d'aube (20) et la première partie de pale d'aube (10) pouvant tourner par rapport à la seconde partie de pale d'aube (20) autour d'un axe de rotation (D) de manière réversible d'une première position à une seconde position, l'axe de rotation (D) étant disposé à l'extérieur d'un profil (11) de la première partie de pale d'aube (10) dans au moins une section transversale de la pale d'aube et
    un profil (11) de la première partie de pale d'aube présentant un côté aspiration (12) comportant une première (12A) et une seconde partie de contour (12B) et
    un profil (21) de la seconde partie de pale d'aube (20) présentant une partie de contour (21A) côté refoulement, que la première partie de contour (12A) de la première partie de pale d'aube recouvre dans la première position et que la seconde partie de contour (12B) de la première partie de pale d'aube recouvre dans la seconde position au lieu de cela, dans la direction périphérique,
    caractérisée en ce que
    l'axe de rotation (D) se situe sur le côté du côté refoulement et en aval du bord d'attaque (23) et en amont du bord de fuite (23) de la seconde partie d'aube (20).
  2. Aube directrice selon la revendication 1, caractérisée en ce que la seconde partie de pale d'aube (20), vue dans un sens d'écoulement, se situe en aval de la première partie de pale d'aube (10).
  3. Aube directrice selon la revendication 1, caractérisée en ce que la seconde partie de pale d'aube (20), vue dans un sens d'écoulement, se situe en amont de la première partie de pale d'aube (10).
  4. Aube directrice selon la revendication 1, caractérisée en ce qu'un profil de la seconde partie de pale d'aube présente une tangente (T2) côté aspiration en au moins un point (P2) dans un dixième le plus en amont de son côté aspiration et un profil (11) de la première partie de pale d'aube présente une tangente (T1) en un point (P1) situé le plus près de ce point (P2) dans la première ou la seconde position, lesquelles tangentes forment l'une avec l'autre un angle (α) d'au maximum 20°.
  5. Aube directrice selon la revendication 1, caractérisée en ce qu'une distance (r) à l'axe de rotation (D) varie d'au maximum 10 % le long de la première partie de contour (12A), une distance (r) à l'axe de rotation (D) varie d'au maximum 10 % le long de la seconde partie de contour (12B) ou une distance (R) à l'axe de rotation (D) varie d'au maximum 10 % le long de la partie de contour (21A) côté refoulement, ou la seconde partie de pale d'aube présente une région de type cône ou cylindre qui présente la partie de contour côté refoulement.
  6. Aube directrice selon l'une des revendications précédentes, caractérisée par un joint d'étanchéité (22) permettant la réduction d'une largeur de fente entre des régions, se faisant face dans la première et/ou la seconde position, de la première et de la seconde partie de pale d'aube.
  7. Aube directrice selon l'une des revendications précédentes, caractérisée par un carénage extérieur (30) et/ou un carénage intérieur, sur lequel la première partie de pale d'aube est disposée de manière à pouvoir tourner autour de l'axe de rotation.
  8. Étage de compresseur pour une turbine à gaz comportant au moins une aube directrice, en particulier une aube directrice de sortie, selon l'une des revendications précédentes.
  9. Turbomachine, en particulier turbine à gaz, comportant au moins une aube directrice, en particulier un étage de compresseur, selon l'une des revendications précédentes.
  10. Procédé permettant de faire fonctionner une turbomachine, en particulier une turbine à gaz, selon la revendication précédente, caractérisé en ce que la première partie de pale d'aube (10) de l'au moins une aube directrice, en particulier les premières parties de pale d'aube de plusieurs aubes directrices selon l'une des revendications précédentes, sont réglées de la première à la seconde position.
EP21187375.7A 2020-08-04 2021-07-23 Aube directrice, étage de compresseur pour une turbine à gaz, turbomachine et procédé pour exploiter une turbomachine Active EP3954875B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102020209792.5A DE102020209792A1 (de) 2020-08-04 2020-08-04 Leitschaufel

Publications (3)

Publication Number Publication Date
EP3954875A2 EP3954875A2 (fr) 2022-02-16
EP3954875A3 EP3954875A3 (fr) 2022-05-04
EP3954875B1 true EP3954875B1 (fr) 2024-05-15

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EP21187375.7A Active EP3954875B1 (fr) 2020-08-04 2021-07-23 Aube directrice, étage de compresseur pour une turbine à gaz, turbomachine et procédé pour exploiter une turbomachine

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US (1) US11555500B2 (fr)
EP (1) EP3954875B1 (fr)
DE (1) DE102020209792A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AT526083B1 (de) * 2022-09-07 2023-11-15 Andritz Hydro Gmbh Leitschaufel

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Publication number Priority date Publication date Assignee Title
US4856962A (en) 1988-02-24 1989-08-15 United Technologies Corporation Variable inlet guide vane
FR2714109B1 (fr) * 1993-12-22 1996-01-19 Snecma Aube de turbomachine à cambrure variable.
US5931636A (en) * 1997-08-28 1999-08-03 General Electric Company Variable area turbine nozzle
DE10257044B4 (de) 2002-12-06 2005-01-27 Mtu Aero Engines Gmbh Gasturbine
EP1505263A1 (fr) * 2003-08-08 2005-02-09 Siemens Aktiengesellschaft Dispositif de guidage dans un passage d'échappement pour une turbomachine et procédé d'opération
US7114911B2 (en) 2004-08-25 2006-10-03 General Electric Company Variable camber and stagger airfoil and method
FR2933148B1 (fr) * 2008-06-25 2010-08-20 Snecma Compresseur de turbomachine
DE102008058014A1 (de) 2008-11-19 2010-05-20 Rolls-Royce Deutschland Ltd & Co Kg Mehrschaufelige Verstellstatoreinheit einer Strömungsarbeitsmaschine
EP3009607A1 (fr) * 2014-10-13 2016-04-20 United Technologies Corporation Aube fixe-variable avec enrobage dans l'interstice
GB201419951D0 (en) * 2014-11-10 2014-12-24 Rolls Royce Plc A guide vane
JP6381425B2 (ja) 2014-12-01 2018-08-29 三菱日立パワーシステムズ株式会社 軸流圧縮機
CN105715585B (zh) 2014-12-05 2019-06-28 上海电气集团股份有限公司 可变几何出口导叶
DE102015004649A1 (de) 2015-04-15 2016-10-20 Man Diesel & Turbo Se Leitschaufelverstellvorrichtung und Strömungsmaschine
GB201621739D0 (en) * 2016-12-20 2017-02-01 Rolls Royce Plc Variable guide vane device
US10815821B2 (en) * 2018-08-31 2020-10-27 General Electric Company Variable airfoil with sealed flowpath

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Publication number Publication date
US20220042514A1 (en) 2022-02-10
DE102020209792A1 (de) 2022-02-10
EP3954875A2 (fr) 2022-02-16
US11555500B2 (en) 2023-01-17
EP3954875A3 (fr) 2022-05-04

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