EP3954875A2 - Aube directrice, étage de compresseur, turbomachine et procédé pour exploiter une turbomachine - Google Patents

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

Info

Publication number: EP3954875A2
Authority: EP; European Patent Office
Prior art keywords: section; airfoil; profile; axis; contour
Prior art date: 2020-08-04
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

EP21187375.7A

Other languages

German (de)

English (en)

Other versions

EP3954875B1 (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.)

2020-08-04

Filing date

2021-07-23

Publication date

2022-02-16

2021-07-23 Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG

2022-02-16 Publication of EP3954875A2 publication Critical patent/EP3954875A2/fr

2022-05-04 Publication of EP3954875A3 publication Critical patent/EP3954875A3/fr

2024-05-15 Application granted granted Critical

2024-05-15 Publication of EP3954875B1 publication Critical patent/EP3954875B1/fr

Status Active legal-status Critical Current

2041-07-23 Anticipated expiration legal-status Critical

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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
- 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
- F01D17/165—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 6, 7 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 matter of the dependent claims.
a guide vane has an airfoil, which in turn has a first airfoil section and a second airfoil section, the first airfoil section being mounted reversibly rotatably, preferably rotatably, relative to the second airfoil section about an axis of rotation from a first position to a second position , is.
a compact, reliable, precise and/or mechanically and/or aerodynamically favorable adjusting kinematic system can be implemented by rotating about an axis of rotation.
the axis of rotation forms an angle with a radial direction that is at most 15°; in a further development, it extends in the radial direction.
particularly advantageous adjustment kinematics can be implemented in one embodiment.
an axial direction is parallel to a rotational or (Main) machine axis of a turbomachine, in particular 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, a direction of rotation about this rotary or (main) machine axis, a Radial direction a direction perpendicular to the axial and circumferential direction or a direction (axis) that intersects the rotary or (main) machine axis perpendicularly.
a direction of flow is a direction of an intended or design flow and/or a direction from a leading edge to a trailing edge of the guide vane or its vane blade and/or parallel to the rotational or (Main) machine axis or axial direction and/or, in one embodiment parallel to the axis of rotation or (main) machine axis or axial direction, from an inlet to an outlet of the turbomachine, "upstream” therewith, in an embodiment in or with respect to or along the axial direction, towards the leading edge or inlet, "downstream” towards the trailing edge or outlet, in one embodiment in or with respect to or along the axial direction towards the trailing edge or outlet.
a leading edge is correspondingly an upstream edge or an edge closer to an entry
a trailing edge is correspondingly an edge downstream or an edge closer to an exit.
an upstream-most point of a section of an airfoil, or its first or second airfoil section is defined by a cylinder about the rotational or (Major) machine axis a leading edge and a most downstream point of this section, ie at the same radial height, a trailing edge of a profile (section) of this airfoil (section) s, the connecting line a (profile) chord of this profile (section) and the profile or the profile section itself is the, in particular flat, (cross) section that contains this (profile) chord and is perpendicular to a (straight line of) the shortest connection between the axis of rotation or (main) machine axis and (profile) chord.
radially consecutive profiles (sections) that are threaded along the threading axis define or form the airfoil or its outer contour and corresponding elements of these profiles (sections) as profiles (sections) of the first airfoil section or its Outer contour and other elements of these profiles (sections) as profile (sections) e the second airfoil section or its outer contour.
Profile and profile section can in particular be synonymous.
the axis of rotation is arranged outside of a profile (section) of the first airfoil section. In one embodiment, the axis of rotation is located outside of the airfoil.
a first portion of the suction side of the first airfoil section circumferentially overlies a portion of the pressure side of the second airfoil section, and in the second position a second portion of the suction side of the first airfoil section circumferentially overlays that portion of the pressure side of the second airfoil section instead.
the rotatable first airfoil section can be arranged upstream in a through-flow direction and the second airfoil section can be arranged downstream of the first airfoil section, seen in a through-flow direction.
variations in an inflow or incidence angle can advantageously be at least partially compensated in one embodiment, and pressure losses and/or losses in efficiency that are usually associated with such a variation can be reduced in one embodiment.
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, viewed in a flow direction. This allows the outflow condition to be advantageously varied.
a negative effect of a leakage (return) flow between the first and second airfoil section in particular the risk of this flow being separated from the suction side of the second airfoil section, can be reduced.
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 section contact one another, or a free gap or gap in which the first and second airfoil sections not contacting each other, separate or the first and second airfoil sections unconnected.
the first blade section is arranged on, in one embodiment, on at least one platform that can rotate about the axis of rotation, in one embodiment is rotatably mounted, in particular a turntable, 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 detachable with the or one or both platforms or turntables non-destructively, in particular frictionally and/or positively, or non-destructively detachable, in particular cohesively, connected or integrally formed.
the first blade section is arranged on the edge of the or one or both platforms or turntables.
a distance from the axis of rotation along the first contour section of the first airfoil section varies by at most 10%, in particular by 10% 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 airfoil section varies by a maximum of 10%, in particular by a maximum of 5%, in one embodiment by a maximum of 1%, in particular the second contour section can thus be a segment of, in particular the first, be a circle around the axis of rotation.
a distance from the axis of rotation along the pressure-side contour section of the second airfoil section varies by a maximum of 10%, in particular by a maximum of 5%, in one embodiment by a maximum of 1%, in particular the pressure-side contour section can thus be a segment of, in particular the first circle concentric, circle around the axis of rotation.
the first airfoil section has a conical or cylindrical area which has the first and second contour section(s), and/or the second airfoil section has a conical or cylindrical area, in particular congruent thereto, which has the or the has pressure-side contour sections.
the guide vane has an elastic and/or contacting seal in one embodiment, a lip seal or brush seal in one embodiment, which has a gap width between opposite areas of the first and second blade section in the first and/or second position is reduced or provided for this purpose, in particular set up or used.
the seal can in particular on the second airfoil section, in particular the pressure-side contour section of the second airfoil section, and/or on the first airfoil section, in particular on the first and/or second contour section of the first airfoil section.
the axis of rotation is arranged on the side of the pressure side of the airfoil or to the side of the pressure side of the airfoil.
the axis of rotation is arranged in one embodiment in the at least one profile section of the airfoil, in one embodiment in the axial direction, downstream after or upstream in front of a leading edge of the profile (section) of the second airfoil section. In one embodiment, the axis of rotation is located, in one embodiment in the axial direction, downstream of a leading edge of the second airfoil section.
the axis of rotation is arranged in one embodiment in the at least one profile section of the airfoil, in one embodiment in the axial direction, upstream in front of a trailing edge of the profile (section) of the second airfoil section. In one embodiment, the axis of rotation is located, in one embodiment in the axial direction, upstream of a trailing edge of the second airfoil section.
the axis of rotation is arranged in one embodiment in the first and/or second position in the at least one profile section of the airfoil, in one embodiment in the axial direction, downstream after a leading edge of the profile (section) of the first airfoil section. In one embodiment, the axis of rotation is located in the first and/or second position, in one embodiment in the axial direction, downstream of a leading edge of the first airfoil section.
the axis of rotation in the at least one profile section of the airfoil is outside of the profile section of the second Airfoil section arranged. In one embodiment, the axis of rotation is located outside of the second airfoil section.
an adjustment of the guide vane that is particularly advantageous, in particular aerodynamically and/or mechanically, and in one embodiment is low-loss, compact, simple and/or reliable, can be implemented.
the vane includes an outer shroud that is located radially outward of the airfoil in one embodiment and/or an inner shroud that is located radially inward of the airfoil in one embodiment.
the first airfoil section is mounted on the outer shroud so as to be rotatable about the axis of rotation in one embodiment via the or one of the platform(s).
the first airfoil section is mounted on the inner shroud so as to be rotatable about the axis of rotation, in one embodiment via the or other platform(s).
the second airfoil section is fixed, in particular non-rotatably, in one embodiment stationary, arranged on the outer shroud, in one embodiment with the outer shroud detachable non-destructively, in particular frictionally and/or positively, or non-destructively detachable, in particular cohesively, connected or formed integrally.
the second airfoil section is fixed, in particular non-rotatably, in one embodiment stationary, arranged on the inner shroud, in one embodiment with the inner shroud detachable non-destructively, in particular frictionally and/or positively, or non-destructively detachable, in particular cohesively, connected or formed integrally.
an adjustment of the guide vane that is particularly advantageous, in particular aerodynamically and/or mechanically, and in one embodiment is low-loss, compact, simple and/or reliable, can be implemented.
the present invention is particularly suitable for gas turbines and in particular their compressor stages and/or outlet guide vanes and is accordingly used 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 , but not limited to this.
the first vane section(s) thereof for or during the operation of a turbomachine, in particular a gas turbine, with one or more guide vanes described here, the first vane section(s) thereof, in one embodiment, synchronously, from the first to the second position adjusted or rotated.
an axial distance between a leading edge of the first airfoil section and a trailing edge of the second airfoil 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 airfoil section and a leading or trailing edge or suction side of the second airfoil section of the vane(s) in the second position or an axial extent of the vane(s) in the second Position shorter than in the first position.
the first airfoil section of the guide vane or the first airfoil sections of the guide vanes is/are in or for operation in an operating point with a suction-side angle of attack(s) in the second position and/or in or for operation in an operating point with a pressure-side(re)n inflow angle into the first position.
the operation of the turbomachine, in particular the gas turbine, in particular its efficiency, can be improved.
the first blade section is preferably continuously in positions between the first and second position and/or or can be adjusted or rotated beyond the first and/or second position.
Figure 12 shows a profile section of an airfoil of a vane according to an embodiment of the present invention in a first position.
the airfoil has an upstream first airfoil section 10 which, in the profile section of FIG 1 has a profile (section) 11 with a suction side 12, and in a flow direction (from left to right in 1 ) Second airfoil section 20, which in the profile section of 1 a (en) profile (section) 21 has.
the second airfoil section 20 is fixedly arranged on an outer shroud 30 .
the first airfoil section 10 is separated from the second airfoil section by a gap S, in which a seal 22 arranged on the second airfoil section 20 is arranged, which reduces the gap width, at least essentially, to zero.
the first and second airfoil section can contact each other, likewise a free gap can be formed between them.
the first airfoil 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 so that it can be rotated about the axis of rotation D via this platform 40 .
the non-visible other end of the vane can be arranged in an analogous manner on an inner shroud or also be designed without an inner shroud.
the axis of rotation D is on the side of the pressure side (below in 1 ) and in the profile section of the 1 located outside the profile 11 of the first airfoil section 10, downstream after a leading edge 23, upstream in front of a trailing edge 24 and outside the profile 21 of the second airfoil section 20.
the suction side 12 of the profile 11 of the first airfoil section 10 has a first contour section 12A and a second contour section 12B adjoining it upstream, the profile 21 of the second airfoil 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 1 ).
a guide vane angle of attack changes to its suction side (up in 1 ) is shifted towards or towards the suction side, the first airfoil section 10 is moved about the axis of rotation D into the in 2 shown second position adjusted or (ver) 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 relative to the second airfoil section 20 takes the place of the first contour section 12A.
the first airfoil section 10 is moved back into the in 1 shown first position moved back or (ver) 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, at least essentially, a circular segment of a circle concentric thereto, so that the distances r, R to the axis of rotation D along these contour sections, are, at least essentially, constant.
FIG. 3 shows the profile section of the 1 , where a point P2 is drawn, which is in a most upstream twentieth of the suction side (above in 3 ) of the second airfoil section 20 or profile (section) 21, i.e. a suction-side point in the area or near the leading edge 23.
suction-side tangent T2 is at point P2 (to the suction side of the second airfoil section 20 or profile (section) 21) and the suction-side tangent T1 is at point P1 (to the suction side of the first airfoil section 10 or profile (section) s 11 ) and the angle ⁇ between these two tangents T1, T2, which is more than 20°.

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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)

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

Family

ID=77042804

Family Applications (1)

Application Number	Title	Priority Date	Filing Date
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

Country Status (3)

Country	Link
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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FR2714109B1 (fr) *	1993-12-22	1996-01-19	Snecma	Aube de turbomachine à cambrure variable.
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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
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FR2933148B1 (fr) *	2008-06-25	2010-08-20	Snecma	Compresseur de turbomachine
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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
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GB201621739D0 (en) *	2016-12-20	2017-02-01	Rolls Royce Plc	Variable guide vane device
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2020
- 2020-08-04 DE DE102020209792.5A patent/DE102020209792A1/de active Pending
2021
- 2021-07-23 EP EP21187375.7A patent/EP3954875B1/fr active Active
- 2021-07-29 US US17/388,825 patent/US11555500B2/en active Active

Also Published As

Publication number	Publication date
US20220042514A1 (en)	2022-02-10
DE102020209792A1 (de)	2022-02-10
US11555500B2 (en)	2023-01-17
EP3954875B1 (fr)	2024-05-15
EP3954875A3 (fr)	2022-05-04

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