EP3176385A1 - Boitier de stator pour une turbomachine et turbomachine comprenant un boitier de stator - Google Patents

Boitier de stator pour une turbomachine et turbomachine comprenant un boitier de stator Download PDF

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Publication number
EP3176385A1
EP3176385A1 EP15198097.6A EP15198097A EP3176385A1 EP 3176385 A1 EP3176385 A1 EP 3176385A1 EP 15198097 A EP15198097 A EP 15198097A EP 3176385 A1 EP3176385 A1 EP 3176385A1
Authority
EP
European Patent Office
Prior art keywords
receptacles
housing
vane
guide
turbomachine
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
EP15198097.6A
Other languages
German (de)
English (en)
Other versions
EP3176385B1 (fr
Inventor
Vitalis Mairhanser
Lothar Albers
Georg Zotz
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
Priority to EP15198097.6A priority Critical patent/EP3176385B1/fr
Priority to US15/367,930 priority patent/US20170159467A1/en
Publication of EP3176385A1 publication Critical patent/EP3176385A1/fr
Application granted granted Critical
Publication of EP3176385B1 publication Critical patent/EP3176385B1/fr
Active legal-status Critical Current
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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/128—Nozzles

Definitions

  • the invention relates to a vane ring housing for a turbomachine, a segment of a vane ring housing, a kit for a turbomachine and a turbomachine with a vane ring housing.
  • Turbomachines such as aircraft engines and stationary gas turbines often have at least one compressor-side vane row with a plurality of vanes for setting optimum operating conditions.
  • the guide vanes preferably have, at a region to be positioned radially inward, and in a region to be positioned radially outside, in each case a blade plate, which may each have a pin on its side facing away from the blade leaf.
  • the vanes to be mounted or mounted between inner ring and vane ring housing are advantageously mounted pivotably about their longitudinal axis.
  • the pins which are mounted on the vane ring housing (and which are then referred to as "adjustment pin") cooperate with an adjusting device, via which a pivoting can be effected.
  • the vane ring housing may be composed of a plurality of vane ring housing parts, which may each have recordings for blade plates.
  • Such vane ring housing parts may include, for example, ring segments and / or axially separate parts.
  • the guide vane ring housing preferably has a plurality of receptacles extending in the radial direction, in each of which a corresponding blade plate of a guide vane is or can be inserted. Such a blade plate is used for stabilization or storage of the guide vanes.
  • the receptacle may be adapted to also receive a pin arranged on the blade plate, possibly together with an associated bushing and / or a sliding disk for the blade plate.
  • the recordings in the vane ring housing are separated in the circumferential direction by respective partitions.
  • the partition wall of the turbomachine can be bent in the direction of an adjacent receptacle and thus affect the pivotability of a guide blade inserted therein.
  • the number of shovel plate seats is determined by the given bucket plate sizes as well as the minimum wall thickness to be maintained. These parameters thus have a restrictive effect on a design of the turbomachine with a large number of pivotable guide vanes or large vanes.
  • a design and / or a minimum size of the blade plates is often aerodynamically and / or structurally advantageous.
  • the object of the present invention is to provide a technique which enables an aerodynamically and / or structurally improved design of a row of guide vanes.
  • An inventive vane ring housing for a turbomachine has an inner housing surface which extends (preferably substantially along a cylindrical or conical surface) about a central (geometric) axis and faces this axis; the central axis is preferably arranged such that in the assembled state, a rotational axis of a rotor inserted into the guide vane ring housing coincides with the central axis.
  • a plurality of receptacles each for a blade plate of a vane is arranged. Between at least two adjacent receptacles, the housing surface has a radial recess, which connects the two receptacles (in the circumferential direction) with each other.
  • a segment of a vane ring housing according to the invention can be combined with at least one further segment to form a vane ring housing according to the invention (according to one of the embodiments disclosed in this document). It comprises the at least two adjacent, by a radial recess interconnected shots for blade plate.
  • an inventive segment is designed as a ring segment, for example as a half, third or quarter ring.
  • An inventive kit for a turbomachine comprises an inventive Leitschaufelkranzgepuse according to one of the disclosed embodiments in this document and one or more vanes, which are each inserted or used in one of the receptacles of the vane ring housing.
  • a turbomachine according to the invention comprises a guide blade row, which has a plurality of guide vanes and a guide vane housing according to the invention one of the disclosed in this document embodiments, in whose receptacles each a guide plate of the vanes is inserted.
  • An inventive vane ring housing, an inventive segment of a vane ring housing, a kit according to the invention and a turbomachine according to the invention advantageously each allow an arrangement of vanes in which minimizes a distance between adjacent vane plates and nevertheless the risk of deformation of a recording can be avoided: Especially if two adjacent Recordings have circular cylindrical shaped sections, they run radially inwardly towards each other. In the region of the (the central axis facing) inner housing surface, they therefore have a minimum distance from each other. According to the present invention, no minimum distance needs to be maintained in this area in order to prevent an excessively thin partition wall from unfavorably deforming in this area. According to the invention, in this narrowest area there is a recess in the housing surface between the receptacles, so that a partition wall that could deform, there is nonexistent.
  • a guide vane ring according to the invention makes possible the design with a large number of guide vanes or with large guide vanes, and thus an improvement in the efficiency and durability of a turbomachine.
  • the at least two receptacles on the same dimensions are formed consistently.
  • a variant embodiment is advantageous in which the at least two receptacles each have a substantially circular-cylindrical section (for example a circular-cylindrical bore) which extends radially relative to the central axis of the guide vane ring housing.
  • Such recordings can record correspondingly shaped guide plate plates with a circular cylindrical section, which allows a particularly secure and stable storage and pivoting of the guide vanes.
  • the at least two receptacles are each adapted to receive a stator blade, which at the the blade leaf facing away (or opposite) side has a cylindrical adjusting pin.
  • the at least two receptacles may each have two concentric cylindrical sections, of which a radially further outward (for receiving an adjusting pin) is narrower than the radially further inward (for receiving the plate itself).
  • the recess preferably extends in the radial direction (relative to the vane ring housing or a rotation shaft) to at most one (radial) depth of the radially inner cylindrical section of the receptacles.
  • the receptacles in such a radially inward portion have a radial depth (i.e., radial extent into the vane ring housing) which is preferably between 2 mm and 3 mm.
  • a radial depth i.e., radial extent into the vane ring housing
  • Such dimensions allow a pickup of Leitschaufeltellern usual thickness (and possibly also a sliding disk), without the radially inner surface to be arranged of the guide blade plate protrudes from the inner housing surface (which would be disadvantageous in terms of flow).
  • the recess has a radial extent which is smaller than a radial depth of at least one of the receptacles or a radially inner cylindrical portion of the receptacle.
  • a partition is formed, which extends radially between a bottom surface of at least one of the receptacles and the radial recess;
  • the bottom surface is a surface that limits at least a portion of the receptacle radially outward.
  • the bottom surface preferably forms a radial bearing surface for the blade plate and is disposed in the bottom surface an opening through which the adjusting pin can be pushed.
  • the said partition wall is thus preferably located radially further outward than the recess which connects the adjacent receptacles to one another. If necessary, circular-shaped sections of the receptacles are located farther apart in this area, so that there is no risk of deformation of the dividing wall.
  • the partition wall thus allows a safe and stable storage of inserted guide vanes and possibly a stable positioning of a sliding disk between the bottom surface and the blade plate and thus in a region in which a partition wall thickness is not critical due to the radially outwardly spaced receptacles.
  • the partition wall has a base surface which is concave on both sides in the circumferential direction (concave); In this way, it can record an annular sliding disk with a precise fit and thus low-leakage.
  • the partition has a radial height which is between 1 mm and 1.5 mm.
  • a radial height is a distance between a bottom of at least one of the receptacles and the radial recess; If the at least two receptacles have different radial depths, a bottom of that receptacle is to be selected which has the smaller depth.
  • Such a radial height reduces leakage between the at least two receptacles in a region which is not critical for the dividing wall thickness, and also makes it possible to receive a sliding disk provided between the receiving floor and a guide blade insert to be inserted.
  • the partition wall in the axial direction has a length which is between 10 mm and 20 mm; In this way, an unfavorably small partition wall thickness can be avoided laterally of a center of the recess (for example located in a narrowest area between two receptacles).
  • the dividing wall preferably has a thickness which is between 0.3 mm and 0.5 mm. This can on the one hand a deformation of the On the other hand, such a thickness allows an advantageously narrow design of the guide vanes during insertion of the guide vanes or in use prevented.
  • Sliding discs are preferably inserted into the receptacles between the vane ring housing and the guide vanes;
  • An inventive kit or a turbomachine according to the invention may preferably comprise such sliding disks. You can a friction reduction when adjusting the vanes are effected.
  • FIG. 1 For example, a segment of a conventional vane ring housing 10 is illustrated that is substantially semi-annular in the present example. Together with a further, analogously formed (and not shown) segment, the vane ring housing 10 has a (abstract) central geometric axis A, which coincides with mounted turbomachine with the axis of rotation of a (not shown in the figure) rotor. For assembly or assembly with other parts of the vane ring housing, the segment shown has a mounting edge 19 with holes for fittings.
  • segment of a vane ring housing 10 has on its inner housing surface 11 three axially behind each other (in the illustration below each other) arranged annular areas, each comprising a plurality of receptacles 12 for blade plate of vanes.
  • the regions have different radii, so that the inner surface of the housing in the intended skin flow direction R (in the figure from bottom to top) gradually tapers in the sections.
  • Between the sections with the receptacles 12 are each Areas of the housing surface 11, which are arranged on a cylindrical surface.
  • the receptacles 12 each have a pin receptacle 17, which is adapted to receive an adjustment pin on a guide plate.
  • a radially outer adjusting mechanism (not shown), the adjustment pins and thus the associated guide vanes can preferably be pivoted.
  • the guide vanes 20 have, on the side opposite the blade plates 21a, respective blade plates 21b, which are set up to be inserted in receptacles in an inner ring (not shown).
  • the receptacles 12 are separated from one another in a conventional manner by partitions.
  • these partitions are very thin, so that it can be as described above to deformations.
  • FIG. 2 a portion of a housing surface 11 of a vane ring according to the invention is outlined; the housing surface faces a central axis (not shown) of the vane ring housing.
  • receptacles 12 ' are arranged to be used in the radially outer blade plates suitable vanes.
  • the openings of the receptacles 12 'in the housing surface 11 opposite the receptacles each have an annular bottom surface 14, in the center of a pin receptacle 17 for a Adjustment of the respective vane is arranged.
  • the receptacles 12 'are each shaped the same and in particular have a circular cylindrical basic shape, from which (concentric) the (likewise circular cylindrical) pin receptacle 17 is arranged.
  • the housing surface 11 has between in the FIG. 2 shown adjacent receptacles 12 'has a radial recess 16 which connects the adjacent recordings together.
  • the recesses each have a radial depth t, which is preferably in a range of 1 mm to 1.5 mm.
  • a partition wall 15 is formed, which extends between the bottom 14 of the receptacles and the recess 16 (or radially relative to a central axis of the vane ring housing).
  • the partition 15 has a radial height h, which is preferably between 1 mm and 1.5 mm. Such a height allows an advantageous centering of the blade plates or sliding disks to be used and reduces leakage in this area.
  • the partition wall In the axial direction (with respect to a central axis of the vane ring housing), the partition wall has a length 1; this is preferably between 10 mm and 20 mm.
  • the dividing wall 15 has a base area which is curved inward in the circumferential direction on both sides.
  • the partition wall 15 at its thickest point (at their ends) has a thickness d 1 and at its thinnest point has a thickness d 2 ; preferably d 2 is in a range of 0.3 mm to 0.5 mm;
  • the risk of deformation of the partition can be minimized.
  • the thickness d 1 (at the thickest point of the partition 15) results from d 2 , the length of the partition and the radius of the receptacles 12 '.
  • d 1 is in a range between 2.5 mm and 3 mm.
  • FIG. 3 a section of a vane ring housing 10 'according to the invention is shown.
  • the vane ring housing 10 ' has a housing surface 11 with receptacles 12', of which adjacent are each connected by a recess 16 in the housing surface 11 with each other.
  • a bottom surface 14 of the receptacles these each have a pin receptacle 17 into which a bushing 31 for the adjusting pin 23 of a guide blade 20 is inserted.
  • FIG. 3 In an exploded view is in the FIG. 3 exemplifies how such a vane 20 is to be used with a stator blade 21a and the adjusting pin 23 extending therefrom in the vane ring housing; between the blade plate 21a and the bottom surface of the receptacle 12 'while a sliding disk 30 is used, which is designed as a ring through which the adjustment pin is pushed.
  • An inventive vane ring housing 10 'for a turbomachine has a about a central axis A extending and the axis facing housing surface 11 in which a plurality of receptacles 12' is arranged in each case for a blade plate 21a of a guide vane 20. Between at least two adjacent receptacles 12 ', a radial recess 16 is arranged in the housing surface 11, which connects the two receptacles together.
  • a segment according to the invention of a vane ring housing according to the invention (according to one of the embodiments disclosed in this document) comprises the at least two adjacent receptacles 12 'interconnected by a radial recess 16.
  • An inventive kit for a turbomachine comprises an inventive vane ring housing 10 '(according to one of the embodiments disclosed in this document) and one or more of vanes 20, which are each in one of the receptacles 12' are inserted and / or of which at least one part are used ,
  • a turbomachine according to the invention comprises a plurality of guide vanes 20 and a guide vane housing 10 'according to the invention (according to one of the embodiments disclosed in this document), in whose receptacles 12' a guide blade plate 21a of the guide vanes is inserted.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP15198097.6A 2015-12-04 2015-12-04 Boitier de stator pour une turbomachine et turbomachine comprenant un boitier de stator Active EP3176385B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP15198097.6A EP3176385B1 (fr) 2015-12-04 2015-12-04 Boitier de stator pour une turbomachine et turbomachine comprenant un boitier de stator
US15/367,930 US20170159467A1 (en) 2015-12-04 2016-12-02 Guide vane ring casing for a turbomachine and turbomachine having a guide vane ring casing

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP15198097.6A EP3176385B1 (fr) 2015-12-04 2015-12-04 Boitier de stator pour une turbomachine et turbomachine comprenant un boitier de stator

Publications (2)

Publication Number Publication Date
EP3176385A1 true EP3176385A1 (fr) 2017-06-07
EP3176385B1 EP3176385B1 (fr) 2022-01-26

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Family Applications (1)

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EP15198097.6A Active EP3176385B1 (fr) 2015-12-04 2015-12-04 Boitier de stator pour une turbomachine et turbomachine comprenant un boitier de stator

Country Status (2)

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US (1) US20170159467A1 (fr)
EP (1) EP3176385B1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20170226887A1 (en) * 2016-02-05 2017-08-10 MTU Aero Engines AG Guide vane system for a turbomachine
EP3536913A1 (fr) * 2018-03-07 2019-09-11 MTU Aero Engines GmbH Bague intérieure pour une turbomachine et procédé de fabrication de cette bague intérieure

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11428113B2 (en) * 2020-12-08 2022-08-30 General Electric Company Variable stator vanes with anti-lock trunnions

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1760272A2 (fr) * 2005-09-02 2007-03-07 United Technologies Corporation Cousinet interne pour aube statorique variable des turbines à gaz
US20140140822A1 (en) * 2012-11-16 2014-05-22 General Electric Company Contoured Stator Shroud
WO2015079144A1 (fr) * 2013-11-29 2015-06-04 Snecma Dispositif de guidage d'aubes de redresseur a angle de calage variable de turbomachine et procédé d'assemblage d'un tel dispositif.

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1760272A2 (fr) * 2005-09-02 2007-03-07 United Technologies Corporation Cousinet interne pour aube statorique variable des turbines à gaz
US20140140822A1 (en) * 2012-11-16 2014-05-22 General Electric Company Contoured Stator Shroud
WO2015079144A1 (fr) * 2013-11-29 2015-06-04 Snecma Dispositif de guidage d'aubes de redresseur a angle de calage variable de turbomachine et procédé d'assemblage d'un tel dispositif.

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20170226887A1 (en) * 2016-02-05 2017-08-10 MTU Aero Engines AG Guide vane system for a turbomachine
US10450888B2 (en) * 2016-02-05 2019-10-22 MTU Aero Engines AG Guide vane system for a turbomachine
EP3536913A1 (fr) * 2018-03-07 2019-09-11 MTU Aero Engines GmbH Bague intérieure pour une turbomachine et procédé de fabrication de cette bague intérieure
US11098603B2 (en) 2018-03-07 2021-08-24 MTU Aero Engines AG Inner ring for a turbomachine, vane ring with an inner ring, turbomachine and method of making an inner ring

Also Published As

Publication number Publication date
US20170159467A1 (en) 2017-06-08
EP3176385B1 (fr) 2022-01-26

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