EP1757775A2 - Dispositif d'étanchéité pour une aube statorique variable - Google Patents

Dispositif d'étanchéité pour une aube statorique variable Download PDF

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Publication number
EP1757775A2
EP1757775A2 EP06013281A EP06013281A EP1757775A2 EP 1757775 A2 EP1757775 A2 EP 1757775A2 EP 06013281 A EP06013281 A EP 06013281A EP 06013281 A EP06013281 A EP 06013281A EP 1757775 A2 EP1757775 A2 EP 1757775A2
Authority
EP
European Patent Office
Prior art keywords
machine axis
radius
rotor
blade
sphere
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.)
Withdrawn
Application number
EP06013281A
Other languages
German (de)
English (en)
Other versions
EP1757775A3 (fr
Inventor
Ingo Jahns
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP1757775A2 publication Critical patent/EP1757775A2/fr
Publication of EP1757775A3 publication Critical patent/EP1757775A3/fr
Withdrawn legal-status Critical Current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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/24—Three-dimensional ellipsoidal
    • F05D2250/241—Three-dimensional ellipsoidal spherical

Definitions

  • the invention relates to a gap control device for a gas turbine.
  • the GB 2 235 730 A plans to perform the gap control on the housing via an adjustable outer shroud.
  • the adjustment of the respective shroud segment is ensured by a mounted on the housing adjustment mechanism.
  • the housing and the inner cover strip thus form the interfaces for the gas flow.
  • the DE 42 137 16 A1 provides for the inner blade tip end of the adjustable stator blade and the opposite wall to form spherical, wherein the axis of the adjusting blades is perpendicular to the machine axis.
  • the US 2002/0061249 A1 has local spherical recesses in the housing for each adjustment vane.
  • the adjustable Statorschaufelachsen are there inclined to the machine axis to make the local corrugations aerodynamic.
  • the compression of the air by the compressor rotor blades makes it necessary to make the gas channel more and more narrow, and thus the housing and / or to provide the inner cover tapes with a slope that can be very large, especially in the front steps.
  • the front stator blades of the compressor are mostly adjustable. Due to this rotation, however, the gap between the housing and the variable stator blade changes as well as the gap between the inner shroud and the variable stator blade in conventional design. This gap formation proves to be disadvantageous and leads to aerodynamic losses.
  • the invention has for its object to provide a gap control device of the type mentioned, which allows a simple design and simple, cost manufacturability minimizing the gap and minimizes aerodynamic losses while allowing an aerodynamic optimized design of the gas channel.
  • the radial difference in height of the annular space is achieved by a spherical segment, wherein the spherical segment before / or. is cut behind the equator.
  • the axis of rotation of the adjustable stator blades passes through the center of the sphere and is inclined at an angle ( ⁇ ) to the machine axis.
  • the radius of the ball segment (R ball ) results from the radial distance of the blade tip at the intersection of the stator blade axis of rotation (R ma ) to the machine axis of rotation divided by sin ( ⁇ ).
  • the angle ( ⁇ ) is inventively chosen so that the desired narrowing of the flow channel is formed.
  • the angle of the axis of rotation is set so that the front edge of the radially outer end of the adjustable stator blade is covered by the rotary spindle.
  • the gap between the trailing edge of the radially outer end of the stator blade and the housing can be minimized by the opposite inclination of the annular space in the axial direction and the inclination of the annular channel in the circumferential direction upon rotation of the adjustable stator blade.
  • the spherically shaped region of the inner cover tape is followed by the gas channel geometry of the next rotor disk. The fact that the ball segment is not in the region of the equator of the ball, there is no turning point in the gas channel.
  • the gas-flow area adjoining the blade row is formed substantially in the form of a spherical surface ring.
  • this specially shaped gas-flowed region either on the housing, on the inner cover strip or on the rotor (one-sided mounting of the variable stator blade). The invention is thus applicable both to the radially inner region of the blade and to the radially outer region of the blade.
  • the gas-circulated surface is inclined in the axial direction to the horizontal plane which encompasses the axis of rotation of the gas turbine.
  • the spherical surface ring is thus not arranged in the equator of the ball, but laterally offset. Thus, a taper or narrowing of the flow cross-section of the compressor is possible. Since the axis of rotation of the adjustable stator blade extends through the ball center, thus the axis of rotation is inclined axially forward.
  • the gap control device thus makes it possible to carry out an exact gap check.
  • the gap remains constant over the entire adjustment range of the blade. This results in smaller gaps in the operating point of the compressor, whereby the efficiency is increased and the aerodynamic losses are reduced.
  • the shape of a spherical surface can also be left slightly, so that deviates slightly from the ideal shape. This is covered by the invention.
  • the gap control device comprises a housing 1 of a gas turbine known from the prior art which is by means of a spindle 10 and a not further explained in detail, since known from the prior art adjusting a blade 2 is mounted. This is part of a compressor (compressor), as is also known from the prior art.
  • FIG. 1 also shows the representation of a rotation axis 7 of the blade 2 and the gaps 8 or distances 8 which result between the ends of the blade 2.
  • a gasumströmte surface 4 (see, for example, Fig. 2) of the housing 1 and / or the inner shroud 3 have an inclination to the engine rotational axis in the axial direction, so that narrows the gas channel during the compression of the air (see Fig. 1).
  • the radially inner end of the adjustable stator blade and the gas-flowed surface (4) of the inner cover strip (3) is designed spherically.
  • the radius of the ball (R ball) for intersecting the Statorschaufelspitze is inventively equal to the radial distance from the machine axis to Schaufelspizte at the node of Statorschaufelmosachse (R ma) divided by the sine of the inclination angle of Statorschauelwindachse 7 to the machine axis ( ⁇ ).
  • the inclination of the axis of rotation 7 is inventively chosen so that the required height difference between the inlet and outlet edge of the axially cut inner shroud is formed (3).
  • a spindle 9 of the blade 2 is blended according to the invention in a favorable development with the shape of a ball and thus is no longer in the gas stream.
  • the region 6 of the rotor is also spherical in shape in accordance with the above-mentioned criteria, so that a uniform running gap is created with the spherical radially inner end of the stator blade.
  • the region 6 corresponds at least to the maximum axial extent of the adjustable stator blade in its torsion region.
  • Gasumströmten surfaces in a section transverse to the engine axis are annular or circular, as shown by the reference numeral 5 of FIG. 4.
  • the axis of rotation 7 of the variable stator blade (blade 2) is arranged such that it lies perpendicular to the surface of the inner cover tape 3.
  • the axis of rotation 7 of the blade 2 is thus, depending on the required inclination of the gasumströmten surface 4, axially inclined forward.
  • the gasumströmte surface 4 is inventively designed so that it has the same curvature (reference numeral 6 in Fig. 3), as in the circumferential direction (reference numeral 5 of the circular shape of FIG. 4).
  • the gasumströmte surface 4 thus forms a section of a ball or a spherical surface ring, as is clear from the representation of a ball 9 in Fig. 7.
  • the blade 2 (stator blade) is arranged at a distance (gap 8) to the inner shroud 3 is formed so that the end of the blade 2 also forms part of a spherical surface.
  • the distance or gap 8 is therefore only dependent from the manufacturing tolerances and thermal expansions. Incidentally, the distance remains constant with each rotation or adjustment of the blade 2, since two spherical surface parts are moved relative to each other.
  • the adjustable stator screen is mounted on one side (FIG. 12).
  • the stator blade has no inner spindle.
  • the radially inner region of the adjustable stator blade runs against the rotor drum 11.
  • the opposite surfaces of the variable displacement vane (12) and the rotor (11) are spherical as described above.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Control Of Turbines (AREA)
EP06013281A 2005-08-26 2006-06-27 Dispositif d'étanchéité pour une aube statorique variable Withdrawn EP1757775A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102005040574A DE102005040574A1 (de) 2005-08-26 2005-08-26 Spaltkontrollvorrichtung für eine Gasturbine

Publications (2)

Publication Number Publication Date
EP1757775A2 true EP1757775A2 (fr) 2007-02-28
EP1757775A3 EP1757775A3 (fr) 2008-07-23

Family

ID=36968166

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06013281A Withdrawn EP1757775A3 (fr) 2005-08-26 2006-06-27 Dispositif d'étanchéité pour une aube statorique variable

Country Status (3)

Country Link
US (1) US20070160463A1 (fr)
EP (1) EP1757775A3 (fr)
DE (1) DE102005040574A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2194235A1 (fr) * 2008-12-05 2010-06-09 Siemens Aktiengesellschaft Composant de boîtier pour une turbomachine axiale doté d'un contrôle d'intervalle passif, turbine à gaz dotée du composant de boîtier et procédé destiné au rééquipement d'un composant de boîtier existant
EP2960438A1 (fr) * 2014-06-26 2015-12-30 MTU Aero Engines GmbH Système d'aubes de guidage variables pour une turbine à gaz et turbine à gaz dotée d'un tel système
US10539024B2 (en) 2013-03-10 2020-01-21 Rolls-Royce Corporation Variable pitch fan for a gas turbine engine

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9353643B2 (en) * 2007-04-10 2016-05-31 United Technologies Corporation Variable stator vane assembly for a turbine engine
EP2405104A1 (fr) * 2010-07-08 2012-01-11 Siemens Aktiengesellschaft Compresseur et moteur à turbine à gaz associé
DE102011119879A1 (de) * 2011-12-01 2013-06-06 Ihi Charging Systems International Gmbh Fluidenergiemaschine, insbesondere für einen Abgasturbolader eines Kraftwagens
US9303524B2 (en) * 2012-10-25 2016-04-05 Solar Turbines Incorporated Variable area turbine nozzle with a position selector
US20140119894A1 (en) * 2012-10-25 2014-05-01 Solar Turbines Incorporated Variable area turbine nozzle
EP2961941B1 (fr) 2013-02-26 2020-02-19 Rolls-Royce Corporation Appareils comprenant une aube statorique de turbine pivotable
DE102013218303A1 (de) * 2013-09-12 2015-03-12 Bosch Mahle Turbo Systems Gmbh & Co. Kg Abgasturbolader mit Turbine
US9995166B2 (en) * 2014-11-21 2018-06-12 General Electric Company Turbomachine including a vane and method of assembling such turbomachine
DE102014223975A1 (de) * 2014-11-25 2016-05-25 MTU Aero Engines AG Leitschaufelkranz und Strömungsmaschine
EP3954882B1 (fr) * 2016-03-30 2023-05-03 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Turbocompresseur à géométrie variable
US20190301488A1 (en) * 2018-04-03 2019-10-03 Pratt & Whitney Canada Corp. Gas path duct for a gas turbine engine
US12158078B2 (en) 2023-03-14 2024-12-03 Rtx Corporation Compressor case with a cooling cavity

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2235730A (en) 1989-09-08 1991-03-13 Gen Electric Blade tip clearance control apparatus for a gas turbine engine
DE4213716A1 (de) 1992-04-25 1993-10-28 Asea Brown Boveri Axialdurchströmte Turbine
US20020061249A1 (en) 2000-09-18 2002-05-23 Snecma Moteurs Compressor stator having a constant clearance

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DE2643607C2 (de) * 1976-09-28 1978-05-18 Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen Vorrichtung zur Übertragung und Ermittlung des wahren Schaufelanstellwinkels verstellbarer Leitschaufeln einer Turbomaschine, insbesondere eines Gasturbinentriebwerks
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DE2931766C2 (de) * 1979-08-04 1982-08-05 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Dichtungseinrichtung für die freien Schaufelenden eines Verstell-Leitapparates einer Gasturbine
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FR2599785B1 (fr) * 1986-06-04 1990-10-12 Snecma Aubage directeur d'entree d'air a calage variable pour turboreacteur
FR2603340B1 (fr) * 1986-09-03 1988-11-04 Snecma Turbomachine comportant un dispositif d'ajustement des jeux d'un joint a labyrinthe entre rotor et stator et de l'alignement de veine des gaz et methode d'application
FR2775731B1 (fr) * 1998-03-05 2000-04-07 Snecma Etage circulaire d'aubes aux extremites interieures unies par un anneau de liaison
US6092984A (en) * 1998-12-18 2000-07-25 General Electric Company System life for continuously operating engines
US6086327A (en) * 1999-01-20 2000-07-11 Mack Plastics Corporation Bushing for a jet engine vane
DE10016745B4 (de) * 2000-04-04 2005-05-19 Man B & W Diesel Ag Axialströmungsmaschine mit einem eine Reihe von verstellbaren Leitschaufeln umfassenden Leitapparat
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ITTO20010445A1 (it) * 2001-05-11 2002-11-11 Fiatavio Spa Statore di una turbina assiale a geometria variabile per applicazioniaeronautiche.
US7125222B2 (en) * 2004-04-14 2006-10-24 General Electric Company Gas turbine engine variable vane assembly
US7360990B2 (en) * 2004-10-13 2008-04-22 General Electric Company Methods and apparatus for assembling gas turbine engines
US7510369B2 (en) * 2005-09-02 2009-03-31 United Technologies Corporation Sacrificial inner shroud liners for gas turbine engines
DE102005060699A1 (de) * 2005-12-19 2007-06-21 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit Verstellstator

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2235730A (en) 1989-09-08 1991-03-13 Gen Electric Blade tip clearance control apparatus for a gas turbine engine
DE4213716A1 (de) 1992-04-25 1993-10-28 Asea Brown Boveri Axialdurchströmte Turbine
US20020061249A1 (en) 2000-09-18 2002-05-23 Snecma Moteurs Compressor stator having a constant clearance

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2194235A1 (fr) * 2008-12-05 2010-06-09 Siemens Aktiengesellschaft Composant de boîtier pour une turbomachine axiale doté d'un contrôle d'intervalle passif, turbine à gaz dotée du composant de boîtier et procédé destiné au rééquipement d'un composant de boîtier existant
US10539024B2 (en) 2013-03-10 2020-01-21 Rolls-Royce Corporation Variable pitch fan for a gas turbine engine
EP2971596B1 (fr) * 2013-03-10 2020-07-15 Rolls-Royce Corporation Moteur à turbine à gaz et procédé correspondant
EP2960438A1 (fr) * 2014-06-26 2015-12-30 MTU Aero Engines GmbH Système d'aubes de guidage variables pour une turbine à gaz et turbine à gaz dotée d'un tel système
US10450877B2 (en) 2014-06-26 2019-10-22 MTU Aero Engines AG Guide means for a gas turbine and gas turbine having such a guide means

Also Published As

Publication number Publication date
DE102005040574A1 (de) 2007-03-15
EP1757775A3 (fr) 2008-07-23
US20070160463A1 (en) 2007-07-12

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