EP1918529A2 - Turbomachine avec aubes statoriques ajustables - Google Patents

Turbomachine avec aubes statoriques ajustables Download PDF

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Publication number
EP1918529A2
EP1918529A2 EP07021130A EP07021130A EP1918529A2 EP 1918529 A2 EP1918529 A2 EP 1918529A2 EP 07021130 A EP07021130 A EP 07021130A EP 07021130 A EP07021130 A EP 07021130A EP 1918529 A2 EP1918529 A2 EP 1918529A2
Authority
EP
European Patent Office
Prior art keywords
turntable
flanks
stator
rotation
turbomachine according
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Withdrawn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
EP07021130A
Other languages
German (de)
English (en)
Other versions
EP1918529A3 (fr
Inventor
Volker Dr.-Ing. Gümmer
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 EP1918529A2 publication Critical patent/EP1918529A2/fr
Publication of EP1918529A3 publication Critical patent/EP1918529A3/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Withdrawn legal-status Critical Current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

Definitions

  • the present invention relates to variable stator blades of fluid flow machines such as fans, compressors, pumps, and fans in the axial, semi-axial, or even radial form.
  • the working medium can be gaseous or liquid.
  • the invention relates to at least one adjustable stator blade, possibly also an adjustable Vorleitrad, a fluid flow machine.
  • the blading in question is within a housing, which limits the flow of at least one rotor and a stator with a fluid to the outside.
  • a rotor comprises a plurality of rotor blades attached to a rotating shaft and supplies energy to the working fluid
  • a stator consists of a plurality of stator blades usually mounted in the housing.
  • the aerodynamic load capacity and the efficiency of fluid flow machines is limited in particular by the growth and detachment of boundary layers in the region of the radial gap between the blading and housing or hub, which is structurally necessary at the annular channel edge.
  • the radial gaps which can arise through free cuts in front of and behind the rotating spindle, are particularly pronounced on rotating adjustable stators and cause considerable flow losses.
  • the turntables are usually completely round.
  • Fig. 1 shows a part of a fluid flow machine in the region of one of its prior art Verstellstator Horn, shown in the meridian plane. Apart from the Verstellstator #2 itself components in the hub 4 and housing portion 5 are indicated that hold the Verstellstator (stator 2) inside and outside.
  • the view AA is shown, which shows a parallel to the axis of rotation of the variable stator (stator blade 2) oriented view of the inner flow path boundary (hub).
  • stator stator blade 2
  • hub inner flow path boundary
  • the representation is made as an example for the hub, but there is a principle same arrangement of the turntable in mosachs-parallel perspective on the housing side boundary of the flow path of the fluid flow machine.
  • the present invention relates to stators (stator blade 2) which are rotatably mounted on at least one blade end and can be adjusted via a spindle about a rotation axis 1. As in all representations shown here, the flow of the relevant row of blades takes place, as indicated by the thick arrow, from left to right.
  • the present invention has for its object to provide an adjustable stator blade of the type mentioned, which achieved while avoiding the prior art, a substantial or complete avoidance of Radialteilspalten at the blade end by a special gate of the otherwise round turntable.
  • an adjustable stator blade for use in a turbomachine having at least one of its ends a turntable whose cross section, viewed in the direction of the axis of rotation of the Verstellstators (stator blade 2), substantially deviates from a circular shape, such that by bleed the circular shape on opposite sides of the turntable two straight or curved shaped flanks arise, and the turntable adjacent Verstellstatoren are mounted in overlapping circular recesses in the housing or hub member.
  • FIG. 2 shows a part of a fluid flow machine in the region of one of its displacement stator rows (stator blade 2), shown in the meridian plane. Apart from the Verstellstator #2 itself components in the hub 4 and housing portion 5 are indicated that hold the Verstellstator (stator 2) inside and outside.
  • Verstellstatoran extract in which a storage is provided solely in housing or hub with full radial gap at the other end of the blade.
  • the right-hand side of the picture shows the view A-A, which shows a view of the inner flow path boundary (hub) oriented parallel to the axis of rotation of the variable stator (stator blade 2).
  • the solution according to the invention shown here provides a special shape of the turntable 3 located at the blade ends.
  • the blade 8 is located here in the leading edge region completely on the turntable 3 and protrudes only with its trailing edge on the turntable 3 addition.
  • the originally circular turntable 3 has two flanks S, D obtained by a cut at opposite edge zones of the turntable 3, which are executed in a straight line in the example shown here. Between the flank S located near the convex suction side of a blade profile and the flank D located near the concave shaped pressure side of the adjacent blade profile there is a gap which allows the displacement of the displacement stator (stator blade 2) over a certain angular range.
  • a solution according to the invention can also have any other relative rotary position between the blade profile and the trimmed turntable 3.
  • Fig. 3 shows a Verstellstator Hor in the meridian plane.
  • view AA is also shown, which shows a parallel to the axis of rotation of the adjusting stator (stator blade 2) oriented view of the inner flow path boundary (hub).
  • the solution according to the invention shown here provides a positioning of the blade profile on the turntable 3, which leads in a part of the adjustment range of the stator to an overlap of the blade trailing edge with the turntable 3 of an adjacent stator blade 2.
  • Fig. 4 shows a Verstellstator II in the meridian plane.
  • A-A view is shown, which shows a parallel to the axis of rotation 1 of the adjusting stator oriented view of the inner flow path boundary (hub).
  • the solution according to the invention shown here provides for complete positioning of the blade profile on the turntable 3.
  • the originally circular turntable 3 has received two very long flanks through the gate, which are straight again executed in the example shown here, but can also be curved.
  • the gap between the flanks of two adjacent turntables 3 at the respective edges of the Statorverstell Anlagenes is low or equal to zero.
  • Fig. 6 shows a turntable 3 in battingachsparalleler view.
  • the blade is not drawn in favor of a clearer representation.
  • two very different gates can be provided according to the invention, the contours of which fit together with parts of the edge when the rotational position of the adjusting stator is correctly selected.
  • the penetration depths S1 and S2 into the circle of the diameter D can deviate from one another as desired.
  • a solution according to the invention can also have other arbitrarily shaped contours of the flanks S and D.
  • the flow-facing (wetted) surface of the turntable 3 according to the invention may be flat or oblique, bevelled, wavy or otherwise contoured to create a particularly favorable transition between turntables 3 adjacent stator blades 2.
  • FIG. 7 shows a turntable 3 in a rotation-parallel view.
  • the stator blade 2 is not in favor of a clearer view also drawn.
  • two straight flanks with different penetration depths S1 and S2 have been chosen here.
  • This and also previous illustrations show solutions according to the invention in which the edges formed on the flanks are at right angles to the surface of the turntable. Deviating from this, it may be particularly advantageous according to the invention not to provide the surface of the flank parallel to the blade axis of rotation 1, but inclined relative thereto and / or with a special contouring.
  • Fig. 8 shows the section BB defined in Fig. 7 through the turntable 3 and a small portion of the airfoil 8.
  • the upper part of the figure shows the solution according to the invention with rectangular edges of the flanks (turntable without inclination of the flanks S and D (orientation approximately parallel to the axis of rotation)), the lower part of the image, however, shows an example of a coordinated inclination / contouring of the flanks S and D (turntable with inclination and contouring of the flanks S and D).
  • the flow-facing (wetted) surface of the turntable 3 according to the invention flat or to create a particularly favorable transition between turntables 3 adjacent stator blades 2 can be made oblique, bevelled, wavy or otherwise contoured.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP07021130A 2006-11-03 2007-10-29 Turbomachine avec aubes statoriques ajustables Withdrawn EP1918529A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102006052003A DE102006052003A1 (de) 2006-11-03 2006-11-03 Strömungsarbeitsmaschine mit verstellbaren Statorschaufeln

Publications (2)

Publication Number Publication Date
EP1918529A2 true EP1918529A2 (fr) 2008-05-07
EP1918529A3 EP1918529A3 (fr) 2010-05-12

Family

ID=38693297

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07021130A Withdrawn EP1918529A3 (fr) 2006-11-03 2007-10-29 Turbomachine avec aubes statoriques ajustables

Country Status (3)

Country Link
US (1) US20080131268A1 (fr)
EP (1) EP1918529A3 (fr)
DE (1) DE102006052003A1 (fr)

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102008058014A1 (de) 2008-11-19 2010-05-20 Rolls-Royce Deutschland Ltd & Co Kg Mehrschaufelige Verstellstatoreinheit einer Strömungsarbeitsmaschine
FR2941018B1 (fr) 2009-01-09 2011-02-11 Snecma Aube a calage variable pour etage de redresseur, comprenant une plateforme interne non circulaire
US8123471B2 (en) * 2009-03-11 2012-02-28 General Electric Company Variable stator vane contoured button
US8328513B2 (en) * 2009-12-31 2012-12-11 General Electric Company Systems and apparatus relating to compressor stator blades and diffusers in turbine engines
US20140119894A1 (en) * 2012-10-25 2014-05-01 Solar Turbines Incorporated Variable area turbine nozzle
EP2738356B1 (fr) * 2012-11-29 2019-05-01 Safran Aero Boosters SA Aube de redresseur de turbomachine, redresseur de turbomachine et procédé de montage associé
US9915149B2 (en) 2015-08-27 2018-03-13 Rolls-Royce North American Technologies Inc. System and method for a fluidic barrier on the low pressure side of a fan blade
US10233869B2 (en) 2015-08-27 2019-03-19 Rolls Royce North American Technologies Inc. System and method for creating a fluidic barrier from the leading edge of a fan blade
US9976514B2 (en) 2015-08-27 2018-05-22 Rolls-Royce North American Technologies, Inc. Propulsive force vectoring
US10718221B2 (en) 2015-08-27 2020-07-21 Rolls Royce North American Technologies Inc. Morphing vane
US10125622B2 (en) 2015-08-27 2018-11-13 Rolls-Royce North American Technologies Inc. Splayed inlet guide vanes
US20170057649A1 (en) 2015-08-27 2017-03-02 Edward C. Rice Integrated aircraft propulsion system
US10267160B2 (en) 2015-08-27 2019-04-23 Rolls-Royce North American Technologies Inc. Methods of creating fluidic barriers in turbine engines
US10267159B2 (en) 2015-08-27 2019-04-23 Rolls-Royce North America Technologies Inc. System and method for creating a fluidic barrier with vortices from the upstream splitter
US10280872B2 (en) 2015-08-27 2019-05-07 Rolls-Royce North American Technologies Inc. System and method for a fluidic barrier from the upstream splitter
US10287902B2 (en) * 2016-01-06 2019-05-14 General Electric Company Variable stator vane undercut button
US11607826B2 (en) * 2017-12-14 2023-03-21 Lm Wind Power International Technology Ii Aps Method of manufacturing at least two preforms for moulding a wind turbine blade
US11572798B2 (en) 2020-11-27 2023-02-07 Pratt & Whitney Canada Corp. Variable guide vane for gas turbine engine
CN114109522B (zh) * 2021-11-29 2022-12-02 清华大学 控制间隙损失的导叶结构和动力***
JP2023166117A (ja) * 2022-05-09 2023-11-21 三菱重工業株式会社 可変静翼及び圧縮機

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2917275A (en) * 1952-10-03 1959-12-15 Napier & Son Ltd Turbo machines having adjustable guide blades
GB946995A (en) * 1961-05-23 1964-01-15 Rolls Royce Fluid flow machine such as a gas turbine engine
GB1201949A (en) * 1966-10-31 1970-08-12 United Aircraft Corp Movable stator vane unit for a bladed fluid flow machine
US3687569A (en) * 1971-03-19 1972-08-29 Gen Electric Rotor with variable angle blades
DE2835349B1 (de) * 1978-08-11 1979-04-26 Motoren Turbinen Union Verstelleitgitter fuer hochbelastete Verdichter,insbesondere von Gasturbinentriebwerken
EP1217173A2 (fr) * 2000-12-20 2002-06-26 United Technologies Corporation Aube de guidage pour turbomachines
US6461105B1 (en) * 2001-05-31 2002-10-08 United Technologies Corporation Variable vane for use in turbo machines
EP1746260A2 (fr) * 2005-07-20 2007-01-24 United Technologies Corporation Train d'engrenage avec mécanisme de synchronisation pour les aubes de guidage variables et l' anneau des aubes à diamètre interne

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6910854B2 (en) * 2002-10-08 2005-06-28 United Technologies Corporation Leak resistant vane cluster

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2917275A (en) * 1952-10-03 1959-12-15 Napier & Son Ltd Turbo machines having adjustable guide blades
GB946995A (en) * 1961-05-23 1964-01-15 Rolls Royce Fluid flow machine such as a gas turbine engine
GB1201949A (en) * 1966-10-31 1970-08-12 United Aircraft Corp Movable stator vane unit for a bladed fluid flow machine
US3687569A (en) * 1971-03-19 1972-08-29 Gen Electric Rotor with variable angle blades
DE2835349B1 (de) * 1978-08-11 1979-04-26 Motoren Turbinen Union Verstelleitgitter fuer hochbelastete Verdichter,insbesondere von Gasturbinentriebwerken
EP1217173A2 (fr) * 2000-12-20 2002-06-26 United Technologies Corporation Aube de guidage pour turbomachines
US6461105B1 (en) * 2001-05-31 2002-10-08 United Technologies Corporation Variable vane for use in turbo machines
EP1746260A2 (fr) * 2005-07-20 2007-01-24 United Technologies Corporation Train d'engrenage avec mécanisme de synchronisation pour les aubes de guidage variables et l' anneau des aubes à diamètre interne

Also Published As

Publication number Publication date
US20080131268A1 (en) 2008-06-05
EP1918529A3 (fr) 2010-05-12
DE102006052003A1 (de) 2008-05-08

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