EP1655455A1 - Dispositif pour régler le jeu radial des aubes de guidage d'une turbomachine - Google Patents

Dispositif pour régler le jeu radial des aubes de guidage d'une turbomachine Download PDF

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Publication number
EP1655455A1
EP1655455A1 EP04026305A EP04026305A EP1655455A1 EP 1655455 A1 EP1655455 A1 EP 1655455A1 EP 04026305 A EP04026305 A EP 04026305A EP 04026305 A EP04026305 A EP 04026305A EP 1655455 A1 EP1655455 A1 EP 1655455A1
Authority
EP
European Patent Office
Prior art keywords
turbomachine
carrier
adjusting ring
guide
segments
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Withdrawn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
EP04026305A
Other languages
German (de)
English (en)
Inventor
Holger Bauer
Bernhard Küsters
Dieter Minninger
Marc Dr. Mittelbach
Andreas Peters
Stephan Schmidt
Steffen Dr. Skreba
Bernd Dr. Stöcker
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.)
Siemens AG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Priority to EP04026305A priority Critical patent/EP1655455A1/fr
Publication of EP1655455A1 publication Critical patent/EP1655455A1/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Withdrawn legal-status Critical Current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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/22—Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
    • 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
    • F05D2260/00—Function
    • F05D2260/50—Kinematic linkage, i.e. transmission of position

Definitions

  • the invention relates to a turbomachine comprising a rotatable annular vane support arranged in a housing, to which an outer guide surface extending axially beyond a ring of vanes is provided, to which the radially inwardly extending vanes are attached and to one in the housing rotatably mounted rotor on which an axially extending beyond a ring of blades out inner guide surface is provided, on which the radially outwardly extending blades are mounted, radially seen each inner end of the vanes facing one another to form a radial gap of the inner guide surface and each outer end of the blades faces a radial gap of the outer guide surface to form a radial gap.
  • the guide blade carrier is designed to be slidable when viewed in the axial direction of the rotor by providing axially actuated, hydraulically actuated cylinders between the housing and the guide blade carrier.
  • the object of the invention is to improve the setting of the gap of the radial gap by an alternative embodiment of a turbomachine to further optimize the efficiency and the warm start behavior of the turbomachine.
  • the solution according to the invention is based on the idea of dividing the guide blade carrier in the circumferential direction into at least four carrier segments which can be moved in the radial direction and which are coupled to change their position with an adjusting ring which engages around the carrier segments and is rotatable in the circumferential direction.
  • the invention offers a further advantage with regard to the equalization of the radial gaps over the circumference.
  • Stationary turbomachines for example gas turbines, consisted of two housing halves, which adjoin each other at above-average massive Operafugenflanschen.
  • the ovalization causes radial gaps for each blade of a blade ring, each of which could have different gap dimensions.
  • the new adjustment mechanism the ovalization is reduced or possibly even completely suppressed since the components involved in the adjustment are connected to each other via adhesion. Consequently, the radial gaps formed between the blades of a blade ring and a guide surface have almost identical gap dimensions, which can be further reduced in efficiency without the rubbing or touching of the two assemblies involved.
  • the vane support is divided into an even number of support segments in the circumferential direction.
  • the adjusting ring is supported by a plurality of support rollers mounted on an inner wall of the housing.
  • the ovalization of the housing can be decoupled from vane carrier. This minimizes the size differences between the 6: 00/12: 00 o'clock level and the 03: 00/09: 00 o'clock level occurring during ovalization.
  • the adjusting ring and the carrier segment are coupled by at least one pair of a running surface and a positioning roller which can be unrolled thereon.
  • the positioning roller can roll along the circumferentially extending tread energy-saving and wear-free.
  • the running surfaces on the carrier segment or on the adjusting ring and the positioning rollers are arranged on the adjusting ring or on the carrier segment.
  • the running surfaces may be curved in the circumferential direction. In the event that they part are an imaginary circle with a lying outside the axis of rotation of the rotor center, a non-proportional relationship between the angle of rotation of the adjusting and radial displacement of the carrier segment can be made.
  • a comparatively large radial adjustment path of the carrier segment is first forced, which has a decreasing adjustment path of the carrier segment with uniformly continued rotation of the adjusting ring.
  • a curved running surface causes a straight running surface during a rotational movement of the adjusting ring by a twisting a proportional thereto, radial movement of the carrier segments.
  • the adjusting ring is rotatable via a plurality of tension and compression rods engaging in the circumferential direction. These act essentially tangentially on the adjusting ring, so that it is rotatable about an axis which is coaxial with the axis of rotation of the rotor.
  • the tension rods and push rods are driven by hydraulic or electrical means.
  • turbomachine is designed as a compressor or as a turbine unit of a gas turbine, in which the radially displaceable support segments are arranged as Ver Whyrleitschaufelany or as Turbinenleitschaufelitati.
  • Turbomachines such as axially flowed gas turbines, compressors or steam turbines, are well known.
  • 1 shows a cross section through an axial flow-through turbomachine 11.
  • the turbomachine 11 has a rotatably mounted about an axis of rotation 13 rotor 15, on the outer circumference in rings arranged blades 17 in the flow channel 19, which is also referred to as a flow path, radially extend into it.
  • the flow channel 19 is seen from the outside radially outer surfaces 20a and radially inwardly limited by inner guide surfaces 20b.
  • the vanes 21 are secured with their radially outer end respectively to carrier segments 23, which also form the guide surface 20a.
  • the inner guide surface 20 b is given by the peripheral surface of the rotor 15.
  • carrier segments 23 each extending over 90 ° of a circle form a vane carrier 24.
  • Six, eight, or even more carrier segments 23 could be provided to form the vane carrier 24.
  • Both the blades 17 and the guide vanes 21 each have a gas blade 25, for example compressor air or turbine hot gas, flow around the airfoil 27, which with a cantilevered blade end 29 of a guide surface 20a, 20b, with blades 17, the carrier segments 23 and guide vanes 21st the outer circumference of the Rotor 15, each opposite to form a radial gap 31.
  • a gas blade 25 for example compressor air or turbine hot gas
  • the radial gaps 31 are set as small as possible for each operating state via a regulator.
  • the invention proposes that the carrier segments 23 are radially displaceable over a still to be described in detail adjusting mechanism 33.
  • the measure of the radial gap is determined, which serves as an input variable of the controller.
  • the adjusting mechanism 33 comprises an adjusting ring 35 arranged concentrically with respect to the axis of rotation 13 of the rotor 15 and which can be rotated in the circumferential direction X U.
  • support rollers 49 are provided, which are supported on first support 39 'on an inner wall 51 of the housing 47.
  • the support rollers 49 rest against the outer circumference 53 of the adjusting ring 35, so that it can be rotated in the circumferential direction via tension and compression rods 57 mounted on it by an adjusting force F v acting on the tension and compression rods 57.
  • the support rollers 49 are preferably - compared to the clock face - on 01: 30, 04: 30, 07: 30 and arranged at 10: 30 o'clock to the occurring during transient operation by the ovalization size differences in the radial gaps of a blade ring 16, 18 between the 06: 00/12: 00 o'clock level and the 03: 00/09: 00 o'clock level to minimize or at best completely avoid.
  • the tension and compression rods 57 can be connected via means not shown in detail, such as. hydraulically actuated piston or via an electric motor kraftbeetzschlagt.
  • the adjusting ring 35 has positioning rollers 41 fastened to its inner circumference 37 via second supports 39 "which can each be unrolled on a running surface 43 located on each carrier segment 23.
  • Each running surface 43 is defined by a distance between two end points for the associated positioning roller 41,
  • Each of the positioning rollers 41 forms a pair with a running surface 43 assigned to it, it being possible to provide several, preferably three, pairs for each carrier segment 23.
  • the running surface 43 deviates from each circle concentric with the axis of rotation 13 of the rotor 15 and is preferably curved in the circumferential direction X u .
  • the support segments 23 are shown either on the inner wall 51 of the housing 47, as shown in the upper half of the housing by the arrows designated F R ', or, as shown in the lower half of the housing by the arrows F R '', on the inner circumference 37 of Adjusting ring 35 supported radially movable. This can be done for example by springs 67 (Fig. 2), which are mounted on the corresponding components.
  • a restoring force F R acting radially inwardly on the carrier segments 23 by the pretensioned springs causes the provision of the carrier segments 23 to be inward.
  • the outer guide surface 20a of the flow channel is composed of four 19 support segments 23, each having a face each other to form in the circumferential direction X and extending variable gap 61st For sealing these, each formed between two immediately adjacent support segments 23 column 61 whose opposite end faces 63 each have a groove 64 into which a sealing element 65 is inserted.
  • the adjusting ring 35 is rotated over the approximately tangentially acting tensile and compression rods 57 in the circumferential direction X u .
  • the constricting operation can be counteracted by the carrier segments 23 moved radially outwards by means of the adjusting device 33, so that the brushing of the blade ends 29 against the guide surface 20 can be prevented.
  • a rotation of the adjusting ring 35 can produce a proportional or disproportionate radial displacement X R of the adjusting ring 35.
  • FIG. 2 shows a plan view of a pair of a positioning roller 41 and a running surface 43.
  • the running surface 43 is formed by a hook located on the carrier segment 23.
  • FIG. 2 shows a spring 67 which is supported between the carrier segment 23 and the adjusting ring 35 and which is used to generate the restoring force F R.
  • an adjusting device 33 can also be provided per blade ring 16, 28 or else per compressor or turbine stage.
  • the radial gaps 31 can each be adapted to current operating conditions of the turbomachine 11. Even if, for example, during the departure of a turbomachine 11, the radial gap 31 changes, this can be adjusted via the proposed adjustment mechanism 33.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP04026305A 2004-11-05 2004-11-05 Dispositif pour régler le jeu radial des aubes de guidage d'une turbomachine Withdrawn EP1655455A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP04026305A EP1655455A1 (fr) 2004-11-05 2004-11-05 Dispositif pour régler le jeu radial des aubes de guidage d'une turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04026305A EP1655455A1 (fr) 2004-11-05 2004-11-05 Dispositif pour régler le jeu radial des aubes de guidage d'une turbomachine

Publications (1)

Publication Number Publication Date
EP1655455A1 true EP1655455A1 (fr) 2006-05-10

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ID=34927257

Family Applications (1)

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EP04026305A Withdrawn EP1655455A1 (fr) 2004-11-05 2004-11-05 Dispositif pour régler le jeu radial des aubes de guidage d'une turbomachine

Country Status (1)

Country Link
EP (1) EP1655455A1 (fr)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008086782A2 (fr) * 2007-01-20 2008-07-24 Mtu Aero Engines Gmbh Turbomachine
DE102009023061A1 (de) * 2009-05-28 2010-12-02 Mtu Aero Engines Gmbh Spaltkontrollsystem, Strömungsmaschine und Verfahren zum Einstellen eines Laufspalts zwischen einem Rotor und einer Ummantelung einer Strömungsmaschine
EP2273073A3 (fr) * 2009-06-12 2013-07-03 Rolls-Royce plc Système et procédé pour régler le jeu rotor-stator
US8727709B2 (en) 2009-09-28 2014-05-20 Rolls-Royce Plc Casing component
WO2014143311A1 (fr) * 2013-03-14 2014-09-18 Uskert Richard C Carénages de turbine
CN104948242A (zh) * 2014-03-27 2015-09-30 三菱日立电力系统株式会社 回转机械及回转机械控制方法
EP2935800A4 (fr) * 2012-12-20 2016-01-27 United Technologies Corp Commande de fluide à joint à air externe variable
EP3176382A1 (fr) * 2015-12-04 2017-06-07 United Technologies Corporation Système de commande de jeu d'extrémité de turbine à réactivité élevée

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3085398A (en) * 1961-01-10 1963-04-16 Gen Electric Variable-clearance shroud structure for gas turbine engines
GB2024336A (en) * 1978-05-30 1980-01-09 Rolls Royce Gas turbine rotor tip clearance control apparatus
GB2068470A (en) * 1980-02-02 1981-08-12 Rolls Royce Casing for gas turbine engine
US4714404A (en) * 1985-12-18 1987-12-22 Societe Nationale d'Etudes et de Construction de Moteurs O'Aviation (S.N.E.C.M.A.) Apparatus for controlling radial clearance between a rotor and a stator of a tubrojet engine compressor
US5362202A (en) * 1992-10-07 1994-11-08 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Turbomachine equipped with means for adjusting the play between the stator blades and the rotor of a compressor

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3085398A (en) * 1961-01-10 1963-04-16 Gen Electric Variable-clearance shroud structure for gas turbine engines
GB2024336A (en) * 1978-05-30 1980-01-09 Rolls Royce Gas turbine rotor tip clearance control apparatus
GB2068470A (en) * 1980-02-02 1981-08-12 Rolls Royce Casing for gas turbine engine
US4714404A (en) * 1985-12-18 1987-12-22 Societe Nationale d'Etudes et de Construction de Moteurs O'Aviation (S.N.E.C.M.A.) Apparatus for controlling radial clearance between a rotor and a stator of a tubrojet engine compressor
US5362202A (en) * 1992-10-07 1994-11-08 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Turbomachine equipped with means for adjusting the play between the stator blades and the rotor of a compressor

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008086782A3 (fr) * 2007-01-20 2009-11-19 Mtu Aero Engines Gmbh Turbomachine
US8376691B2 (en) 2007-01-20 2013-02-19 Mtu Aero Engines Gmbh Turbo engine
WO2008086782A2 (fr) * 2007-01-20 2008-07-24 Mtu Aero Engines Gmbh Turbomachine
DE102009023061A1 (de) * 2009-05-28 2010-12-02 Mtu Aero Engines Gmbh Spaltkontrollsystem, Strömungsmaschine und Verfahren zum Einstellen eines Laufspalts zwischen einem Rotor und einer Ummantelung einer Strömungsmaschine
US8678742B2 (en) 2009-05-28 2014-03-25 Mtu Aero Engines Gmbh Clearance control system, turbomachine and method for adjusting a running clearance between a rotor and a casing of a turbomachine
EP2273073A3 (fr) * 2009-06-12 2013-07-03 Rolls-Royce plc Système et procédé pour régler le jeu rotor-stator
US8555477B2 (en) 2009-06-12 2013-10-15 Rolls-Royce Plc System and method for adjusting rotor-stator clearance
US8727709B2 (en) 2009-09-28 2014-05-20 Rolls-Royce Plc Casing component
EP2935800A4 (fr) * 2012-12-20 2016-01-27 United Technologies Corp Commande de fluide à joint à air externe variable
WO2014143311A1 (fr) * 2013-03-14 2014-09-18 Uskert Richard C Carénages de turbine
WO2014143322A1 (fr) * 2013-03-14 2014-09-18 Uskert Richard C Ensemble piste de turbine, moteur à turbine à gaz correspondant et procédé
US9598975B2 (en) 2013-03-14 2017-03-21 Rolls-Royce Corporation Blade track assembly with turbine tip clearance control
US9926801B2 (en) 2013-03-14 2018-03-27 Rolls-Royce Corporation Blade track assembly with turbine tip clearance control
US10316687B2 (en) 2013-03-14 2019-06-11 Rolls-Royce Corporation Blade track assembly with turbine tip clearance control
CN104948242A (zh) * 2014-03-27 2015-09-30 三菱日立电力系统株式会社 回转机械及回转机械控制方法
EP3176382A1 (fr) * 2015-12-04 2017-06-07 United Technologies Corporation Système de commande de jeu d'extrémité de turbine à réactivité élevée
US10316686B2 (en) 2015-12-04 2019-06-11 United Technologies Corporation High response turbine tip clearance control system

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