EP2206889A1 - Procédé de réduction de jeu des extrémités des aubes par un rotor déplaçable et turbine à gaz associée - Google Patents

Procédé de réduction de jeu des extrémités des aubes par un rotor déplaçable et turbine à gaz associée Download PDF

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Publication number
EP2206889A1
EP2206889A1 EP09000358A EP09000358A EP2206889A1 EP 2206889 A1 EP2206889 A1 EP 2206889A1 EP 09000358 A EP09000358 A EP 09000358A EP 09000358 A EP09000358 A EP 09000358A EP 2206889 A1 EP2206889 A1 EP 2206889A1
Authority
EP
European Patent Office
Prior art keywords
turbine
rotor
gas turbine
compressor
displacement device
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Withdrawn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
EP09000358A
Other languages
German (de)
English (en)
Inventor
Francois Dr. Benkler
Tobias Dr. Buchal
Andreas Dr. Böttcher
Patricia Dr. Hülsmeier
Ekkehard Dr. Maldfeld
Dieter Minninger
Peter Schröder
Rostislav Dr. Teteruk
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 EP09000358A priority Critical patent/EP2206889A1/fr
Publication of EP2206889A1 publication Critical patent/EP2206889A1/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Withdrawn legal-status Critical Current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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
    • F04D29/052—Axially shiftable rotors

Definitions

  • the invention relates to a gas turbine with an axial compressor and an axial turbine, whose radial gaps are reduced, and a method for reducing the radial gaps in the gas turbine.
  • An axial-flow gas turbine includes a compressor, a turbine, and a rotor having compressor blade rows in the compressor and turbine blade rows in the turbine. Between the compressor blade rows and the inner contour of the housing of the compressor, a radial gap is provided. In an analogous manner, a radial gap is also provided between the turbine blade rows and the inner contour of the housing of the turbine.
  • the radial gaps lead to significant losses in the efficiency of the compressor and the turbine. In order to achieve the highest possible efficiency of the compressor and the turbine, it is desirable to keep the radial gaps as small as possible at all operating times.
  • the radial gaps change over time.
  • the radial gaps change when switching from part load operation to full load operation of the gas turbine.
  • the compressor and turbine are designed such that the radial gaps are sufficiently large for all compressor blade rows and turbine blade rows for the operating case where the radial gaps are found to be smallest so that there is virtually no contact between the rotor blade rows and the inner contour of the housing comes. This has the consequence that in continuous operation of the gas turbine unnecessarily large radial gaps must be kept for this critical operating condition, which is associated with a significant loss of efficiency.
  • the temporal change of the radial gaps is the result of different thermal inertia behavior of the individual components of the compressor and the turbine, in particular the rotor, the compressor blade rows, the turbine blade rows, the compressor housing and the turbine housing.
  • the temporal change of the radial gap is caused by the centrifugal force expansion of the blade rows, the transverse contraction of the rotor, a possible play in the thrust bearing of the rotor, in particular in connection with the reversal of axial thrust under appropriate operating conditions of the gas turbine, a possible ovalization of the housing due to montage charitableer Preload and uneven heating of the housing.
  • the object of the invention is to provide a gas turbine with a high thermal efficiency.
  • the gas turbine according to the invention comprises an axial compressor with a compressor housing inner contour tapering in the throughflow direction of the gas turbine, an axial turbine with a turbine housing inner contour widening in the throughflow direction, on which an axially displaceable turbine guide carrier is mounted, and a rotor with at least one compressor blade row and at least one turbine blade row and rotor displacement means for axially displacing the rotor and turbine vane support shifting means for axially displacing the turbine vane support, wherein the rotor displacement means and the turbine vane support displacement means are arranged such that when the rotor is shifted from a first position to a second position axially in the flow direction by means of the rotor displacement means TurbinenleitschaufelifverschiebeISS the turbine vane carrier is axially displaced in the flow direction from a third position to a fourth position, whereby the radial gaps are both between the compressor blade row and the compressor housing internal contour as well as the turbine blade row and the turbine housing inner contour are adapted
  • the radial gaps in the compressor can be reduced with the rotor displacement device, wherein without actuation of the turbine guide plate carrier displacement device, the radial gaps in the turbine would be increased.
  • the magnification caused by the rotor displacement device can be reversed and also the radial gaps in the turbine are set to smaller size.
  • a hydraulically drivable drive is preferably provided on the turbine as the turbine vane carrier displacement device with which the turbine vane carrier is displaceable between the third position and the fourth position.
  • the hydraulically driven drive preferably has a plurality of hydraulic cylinders, which are mounted distributed on the turbine over the circumference.
  • the hydraulic cylinders can be operated for example by an externally generated pressure.
  • the turbine vane carrier is suitably mounted to provide its axial displaceability.
  • a pneumatically drivable drive is preferably provided as Turbinenleitschaufelaverschiebe highlighted with which the Turbinenleitschaufelani between the third position and the fourth position is displaceable.
  • the pneumatically driven drive preferably has a pressure chamber which is integrated on the turbine guide vane carrier.
  • the pressure chamber is preferably designed as a thrust balance piston.
  • the pneumatically driven drive is preferably drivable with removed from the compressor compressed air.
  • the rotor displacement device is preferably hydraulically operable.
  • the inventive method for reducing radial gaps in the gas turbine comprises the steps of: providing a correspondingly formed gas turbine; Moving the rotor from the first position to the second position axially in the flow direction by means of the rotor displacement device; Axially displacing the turbine vane support in the flow direction by means of the turbine vane support displacement device so that the radial gaps are reduced between both the compressor blade row and the compressor housing inner contour and the turbine blade row and the turbine housing inner contour.
  • the displacement of the rotor by means of the rotor displacement device and the displacement of the turbine guide vane carrier by means of the turbine vane carrier displacement device during stationary operation of the gas turbine is accomplished.
  • FIG. 1 schematically, a gas turbine 1 a compressor 2, a combustion chamber 3 and a turbine 4.
  • the gas turbine 1 is in operation in FIG. 1 flows through from left to right, so that the flow direction the gas turbine 1 in the 1 to 4 from left to right.
  • the compressor 2 has a housing with a compressor housing inner contour 17, which tapers in the direction of flow.
  • the turbine 4 has a housing with a turbine housing inner contour 18, which tapers counter to the direction of flow.
  • the gas turbine 1 further comprises a rotor, not shown, on which compressor rotor blades 2 are provided with radially arranged compressor rotor blades, each having a compressor blade 5.
  • turbine blade rows are attached to the rotor, which are formed by turbine blades, each having a turbine blade airfoil 6.
  • Both the compressor blade 5 and the turbine blade 6 extend radially outward from the center, ie, rotor of the compressor 2 and the turbine 4, respectively, spaced from each other to form the compressor housing inner contour 17 and the turbine housing inner contour 18, respectively, forming a radial gap 19.
  • the gas turbine 1 further comprises a rotor displacement device, with which the rotor in a rotor displacement direction 7 in 1 to 4 from left to right is axially displaceable.
  • a rotor displacement device With which the rotor in a rotor displacement direction 7 in 1 to 4 from left to right is axially displaceable.
  • both the compressor blade 5 and the turbine blade 6 is moved from a first position 8 to a second position 9, wherein the second position 9 with respect to the first position 8 in 1 to 4 is settled further to the right.
  • the compressor housing inner contour 17 in FIG. 1 is formed tapering from left to right, the radial gap on the compressor blade 5 in the first position 8 is greater than in the second position 9.
  • the radial gap on the turbine blade airfoil 6 is smaller in the first position 8 than in the second position 9.
  • a turbine vane carrier 10 is provided in FIGS. 2 to 4 in the turbine 4, a turbine vane carrier 10 is provided.
  • the turbine vane carrier 10 is mounted axially displaceable parallel to the rotor displacement direction 7, so that the turbine guide vane carrier 10 can be brought from a third position 12 to a fourth position 13.
  • the third position 12 is located farther to the right than the fourth position 13.
  • the third position 12 is tuned to the first position 8 such that, when the compressor blade 5 is in the first position 8, a corresponding radial gap suitable for operating the gas turbine 1 is set on the turbine blade 6.
  • the fourth position 13 is selected such that when the rotor is displaced from the rotor shifting device into the rotor shifting direction 7 such that the compressor blade 5 is in the second position 9 on the turbine blade 6 in the second position 9 and the turbine blade carrier 10 in FIG the fourth position 13, a corresponding to the operation of the gas turbine 1 suitable radial gap is set.
  • the gas turbine 1 has a turbine vane support displacement device 11.
  • the turbine vane support displacement device 11 is set to operate the rotor displacement device such that, when the rotor displacement device is displaced in the rotor displacement direction 7, so that the compressor blade 5 is brought from the first position 8 to the second position 9, the turbine guide 10 of the Turbine vane support displacement device 11 is brought from the third position 12 to the fourth position 13.
  • the turbine vane support displacement device 11 is formed as a hydraulic cylinder 14.
  • the hydraulic cylinder 14 is arranged to be actuatable in the axial direction of the gas turbine 1, so that with the hydraulic cylinder 14 on the turbine blade carrier 10, an axial compressive force can be applied. Because of the turbine vane carrier 10 is slidably mounted parallel to the axial direction of the gas turbine 1, upon actuation of the hydraulic cylinder 14, the turbine vane carrier 10 can be axially displaced when the turbine blade carrier 10 is displaced from the hydraulic cylinder 14 from the third position 12 to the fourth position.
  • the turbine vane support shifting device 11 may be shown in FIG. 4 pneumatically driven, for which purpose compressed air is branched off from the compressor 2, which applies an axial force to the turbine guide vane carrier 10 in a pressure chamber 16, which is coupled to the turbine guide vane carrier 10.
  • the pressure chamber 16 is designed in principle like a thrust balance piston.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP09000358A 2009-01-13 2009-01-13 Procédé de réduction de jeu des extrémités des aubes par un rotor déplaçable et turbine à gaz associée Withdrawn EP2206889A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP09000358A EP2206889A1 (fr) 2009-01-13 2009-01-13 Procédé de réduction de jeu des extrémités des aubes par un rotor déplaçable et turbine à gaz associée

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP09000358A EP2206889A1 (fr) 2009-01-13 2009-01-13 Procédé de réduction de jeu des extrémités des aubes par un rotor déplaçable et turbine à gaz associée

Publications (1)

Publication Number Publication Date
EP2206889A1 true EP2206889A1 (fr) 2010-07-14

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP09000358A Withdrawn EP2206889A1 (fr) 2009-01-13 2009-01-13 Procédé de réduction de jeu des extrémités des aubes par un rotor déplaçable et turbine à gaz associée

Country Status (1)

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EP (1) EP2206889A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102010045851A1 (de) * 2010-09-17 2012-03-22 Mtu Aero Engines Gmbh Kompensation unterschiedlicher Längsdehnungen von Gehäuse und Rotorwelle einer Turbomaschine
DE102011003841A1 (de) * 2011-02-09 2012-08-09 Siemens Aktiengesellschaft Turbine mit relativ zueinander einstellbaren Rotor und Turbinengehäuse
US20160160875A1 (en) * 2013-08-26 2016-06-09 United Technologies Corporation Gas turbine engine with fan clearance control
EP3203016A1 (fr) * 2016-02-04 2017-08-09 United Technologies Corporation Régulation du jeux dans un moteur à turbine à gaz par canaux de ventilation d'équilibrage de poussée
CN113756883A (zh) * 2021-09-26 2021-12-07 中国联合重型燃气轮机技术有限公司 一种燃气轮机叶顶间隙主动控制装置及方法

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2165528A1 (de) * 1971-12-30 1973-07-12 Kloeckner Humboldt Deutz Ag Einrichtung zum herstellen eines geringen spaltes zwischen den umlaufenden schaufeln und der wandung einer stroemungsmaschine
WO2000028190A1 (fr) * 1998-11-11 2000-05-18 Siemens Aktiengesellschaft Palier d'arbre pour turbomachine, turbomachine correspondante et procede de fonctionnement d'une turbomachine
EP1746256A1 (fr) * 2005-07-20 2007-01-24 Siemens Aktiengesellschaft Diminution des pertes dues au jeu en bout d'aubes dans les turbomachines
DE102005048982A1 (de) * 2005-10-13 2007-04-19 Mtu Aero Engines Gmbh Vorrichtung und Verfahren zum axialen Verschieben eines Turbinenrotors
US20080267769A1 (en) * 2004-12-29 2008-10-30 United Technologies Corporation Gas turbine engine blade tip clearance apparatus and method

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2165528A1 (de) * 1971-12-30 1973-07-12 Kloeckner Humboldt Deutz Ag Einrichtung zum herstellen eines geringen spaltes zwischen den umlaufenden schaufeln und der wandung einer stroemungsmaschine
WO2000028190A1 (fr) * 1998-11-11 2000-05-18 Siemens Aktiengesellschaft Palier d'arbre pour turbomachine, turbomachine correspondante et procede de fonctionnement d'une turbomachine
US20080267769A1 (en) * 2004-12-29 2008-10-30 United Technologies Corporation Gas turbine engine blade tip clearance apparatus and method
EP1746256A1 (fr) * 2005-07-20 2007-01-24 Siemens Aktiengesellschaft Diminution des pertes dues au jeu en bout d'aubes dans les turbomachines
DE102005048982A1 (de) * 2005-10-13 2007-04-19 Mtu Aero Engines Gmbh Vorrichtung und Verfahren zum axialen Verschieben eines Turbinenrotors

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102010045851A1 (de) * 2010-09-17 2012-03-22 Mtu Aero Engines Gmbh Kompensation unterschiedlicher Längsdehnungen von Gehäuse und Rotorwelle einer Turbomaschine
DE102011003841A1 (de) * 2011-02-09 2012-08-09 Siemens Aktiengesellschaft Turbine mit relativ zueinander einstellbaren Rotor und Turbinengehäuse
US20160160875A1 (en) * 2013-08-26 2016-06-09 United Technologies Corporation Gas turbine engine with fan clearance control
EP3203016A1 (fr) * 2016-02-04 2017-08-09 United Technologies Corporation Régulation du jeux dans un moteur à turbine à gaz par canaux de ventilation d'équilibrage de poussée
US10247029B2 (en) 2016-02-04 2019-04-02 United Technologies Corporation Method for clearance control in a gas turbine engine
CN113756883A (zh) * 2021-09-26 2021-12-07 中国联合重型燃气轮机技术有限公司 一种燃气轮机叶顶间隙主动控制装置及方法

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