EP3397843A1 - Turbine à gaz équipée d'un piston à poussée axiale et d'un palier radial - Google Patents

Turbine à gaz équipée d'un piston à poussée axiale et d'un palier radial

Info

Publication number
EP3397843A1
EP3397843A1 EP17700929.7A EP17700929A EP3397843A1 EP 3397843 A1 EP3397843 A1 EP 3397843A1 EP 17700929 A EP17700929 A EP 17700929A EP 3397843 A1 EP3397843 A1 EP 3397843A1
Authority
EP
European Patent Office
Prior art keywords
compressor
compressor air
gas turbine
radial bearing
air
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Withdrawn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
EP17700929.7A
Other languages
German (de)
English (en)
Inventor
Marco LARSON
Nicolas Savilius
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
Publication of EP3397843A1 publication Critical patent/EP3397843A1/fr
Withdrawn legal-status Critical Current

Links

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
    • F01D3/00—Machines or engines with axial-thrust balancing effected by working-fluid
    • F01D3/04—Machines or engines with axial-thrust balancing effected by working-fluid axial thrust being compensated by thrust-balancing dummy piston or the like
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/08—Restoring position
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • 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
    • F01D7/00—Rotors with blades adjustable in operation; Control thereof
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/06—Arrangements of bearings; Lubricating
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/321—Application in turbines in gas turbines for a special turbine stage
    • F05D2220/3215—Application in turbines in gas turbines for a special turbine stage the last stage of the turbine
    • 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
    • F05D2240/20—Rotors
    • F05D2240/24—Rotors for turbines
    • F05D2240/242—Rotors for turbines of reaction type
    • 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
    • F05D2240/50—Bearings
    • F05D2240/52—Axial thrust bearings

Definitions

  • the present invention relates to a gas turbine with a rotor that is adjustable with respect to an axial compensation thrust (axial compensation force).
  • a gas turbine in particular a single-shaft gas turbine, which typically includes a compressor, a combustor having so ⁇ as an expansion turbine is in operation, that the axial forces which act on the rotor, will vary depending on mode of operation.
  • the gas turbine has in ⁇ if axial bearings, which are adapted to the axial thrust occurring in the various modes
  • the axial thrust results from the thrust difference between the thrust in the compressor and the thrust in the expansion turbine.
  • the axial thrust typically acts in the direction of the compressor to the turbine or in other words in the direction of flow of the working fluid in the gas turbine.
  • the gas turbine operated at about lower power, the axial thrust falls off, whereby about the thrust bearing is relieved.
  • the thrust difference can even come close to zero, so that it comes even at very low partial load modes even to a thrust reverser.
  • Such a thrust reversal is also promoted by manufacturing tolerances in the gas turbine, which can provide different axial thrusts at different Gasturbi ⁇ NEN.
  • the operation of external auxiliary systems, such as the anti-icing system may give rise to an axial thrust reversal.
  • an axial thrust reversal of the rotor is placed in unwanted axial and radial vibrations, whereby not only the La ⁇ ger but the entire gas turbine can be damaged. In this respect, it is necessary to avoid such reversals of the axial thrust and to maintain good control over the axial thrust and its direction.
  • Control valve for adjusting the amount of at least one external compressor extraction taken
  • Compressor air can be supplied via a supply line such that upon adjustment of the amount of compressor air an un ⁇ different axial compensation thrust is applied to this;
  • Radial bearing which in particular with the Axialschubkol ⁇ ben storage technically cooperates, and which is also directly or indirectly supplied with the extracted compressor air via the Zulei ⁇ tion.
  • the radial bearing is typically supplied with the compressor air for blocking purposes and / or for cooling purposes.
  • the control valve can typically be designed as a valve flap forms ⁇ .
  • the Axialschubkolben which is provided for the impingement of the rotor with a Axialaus Heidelbergskraft extent cooperate delay technically with the radial bearing la ⁇ that both are supplied with the extracted compressor air via the feed line directly or indirectly.
  • the taken for the Axialschubkolben air compressor can also be used to supply the Ra ⁇ diallagers.
  • no additional external compressor extraction will be riding ⁇ asked what could ver ⁇ worry not the radial bearing.
  • radial bearings are mounted terminally in the gas turbine, so that the axial thrust piston is arranged in the end region of the gas turbine. Should now be a maintenance case, the gas turbine can be conveniently maintained from the end, without having to remove about the entire housing of the gas turbine. For example, it would be sufficient merely to remove the radial bearing in order to gain direct access to the axial thrust piston.
  • the system according to the invention is arranged in a relatively cold region of the gas turbine.
  • the compressor air line system can thus be designed for relatively low temperatures, which also cheaper components can be used. Due to the local proximity of axial thrust pistons and radial bearings and their storage technology
  • the compressor air can provide the necessary axial ⁇ shear compensation by the compressor air flows against the axial thrust piston and this is acted upon by a corresponding balancing force.
  • the compressor air can also serve as blocking or cooling air, for example, to avoid the escape of oil from the radial bearing.
  • This dual function of the compressor air thus can provide an efficient betreib ⁇ bare gas turbine as well as an easy-to-maintain gas turbine.
  • the axial thrust piston and the radial bearing are connected in series with each other with regard to the supply of compressor air.
  • one component receives the compressor air after it has been supplied to the other component first.
  • the compressor air is at first supplied to the axial thrust piston and flows from the ⁇ sem over to the radial bearing, where it shuts off approximately against leakage of bearing fluid or the radial bearing cools against heating.
  • Both, ie Axialschubkolben and radial bearings can be fluidly decoupled from each other by suitable seals from each other at least partially. However, complete decoupling from the point of view of the passage of compressor air is not provided according to the first embodiment.
  • the components can be supplied with individually conditioners ⁇ ter compressor air like that.
  • the power supplied to the Ra ⁇ diallager compressor air can be specially thermally stor ⁇ rides be about cooled.
  • the compressor air supplied to the axial thrust piston can have a significantly greater flow rate in order to be able to apply the required axial compensation thrust, for example.
  • the compressor air can be taken from the same external removal of the Ver ⁇ poet.
  • each component can be subjected to a targeted amount of compressor air so as to fulfill the desired function, as far as it is not affected by the overflow.
  • At least two external compressor withdrawals for removing compressor air at different pressure levels are provided and both open into the supply line for the axial thrust piston or the radial bearing. This is already before or at the supply line, a mixture of
  • compressor air at different pressure levels instead, resulting in a new effective pressure level.
  • the mixing of the two compressor air streams takes place with an ejector, which can allow a mixture of two compressor air streams at different pressure levels.
  • compressor air can therefore be taken at different Be ⁇ rich of the compressor.
  • a sampling of the compressor air in the front region of the compressor (based on the direction of the working fluid) in this case allows a Ent ⁇ acquisition of compressor air at relatively low pressure ⁇ level, but due to the low compression of the compressor air, this can be considered as relatively low.
  • the further back in the compressor (again based on the direction of the working fluid) extracted compressor air is ever ⁇ but relatively expensive in comparison, since a re ⁇ tively strong typographic treatment is done.
  • a cooling device is connected in the supply line, which allows cooling of the compressor air. The dissipated by means of the cooling device heat from the
  • Compressor air can in turn be used for other purposes in the context of the operation of the gas turbine as well as to other not further ⁇ related purposes.
  • the cooling device allows a thermal conditioning of the extracted compressor air to a temperature level which is suitable for use at the radial bearing, since a minimum temperature should not be exceeded when supplying compressor air to the radial bearing.
  • a further adjusting member is connected in the supply line, which allows to adjust the at least two of the external compressor withdrawals entnom- mene and already mixed with each other compressor air towards ⁇ clearly their quantity. The adjustment allows thus in the case of at least two external compressor ⁇ withdrawals a further, possibly more accurate adjustment of the amount of compressor air, which is supplied to the axial thrust piston as well as the radial bearing.
  • a pressure measuring device is connected in the supply line, which allows a determination of the pressure level at which the compressor air is supplied to the axial thrust piston.
  • the lead extends here ⁇ typi cally from a plenum or plenums of a plurality of the compressor to the Axialschubkolben or up to the radial bearing.
  • the supply line can be formed by externally attached to the housing of the gas turbine lines as well as some already existing internal lines.
  • the pressure measuring device allows the determination of the pressure level at which the compressor air is supplied to the axial thrust piston.
  • the axial thrust piston and the radial bearing are in contact with one another in the region of a bearing surface in order to provide the rotor bearing.
  • Both components thus interact with each other in terms of storage technology. Due to the immediately adjacent arrangement of the two components can also be a thermal cooling effect of a Component to the other done. In particular, the attached flow at relatively large amount of compressor air thrust ⁇ piston can contribute to the thermal conditioning of the radial bearing.
  • Figure 1 is a schematic side sectional view through a first embodiment of a gas turbine according to the invention
  • Figure 2 is a schematic sectional view through another
  • Embodiment of a gas turbine according to the invention Embodiment of a gas turbine according to the invention.
  • FIG. 1 shows a lateral sectional view through a first embodiment of the gas turbine 1 according to the invention, which has a rotor 2 which can be adjusted in the axial direction A with respect to an axial compensation thrust.
  • a rotor 2 which can be adjusted in the axial direction A with respect to an axial compensation thrust.
  • air is sucked in via the intake passage 15, and subsequently compressed in individual stages of the compressor.
  • the working medium is removed again via an exhaust gas diffuser 16, which is arranged in the region of the rear bearing star 17, out of the gas turbine 1.
  • the rotor 2 is equipped at the front with a thrust bearing 8, which is adapted to receive the axial thrust forces, or to apply corresponding counter-forces to the rotor 2.
  • the gas turbine has a radial bearing 11, which is sealed against an axial piston 10 by means of seals 12. Both components, the radial bearing 11 and the axial thrust piston 10 cooperate storage technically, by about the axial thrust piston 10 is disposed on a bearing surface of the radial bearing 11 for storage purposes.
  • the axial thrust on the rotor 2 changes in the axial direction A.
  • different forces are to be absorbed by the axial bearing 8 or, in the case of relatively deep part-load modes, an axial thrust reversal may also occur.
  • the direction of the resulting axial thrust changes from initially directing the compressor to the expansion turbine, in a direction which is precisely opposite.
  • Such an axial thrust reversal can lead to undesired vibrations of the rotor 2, as a result of which not only the axial bearing 8 is damaged, but the entire gas turbine 1 can be damaged.
  • the present embodiment of the gas turbine 1 on three external compressor withdrawals 3 may be via which compressor air from individual plenums of the compressor to below ⁇ different union pressure level PI, P2 and P3 removed.
  • the compressor air streams can be introduced into a supply line 5 and mixed.
  • suitable ejectors may be used (not shown here).
  • the present invention each has a control valve
  • Compressor air flows from the individual Plena targeted Adjustab ⁇ len.
  • the mixed stream of compressor air can also interact thermally with a cooling device 20 before being fed to the axial thrust piston 10 as well as the radial bearing 11, as a result of which the components just mentioned can be thermally conditioned. This is particularly advantageous if the extracted compressor air having a relatively high tem ⁇ peraturclude, and thus would not be suitable to come into direct ⁇ th contact with the radial bearing.
  • 11 In order to adjust the total flow of compressor air in the supply line 5 suitably, is an adjusting member 6 in the supply line
  • the setting member 6 as well as the control valves 4 are from ⁇ guide according turned provides ⁇ by a suitable setting unit 23, which in turn suitable readings taken into ⁇ into account can.
  • the axial thrust on the Axialla ⁇ ger can be followed directly as about.
  • the integrated Einstellein ⁇ can 23, the measured values of a pressure-measuring device 30 into account into account which is mounted in the area of the bearing star 17 of the Gasturbi ⁇ ne. 1
  • the pressure measuring device 30 detects the pressure prevailing in the compressor air channel, which is directly correlated with the pressure on the axial thrust piston 10.
  • the compressor air channel in the bearing star 17 is in this case part of the supply line 5. Is the compressor air to the
  • FIG. 2 shows a further embodiment of the inventive gas turbine 1, which differs from that shown in Figure 1 embodiment only in that now there are two separate fluid passages in the bearing support 17 which are adapted to a ⁇ guided in the respective channels Compressor air in each case to one of the components of axial thrust piston 10 and radial bearings 11 to lead. Both supply lines are individually provided with an adjusting member 6, so that the two channels can each be supplied with different amounts of compressed air.
  • Compressed air has been transferred to the components, these can either not be mixed in complete decoupling or be mixed together again in partial decoupling.
  • the compressor air supplied to the axial thrust piston 10 is at least partially supplied to the radial bearing.
  • the compressor air would flow via the seal 12 to the radial bearing 11.
  • seal 12 be such that a substantial fluidic decoupling of the two components is present, or gene, the compressor air of the respective components in differing ⁇ che discharge channels for discharging from the gas turbine gelan-.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Magnetic Bearings And Hydrostatic Bearings (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)

Abstract

L'invention concerne une turbine à gaz (1), équipée d'un rotor réglable axialement (2), comprenant les composants suivants : - au moins une prise de compresseur extérieure (3) destinée à prélever de l'air de compresseur ; - une soupape de commande (4) destinée à régler la quantité d'air de compresseur prélevé au niveau de l'au moins une prise de compresseur extérieure (3) ; - un piston à poussée axiale (10) qui peut être alimenté en air de compresseur prélevé via un conduit d'alimentation (5) de telle sorte que, lors du réglage de la quantité d'air de compresseur, une poussée de compensation axiale différente est appliquée sur celui-ci ; - un palier radial (11) qui coopère en particulier avec le piston de poussée axiale (10) par une technique de montage sur paliers, et qui peut également être alimenté directement ou indirectement en air de compresseur prélevé via le conduit d'alimentation (5).
EP17700929.7A 2016-02-04 2017-01-12 Turbine à gaz équipée d'un piston à poussée axiale et d'un palier radial Withdrawn EP3397843A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102016201682 2016-02-04
PCT/EP2017/050552 WO2017133873A1 (fr) 2016-02-04 2017-01-12 Turbine à gaz équipée d'un piston à poussée axiale et d'un palier radial

Publications (1)

Publication Number Publication Date
EP3397843A1 true EP3397843A1 (fr) 2018-11-07

Family

ID=57860836

Family Applications (1)

Application Number Title Priority Date Filing Date
EP17700929.7A Withdrawn EP3397843A1 (fr) 2016-02-04 2017-01-12 Turbine à gaz équipée d'un piston à poussée axiale et d'un palier radial

Country Status (5)

Country Link
US (1) US20190063222A1 (fr)
EP (1) EP3397843A1 (fr)
JP (1) JP2019508619A (fr)
CN (1) CN108603415A (fr)
WO (1) WO2017133873A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA2957467A1 (fr) * 2016-02-24 2017-08-24 General Electric Company Commande de gorge d'ejecteur de moteur de turbine
CN112211726B (zh) * 2020-09-01 2021-12-07 中国空气动力研究与发展中心低速空气动力研究所 一种基于涡喷发动机的持续引气系统
US11859547B2 (en) 2022-02-25 2024-01-02 General Electric Company Turbine engine having a balance cavity

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2708044B1 (fr) * 1993-07-21 1995-09-01 Snecma Turbomachine comportant un dispositif de mesure de la poussée axiale d'un rotor.
US6035627A (en) * 1998-04-21 2000-03-14 Pratt & Whitney Canada Inc. Turbine engine with cooled P3 air to impeller rear cavity
JP2005069167A (ja) * 2003-08-27 2005-03-17 Hitachi Ltd ２軸式ガスタービン
US7559696B2 (en) * 2004-08-30 2009-07-14 Hamilton Sundstrand Corporation Active thrust management system
EP2011963B1 (fr) 2007-07-04 2018-04-04 Ansaldo Energia Switzerland AG Procédé de fonctionnement d'une turbine à gaz à poussée axiale compensée
DE102008022966B4 (de) * 2008-05-09 2014-12-24 Siemens Aktiengesellschaft Rotationsmaschine
US8197182B2 (en) * 2008-12-23 2012-06-12 General Electric Company Opposed flow high pressure-low pressure steam turbine
KR101278944B1 (ko) * 2010-12-21 2013-06-26 두산중공업 주식회사 가스터빈 엔진의 로터 조립체 축하중 조절 장치
ITCO20120066A1 (it) * 2012-12-20 2014-06-21 Nuovo Pignone Srl Metodo per bilanciare la spinta, turbina e motore a turbina
US9963994B2 (en) * 2014-04-08 2018-05-08 General Electric Company Method and apparatus for clearance control utilizing fuel heating
CN204663669U (zh) * 2015-03-27 2015-09-23 北京华清燃气轮机与煤气化联合循环工程技术有限公司 燃气轮机转子轴向推力平衡引气结构

Also Published As

Publication number Publication date
US20190063222A1 (en) 2019-02-28
JP2019508619A (ja) 2019-03-28
WO2017133873A1 (fr) 2017-08-10
CN108603415A (zh) 2018-09-28

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