EP2011963A1 - Turbine à gaz à poussée axiale compensée - Google Patents

Turbine à gaz à poussée axiale compensée Download PDF

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Publication number
EP2011963A1
EP2011963A1 EP08159584A EP08159584A EP2011963A1 EP 2011963 A1 EP2011963 A1 EP 2011963A1 EP 08159584 A EP08159584 A EP 08159584A EP 08159584 A EP08159584 A EP 08159584A EP 2011963 A1 EP2011963 A1 EP 2011963A1
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EP
European Patent Office
Prior art keywords
thrust
turbine
load
annular space
pressure
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.)
Granted
Application number
EP08159584A
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German (de)
English (en)
Other versions
EP2011963B1 (fr
Inventor
Stefan Rofka
Rene Waelchli
Sven Olmes
Thomas Zierer
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.)
Ansaldo Energia Switzerland AG
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Alstom Technology AG
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Publication of EP2011963A1 publication Critical patent/EP2011963A1/fr
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    • 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

Definitions

  • the invention relates to a method for operating a gas turbine with axial thrust compensation and a gas turbine with apparatus for carrying out the method.
  • the axial thrust of a gas turbine is the resulting force of aerodynamic forces and compressive forces, which exert an axial force on the rotor in the compressor and turbine, as well as all acting in the axial direction of the rotor pressure forces.
  • the resulting thrust is absorbed by a thrust bearing.
  • gas turbines are designed to have a minimum thrust at idle.
  • the axial thrust increases proportionally to the load.
  • a counterforce to the thrust balance can be applied against the increasing axial load with the load.
  • the maximum thrust to be absorbed by the thrust bearing can be reduced. Accordingly, the size and the power loss of the thrust bearing can be reduced.
  • the thrust of turbines and compressors as well as the compressive forces acting on the rotor in the axial direction are determined by operating parameters, in particular the position of compressor guide vanes and compressor discharge pressure as well as the design. He is determined by the selected geometries, in particular by the geometries of the blade channels and the degrees of reaction of the turbine stages.
  • the operating parameters are of the desired Process and operating concept of the gas turbine dependent. The load-dependency of the thrust can not be changed once the design has been selected.
  • a pressure compensating piston is in the US4653267 shown.
  • the pressure equalizing piston in the middle part, that is, the part located between the compressor and turbine, running a two-shaft system.
  • the axial force of the piston is reduced in normal operation by a second chamber pressurized with leakage air. Air can be discharged from this second chamber via a valve and thus the pressure level in this chamber can be reduced. By changing the pressure level in the second chamber, the resulting axial force of the pressure compensating piston is regulated.
  • the advantage of this arrangement is that the air discharged from the second chamber for control can continue to be used for turbine cooling.
  • the object of the present invention is to provide a controllable thrust balance in gas turbines without the use of additional structural components, which at high load and in particular at the design point has no additional cooling air consumption for acting on pressure equalization piston or the like result.
  • the controllable thrust balance in gas turbines to be retrofitted, the one accordingly EP0447886 have executed middle part.
  • a gas turbine according to the invention with respect to aerodynamic forces and compressive forces that exert an axial force on the rotor, so designed that it has a negative thrust at idle and deep part load.
  • a negative thrust is a thrust that points from the turbine towards the compressor. Further, it is designed so that it has a positive thrust at high gas turbine load and especially at full load.
  • an additional thrust in the main thrust direction that is to say a positive thrust in the direction of the compressor to the turbine, is applied at idle and part load.
  • the resulting maximum thrust force to be absorbed by the at least one thrust bearing is consequently smaller than in a conventionally designed gas turbine without thrust balance.
  • a thrust reversal in loading or unloading of the gas turbine is prevented by the additional thrust.
  • the load range in which an additional thrust is applied is, for example, in the range from idle to about 60% full load.
  • the part load range in which an additional boost is applied for example, to about 90% full load range.
  • the partial load range in which additional thrust is applied for example, only up to about 10% full load range.
  • the additional thrust is generated by a method for regulating the pressure on the end face or on a partial surface of the end face of the turbine rotor.
  • a substantially annular space between the drum cover and the first turbine disk which is closed by a rotor seal a turbine blade root seal, divided by a seal in an outer and an inner annulus.
  • the turbine rotor is supplied with high-pressure cooling air from the outer annular space, which is fed into this annular space with the highest possible tangential velocity.
  • the static pressure in the outer annulus is due to the strong acceleration to the highest possible tangential velocity significantly below the compressor end pressure.
  • a swirl nozzle is used, for example.
  • the ratio of the pressure drop across the rotor seal and turbine disk seal is inversely proportional to the ratio of the equivalent areas of both seals.
  • the rotor seal has a significantly smaller equivalent area than the turbine disk seal.
  • the pressure drop across the rotor seal is correspondingly much larger than that over the turbine disk seal. The pressure in the inner annular space is therefore determined when the control valve is closed essentially by the pressure in the outer annular space.
  • the inner annular space is acted upon by at least one line from Kompressorplenum or other suitable extraction point with compressed air.
  • at least one control valve is provided to control the pressurization.
  • pressurize for example, externally supplied compressed air or steam can be used or an externally supplied medium can be used in combination with compressor air.
  • the advantage of this method is that in the high load range no additional pressurization is required and thus no compressed air is consumed under performance andumblesgradeinbusse. Even if the pressurization is active at partial load, the air escaping via the seal between the inner and outer annular space is usefully added to the rotor cooling air.
  • the at least one control valve may be open at low load and closed when a discrete limit is exceeded. Conversely, the at least one control valve is opened again when it falls below the discrete limit value.
  • a hysteresis can be provided.
  • Another control option is, for example, a closure of the control valve proportional to the load.
  • the position of the control valve is not specified as a function of the load, but the pressure ratio between the inner annular space and compressor discharge pressure is predetermined and this ratio is regulated via the control valve.
  • the target value is not necessarily constant, but is, for example, a function of the load.
  • the function can, for example, be determined in such a way that a constant axial thrust is achieved over the widest possible operating range.
  • the position of the control valve or the target value of the pressure conditions in the inner annular space can for example also be provided as a function of the Ver Whyreintrittsleitschaufelwinkel or the relative load. Regulations depending on combinations of parameters or other relevant parameters are also possible.
  • a special case is the application in connection with the upgrade of a gas turbine.
  • a change in one of the main components turbine or compressor can lead to a reduction of the axial thrust. This will be the case, for example, when the compressor thrust increases due to an upgrade compressor with virtually unchanged intake mass flow and thus virtually unchanged compressor discharge pressure and turbine thrust.
  • the increase in compressor thrust can cause a thrust reverser after the upgrade.
  • the method according to the invention can be used and a controlled additional thrust can be applied.
  • a gas turbine with reduced maximum axial thrust characterized by at least one pressurizable partial surface of the turbine rotor, the subject of the invention.
  • One embodiment is a gas turbine with a seal that divides the substantially annular space between the drum cover and the first turbine disk into an outer and an inner annular space. It has at least one line from the compressor plenum to the drum cover, at least one control valve in this line and at least one inlet into the inner annulus.
  • a labyrinth seal is an example of a suitable seal.
  • the introduction into the inner annulus of the drum cover is a generally annular plenum connected to the inner annulus through a plurality of orifices.
  • At least one pressure gauge is also provided in the inner annulus and in the compressor plenum.
  • the at least one supply line for pressurizing the inner plenum is not connected to the Kompressplplenum, but another suitable extraction point for compressor air via at least one control valve.
  • the invention is based on embodiments in the Fig. 1 to 4 shown schematically.
  • a gas turbine with a device for carrying out the method according to the invention essentially has at least one compressor, at least one combustion chamber and at least one turbine, which drives the compressor and a generator via at least one shaft.
  • Fig. 1 shows a section through the middle part of a gas turbine, that is, the area between the compressor and turbine and the final stage of the compressor and the first stage of the turbine.
  • the compressor 1 compresses the air. Most of the air is introduced via the Kompressplplenum 2 in a combustion chamber 3 and mixed with fuel, which burns there. From there, the hot fuel gases flow under labor output through a turbine 4. Turbine 4 and compressor 1 are arranged on a common shaft 18, wherein the part of the shaft located between compressor 1 and turbine 4 is designed as a drum 6.
  • the high-pressure part of the rotor cooling air is swirled after the last compressor blade through an annular channel 7 between the rotor drum 6 and drum cover 5 and introduced via the rotor cooling air supply 12 and a swirl grille 13 in an annular space between the drum cover and a first turbine disk.
  • This annulus is divided by a seal 9 in an inner annulus 10 and an outer annulus 11.
  • the outer annular space is bounded, for example, by the rear side of a drum cover 5, an inner platform of a first turbine guide vane facing the rotor 18, a first turbine disk and the seal 9.
  • the inner annular space is bounded, for example, by the rear side of a drum cover 5, a seal 9, a first turbine disk of a rotor seal 8 and the walls of a part of an annular channel 7 lying downstream of a rotor seal 8.
  • the seal 9 can be performed, for example, as a labyrinth seal 21.
  • a labyrinth seal 21 For receiving the labyrinth seal 21, for example, as in Fig. 2 shown, offset from each other, referred to as balconies projections on a drum cover 19 and a first turbine disk 20 are provided.
  • the rotor cooling air supply 12 may be connected, for example via a swirl grille 13 with an outer annular space 11 that accelerates the rotor cooling air tangentially and thus lowers the static pressure in an outer annular space 11. From the one outer annular space 11, the rotor cooling air enters a first turbine disk.
  • annular space in front of a first turbine disk ie the substantially annular space between the drum cover 5 and the first turbine disk, which is closed by a rotor seal 8, a turbine blade root seal 24, divided by a seal 9 in an inner 10 and outer annular space 11.
  • This division makes it possible to pressurize the inner annulus 10 via a pressure line 14 and a control valve 15 with compressed air from the Kompressplplenum 2.
  • the introduction 16 of the compressed air into the inner annular space 10 can take place via holes through the drum cover or, as in Fig. 1 represented, via a plenum 17. In this case, the compressed air is fed via the at least one pressure line 14 into the plenum 17. From there it passes via the introduction 16, which is designed, for example, as a plurality of holes in the inner annular space 10th
  • the inner annular space 10 is applied at partial load to increase the thrust by opening the control valve 15 via the pressure line 14 and the introduction 16 with pressure.
  • This air passes together with the leakage air of the rotor seal 8 in the outer annular space 11.
  • Fig. 3 the resulting axial thrust for control is shown as a function of the gas turbine load in regulation with a limit value and hysteresis.
  • the control valve 15 is initially open at low load of the gas turbine. After exceeding a limit value ⁇ , the control valve is closed and remains closed in the upper load range (solid line). When reducing the load, the control valve 15 when falling below the load ⁇ is opened again (dashed line).
  • dashed lines show the thrust profile with thrust reversal, which would result without additional thrust in the lower load range.
  • Fig. 4 shows the idealized thrust curve (solid line) over gas turbine load when controlling the load-dependent pressure ratio between pressure in the inner annulus and compressor end pressure.
  • the control valve 15 is initially open at low load of the gas turbine. From reaching a target thrust, for example, at the load ⁇ , the thrust is kept constant by changing the pressure in the inner annulus. Only when the control valve 15 is completely closed, which is the case, for example, at the load ⁇ , the thrust continues to increase to reach its maximum value at full load.
  • the dependence of the pressure ratio of load can be determined by model calculations or from experiments and programmed in the gas turbine controller.
  • dashed lines show the thrust curve with thrust reversal, which would result without additional thrust.
  • seals (8 and / or 9) can be designed as a brush seal. All explained advantages can be used not only in the respectively specified combinations, but also in other combinations or alone, without departing from the scope of the invention.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Control Of Turbines (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP08159584.5A 2007-07-04 2008-07-03 Procédé de fonctionnement d'une turbine à gaz à poussée axiale compensée Active EP2011963B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH10792007 2007-07-04

Publications (2)

Publication Number Publication Date
EP2011963A1 true EP2011963A1 (fr) 2009-01-07
EP2011963B1 EP2011963B1 (fr) 2018-04-04

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US (1) US8092150B2 (fr)
EP (1) EP2011963B1 (fr)
JP (1) JP5511158B2 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2246528A3 (fr) * 2009-04-24 2014-05-14 Pratt & Whitney Canada Corp. Système de distribution de charge pour moteur à turbine à gaz
DE102016201685A1 (de) 2016-02-04 2017-08-10 Siemens Aktiengesellschaft Verfahren für den Axialkraftausgleich eines Rotors einer Gasturbine
WO2017133873A1 (fr) 2016-02-04 2017-08-10 Siemens Aktiengesellschaft Turbine à gaz équipée d'un piston à poussée axiale et d'un palier radial
DE102017205055A1 (de) 2017-03-24 2018-09-27 Siemens Aktiengesellschaft Verfahren zur Axialschubregelung eines Rotors einer Strömungsmaschine

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130195627A1 (en) * 2012-01-27 2013-08-01 Jorn A. Glahn Thrust balance system for gas turbine engine
US10815891B2 (en) * 2012-09-28 2020-10-27 Raytheon Technologies Corporation Inner diffuser case struts for a combustor of a gas turbine engine
ITCO20120066A1 (it) * 2012-12-20 2014-06-21 Nuovo Pignone Srl Metodo per bilanciare la spinta, turbina e motore a turbina
US9869190B2 (en) 2014-05-30 2018-01-16 General Electric Company Variable-pitch rotor with remote counterweights
US10072510B2 (en) 2014-11-21 2018-09-11 General Electric Company Variable pitch fan for gas turbine engine and method of assembling the same
EP3037674A1 (fr) * 2014-12-22 2016-06-29 Alstom Technology Ltd Moteur et procédé de fonctionnement dudit moteur
US10100653B2 (en) 2015-10-08 2018-10-16 General Electric Company Variable pitch fan blade retention system
US10325061B2 (en) * 2016-03-29 2019-06-18 Mentor Graphics Corporation Automatic axial thrust analysis of turbomachinery designs
US10801549B2 (en) * 2018-05-31 2020-10-13 General Electric Company Axial load management system
US11674435B2 (en) 2021-06-29 2023-06-13 General Electric Company Levered counterweight feathering system
US11795964B2 (en) 2021-07-16 2023-10-24 General Electric Company Levered counterweight feathering system

Citations (12)

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Publication number Priority date Publication date Assignee Title
CH246779A (de) * 1945-10-13 1947-01-31 Bbc Brown Boveri & Cie Turbomaschine mit Axialschub-Ausgleichvorrichtung.
US2647684A (en) * 1947-03-13 1953-08-04 Rolls Royce Gas turbine engine
US3989410A (en) * 1974-11-27 1976-11-02 General Electric Company Labyrinth seal system
US4653267A (en) 1983-05-31 1987-03-31 United Technologies Corporation Thrust balancing and cooling system
US4730977A (en) * 1986-12-31 1988-03-15 General Electric Company Thrust bearing loading arrangement for gas turbine engines
GB2200410A (en) * 1987-01-28 1988-08-03 Gen Electric Thrust balancing in turbine engine
EP0447886A1 (fr) 1990-03-23 1991-09-25 Asea Brown Boveri Ag Turbine à gaz avec flux axiale
EP0702129A2 (fr) * 1994-09-19 1996-03-20 ABB Management AG Refroidissement du rotor d'une turbine à gaz axiale
US5735666A (en) * 1996-12-31 1998-04-07 General Electric Company System and method of controlling thrust forces on a thrust bearing in a rotating structure of a gas turbine engine
US5760289A (en) 1996-01-02 1998-06-02 General Electric Company System for balancing loads on a thrust bearing of a gas turbine engine rotor and process for calibrating control therefor
US6422809B1 (en) * 1998-05-25 2002-07-23 Abb Ab Gas turbine arrangement
EP1541803A2 (fr) * 2003-12-11 2005-06-15 Rolls-Royce Deutschland Ltd & Co KG Arrangement de soulagement des paliers dans une turbine à gaz

Family Cites Families (6)

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Publication number Priority date Publication date Assignee Title
US3704077A (en) * 1970-11-03 1972-11-28 Barber Colman Co Thrust controller for propulsion systems with commonly driven, controllable pitch propellers
US4018045A (en) * 1971-06-25 1977-04-19 Motoren- Und Turbinen-Union Munchen Gmbh Regulating device for a prime mover, more particularly for a single-spool gas turbine
DE3475548D1 (en) * 1983-05-31 1989-01-12 United Technologies Corp Thrust balancing and cooling system
US20070122265A1 (en) * 2005-11-30 2007-05-31 General Electric Company Rotor thrust balancing apparatus and method
US8147178B2 (en) * 2008-12-23 2012-04-03 General Electric Company Centrifugal compressor forward thrust and turbine cooling apparatus
US8682562B2 (en) * 2009-05-08 2014-03-25 Rolls-Royce Corporation Turbine engine thrust scheduling

Patent Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH246779A (de) * 1945-10-13 1947-01-31 Bbc Brown Boveri & Cie Turbomaschine mit Axialschub-Ausgleichvorrichtung.
US2647684A (en) * 1947-03-13 1953-08-04 Rolls Royce Gas turbine engine
US3989410A (en) * 1974-11-27 1976-11-02 General Electric Company Labyrinth seal system
US4653267A (en) 1983-05-31 1987-03-31 United Technologies Corporation Thrust balancing and cooling system
US4730977A (en) * 1986-12-31 1988-03-15 General Electric Company Thrust bearing loading arrangement for gas turbine engines
GB2200410A (en) * 1987-01-28 1988-08-03 Gen Electric Thrust balancing in turbine engine
EP0447886A1 (fr) 1990-03-23 1991-09-25 Asea Brown Boveri Ag Turbine à gaz avec flux axiale
EP0702129A2 (fr) * 1994-09-19 1996-03-20 ABB Management AG Refroidissement du rotor d'une turbine à gaz axiale
US5760289A (en) 1996-01-02 1998-06-02 General Electric Company System for balancing loads on a thrust bearing of a gas turbine engine rotor and process for calibrating control therefor
US5735666A (en) * 1996-12-31 1998-04-07 General Electric Company System and method of controlling thrust forces on a thrust bearing in a rotating structure of a gas turbine engine
US6422809B1 (en) * 1998-05-25 2002-07-23 Abb Ab Gas turbine arrangement
EP1541803A2 (fr) * 2003-12-11 2005-06-15 Rolls-Royce Deutschland Ltd & Co KG Arrangement de soulagement des paliers dans une turbine à gaz

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2246528A3 (fr) * 2009-04-24 2014-05-14 Pratt & Whitney Canada Corp. Système de distribution de charge pour moteur à turbine à gaz
DE102016201685A1 (de) 2016-02-04 2017-08-10 Siemens Aktiengesellschaft Verfahren für den Axialkraftausgleich eines Rotors einer Gasturbine
WO2017133873A1 (fr) 2016-02-04 2017-08-10 Siemens Aktiengesellschaft Turbine à gaz équipée d'un piston à poussée axiale et d'un palier radial
WO2017133872A1 (fr) * 2016-02-04 2017-08-10 Siemens Aktiengesellschaft Procédé de compensation des forces axiales du rotor d'une turbine à gaz et turbine à gaz associée
DE102017205055A1 (de) 2017-03-24 2018-09-27 Siemens Aktiengesellschaft Verfahren zur Axialschubregelung eines Rotors einer Strömungsmaschine

Also Published As

Publication number Publication date
US20090067984A1 (en) 2009-03-12
JP5511158B2 (ja) 2014-06-04
US8092150B2 (en) 2012-01-10
JP2009041559A (ja) 2009-02-26
EP2011963B1 (fr) 2018-04-04

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