EP0704603A2 - Système d'étanchéité et de réfroidissement pour le cÔté chaud d'un arbre d'une turbine à gaz - Google Patents

Système d'étanchéité et de réfroidissement pour le cÔté chaud d'un arbre d'une turbine à gaz Download PDF

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Publication number
EP0704603A2
EP0704603A2 EP95810584A EP95810584A EP0704603A2 EP 0704603 A2 EP0704603 A2 EP 0704603A2 EP 95810584 A EP95810584 A EP 95810584A EP 95810584 A EP95810584 A EP 95810584A EP 0704603 A2 EP0704603 A2 EP 0704603A2
Authority
EP
European Patent Office
Prior art keywords
air
sealing
cooling air
rotor
exhaust gas
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Withdrawn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
EP95810584A
Other languages
German (de)
English (en)
Inventor
Alexander Dr. Beeck
Eduard Brühwiler
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.)
ABB AG Germany
Original Assignee
ABB Management 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 ABB Management AG filed Critical ABB Management AG
Publication of EP0704603A2 publication Critical patent/EP0704603A2/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Withdrawn legal-status Critical Current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
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
    • 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
    • F01D5/08—Heating, heat-insulating or cooling means

Definitions

  • the invention relates to a method and a device for shaft sealing and for cooling on the exhaust gas side of a thermal turbomachine, in particular a gas turbine with axial flow, according to the preamble of patent claim 1.
  • thermal turbomachines in particular gas turbines with axial flow, essentially consist of the bladed rotor and the vane carrier equipped with guide vanes, which is suspended in the turbine housing.
  • the gas housing Connected to the turbine housing is the gas housing, which is flanged to the turbine housing in modern machines and essentially consists of a hub-side annular inner part and an annular outer part, which delimit the gas diffuser.
  • the inner part and the outer part are connected to one another by a plurality of radial flow ribs arranged uniformly over the circumference.
  • the outlet-side bearing of the turbine rotor is arranged in the cavity within the inner part, that is to say inside the diffuser construction itself.
  • Shaft seals (labyrinth seals, stuffing box) are provided for the contact-free sealing of the rotor bushings through the exhaust housing and to reduce leakage to a reasonable level.
  • compressor air from a certain stage has so far been taken, led to the exhaust housing via a separate line and fed directly into the stuffing box on the exhaust side as sealing air. Part of the air escapes through the seal into the storage room, the rest flows along the wave washer into the hot gas duct.
  • Extracting the air at a high level has the disadvantage that, at full load, highly compressed air is "consumed” without output, which has an unfavorable effect on the efficiency of the gas turbine. If, on the other hand, you switch between different stages, more tapping points on the compressor and switching valves are necessary, so that the costs increase.
  • the rotor cooling air is also extracted from a certain compressor stage in addition to the sealing air and fed into the rotor via a special pipe.
  • the pipeline / rotor transition is made with labyrinth seals sealed.
  • the labyrinth leakage air gets into the vicinity of the warehouse and causes the storage room to heat up. This is undesirable because the storage temperature is limited due to the instruments available, the storage oil and the possibility of inspection.
  • the storage room In addition to the leakage of sealing air and rotor cooling air, the storage room is also warmed up by the heat flow from the exhaust gas flow through the insulation or the support structure. In most machines, the storage room is cooled by natural convection. Also known is the cooling of the storage space by cooling air, which enters through openings in the exhaust gas diffuser and exits through the gap between the cladding and the rib of the exhaust gas housing. With this solution, the supporting structure of the exhaust gas housing does not have a uniform temperature on the circumference, which disadvantageously leads to thermal stresses occurring and / or the bearing no longer being in the center.
  • the invention tries to avoid all of these disadvantages. It is based on the task of developing a sealing and cooling air system on the exhaust side in a thermal turbomachine, in particular an axially flow-through gas turbine, which prevents the entry of the exhaust gas into the storage space with low manufacturing and / or operating costs, which minimizes air leakage in the Allows storage space and with which the storage space temperature can be kept relatively low and in which the supporting structure of the exhaust gas housing has a uniform temperature on the circumference.
  • this is done in a device for performing the above.
  • the method is achieved in that the labyrinth seals are divided at the transition from the rotor cooling air line to the exhaust-side end of the cooled rotor and an intermediate tap with a pipe to the stuffing box for the sealing air is arranged at the dividing point, so that another pipe terminating at the stuffing box for acting as cooling air Ambient air is arranged in the storage room, the stuffing box being divided into two concentric annular spaces for the sealing air and for the cooling air, and the storage space is fed with cooling air from the cooling air ring space and that the storage space is divided in the upper part by means of a hood and in the lower part by means of an oil drip plate is.
  • the amount of sealing air and the sealing air pressure are set to an optimal level by changing the number of labyrinths and the respective gap sizes of the labyrinths, because this allows the leakage air entering the storage room to be kept at a low level and thus prevents undesired storage room heating.
  • cooling channels are arranged between the supporting structure and the insulation in the inner part of the exhaust gas housing along the flow ribs, preferably on both sides at the foot of the flow ribs, which cooling channels have holes on their turbine-side inlet part with the cooling air ring duct of the stuffing box and on their outlet part are connected to the storage room and the cooling air flows through them from the cooling air ring duct.
  • Fig. 1 shows an overview of a partial longitudinal section of a single-shaft axial gas turbine, through which the exhaust side and the last stage of the turbine are shown.
  • the storage area in the exhaust tract is shown in partial longitudinal sections in FIG. 2 and the area of the labyrinth in FIG. 3 is enlarged.
  • the gas turbine with axial flow essentially consists of the rotor 2 equipped with rotor blades 1 and the blade carrier 4 equipped with guide vanes 3, which is suspended in the turbine housing 5.
  • the exhaust gas housing 6 is flanged to the turbine housing 5, in which a plurality of flow ribs 12 are uniformly distributed over the circumference. It can be seen from FIG. 2 that the flow ribs 12 envelop the support ribs 20, which are surrounded by insulation 11.
  • the exhaust gas diffuser 9 is flanged to the exhaust gas housing 6.
  • the outlet-side mounting of the rotor 2 (bearing housing 14, bearing 15) is arranged within the exhaust housing construction. Between the bearing housing 14 and the annular inner part 7 of the exhaust gas housing 6 extends the storage space 16, which is sealed on the turbine side via the stuffing box 18 against the exhaust gas channel 32 and via labyrinth seals 17 against the rotor cooling air.
  • rotor cooling air R is taken from the compressor, not shown here, and through a pipe 19 which, coming from the compressor, leads through one of the passages 8 located at the end of the exhaust tract and extends in the region of the extended machine axis to the exhaust-side shaft end exhaust shaft end introduced into the rotor 2.
  • a leakage L of this air which, according to the prior art, emerges as a whole into the storage space 16 and reaches the surroundings of the bearing 15. This point is usually sealed with labyrinth seals 17.
  • the labyrinth 17 is now subdivided into a labyrinth 17.1 with n1 sealing strips and a gap width s1 and into a labyrinth 17.2 with n2 sealing strips and a gap width s2.
  • a pipe 22 for the sealing air S is arranged in the two labyrinths 17.1 and 17.2, which leads past the bearing housing 14 to the stuffing box 18.
  • Part of the rotor cooling air leakage L is therefore used as sealing air S. So that the sealing air S just has the required pressure, it is removed after part of the seals. This removal reduces the amount of leakage air over the remaining labyrinths, so that only a minimum of air loss and thus a minimum of efficiency loss occurs and the storage room environment is warmed up only slightly.
  • the invention is not limited to the arrangement of a single sealing air line 22.
  • two or more such pipes can be arranged at any possible locations around the bearing housing.
  • FIG. 4 shows an example of the dependence of the mass flow ratios (mass flow m1 of the total rotor cooling air leakage L1 / mass flow m2 of the leakage air L2 actually flowing into the storage space 16) in a divided labyrinth on the ratio of the number of sealing strips (n2 / n1) or on the size ratio the column (s1 / s2).
  • the mass flow ratio m1 / m2 increases with an increase in n2 / n1 and s1 / s2.
  • the amount of sealing air S (m1-m2) and its pressure can therefore be changed by changing the number of sealing strips of the labyrinth seals and by changing the gap sizes.
  • a significant additional advantage of the solution according to the invention is that no separate sealing air supply from the compressor is necessary and that there is also no need for a separate extraction point for the sealing air S in the compressor.
  • the storage space 16 does not heat up too much due to the leakage air and the heat flow from the exhaust gas flow A through the insulation 11 and the support structure 10, which comprises the hub 31 and the support ribs 20, it is cooled (see FIG. 2).
  • the heat entering the storage space 16 is transported outside through the passages 8 in the exhaust gas diffuser 9 by ambient air, which is introduced by a fan 23 through a pipe 24 reaching to the stuffing box 18.
  • the stuffing box 18 is divided into two concentric annular spaces 25, 26, the annular space 25 serving for the sealing air S and the annular space 26 for the storage space cooling air K.
  • the air is distributed evenly over the circumference by the stuffing box 18.
  • the storage space 16 is divided into two parts in the upper part by means of a hood 27 arranged between the bearing housing 14 and the support structure 10, essentially parallel to the support structure 10, and in the lower part by means of an oil drip plate 28, with holes drilled in the stuffing box 18 in the cooling air ring space 26 29 the necessary amount of cooling air in the two parts of the storage room 16 is determined.
  • the support structure 10 can thus be cooled in a targeted and uniform manner on the circumference.
  • the surroundings of the bearing housing 14 and the instruments arranged inside the hood 27 are cooled separately.
  • the hood 27 has the task of preventing heat radiation on instruments and bearing housing 14.
  • cold air is brought selectively into the vicinity of the oil wipers 13 in the upper and lower part from the cooling air ring space 26. This ensures that only cold air penetrates into the bearing body 15, in which a small negative pressure should always prevail.
  • cooling channels 30 are also arranged in the support structure 10 here. These cooling channels 30 are located at the foot of the supporting ribs 20 and are fed with air from the cooling air ring space 26 via bores 29. The cooling channels 30 are each preferably arranged on both sides at the foot of the support ribs 20 and serve to dissipate the heat coming from the exhaust gas stream before it enters the hub 31 or the interior.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
EP95810584A 1994-10-01 1995-09-20 Système d'étanchéité et de réfroidissement pour le cÔté chaud d'un arbre d'une turbine à gaz Withdrawn EP0704603A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4435322A DE4435322B4 (de) 1994-10-01 1994-10-01 Verfahren und Vorrichtung zur Wellendichtung und zur Kühlung auf der Abgasseite einer axialdurchströmten Gasturbine
DE4435322 1994-10-01

Publications (1)

Publication Number Publication Date
EP0704603A2 true EP0704603A2 (fr) 1996-04-03

Family

ID=6529844

Family Applications (1)

Application Number Title Priority Date Filing Date
EP95810584A Withdrawn EP0704603A2 (fr) 1994-10-01 1995-09-20 Système d'étanchéité et de réfroidissement pour le cÔté chaud d'un arbre d'une turbine à gaz

Country Status (5)

Country Link
US (1) US5564896A (fr)
EP (1) EP0704603A2 (fr)
JP (1) JP3768271B2 (fr)
CN (1) CN1127327A (fr)
DE (1) DE4435322B4 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
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WO2009146785A1 (fr) * 2008-06-06 2009-12-10 Uhde Gmbh Blocage du compresseur de no et du détendeur de gaz résiduel dans une installation d’acide nitrique
EP2154348A3 (fr) * 2008-08-13 2010-03-31 Cummins Turbo Technologies Limited Procédé et système de freinage de moteur
WO2012141858A1 (fr) * 2011-04-12 2012-10-18 Siemens Energy, Inc. Système d'étanchéité de refroidissement à basse pression pour un moteur à turbine à gaz
EP3023583A1 (fr) * 2014-11-20 2016-05-25 Siemens Aktiengesellschaft Turbine à gaz avec le refroidissement du dernier étage de la turbine

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FR2916018B1 (fr) * 2007-05-10 2009-08-21 Snecma Propulsion Solide Sa Systeme d'echappement pour turbine a gaz
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JP5357659B2 (ja) * 2009-08-11 2013-12-04 三菱重工業株式会社 ガスタービン
EP2405103B1 (fr) * 2009-08-24 2016-05-04 Mitsubishi Heavy Industries, Ltd. Anneaux fendus avec structure de refroidissement
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US8347600B2 (en) 2011-08-25 2013-01-08 General Electric Company Power plant and method of operation
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US20130064638A1 (en) * 2011-09-08 2013-03-14 Moorthi Subramaniyan Boundary Layer Blowing Using Steam Seal Leakage Flow
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DE102012203144A1 (de) * 2012-02-29 2013-08-29 Siemens Aktiengesellschaft Strömungsmaschine
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CN103089451B (zh) * 2013-01-18 2015-01-28 中国科学院工程热物理研究所 一种隔热罩
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Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009146785A1 (fr) * 2008-06-06 2009-12-10 Uhde Gmbh Blocage du compresseur de no et du détendeur de gaz résiduel dans une installation d’acide nitrique
RU2478568C2 (ru) * 2008-06-06 2013-04-10 Уде Гмбх Уплотнение no-компрессора и расширителя остаточного газа в установке для получения азотной кислоты
EP2154348A3 (fr) * 2008-08-13 2010-03-31 Cummins Turbo Technologies Limited Procédé et système de freinage de moteur
US8474433B2 (en) 2008-08-13 2013-07-02 Cummins Turbo Technologies Limited Engine braking method and system
US9194304B2 (en) 2008-08-13 2015-11-24 Cummins Turbo Technologies Limited Engine braking method and system
WO2012141858A1 (fr) * 2011-04-12 2012-10-18 Siemens Energy, Inc. Système d'étanchéité de refroidissement à basse pression pour un moteur à turbine à gaz
US8684666B2 (en) 2011-04-12 2014-04-01 Siemens Energy, Inc. Low pressure cooling seal system for a gas turbine engine
EP3023583A1 (fr) * 2014-11-20 2016-05-25 Siemens Aktiengesellschaft Turbine à gaz avec le refroidissement du dernier étage de la turbine
WO2016078980A1 (fr) * 2014-11-20 2016-05-26 Siemens Aktiengesellschaft Turbine à gaz à refroidissement du dernier étage de la turbine
US10125624B2 (en) 2014-11-20 2018-11-13 Siemens Aktiengesellschaft Gas turbine with cooling of the last turbine stage

Also Published As

Publication number Publication date
CN1127327A (zh) 1996-07-24
US5564896A (en) 1996-10-15
DE4435322B4 (de) 2005-05-04
JPH08100674A (ja) 1996-04-16
JP3768271B2 (ja) 2006-04-19
DE4435322A1 (de) 1996-04-04

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