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EP3034784A1 - Possibilité de refroidissement pour turbomachines - Google Patents

Possibilité de refroidissement pour turbomachines Download PDF

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Publication number
EP3034784A1
EP3034784A1 EP14199318.8A EP14199318A EP3034784A1 EP 3034784 A1 EP3034784 A1 EP 3034784A1 EP 14199318 A EP14199318 A EP 14199318A EP 3034784 A1 EP3034784 A1 EP 3034784A1
Authority
EP
European Patent Office
Prior art keywords
rotor
flow
flow channel
steam
turbomachine according
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Withdrawn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
EP14199318.8A
Other languages
German (de)
English (en)
Inventor
Christian Musch
Simon Hecker
Ralf Voss
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to EP14199318.8A priority Critical patent/EP3034784A1/fr
Priority to PCT/EP2015/078301 priority patent/WO2016096420A1/fr
Publication of EP3034784A1 publication Critical patent/EP3034784A1/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Withdrawn legal-status Critical Current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
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/26—Double casings; Measures against temperature strain in casings
    • 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
    • F01D3/02—Machines or engines with axial-thrust balancing effected by working-fluid characterised by having one fluid flow in one axial direction and another fluid flow in the opposite direction
    • 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
    • F05D2220/31—Application in turbines in steam turbines

Definitions

  • the invention relates to a turbomachine, in particular a steam turbine, comprising a rotatably mounted rotor and a housing arranged around the rotor, wherein between the rotor and the housing a first flow channel pointing in a first direction and a second flow channel pointing in a second flow direction is arranged between the first and the second flow channel a labyrinth seal comprising a plurality of tips is arranged.
  • Turbomachines in the context of this invention are, for example, steam turbines, gas turbines or compressors, the invention preferably referring to steam turbines.
  • Turbomachines are characterized by a flow medium. Hydraulic turbines, steam and gas turbines, wind turbines, centrifugal pumps and centrifugal compressors as well as propellers are summarized under the collective term turbomachinery. All of these machines have in common that they serve the purpose of extracting energy from one fluid in order to drive another machine, or vice versa, to supply energy to a fluid in order to increase its pressure.
  • the energy conversion is indirect and preferably takes the path over the kinetic energy of the fluid.
  • turbomachines such. B. in steam turbines
  • a flow medium in a main flow direction, which corresponds substantially to the direction of the axis of rotation.
  • the flow medium should ideally only flow through a so-called flow channel, which has so-called guide vanes and rotor blades.
  • the flow channel is formed of different successively arranged guide and moving blades.
  • the flow medium passes through the flow channel past the vanes and blades, the kinetic energy into rotational energy is converted, which leads to a rotation of the rotor.
  • gaps can not be avoided, resulting in undesirable flow through the gaps.
  • a first approach is to place so-called sealing lips between the rotating and fixed components.
  • the sealing lips are arranged rotationally symmetrical and act as a kind of barrier to the secondary flow.
  • a secondary flow substantially flowing to the main flow is decelerated.
  • steam turbines known as an embodiment of a turbomachine having two floods.
  • a steam turbine has a first flow channel and is arranged opposite to a second flow channel.
  • Such steam turbines are characterized by two inflow regions. A first inflow region for the first flow channel and a second inflow region for the second flow channel.
  • a common rotor has a blading region for the first flow channel and a second blading region for the second flow channel.
  • a so-called intermediate floor is arranged, which has a surface which must be arranged as close as possible to a housing arranged around the rotor.
  • a gap between the intermediate bottom and the housing should be as small as possible, because a steam flowing in in the first inflow region can partially flow through this gap and into the second inflow region of the second flow channel can flow. Therefore, such gaps are performed with so-called labyrinth seals.
  • Labyrinth seals have so-called tips, which are arranged both on the surface of the rotor and on the inner surface of the housing. Labyrinth seals are known in the art and need not be further elaborated here.
  • rotors have so-called relief grooves in the inflow region.
  • relief grooves are characterized by a smaller radius.
  • the shaft temperatures in the relief groove are limiting for the life of the shaft.
  • the shaft temperature is also limiting for the transmissive power of the shaft. Therefore, great efforts are made to lower the temperature as much as possible.
  • the invention begins, whose task is to provide a further way to reduce the temperature in the relief groove.
  • a turbomachine in particular a steam turbine, comprising a rotatably mounted rotor and a housing arranged around the rotor, wherein between the rotor and the housing a first flow channel pointing in a first direction and a second flow channel pointing in a second flow direction are arranged , wherein between the first and the second flow channel a multi-tip labyrinth seal is arranged, seen in the second flow direction after a last tip a Umlenkleit worn is arranged, which is designed such that a flowing in the axial direction in the labyrinth seal leakage at least partially into Circumferential direction of the rotor is deflected.
  • a cooling option is offered which is comparatively inexpensive to manufacture and is characterized by a Umlenkleit issued.
  • the Umlenkleit issued generates a twist of the flowing leakage steam in Area of the relief groove and can further lower the temperature at the shaft surface in the relief groove.
  • the leakage steam flowing out of the labyrinth seal is deflected by the deflection guide into the shaft rotation direction.
  • the transmissible power through the relief groove can be increased. Furthermore, the achievable lower temperature in the relief groove may also result in a cooling action on a first blade groove. This would lead to a lower utilization and thereby to an improvement in the blade design.
  • the deflecting device has a plurality of deflecting elements distributed on the circumference. This enhances the effect by distributing an appropriate number of diverters around the circumference.
  • the Umlenkleit adopted has the task to redirect the flowing in the labyrinth seal leakage steam flow and thereby to generate a twist, which causes the leakage steam is deflected in a shaft rotation direction.
  • the number of deflecting elements should be chosen appropriately.
  • the deflecting elements are bent.
  • the bow can be a parabolic Contour. It is also conceivable a circular contour.
  • the deflection elements are initially designed to be directed in the axial direction, which points in the direction of rotation, and then the deflection elements have an arc which points in the circumferential direction.
  • the deflection elements are designed such that a deflection takes place by 90 °. This is to be understood as meaning that the leakage steam flow essentially flows in the axial direction and is deflected by 90 °, which essentially corresponds to the circumferential direction.
  • the deflecting elements can be formed profiled in an advantageous development. This means that the deflecting elements have a guide-blade-shaped contour.
  • the Leitschaufelförmige contour causes a flow is deflected and accelerated, resulting in the aforementioned effect of the cooling.
  • the deflection elements are designed as a stator blade stage.
  • the FIG. 1 shows a steam turbine as an embodiment of a turbomachine and has an outer housing 2, which is arranged around a rotor 3 which is rotatably mounted about a rotation axis 4. To the rotor 3, an inner housing 5 is arranged.
  • the steam turbine 1 has a high-pressure part 6 and a medium-pressure part 7.
  • the high-pressure part 6 has a high-pressure inflow region 8, through which a high-pressure fresh steam flows.
  • the high pressure fresh steam then flows through first flow channel 10 aligned in a first direction 9, which may also be referred to as a high pressure flow channel.
  • the thermal energy of the steam in the first flow channel 10 is converted into rotational energy of the rotor 3.
  • the steam then flows out of the high-pressure outflow region 11 and from there, if necessary, to a reheater (not shown). Thereafter, the vapor flows as Mittelchristeinströmdampf in a Mittelchristeinström Scheme 12. After flowing into the Mittelchristeinström Scheme 12, the steam flows in a pointing in a second direction 13 second flow channel 14. After the second flow channel 14, the steam flows through a Mittelbuchausström Scheme 15 out of the turbomachine.
  • the rotor 3 has in the region of the Hochbucheinströmrios 8 a Relief groove 16, which can be characterized in that the rotor 3 at this point in a certain axial region has a smaller radius than the area in front and behind.
  • the rotor 3 in the region of the medium-pressure inflow region 12, the rotor 3 likewise has a relief groove 17, which can likewise be characterized in that the rotor 3 has a smaller radius in a certain axial length than the rotor 3 before the relief groove 17 and behind the relief groove 17 in FIG the second direction 13 seen from.
  • a live steam flows in the Hochdruckeinström Scheme 8 and flows for the most part through the first flow channel 10, which is formed with guide and blades not shown.
  • An undesirably small part of the high pressure fresh steam flows through a gap between the inner housing 5 and the rotor 3 in a central region 18.
  • the rotor 3 In the central region 18, the rotor 3 has a radius of a certain length and forms a so-called large intermediate bottom 19.
  • the gap between the inner housing 5 and the large intermediate bottom 19 should be formed as vapor-tight as possible and therefore has, as in FIG. 2 shown, a labyrinth seal 25 on.
  • the labyrinth seal 25 comprises a plurality of labyrinth seal segments 20, which are resiliently arranged in labyrinth seal grooves 21.
  • the labyrinth seal segments 20 can thus be moved in a radial direction 34.
  • tips 22 are arranged on the surface of the large intermediate bottom 19, as is customary with labyrinth seals 25, so-called tips 22 are arranged.
  • the tips 22 are also referred to as sealing lips or the like.
  • a tip 23 or sealing lip is likewise arranged. In an axial direction 24, the tips 22 and 23 are formed sequentially, which is in the FIG. 3 again shown separately.
  • FIG. 3 shows an arrangement according to the invention.
  • the FIG. 2 shows an enlarged section FIG. 1 namely the part of the turbomachine 1 marked with the oval FIG. 1 represented, the Medium pressure steam from the Mitteltikeinström Scheme 8 pass through the gap through the labyrinth seal 25 to the Mitteltikeinström Scheme 12.
  • This leakage should be kept as small as possible.
  • the leakage current flowing into the relief groove 17 has a comparatively high temperature, which can lead to damage to the rotor 3 in the relief groove 17. According to the invention this is prevented here, as in FIG.
  • a Umlenkleit worn 26 is arranged after a last tip 27 and which is formed such that a flowing in the axial direction 24 leakage steam is at least partially deflected in the circumferential direction 28 of the rotor.
  • the Umlenkleit Vietnamese 26 has a plurality of arranged in the circumferential direction 28 deflecting elements 29. These deflecting elements 29 can be designed bent. This means that the deflecting elements 29 are initially designed to be straight in the axial direction 24 and then have an arc 30 which finally points in the circumferential direction 28 into an end region 31.
  • the deflection elements 29 are in this case designed such that the deflection takes place by 90 °, which means that the deflection elements 29 are first formed in the axial direction 24 parallel in an initial region 32 and are formed in the end region 31 parallel to the circumferential direction 28.
  • the end region 31 may not necessarily be formed parallel to the circumferential direction 28.
  • the end portion 31 and the circumferential direction 28 may be inclined by an angle ⁇ (where ⁇ is between 0 ° and 40 °) to each other.
  • the baffles 29 may be profiled, that is, in a cross-sectional view (not shown), the baffles have a vane shape and accelerate the flow that is between the baffles.
  • the deflected leakage vapor may be mixed with a medium pressure fresh steam flowing through the medium pressure inflow region 12.
  • the turbomachine 1 has a diagonal ring 33, which acts as a first guide blade stage and deflects the medium pressure fresh steam directly into the second flow region 14, without causing a vapor to the relief groove 17.
  • a so-called swirl cooling may be considered in the diagonal ring 33, which flows a vapor from the medium-pressure inflow region into the relief groove 17, which vapor has cooled by the swirl cooling.
  • the diagonal ring 33 has for this purpose a plurality of nozzles, which represents a fluidic connection between the Mitteldruckeinström Suite 12 and the relief groove 17.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
EP14199318.8A 2014-12-19 2014-12-19 Possibilité de refroidissement pour turbomachines Withdrawn EP3034784A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP14199318.8A EP3034784A1 (fr) 2014-12-19 2014-12-19 Possibilité de refroidissement pour turbomachines
PCT/EP2015/078301 WO2016096420A1 (fr) 2014-12-19 2015-12-02 Système de refroidissement pour turbomachines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP14199318.8A EP3034784A1 (fr) 2014-12-19 2014-12-19 Possibilité de refroidissement pour turbomachines

Publications (1)

Publication Number Publication Date
EP3034784A1 true EP3034784A1 (fr) 2016-06-22

Family

ID=52146258

Family Applications (1)

Application Number Title Priority Date Filing Date
EP14199318.8A Withdrawn EP3034784A1 (fr) 2014-12-19 2014-12-19 Possibilité de refroidissement pour turbomachines

Country Status (2)

Country Link
EP (1) EP3034784A1 (fr)
WO (1) WO2016096420A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108119189A (zh) * 2016-11-30 2018-06-05 通用电气公司 叶片、旋转机械及其组装方法
US11408299B1 (en) 2021-02-16 2022-08-09 Hamilton Sundstrand Corporation Erosion mitigating labyrinth seal mating ring

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111878451A (zh) * 2020-08-11 2020-11-03 新奥能源动力科技（上海）有限公司 轴流压气机封严装置、轴流压气机及燃气轮机

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2004113770A2 (fr) * 2003-06-20 2004-12-29 Elliott Company Presse-garniture a labyrinthe abradable a inversion de tourbillon
US20060269399A1 (en) * 2005-05-31 2006-11-30 Pratt & Whitney Canada Corp. Deflectors for controlling entry of fluid leakage into the working fluid flowpath of a gas turbine engine
WO2014087512A1 (fr) * 2012-12-06 2014-06-12 三菱重工コンプレッサ株式会社 Dispositif d'étanchéité, et machine rotative
EP2775096A2 (fr) * 2013-03-08 2014-09-10 Siemens Aktiengesellschaft Diffuseur pour un carter d'échappement d'une turbine à vapeur et turbine à vapeur équipée d'un tel diffuseur

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2004113770A2 (fr) * 2003-06-20 2004-12-29 Elliott Company Presse-garniture a labyrinthe abradable a inversion de tourbillon
US20060269399A1 (en) * 2005-05-31 2006-11-30 Pratt & Whitney Canada Corp. Deflectors for controlling entry of fluid leakage into the working fluid flowpath of a gas turbine engine
WO2014087512A1 (fr) * 2012-12-06 2014-06-12 三菱重工コンプレッサ株式会社 Dispositif d'étanchéité, et machine rotative
EP2775096A2 (fr) * 2013-03-08 2014-09-10 Siemens Aktiengesellschaft Diffuseur pour un carter d'échappement d'une turbine à vapeur et turbine à vapeur équipée d'un tel diffuseur

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108119189A (zh) * 2016-11-30 2018-06-05 通用电气公司 叶片、旋转机械及其组装方法
EP3330491A1 (fr) * 2016-11-30 2018-06-06 General Electric Company Aube fixée pour une machine rotative, machine rotative associée et procédés d'assemblage d'une machine rotative
US10822977B2 (en) 2016-11-30 2020-11-03 General Electric Company Guide vane assembly for a rotary machine and methods of assembling the same
US11408299B1 (en) 2021-02-16 2022-08-09 Hamilton Sundstrand Corporation Erosion mitigating labyrinth seal mating ring

Also Published As

Publication number Publication date
WO2016096420A1 (fr) 2016-06-23

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