EP3396114A1 - Turbomaschine und zugehöriges betriebsverfahren - Google Patents

Turbomaschine und zugehöriges betriebsverfahren Download PDF

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Publication number
EP3396114A1
EP3396114A1 EP17168744.5A EP17168744A EP3396114A1 EP 3396114 A1 EP3396114 A1 EP 3396114A1 EP 17168744 A EP17168744 A EP 17168744A EP 3396114 A1 EP3396114 A1 EP 3396114A1
Authority
EP
European Patent Office
Prior art keywords
turbomachinery
seal
casing
seal member
rotor
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Withdrawn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
EP17168744.5A
Other languages
English (en)
French (fr)
Inventor
Arnd Reichert
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 EP17168744.5A priority Critical patent/EP3396114A1/de
Publication of EP3396114A1 publication Critical patent/EP3396114A1/de
Withdrawn legal-status Critical Current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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/127—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with a deformable or crushable structure, e.g. honeycomb
    • 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
    • F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
    • F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
    • 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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/232—Three-dimensional prismatic conical

Definitions

  • the present invention relates to a turbomachinery, having a casing through which a working fluid flows during operation in a direction of flow, an axially displacable rotor arranged in the casing and an annular seal.
  • the present invention relates also to a method of operating such turbomachinery.
  • seals are implemented on the rotor and/or the stator of the turbomachinery.
  • seals can be divided into seals with and without contact. Seals with contact are susceptible to wear and for this reason their performance decreases over time.
  • noncontact seals labyrinth seals are widely used.
  • PCT application WO 93/20335 A1 describes a method and a configuration for controlling a gap width between the blade tip of a rotor blade and a stator housing of a rotating machine with a turbine part and a compressor part.
  • the control of the gap width takes place in such a way that, during the startup phase of the gas turbine, the shutting down of the gas turbine and load changes of the gas turbine, the gap width is larger than it is during continuous operation of the gas turbine.
  • the rotors of the compressor and the turbine are permanently connected together so that they form a single rotor.
  • the housings of the compressor and the turbine are separated from one another and the compressor housing is arranged so that it can be displaced relative to the turbine casing. Due to a displacement of the compressor casing, a displacement of the complete rotor and, therefore, a displacement between the turbine rotor blades and the turbine casing, take place simultaneously.
  • Displacing the rotor in order to optimize turbine clearances during steady state operation is also described in WO 00/28190 A1 .
  • the axial movement of the rotor is performed e.g. automatically by hydraulic pistons behind the compressor thrust bearing.
  • Such clearance optimization upgrade is implemented after about one hour of warm-up period, i.e., when the different thermal expansions of rotor and casing components are aligned with each other. Should a loss of hydraulic pressure occur, the system is designed for the rotor to move back to its original position automatically in a "fail-safe" manner.
  • the benefit of this design is a better control the size of the clearance by displacing the rotor. Shifting the rotor upstream will increase the clearances while shifting the rotor downstream in the direction of flow of the working fluid will decrease the clearances. Large clearances are required e.g. during the start-up when parts change their shape due to large transient temperature gradients. When these differences have decayed, smaller clearances can be established by displacing of the rotor in the upstream direction.
  • a turbomachinery in particular a gas turbine, having a casing through which a working fluid flows during operation in a direction of flow, an axially displacable rotor arranged in the casing and an annular seal comprising:
  • the idea of the present invention is to provide an annular seal having an improved shape which results in an improved sealing quality when axially shifting the rotor after the transient movements have ceased.
  • the result is achieved by dividing the outer seal member in two or more annular seal segments, in particular identical seal segments, and forming each seal segment as a cone having a diameter increasing in the direction of flow.
  • the seal elements of the inner seal member are moved towards the outer seal member.
  • the projecting seal elements of the inner seal member are displaced axially from the wider part to the narrower part of the conical segments, so that the further the seal elements are shifted upstream, the smaller the gap between the seal elements on the rotor and the conical seal segments on the housing becomes. This way merely by shifting the inner seal member the gap can be closed without any radial shift of the inner or outer seal members.
  • the inner seal member is hereby attached to a rotor component and the outer seal member is attached to a casing component.
  • the rotor component is for example a turbine blade mounted on the rotor shaft.
  • the rotor component can be also the rotor shaft so that the inner seal member is attached directly to the rotor.
  • the turbomachinery is preferably a gas turbine, an aircraft engine turbine, or a stationary gas turbine for the generation of electrical energy.
  • a stationary gas turbine can then have an electrical output of more than 60 MW.
  • the turbomachinery preferably has at least two rows of rotor blades (blade rows) which are at an axial distance from one another, the casing and/or the blade tips being designed in such a way that an axial displacement of the rotor provides approximately the same radial gap for each blade row.
  • the seal elements are knife edges.
  • Knife edge seal assemblies are one variety of rotary seal employed in gas turbine engines.
  • each of the seal segments of the outer seal member has a honeycomb structure.
  • Such seal assemblies typically include a disk with an integral flange with one or more radial projections - the knife edges - and a honeycomb ring, here the outer seal member, attached e.g. to the casing or a guide vane.
  • the disk and knife edge rotate with other components of the gas turbine, while the guide vane and honeycomb ring are stationary.
  • the disk and knife edge rotate with other components of the gas turbine, while the guide vane and honeycomb ring are stationary.
  • the knife edge and honeycomb ring are assembled relative to each other to leave a small radial gap between the top of the knife edge and the inner surface of the honeycomb ring before the knife edge begins rotating in the gas turbine.
  • the displacement of the rotor shaft and hence the displacement of the knife edges towards the honeycomb ring closes the gap between the knife edge and honeycomb ring and causes the knife edge to cut into the outer seal member with the honeycomb structure.
  • the inner seal member is designed for displacement between 0.5 mm and 5 mm. This displacement is preferably provided in one direction so that the gap between the inner and the outer seal member and thus also the gap between the rotor and the casing of the turbomachinery is reduced during normal operation of the turbomachinery.
  • the object of the invention is achieved by a method of operating such turbomachinery as described above, in particularly a gas turbine, wherein the rotor is displaced relative to the casing when a steady state operation condition of the turbomachinery is reached.
  • a displacement of the rotor and respectively of the inner seal member is only carried out when a steady state operating condition of the turbomachinery has been reached with a completely steady-state temperature distribution of the individual components of the turbomachinery.
  • the achievement of such operation condition in particular the normal powered operation condition of the turbomachinery, can be determined by specifying a predetermined period, by the measurement of temperatures in the casing, by the measurement of temperature differences, by the measurement of the radial gap occurring as a consequence of the thermal expansions, and/or by relative displacement between the casing and the rotor.
  • the axial shift of the rotor is performed e.g. automatically by hydraulic pistons behind the compressor thrust bearing.
  • Such clearance optimization upgrade is implemented after e.g. about one hour of warm-up period, i.e. when the different thermal expansions of rotor and casing components are aligned with each other. Should a loss of hydraulic pressure occur, the system is designed for the rotor to move back to its original position automatically in a "fail-safe" manner.
  • FIG 1 there is seen a partial sectional view of a rotor component 2 and a casing (or stator) component 4 of a turbomachinery, which is not shown in detail and which, in the present case, is a gas turbine.
  • a gap 6 is formed between the rotor component 2 and the casing component 4.
  • a flow direction of a hot gas being the working fluid is shown during the operation of the gas turbine.
  • a radial direction is indicated by the arrow R.
  • annular seal 8 In order to seal the gap 6 an annular seal 8 is provided in the gap 6.
  • An inner seal member 8a of the annular seal 8 is attached to the rotor component 2, for example to a turbine blade.
  • the inner seal member 8a has a plurality of axially spaced, radially projecting seal elements 10, which are designed as knife edges.
  • An outer seal member 8b consists of a plurality of seal segments 12 having a honeycomb structure, each seal segment 12 having a conical shape with a diameter increasing in the direction of flow F.
  • the outer seal member 8b, i.e. the single conical seal segments 12 are attached to the casing 4.
  • the gas turbine actually operates at transient condition for a considerable time.
  • the thermodynamic parameters variations the heat transfer at the engine metallic parts, as well as the variations of engine dimensions influence significantly the engine behavior.
  • Such non-steady operation is set for example during start-up, stop and load changes of the gas turbine.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP17168744.5A 2017-04-28 2017-04-28 Turbomaschine und zugehöriges betriebsverfahren Withdrawn EP3396114A1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP17168744.5A EP3396114A1 (de) 2017-04-28 2017-04-28 Turbomaschine und zugehöriges betriebsverfahren

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP17168744.5A EP3396114A1 (de) 2017-04-28 2017-04-28 Turbomaschine und zugehöriges betriebsverfahren

Publications (1)

Publication Number Publication Date
EP3396114A1 true EP3396114A1 (de) 2018-10-31

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EP17168744.5A Withdrawn EP3396114A1 (de) 2017-04-28 2017-04-28 Turbomaschine und zugehöriges betriebsverfahren

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EP (1) EP3396114A1 (de)

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1993020335A1 (en) 1992-04-01 1993-10-14 Abb Carbon Ab A method and a device in a rotating machine
WO2000028190A1 (de) 1998-11-11 2000-05-18 Siemens Aktiengesellschaft Wellenlager für eine strömungsmaschine, strömungsmaschine sowie verfahren zum betrieb einer strömungsmaschine
US20060140756A1 (en) * 2004-12-29 2006-06-29 United Technologies Corporation Gas turbine engine blade tip clearance apparatus and method
US20090014964A1 (en) * 2007-07-09 2009-01-15 Siemens Power Generation, Inc. Angled honeycomb seal between turbine rotors and turbine stators in a turbine engine
US20110229301A1 (en) * 2010-03-22 2011-09-22 General Electric Company Active tip clearance control for shrouded gas turbine blades and related method
US20150167488A1 (en) * 2013-12-18 2015-06-18 John A. Orosa Adjustable clearance control system for airfoil tip in gas turbine engine

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1993020335A1 (en) 1992-04-01 1993-10-14 Abb Carbon Ab A method and a device in a rotating machine
WO2000028190A1 (de) 1998-11-11 2000-05-18 Siemens Aktiengesellschaft Wellenlager für eine strömungsmaschine, strömungsmaschine sowie verfahren zum betrieb einer strömungsmaschine
US20060140756A1 (en) * 2004-12-29 2006-06-29 United Technologies Corporation Gas turbine engine blade tip clearance apparatus and method
US20090014964A1 (en) * 2007-07-09 2009-01-15 Siemens Power Generation, Inc. Angled honeycomb seal between turbine rotors and turbine stators in a turbine engine
US20110229301A1 (en) * 2010-03-22 2011-09-22 General Electric Company Active tip clearance control for shrouded gas turbine blades and related method
US20150167488A1 (en) * 2013-12-18 2015-06-18 John A. Orosa Adjustable clearance control system for airfoil tip in gas turbine engine

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