EP2282015A1 - Turbomachine avec joint amélioré - Google Patents

Turbomachine avec joint amélioré Download PDF

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Publication number
EP2282015A1
EP2282015A1 EP09164090A EP09164090A EP2282015A1 EP 2282015 A1 EP2282015 A1 EP 2282015A1 EP 09164090 A EP09164090 A EP 09164090A EP 09164090 A EP09164090 A EP 09164090A EP 2282015 A1 EP2282015 A1 EP 2282015A1
Authority
EP
European Patent Office
Prior art keywords
rotor
seal
rotating machine
row
guide vane
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
EP09164090A
Other languages
German (de)
English (en)
Other versions
EP2282015B1 (fr
Inventor
Cyrille Bricaud
Thomas Zierer
Carlos Simon-Delgado
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.)
GE Vernova GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Priority to EP09164090.4A priority Critical patent/EP2282015B1/fr
Priority to CN201010256653.8A priority patent/CN101936194B/zh
Publication of EP2282015A1 publication Critical patent/EP2282015A1/fr
Application granted granted Critical
Publication of EP2282015B1 publication Critical patent/EP2282015B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D11/001—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
    • F01D11/02—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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • 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
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator

Definitions

  • the present invention relates to a rotating machine with an improved seal.
  • Turbo machines such as gas turbines or steam turbines are provided with a stator (made of a plurality of stator parts) enclosing a rotor (that carries a plurality of rotor parts) rotating within it.
  • stator parts and the rotor parts are usually provided with labyrinth or brush seals, in order to control and limit the leakage between high and low pressure areas.
  • the technical aim of the present invention is therefore to provide a rotating machine with an improved seal by which the said problems of the known art are eliminated.
  • an object of the invention is to provide a rotating machine by which the pressure energy of the fluid is not dissipated and thus wasted.
  • the pressure energy of the fluid is not dissipated as heat.
  • Another object of the invention is to provide a rotating machine by which the leakage can be regulated independently from the clearance between the stator and rotor parts.
  • the rotating machine 1 (such as a gas turbine or a steam turbine) with an improved seal comprises stator parts 2 and rotor parts 3; between the stator parts 2 and rotor parts 3 a gap 4 is defined.
  • the gap 4 houses a seal 5 that comprises a guide vane row 6 extending from the stator parts 2 and arranged to guide a fluid flow 7 in the gap 4 and a rotor blade row 14 extending from the rotor part 3 and arranged to exchange mechanical power with the fluid flow 7.
  • the guide vane row 6 and rotor blade row 14 maintain the differential pressure between areas at the opposite ends of the seal 5 and prevent the fluid flow 7 from dissipating its pressure energy generating heat.
  • the seal 5 also comprises an obstruction arranged to limit the fluid flow 7 through the gap 4.
  • the obstruction comprises annular plates 9, 11 and, in this respect, a first annular plate 9 extends transversally from a stator part 2, defining an annular passage 10 for the fluid flow 7 having a prefixed thickness.
  • the guide vane row 6 may extend from this stator annular plate 9.
  • annular plate 11 extends transversally from a rotor part 3, defining an annular passage 12 for the fluid flow 7 having a prefixed thickness.
  • the rotor blade row 14 may extend from the annular plate 11.
  • the seal 5 may define an axial or a radial micro-turbine.
  • the pressure energy of the fluid is not dissipated as heat, but is used to provide turbine work thus leading to a decrease of the total temperature of the air (up to 60K per stage). So the rotor and stator temperature are also reduced.
  • figure 13 shows an axial micro-turbine having the guide vane row 6 followed by the rotor blade row 14, nevertheless in different embodiments the rotor blade row 14 may not be provided; in this case the guide vane row 6 drives the fluid flow 7 towards the main rotor blades 16 of the rotating machine 1.
  • the obstructions may not be provided or may be provided in different positions.
  • the seal 5 could have one or more annular plates 9 extending from a stator part 2 and/or one or more annular plates 11 extending from the rotor part 3; the plates 9 and 11 may be placed partly or totally upstream of and/or between and/or downstream of the guide vane row 6 and rotor blade row 14.
  • the seal of the invention defines an axial or radial micro-compressor.
  • the seal has the rotor blade row 14 followed by the guide vane row 6; nevertheless in different embodiments the guide vane row 6 may not be provided.
  • the obstructions may not be provided or may be provided in different positions.
  • the seal 5 could have one or more annular plates 9 extending from the stator part 2 and/or one or more annular plates 11 extending from the rotor part 3; the plates 9 and 11 may be placed partly or totally upstream of and/or between and/or downstream of the guide vane row 6 and rotor blade row 14.
  • micro-turbine and the micro-compressor may have one single stage or multiple stages.
  • the micro-turbine can be implemented in the rim seal, at the rotor heat shield/vane, at the stator heat shield/blade, as a radial or axial seal arrangement or in combination with labyrinth or brush seal.
  • micro-compressor may be implemented in the bearing areas, (no leakage tolerated), as an axial or radial seal arrangement or in combination with labyrinth or brush seal.
  • micro-turbine and micro-compressor are possible.
  • the blades of the guide vane row 6 and/or rotor blade row 14 may have a height of some millimetres, such as less than 10 millimetres, preferably less than 5 millimetres and more preferably less than 3 millimetres.
  • the blades can be directly machined on the rotor shaft, rotor disk, blade root, casing, honeycomb at the vane hub, stator heat shield or rotor heat shield. Nevertheless the blades can also be designed on the sealing strips, or be separated attached parts.
  • Figure 1 shows an embodiment wherein the seal 5 defines an axial micro-turbine.
  • FIG 1 shows a stator part 2 from which the main stator blades 18 defining a plurality of guide vanes extend (i.e. the stator blades 18 are those of the gas or steam turbine).
  • Figure 1 also shows a rotor part 3 from which the main rotor blades 16 extend (i.e. the rotor blades 16 are those of the gas or steam turbine).
  • a gap 4 is defined between the tip of the stator blades 18 and the rotor part 3 .
  • the stator blades 18 have at their tip the guide vane row 6 extending within the gap 4.
  • the hot gases pass through the stator blades 18 and rotor blades 16.
  • a part of the hot gases (i.e. the fluid flow 7) leaks in the gap 4 and passes through the guide vane row 6 that processes it and drives it towards the main rotor blades 16.
  • the mass flow through the gap 4 is defined by the thickness of the gap 4 and the shape of the guide vane row 6 (and naturally also the differential pressure upstream and downstream of the guide vane row 6).
  • This embodiment lets further mechanical power be collected by the main rotor blades 16 (the power that in traditional seals is dissipated, in the seal according to this embodiment of the invention is collected by the rotor blades 16); thus the local temperatures (in particular those of the air and rotor parts) are reduced with respect to traditional seals, because there is no or less fluid flow pressure energy that is converted into heat.
  • Figure 2 through 6 show different embodiments of axial micro-turbines having a guide vane row 6 and a rotor blade row 14.
  • figure 2 shows an axial micro-turbine having a stator part 2 and a rotor part 3 defining a gap 4; the stator part 2 supports the guide vane row 6 and the rotor part 3 supports the rotor blade row 14.
  • the fluid flow 7 (i.e. the leakage) passes through the passage 10 between the annular plate 9 and the rotor part 3 and passes through the guide vane row 6; then the fluid flow 7 passes through the rotor blade row 14 and delivers mechanical power to the rotor part 3.
  • the mass flow of the fluid passing through the gap 4 is defined by the passage 10 (i.e. the annular plate 9) and by the geometry and configuration of the guide vane row 6 and rotor blade row 14.
  • FIG 3 shows a seal 5 with two annular plates 9 extending from the stator part 2 respectively one upstream of the guide vane row 6, and the other downstream of the rotor blade row 14.
  • Figure 4 shows a seal 5 with and annular plate 11 extending from the rotor part 3 upstream of the guide vane row 6 and a further annular plate 9 extending from the stator part 2 between the guide vane row 6 and the rotor blade row 14.
  • Figure 5 shows a seal 5 with a guide vane row 6 extending from the stator part 2 and an annular plate 11 extending from the rotor part 3 downstream of the guide vane row 6 and carrying at its border the rotor blade row 14.
  • Figure 6 shows a seal 5 with an annular plate 9 extending from the stator part 2; from the border of the annular plate 9 the guide vane row 6 extends. Downstream of the guide vane row 6, the rotor blade row 14 extends from a rotor part 3.
  • FIG. 7 through 9 show three different embodiments of a seal defining a radial micro-turbine; also in this case the same numbers are used for the same or similar elements.
  • figure 7 shows a stator part 2 carrying the main stator blades 18 and a rotor part 3 carrying the main rotor blades 16.
  • the radial gap 4 is defined, housing an annular plate 11 extending from the rotor part 3 and downstream of it (with respect to the direction of the fluid flow 7) a guide vane row 6 extending (in this embodiment) from an annular plate 9.
  • a fluid flow 7 of compressed air (purge air) is injected through the gap 4 towards the hot gases path 20.
  • This fluid flow 7 passes through the passage 12 between the border of the annular plate 11 and the stator part 2 and then passes through the guide vane row 6 that prepares the fluid flow 7 to pass through the main rotor blades 16 and drives it towards it.
  • the mass flow of the fluid flow 7 is limited by the plate 11 (i.e. the thickness of the passage 12) and the shape and configuration of the guide vane row 6 and annular plate 9.
  • the temperature increase is limited because the amount of energy pressure of the fluid flow converted into heat is limited (this energy is gathered as mechanical power by the main rotor blades 16).
  • Figures 8 and 9 show two embodiments of a radial micro-turbine having the guide vane row 6 and the rotor blade row 14.
  • figure 8 shows a stator part 2 from which the main stator blades 18 extend and a rotor part 3 from which the main rotor blades 16 extend.
  • annular plate 9 extending from the stator part 2 and carrying at its border the guide vane row 6 and downstream of it a rotor blade row 14 extending from the rotor part 3 are housed.
  • Figure 9 shows a further embodiment similar to those already described. This embodiment has a guide vane row 6 extending from an annular plate 9 connected to a stator part 2, a rotor blade row 14 and a further annular plate 9.
  • Figures 10 through 12 show three seals defining a micro-compressor; also in these cases the reference numbers are the same as those already used to indicate the same or similar elements.
  • figure 10 shows a seal 5 defining an axial micro-compressor.
  • figure 10 shows a stator part 2 and a rotor part 3 defining a gap 4.
  • the stator part 2 carries a guide vane row 6 and upstream of it (with respect to the fluid flow 7) the rotor part 3 carries a rotor blade row 14.
  • the seal 5 upstream of the rotor blade row 14, the seal 5 has an annular plate 9 extending from the stator part 2 and a further annular plate 11 extending from the rotor part 3.
  • the fluid flow 7 (initially in the lower pressure area 22) overcomes the annular plates 11 and 9 and then passes through the rotor blade row 14 and thus through the guide vane row 6 to be supplied to the higher pressure area 24.
  • the seal 5 can thus be designed in order to have a desired flow from the higher pressure area 24 towards the lower pressure area 22, or no flow at all (i.e. the leakage 25 from the higher pressure area 24 towards the lower pressure area 22 is fully compensated by the flow 7 from the lower pressure area 22 towards the higher pressure area 24).
  • the seal 5 can be designed in order to have a reverse flow, i.e. the fluid flow 7 from the lower pressure area 22 towards the higher pressure area 24 is greater than the leakage 25 from the higher pressure area 24 towards the lower pressure area 22.
  • the mass flow of the fluid is defined by the annular plates 11 and 9 and by the configuration and shape of the rotor blade row 14 and guide vane row 6.
  • Figure 11 shows a further embodiment of axial micro-compressor having rotor blade row 14.
  • the rotor part 3 carries the rotor blade row 14 and, upstream of it, an annular plate 11; between the rotor blade row 14 and annular plate 11 the stator part 2 carries an annular plate 9.
  • Figure 12 shows an embodiment of radial micro-compressor.
  • stator part 2 carries the main stator blades 18 and a rotor part 3 carries the main rotor blades 16.
  • the gap 4 is provided.
  • a rotor blade row 14 extends from the rotor part 3 and a guide vane row 6 extends from the stator part 2.
  • This embodiment could be used for example to reduce or eliminate the purge air, i.e. the air injected in the gap 4 to prevent the hot gases flowing in the hot gases path 20 from entering the gap 4.
  • the seal 5 could be designed such that a recirculation occurs that keeps the hot gases in the hot gases path 20.
  • the mass flow of the fluid is defined by the configuration and shape of the rotor blade row 14 and guide vane row 6.
  • the temperature increase is limited, because the amount of energy pressure converted into heat is limited (the energy of the fluid is increased).

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP09164090.4A 2009-06-30 2009-06-30 Turbomachine avec joint amélioré Active EP2282015B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP09164090.4A EP2282015B1 (fr) 2009-06-30 2009-06-30 Turbomachine avec joint amélioré
CN201010256653.8A CN101936194B (zh) 2009-06-30 2010-06-30 具有改进的密封结构的旋转机械

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP09164090.4A EP2282015B1 (fr) 2009-06-30 2009-06-30 Turbomachine avec joint amélioré

Publications (2)

Publication Number Publication Date
EP2282015A1 true EP2282015A1 (fr) 2011-02-09
EP2282015B1 EP2282015B1 (fr) 2013-04-17

Family

ID=41401802

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09164090.4A Active EP2282015B1 (fr) 2009-06-30 2009-06-30 Turbomachine avec joint amélioré

Country Status (2)

Country Link
EP (1) EP2282015B1 (fr)
CN (1) CN101936194B (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112832872B (zh) * 2021-02-03 2022-09-06 东方电气集团东方汽轮机有限公司 一种用于汽轮机的引流回旋式汽封
CN116663265B (zh) * 2023-05-18 2025-03-21 哈尔滨工业大学 一种轴向偏心摆电磁式能量收集器的功率优化方法

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4875831A (en) * 1987-11-19 1989-10-24 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Compressor rotor blade having a tip with asymmetric lips
US6059530A (en) * 1998-12-21 2000-05-09 General Electric Company Twin rib turbine blade
US20050058533A1 (en) * 2003-09-12 2005-03-17 Mes International, Inc. Sealing arrangement in a compressor
DE102004050739A1 (de) * 2004-10-19 2006-04-20 Mtu Aero Engines Gmbh Turbomaschine, insbesondere Gasturbine
US20060133927A1 (en) * 2004-12-16 2006-06-22 Siemens Westinghouse Power Corporation Gap control system for turbine engines
US20070237627A1 (en) * 2006-03-31 2007-10-11 Bunker Ronald S Offset blade tip chord sealing system and method for rotary machines

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7001145B2 (en) * 2003-11-20 2006-02-21 General Electric Company Seal assembly for turbine, bucket/turbine including same, method for sealing interface between rotating and stationary components of a turbine
GB0808206D0 (en) * 2008-05-07 2008-06-11 Rolls Royce Plc A blade arrangement

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4875831A (en) * 1987-11-19 1989-10-24 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Compressor rotor blade having a tip with asymmetric lips
US6059530A (en) * 1998-12-21 2000-05-09 General Electric Company Twin rib turbine blade
US20050058533A1 (en) * 2003-09-12 2005-03-17 Mes International, Inc. Sealing arrangement in a compressor
DE102004050739A1 (de) * 2004-10-19 2006-04-20 Mtu Aero Engines Gmbh Turbomaschine, insbesondere Gasturbine
US20060133927A1 (en) * 2004-12-16 2006-06-22 Siemens Westinghouse Power Corporation Gap control system for turbine engines
US20070237627A1 (en) * 2006-03-31 2007-10-11 Bunker Ronald S Offset blade tip chord sealing system and method for rotary machines

Also Published As

Publication number Publication date
CN101936194A (zh) 2011-01-05
CN101936194B (zh) 2016-01-06
EP2282015B1 (fr) 2013-04-17

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