US20080056895A1 - Axial turbine - Google Patents

Axial turbine Download PDF

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Publication number
US20080056895A1
US20080056895A1 US11/836,437 US83643707A US2008056895A1 US 20080056895 A1 US20080056895 A1 US 20080056895A1 US 83643707 A US83643707 A US 83643707A US 2008056895 A1 US2008056895 A1 US 2008056895A1
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United States
Prior art keywords
blades
flow
stator
stator blades
moving blades
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.)
Abandoned
Application number
US11/836,437
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English (en)
Inventor
Shigeki Senoo
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.)
Hitachi Ltd
Original Assignee
Hitachi Ltd
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 Hitachi Ltd filed Critical Hitachi Ltd
Assigned to HITACHI, LTD. reassignment HITACHI, LTD. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: SENOO, SHIGEKI
Publication of US20080056895A1 publication Critical patent/US20080056895A1/en
Abandoned legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • 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
    • 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
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/126—Baffles or ribs
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/129—Cascades, i.e. assemblies of similar profiles acting in parallel
    • 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
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • F05D2240/56—Brush seals

Definitions

  • the present invention relates to axial turbines and more particularly to a drum-type rotor turbine.
  • the axial turbine such as a steam turbine or gas turbine comprise a turbine stage including stator blades formed to transform the pressure of a fluid into kinetic energy and moving blades for transforming the pressure or kinetic energy of the fluid into the rotational energy of a rotating section.
  • the stator blades are fixedly provided between an outer circumferential diaphragm and inner circumferential diaphragm forming a stationary section.
  • the moving blades are provided on a rotor that forms the rotating section.
  • a clearance is provided between the inner circumferential diaphragm and the rotor, and the clearance has a seal. This seal reduces a leakage flow that passes through the clearance. This leakage flow passing through the clearance, however, cannot be completely zeroed since the clearance must be maintained within a definite dimensional range to obtain stable rotation of the rotor.
  • JP-A-59-122707 proposes a turbine structure that cools a rotor by introducing steam through a clearance first and then through a balance hole formed in extend-through form in a rotor disc.
  • the remainder of the steam which has been passed through the clearance is further diffused outward to cool the outer surface of the rotor disc and then join the main flow of steam.
  • the method of providing a plurality of balance holes in a circumferential direction cannot be used for an axial turbine not having such a space as a drum-type rotor in which to provide the balance holes.
  • a stage with significant differences in pressure between the front and rear of the moving blades increases the flow rate of the steam flowing through the balance holes, and takes in this flow between the stator blades and the moving blades. Accordingly, the amount of steam flowing into the moving blades will be reduced and this, in turn, could reduce stage output power.
  • An object of the present invention is to provide an axial turbine having a structure in which a flow blowing out from a space formed between stator blades and moving blades exists and in which a decrease in stage output power due to such blowout flow is prevented to occur thereby to enable the turbine stage efficiency to be improved.
  • an axial turbine having a turbine stage including stator blades fixedly provided on a stationary section and moving blades fixedly provided on a rotating section of a rotor, wherein said axial turbine comprises a member coupling an inner circumferential side of said stator blades, and a structure provided on a surface of said member opposed to said moving blades for bending a flow blowing out from the side of said rotor into a space between said stator blades and said moving blades in a rotational direction of the rotating section.
  • an axial turbine having a turbine stage including stator blades fixedly provided on a stationary section and moving blades fixedly provided on a rotating section of a rotor, wherein said axial turbine comprises a diaphragm disposed at the inner circumferential side of said stator blades, and a structure provided on a surface of said diaphragm opposed to said moving blades for bending a flow blowing out from the side of said rotor into a space between said stator blades and said moving blades in a rotational direction of the rotating section.
  • an axial turbine having a turbine stage including stator blades fixedly provided on a stationary section and moving blades fixedly provided on a rotating section of a rotor, wherein said axial turbine comprises a cover formed integrally with the inner circumferential side of said stator blades, and a structure provided on a surface of said cover opposed to said moving blades for bending a flow blowing out from the side of said rotor into a space between said stator blades and said moving blades in a rotational direction of the rotating section.
  • the flow blowing out from the space between the stator blades and the moving blades is bent in the rotational direction of the rotor, it is possible to suppress interference of the blowout flow with a main flow of steam that has run in from an upstream direction between stator blades, and consequently to prevent a decrease in stage output power to occur, thereby improving turbine stage efficiency.
  • FIG. 1 is a view showing a turbine structure of an embodiment of the present invention
  • FIG. 2 is a view that shows the interference between the leakage flow in the conventional turbine structure and a flow that has run in from an upstream direction between stator blades;
  • FIG. 3 is a view that shows from a downstream side of the stator blades the interference between the leakage flow in the conventional turbine structure and the flow that has run in from the upstream direction between stator blades;
  • FIG. 4 is a diagram illustrating the way the interference between the leakage flow in the conventional turbine structure and the flow that has run in from the upstream direction between stator blades affects the moving blades;
  • FIG. 5 is a view showing a turbine stage of the present invention from a downstream side of stator blades
  • FIG. 6 is a view showing the turbine stage of the present invention from a downstream side of stator blades
  • FIG. 7 is a view showing a turbine structure of another embodiment of the present invention.
  • FIG. 8 is a view showing a turbine structure of yet another embodiment of the present invention.
  • FIG. 1 A sectional view of the turbine stage of the present invention is shown in FIG. 1 .
  • the turbine stage is provided between a high-pressure side P 0 and a low-pressure side P 1 , and includes stator blades 1 fixed to an outer circumferential diaphragm 6 and an inner circumferential diaphragm 7 , and moving blades 10 provided on a rotor 15 that rotates.
  • moving blades 10 a of another stage exist at an upstream side of the stator blades 1 .
  • a main flow of steam 20 is induced by a differential pressure P 0 -P 1 , and the flow 20 is speeded up by the stator blades 1 and deflected in a circumferential direction thereof.
  • the flow to which the circumferential velocity component has been assigned by the stator blades 1 gives kinetic energy to the moving blades 10 and rotates the rotor 15 provided with the moving blades 10 .
  • the turbine stage has a clearance 2 between the inner circumferential diaphragm 7 and the rotor 15 , and is constructed so that the rotor can rotate at high speed and stably.
  • a flow running from the high-pressure side to the low-pressure side occurs in the clearance 2 .
  • This flow is called the leakage flow. Since the leakage flow keeps away from the stator blades 1 , the leakage flow is not deflected in the circumferential direction of the stator blades and cannot assign usable rotational energy to the moving blades 10 . If the leakage flow is significant, therefore, this reduces the rotational energy or output power obtained by the turbine stage. In order to reduce the leakage flow, a seal exists in the clearance 2 .
  • the seal is formed by, for example, a combination of multiple fins 4 and multiple protrusions 5 .
  • the fins 4 themselves have a flow contraction effect, and the combination between the fins 4 and the protrusions 5 yields a thermal dissipation effect to dissipate kinetic energy by creating a complex flow path. These effects reduce the leakage flow.
  • This leakage flow passing through the clearance 2 cannot be completely zeroed since the clearance between the fins 4 and the rotor 15 must be maintained within a definite dimensional range to obtain stable rotation of the rotor 15 .
  • the inner circumferential diaphragm 7 has a structure 40 that bends the leakage flow in a rotational direction of the rotor when the flow blows out into the space between the stator blades and the moving blades.
  • the structure 40 is based on the analyses described in detail below.
  • leakage flow 25 blows out into the space formed between the stator blades and the moving blades.
  • the leakage flow 25 interferes with and disturbs the main steam flow 21 to which kinetic energy and a swirling or circumferential velocity component have been assigned after passing between stator blades.
  • FIG. 3 is a view that shows from a downstream side of the stator blades, the flow occurring at an exit of the stator blades.
  • the leakage flow 25 forms a vortex 23 by blowing upward the flow 21 that has run in between stator blades. If the leakage flow 25 is absent, the flow between stator blades becomes a circumferentially swirling flow to produce the rotational energy 30 of the rotor. This flow is denoted by reference number 22 in FIG. 3 .
  • the vortex 23 that has been formed by the interference between the leakage flow 25 and the stator exit flow 21 grows up into such a vortex 24 that behaves as if it twined the moving blades.
  • the vortex 23 cannot retrieve rotational energy effectively inside the moving blades. That is to say, the leakage flow 25 yields a double effect not only in that the flow itself produces no rotational energy, but also in that the flow reduces part of the rotational energy which the flow 21 should originally produce, and consequently, the leakage flow 25 reduces stage output power.
  • the inner circumferential diaphragm 7 of the stator blades (i.e., a member coupling an inner circumferential side of the stator blades) has the structure 40 on a surface of the diaphragm 7 opposed to the moving blades 10 .
  • the structure 40 bends the leakage flow in the rotational direction of the rotor.
  • FIG. 5 is a view showing the structure 40 from the downstream side of the stator blades.
  • the structure 40 comprises a plurality of protrusions or plates provided on the surface of the diaphragm 7 opposed to the moving blades 10 and arranged to incline in the rotational direction 30 of the rotor 15 such that an outer circumferential side of the protrusions shifts relative to an inner circumferential side thereof in the rotational direction 30 of said rotor 15 .
  • the leakage flow 25 blows upward in the flow path formed between the adjacent protrusions 40 , the leakage flow 25 is guided along the flow path and deflected in the rotational direction 30 of the rotor 15 .
  • the flow 22 that runs in from an upstream direction between stator blades is also oriented in the rotational direction 30 , and a difference in velocity between the leakage flow 25 and the stator blade flow 22 becomes smaller than in a turbine stage not having the structure 40 of the present invention.
  • a loss of flow due to interference between the leakage flow 25 and the stator blade flow 22 , and a vortex that causes the loss are augmented as the difference in relative velocity between the leakage flow 25 and the stator blade flow 22 increases. In the present invention, therefore, the occurrence of the vortex that causes the loss is suppressed and a decrease in stage output power can be avoided.
  • FIG. 6 Another example of a structure 40 formed so that the flow blowing upward between the stator blades and the moving blades will bend in a rotational direction of the moving blades is shown in FIG. 6 .
  • the structure 40 comprises a plurality of protrusions or plate each having a shape curved such that an inner circumferential side of the protrusion is oriented in a radial direction and an outer circumferential side thereof is oriented in a rotational direction 30 of the rotor 15 , thereby enabling to form a flow path directed at an inner circumferential side thereof in a radial direction and at an outer circumferential side thereof in the rotational direction 30 of the rotor.
  • a loss of flow due to the interference between the leakage flow 25 and the stator blade flow 22 can also be suppressed in the present modification of the structure 40 .
  • the structure 40 for bending in the rotational direction of the moving blades the flow blowing upward between the stator blades and the moving blades does not need to have a shape that allows the formation of a flow path with protrusions. More specifically, chipping an inner circumferential diaphragm 7 of the stator blades 1 , that is, adopting a shape that allows the formation of a flow path concaved in the rotational direction may allow the present modification of the structure 40 to be constructed so that the above blowout flow bends in the rotational direction of the moving blades.
  • a steam guide plate exists on the face of a nozzle diaphragm inner ring that is opposed to the rotor disc, and the steam guide plate gives a rotor rotational velocity component to the cooling steam that flows through the clearance formed between the nozzle diaphragm inner ring and the rotor disc.
  • the conventional turbine structure minimizes turbine work loss by giving, by the steam guide plate, the rotor rotational velocity component to the steam that flows into a balance hole, and preventing the balance hole-through steam from being assigned some kind of work.
  • both the nozzle diaphragm inner ring and the rotor disc have a protrusion(s) to obstruct the above flow at a position even more outward than the balance hole, so the advantageous effect provided by the steam guide plate has no impacts upon the flow that blows upward between the stator blades and the moving blades.
  • the balance hole since the balance hole is present, although the flow that blows out from the space between the stator blades and the moving blades originally has no significant effects, suppression of the interference between the blowout flow from the space between the stator blades and the moving blades and the main steam flow that has run in from an upstream direction between stator blades cannot be expected.
  • FIG. 7 Another embodiment of the present invention is described below by using FIG. 7 .
  • the present embodiment further augments the effect of suppressing a decrease in stage output power.
  • a clearance 45 must, as shown in FIG. 1 , be provided between the structure 40 and a rotating section 16 of the rotor 15 in order to obtain stable rotor rotation.
  • the structure 40 does not need to be in contact with the rotating section 16 , and the advantageous effect of the present invention can be obtained.
  • the advantageous effect of the present invention can be further enhanced if the structure for bending the above-described blowout flow in the rotational direction of the moving blades is installed at sections as many as possible in a direction of a rotational axis between the stator blades and the moving blades.
  • To determine the clearance 45 formed between the structure 40 and the rotating section 16 there is a need to consider not only a steady rotational state, but also a starting/stopping non-steady operational state.
  • the clearance 45 changes.
  • the clearance 45 is usually set to prevent contact between the rotating section and the stationary section, even under the above temperature change, so during steady rotation, the clearance 45 becomes larger than that actually required.
  • the structure for bending in the rotational direction of the rotor the flow that blows out from the rotor side into the space formed between the stator blades and the moving blades uses a brush seal 42 that has a brush at a side opposed to the moving blades.
  • FIG. 8 yet another embodiment of the present invention is described below by using FIG. 8 .
  • the present embodiment applies the invention to a turbine stage which, as shown in FIG. 8 , includes: a blade section constituted by stator blades 1 formed integrally with a root 6 and a cover 9 (member for coupling an inner circumferential side of the stator blades), and by moving blades 10 likewise formed integrally with a root 18 and a cover 19 ; and a coupling structure.
  • a drum-type rotor is used as a rotor 15 .
  • a structure 43 for bending in a rotational direction of the moving blades a flow that blows upward between the stator blades and the moving blades is provided on the surface of the cover 9 that is opposed to the moving blades.
  • a more specific shape of the structure 43 is essentially the same as that of the structure 40 shown in FIG. 5 or 6 .
  • such brush seal 42 as shown in FIG. 7 may be used.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US11/836,437 2006-08-31 2007-08-09 Axial turbine Abandoned US20080056895A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2006234853A JP2008057416A (ja) 2006-08-31 2006-08-31 軸流タービン
JP2006-234853 2006-08-31

Publications (1)

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US20080056895A1 true US20080056895A1 (en) 2008-03-06

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US11/836,437 Abandoned US20080056895A1 (en) 2006-08-31 2007-08-09 Axial turbine

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JP (1) JP2008057416A (zh)
KR (1) KR20080020478A (zh)
CN (1) CN101135247A (zh)

Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100193855A1 (en) * 2009-02-03 2010-08-05 Nec Electronics Corporation Non-volatile semiconductor memory device and method of manufacturing same
WO2011029420A1 (de) * 2009-09-10 2011-03-17 Mtu Aero Engines Gmbh Umlenkvorrichtung für einen leckagestrom in einer gasturbine und gasturbine
WO2013001240A1 (fr) * 2011-06-30 2013-01-03 Snecma Joint d'etancheite a labyrinthe pour turbine d'un moteur a turbine a gaz
US20130017081A1 (en) * 2011-07-15 2013-01-17 Flowserve Management Company System for enhanced recovery of tangential energy from an axial pump in a loop reactor
US20130189107A1 (en) * 2012-01-24 2013-07-25 General Electric Company Turbine Packing Deflector
US20130266427A1 (en) * 2012-04-04 2013-10-10 Mtu Aero Engines Gmbh Sealing system for a turbomachine
WO2014085464A1 (en) * 2012-11-29 2014-06-05 Siemens Aktiengesellschaft Turbine blade angel wing with pumping features
US20140205444A1 (en) * 2013-01-21 2014-07-24 General Electric Company Turbomachine having swirl-inhibiting seal
US8979480B2 (en) 2009-01-16 2015-03-17 Kabushiki Kaisha Toshiba Steam turbine
FR3014160A1 (fr) * 2013-11-29 2015-06-05 Snecma Limiteur de debit pour joint a brosse
EP2792852A4 (en) * 2011-12-13 2015-07-22 Mitsubishi Hitachi Power Sys TURBINE
WO2016022138A1 (en) * 2014-08-08 2016-02-11 Siemens Aktiengesellschaft Compressor usable within a gas turbine engine
EP2617942A4 (en) * 2010-09-17 2018-02-28 Mitsubishi Hitachi Power Systems, Ltd. Turbine
US20180149022A1 (en) * 2016-11-30 2018-05-31 General Electric Company Guide vane assembly for a rotary machine and methods of assembling the same
US10458267B2 (en) 2017-09-20 2019-10-29 General Electric Company Seal assembly for counter rotating turbine assembly
US10711629B2 (en) 2017-09-20 2020-07-14 Generl Electric Company Method of clearance control for an interdigitated turbine engine
US10774668B2 (en) 2017-09-20 2020-09-15 General Electric Company Intersage seal assembly for counter rotating turbine
US11053807B2 (en) * 2017-06-12 2021-07-06 Mitsubishi Power, Ltd. Axial flow rotating machine
US11092026B2 (en) 2016-03-25 2021-08-17 Mitsubishi Power, Ltd. Rotary machine
US11428160B2 (en) 2020-12-31 2022-08-30 General Electric Company Gas turbine engine with interdigitated turbine and gear assembly
US20220389825A1 (en) * 2021-06-04 2022-12-08 General Electric Company Turbine engine with a rotor seal assembly
US12006829B1 (en) 2023-02-16 2024-06-11 General Electric Company Seal member support system for a gas turbine engine
US12116896B1 (en) 2023-03-24 2024-10-15 General Electric Company Seal support assembly for a turbine engine

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FR2974841B1 (fr) * 2011-05-04 2013-06-07 Snecma Dispositif d'etancheite pour distributeur de turbine de turbomachine
JP2014020509A (ja) * 2012-07-20 2014-02-03 Toshiba Corp シール装置、軸流タービン、および発電プラント
JP6827346B2 (ja) * 2017-03-13 2021-02-10 三菱重工業株式会社 軸流タービン
CN107131004A (zh) * 2017-07-11 2017-09-05 江苏金通灵流体机械科技股份有限公司 一种轴流径流混流式汽轮机
JP7130575B2 (ja) * 2019-02-28 2022-09-05 三菱重工業株式会社 軸流タービン

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Cited By (39)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8979480B2 (en) 2009-01-16 2015-03-17 Kabushiki Kaisha Toshiba Steam turbine
US20100193855A1 (en) * 2009-02-03 2010-08-05 Nec Electronics Corporation Non-volatile semiconductor memory device and method of manufacturing same
WO2011029420A1 (de) * 2009-09-10 2011-03-17 Mtu Aero Engines Gmbh Umlenkvorrichtung für einen leckagestrom in einer gasturbine und gasturbine
EP2617942A4 (en) * 2010-09-17 2018-02-28 Mitsubishi Hitachi Power Systems, Ltd. Turbine
FR2977274A1 (fr) * 2011-06-30 2013-01-04 Snecma Joint d'etancheite a labyrinthe pour turbine d'un moteur a turbine a gaz
GB2506795A (en) * 2011-06-30 2014-04-09 Snecma Labyrinth seal for gas turbine engine turbine
US9683452B2 (en) 2011-06-30 2017-06-20 Snecma Labyrinth seal for gas turbine engine turbine
GB2506795B (en) * 2011-06-30 2018-05-09 Snecma Labyrinth seal for gas turbine engine turbine
WO2013001240A1 (fr) * 2011-06-30 2013-01-03 Snecma Joint d'etancheite a labyrinthe pour turbine d'un moteur a turbine a gaz
US20130017081A1 (en) * 2011-07-15 2013-01-17 Flowserve Management Company System for enhanced recovery of tangential energy from an axial pump in a loop reactor
US10006292B2 (en) 2011-12-13 2018-06-26 Mitsubishi Hitachi Power Systems, Ltd. Turbine
EP2792852A4 (en) * 2011-12-13 2015-07-22 Mitsubishi Hitachi Power Sys TURBINE
US20130189107A1 (en) * 2012-01-24 2013-07-25 General Electric Company Turbine Packing Deflector
EP2620595A1 (en) * 2012-01-24 2013-07-31 General Electric Company Turbine packing deflector
US20130266427A1 (en) * 2012-04-04 2013-10-10 Mtu Aero Engines Gmbh Sealing system for a turbomachine
WO2014085464A1 (en) * 2012-11-29 2014-06-05 Siemens Aktiengesellschaft Turbine blade angel wing with pumping features
US9394800B2 (en) * 2013-01-21 2016-07-19 General Electric Company Turbomachine having swirl-inhibiting seal
US20140205444A1 (en) * 2013-01-21 2014-07-24 General Electric Company Turbomachine having swirl-inhibiting seal
FR3014160A1 (fr) * 2013-11-29 2015-06-05 Snecma Limiteur de debit pour joint a brosse
US10393132B2 (en) 2014-08-08 2019-08-27 Siemens Aktiengesellschaft Compressor usable within a gas turbine engine
WO2016022138A1 (en) * 2014-08-08 2016-02-11 Siemens Aktiengesellschaft Compressor usable within a gas turbine engine
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KR20080020478A (ko) 2008-03-05
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