EP3358134B1 - Turbine à vapeur avec aube rotorique - Google Patents

Turbine à vapeur avec aube rotorique Download PDF

Info

Publication number
EP3358134B1
EP3358134B1 EP17154386.1A EP17154386A EP3358134B1 EP 3358134 B1 EP3358134 B1 EP 3358134B1 EP 17154386 A EP17154386 A EP 17154386A EP 3358134 B1 EP3358134 B1 EP 3358134B1
Authority
EP
European Patent Office
Prior art keywords
airfoil
steam turbine
steam
axial width
turbine
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.)
Active
Application number
EP17154386.1A
Other languages
German (de)
English (en)
Other versions
EP3358134A1 (fr
Inventor
Brian Robert Haller
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Priority to EP17154386.1A priority Critical patent/EP3358134B1/fr
Priority to US16/483,201 priority patent/US20200232327A1/en
Priority to KR1020197022833A priority patent/KR102496125B1/ko
Priority to CN201880010720.2A priority patent/CN110268136A/zh
Priority to JP2019541265A priority patent/JP7106552B2/ja
Priority to PCT/US2018/016330 priority patent/WO2018144658A1/fr
Publication of EP3358134A1 publication Critical patent/EP3358134A1/fr
Application granted granted Critical
Publication of EP3358134B1 publication Critical patent/EP3358134B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

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
    • 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
    • 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
    • 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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • 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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/301—Cross-sectional characteristics
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade

Definitions

  • the present application and the resultant patent relate generally to axial flow turbines of any type and more particularly relate to a steam turbine including a number of rotor blades.
  • steam turbines and the like may have a defined steam path that includes a steam inlet, a turbine section, and a steam outlet.
  • Steam leakage either out of the steam path, or into the steam path from an area of higher pressure to an area of lower pressure, may adversely affect the operating efficiency of the steam turbine.
  • steam path leakage in the steam turbine between a rotating shaft and a circumferentially surrounding turbine casing may lower the overall efficiency of the steam turbine
  • Steam may generally flow through a number of turbine stages typically disposed in series through first-stage guide vanes and blades (or nozzles and buckets) and subsequently through guide vanes and blades of later stages of the turbine.
  • the guide vanes may direct the steam toward the respective blades, causing the blades to rotate and drive a load, such as an electrical generator and the like.
  • the steam may be contained by circumferential shrouds surrounding the blades, which also may aid in directing the steam or combustion gases along the path.
  • the turbine guide vanes, blades, and shrouds may be subjected to high temperatures resulting from the steam, which may result in the formation of hot spots and high thermal stresses in these components. Because the efficiency of a steam turbine is dependent on its operating temperatures, there is an ongoing demand for components positioned along the steam or hot gas path to be capable of withstanding increasingly higher temperatures without failure or decrease in useful life.
  • US 2010/284801 A1 discloses a blade of a turbomachine, especially of a high pressure steam turbine, which is characterized in that the chord length in the middle region of the blade airfoil is shorter than the chord lengths in the tip-side region or root-side region of the blade airfoil.
  • US 2008/206065 A1 discloses a turbine bucket for a low-pressure turbine final stage that can make centrifugal stress acting on a blade or dovetail not greater than a limit value of a material and that is provided with a shape of a blade root that can ensure a steam passage even if the blade is increased in length in order to increase an exhaust area.
  • US 5 277 549 A discloses a controlled reaction blade for use in the second from last stage of a low pressure steam turbine that provides high performance by use of an airfoil shape that maintains the steam velocity at relatively low values, ensures that the steam does not decelerate too rapidly as it expands toward the trailing edge, and that controls the reaction so as to produce a radial reaction distribution that tends to minimize secondary flow at the base of the airfoil and steam leakage at the tip. It specifies a great number of various parameters for different portions of such an airfoil shape. It also describes that a back surface deflection angle, also called suction surface turning angle, is maintained below 16° at the base of the airfoil and below 9° at the tip to ensure that boundary layer separation does not occur in the trailing edge region.
  • a back surface deflection angle also called suction surface turning angle
  • Certain turbine blades may be formed with an airfoil geometry.
  • the airfoils may be attached to tips and roots, where the roots are used to couple an airfoil to a disc or drum.
  • the turbine airfoil geometry and dimensions may result in certain profile losses, secondary losses, leakage losses, mixing losses, etc. that may adversely affect efficiency and/or performance of a steam turbine.
  • the present invention provides a steam turbine including a number of rotor blades as claimed in independent claim 1. Especially preferred embodiments of the present invention are subject-matter of the dependent claims.
  • FIG. 1 shows a schematic diagram of an example of a steam turbine 10.
  • the steam turbine 10 includes a high pressure section 15 and an intermediate pressure section 20.
  • An outer shell or casing 25 may be divided axially into an upper half section 30 and a lower half section 35.
  • a central section 40 of the casing 25 may include a high pressure steam inlet 45 and an intermediate pressure steam inlet 50.
  • the high pressure section 15 and the intermediate pressure section 20 may be arranged about a rotor or disc 55.
  • the disc 55 may be supported by a number of bearings 60.
  • a steam seal unit 65 may be located inboard of each of the bearings 60.
  • An annular section divider 70 may extend radially inward from the central section 40 towards the disc.
  • the divider 70 may include a number of packing casings 75. Other components and other configurations may be used.
  • the high pressure steam inlet 45 receives high pressure steam from a steam source.
  • the steam may be routed through the high pressure section 15 such that work is extracted from the steam by rotation of the disc 55.
  • the steam exits the high pressure section 15 and then may be returned to the steam source for reheating.
  • the reheated steam then may be rerouted to the intermediate pressure section inlet 50.
  • the steam may be returned to the intermediate pressure section 20 at a reduced pressure as compared to the steam entering the high pressure section 15 but at a temperature that is approximately equal to the temperature of the steam entering the high pressure section 15.
  • an operating pressure within the high pressure section 15 may be higher than an operating pressure within the intermediary section 20 such that the steam within the high pressure section 15 tends to flow towards the intermediate section 20 through leakage paths that may develop between the high pressure 15 and the intermediate pressure section 20.
  • One such leakage path may extend through the packing casing 75 about the disc shaft 55. Other leaks may develop across the steam seal unit 65 and elsewhere.
  • FIG. 2 shows a schematic diagram of a portion of the steam turbine turbine 10 including a number of stages 52 positioned in a steam or hot gas path 54 of the steam turbine 10.
  • a first stage 56 may include a number of circumferentially-spaced first-stage guide vanes 58 and a number of circumferentially-spaced first-stage rotor blades 60.
  • the first stage 56 also may include a first-stage shroud 62 extending circumferentially and surrounding the first-stage rotor blades 60.
  • the first-stage shroud 62 may include a number of shroud segments positioned adjacent one another in an annular arrangement.
  • a second stage 64 may include a number of second-stage guide vanes 66, a number of second-stage rotor blades 68, and a second-stage shroud 70 surrounding the second-stage rotor blades 68. Any number of stages and corresponding guide vanes and rotor blades may be included. Other embodiments may have different configurations.
  • FIG. 3 depicts a turbine rotor blade or bucket 80 as may be used in one of the stages 52 of the turbine 10.
  • the bucket 80 may be used in the second stage 64 or a later stage of the turbine 10.
  • the turbine bucket 80 may include an airfoil 82, a dovetail or root 84, and a platform 86 disposed between the airfoil 82 and the root 84.
  • a number of the rotor blades or buckets 80 may be arranged in a circumferential array within the stage 52 of the turbine 10. In this manner, the airfoil 82 of each bucket 80 may extend radially with respect to a central axis of the turbine 10, while the platform 86 of each bucket 80 extends circumferentially with respect to the central axis of the turbine 10.
  • the airfoil 82 may extend radially outward from the root 84 to an optional tip shroud 88 positioned about a tip end 90 of the bucket 80.
  • the tip shroud 88 may be integrally formed with the airfoil 82.
  • the root 84 may extend radially inward from the platform 86 to a root end 92 of the bucket 80, such that the platform 86 generally defines an interface between the airfoil 82 and the root 84.
  • the platform 86 may be formed so as to extend generally parallel to the central axis of the turbine 10 during operation thereof.
  • the root 84 may be formed to define a root structure, such as a dovetail, configured to secure the bucket 80 to a turbine disc or drum of the turbine 10.
  • the flow of steam or combustion gases 35 travels along the steam or hot gas path 54 and over the platform 86, which along with an outer circumference of the turbine disc forms the radially inner boundary of the steam or hot gas path 54. Accordingly, the flow of steam or combustion gases 35 is directed against the airfoil 82 of the bucket 80, and thus the surfaces of the airfoil 82 are subjected to very high temperatures.
  • the steam turbine 100 may include a first guide vane 120 for a first stage, and a first rotor blade 130 for the first stage.
  • the first rotor blade 130 may be positioned adjacent to the first guide vane 120.
  • the first guide vane 120 and the first rotor blade 130 may be coupled to a disc or drum 110.
  • the guide vanes of the steam turbine may be guide vanes and the rotor blades may be rotor blades.
  • the steam turbine 100 may include a second guide vane 140 for a second stage, and a second rotor blade 150 for the second stage.
  • the second guide vane 140 may be a guide vane and the second rotor blade 150 may be a rotor blade. Any number of stages and/or guide vanes and rotor blades may be included.
  • One or more of the rotor blades may include a tip, an airfoil, and a root.
  • the root may be configured to couple the rotor blade to the disc 110.
  • the airfoil may be positioned between the root and the tip.
  • a tip shroud may be coupled to the tip.
  • the airfoil of the first rotor blade 130 may have a bowed configuration 132. Specifically, the airfoil of the first rotor blade 130 may have a reduced axial width about a midsection of the first rotor blade 130. As illustrated in FIG. 4 , the airfoil of the first rotor blade 130 includes a top width 134, a middle width 136, and a bottom width 138. The widths are axial widths.
  • the top width 134 is an axial width of a top portion of the first rotor blade 130.
  • the top width 134 may be a width of a portion of the first rotor blade 130, or more specifically, the airfoil, that is radially outward from the disc 110.
  • the middle width 136 may be an axial width of the first rotor blade 130 or the blade that is determined or measured about a middle portion of the airfoil of the first rotor blade 130.
  • the bottom width 138 may be an axial width of the airfoil or the first rotor blade 130 at a bottom portion, which may be adjacent to the disc or drum 110.
  • the second rotor blade 150 may also have an axial width that varies at different distances measured from the root of the second rotor blade 150 or the turbine disc.
  • the second rotor blade 150 may have a top axial width 152, a middle axial width 154, and a bottom axial width 156.
  • the bottom axial width 156 may be an axial width of the second rotor blade 150 that is measured a first radial distance 158 from the disc 110.
  • the middle axial width 154 may be an axial width of the second rotor blade 150 that is measured a second radial distance 160 from the disc 110.
  • the second radial distance 160 may be greater than the first radial distance 158.
  • the top axial width 152 may be an axial width of the second rotor blade 150 that is measured a third radial distance 162 from the disc 110.
  • the third radial distance 162 may be greater than the first radial distance 158 and the second radial distance 160.
  • the middle axial width 154 of the second rotor blade 150 may be reduced relative to the top axial width 152 and the bottom axial width 156, so as to result in reduced profile losses.
  • the second rotor blade 150 may have a height that is greater than a height of the first rotor blade 130.
  • the middle width of one or more, or all, of the rotor blades in the steam turbine 100 is less than the respective top widths and the bottom widths.
  • the rotor blades may therefore have a bowed configuration.
  • the middle widths of the rotor blades in the steam turbine 100 may be dimensioned so as to reduce profile losses. For example, dimensioning the middle width to be less than the top and/or bottom widths may reduce profile losses in the steam turbine 100.
  • the bottom width of the respective rotor blades may be greater than the top widths.
  • the rotor blades may therefore be configured to accelerate guide vane wake and reduce mixing losses in the steam turbine 100.
  • steam turbines may include multiple stages with respective pairs of guide vanes and rotor blades that correspond to respective turbine stages.
  • an blade portion 164 of a rotor blade as described herein is depicted in perspective view.
  • the blade portion 164 may have an airfoil geometry 162, with a bowed configuration 160 at a trailing edge.
  • a bottom portion 166 of the blade portion 164 may have a different center of gravity than top or middle portions of the blade portion 164.
  • the rotor blade may have a bowed stack configuration 160, where the tip, airfoil, and root are stacked with offset centers-of-gravity. Specifically, a first center of gravity of the tip of the rotor blade may be offset from a second center of gravity of the airfoil. The second center of gravity of the airfoil may be offset from a third center of gravity of the root.
  • the bowed trailing edge and/or the opening/pitch distribution of the airfoil may generate optimized controlled flow vortex distribution as gas passes over the rotor blade.
  • FIG. 5 further illustrates the airfoil in a top perspective view 170, a front view 180, and a side view 190, which illustrates the bowed midsection 192 of the airfoil.
  • FIG. 6 schematically depicts one example embodiment of a portion of a turbine 200.
  • the turbine 200 includes a number of rotor blades 202 positioned adjacent to one another to form a stage.
  • the rotor blades 202 may form the last stage of the turbine 200.
  • Any number of rotor blades 202 may be used herein to form any stage of the turbine 200.
  • the rotor blades 202 may form a first stage, a last stage, or any stage there between.
  • the rotor blades 202 may be attached to a disc and circumferentially spaced apart from one another.
  • Each of the rotor blades 202 includes a leading edge 208, a trailing edge 210, a pressure side 212, and a suction side 214.
  • a passage 216 is formed between adjacent rotor blades 202.
  • the passage 216 includes a throat area 218.
  • the throat area 218 is the shortest distance from the trailing edge 210 to the suction side 214 of adjacent blades 202.
  • the rotor blades may have an ultra-high back surface deflection. According to the invention, the back surface deflection is greater than a threshold value of 10 degrees. In some embodiments not forming part of the invention the threshold value may be between about 5 degrees and about 25 degrees. Preferably, in accordance with embodiments of the invention, the threshold value may be between 10 degrees and 25 degrees.
  • FIG. 6 further schematically illustrates mean section differences between a rotor blade as described herein, and another rotor blade (shown in dashed lines).
  • the differences in geometry are indicated by the change in position of the respective suction sides 220, 222 and pressure sides 228, 230, as well as the separation 226 between the leading edges and separation 224 between the trailing edges.
  • FIG. 6 Tip section differences between a rotor blade as described herein, and another rotor blade (shown in dashed lines) are also illustrated in FIG. 6 . As shown, differences in positioning of the suction sides 240, 242, and 246, 248, as well as differences in separation (which may be minimal), may result in increased strength and reduced losses.
  • FIG. 6 further illustrates an example back surface deflection, represented by ⁇ , which may indicate uncovered flow turning on the suction surface, and may be an angle between a tangent to the suction surface at the throat point and a tangent drawn at the suction surface trailing edge circle blend point.
  • ⁇ back surface deflection
  • a method of using the rotor blades described herein may include the steps of providing a root for a rotor blade in a steam turbine, coupling an airfoil for the rotor blade to the root, where the airfoil has a top width, a middle width, and a bottom width, and where the middle width is less than the top width and the bottom width.
  • the method may include coupling a tip to the airfoil.
  • stage efficiency gains for steam turbines may be about 0.20%, with reduced profile loss at the rotor blade, reduced secondary loss, and improved positive incidence.
  • Certain embodiments may be used to retrofit existing steam turbines.
  • Certain embodiments may provide reduced weight rotor blades with consistent mechanical reliability, while maintaining costs. The rotor blade may therefore improve stage efficiency, while maintaining or improving mechanical reliability and without increasing cost or complexity of the steam turbine. Emissions may be reduced.

Claims (10)

  1. Turbine à vapeur (10) incluant une section à haute pression (15) et une section à pression intermédiaire (20), au moins une de la section à haute pression (15) et de la section à pression intermédiaire (20) incluant un certain nombre d'aubes de rotor (80, 130, 150, 202), chacune des aubes de rotor (80, 130, 150, 202) incluant un bord d'attaque (208), un bord de fuite (210), un côté pression (212) et un côté aspiration (214), un passage (216) formé entre des aubes de rotor adjacentes (80, 130, 150, 202), le passage (216) incluant une zone de gorge (218) qui est la distance la plus courte depuis le bord de fuite (210) jusqu'au côté aspiration (214) d'aubes adjacentes (202), chacune des aubes de rotor (80, 130, 150, 202) comprenant en outre :
    une pointe ;
    une surface portante (82) adjacente à la pointe, la surface portante (82) comprenant une largeur axiale supérieure (134, 152), une largeur axiale centrale (136, 154) et une largeur axiale inférieure (138, 156), dans laquelle la largeur axiale centrale (136, 154) est inférieure à la largeur axiale supérieure (134, 152) et à la largeur axiale inférieure (138, 156) ; et
    une emplanture (84) adjacente à la surface portante (82) ;
    caractérisée en ce que la surface portante (82) a une déviation de surface arrière (δ) qui est un angle entre une tangente au côté d'aspiration (214) au niveau de la zone de gorge (218) et une tangente dessinée au niveau du point de juxtaposition du cercle de bord de fuite (219) du côté d'aspiration (214), dans laquelle la déviation de surface arrière (δ) est supérieure à 10 degrés.
  2. Turbine à vapeur (10) selon la revendication 1, dans laquelle la déviation de surface arrière (δ) de la surface portante (82) est comprise entre 10 degrés et 25 degrés.
  3. Turbine à vapeur (10) selon la revendication 1, dans laquelle la surface portante (82) comprend une configuration de pile arquée (132).
  4. Turbine à vapeur (10) selon une quelconque revendication précédente, dans laquelle un premier centre de gravité de la surface portante (82) est décalé d'un deuxième centre de gravité de l'emplanture (84) à la fois dans la direction axiale et dans la direction circonférentielle lorsqu'il est vu dans une direction radiale.
  5. Turbine à vapeur (10) selon la revendication 4, dans laquelle le premier centre de gravité est décalé d'un troisième centre de gravité de la pointe à la fois dans la direction axiale et dans la direction circonférentielle lorsqu'il est vu dans la direction radiale.
  6. Turbine à vapeur (10) selon une quelconque revendication précédente, dans laquelle le bord de fuite (210) de la surface portante (82) comprend une configuration arquée.
  7. Turbine à vapeur (10) selon une quelconque revendication précédente, dans laquelle la largeur axiale inférieure (138, 156) est supérieure à la largeur axiale supérieure (134, 152).
  8. Turbine à vapeur (10) selon une quelconque revendication précédente, comprenant en outre un carénage de pointe (88) accouplé à la pointe et dans laquelle la largeur axiale supérieure (134, 152) est adjacente au carénage de pointe (88).
  9. Turbine à vapeur (10) selon une quelconque revendication précédente, dans laquelle l'emplanture (84) est accouplée à un disque (110) et dans laquelle la largeur axiale inférieure (138, 156) est adjacente à l'emplanture (84).
  10. Turbine à vapeur (10) selon une quelconque revendication précédente, dans laquelle le nombre d'aubes de rotor d'aubes de rotor (80, 130, 150, 202) est positionné adjacent à un certain nombre d'aubes directrices (120, 140).
EP17154386.1A 2017-02-02 2017-02-02 Turbine à vapeur avec aube rotorique Active EP3358134B1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP17154386.1A EP3358134B1 (fr) 2017-02-02 2017-02-02 Turbine à vapeur avec aube rotorique
US16/483,201 US20200232327A1 (en) 2017-02-02 2018-02-01 Controlled flow runners for turbines
KR1020197022833A KR102496125B1 (ko) 2017-02-02 2018-02-01 터빈을 위한 제어식 유동 러너
CN201880010720.2A CN110268136A (zh) 2017-02-02 2018-02-01 用于涡轮的受控流式转轮
JP2019541265A JP7106552B2 (ja) 2017-02-02 2018-02-01 背面のそりを有する翼形部（８２）を備える蒸気タービン
PCT/US2018/016330 WO2018144658A1 (fr) 2017-02-02 2018-02-01 Roues mobiles à écoulement contrôlé pour turbines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP17154386.1A EP3358134B1 (fr) 2017-02-02 2017-02-02 Turbine à vapeur avec aube rotorique

Publications (2)

Publication Number Publication Date
EP3358134A1 EP3358134A1 (fr) 2018-08-08
EP3358134B1 true EP3358134B1 (fr) 2021-07-14

Family

ID=57995034

Family Applications (1)

Application Number Title Priority Date Filing Date
EP17154386.1A Active EP3358134B1 (fr) 2017-02-02 2017-02-02 Turbine à vapeur avec aube rotorique

Country Status (6)

Country Link
US (1) US20200232327A1 (fr)
EP (1) EP3358134B1 (fr)
JP (1) JP7106552B2 (fr)
KR (1) KR102496125B1 (fr)
CN (1) CN110268136A (fr)
WO (1) WO2018144658A1 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10808535B2 (en) * 2018-09-27 2020-10-20 General Electric Company Blade structure for turbomachine
US11566530B2 (en) 2019-11-26 2023-01-31 General Electric Company Turbomachine nozzle with an airfoil having a circular trailing edge

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5277549A (en) * 1992-03-16 1994-01-11 Westinghouse Electric Corp. Controlled reaction L-2R steam turbine blade

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2392673A (en) * 1943-08-27 1946-01-08 Gen Electric Elastic fluid turbine
CN1039874A (zh) * 1988-07-28 1990-02-21 四川重庆永荣矿务局 双曲线变截面叶片
JP3912989B2 (ja) * 2001-01-25 2007-05-09 三菱重工業株式会社 ガスタービン
JP2003269109A (ja) 2002-03-18 2003-09-25 Toshiba Corp 蒸気タービン
DE112006002658B4 (de) * 2005-10-11 2021-01-07 General Electric Technology Gmbh Turbomaschinenschaufel
JP4713509B2 (ja) * 2007-01-26 2011-06-29 株式会社日立製作所 タービン動翼
US8602727B2 (en) 2010-07-22 2013-12-10 General Electric Company Turbine nozzle segment having arcuate concave leading edge
US8366397B2 (en) * 2010-08-31 2013-02-05 General Electric Company Airfoil shape for a compressor
US8517688B2 (en) * 2010-09-21 2013-08-27 General Electric Company Rotor assembly for use in turbine engines and methods for assembling same
JP5603800B2 (ja) * 2011-02-22 2014-10-08 株式会社日立製作所 タービン静翼、およびそれを用いた蒸気タービン設備
FR2977908B1 (fr) 2011-07-13 2016-11-25 Snecma Aube de turbomachine
JP5985351B2 (ja) * 2012-10-25 2016-09-06 三菱日立パワーシステムズ株式会社 軸流タービン
JP6012519B2 (ja) * 2013-03-21 2016-10-25 三菱重工業株式会社 タービン、及びこれを備えた回転機械
EP3023585B1 (fr) * 2014-11-21 2017-05-31 General Electric Technology GmbH Agencement de turbine
EP3059394B1 (fr) * 2015-02-18 2019-10-30 Ansaldo Energia Switzerland AG Aube de turbine et ensemble d'aubes de turbine
US10808535B2 (en) 2018-09-27 2020-10-20 General Electric Company Blade structure for turbomachine

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5277549A (en) * 1992-03-16 1994-01-11 Westinghouse Electric Corp. Controlled reaction L-2R steam turbine blade

Also Published As

Publication number Publication date
JP2020506325A (ja) 2020-02-27
KR102496125B1 (ko) 2023-02-03
US20200232327A1 (en) 2020-07-23
CN110268136A (zh) 2019-09-20
EP3358134A1 (fr) 2018-08-08
KR20190107052A (ko) 2019-09-18
WO2018144658A1 (fr) 2018-08-09
JP7106552B2 (ja) 2022-07-26

Similar Documents

Publication Publication Date Title
EP2820279B1 (fr) Aube de turbomachine
EP2199543B1 (fr) Aube de rotor de turbine à gaz et procédé de conception d'une telle aube
US7290986B2 (en) Turbine airfoil with curved squealer tip
EP1965025B1 (fr) Aube de turbine
US9874101B2 (en) Platform with curved edges
US10934849B2 (en) Endwall contouring for a turbomachine
JP2010156335A (ja) 改良型タービン翼プラットフォームの輪郭に関する方法および装置
JP6461382B2 (ja) シュラウド付きタービンブレード
JP2010156338A (ja) タービン翼付け根構成
US20110097205A1 (en) Turbine airfoil-sidewall integration
US20180179901A1 (en) Turbine blade with contoured tip shroud
EP3358134B1 (fr) Turbine à vapeur avec aube rotorique
EP3735517B1 (fr) Guides à écoulement contrôlés pour turbines
US11199095B2 (en) Controlled flow turbine blades
EP3177811B1 (fr) Compresseur d'une turbine à gaz
CN112943383A (zh) 带有具有曲线形后缘的翼片的涡轮机喷嘴
WO2016033465A1 (fr) Éléments de guidage de flux pour carénage d'extrémité d'aube de turbine à gaz
US20210062657A1 (en) Control stage blades for turbines
US8052393B2 (en) Steam turbine rotating blade for a low pressure section of a steam turbine engine
JP2007009761A (ja) 軸流タービン

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION HAS BEEN PUBLISHED

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20190208

RBV Designated contracting states (corrected)

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: EXAMINATION IS IN PROGRESS

17Q First examination report despatched

Effective date: 20190806

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: EXAMINATION IS IN PROGRESS

RIC1 Information provided on ipc code assigned before grant

Ipc: F01D 5/22 20060101ALN20201222BHEP

Ipc: F01D 5/14 20060101AFI20201222BHEP

RIC1 Information provided on ipc code assigned before grant

Ipc: F01D 5/14 20060101AFI20210112BHEP

Ipc: F01D 5/22 20060101ALN20210112BHEP

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: GRANT OF PATENT IS INTENDED

RIC1 Information provided on ipc code assigned before grant

Ipc: F01D 5/14 20060101AFI20210122BHEP

Ipc: F01D 5/22 20060101ALN20210122BHEP

INTG Intention to grant announced

Effective date: 20210223

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602017041973

Country of ref document: DE

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1410807

Country of ref document: AT

Kind code of ref document: T

Effective date: 20210815

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG9D

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20210714

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 1410807

Country of ref document: AT

Kind code of ref document: T

Effective date: 20210714

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210714

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210714

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20211014

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20211115

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210714

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210714

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210714

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210714

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20211014

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210714

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210714

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210714

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20211015

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602017041973

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210714

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210714

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210714

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210714

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210714

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210714

26N No opposition filed

Effective date: 20220419

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210714

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20220228

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220202

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220228

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220202

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220228

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220228

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20230119

Year of fee payment: 7

Ref country code: CZ

Payment date: 20230123

Year of fee payment: 7

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: SE

Payment date: 20230119

Year of fee payment: 7

Ref country code: IT

Payment date: 20230120

Year of fee payment: 7

Ref country code: GB

Payment date: 20230121

Year of fee payment: 7

Ref country code: DE

Payment date: 20230119

Year of fee payment: 7

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20230523

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 602017041973

Country of ref document: DE

Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH, CH

Free format text: FORMER OWNER: GENERAL ELECTRIC COMPANY, SCHENECTADY, NY, US

REG Reference to a national code

Ref country code: GB

Ref legal event code: 732E

Free format text: REGISTERED BETWEEN 20240222 AND 20240228

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20170202

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210714

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210714

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20240123

Year of fee payment: 8

Ref country code: CZ

Payment date: 20240125

Year of fee payment: 8

Ref country code: GB

Payment date: 20240123

Year of fee payment: 8