EP2816199B1 - Commande d'instabilités de faible débit volumétrique dans des turbines à vapeur - Google Patents

Commande d'instabilités de faible débit volumétrique dans des turbines à vapeur Download PDF

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Publication number
EP2816199B1
EP2816199B1 EP14170721.6A EP14170721A EP2816199B1 EP 2816199 B1 EP2816199 B1 EP 2816199B1 EP 14170721 A EP14170721 A EP 14170721A EP 2816199 B1 EP2816199 B1 EP 2816199B1
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EP
European Patent Office
Prior art keywords
passages
configuration
flow
rotor blades
vane carrier
Prior art date
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EP14170721.6A
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German (de)
English (en)
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EP2816199A3 (fr
EP2816199A2 (fr
Inventor
Brian Robert Haller
Timothy Stephen Rice
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General Electric Technology GmbH
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General Electric Technology GmbH
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Priority to EP14170721.6A priority Critical patent/EP2816199B1/fr
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    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/10—Anti- vibration means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/10—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using sealing fluid, e.g. steam
    • 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
    • F01D19/00—Starting of machines or engines; Regulating, controlling, or safety means in connection therewith
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/003—Arrangements for testing or measuring
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/04—Antivibration arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/04—Antivibration arrangements
    • F01D25/06—Antivibration arrangements for preventing blade vibration
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • 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
    • 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
    • F01D5/16—Form or construction for counteracting blade vibration
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector

Definitions

  • the present invention relates to a configuration of the last stage in a steam turbine for controlling rotating flow instabilities in the last stage rotor blades when the steam turbine operates at low volumetric flow conditions, particularly during starting and low load conditions.
  • Stalling is a known phenomenon based on the sudden decrease of the load exerted onto a profile subjected to a flow: in steam turbines, the stalling phenomenon induces rotating flow instabilities in the rotor blades, particularly in the last stage rotor blades.
  • the flow structure In steam turbines, during starting and low load conditions (up to around 10% of the design mass flow), the flow structure is very disorderly, particularly in the low pressure stage of the steam turbine: this flow is centrifuged radially outwards in the rotor blades, the flow being centrifuged radially inwards in the stator blades.
  • this flow is centrifuged radially outwards in the rotor blades, the flow being centrifuged radially inwards in the stator blades.
  • At low load conditions there is high flow incidence onto the last stage rotor blades, which can cause flow separation from the rotor blades surface and flow instabilities, these instabilities are commonly found to rotate at about one half of the blade rotational speed.
  • the flow field also contains large toroidal vortex structures are set up. These rotating instabilities can couple with the natural frequency of the rotor blades and produce undesirable vibration effects.
  • a solution to windage at low load conditions includes a plurality of nozzle stages located between the bucket stages, a circumferentially extending groove, with the groove located upstream of one of the bucket stages and between that bucket stage and an adjacent nozzle stage, a circumferentially extending extraction chamber, and at least one first bore extending from the groove to the extraction chamber.
  • the diaphragm assembly also includes at least one second bore extending from the extraction chamber through an outer surface of the diaphragm assembly. This permits cold steam to be delivered into the tip recirculation zone of the last stage blade to reduce windage heating conditions during startup.
  • JPH04308301 A discloses another prior art steam turbine configuration.
  • the invention is oriented towards solving these problems.
  • the invention as herein claimed relates to a configuration for controlling flow instabilities of a last stage of a steam turbine, as set forth in claim 1. Further embodiments of the invention as herein claimed are set forth in the dependent claims.
  • the passages are shaped circumferentially in order to increase the circumferential coverage of each passage.
  • the fluid blown through the passages into the rotor blades is such that the swirl injection angle incident on the rotor blades forms an angle from zero to -90 degrees.
  • the positive angle being taken in the direction of the turbine rotor rotation, with zero degrees being axial, wherein in the axial/radial plane the jet is directed downwards from the outer flow boundary.
  • the present invention relates to a configuration 10 for controlling flow instabilities in the last stage rotor blades 2 of a steam turbine when the turbine operates at low volumetric conditions, particularly during starting and low load conditions.
  • the configuration 10 is such that a plurality of passages 20 are located in the vane carrier 1 of the last stage of the steam turbine, these passages 20 being located at specific positions at the circumference of the vane carrier 1. Through these passages 20, a fluid is blown onto the rotor blades 2.
  • the number of passages 20 and their specific positions are defined in such a way that the fluid blown through the passages 20 is directed towards the rotor blades 2 avoiding rotating stability problems in these last stage rotor blades 2 that produce undesired vibration effects on them.
  • Figure 1 shows the flow pattern in the last stage low pressure vane carrier 1 during starting and low load conditions (up to around 10% of the design mass flow), showing that the flow structure is very disorderly.
  • the through flow in the vane carrier 1 adopts a wavy shape, as shown in Figure 1 , existing large toroidal vortex structures 30: the last stage low pressure vane carrier 1 actually acts as a radial pump and there is net energy input to the stage.
  • a solution is to use water sprays injected in the exhaust diffuser to cool the exhaust casing vane carrier walls and last stage blades, but this solution has not been found to be reliable.
  • the purpose of the configuration 10 of the invention is to design the passages 20 to eliminate the rotating flow instabilities in the last stage rotor blades 2 during starting and low load conditions of the steam turbine.
  • the positions of the passages 20 upstream of the last stage rotor blade 2 is such that the injection flow is directed through the last stage vane carrier 1 to approximately 80% last stage blade height, as measured from the blade platform to the tip, so as to blow into the torodial vortex 30 typically formed upstream of the rotor blade 2 tip region.
  • Figs. 4a , 4b and 4c shows a series of tests that demonstrate the surprising effect that a negative injection angle results in a more stable and steady separated flow, decoupled from resonance can be seen.
  • the tests were carried out in a one third scale model low pressure steam turbine over a range of mass flow rates and condenser pressure. During the tests measurement were made of last stage blade stress using a strain gauge located on the surface of the last stage blade. Results of these measurements are shown as lines representation vibrational amplitude in Figs. 4a , 4b and 4c .
  • An additional dynamic pressure sensor acting as a microphone, was additional located in the flow to detect the formation of the rotating events that can give rise to blade vibration. From the pressure signal it was possible to determine frequency, which is transformable into fractional speed, and represent this as spheres in Figs 4a , 4b and 4c . The amplitude from the pressure sensor was then used in Figs. 4a , 4b and 4c to define the size of the grey spheres on each of the graphs.
  • the fluid injected from the passages 20, which preferably is steam, is such that the injection angle incident on the rotor blades 2 forms an angle from zero to -90 degrees, the negative angle being taken in the direction counter to the turbine rotor rotation.
  • the preferred injection angle range is -45 to -75 degrees, the most preferred injection angle being -60 degrees.
  • the flow injected from the passages 20 is up to 10% of the mainstream flow.
  • the number of passages 20 relative to the number of rotor blades 2 is set to provide sufficient stabilization of the rotating events. In the case of the test results given, 12 passages were used. Other embodiments of this invention may use a different number of passages to obtain sufficient stabilization.
  • the passages are equally spaced around the circumference. In an alternative embodiment the passages are unevenly spaced around the circumference for enhanced performance or for practical considerations.
  • the following parameters influence the performance of the configuration 10 of the invention maintaining the trajectory length of the fluid blown from the passages 20 as small as possible; maintaining the velocity of the fluid injected as high as possible; and maximizing the circumferential extent of the passages 20 in the vane carrier 1.
  • the passages 20 are circumferentially shaped to increase the circumferential coverage in the vane carrier 1 as shown in Fig. 2 .

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Control Of Turbines (AREA)

Claims (11)

  1. Configuration (10) pour réguler des instabilités de flux d'un dernier étage d'une turbine à vapeur où des pales de rotor (2) tournent encerclées par un support d'aube (1), dans laquelle une pluralité de passages (20) sont situés dans le support d'aube (1), de telle sorte qu'un fluide est soufflé à travers ces passages (20) en amont des pales de rotor (2) et agencés pour former un flux qui arrive sur les pales de rotor (2), caractérisé en ce que ce flux arrive sur les pales de rotor avec un angle d'injection négatif entre zéro et -90 degrés dans une direction contraire à la rotation des pales de rotor (2), zéro degré étant axial, caractérisé par les passages (20) configurés et agencés pour souffler un fluide en direction d'un point qui est à 80 % d'une hauteur de la pale de rotor de dernier étage (2) pris à partir d'une base jusqu'à une extrémité de la pale de rotor (2).
  2. Configuration (10) selon la revendication 1, dans laquelle la pluralité de passages (20) sont espacés de façon circonférentiellement uniforme dans le support d'aube (1).
  3. Configuration (10) selon la revendication 2, dans laquelle le nombre de passages (20) espacés de façon circonférentiellement uniforme dans le support d'aube (1) est de huit.
  4. Configuration (10) selon la revendication 2, dans laquelle le nombre de passages (20) espacés de façon circonférentiellement uniforme dans le support d'aube (1) est de douze.
  5. Configuration (10) selon la revendication 1, dans laquelle les passages (20) sont circonférentiellement profilés.
  6. Configuration (10) selon la revendication 1, dans laquelle l'angle d'injection est dans une plage de -45 à -75 degrés.
  7. Configuration (10) selon la revendication 1, dans laquelle l'angle d'injection est d'environ -60 degrés.
  8. Configuration (10) selon la revendication 1 dans laquelle le flux injecté à travers les passages (20) va jusqu'à 10 % du flux de courant principal circulant à travers les pales de rotor (2) et le support d'aube (1).
  9. Configuration (10) selon la revendication 1, dans laquelle le fluide soufflé à travers les passages (20) est de la vapeur.
  10. Configuration (10) selon une quelconque revendication précédente, dans laquelle dans un plan axial/radial, le flux est dirigé vers le bas à partir d'une limite de flux externe.
  11. Turbine à vapeur comprenant une configuration de dernier étage (10) selon l'une quelconque des revendications 1 à 10.
EP14170721.6A 2013-06-17 2014-06-02 Commande d'instabilités de faible débit volumétrique dans des turbines à vapeur Active EP2816199B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP14170721.6A EP2816199B1 (fr) 2013-06-17 2014-06-02 Commande d'instabilités de faible débit volumétrique dans des turbines à vapeur

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP13172223 2013-06-17
EP14170721.6A EP2816199B1 (fr) 2013-06-17 2014-06-02 Commande d'instabilités de faible débit volumétrique dans des turbines à vapeur

Publications (3)

Publication Number Publication Date
EP2816199A2 EP2816199A2 (fr) 2014-12-24
EP2816199A3 EP2816199A3 (fr) 2015-03-04
EP2816199B1 true EP2816199B1 (fr) 2021-09-01

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US (1) US20140369815A1 (fr)
EP (1) EP2816199B1 (fr)
JP (1) JP6239447B2 (fr)
CN (1) CN104234757B (fr)
IN (1) IN2014DE01617A (fr)

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WO2016094409A1 (fr) * 2014-12-09 2016-06-16 Villarreal Anna Procédés et dispositifs de surveillance de la santé féminine
US10662802B2 (en) 2018-01-02 2020-05-26 General Electric Company Controlled flow guides for turbines
JP6916755B2 (ja) * 2018-03-09 2021-08-11 三菱重工業株式会社 回転機械
WO2019236062A1 (fr) 2018-06-05 2019-12-12 Siemens Energy, Inc. Agencement d'un dernier étage avec des bloqueurs de flux et procédé correspondant pour supprimer des cellules d'instabilité de flux rotatives
EP3816397B1 (fr) * 2019-10-31 2023-05-10 General Electric Company Aubes de turbines avec écoulement contrôlé
CN112699505B (zh) * 2020-12-28 2022-11-25 哈尔滨汽轮机厂有限责任公司 一种用于核电机组低压缸长叶片的动应力有限元计算方法
CN113153453B (zh) * 2021-03-02 2022-10-11 哈尔滨工业大学 汽轮机末级叶片容积流量估计方法、颤振预警方法及系统和装置

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US20130017066A1 (en) * 2011-07-14 2013-01-17 Honeywell International Inc. Compressors with integrated secondary air flow systems

Also Published As

Publication number Publication date
IN2014DE01617A (fr) 2015-06-19
CN104234757A (zh) 2014-12-24
CN104234757B (zh) 2016-10-05
US20140369815A1 (en) 2014-12-18
EP2816199A3 (fr) 2015-03-04
JP6239447B2 (ja) 2017-11-29
JP2015001228A (ja) 2015-01-05
EP2816199A2 (fr) 2014-12-24

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