US20150132114A1 - Axial turbine - Google Patents

Axial turbine Download PDF

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Publication number
US20150132114A1
US20150132114A1 US14/535,362 US201414535362A US2015132114A1 US 20150132114 A1 US20150132114 A1 US 20150132114A1 US 201414535362 A US201414535362 A US 201414535362A US 2015132114 A1 US2015132114 A1 US 2015132114A1
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US
United States
Prior art keywords
rotor
outer ring
guide plate
shroud
diaphragm outer
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
US14/535,362
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English (en)
Inventor
Hisataka FUKUSHIMA
Takanori Shibata
Kiyoshi Segawa
Goingwon Lee
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.)
Mitsubishi Power Ltd
Original Assignee
Mitsubishi Hitachi Power Systems 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 Mitsubishi Hitachi Power Systems Ltd filed Critical Mitsubishi Hitachi Power Systems Ltd
Assigned to MITSUBISHI HITACHI POWER SYSTEMS, LTD. reassignment MITSUBISHI HITACHI POWER SYSTEMS, LTD. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: LEE, GOINGWON, SHIBATA, TAKANORI, SEGAWA, KIYOSHI, Fukushima, Hisataka
Publication of US20150132114A1 publication Critical patent/US20150132114A1/en
Abandoned legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/02—Arrangement of sensing elements
    • F01D17/08—Arrangement of sensing elements responsive to condition of working-fluid, e.g. pressure
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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
    • 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
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/28—Arrangement of seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • 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
    • F05D2250/00—Geometry
    • F05D2250/40—Movement of components
    • F05D2250/41—Movement of components with one degree of freedom
    • F05D2250/411—Movement of components with one degree of freedom in rotation

Definitions

  • the invention relates to an axial turbine such as a gas turbine and a steam turbine for use in an electric power plant, etc.
  • the gas turbine, the steam turbine, etc., for use in the electric power plant, etc. are each broadly classified into three categories on the basis of the flow direction of a working fluid thereof, including an axial turbine with the fluid flowing in the direction of the rotation axis of the turbine, a diagonal turbine with the fluid flowing in such a way as to be diagonally spread from the rotation axis of the turbine, and a radial turbine with the fluid flowing in the radial direction of the turbine.
  • the axial turbine in particular, among these turbines, is suited for use in an electric power plant with a capacity intermediate through large, in magnitude, and the axial turbine is generally in widespread use at a large-sized thermal power plant.
  • stage loss takes a variety of forms, and is broadly classified into (1) a profile loss attributable to a blade profile itself, (2) a secondary flow loss attributable to a flow crossing a passage between blades, (3) a leakage loss due to a working fluid leaking out of the passage between blades, etc.
  • the leakage loss (3) includes (a) a bypass loss caused by a leakage flow passing through a path other than a path for a main stream, thereby preventing effective use of energy held by steam, (b) a mixing loss occurring at the time of a portion of the leakage flow, breaking off a main stream, flowing back into the main stream again, and (c) an incidence loss caused by interference of a portion of the leakage flow, flowing back into the main stream, with downstream cascade of blades. Accordingly, in order to cause reduction in those leakage losses, it becomes important to cause the leakage flow to return to the main stream without a loss, while reducing a quantity of the leakage flow.
  • Patent Literature 1 Japanese Unexamined Patent Application Publication No. 2011-106474
  • Patent Literature 1 Japanese Unexamined Patent Application Publication No. 2011-106474
  • Patent Literature 1 has not disclosed a relationship between an operation state of the turbine and the guide plate, and there is a possibility that the effect of turning the direction of the leakage flow through the use of the guide plate cannot be sufficiently secured depending on the operation state of the turbine.
  • the operation state of the turbine undergoes a change to thereby cause a flow angle of the main stream to change
  • an optimum flow angle suitable for installation of the guide plate is changed, and therefore, a mismatch in flow angle between the leakage flow and the main stream is caused to occur as a result of the installation of the guide plate, so that a possibility of fostering the mixing loss contrary to expectations is conceivable.
  • the present invention provides in its one aspect an axial turbine including a rotatably supported rotor, a bucket fixed to the rotor, a shroud provided at the tip of the bucket, a diaphragm outer ring opposed to the shroud with a gap interposed therebeteen, a radial seal fin provided in such a way as to protrude from the diaphragm outer ring in the radial direction of the rotor in the gap between the diaphragm outer ring and the shroud, an axial seal fin provided in such a way as to protrude from the diaphragm outer ring in the direction of a rotation axis of the rotor in the gap between the shroud and the diaphragm outer ring, a plurality of ribs provided in such a way as to be sandwiched between the diaphragm outer ring and the axial seal fin in the gap between the shroud and the diaphragm outer
  • FIG. 1 is a sectional view schematically showing a part of a steam turbine according to one embodiment of the invention
  • FIG. 2 is a sectional view schematically showing a part of the steam turbine according to the one embodiment of the invention
  • FIG. 3 is a view schematically showing a state between blades, and a state of a leakage flow between the blades, on a blade-tip side of the steam turbine according to the one embodiment of the invention
  • FIG. 4 is a sectional view schematically showing the state of the leakage flow, on the blade-tip side of the steam turbine according to the one embodiment of the invention
  • FIG. 5 is a view schematically showing the state between the blades, and the state of the leakage flow between the blades, on the blade-tip side of the steam turbine according to the one embodiment of the invention
  • FIG. 6 is a view schematically showing a state of the leakage flow, on the downstream side of a bucket tip, inside a cavity of the steam turbine according to the one embodiment of the invention
  • FIG. 7 is a graph showing effects of a deviation angle, that is, a difference in flow angle between the main-stream and the leakage flow, exerted on a mixing loss according to the one embodiment of the invention.
  • FIG. 8 is a graph showing effects of the leakage flow of the steam turbine according to the one embodiment of the invention, exerted on distribution of absolute discharge-angles downstream from a bucket, in the radial-direction of the bucket;
  • FIG. 9 is a graph showing effects of the leakage flow of the steam turbine according to the one embodiment of the invention, exerted on distribution of bucket loss factors downstream from the bucket, in the radial-direction of the bucket;
  • FIG. 10 is a sectional view schematically showing a part of a steam turbine according to the one embodiment of the invention.
  • FIG. 11 is a sectional view schematically showing a part of the steam turbine according to the one embodiment of the invention.
  • FIG. 12 is a plan view schematically showing a part of the steam turbine according to the one embodiment of the invention.
  • FIGS. 1 and 2 each show a stage structure of a steam turbine according to a first embodiment of the invention.
  • a turbine-stage of the steam turbine according to the present embodiment is provided with a rotatably supported rotor 3 , a bucket 5 fixed to the rotor 3 , a shroud 6 provided at the tip of the bucket 5 , a diaphragm outer ring 1 opposed to the shroud 6 with a gap provided therebetween, a radial seal fin 7 provided in such a way as to protrude from the diaphragm outer ring 1 in the radial direction of the rotor 3 in a gap between the shroud 6 and the diaphragm outer ring 1 , an axial seal fin 8 provided in such away as to protrude from the diaphragm outer ring 1 in the direction of a rotation axis of the rotor 3 in a gap between the shroud 6 and the diaphragm outer ring 1 , a plurality of ribs 9 provided in
  • the guide plate 10 is provided such that the position thereof is variable in the circumferential direction of the rotor 3 in response to an operation state of the steam turbine.
  • the guide plate 10 , and the axial seal fin 8 each have a hole penetrating therethrough along the radial direction of the rotor 3 , and the guide plate 10 is linked to the axial seal fin 8 with the use of a guide plate support-member 19 provided inside the respective holes.
  • the hole of the guide plate 10 is provided at a position closer to a side of the guide plate 10 , adjacent to the shroud 6 , than the central part of the guide plate 10 .
  • a face of the guide plate 10 opposed to the rotor 3 , is disposed on a side of the guide plate 10 , inner than a face of the shroud 6 , adjacent to the bucket 5 , along the radial direction of the rotor 3 .
  • a turbine stage of the steam turbine according to the present embodiment is made up of one sheet of the bucket 5 , or plural sheets of the buckets 5 , fixed to the rotor 3 , in the circumferential direction thereof, and one sheet of nozzle 4 , or plural sheets of the nozzles 4 , fixed to the turbine in the circumferential direction thereof, between the diaphragm outer ring 1 and a diaphragm inner ring 2 .
  • the shroud 6 is provided at the tip of the bucket 5 , on the outer periphery side thereof in a rotation radial direction of the turbine.
  • a rotating body in other words, plural sheets of the radial seal fins 7 for the purposes of minimizing a gap between the shroud 6 and a stationary part, that is, the diaphragm outer ring 1 , and suppressing the leakage flow are provided in the direction of the rotation axis of the rotor 3 inside the gap between a casing wall of the shroud 6 provided at the tip of the bucket 5 , on the outer peripheral side of the shroud 6 , and the stationary part opposed to the casing wall of the shroud, that is, the diaphragm outer ring 1 .
  • the axial seal fin 8 is provided between a casing wall of the shroud 6 , on the downstream side thereof, that is, the casing wall of the shroud 6 , on the downstream side of a steam flow and the stationary part opposed to the casing wall of the shroud 6 , that is, the diaphragm outer ring 1 , and a void, the so-called cavity, is formed between the shroud 6 and the stationary part, that is, the diaphragm outer ring 1 , and between the shroud 6 and the radial seal fin 7 provided on the most downstream side, in a seal passage.
  • the axial seal fin 8 is provided with the guide plate 10 for causing the direction of the leakage flow to be turned into the circumferential direction, and the guide plate 10 is installed such that the same can be driven in the circumferential direction of the rotor 3 .
  • a steam main-stream 11 flows out from the nozzle 4 provided on the upstream side of the bucket 5 , in the direction of a steam flow, the majority of the steam main-stream 11 having flowed out flows into the bucket 5 , whereas a portion thereof flows into the seal passage formed between the diaphragm outer ring 1 , as the stationary part, and the shroud 6 , as a rotator. And the portion, as a leakage flow 12 , passes between the plural sheets of the radial seal fins 7 to be subsequently merged with the steam main-stream 11 again downstream from the bucket 5 .
  • the steam turbine causes the steam main-stream 11 having flowed out from the nozzle 4 provided upstream from the bucket 5 to flow into the bucket 5 , causing the rotor 3 with the bucket 5 fixed thereto, together with the bucket 5 , to be rotated, thereby executing power generation through conversion of rotation energy into electric energy via a generator (not shown) connected to an end of the rotor 3 . Accordingly, the leakage flow 12 having passed through the seal passage after circumventing the bucket 5 , as it is, is not converted into the rotation energy of the rotor 3 , and therefore, the leakage flow 12 represents a loss.
  • FIG. 3 shows blade profiles as seen from the tip side of the bucket 5 , and a velocity triangle.
  • a broken line denoted by reference sign 15 indicates a rotational speed.
  • the steam main-stream 11 (not shown) flowing out from the back-edge of the nozzle 4 at a nozzle-outlet absolute velocity 13 flows into the bucket 5 as a nozzle-outlet relative velocity 14 .
  • the steam main-stream 11 is turned in flow angle at the bucket 5 to flow out at a bucket-outlet relative velocity 17 .
  • the flow has been turned into a flow at a bucket-outlet absolute velocity 16 , in a direction close to the axial direction, thereby lowering pressure and temperature to the extent of energy recovered by the bucket 5 , before flowing into the next stage.
  • the leakage flow 12 circumventing the bucket 5 is turned into a contracted flow upon passing between the plural sheets of the radial seal fins 7 (not shown) provided in the axial direction, whereupon total pressure drops and an axial velocity increases, however, the leakage flow 12 passes through the seal passage at a circumferential velocity nearly maintaining a circumferential velocity component at the time of flowing out from the nozzle 4 , owing to the law of conservation of each momentum. More specifically, the leakage flow 12 flows out without being turned in the seal passage, as show in FIG. 3 , so that mismatch between the flow angles will occur upon the leakage flow 12 being merged with the steam main-stream 11 . The mixing loss occurring upon the steam main-stream 11 merging with the leakage flow 12 is fostered due to the mismatch between the flow angles.
  • FIG. 4 shows the state of a leakage flow on the blade-tip side according to the present invention.
  • the plural sheets of the radial seal fins 7 arranged in the direction of the rotation axis of the rotor 3 are provided between the diaphragm outer ring 1 and the shroud 6 provided at the tip of the bucket 5 .
  • the radial seal fins 7 has a sectional shape that is rotationally symmetric with respect to the rotation axis of the rotor 3 , the tip of the radial seal fin 7 being acute wedge-like in shape.
  • a gap is provided between the radial seal fin 7 and the casing wall of the shroud 6 , on the outer peripheral side thereof in order to prevent a rotating part, that is, the shroud 6 from coming into contact with the stationary part, that is, the diaphragm outer ring 1 .
  • the leakage flow 12 upon passing through the gap, undergoes contraction and expansion, whereupon the total pressure drops due to heat diffusion of velocity energy. This contraction and expansion phenomenon acts as resistance to the leakage flow 12 to thereby enable a quantity of the leakage flow 12 to be reduced.
  • the radial seal fins 7 are fixed to the diaphragm outer ring 1 , and the tip of the radial seal fin 7 is directed to a side of the bucket 5 , adjacent to the shroud 6 , however, in contrast, even if the radial seal fins 7 are fixed to the shroud 6 , and the tip of the radial seal fin 7 is directed toward the diaphragm outer ring 1 , the same effect can be obtained.
  • the casing wall of the shroud 6 on the outer peripheral side thereof, is formed in a step-wise shape, the effects of the present invention will be the same even if other shapes including a flat shape are adopted.
  • the axial seal fin 8 is provided on the downstream side of the radial seal fins 7 .
  • the axial seal fin 8 is provided in such a way as to protrude in the direction of the rotation axis of the rotor 3 in the seal passage between the casing wall of the shroud 6 , on the downstream side thereof, and the stationary part, that is, the diaphragm outer ring 1 .
  • the voids, the so-called cavities, are formed by the axial seal fin 8 , together with the shroud 6 , the stationary part, that is, the diaphragm outer ring 1 , and the radial seal fin 7 provided on the most downstream side of the seal passage, and the leakage flows 12 having flowed into the respective cavities generate two pairs of strong recirculation flows 18 .
  • the leakage flow 12 is under the influence of viscosity from the surrounding wall-faces forming the respective cavities in the process of the leakage flow 12 circulating in the respective cavities, whereupon a circumferential-velocity component thereof is attenuated.
  • the plural ribs 9 for causing the circumferential velocity to be reduced are discretely provided at a given intervals inside the cavity.
  • the ribs 9 each are a thin sheet for stretching the interior of the cavity in the direction of the rotation axis of the rotor 3 , and are fixed to the stationary part, that is, the diaphragm outer ring 1 .
  • the ribs 9 are installed at equal intervals, and at circumferential pitches identical to those of the buckets in the circumferential direction (in other words, the number of the ribs is identical to that of the buckets), this will enable the circumferential velocity of the leakage flow 12 to be more effectively reduced.
  • the leakage flow 12 having flowed into the cavity comes into collision with the ribs 9 to be turned in flow-angle to be then oriented in the direction of the rotation axis of the rotor 3 , thereby forming the recirculation flows 18 .
  • the leakage flow 12 can be caused to flow out in the direction of the rotation axis of the rotor 3 .
  • the axial seal fin 8 has the effect of preventing the steam main-stream 11 at a high pressure from flowing back into the cavity, and the mixing loss can be still further reduced owing to this effect.
  • the axial seal fin 8 is further provided with the guide plate 10 .
  • the guide plate 10 , and the axial seal fin 8 are each provided with the hole penetrating therethrough along the rotation radial direction of the rotor 3 , and the guide plate 10 is held to the axial seal fin 8 by the guide plate support-member 19 .
  • the guide plate support-member 19 is provided on an upstream side of the guide plate 10 , more than the center thereof, that is, on the upstream side of the steam main-stream 11 , thereby allowing the guide plate 10 to protrude as far as the steam main-stream 11 larger in mass flow rate than the leakage flow 12 , that is, up to the inner periphery side of the shroud 6 , the guide plate 10 will be spontaneously oriented in the same direction as that of the steam main-stream 11 owing to interference with the steam main-stream 11 , which is as changeable as a weathercock.
  • FIGS. 8 , and 9 each show a difference in distribution of absolute discharge-angles downstream from the bucket 5 between the presence and absence with respect to the guide plate 10 in the case where the operation state of the turbine is changed.
  • the leakage flow 12 whose circumferential-velocity component has turned substantially zero will differ in flow angle from the steam main-stream 11 owing to the effects of the ribs 9 , so that variation in flow angle distribution in the vicinity of a blade tip will increase.
  • the flow angle of the leakage flow 12 can be matched with the flow angle of the steam main-stream 11 , so that the deviation angle 24 between the leakage flow 12 and the steam main-stream 11 can be kept small regardless of the operation state of the turbine, and therefore, the variation in the flow angle distribution in the vicinity of the blade tip can be further suppressed. Accordingly, the mixing loss resulting from mixing of the steam main-stream 11 with the leakage flow 12 becomes smaller. As a result, a loss at the bucket, including the mixing loss from mixing of the steam main-stream 11 with the leakage flow 12 , can be reduced at the tip-part of the bucket, as shown in FIG. 9 , thereby enhancing the stage efficiency of a stage where the present invention is applied.
  • the present embodiment it is possible to reduce not only a bypass loss by suppressing a quantity of the leakage flow 12 but also the mixing loss by preventing the steam main-stream from flowing into the cavity, by removing the circumferential velocity component, and by suppressing the mismatch between the flow angles at the time of the leakage flow 12 merging with the steam main-stream 11 through the turning of the flow angle of the leakage flow 12 with the use of the guide plate 10 , so that the leakage loss can be effectively reduced regardless of the operation state of the turbine.
  • a distribution of flow angles in a blade-height direction is rendered uniform due to the suppression of the mismatch between the flow angles at the time of the leakage flow 12 merging with the steam main-stream 11 , so that a flow toward the nozzle 4 in a subsequent stage can be rectified so as to be oriented in the blade height direction.
  • the incidence loss can be reduced, thereby enabling a leakage flow loss to be effectively reduced.
  • the ribs 9 and the guide plates 10 are respectively installed at equal intervals in the same circumferential direction as that of the bucket 5 , (that is, the number thereof is the same as that of the bucket 5 ), however, even if the number thereof is less than that of the bucket 5 , the same effect can be obtained depending on the circumferential velocity imparted by the nozzle 4 .
  • FIGS. 10 , and 11 each show a stage structure of a steam turbine according to a second embodiment of the invention.
  • FIG. 12 is a plan view of a guide plate 10 shown in FIG. 11 .
  • a turbine stage of the steam turbine according to the present embodiment is provided with a rotatably supported rotor 3 , a bucket 5 fixed to the rotor 3 , a shroud 6 provided at the tip of the bucket 5 , a diaphragm outer ring 1 opposed to the shroud 6 with a gap provided therebetween, a radial seal fin 7 provided in such a way as to protrude from the diaphragm outer ring 1 in the radial direction of the rotor 3 in a gap between the shroud 6 and the diaphragm outer ring 1 , an axial seal fin 8 provided in such a way as to protrude from the diaphragm outer ring 1 in the direction of the rotation axis of the rotor 3 in the gap between the shroud 6
  • the pipe 22 serving as the guide-plate driving device for varying the position of the guide plate 10 on the basis of data of the pressure measurement device.
  • a face of the guide plate 10 opposed to the rotor 3 , is disposed on a side of the guide plate 10 , inner than a face of the shroud 6 , adjacent to the bucket 5 , along the radial direction of the rotor 3 .
  • the pipe 22 serving as the guide-plate driving device is provided so as to cover the first static pressure hole 20 , and the second static pressure hole 21 .
  • the pipe 22 serving as the guide-plate driving device is provided at a position closer to a face on the opposite side of the face provided with the first static pressure hole 20 , and the second static pressure hole 21 , than the center part of the guide plate 10 .
  • a turbine stage of the steam turbine according to the present embodiment is provided with the pipe 22 serving as the guide-plate driving device for driving the guide plate 10 in the circumferential direction, while holding the guide plate 10 having the two static pressure holes 20 , 21 in the diaphragm outer ring 1 .
  • the configuration as well as the function effect of the second embodiment is described below by focusing attention on a point where the second embodiment differs from the first embodiment.
  • the steam main-stream 11 having flowed out from the outlet of the bucket 5 is not oriented in the direction of the rotation axis of the rotor 3 depending on the operation state of the turbine. Accordingly, if the guide plate 10 is not installed, the leakage flow 12 whose circumferential-velocity component has turned substantially zero will merge with the steam main-stream 11 in a direction differing from the direction in which the steam main-stream 11 is oriented, thereby creating the cause of fostering the mixing loss.
  • the second embodiment is made up such that the two static pressure holes 20 , 21 provided in the guide plate 10 disposed in such a way as to protrude as far as the steam main-stream 11 , on the inner periphery side thereof, still inner than the shroud 6 , are connected to the pressure measurement device provided outside the turbine, thereby enabling the state of the steam main-stream 11 to be monitored at all times. Accordingly, with the second embodiment, the flow angle of the steam main-stream 11 is identified from a difference in pressure between the two static pressure holes 20 , 21 , and the guide plate 10 can be rotated in the circumferential direction so as to be oriented in the direction of the steam main-stream 11 via the pipe 22 serving as the guide-plate driving device.
  • the deviation angle between the leakage flow 12 and the steam main-stream 11 can be kept small regardless of the operation state of the turbine, so that the mixing loss resulting from mixing of the steam main-stream 11 with the leakage flow 12 becomes smaller, and the bucket loss including the mixing loss from mixing of the steam main-stream 11 with the leakage flow 12 can be reduced at the bucket-tip part.
  • the stage efficiency of the stage with the present invention applied thereto is enhanced.
  • the first embodiment shows an example whereby the guide plate 10 is controlled through the interference with the steam main-stream 11 , which is as changeable as the weathercock
  • the second embodiment shows an example whereby the flow angle of the steam main-stream 11 is identified from the difference in pressure between the two static pressure holes 20 , and 21 , thereby mechanically controlling the guide plate 10 via the pipe 22 serving as the guide-plate driving device
  • the present invention is capable of securing the same effects even with the use of other guide-plate control mechanism.
  • the advantageous effects of the invention is not dependent on the form of the control mechanism

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US14/535,362 2013-11-08 2014-11-07 Axial turbine Abandoned US20150132114A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2013-232039 2013-11-08
JP2013232039A JP2015094220A (ja) 2013-11-08 2013-11-08 軸流タービン

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US20150132114A1 true US20150132114A1 (en) 2015-05-14

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US14/535,362 Abandoned US20150132114A1 (en) 2013-11-08 2014-11-07 Axial turbine

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US (1) US20150132114A1 (ja)
EP (1) EP2871324A3 (ja)
JP (1) JP2015094220A (ja)
KR (1) KR101660120B1 (ja)
CN (1) CN104632296B (ja)
IN (1) IN2014DE03228A (ja)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20170130588A1 (en) * 2015-11-11 2017-05-11 Rolls-Royce Plc Shrouded turbine blade
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JP6930896B2 (ja) * 2017-10-31 2021-09-01 三菱重工業株式会社 タービン及び動翼
CN110863863A (zh) * 2019-11-29 2020-03-06 四川大学 一种燃气轮机带蓖齿封严的动叶护环结构
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US20170130588A1 (en) * 2015-11-11 2017-05-11 Rolls-Royce Plc Shrouded turbine blade
US11092026B2 (en) 2016-03-25 2021-08-17 Mitsubishi Power, Ltd. Rotary machine
CN106996389A (zh) * 2017-05-26 2017-08-01 西安理工大学 一种无叶顶间隙空化的短距诱导轮
US20220120188A1 (en) * 2019-01-31 2022-04-21 Mitsubishi Heavy Industries, Ltd. Rotating machine
US11519287B2 (en) 2019-01-31 2022-12-06 Mitsubishi Heavy Industries, Ltd. Rotating machine
US11655723B2 (en) 2019-01-31 2023-05-23 Mitsubishi Heavy Industries, Ltd. Rotating machine
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CN104632296A (zh) 2015-05-20
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