WO2013027239A1 - Turbine à écoulement axial - Google Patents

Turbine à écoulement axial Download PDF

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Publication number
WO2013027239A1
WO2013027239A1 PCT/JP2011/004682 JP2011004682W WO2013027239A1 WO 2013027239 A1 WO2013027239 A1 WO 2013027239A1 JP 2011004682 W JP2011004682 W JP 2011004682W WO 2013027239 A1 WO2013027239 A1 WO 2013027239A1
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WO
WIPO (PCT)
Prior art keywords
turbine
stage
working fluid
axial
flow
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Application number
PCT/JP2011/004682
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English (en)
Japanese (ja)
Inventor
英樹 小野
村田　健一
茂樹 妹尾
Original Assignee
株式会社 日立製作所
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 株式会社 日立製作所 filed Critical 株式会社 日立製作所
Priority to PCT/JP2011/004682 priority Critical patent/WO2013027239A1/fr
Publication of WO2013027239A1 publication Critical patent/WO2013027239A1/fr

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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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/32—Collecting of condensation water; Drainage ; Removing solid particles
    • 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
    • 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

Definitions

  • the present invention relates to an axial flow turbine such as a steam turbine or a gas turbine.
  • Patent Document 1 a plurality of turbine stages, each including a stationary blade fixed to an outer peripheral diaphragm and an inner peripheral diaphragm, and a moving blade fixed to a turbine rotor rotating around a turbine central axis, are provided in a working fluid flow path.
  • An axial flow turbine having a function of converting kinetic energy generated when a high-pressure working fluid expands toward a low-pressure portion in a flow path into a rotational force by a turbine stage composed of stationary blades and moving blades is disclosed. Yes.
  • the ring zone area is the product of the blade length and the average diameter obtained by adding the outer peripheral end diameter and the inner peripheral end diameter of the blade and dividing by two, and multiplying by the circular ratio. Therefore, in order to increase the ring zone area, the blade length and the average diameter are increased.
  • the total specific enthalpy H 0 which is the sum of the enthalpy per unit mass of the working fluid (specific enthalpy) and the kinetic energy per unit mass divided by the square of the flow velocity divided by 2, is the rotation
  • the value is substantially constant from the inner peripheral side close to the shaft to the outer peripheral side.
  • the specific enthalpy h 1 between the stationary blade and the moving blade becomes larger toward the outer peripheral side than the inner peripheral side so as to balance with the swirling flow between the stationary blades. Accordingly, the specific enthalpy difference H 0 ⁇ h 1 becomes smaller toward the outer peripheral side.
  • the velocity of the flow leaving the stationary blade is proportional to the square root of this specific enthalpy difference H 0 -h 1 . That is, the stationary blade outflow speed becomes smaller toward the outer peripheral side.
  • the loss increases due to the supersonic speed of the relative inflow Mach number of the moving blades.
  • Increasing the blade length and the average diameter increases the peripheral speed, which is the rotational speed of the moving blade.
  • the peripheral speed of the moving blade is greatest at the outer peripheral end where the radial position is the largest, that is, at the tip of the moving blade. If the peripheral Mach number obtained by dividing the peripheral speed of the moving blade by the sonic speed exceeds 1 and becomes supersonic, and the rotational direction component of the flow from the stationary blade is not sufficient, the relative velocity of the flow flowing into the moving blade is Supersonic speed.
  • an object of the present invention is to provide an axial flow turbine that can suppress shock wave loss due to an increase in annulus area and improve turbine efficiency.
  • an axial turbine including a plurality of turbine stages each having a stationary stage fixed to a stationary body and a moving blade fixed to a turbine rotor in a working fluid flow path is provided outside the working fluid flow path. And a bypass flow path that bypasses at least one stage of the turbine stage and introduces a part of the working fluid from the upstream side in the working fluid flow direction to the turbine stage on the downstream side in the working fluid flow direction of the bypassed turbine stage.
  • FIG. 1 is a meridional cross-sectional view showing a main structure of a turbine stage part of a general steam turbine.
  • the steam high pressure part P 0 on the upstream side in the flow direction of the steam 1 as the working fluid hereinafter simply referred to as upstream side
  • downstream side the downstream side in the steam flow direction
  • the turbine stage includes a stationary blade 6 fixed between the outer peripheral diaphragm 4 and the inner peripheral diaphragm 5 and a moving blade 7 fixed to the turbine rotor 8 so as to face the downstream side of the stationary blade 6. Is done.
  • the turbine stage is a multi-stage turbine composed of a plurality of stages
  • a plurality of turbine stages are repeatedly provided from the high pressure part P 0 toward the low pressure part P 1 along the turbine central axis 9.
  • the paragraph closest to the steam inlet of the high-pressure part P 0 is called the first paragraph
  • the paragraph closest to the steam outlet of the low-pressure part P 1 is called the last paragraph.
  • the casing 3 includes a diaphragm support 16 and an extraction chamber partition plate 17.
  • the diaphragm support 16 has a plate-like structure having a thickness in the vertical direction on the paper surface, and a plurality of diaphragm supports 16 are provided around the rotation axis.
  • the extraction chamber partition plate 17 has an axisymmetric structure around the rotation axis.
  • a bleed chamber 18 is formed inside the casing 3. Part of the working steam that passes through the steam main flow path 2 is introduced into the extraction chamber, and is sent out of the turbine by extraction means (not shown). In FIG. 1, higher specific enthalpy and high-pressure working steam is extracted in the upstream extraction chamber.
  • the turbine stage has four stages and the extraction chambers 18a, 18b, and 18c are provided.
  • the number of stages and the number of extraction chambers are not particularly limited to this example.
  • the turbine rotor 8 is mechanically connected to a generator (not shown).
  • a generator not shown
  • kinetic energy generated when high-pressure steam expands toward a low-pressure portion is converted into rotational force by a turbine stage composed of stationary blades 6 and moving blades 7, and is electrically generated by a generator via a turbine rotor 8. It converts into energy and generates electricity.
  • FIG. 3 is a graph showing the specific enthalpy distribution in the blade height direction of the turbine last stage of the steam turbine shown in FIG.
  • the horizontal axis represents the specific enthalpy, and the axial direction is determined so that the specific enthalpy increases toward the left as the working fluid vapor flows from left to right in FIG.
  • the vertical axis represents the blade height direction
  • BH represents the blade exit height.
  • H 0 is the total specific enthalpy which is the sum of the specific enthalpy per unit mass at the paragraph inlet and the kinetic energy per unit mass divided by the square of the working fluid flow velocity divided by 2
  • h 1 is the stationary and moving blade
  • the specific enthalpy between and h 2 represents the specific enthalpy of the paragraph exit.
  • the total specific enthalpy H 0 at the paragraph inlet is substantially constant in the blade height direction.
  • the specific enthalpy h 1 between the stationary blades and the moving blades increases toward the outer peripheral side in the turbine radial direction (hereinafter simply referred to as the outer peripheral side) so as to balance with the centrifugal force mainly due to the swirling speed between the stationary blades.
  • the specific enthalpy difference ⁇ h applied to the outer stationary vane is reduced, and the stationary blade outflow speed proportional to the square root of the specific enthalpy difference is also reduced.
  • the tendency of the specific enthalpy difference and the stationary blade outflow speed of the stationary blade to decrease is that the blade diameter and the average diameter obtained by adding the outer peripheral end diameter and the inner peripheral end diameter of the blade and dividing by 2 are increased. As the annular area increases, the outer peripheral end position of the wing becomes more prominent as it comes to the outer peripheral side.
  • FIG. 4 schematically shows the relationship among the stationary blade outflow speed, the moving blade peripheral speed, and the relative inflow speed of the moving blade when the peripheral speed of the moving blade is large.
  • the steam flowing into the moving blade 7 becomes a flow having a relatively speed W (hereinafter referred to as a moving blade relative inflow velocity W).
  • a triangle formed by the stationary blade outflow velocity vector V, the peripheral velocity vector U, and the moving blade relative inflow velocity vector W is referred to as a velocity triangle.
  • the moving blade circumferential speed U increases, the moving blade relative speed W flowing into the moving blade 7 increases.
  • FIG. 5 is a graph showing the blade height direction distribution of the blade relative inflow Mach number when the blade peripheral speed is high.
  • the Mach number exceeds 1.0 and supersonic inflow occurs.
  • the specific enthalpy difference H 0 -h 2 of the turbine stage itself is increased in order to increase the specific enthalpy difference ⁇ h of the outer stationary blade, the relative inflow Mach number of the moving blade at the inner peripheral end becomes 1.0.
  • FIG. 2 is a meridional cross-sectional view of the main structure of the turbine stage part of the steam turbine according to the first embodiment of the present invention.
  • the steam flow path to the final stage includes a steam main flow path 2 and a bypass flow path 11 provided outside the steam main flow path 2.
  • the bypass flow path 11 is a flow path for introducing a part of the main steam flowing from the upstream side into a turbine stage downstream of the bypassed turbine stage by bypassing at least one stage of the turbine stage.
  • a stationary blade bypass channel partition cover 12 is provided between the stationary blades 6a adjacent to each other in the circumferential direction at the final stage.
  • a stationary blade bypass passage partition cover 12 divides the passage between the stationary blades into a steam main passage 2 on the inner peripheral side and a stationary blade bypass passage 19 on the outer peripheral side in the radial direction. Steam that flows down the bypass passage 11 flows into the stationary blade bypass passage 19, and the main steam flows into the steam main passage 2 on the inner peripheral side.
  • a blade bypass passage partition cover 13 is provided between the blades 7a adjacent in the circumferential direction of the final stage.
  • the blade bypass passage partition cover 13 divides the passage between the rotor blades into the steam main passage 2 on the inner peripheral side and the blade bypass passage 20 on the outer peripheral side in the radial direction.
  • the steam that flows down through the bypass flow path 11 and the stationary blade bypass flow path 19 mainly flows into the moving blade bypass flow path 20, and the main steam flow flows into the steam main flow path 2 on the inner peripheral side.
  • the moving blade bypass flow path partition cover 13 includes a type in which a plurality of moving blades 7a are collected and fixed by one member, a type that is closely attached by a blade integrated cover having a pitch between blades, etc. Any form may be used as long as it has a function of dividing the flow path so that the steam of the steam main flow path 2 and the bypass flow path 11 are not in direct contact with each other.
  • the bypass flow path 11 is a cylindrical flow path centered on the turbine central shaft 9 provided in the casing portion, and communicates the upstream extraction chamber 18b and the stationary blade bypass flow path 19 with each other.
  • the extraction chamber 18b is an extraction chamber into which the extracted steam extracted immediately upstream of the turbine stage one upstream of the final stage flows.
  • bypass flow path 11 a part of the steam extracted from the steam main flow path immediately upstream of the turbine stage one upstream of the final stage bypasses the turbine stage one upstream of the final stage, and the stationary blades of the final stage and It flows into the blade bypass passage. Therefore, steam having a high specific enthalpy is introduced from the upstream extraction chamber 18 b into the moving blade bypass passage 20 through the stationary blade bypass passage 19 by the bypass passage 11.
  • the bypass channel 11 is provided with a plurality of extraction tubes 14 in the circumferential direction.
  • FIG. 6 is a graph showing the specific enthalpy distribution in the blade height direction of the final stage of the steam turbine according to the present embodiment and one upstream stage thereof.
  • the steam main flow path 2 is below the span position BH c , and the bypass flow path 11 is above.
  • H 0 is the total specific enthalpy upstream of the stationary blade 6b shown in FIG.
  • h 1 , H 2 , h 3 , and h 4 are specific enthalpy h and total specific enthalpy, respectively, upstream of the moving blade 7b, upstream of the stationary blade 6a, upstream of the moving blade 7a, and downstream of the moving blade 7a of the steam main flow path 2.
  • h 3 ′ is a specific enthalpy h upstream of the moving blade 7 a of the bypass flow path 11.
  • the specific enthalpy drop on the outer peripheral side of the final stage is conventionally ⁇ h, but in the bypass flow path, the specific enthalpy drop ⁇ h ′ on the outer periphery of the moving blade is increased because the specific enthalpy of the inlet is increased. Therefore, on the outer peripheral side, the steam outflow speed of the stationary blade increases and the steam inflow speed of the moving blade inlet decreases.
  • FIG. 7 shows the blade height direction distribution of the moving blade inlet angle measured from the circumferential direction of the final stage of the steam turbine according to the present embodiment.
  • the span height BH c it is designed such that the relative inflow angle of the main steam flow path and bypass flow of the rotor blade 7a is continuous.
  • FIG. 8 is a graph showing the blade height direction distribution of the moving blade relative inflow Mach number in the final stage of the steam turbine according to the present embodiment shown in FIG. 2.
  • M r3 ′ shown by a solid line is the moving blade relative inflow Mach number of the final stage of the steam turbine according to the present embodiment
  • M r3 shown by a broken line is the relative inlet of the moving blade of the general last stage of the steam turbine shown in FIG. Mach number.
  • the specific enthalpy difference of the stationary blade is increased from ⁇ h to ⁇ h ′, so that the stationary blade outflow speed on the outer peripheral side of the stationary blade is increased, and as described with reference to FIG. Sonic inflow is avoided.
  • the specific enthalpy difference ⁇ h on the outer peripheral side of the stationary blade is increased by increasing the total specific enthalpy H 0 on the outer peripheral side of the final stage inlet.
  • the stationary blade outflow speed can be increased. Therefore, the speed component in the turning direction of the stationary blade outflow speed component V can be increased, and the relative inflow speed of the moving blade flowing into the moving blade in the final stage can be reduced even though the circumferential speed U is the same. . Therefore, the supersonic inflow to the moving blade can be avoided, the generation of the shock wave at the moving blade inlet can be suppressed, and the loss accompanying the generation of the shock wave can be suppressed.
  • the expansion rate of the meridian plane flow path that is, the increase rate of the flow path height of the paragraph outlet with respect to the flow path height of the turbine stage inlet increases.
  • the axial length of the stage cannot generally be increased because of the restriction of the overall length of the turbine.
  • the increase is generally realized by increasing the spread angle of the meridional flow path shape at the outer peripheral end or inner peripheral end of the stationary blade portion. It is known that if the spread angle of the meridional flow path is increased, peeling occurs and a loss occurs, which is particularly remarkable on the outer peripheral side.
  • the working steam on the outer peripheral side passes through the bypass flow path substantially parallel to the axis, and therefore no separation occurs.
  • the rotational force extracted by the paragraph composed of the stationary blade 6b and the moving blade 7b is reduced, but the decrease is extracted as rotational force in the paragraph composed of the stationary blade 6a and the moving blade 7a. Therefore, the rotational power of the turbine as a whole is not reduced. Rather, it is possible to increase the rotational force as the loss is reduced.
  • the shroud cover 10 is provided on the outer peripheral side of the final stage rotor blade, but the shroud cover 10 is not necessarily required in the configuration of the present invention, and a configuration without the shroud cover 10 may be employed (FIG. 9).
  • FIG. 10 is a meridional cross-sectional view showing the main structure of the turbine stage part of the steam turbine according to the second embodiment of the present invention.
  • symbol is attached
  • the steam pressure is designed to be substantially equal at a portion where the bypass flow passage 11 and the steam main flow passage 2 join the upstream portion of the final stage moving blade 7a downstream of the final stage stationary blade 6a. Since the steam merged from the bypass flow path 11 and the steam main flow path 2 does not drift in the radial direction, the blade bypass flow path partition cover 13 is unnecessary.
  • the steam from the bypass flow path 11 and the steam main flow path 2 are not necessarily the same in speed and flow direction. Therefore, a shear layer is formed at the junction of the bypass flow path 11 and the steam main flow path 2, and energy loss occurs. However, the loss due to the shear layer is negligible for the shaft power generated in the final paragraph. Rather, since the centrifugal stress design value of the moving blade 7a can be afforded by eliminating the moving blade bypass flow path partition cover 13, it is possible to further increase the length of the blade and increase the annular zone area. The output can be increased without increasing.
  • FIG. 11 is a meridional cross-sectional view illustrating a main structure of a turbine stage portion of a steam turbine according to a third embodiment of the present invention.
  • symbol is attached
  • the pressure and specific enthalpy level are low, and the working steam becomes wet steam.
  • a liquid film is formed on the surface of the stationary blade 6a, and coarse droplets are discharged from the trailing edge of the stationary blade 6a to the moving blade 7a.
  • Coarse droplets are refined by working steam between the stationary blades, but a part of them collides with the tip of the blade and erodes the blade 7a.
  • the progress of erosion has a problem that it is accompanied by a decrease in shaft power and blade strength.
  • the moisture removal slit 15 is provided in the outer wing portion located in the stationary blade bypass passage 19 of the stationary blade 6a.
  • the stationary blade bypass channel partition cover 12, the outer wing portion of the stationary blade 6a, and the outer diaphragm 4a are formed hollow, and the steam upstream of the stationary blade 6a is the outer wing portion of the stationary blade bypass channel partition cover 12 and the stationary blade 6a. From the inside of the outer peripheral side diaphragm 4a, it is led out to the extraction chamber 18a.
  • the moisture removal slit 15 communicates with the inside and outside of the stationary blade, and the pressure outside the stationary blade is higher than the inside of the stationary blade. Therefore, the liquid film formed on the stationary blade passes through the moisture removal slit 15 and is removed to the extraction chamber 18a. Since there are no coarse droplets discharged to the wake of the stationary blade 6a, no erosion of the moving blade occurs.
  • the present invention is not limited to the final paragraph, and can be applied to the upstream paragraph. Further, the present invention is applicable not only to a steam turbine but also to a gas turbine.
  • the first advantage is that wetting loss is reduced.
  • the water film adhering to the blade surface of the moving blade 7 constituting the upstream stage of the final stage is collected on the outer peripheral side by centrifugal force, and toward the stationary blade 6a of the final stage. Released. Therefore, the degree of wetness increases on the outer peripheral side of the final paragraph inlet, which causes an increase in wet loss and an increase in erosion in the final stage where the moving blade peripheral speed is high.
  • the present invention when the present invention is applied to the final stage of the steam turbine, the wetness, which is the mass fraction of the liquid phase, is small because the total inlet enthalpy on the outer periphery side of the final stage is large.
  • the present invention reduces wet loss and can suppress the occurrence of erosion. Therefore, turbine efficiency can be improved and the reliability of the steam turbine can be improved.
  • the second advantage is that the reliability of the wing can be improved.
  • the Wilson line that transitions from superheated steam of a steam turbine to wet steam that is in a two-phase flow state is often located in the turbine stage one upstream of the last stage.
  • the Wilson line moves in the flow direction depending on the turbine load and steam conditions. Therefore, in the turbine stage where the Wilson line exists, the state of dry steam and wet steam is repeated, and corrosion pits are likely to occur.
  • the turbine stage upstream of the final stage where the Wilson line is generated has a small blade length, so that the stress applied to the blade can be reduced, and the reliability of the blade is reduced due to corrosion pits. Can be suppressed.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne une turbine à écoulement axial qui, afin de réduire des pertes par onde de choc dues à un accroissement de la section annulaire et des pertes dues à un décollement en vue d'améliorer ainsi le rendement de ladite turbine à écoulement axial, comporte un étage de turbine constitué d'une aube fixe fixée à un corps fixe et d'une aube tournante fixée à un rotor de turbine, ainsi qu'un passage (2) d'écoulement de fluide de travail comportant une pluralité d'étages de turbine dans la direction axiale de la turbine. La turbine à écoulement axial est dotée d'un passage (11) d'écoulement de dérivation qui est situé en dehors du passage (2) d'écoulement de fluide de travail et qui permet à une partie d'un fluide de travail, entrant par le côté amont dans le sens de l'écoulement du fluide de travail, de contourner le côté périphérique extérieur d'au moins un des étages de turbine et d'être introduit dans un étage de turbine situé du côté aval de l'étage de turbine contourné dans le sens de l'écoulement du fluide de travail.
PCT/JP2011/004682 2011-08-24 2011-08-24 Turbine à écoulement axial WO2013027239A1 (fr)

Priority Applications (1)

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PCT/JP2011/004682 WO2013027239A1 (fr) 2011-08-24 2011-08-24 Turbine à écoulement axial

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PCT/JP2011/004682 WO2013027239A1 (fr) 2011-08-24 2011-08-24 Turbine à écoulement axial

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WO2013027239A1 true WO2013027239A1 (fr) 2013-02-28

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2021124021A (ja) * 2020-01-31 2021-08-30 三菱重工業株式会社 タービン

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1597467A (en) * 1923-09-12 1926-08-24 Westinghouse Electric & Mfg Co Turbine blading
JPS63117105A (ja) * 1986-11-06 1988-05-21 Mitsubishi Heavy Ind Ltd 蒸気タ−ビンの翼列湿分除去装置
JPH08232604A (ja) * 1995-02-27 1996-09-10 Toshiba Corp 蒸気タービンのエロージョン防止装置
JPH10331604A (ja) * 1997-05-30 1998-12-15 Toshiba Corp 蒸気タービンプラント
JP2007211660A (ja) * 2006-02-08 2007-08-23 Toyota Motor Corp チップタービンファン
JP2011069308A (ja) * 2009-09-28 2011-04-07 Hitachi Ltd 軸流タービン
JP2011099380A (ja) * 2009-11-06 2011-05-19 Hitachi Ltd 軸流タービン

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1597467A (en) * 1923-09-12 1926-08-24 Westinghouse Electric & Mfg Co Turbine blading
JPS63117105A (ja) * 1986-11-06 1988-05-21 Mitsubishi Heavy Ind Ltd 蒸気タ−ビンの翼列湿分除去装置
JPH08232604A (ja) * 1995-02-27 1996-09-10 Toshiba Corp 蒸気タービンのエロージョン防止装置
JPH10331604A (ja) * 1997-05-30 1998-12-15 Toshiba Corp 蒸気タービンプラント
JP2007211660A (ja) * 2006-02-08 2007-08-23 Toyota Motor Corp チップタービンファン
JP2011069308A (ja) * 2009-09-28 2011-04-07 Hitachi Ltd 軸流タービン
JP2011099380A (ja) * 2009-11-06 2011-05-19 Hitachi Ltd 軸流タービン

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2021124021A (ja) * 2020-01-31 2021-08-30 三菱重工業株式会社 タービン
CN115003898A (zh) * 2020-01-31 2022-09-02 三菱重工业株式会社 涡轮机
JP7368260B2 (ja) 2020-01-31 2023-10-24 三菱重工業株式会社 タービン
US11852032B2 (en) 2020-01-31 2023-12-26 Mitsubishi Heavy Industries, Ltd. Turbine

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