WO2015046970A1 - Structure de turbine multi-étages de type axial - Google Patents

Structure de turbine multi-étages de type axial Download PDF

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Publication number
WO2015046970A1
WO2015046970A1 PCT/KR2014/009054 KR2014009054W WO2015046970A1 WO 2015046970 A1 WO2015046970 A1 WO 2015046970A1 KR 2014009054 W KR2014009054 W KR 2014009054W WO 2015046970 A1 WO2015046970 A1 WO 2015046970A1
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WO
WIPO (PCT)
Prior art keywords
fluid
turbine
blade
axial
multistage turbine
Prior art date
Application number
PCT/KR2014/009054
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English (en)
Korean (ko)
Inventor
최혁선
Original Assignee
최혁선
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 최혁선 filed Critical 최혁선
Priority to CN201480057246.0A priority Critical patent/CN105658910A/zh
Priority to JP2016545690A priority patent/JP2016535205A/ja
Priority to US15/024,917 priority patent/US20160237821A1/en
Priority to EP14849067.5A priority patent/EP3051060A1/fr
Priority to RU2016116404A priority patent/RU2016116404A/ru
Publication of WO2015046970A1 publication Critical patent/WO2015046970A1/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
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
    • 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
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
    • F01D1/04—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines traversed by the working-fluid substantially axially
    • 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
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
    • F01D1/10—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines having two or more stages subjected to working-fluid flow without essential intermediate pressure change, i.e. with velocity stages
    • 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
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/34—Non-positive-displacement machines or engines, e.g. steam turbines characterised by non-bladed rotor, e.g. with drilled holes
    • 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
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
    • F01D1/026—Impact turbines with buckets, i.e. impulse turbines, e.g. Pelton turbines

Definitions

  • the present invention relates to a structure of an axial multistage turbine which can be arbitrarily formed in one or multiple stages depending on the type or flow rate of the fluid and the speed or drop of the fluid.
  • the turbine structure may be a collision type (aka impulse type)
  • impulse type aka impulse type
  • the reaction type the user can selectively use it according to the site situation, and in particular, the angle of the blade and nozzle of the turbine is best formed to maximize the efficiency, thereby greatly improving the quality and reliability of the product. It is to make a good image by satisfying various needs of users who are users.
  • the present invention is to know in advance that the present invention is an improved invention of the patent application No. 1184877 (name: improved structure of the axial turbine) registered and filed by the present applicant.
  • a turbine is a machine that converts energy of a fluid such as wind, water, gas, steam, etc. into useful mechanical work, and is characterized by rotational motion.
  • a turbine is a turbo type machine in which a plurality of blades or wings are planted on a circumference of a rotating body, and a fluid having a constant speed is ejected and rotated at high speed.
  • a hydro turbine is used to drop water from a high place and pass it through a runner, which is a rotating chain, to convert the energy of the flowing water into mechanical work.
  • a steam turbine uses steam energy that spouts steam from a nozzle and strikes a blade. .
  • Steam turbines also have impulse and recoil turbines, as well as hybrid gas turbines that combine the best of both worlds.
  • a gas turbine uses energy of high temperature and high pressure gas
  • an air turbine uses energy of high pressure compressed air. Any turbine is important for industrial power.
  • Steam turbines are used to drive generators in nuclear power plants, including thermal power plants, and hydro turbines are used to move generators in hydropower plants.
  • a multistage turbine refers to a turbine that expands gas or vapor expansion into several stages, which is a combination of stages consisting of nozzles or fixed vanes and rotary vanes.
  • the gas turbine has low thermal efficiency and high fuel consumption, and the structure of the rotor is complicated and enlarged, so that a large space in the axial direction is required, and thus the installation is not easy.
  • the prior art has a big problem that the efficiency is lowered because the angle of the blade and the nozzle of the turbine is not formed best.
  • Patent Document 1 Korean Unexamined Patent Publication No. 2010-0105103 (name: axial type multi-stage turbine) has been published.
  • Patent Document 2 Korean Patent Registration No. 1184877 (name: improved structure of axial multistage turbine) has been registered.
  • the present invention has been made in order to solve the problems of the prior art as described above, the first object of the first and second rotating blades and the fixed blade and the inclined slope and the resistance projections are provided in the body, the technical configuration described above According to the second object of the present invention, one or multiple stages may be arbitrarily formed and used depending on the type or flow rate of the fluid, and the speed or drop of the fluid.
  • the third object is a collision type (called impulse type).
  • impulse type the user can selectively use it according to the site situation.
  • the fourth purpose is to form the best angle of the blade and nozzle of the turbine to maximize the efficiency
  • the fifth purpose is to As it greatly improves the quality and reliability of the product, it can meet the various needs (users) of consumers as users and instill a good image. It provides a structure of an axial multistage turbine.
  • a mixed turbine turbine mixed with a collision type and a reaction type having a fluid filled therein, and the mixed turbine has a fluid inside the rotor.
  • the space portion 108 is formed to be filled, the body 101 formed with the inlet 102 and the outlet 103 at the top and bottom, respectively;
  • a rotating shaft 140 installed in the center of the body to rotate at a high speed and having a discharge hole formed therein;
  • At least one first rotating blade 110 which is integrally formed with the rotating shaft 140;
  • a second rotary blade 120 integrally formed with the rotary shaft at a predetermined interval;
  • a blowout hole 106 formed inside the upper end of the body, and a plurality of fixed blades 130 at the lower end thereof.
  • the axial flow type multistage turbine is provided.
  • the reaction turbine is provided with a fluid filled inside the rotor, the reaction turbine, the space 108 is formed so that the fluid is filled therein, the upper end A body formed with an inlet and an outlet at the bottom and the bottom, respectively; A rotating shaft arranged in the center of the body to rotate at a high speed and having a discharge hole formed therein; A plurality of rotating blades integrally formed with the rotating shaft at regular intervals and having a fixed space formed thereon; And a plurality of stationary blades at fixed intervals inside the body.
  • the structure of the axial multistage turbine is fixed.
  • the present invention is provided so that the first and second rotating blades and the fixed blades and the collision inclined surfaces and the resistance protrusions are provided on the body.
  • the present invention by the above-described technical configuration is to be used to form any one or multiple stages depending on the type or flow rate of the fluid and the speed or drop of the fluid.
  • the present invention is to allow the user to selectively use the turbine structure of the collision type (aka impulse type), the reaction type according to the site situation.
  • the turbine structure of the collision type aka impulse type
  • the present invention is to form the best angle of the blade and the nozzle of the turbine to maximize the efficiency.
  • the present invention greatly improves the quality and reliability of the product due to the above-described effects, which is a very useful invention that can be used to plant a good image by satisfying various needs (needs) of consumers.
  • FIG. 1 is a cross-sectional view of a first embodiment of an axial multistage turbine structure applied to the present invention.
  • FIG. 2 is a sectional view of a second embodiment of an axial multistage turbine structure applied to the present invention
  • FIG. 3 is a cross-sectional view of a third embodiment of an axial multistage turbine structure applied to the present invention.
  • FIG. 4 is a sectional view of a fourth embodiment of an axial multistage turbine structure applied to the present invention.
  • FIG. 5 is a plan sectional view of an axial multistage turbine applied to the present invention.
  • FIG. 6 is a sectional view of a first embodiment of a nozzle applied to the present invention.
  • FIG. 7 (a) is a cross-sectional view of a second embodiment of a nozzle applied to the present invention
  • FIG. 8 (a) is a cross-sectional view of a fourth embodiment of a nozzle applied to the present invention.
  • FIG. 9 is a sectional view of a sixth embodiment of a nozzle applied to the present invention.
  • FIG. 10 is a configuration diagram of another embodiment of the electric blade applied to the present invention.
  • hybrid turbine 110 first rotating blade
  • the structure of the axial multistage turbine applied to the present invention is configured as shown in Figs.
  • the first embodiment of the present invention in the structure of the axial multistage turbine, as shown in Figure 1, is provided with a hybrid turbine 100 is filled with a fluid inside, the hybrid turbine, the fluid inside The space portion 105 is formed to be filled, and the body 101 formed with the inlet 102 and the outlet 103 at the top and bottom, respectively.
  • the fluid passage 107 is formed so that the fluid flows and the rotating shaft 140 is provided.
  • At least one first rotating blade 110 is formed integrally with the rotating shaft 140 is provided.
  • the second rotary blade 120 is provided with a plurality of integrally arranged at a predetermined interval with the rotary shaft 140.
  • Blowing holes 121 to be guided to flow is formed and a plurality of fixed blades 130 are fixed.
  • the resistance protrusion 104 is formed at a predetermined interval so that the fluid hits the inside of the body 101 applied to the present invention.
  • first rotary blade 110 is further formed with a collision wing inclined surface 111 to bump the fluid to increase the rotational force.
  • the second rotating blade 120 is further formed with a blow hole 121 so that the fluid introduced into the discharge protrusion toward the resistance projection.
  • the second embodiment of the present invention in the structure of the axial multistage turbine, as shown in Figure 2, provided with a reaction turbine 200 is filled with a fluid inside, the reaction turbine, the fluid inside The space portion 203 is formed to be filled, and the body 201 is formed with the injection hole 202 and the discharge hole at the top and bottom, respectively.
  • the rotating shaft 220 is arranged in the center of the body 201 to rotate at a high speed, so that the inlet space 204 is formed.
  • a plurality of pieces are arranged at regular intervals integrally with the rotating shaft 220, and a rotating blade 230 is formed to form a fixed space 205.
  • a plurality of fixed blades 210 are fixedly installed at predetermined intervals inside the body 201.
  • the rotary blade 230 and the fixed blade 210 applied to the present invention is installed to be crossed to each other " ⁇ " or " ⁇ ".
  • a fluid passage is formed at a first end portion 207 in which a fluid ejecting direction is formed in an inner space at an outer portion of the rotary blade 230 as shown in FIG. 5.
  • the outer edge of the rotating blade 230 is formed with a second end portion 208 protruding upward, the bent portion 230a is fluid flows from the inside of the wing to the outside through the conduit groove 200 as shown in FIG. And it is formed to hit the resistance protrusion 206 formed inside the housing to obtain a reaction force.
  • the nozzle sphere end surface 231 is formed in parallel with the rotary blade end surface 232 in order to prevent loss of fluid, and has at least one or a plurality of multiple nozzle structures.
  • the nozzle sphere end surface 231 applied to the present invention is formed with a cover 300 so that the fluid does not spread out.
  • the present invention is the blade blade of the rotating blade 230 is formed on the end side of the rotating blade like a gear, the vertical angle is made vertical, the angle before (rotation direction) after (counter rotation direction) It is preferable to form inclined in the range of 5 ⁇ 45 degrees around the central axis 701 in the rotation direction.
  • the rotating blade 230 is formed as a fan (Fig. 8a), the left and right angles are preferably inclined in the rotational direction to 90 to 60 degrees, the front and rear angles are formed to be inclined to 5 to 45 degrees toward the rotational direction.
  • the present invention is such that the angle of the nozzle is in a straight line perpendicular to the wing surface where the fluid collides, the upper and lower angles of the nozzle in the fan-shaped disk shape is made in the range of 1 ⁇ 30 degrees, the left and right angles are inclined in the rotation direction Form at right angles to the wing surface.
  • the fluid enters the inlet 202 and enters the fixed space 205 formed inside the rotating blade through the inlet space 204, and the pipe groove formed at the end of the rotating body. Receives a reaction force by hitting the resistance wall 221 formed in the front of the conduit groove through the 230b propelling action and the ejection to the opposite direction in which the fluid is rotated to hit the resistance projection wall 206 formed inside the housing It is characterized by.
  • the present invention as shown in Figure 7a, 7b the end surface of the nozzle is formed in parallel with the blade end surface 232 of the rotating blade that the fluid collides, the nozzle is made of a plurality of, to prevent the dispersion of the fluid
  • the outer cover is characterized by being covered.
  • the present invention is characterized in that the end surface 231 of the nozzle for ejecting the fluid is formed to be made in parallel with the rotor blade end surface 232.
  • the present invention may be variously modified and may take various forms in applying the above configuration.
  • the wing shape can be transformed into various shapes, particularly in the crash mode.
  • the present invention is to allow the user to selectively use the turbine structure of the collision type, the reaction type according to the site situation, in particular to maximize the efficiency by forming the angle of the blade and nozzle of the turbine to the best.
  • the first embodiment of the present invention will be described first, and the fluid or gas is filled in the inner space 105 through the injection hole 102 in a state in which the outlet 103 of the body 101 is blocked.
  • the passage portion of the fluid or gas is formed in the inner space portion of the first rotary blade 110 and the second rotary blade 120 as well as the space portion 105 of the body 101 and the size of the passage space is fluid Or it is installed according to the type of gas or the situation of pressure.
  • the fluid or gas is introduced into the fluid passage 107 and the first rotating blade 110 is formed around the rotating shaft 140.
  • the second rotating blade 120 is rotated at a high speed.
  • the first rotating blade 110 allows the fluid coming through the ejection hole 106 to face the front to rotate at a high speed, to form a collision wing inclined surface 111 on the end surface of the first rotating blade and the collision wing inclined surface Plurality is formed at 60 to 90 degrees. That is, the angle at which the fluid is ejected is within 1 to 30 degrees, and the impingement wing slope is formed at an inclination angle (tilt) of 60 to 90 degrees, and the angle of the plane (collision wing slope) that matches the ejected angle is perpendicular to each other. It is characterized by.
  • the fluid or gas After the fluid or gas passes through the fluid passage 107, the fluid or gas is injected through the ejection hole 121 formed in the outer circumferential surface of the second rotating blade 120 and then discharged to the next stage.
  • the fluid or gas ejected to the ejection hole 121 is introduced into the inward direction after hitting the resistance protrusion 104, and this process is repeated, the hybrid turbine 100 is operated.
  • the present invention can minimize the flow loss can rotate the second rotating blade 120 at a high speed.
  • the adjacent fixed blade 130 is positioned in a fixed state without rotating.
  • the second embodiment of the present invention is almost similar to the first embodiment described above, and other differences will be described below.
  • the fluid introduced through the injection hole 202 is rotated at a high speed by rotating the rotating blade 230 built on the rotating shaft 220 while exiting the rotating blade 230 and the fixed blade 210 through the inlet space 204. Let's go.
  • the first end portion 207 having a space formed therein is formed on the outer side of the rotating blade 230 so as to increase the rotational force.
  • a second end portion 208 protruding upward is formed on the outer side of the rotating blade 230 in the above process, so that the fluid strikes the second end portion to further increase the rotational force of the rotating blade 230. do.
  • the present invention of course, to be able to use the configuration of the collision and the reaction type turbine as shown in FIG.
  • the end surface of the nozzle can be formed as shown in Figure 6, 7a, 7b, 7c to increase the rotational force of the rotating blade.
  • the present invention is to enable the use of the nozzle formed in one or a plurality of multiple structures as shown in Figure 7 (a) (b), the nozzle is formed in parallel along the circle to reduce the flow rate loss,
  • the rotating blade is formed to be equal to or less than the angle of the ejecting fluid to ensure that there is no loss of fluid.
  • the present invention as shown in Figure 8 (a) (b) to enable the use of a nozzle formed in one or a plurality of multiple structures, the nozzle end surface and the blade end surface of the rotary blade is formed to rotate in parallel Make it possible to increase the rotational force of the blade.
  • the present invention forms a cover 300 on the nozzle end surface as shown in Figure 9 so that the fluid or air is discharged immediately without spreading out to increase the rotational force of the rotating blade.
  • the technical idea of the structure of the axial multistage turbine of the present invention is that the same result can be repeatedly carried out.
  • it is possible to promote technological development and contribute to industrial development, which is worth protecting.

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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)
  • Hydraulic Turbines (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

La présente invention concerne une structure d'une turbine multi-étages de type axial. La structure de la turbine multi-étages de type axial de la présente invention comprend une turbine de type mixte (100) présentant une partie intérieure remplie d'un fluide, et la turbine de type mixte comprend : un corps (101) présentant une partie espace (105) dans laquelle un fluide est rempli, et une entrée (102) et une sortie (103) formées respectivement à une extrémité supérieure et une extrémité inférieure ; un arbre rotatif (140) prévu dans un centre du corps (101) destiné à être mis en rotation à une vitesse élevée et présentant un trou d'évacuation (107) ; au moins une première pale rotative (110) destinée à être intégrée dans l'arbre rotatif (140) ; une pluralité de secondes pales rotatives (120) destinées à être intégrées dans l'arbre rotatif (140) à un intervalle prédéterminé ; et le corps (101) comprenant un trou de réception (106) formé à l'intérieur de son extrémité supérieure et une pluralité de pales de fixation (130) destinées à être fixées à une extrémité inférieure du corps. La présente invention présentant la configuration susmentionnée permet à un utilisateur d'utiliser de manière sélective une structure de turbine parmi un type à immersion, un type à collision et de type actionné par recul en fonction des circonstances sur site, et en particulier, peut réduire le rendement en formant des angles d'une pale et d'une buse de la turbine, formant ainsi une bonne image d'un produit en satisfaisant divers besoins de consommateur grâce à l'amélioration notable de la qualité et de la fiabilité du produit.
PCT/KR2014/009054 2013-09-27 2014-09-26 Structure de turbine multi-étages de type axial WO2015046970A1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
CN201480057246.0A CN105658910A (zh) 2013-09-27 2014-09-26 轴式多级涡轮机结构
JP2016545690A JP2016535205A (ja) 2013-09-27 2014-09-26 軸流型多段タービンの構造
US15/024,917 US20160237821A1 (en) 2013-09-27 2014-09-26 Structure of axial-type multistage turbine
EP14849067.5A EP3051060A1 (fr) 2013-09-27 2014-09-26 Structure de turbine multi-étages de type axial
RU2016116404A RU2016116404A (ru) 2013-09-27 2014-09-26 Конструкция многоступенчатой турбины осевого типа

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
KR20130115511A KR101418345B1 (ko) 2013-09-27 2013-09-27 축류형 다단 터빈의 구조
KR10-2013-0115511 2013-09-27

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WO2015046970A1 true WO2015046970A1 (fr) 2015-04-02

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PCT/KR2014/009054 WO2015046970A1 (fr) 2013-09-27 2014-09-26 Structure de turbine multi-étages de type axial

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US (1) US20160237821A1 (fr)
EP (1) EP3051060A1 (fr)
JP (1) JP2016535205A (fr)
KR (1) KR101418345B1 (fr)
CN (1) CN105658910A (fr)
RU (1) RU2016116404A (fr)
WO (1) WO2015046970A1 (fr)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR101667386B1 (ko) * 2014-12-24 2016-10-19 포스코에너지 주식회사 축력 특성이 개선된 스팀 터빈
KR101578360B1 (ko) * 2015-02-12 2015-12-28 최혁선 축류형 터빈
KR101644924B1 (ko) * 2015-07-10 2016-08-03 포스코에너지 주식회사 반작용식 스팀 터빈
WO2017104916A1 (fr) * 2015-12-15 2017-06-22 포스코에너지 주식회사 Turbine à vapeur du type à réaction
US20180195392A1 (en) * 2017-01-11 2018-07-12 General Electric Company Steam turbine system with impulse stage having plurality of nozzle groups
JP6318332B1 (ja) * 2017-08-18 2018-04-25 村山　修 既設の石炭使用の火力発電装置からｃｏ２を発生させないで発電することを特徴とする発電装置。
KR102078465B1 (ko) * 2018-08-16 2020-02-17 동해기연(주) 정유량 조절구조를 갖는 터빈
RU2728310C2 (ru) * 2018-11-21 2020-07-29 Владимир Викторович Михайлов Радиальная турбина

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2006063811A (ja) * 2004-08-24 2006-03-09 Nidec Shibaura Corp 多段ターボファン
KR20070092841A (ko) * 2006-03-09 2007-09-14 피티엘중공업 주식회사 하이브리드 시너지 제트터빈 발전 시스템
JP2009019516A (ja) * 2007-07-10 2009-01-29 Hitachi Ltd 軸流タービン及びそれを用いた低圧蒸気タービン
KR20100105103A (ko) 2009-03-20 2010-09-29 최혁선 축류형 다단터빈
KR101184877B1 (ko) 2011-04-05 2012-09-26 최혁선 축류형 터빈의 개량구조

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1349487A (en) * 1917-05-31 1920-08-10 Erastus S Bennett Turbine-engine
US1676806A (en) * 1925-06-01 1928-07-10 William D Smalley Turbine
US4027995A (en) * 1975-07-14 1977-06-07 Berry Clyde F Steam track turbine
US4150918A (en) * 1976-01-21 1979-04-24 Hollymatic Corporation Pressure gas engine
US4421454A (en) * 1979-09-27 1983-12-20 Solar Turbines Incorporated Turbines
JP3353259B2 (ja) * 1994-01-25 2002-12-03 謙三 星野 タ−ビン
US6354800B1 (en) * 2000-03-31 2002-03-12 Lance G. Hays Dual pressure Euler turbine
US20120009055A1 (en) * 2009-03-18 2012-01-12 Hk Turbine Co., Ltd. Reaction-type turbine
US8678749B2 (en) * 2010-01-05 2014-03-25 Takeo S. Saitoh Centrifugal reverse flow disk turbine and method to obtain rotational power thereby
DE102010012583A1 (de) * 2010-03-23 2011-09-29 Alstom Technology Ltd. Verfahren zum Betrieb einer Dampfturbine mit einem Impulsrotor sowie Dampfturbine zur Durchführung des Verfahrens
CN201671659U (zh) * 2010-03-26 2010-12-15 西安陕鼓动力股份有限公司 喷汽式汽轮机
US20110311347A1 (en) * 2010-06-16 2011-12-22 John Marsden Flash Steam Turbine
EP2767673A4 (fr) * 2011-10-04 2015-12-02 Hyuk Sun Choi Turbine du type à flux axial

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2006063811A (ja) * 2004-08-24 2006-03-09 Nidec Shibaura Corp 多段ターボファン
KR20070092841A (ko) * 2006-03-09 2007-09-14 피티엘중공업 주식회사 하이브리드 시너지 제트터빈 발전 시스템
JP2009019516A (ja) * 2007-07-10 2009-01-29 Hitachi Ltd 軸流タービン及びそれを用いた低圧蒸気タービン
KR20100105103A (ko) 2009-03-20 2010-09-29 최혁선 축류형 다단터빈
KR101184877B1 (ko) 2011-04-05 2012-09-26 최혁선 축류형 터빈의 개량구조

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CN105658910A (zh) 2016-06-08
JP2016535205A (ja) 2016-11-10
EP3051060A1 (fr) 2016-08-03
KR101418345B1 (ko) 2014-07-10
US20160237821A1 (en) 2016-08-18
RU2016116404A (ru) 2017-11-01

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