Patent Publication Number: US-2016237821-A1

Title: Structure of axial-type multistage turbine

Description:
TECHNICAL FIELD 
     The present invention relates to a structure of an axial-type multistage turbine which may be arbitrarily formed in one stage or multiple stages in accordance with a type and a flow rate of a fluid and a velocity or a head of the fluid, and more particularly, to a structure of an axial-type multistage turbine which may enable a user to selectively use a turbine structure from a collision type turbine and a recoil-operated type turbine in accordance with circumstances on site, and particularly, may maximize efficiency by superlatively forming angles of a blade and a nozzle of the turbine, thereby providing a good image of a product by satisfying various consumer desires (needs) of users by remarkably improving quality and reliability of the product. 
     BACKGROUND ART 
     It should be noted that the present invention is an invention improving on U.S. Pat. No. 1,184,877 (Title: Improved structure of axial-type turbine) which has been registered through earlier application by the present applicant. 
     As is generally known, a turbine is a machine that converts energy that fluid, such as wind, water, gas, steam, and the like, has into useful mechanical energy, and is characterized by performing rotational motion. In general, a turbo-type machine in which multiple blades or wings are provided at a circumference of a rotor and rotated at a high speed by jetting a fluid having a constant speed to the blades or wings is called a turbine. A turbine which drops water from high places and enables the dropped water to pass through a runner that is a rotor to convert the energy of the running water into mechanical energy is a hydraulic turbine, and a turbine which uses steam energy for enabling the turbine to rotate by jetting steam from nozzles to the blades is a steam turbine. In addition, as the steam turbine, there are a collision type turbine and a recoil-operated type turbine, and there is also a mixed-type turbine combining advantages of both turbines. In addition, a gas turbine uses energy which high-temperature and high-pressure gas has, and an air turbine uses energy which high-pressure compressed air has. Any turbine is important as power for industries. The steam turbine is used to drive a generator in a thermoelectric power plant and a nuclear power plant, and the hydraulic turbine is used to move a generator in a hydroelectric power plant. 
     Meanwhile, a multistage turbine refers to a turbine that expands gas or steam in several stages, and is achieved by combining several stages, each of which is constituted of a nozzle or a fixed blade and a rotational blade. 
     However, the above-described gas turbine has low thermal efficiency and large fuel consumption, and a large space is required in an axial direction due to a complex structure and the enlargement of the rotor of the gas turbine, all of which does not facilitate installation. 
     In addition, the above-described conventional technology fails to superlatively form angles of the blade and the nozzle of the turbine, resulting in decreased efficiency. 
     PRIOR ART DOCUMENTS 
     [Patent Document 1] Korean Patent Publication No. 2010-0105103 (Title: Axial-type multistage turbine) has been published. 
     [Patent Document 2] Korean Patent Registration No. 1184877 (Title: Improved structure of Axial-type multistage turbine) has been registered. 
     DISCLOSURE 
     Technical Problem 
     The present invention is directed to providing a structure of an axial-type multistage turbine which may include first and second rotational blades, a fixed blade, a collision wing inclined surface, and a resistance projection provided in a body thereof, be arbitrarily formed in one stage or multiple stages in accordance with a type and a flow rate of a fluid and a velocity or a head of the fluid, enable a user to selectively use a turbine structure from a collision type turbine and a recoil operated type turbine in accordance with circumstances on site, and maximize efficiency by superlatively forming angles of a blade and a nozzle of the turbine, thereby providing a good image of a product by satisfying various consumer desires (needs) of users by remarkably improving quality and reliability of the product. 
     Technical Solution 
     One aspect of the present invention provides a structure of an axial-type multistage turbine in which a mixed-type turbine  100  with a fluid filled therein is provided, wherein the mixed-type turbine includes: a body  101  that has a space portion  105  in which the fluid is filled and an inlet  102  and an outlet  103  respectively formed at an upper end and a lower end thereof; a rotary shaft  140  that is pivotally arranged at a center of the body  101 , is rotated at a high speed, and has a fluid passage  107  in which the fluid flows; one or more first rotational blades  110  that are pivotally arranged to be integrated with the rotary shaft  140 ; a plurality of second rotational blades that are pivotally arranged to be integrated with the rotary shaft  140  at a predetermined interval; and a plurality of fixed blades  130  that are fixedly installed at the lower end of the body  101  while a nozzle portion  106  is formed inside the upper end of the body  101 . 
     Another aspect of the present invention provides a structure of an axial-type multistage turbine in which a recoil-operated type turbine  200  with a fluid filled therein is provided, wherein the recoil-operated type turbine  200  includes: a body  201  that has a space portion  203  in which the fluid is filled and an inlet  202  and an outlet respectively formed at an upper end and a lower end thereof; a rotary shaft  220  that is pivotally arranged at a center of the body  201 , is rotated at a high speed, and has a reception space  204  formed therein; a plurality of rotational blades  230  that are pivotally arranged to be integrated with the rotary shaft  220  at a predetermined interval, and in which a fixed space  205  is formed; and a plurality of fixed blades  210  that are fixedly installed at a predetermined interval inside the body  201 . 
     Advantageous Effects 
     According to embodiments of the present invention, first and second rotational blades, a fixed blade, a collision wing inclined surface, and a resistance projection may be provided in a body in a structure of an axial-type multistage turbine. 
     Also, according to embodiments of the present invention, a structure of an axial-type multistage turbine may be arbitrarily formed in one stage or multiple stages in accordance with a type and a flow rate of a fluid and a velocity or a head of the fluid. 
     Also, according to embodiments of the present invention, a structure of an axial-type multistage turbine may enable a user to selectively use a turbine structure from a collision type turbine and a recoil-operated type turbine in accordance with circumstances on site. 
     In particular, according to embodiments of the present invention, a structure of an axial-type multistage turbine may maximize efficiency by superlatively forming angles of a blade and a nozzle of the turbine. 
     Therefore, according to embodiments of the present invention, a good image of a product can be provided by satisfying various consumer desires (needs) of users by remarkably improving quality and reliability of the product. 
    
    
     
       DESCRIPTION OF DRAWINGS 
         FIG. 1  is a cross-sectional view showing a structure of an axial-type multistage turbine according to a first embodiment of the present invention. 
         FIG. 2  is a cross-sectional view showing a structure of an axial-type multistage turbine according to a second embodiment of the present invention. 
         FIG. 3  is a cross-sectional view showing a structure of an axial-type multistage turbine according to a third embodiment of the present invention. 
         FIG. 4  is a cross-sectional view showing a structure of an axial-type multistage turbine according to a fourth embodiment of the present invention. 
         FIG. 5  is a top cross-sectional view of an axial-type multistage turbine according to the present invention. 
         FIG. 6  is a cross-sectional view showing a nozzle according to the first embodiment of the present invention. 
         FIG. 7A  is a cross-sectional view showing a nozzle according to the second embodiment of the present invention, and  FIG. 7B  is a cross-sectional view showing a nozzle according to the third embodiment of the present invention. 
         FIG. 8A  is a cross-sectional view showing a nozzle according to the fourth embodiment of the present invention, and  FIG. 8B  is a cross-sectional view showing a nozzle according to a fifth embodiment of the present invention. 
         FIG. 9  is a cross-sectional view showing a nozzle according to a sixth embodiment of the present invention. 
         FIG. 10  is a configuration view showing a rotational blade according to another embodiment of the present invention. 
     
    
    
     DESCRIPTION OF MAJOR PARTS OF DRAWINGS 
     
         
           100 : Mixed-type turbine 
           110 : First rotational blade 
           120 : Second rotational blade 
           130 : Fixed blade 
           140 : Rotary shaft 
           300 : Cover 
       
    
     MODES OF THE INVENTION 
     A structure of an axial-type multistage turbine according to the present invention will be described with reference to  FIGS. 1 to 10 . 
     In the following descriptions of possible embodiments operable from the invention, when some of the components and features of the present invention are known and description thereof obscures the subject matter of the present invention, the corresponding detailed description will be omitted, and a specific embodiment illustrated in the drawings will be mainly described. 
     The following terms are defined in consideration of the functions of the present invention, and may be differently defined according to the intention of an operator or custom. Therefore, the terms should be defined based on the overall contents of the specification. 
     First, in a structure of an axial-type multistage turbine according to a first embodiment of the present invention, a mixed-type turbine  100  having an inner portion filled with a fluid is provided as shown in  FIG. 1 , and the mixed-type turbine includes a body  101  having a space portion  105  in which the fluid is filled and an inlet  102  and an outlet  103  respectively formed at an upper end and a lower end thereof. 
     In addition, the mixed-type turbine includes a rotary shaft  140  which is pivotally arranged at the center of the body  101 , is rotated at a high speed, and has a fluid passage  107  inside of which the fluid flows. 
     In addition, the mixed-type turbine includes one or more first rotational blades  110  which are coaxially arranged to be integrated with the rotary shaft  140 . 
     In addition, the mixed-type turbine includes a plurality of second rotational blades  120  which are coaxially arranged to be integrated with the rotary shaft  140  at a predetermined interval. 
     In addition, an ejection hole  121 , through which a fluid flowing into the space portion  109  formed inside the upper end of the body  101  is ejected from a nozzle portion  106  and collides with the first rotational blade  110  so as to flow through the fluid passage  107 , is formed in the body  101 , and a plurality of fixed blades  130  are fixedly installed in the body  101 . 
     In particular, inside the body  101  according to the present invention, a resistance projection  104  is formed to protrude at a predetermined interval so that the fluid collides with the resistance projection  104  to cause a recoil motion. 
     In addition, the collision wing inclined surface  111  which the fluid collides with to enhance a rotational force is further formed at the first rotational blade  110 . 
     The ejection hole  121  through which the fluid flowing into the inside is discharged to a side of the resistance projection is further formed at the second rotational blade  120 . 
     Meanwhile, in a structure of an axial-type multistage turbine according to a second embodiment of the present invention, a recoil-operated type turbine having an inner portion filled with a fluid is provided as shown in  FIG. 1 , and the recoil-operated type turbine includes a body  201  having a space portion  203  in which the fluid is filled and an inlet  202  and an outlet respectively formed at an upper end and a lower end thereof. 
     In addition, the recoil-operated type turbine includes a rotary shaft  220  which is coaxially arranged at the center of the body  201 , is rotated at a high speed, and has a reception space  204  formed therein. 
     In addition, the recoil-operated type turbine includes a plurality of rotational blades  230  which are coaxially arranged at a predetermined interval to be integrated with the rotary shaft  220  and having a fixed space  205  formed therein. 
     In addition, a plurality of fixed blades  210  are fixedly installed at a predetermined interval inside the body  201 . 
     In particular, the rotational blade  230  and the fixed blade  210  according to the present invention are assembled and installed to vertically cross each other in the form of “∈” or “⊃”. 
     In an end portion  207 , in which a path in a fluid ejection direction is formed in an inner space portion from an outer periphery of the rotational blade  230 , a fluid passage is formed as shown in  FIG. 5 . 
     In addition, a second end portion  208  that protrudes upward is formed at the outer periphery of the rotational blade  230 , and a bent portion  230   a  is formed in such a manner that the fluid flows from the inside of a wing to the outside of the blade through a pipe passage groove  200  shown in  FIG. 5  and collides with a resistance projection  206  formed at an inner side of a housing to cause a recoil force. 
     In addition, in the collision type turbine structure, an end surface  231  of the nozzle portion is formed in parallel with an end surface  232  of the rotational blade in order to prevent a flow rate loss of the fluid, and at least one or a plurality of multi-nozzle structures is achieved. 
     In addition, a cover  300  is formed at the end surface  231  of the nozzle portion according to the present invention so that the fluid does not spread out. On the other hand, according to the present invention, it is preferable that a wing blade of the rotational blade  230  be formed at an end side surface of the rotational blade  230  like a gear, and front (a rotational direction) and rear (an opposite direction to the rotational direction) angles be formed to be inclined in the range of 5 to 45 degrees with respect to a center axis  701  in the rotational direction, while upper and lower angles are perpendicular to each other. 
     In addition, it is preferable that left and right angles be inclined in the range of 90 to 60 degrees in the rotational direction and the front and rear angles be formed to be inclined in the range of 5 to 45 degrees in the rotational direction while the rotational blade  230  are formed like ribs of a fan (see  FIG. 8 a   ). 
     In addition, according to the present invention, the angle of a nozzle is in a straight line with or orthogonal to a wing surface which the fluid collides with, and upper and lower angles of the nozzle in a disk shape of ribs of a fan is in the range of 1 to 30 degrees and left and right angles thereof are orthogonal to the wing surface that is inclined in the rotational direction. 
     In addition, according to the present invention, as shown in  FIGS. 2 to 5 , a fluid flows into the inlet  202 , further flows into the fixed space  205  formed inside the rotational blade through the reception space  204 , collides with a resistance wall  221  formed at a front surface of a pipe passage groove  230   b  via the pipe passage groove  230   b  formed at a rotor end portion to thereby cause a propulsion action, and the fluid collides with the resistance projection  206  formed inside the housing while the fluid is ejected in the opposite direction to a direction in which the blade is rotated, and thereby obtains a recoil force. 
     In addition, according to the present invention, as shown in  FIGS. 7 a    and  7   b,  an end surface of a nozzle is formed in parallel with a wing end surface  232  of the rotational blade which the fluid collides with, a plurality of nozzles are provided, and an outer periphery of the end surface is covered with the cover in order to prevent dispersion of the fluid. 
     In addition, according to the present invention, the end surface  231  of the nozzle from which the fluid is ejected is formed in parallel with the wing end surface  232  of the rotational blade. 
     Meanwhile, when the above-described components are applied, the present invention may be modified variously and employ various forms. 
     In addition, it should be understood that the present invention is not limited to the above-mentioned particular form. On the contrary, the invention covers all alternatives, modifications, and equivalents within the spirit and scope of the present invention which are defined by the appended claims, and in particular, a wing shape in the collision type turbine structure may be modified in various forms. 
     Hereinafter, the effect of the structure of the axial-type multistage turbine according to the present invention which is configured as described above will be described. 
     First, according to the present invention, a user may selectively use a turbine structure from a collision type turbine structure and a recoil-operated type turbine structure in accordance with circumstances on site, and in particular, efficiency may be maximized by superlatively forming angles of a blade and a nozzle of the turbine, 
     For this, according to the first embodiment of the present invention, the inner space portion  105  is fully filled with a fluid or a gas through the inlet  102  in a state in which the outlet  103  of the body  101  is closed. 
     Accordingly, a propagation passage of the fluid or the gas is formed in inner space portions of the first rotational blade  110  and the second rotational blade  120  as well as the space portion  105  of the body  101 , and the size of the propagation passage is adjusted and installed in accordance with the type or pressure condition of the fluid or the gas. 
     When the fluid or the gas is injected at a high pressure through the inlet  102  and a nozzle portion  106  in the above-described state, the fluid or the gas rotates the first rotational blade  110  and the second rotational blade  120  with respect to the rotary shaft  140  at a high speed while the fluid or the gas flows into the fluid passage  107 . 
     In particular, the fluid flowing in through the nozzle portion  106  collides with the first rotational blade  110  so that the first rotational blade  110  may be rotated at a high speed. In addition, the collision wing inclined surface  111  is formed at an end surface of the first rotational blade and a plurality of collision wing inclined surfaces  111  are provided to have an angle in the range of 60 to 90 degrees. That is, an angle at which the fluid is ejected is in the range of 1 to 30 degrees, the collision wing inclined surface  111  is formed to have an inclination angle (an inclination) in the range of 60 to 90 degrees, and the angle at which the fluid is ejected and an angle of a surface (the collision wing inclined surface) which the fluid collides with are orthogonal to each other. 
     Next, the fluid or the gas passes through the fluid passage  107 , is ejected through the ejection hole  121  formed in an outer circumferential surface of the second rotational blade  120 , and is then discharged to the next stage. 
     In this instance, the fluid or the gas ejected through the ejection hole  121  collides with the resistance projection  104  and then enters in an inward direction again, and this process is repeatedly performed so that the mixed-type turbine  100  is operated. 
     In addition, the fluid leaks to the spaces of the fixed blade  130  and the second rotational blade  120  and propagates even through the fluid passage  107 , so that a flow rate loss of the fluid may be minimized without a leakage of the fluid between an end surface of a wing of the turbine and an inner wall of the housing in the prior art, thereby rotating the second rotational blade  120  at a high speed. 
     When the second rotational blade  120  is rotated, the fixed blade  120  adjacent to the second rotational blade  120  is positioned in a fixed state without being rotated. 
     Hereinafter, a second embodiment of the present invention will be described. 
     The second embodiment of the present invention is substantially similar to the above-described first embodiment, and a difference therebetween will be described below. 
     A fluid flowing in through the inlet  202  rotates the rotational blade  230  which is coaxially arranged on the rotary shaft  220  at a high speed while it is discharged out of the reception space  204  between the rotational blade  230  and the fixed blade  210 . 
     In the above-described process, a first end portion  207  having an inner space portion formed therein is formed at the outer periphery of the rotational blade  230 , thereby increasing a rotational force. 
     In addition, in the above-described process, the second end portion  208  that protrudes upward is formed at the periphery of the rotational blade  230 , and the fluid also collides with the second end portion  203 , thereby further increasing the rotational force of the rotational blade  230 . 
     Meanwhile, the present invention may obviously be configured and used in the form of the collision type turbine and the recoil-operated type turbine as shown in  FIG. 4 . 
     In addition, according to the present invention, the end surface of the nozzle may be formed as shown in  FIGS. 6, 7   a,    7   b,  and  7   c,  thereby increasing the rotational force of the rotational blade. 
     In addition, according to the present invention, the nozzle may be formed in one or a plurality of multi-structures as shown in  FIGS. 7 a    and  7   b.  The nozzle is formed in parallel along a circumferential surface of the blade in order to reduce a flow rate loss of the fluid, and the rotational blade is formed to have the same angle as that of the ejected fluid or less so that a loss of the fluid is prevented. 
     In addition, according to the present invention, the nozzle may be formed in one or a plurality of multi-structures as shown in  FIGS. 8 a    and  8   b,  so that the end surface of the nozzle and the wing end surface of the rotational blade are formed in parallel with each other, thereby increasing the rotational force of the rotational blade. In addition, according to the present invention, the cover  300  may be formed at the end surface of the nozzle as shown in  FIG. 9 , so that the fluid or the gas may be directly discharged without being spread out, thereby increasing the rotational force of the rotational blade. 
     INDUSTRIAL APPLICABILITY 
     The technical idea of the structure of the axial-type multistage turbine according to the present invention may repeatedly perform the same result in reality, and in particular, technological development may be promoted by performing the present invention to contribute to industrial development, and therefore the present invention may be sufficiently worthy of protection.