WO2016076374A1 - タービン用ロータアセンブリ、タービン、及び、動翼 - Google Patents
タービン用ロータアセンブリ、タービン、及び、動翼 Download PDFInfo
- Publication number
- WO2016076374A1 WO2016076374A1 PCT/JP2015/081793 JP2015081793W WO2016076374A1 WO 2016076374 A1 WO2016076374 A1 WO 2016076374A1 JP 2015081793 W JP2015081793 W JP 2015081793W WO 2016076374 A1 WO2016076374 A1 WO 2016076374A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- rotor shaft
- blade
- radial direction
- rotor
- turbine
- Prior art date
Links
Images
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
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/16—Form or construction for counteracting blade vibration
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
-
- 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
-
- 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
- F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
- F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/022—Blade-carrying members, e.g. rotors with concentric rows of axial blades
-
- 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
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
-
- 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
- F05D2240/00—Components
- F05D2240/80—Platforms for stationary or moving blades
Definitions
- the present disclosure relates to a turbine rotor assembly, a turbine, and a moving blade.
- an axial-flow turbine used for power generation has a plurality of stationary blade rows fixed to a casing and a plurality of blade rows fixed to a rotor shaft.
- Some turbine blades have a T-shaped blade root.
- the blade root portion is fitted into a blade groove provided on the rotor shaft, whereby the turbine rotor blade is fixed to the rotor shaft.
- the blade groove also has a T-shaped cross section corresponding to the shape of the blade root.
- a turbine blade disclosed in Japanese Patent Application Laid-Open No. 7-63004 is provided with a step at the neck corresponding to a T-shaped vertical bar at the blade root. This step is separated from the wall surface of the blade groove when the rotor disk forming a part of the rotor shaft is stationary. On the other hand, this step is configured to abut against the wall surface of the blade groove when the vibration amplitude of the turbine blade increases during operation of the turbine. According to this configuration, the blade frequency can be changed by changing the boundary condition of the vibration of the turbine blade. As a result, resonance with the specific excitation frequency can be avoided, and the reliability of the turbine rotor blade can be greatly improved.
- one end of the neck portion of the blade root portion extends outward from the outer peripheral surface of the rotor shaft in the radial direction of the rotor shaft,
- the axial length of the rotor shaft is formed to be larger than the width of the neck in the blade groove, and this is the platform portion that supports the blade profile portion.
- the contact surface of the blade root portion is represented by (W1-W) in FIG. 1 of Japanese Patent Laid-Open No. 7-63004. This is because it must be extended in the axial direction of the rotor shaft.
- At least one embodiment of the present invention aims to provide a turbine rotor assembly, a turbine, and a moving blade capable of reducing the interval between moving blade rows.
- a turbine rotor assembly includes: A rotor shaft formed with blade grooves extending along the circumferential direction; A plurality of blades each having a blade profile portion disposed outside the rotor shaft in a radial direction of the rotor shaft and a blade root portion integrally provided with the blade profile portion and fitted in the blade groove; With The rotor shaft is Projecting outward from the outer circumferential surface of the rotor shaft in the radial direction of the rotor shaft and spaced apart from each other in the axial direction of the rotor shaft, a part of the wall surface of the blade groove and the blade groove Two protrusions constituting the opening; The blade grooves are provided on the inner side in the radial direction of the rotor shaft than the outer peripheral surface of the rotor shaft and face inward in the radial direction of the rotor shaft, and are spaced apart from each other in the axial direction of the rotor shaft.
- Two bearing surfaces forming part of the wall surface of Each of them is located between the bearing surface and the outer peripheral surface of the protrusion in the radial direction of the rotor shaft, and constitutes part of the wall surface of the blade groove so as to face each other in the axial direction of the rotor shaft.
- Two first opposing surfaces Respectively located between the bearing surface and the outer peripheral surface of the protrusion in the radial direction of the rotor shaft, the outer surface is located outside the two first opposing surfaces, and is more than the interval between the first opposing surfaces.
- the blade root of the blade is Two contact surfaces that are spaced apart from each other in the axial direction of the rotor shaft and that can contact the two bearing surfaces in the radial direction of the rotor shaft; Two first side surfaces respectively facing the two first opposing surfaces; Two second side surfaces respectively opposed to the two second opposing surfaces with an interval smaller than an interval between the first opposing surface and the first side surface;
- the rotor shaft has the first opposing surface and the first surface constituting a part of the wall surface of the blade groove corresponding to the blade root portion of the moving blade having the first side surface and the second side surface. It has two opposing surfaces.
- the spacing between the first facing surfaces is smaller than the spacing between the second facing surfaces, and the contact area between the abutting surface of the blade root portion and the bearing surface of the rotor shaft can be increased corresponding to the difference between these spacings. it can. For this reason, the length of the blade root portion in the axial direction of the rotor shaft can be shortened, and the interval between the rotor blade rows can be narrowed.
- the number of paragraphs can be increased while suppressing an increase in size, or the size can be reduced if the number of paragraphs remains the same.
- the second facing surface is opposed to the second side surface of the blade root portion, covers a part of the blade root portion that extends outward in the radial direction of the rotor shaft from the outer peripheral surface of the rotor shaft, and reduces the exposed portion, The leakage of the working fluid from the gap between adjacent blade roots can be reduced.
- the blade root portion is provided with two flange portions that are located next to the outer peripheral surfaces of the two protrusion portions in the radial direction of the rotor shaft when the blade root portion is assembled to the blade groove.
- the platform portion that supports the blade profile portion can be greatly formed.
- the length of the turbine stage needs to be increased by the width of the protrusion (the length in the axial direction of the rotor shaft). If the length of the turbine stage is not changed, the platform portion (and thus the blade profile portion) need not be formed small.
- the length of the blade root portion in the axial direction of the rotor shaft including the corresponding contact surface at a position where the contact surface is formed is 1.2 times or less of the length of the platform portion. According to this configuration, the length in the axial direction of the rotor shaft including the corresponding contact surface of the blade root portion at the position where the contact surface is formed is 1.2 times or less the length of the platform portion. The interval between the rotor blade rows can be reliably reduced.
- the length of the blade root portion at the position where the contact surface is formed, including the corresponding contact surface, in the axial direction of the rotor shaft is equal to or shorter than the length of the platform portion. According to this configuration, the length of the blade root portion at the position where the contact surface is formed, including the corresponding contact surface, in the axial direction of the rotor shaft is equal to or less than the length of the platform portion. The interval can be narrowed more reliably.
- the two protrusions are composed of a first protrusion located on the upstream side in the flow direction of the working fluid and a second protrusion located on the downstream side, In the radial direction of the rotor shaft, at least the length of the first flange portion is shorter than the length from the outer peripheral surface of the rotor shaft to the outer peripheral surface of the first protrusion.
- the rotor shaft has a drum shape.
- the moving blade is a reaction blade.
- the number of paragraphs tends to increase compared to the case of an impulse blade.
- the interval between the moving blade rows in the axial direction of the rotor shaft can be narrowed, so that the increase in size of the turbine can be suppressed even if the number of paragraphs is large.
- the length of the blade root portion in the axial direction of the rotor shaft can be shortened, and the interval between the moving blade rows can be narrowed. . Therefore, in the turbine using this turbine rotor assembly, the number of paragraphs can be increased while suppressing an increase in size, or the size can be reduced if the number of paragraphs remains the same.
- the rotor blade for use in a turbine rotor assembly according to any one of the configurations (1) to (5).
- a turbine rotor assembly capable of reducing the interval between moving blade rows.
- FIG. 3 is a partially enlarged view schematically showing an enlarged part of FIG. 2.
- FIG. 4 is a diagram schematically illustrating an enlarged part of a rotor shaft and a moving blade in FIG. 3.
- an expression indicating that things such as “identical”, “equal”, and “homogeneous” are in an equal state not only represents an exactly equal state, but also has a tolerance or a difference that can provide the same function. It also represents the existing state.
- expressions representing shapes such as quadrangular shapes and cylindrical shapes represent not only geometrically strict shapes such as quadrangular shapes and cylindrical shapes, but also irregularities and chamfers as long as the same effects can be obtained. A shape including a part or the like is also expressed.
- the expressions “comprising”, “comprising”, “comprising”, “including”, or “having” one constituent element are not exclusive expressions for excluding the existence of the other constituent elements.
- FIG. 1 is a block diagram schematically showing the configuration of a power generation system according to an embodiment of the present invention.
- the power generation system is, for example, a thermal power generation system, and includes a boiler 1, a high pressure turbine 3, an intermediate pressure turbine 5, a low pressure turbine 7, and generators 9 and 11.
- the power generation system is, for example, a cross compound type, and the high pressure turbine 3 and the medium pressure turbine 5 are connected to the generator 9, while the two low pressure turbines 7 are connected to the generator 11.
- the power generation system is a tandem compound type in which the high-pressure turbine 3, the intermediate-pressure turbine 5, and the low-pressure turbine 7 are connected to one generator 9 through one shaft.
- the high-pressure turbine 3, the intermediate-pressure turbine 5, and the low-pressure turbine 7 are single-flow exhaust turbines.
- the high-pressure turbine and the intermediate-pressure turbine are constituted by a high-medium-pressure integrated turbine in which the high-pressure part and the intermediate-pressure part are housed in one vehicle compartment, and the power generation system is configured by combining the low-pressure turbine with the turbine. It is configured.
- the power generation system is configured by combining the high-pressure turbine 3, the intermediate-pressure turbine 5, and the low-pressure turbine 7 with an extra high-pressure turbine.
- the power generation system is a combined power generation system including a gas turbine. Further, in some embodiments, the power generation system is for private use, and in some embodiments, the power generation system is for business use.
- the boiler 1 burns, for example, coal as a fuel, and generates steam by using heat generated by the combustion.
- the boiler 1 includes an economizer 13, an evaporator 15, a superheater 17, and a reheater 19.
- the water is heated by the economizer 13, the evaporator 15 and the superheater 17, whereby superheated steam is obtained.
- the superheated steam is supplied to the high pressure turbine 3.
- the steam supplied to the high-pressure turbine 3 works in the high-pressure turbine 3, and then returns to the boiler 1 and is supplied to the reheater 19.
- the reheater 19 heats the steam, and the heated steam is supplied to the intermediate pressure turbine 5.
- the steam that has worked in the intermediate pressure turbine 5 is supplied to the low pressure turbine 7.
- the steam that has worked in the low-pressure turbine 7 is condensed in the condenser 21 to become water, and the obtained water is supplied again to the boiler 1 by the condensate pump 23.
- FIG. 2 is a longitudinal sectional view showing a schematic configuration of the intermediate pressure turbine 5.
- the intermediate pressure turbine 5 in FIG. 2 includes a housing (cabinet) 25 and a rotor shaft 27.
- the housing 25 surrounds an intermediate portion of the rotor shaft 27, and both end portions of the rotor shaft 27 are rotatably supported by radial bearings 29.
- the high-pressure turbine 3, the intermediate-pressure turbine 5, and the low-pressure turbine 7 have a multi-chamber type having separate housings, but the high-pressure turbine 3, the intermediate-pressure turbine 5, and the low-pressure turbine 7 are common. It may be of a single compartment type having a housing.
- a plurality of rotor blade rows 31 are fixed to the rotor shaft 27 so as to be separated from each other in the axial direction of the rotor shaft 27.
- a plurality of stationary blade rows 35 spaced from each other in the axial direction of the rotor shaft 27 are fixed to the housing 25 via blade rings 32 and 33.
- a cylindrical internal flow path 37 is formed between the blade rings 32 and 33 and the rotor shaft 27, and the stationary blade row 35 and the moving blade row 31 are arranged in the internal flow channel 37.
- Each stationary blade row 35 includes a plurality of stationary blades 39 arranged in the circumferential direction of the rotor shaft 27, and each stationary blade 39 is fixed to the blade rings 32 and 33.
- Each moving blade row 31 includes a plurality of moving blades (turbine moving blades) 41 arranged in the circumferential direction of the rotor shaft 27, and each moving blade 41 is fixed to the rotor shaft 27.
- the flow of steam is accelerated, and in each rotor blade row 31, the steam energy is converted into rotational energy of the rotor shaft 27.
- the housing 25 has a steam inlet 25a at the center in the axial direction of the rotor shaft 27 and two steam outlets 25b on both sides of the steam inlet 25a.
- the intermediate pressure turbine 5 is a double-flow exhaust turbine. It is. For this reason, in the housing 25, two internal flow paths 37 are formed in the axial direction of the rotor shaft 27 from the center toward the opposite sides.
- FIG. 3 schematically shows an enlarged part of FIG. Specifically, FIG. 3 schematically shows one moving blade 41 arranged between two stationary blades 39, 39 belonging to different stationary blade rows 35.
- the blade ring 32 has a blade groove 43 extending in the circumferential direction of the rotor shaft 27.
- the stationary blade 39 has a blade root portion 45, a blade profile portion 47, and a shroud portion 49 that are integrally formed with each other.
- the stationary blade 39 is fixed to the blade ring 32 by fitting the blade root portion 45 into the blade groove 43.
- a seal member 51 is attached to the shroud portion 49 of the stationary blade 39, and the seal member 51 closes a gap between the shroud portion 49 and the rotor shaft 27.
- the rotor shaft 27 is formed with blade grooves 53 extending along the circumferential direction of the rotor shaft 27.
- the moving blade 41 has a blade root portion 55, a blade profile portion 57, and a shroud portion 59 that are integrally formed with each other.
- the blade 41 is fixed to the rotor shaft 27 by fitting the blade root 55 into the blade groove 53.
- a seal member 61 is attached to a portion of the blade ring 32 facing the shroud portion 59 of the moving blade 41, and the seal member 61 closes a gap between the shroud portion 59 and the blade ring 32.
- the rotor shaft 27 and the plurality of rotor blades 41 fixed to the rotor shaft 27 are collectively referred to as a turbine rotor assembly.
- FIG. 4 shows a part of the rotor shaft 27 and the moving blade 41 in FIG. 3 in an enlarged manner.
- the rotor shaft 27 has two protrusions 63A and 63B corresponding to one blade groove 53.
- the protrusions 63A and 63B protrude outward from the outer peripheral surface 65 of the rotor shaft 27 in the radial direction of the rotor shaft 27, and extend from the axial center line of the rotor shaft 27 to the outer peripheral surface 71A of the protrusion 63A.
- the length in the radial direction of the rotor shaft 27 is equal to the length in the radial direction of the rotor shaft from the axial center line of the rotor shaft 27 to the outer peripheral surface 71B of the protrusion 63B.
- the protrusions 63A and 63B are separated from each other in the axial direction of the rotor shaft 27, and the protrusions 63A and 63B constitute a part of the wall surface of the blade groove 53 and the opening of the blade groove 53. .
- the rotor shaft 27 has two bearing surfaces 67A and 67B corresponding to one blade groove 53.
- the two bearing surfaces 67 ⁇ / b> A and 67 ⁇ / b> B are cylindrical surfaces provided on the inner side in the radial direction of the rotor shaft 27 with respect to the outer peripheral surface 65 of the rotor shaft 27, and are inward in the radial direction of the rotor shaft 27. It is suitable.
- the two bearing surfaces 67 ⁇ / b> A and 67 ⁇ / b> B are separated from each other in the axial direction of the rotor shaft 27 and constitute a part of the wall surface of the blade groove 53.
- the rotor shaft 27 has two first facing surfaces 69A and 69B corresponding to one blade groove 53.
- the two first facing surfaces 69A and 69B are positioned between the bearing surfaces 67A and 67B and the outer peripheral surfaces 71A and 71B of the protrusions 63A and 63B in the radial direction of the rotor shaft 27, respectively. It extends along the radial direction of the rotor shaft 27 from the inner end edges 73A and 73B of 67B.
- the two first facing surfaces 69 ⁇ / b> A and 69 ⁇ / b> B are annular surfaces that face each other in the axial direction of the rotor shaft 27, and constitute a part of the wall surface of the blade groove 53.
- the rotor shaft 27 has two second facing surfaces 75A and 75B corresponding to one blade groove 53.
- the two second opposing surfaces 75A and 75B are located between the bearing surfaces 67A and 67B and the outer peripheral surfaces 71A and 71B of the protrusions 63A and 63B in the radial direction of the rotor shaft 27, respectively, and two first opposing surfaces It is located outside the surfaces 69A and 69B.
- the second facing surfaces 75A and 75B are also annular surfaces that extend along the radial direction of the rotor shaft 27 and face each other in the axial direction of the rotor shaft 27, and the second facing surfaces 75A and 75B
- the interval L2 is larger than the interval L1 between the first facing surfaces 69A and 69B.
- 1st opposing surface 69A, 69B and 2nd opposing surface 75A, 75B are mutually connected via level
- the step surfaces 77A and 77B are cylindrical surfaces facing outward in the radial direction of the rotor shaft 27.
- the second facing surfaces 75A and 75B and the step surfaces 77A and 77B also constitute part of the wall surface of the blade groove 53.
- the rotor shaft 27 has a bottom surface 79 that forms the bottom of the blade groove 53, and the bottom surface 79 is a cylindrical surface that faces outward in the radial direction of the rotor shaft 27.
- 3rd opposing surface 81A, 81B which stands up from the both-ends edge of the bottom face 79 in the axial direction of the rotor shaft 27 is extended to the outer end edge of bearing surface 67A, 67B.
- the third facing surfaces 81 ⁇ / b> A and 81 ⁇ / b> B are also annular surfaces that extend along the radial direction of the rotor shaft 27 and face each other in the axial direction of the rotor shaft 27.
- the blade root portion 55 of the moving blade 41 has two contact surfaces 83A and 83B, two first side surfaces 85A and 85B, and two second side surfaces 87A and 87B.
- the blade root portion 55 has a head portion 89 corresponding to a T-shaped horizontal bar and a neck portion 91 corresponding to a T-shaped vertical rod, and the two contact surfaces 83A and 83B are one of the wall surfaces of the head 89.
- the two contact surfaces 83A and 83B face outward in the radial direction of the rotor shaft 27, and are separated from each other in the axial direction of the rotor shaft 27 with the neck portion 91 interposed therebetween.
- the two contact surfaces 83A and 83B can contact the two bearing surfaces 67A and 67B in the radial direction of the rotor shaft 27, respectively, and the moving blades in the radial direction of the rotor shaft 27 by the bearing surfaces 67A and 67B. 41 positions are determined.
- the two first side surfaces 85 ⁇ / b> A and 85 ⁇ / b> B constitute a part of the wall surface of the neck portion 91 and face outward in the axial direction of the rotor shaft 27.
- the two first side surfaces 85A and 85B are opposed to the two first opposing surfaces 69A and 69B with a gap, respectively.
- the two second side surfaces 87 ⁇ / b> A and 87 ⁇ / b> B also constitute part of the wall surface of the neck portion 91 and face outward in the axial direction of the rotor shaft 27.
- the two second side surfaces 87A and 87B are opposed to the two second facing surfaces 75A and 75B, respectively, with an interval smaller than the interval between the first opposing surfaces 69A and 69B and the first side surfaces 85A and 85B.
- the first side surfaces 85A and 85B and the second side surfaces 87A and 87B are fan-shaped surfaces parallel to the radial direction of the rotor shaft 27, and the second side surfaces 87A and 87B are the diameters of the rotor shaft 27 of the first side surfaces 85A and 85B. It is located outside in the direction.
- the first side surfaces 85A and 85B and the second side surfaces 87A and 87B are connected to each other via cylindrical step surfaces 93A and 93B facing inward in the radial direction of the rotor shaft 27.
- the neck portion 91 of the blade root portion 55 has flange portions 95A and 95B on the blade profile portion 57 side.
- the flange portions 95A and 95B are located next to the outer peripheral surfaces 71A and 71B of the two protrusions 63A and 63B in the radial direction of the rotor shaft 27, and are part of the platform portion 96 that supports the blade profile portion 57. It is composed.
- the rotor shaft 27 constitutes a part of the wall surface of the blade groove 53 in correspondence with the moving blade 41 having the first side surfaces 85A and 85B and the second side surfaces 87A and 87B.
- the first opposed surfaces 69A and 69B and the second opposed surfaces 75A and 75B are provided.
- the interval L1 between the first opposing surfaces 69A and 69B is smaller than the interval L2 between the second opposing surfaces 75A and 75B, and the contact surfaces 83A and 83B of the blade root portion 55 correspond to the difference between these intervals L1 and L2.
- the contact area between the bearing surfaces 67A and 67B of the rotor shaft 27 can be increased.
- the length of the head 89 of the blade root portion 55 in the axial direction of the rotor shaft 27 can be shortened, and the interval between the rotor blade rows 31 can be narrowed.
- the number of paragraphs can be increased while suppressing an increase in size, or downsizing can be achieved if the number of paragraphs remains the same.
- the protrusions 63A and 63B protrude from the outer peripheral surface 65 of the rotor shaft 27, the exposed area of the blade root portion 55 of the rotor blade 41 is small, and the adjacent rotor blades in the circumferential direction of the rotor shaft 27 The exposed area of the gap between the 41 blade root portions 55 can also be reduced. For this reason, the leakage flow of the working fluid can be reduced, and the efficiency of the intermediate pressure turbine 5 can be improved.
- the two blade portions 95A and 95B are provided on the blade profile portion 57 side of the blade root portion 55, and are formed as a part of the platform portion 96, so that the platform portion 96 that supports the blade profile portion 57 is largely formed.
- the turbine is equivalent to the width of the protrusions 63A and 63B (the length in the axial direction of the rotor shaft 27). It is not necessary to make the length of the paragraph large, or if the length of the turbine paragraph remains the same, it is not necessary to make the platform portion 96 (and thus the blade profile portion 57) small.
- the distance between the second facing surfaces 75A and 75B of the rotor shaft 27 and the second side surfaces 87A and 87B of the blade root portion 55 is set.
- the minimum gap required for implantation in the blade groove 53 formed in the circumferential direction of the rotor blade 41 is moved in the axial direction of the rotor shaft 27 of the rotor blade 41 or in the blade groove 53 of the rotor blade 41 during turbine operation. It is also possible to constrain the rotation (twisting) of the moving blade 41 and fix the rotor blade 41 to the blade groove 53.
- the rotor assembly for turbines of each embodiment described above can be applied not only to the intermediate pressure turbine 5 but also to the high pressure turbine 3 and the low pressure turbine 7.
- the length W of the head 89 of the blade root 55 in the axial direction of the rotor shaft 27 is 1.2 times or less the length S of the platform 96. According to this configuration, in the axial direction of the rotor shaft 27, the length W of the head 89 of the blade root portion 55 is 1.2 times or less the length S of the platform portion 96, thereby Can be reliably narrowed.
- the length W of the head 89 of the blade root 55 in the axial direction of the rotor shaft 27 is equal to or less than the length S of the platform 96. According to this configuration, in the axial direction of the rotor shaft 27, the length W of the head 89 of the blade root portion 55 is set to be equal to or shorter than the length S of the platform portion 96, so that the interval between the moving blade rows 31 is more reliably narrowed. can do.
- the length W of the head 89 of the blade root 55 in the axial direction of the rotor shaft 27 is 0.7 times or more the length S of the platform 96.
- the two protrusions 63A and 63B include the first protrusion 63A located on one side of the opening of the blade groove 53 in the axial direction of the rotor shaft 27 and the opening of the blade groove 53. It consists of the 2nd projection part 63B located in the other side.
- the blade root portion 55 of the rotor blade 41 includes a first flange portion 95 ⁇ / b> A disposed next to the outer peripheral surface 71 ⁇ / b> A of the first protrusion 63 ⁇ / b> A in the radial direction of the rotor shaft 27, and a second portion in the radial direction of the rotor shaft 27.
- the length of the first flange portion 95A is the length of the first protrusion 63A (the length from the outer peripheral surface 65A of the rotor shaft 27 to the outer peripheral surface 71A of the first protrusion 63A). Is shorter than
- the blade root portion 55 of the rotor blade 41 includes the first flange portion 95 ⁇ / b> A disposed next to the outer peripheral surface 71 ⁇ / b> A of the first protrusion 63 ⁇ / b> A in the radial direction of the rotor shaft 27, and the rotor shaft 27. And a second flange portion 95B disposed next to the outer peripheral surface 71B of the second protrusion 63B in the radial direction. In the radial direction of the rotor shaft 27, the length of the second flange 95B is the length of the second protrusion 63B (the length from the outer peripheral surface 65B of the rotor shaft 27 to the outer peripheral surface 71B of the second protrusion 63B). Is shorter than
- the outer diameter of the rotor shaft 27 on the outer peripheral surface 65A of the rotor shaft 27 located upstream in the steam flow direction is the rotor shaft on the outer peripheral surface 65B of the rotor shaft 27 located downstream in the steam flow direction. It is smaller than or equal to 27 outer diameter.
- each of the first flange portion 95A and the second flange portion 95B has outer surfaces 97A and 97B facing outward in the radial direction of the rotor shaft 27.
- the outer surface 97 ⁇ / b> A of the first flange part 95 ⁇ / b> A and the outer surface 97 ⁇ / b> B of the second flange part 95 ⁇ / b> B constitute part of a tapered surface that is inclined with respect to the axial direction of the rotor shaft 27.
- an inclined tapered surface is provided with R or chamfered.
- the moving blade 41 When the moving blade 41 is a reaction blade, the internal flow path 37 of the working fluid around the rotor shaft 27 gradually expands from upstream to downstream.
- the outer surfaces 97A and 97B of the first flange portion 95A and the second flange portion 95B form a tapered surface, so that the internal flow path 37 of the working fluid is gradually enlarged with a simple configuration. can do.
- the moving blade 41 When the moving blade 41 is a reaction blade, the number of paragraphs tends to increase compared to the case of an impulse blade.
- the interval between the rotor blade rows 31 in the axial direction of the rotor shaft 27 can be narrowed, so that the increase in the size of the intermediate pressure turbine 5 can be suppressed even if the number of paragraphs is large. it can.
- the outer surface 97A of the first flange portion 95A and / or the outer surface 97B of the second flange portion 95B are parallel to the axial direction of the rotor shaft 27. In some embodiments, a surface parallel to the axial direction is R or chamfered.
- At least a part of the cross section of the outer surface 97A of the first flange portion 95A and / or the outer surface 97B of the second flange portion 95B is a simple arc shape or a contour shape (multiple arcs and splines). It is configured.
- each of the outer surfaces 97A and 97B of the flange portions 95A and 95B is made parallel to the axial direction of the rotor shaft 27, or one is parallel to the axis of the rotor shaft 27 and the other is inclined, or
- a flow path having an arbitrary shape can be formed by combining at least a part of each cross-sectional shape with a simple arc shape or a contour shape.
- the rotor shaft 27 is drum-shaped.
- the moving blade 41 is a reaction blade.
- the number of paragraphs tends to increase compared to the case of an impulse blade.
- the interval between the rotor blade rows 31 in the axial direction of the rotor shaft 27 can be narrowed, so that the increase in the size of the intermediate pressure turbine 5 can be suppressed even if the number of paragraphs is large. it can.
- the blade groove 53 is a perforation formed by using a cutting tool from the outer peripheral surface 65 of the rotor shaft 27 toward the inside, and has a T-shaped cross section perpendicular to the circumferential direction. Has a shape.
- the moving blade 41 has the blade root part 55 fitted to the blade groove
- the rotor shaft 27 includes a rotor shaft radial perforation surface extending in the radial direction of the rotor shaft 27 and a rotor shaft outer peripheral surface side perforation surface extending in the axial direction of the rotor shaft 27 that respectively define the blade grooves 53.
- the rotor shaft radial direction drilling surfaces are first opposing surfaces 69A and 69B, and the rotor shaft outer peripheral surface side drilling surfaces are bearing surfaces 67A and 67B.
- the protrusions 63A and 63B protrude in the radial direction of the rotor shaft 27, and the protrusions 63A and 63B are separated from each other in the axial direction of the rotor shaft 27. It has an inner annular surface and a rotor shaft radial top outer peripheral surface located outside in the radial direction of the rotor shaft 27.
- the rotor shaft radial inner ring surfaces are second opposing surfaces 75A and 75B, and the rotor shaft radial top outer circumferential surfaces are outer circumferential surfaces 71A and 71B.
- the rotor blade 41 includes first side surfaces 85A and 85B that face the rotor shaft radial direction drilling surface, contact surfaces 83A and 83B that can contact the rotor shaft outer circumferential surface side drilling surface, and a rotor shaft radial inner annular surface. Opposite second side surfaces 87A and 87B, and a jaw portion that is positioned next to the outer circumferential surface of the top portion in the rotor axial direction and that forms the platform portion 96 of the rotor blade 41. The jaws are the buttocks 95A and 95B.
- the present invention is not limited to the above-described embodiments, and includes forms obtained by modifying the above-described embodiments and forms obtained by appropriately combining these forms.
- the thickness can also be formed with different dimensions.
- the length from the outer peripheral surface 65A of the rotor shaft 27 to the outer peripheral surface 71A of the first protrusion 63A and the outer peripheral surface of the second protrusion 63B from the outer peripheral surface 65B of the rotor shaft 27 can be the same, or either one can be longer than the other.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
タービン動翼には、T形の翼根部を有するものがある。翼根部は、ロータ軸に設けられた翼溝に嵌合され、これによりタービン動翼がロータ軸に固定される。翼溝もまた、翼根部の形状に対応したT形の横断面形状を有している。タービンの運転中、タービン動翼には遠心力が作用し、ロータ軸の径方向にて外方を向いた翼根部の当接面が、ロータ軸の径方向にて内方を向いたロータ軸のベアリング面と当接する。
また、日本国特開平7-63004号公報が開示するタービン動翼では、翼根部の前記首部の一端がロータ軸の外周面からロータ軸の径方向にて外方に延びて、その部位は、ロータ軸の軸方向長さが翼溝内の前記首部の幅より大きく形成され、そこが、翼プロフィル部を支持するプラットホーム部となっている。
しかしながら、日本国特開平7-63004号公報が開示するタービン動翼及びロータ円板を用いた場合、ロータ軸の軸線方向での段落の長さを短縮することは困難である。なぜならば、翼根部の首部に段差を設けた関係上(日本国特開平7-63004号公報の図1、図7参照)、翼溝の横断面形状がT形のままであれば、ロータ軸のベアリング面と翼根部の当接面との間の接触面積を十分に確保するために、翼根部の当接面を日本国特開平7-63004号公報の図1の(W1-W)分ほどロータ軸の軸線方向に延長しなければならないからである。
周方向に沿って延びる翼溝が形成されたロータ軸と、
前記ロータ軸の径方向にて前記ロータ軸の外側に配置される翼プロフィル部及び前記翼プロフィル部と一体に設けられて前記翼溝に嵌合された翼根部をそれぞれ有する複数の動翼と、を備え、
前記ロータ軸は、
それぞれ前記ロータ軸の外周面から前記ロータ軸の径方向にて外方に向かって突出するとともに前記ロータ軸の軸線方向にて相互に離間し、前記翼溝の壁面の一部及び前記翼溝の開口を構成する2つの突起部と、
それぞれ前記ロータ軸の外周面よりも前記ロータ軸の径方向にて内側に設けられるとともに前記ロータ軸の径方向にて内方を向き、前記ロータ軸の軸線方向に相互に離間して前記翼溝の壁面の一部を構成する2つのベアリング面と、
それぞれ前記ロータ軸の径方向にて前記ベアリング面と前記突起部の外周面との間に位置し、前記ロータ軸の軸線方向にて相互に対向して前記翼溝の壁面の一部を構成する2つの第1対向面と、
それぞれ前記ロータ軸の径方向にて前記ベアリング面と前記突起部の外周面との間に位置するとともに前記2つの第1対向面よりも外側に位置し、前記第1対向面同士の間隔よりも大きな間隔を存して前記ロータ軸の軸線方向にて相互に対向して前記翼溝の壁面の一部を構成する2つの第2対向面とを有し、
前記動翼の翼根部は、
前記ロータ軸の軸線方向にて相互に離間するとともに前記ロータ軸の径方向にて前記2つのベアリング面とそれぞれ当接可能な2つの当接面と、
前記2つの第1対向面とそれぞれ対向する2つの第1側面と、
前記第1対向面と前記第1側面との間隔よりも小さい間隔を存して前記2つの第2対向面とそれぞれ対向する2つの第2側面と、
前記動翼の翼根部が前記ロータ軸に形成された前記翼溝に組み付けられたときに、前記ロータ軸の径方向にて前記2つの突起部それぞれの外周面の隣に位置し、前記翼プロフィル部に連なるプラットホーム部の一部となる2つの鍔部とを有する。
この結果として、このタービン用ロータアセンブリを用いたタービンでは、大型化を抑えながら段落数を増やすことができ、或いは、同じ段落数のままであれば小型化を図ることができる。
また、第2対向面が、翼根部の第2側面に対向し、ロータ軸の外周面からロータ軸の径方向にて外方に延びた翼根部の一部を覆い、露出部分を減らして、隣り合う翼根部間の隙間からの作動流体の漏れを低減することができる。
さらにまた、翼根部に、それを翼溝に組み付けたときに、ロータ軸の径方向にて2つの突起部それぞれの外周面の隣に位置することとなる2つの鍔部を設け、その鍔部を含めてプラットホーム部としたことにより、翼プロフィル部を支持するプラットホーム部を大きく形成することができる。
ロータ軸の径方向にて突起部の外側にプラットホーム部の一部を配置したことにより、突起部の幅(ロータ軸の軸線方向の長さ)の分だけタービン段落の長さを大きく形成する必要はなく、あるいは、タービン段落の長さはそのままであれば、プラットホーム部を(延いては翼プロフィル部を)小さく形成する必要はない。
前記当接面を形成する位置における前記翼根部の、該当接面を含めた、前記ロータ軸の軸線方向での長さは前記プラットホーム部の長さの1.2倍以下である。
この構成によれば、当接面を形成する位置における翼根部の、該当接面を含めた、ロータ軸の軸線方向での長さをプラットホーム部の長さの1.2倍以下にすることで、動翼列の間隔を確実に狭くすることができる。
前記当接面を形成する位置における前記翼根部の、該当接面を含めた、前記ロータ軸の軸線方向での長さは前記プラットホーム部の長さ以下である。
この構成によれば、当接面を形成する位置における翼根部の、該当接面を含めた、ロータ軸の軸線方向での長さをプラットホーム部の長さ以下にすることで、動翼列の間隔をより確実に狭くすることができる。
前記2つの突起部は、作動流体の流れ方向にて上流側に位置する第1の突起部と、下流側に位置する第2の突起部とからなり、
前記ロータ軸の径方向において、少なくとも前記第1鍔部の長さは、前記ロータ軸の外周面から前記第1の突起部の外周面までの長さよりも短い。
この結果として、このタービン用ロータアセンブリを用いたタービンでは、効率を高めることができる。
前記ロータ軸はドラム形である。
一般的に、ロータ軸がドラム形である場合、動翼は反動翼である。動翼が反動翼の場合、衝動翼の場合に比べて段落数が多くなる傾向がある。この点、上記構成によれば、ロータ軸の軸線方向での動翼列の間隔を狭くすることができるので、段落数が多くても、タービンの大型化を抑制することができる。
上記構成(1)乃至(5)の何れか1つのタービン用ロータアセンブリと、
前記タービン用ロータアセンブリを囲むハウジングと、
前記ハウジングに取り付けられた複数の静翼と
を備えるタービンが提供される。
(8)本発明の少なくとも一実施形態に係る動翼は、
ロータ軸の外周面から内部へ穿孔される周方向断面T字状の翼溝に周方向へ嵌合される翼根部がT字形状を有する動翼であって、
前記動翼は、
前記翼溝を規定する前記ロータ軸の径方向に延びる2つのロータ軸径方向穿孔面とそれぞれ対向する2つの第1側面と、
前記翼溝を規定する前記ロータ軸の軸方向に延び、ベアリング面となるロータ軸外周面側穿孔面(=ベアリング面)と当接可能な当接面と、
前記ロータ軸の外周面から前記ロータ軸の径方向に突出する突起部の、ロータ軸の軸線方向にて相互に離間し前記翼溝のロータ軸径方向の壁面の一部を構成する、2つのロータ軸径方向環状面(=第2対向面)とそれぞれ対向し、それら間隔が、前記2つの第1側面間の間隔より大きい2つの第2側面と、
前記突起部の、ロータ軸の径方向にて外側に位置するロータ軸径方向頂部外周面の隣に位置し、前記動翼のプラットホーム部を形成する顎部とを有する。
例えば、「ある方向に」、「ある方向に沿って」、「平行」、「直交」、「中心」、「同心」或いは「同軸」等の相対的或いは絶対的な配置を表す表現は、厳密にそのような配置を表すのみならず、公差、若しくは、同じ機能が得られる程度の角度や距離をもって相対的に変位している状態も表すものとする。
例えば、「同一」、「等しい」及び「均質」等の物事が等しい状態であることを表す表現は、厳密に等しい状態を表すのみならず、公差、若しくは、同じ機能が得られる程度の差が存在している状態も表すものとする。
例えば、四角形状や円筒形状等の形状を表す表現は、幾何学的に厳密な意味での四角形状や円筒形状等の形状を表すのみならず、同じ効果が得られる範囲で、凹凸部や面取り部等を含む形状も表すものとする。
一方、一の構成要素を「備える」、「具える」、「具備する」、「含む」、又は、「有する」という表現は、他の構成要素の存在を除外する排他的な表現ではない。
幾つかの実施形態では、発電システムは、高圧タービン3、中圧タービン5及び低圧タービン7が1つの軸を介して一つの発電機9に接続されたタンデムコンパウンド形式である。
幾つかの実施形態では、高圧タービン及び中圧タービンは、高圧部と中圧部とを1個の車室に納めた高中圧一体型のタービンによって構成され、それに低圧タービンを組み合わせて発電システムが構成されている。幾つかの実施形態では、高圧タービン3、中圧タービン5、低圧タービン7に、さらに超高圧タービンを組み合わせて発電システムが構成されている。
また幾つかの実施形態では、発電システムは、ガスタービンを含む複合発電システムである。更に、幾つかの実施形態では、発電システムは自家用であり、幾つかの実施形態では、発電システムは事業用である。
例えば、ボイラ1は、エコノマイザ13、蒸発器15、過熱器17、及び、再熱器19を有する。水は、エコノマイザ13、蒸発器15及び過熱器17により加熱され、これにより過熱蒸気が得られる。過熱蒸気は、高圧タービン3に供給される。高圧タービン3に供給された蒸気は、高圧タービン3で仕事をした後、ボイラ1に一度戻されて再熱器19に供給される。再熱器19は、蒸気を加熱し、加熱された蒸気が中圧タービン5に供給される。そして、中圧タービン5で仕事をした蒸気は、低圧タービン7に供給される。低圧タービン7で仕事をした蒸気は、復水器21で凝縮させられて水になり、得られた水は、復水ポンプ23によって、ボイラ1に再び供給される。
図2の中圧タービン5は、ハウジング(車室)25と、ロータ軸27とを備えている。ハウジング25はロータ軸27の中間部を囲んでおり、ロータ軸27の両端部が、ラジアル軸受29によって回転可能に支持されている。
なお、発電システムは、高圧タービン3、中圧タービン5及び低圧タービン7が、相互に別体のハウジングを有する複車室形であるが、高圧タービン3、中圧タービン5及び低圧タービン7が共通のハウジングを有する単車室形であってもよい。
図3に示したように、翼環32はロータ軸27の周方向に延びる翼溝43を有する。一方、静翼39は、相互に一体に形成された翼根部45、翼プロフィル部47及びシュラウド部49を有する。翼根部45が翼溝43に嵌合されることにより、静翼39は翼環32に固定される。なお、静翼39のシュラウド部49には、シール部材51が取り付けられ、シール部材51は、シュラウド部49とロータ軸27との間の隙間を閉塞している。
なお、本明細書では、ロータ軸27と、ロータ軸27に固定された複数の動翼41をまとめてタービン用ロータアセンブリとも称する。
ロータ軸27は、1つの翼溝53に対応して2つの突起部63A,63Bを有する。突起部63A,63Bは、それぞれロータ軸27の外周面65からロータ軸27の径方向にて外方に向かって突出しており、ロータ軸27の軸中心線から突起部63Aの外周面71Aまでのロータ軸27の径方向の長さと、ロータ軸27の軸中心線から突起部63Bの外周面71Bまでのロータ軸の径方向の長さとは等しい。突起部63A,63Bは、ロータ軸27の軸線方向にて相互に離間しており、そして、突起部63A,63Bは、翼溝53の壁面の一部及び翼溝53の開口を構成している。
翼根部55は、T字の横棒に相当する頭部89と、T字の縦棒に相当する首部91とを有し、2つの当接面83A,83Bは、頭部89の壁面の一部を構成している。2つの当接面83A,83Bは、それぞれロータ軸27の径方向にて外方を向き、首部91を挟んでロータ軸27の軸線方向にて相互に離間している。2つの当接面83A,83Bは、ロータ軸27の径方向にて2つのベアリング面67A,67Bとそれぞれ当接可能であり、ベアリング面67A,67Bによって、ロータ軸27の径方向での動翼41の位置が決定される。
2つの第2側面87A,87Bもまた首部91の壁面の一部を構成し、ロータ軸27の軸線方向にて外方を向いている。2つの第2側面87A,87Bは、第1対向面69A,69Bと第1側面85A,85Bとの間隔よりも小さい間隔を存して、2つの第2対向面75A,75Bとそれぞれ対向する。
第1側面85A,85B及び第2側面87A,87Bは、ロータ軸27の径方向に平行な扇形の面であり、第2側面87A,87Bは、第1側面85A,85Bのロータ軸27の径方向にて外側に位置している。そして、第1側面85A,85Bと第2側面87A,87Bは、ロータ軸27の径方向にて内方を向いた円筒状の段差面93A,93Bを介して相互に繋がっている。
さらに、翼根部55の首部91は、その翼プロフィル部57側に、鍔部95A,95Bを有する。鍔部95A,95Bは、ロータ軸27の径方向にて前記2つの突起部63A,63Bそれぞれの外周面71A,71Bの隣に位置し、翼プロフィル部57を支持するプラットホーム部96の一部を構成している。
この結果として、このタービン用ロータアセンブリを用いた中圧タービン5では、大型化を抑えながら段落数を増やすことができ、或いは、同じ段落数のままであれば小型化を図ることができる。
また、この構成では、翼根部55の翼プロフィル部57側に2つの鍔部95A,95Bを設け、プラットホーム部96の一部としたことにより、翼プロフィル部57を支持するプラットホーム部96を大きく形成することができる。
ロータ軸27の径方向にて突起部63A、63Bの外側にプラットホーム部96の一部を配置したことにより、突起部63A、63Bの幅(ロータ軸27の軸線方向の長さ)の分だけタービン段落の長さを大きく形成する必要はなく、あるいは、タービン段落の長さはそのままであれば、プラットホーム部96を(延いては翼プロフィル部57を)小さく形成する必要はない。
一方で、この構成では、振動振幅が大きくならない限り、翼根部55はベアリング面67A,67Bによってのみ安定して拘束される。このため、中圧タービン5の運転中、動翼41の振動数が安定する。
なお、上述した各実施形態のタービン用ロータアセンブリは、中圧タービン5のみならず、高圧タービン3や低圧タービン7にも適用可能である。
動翼41の翼根部55は、ロータ軸27の径方向にて第1の突起部63Aの外周面71Aの隣に配置される第1鍔部95Aと、ロータ軸27の径方向にて第2の突起部63Bの外周面71Bの隣に配置される第2鍔部95Bとを有する。そして、ロータ軸27の径方向において、第1鍔部95Aの長さは第1の突起部63Aの長さ(ロータ軸27の外周面65Aから第1の突起部63Aの外周面71Aまでの長さ)よりも短い。
この結果として、このタービン用ロータアセンブリを用いた中圧タービン5では、効率を高めることができる。
動翼41が反動翼の場合、衝動翼の場合に比べて段落数が多くなる傾向がある。この点、上記構成によれば、ロータ軸27の軸線方向での動翼列31の間隔を狭くすることができるので、段落数が多くても、中圧タービン5の大型化を抑制することができる。
一般的に、ロータ軸27がドラム形である場合、動翼41は反動翼である。動翼41が反動翼の場合、衝動翼の場合に比べて段落数が多くなる傾向がある。この点、上記構成によれば、ロータ軸27の軸線方向での動翼列31の間隔を狭くすることができるので、段落数が多くても、中圧タービン5の大型化を抑制することができる。
例えば、ロータ軸27の軸中心線から突起部63Aの外周面71Aまでのロータ軸の径方向長さと、ロータ軸27の軸中心線から突起部63Bの外周面71Bまでのロータ軸の径方向長さを異なる寸法で形成することもできる。
また、ロータ軸27の径方向にて、ロータ軸27の外周面65Aから第1の突起部63Aの外周面71Aまでの長さとロータ軸27の外周面65Bから第2の突起部63Bの外周面71Bまでの長さは、同一とすることも、あるいはいずれか一方を他方より長く形成することもできる。
3 高圧タービン
5 中圧タービン
7 低圧タービン
9,11 発電機
13 エコノマイザ
15 蒸発器
17 過熱器
19 再熱器
21 復水器
23 復水ポンプ
25 ハウジング(車室)
25a 蒸気入口
25b 蒸気出口
27 ロータ軸
29 ラジアル軸受
31 動翼列
32,33 翼環
35 静翼列
37 内部流路
39 静翼
41 動翼
43 翼溝
45 翼根部
47 翼プロフィル部
49 シュラウド部
51 シール部材
53 翼溝
55 翼根部
57 翼プロフィル部
59 シュラウド部
61 シール部材
63A 突起部(第1の突起部)
63B 突起部(第2の突起部)
65(65A,65B) 外周面
67A,67B ベアリング面
69A,69B 第1対向面
71A,71B 外周面
73A,73B 内端縁
75A,75B 第2対向面
77A,77B 段差面
79 底面
81A,81B 第3対向面
83A,83B 当接面
85A,85B 第1側面
87A,87B 第2側面
89 頭部
91 首部
93A,93B 段差面
95A 第1鍔部
95B 第2鍔部
96 プラットホーム部
97A,97B 外面
Claims (8)
- 周方向に沿って延びる翼溝が形成されたロータ軸と、
前記ロータ軸の径方向にて前記ロータ軸の外側に配置される翼部及び前記翼部と一体に設けられて前記翼溝に嵌合された翼根部をそれぞれ有する複数の動翼と、
を備え、
前記ロータ軸は、
それぞれ前記ロータ軸の外周面から前記ロータ軸の径方向にて外方に向かって突出するとともに前記ロータ軸の軸線方向にて相互に離間し、前記翼溝の壁面の一部及び前記翼溝の開口を構成する2つの突起部と、
それぞれ前記ロータ軸の外周面よりも前記ロータ軸の径方向にて内側に設けられるとともに前記ロータ軸の径方向にて内方を向き、前記ロータ軸の軸線方向に相互に離間して前記翼溝の壁面の一部を構成する2つのベアリング面と、
それぞれ前記ロータ軸の径方向にて前記ベアリング面と前記突起部の外周面との間に位置し、前記ロータ軸の軸線方向にて相互に対向して前記翼溝の壁面の一部を構成する2つの第1対向面と、
それぞれ前記ロータ軸の径方向にて前記ベアリング面と前記突起部の外周面との間に位置するとともに前記2つの第1対向面よりも外側に位置し、前記第1対向面同士の間隔よりも大きな間隔を存して前記ロータ軸の軸線方向にて相互に対向して前記翼溝の壁面の一部を構成する2つの第2対向面とを有し、
前記動翼の翼根部は、
前記ロータ軸の軸線方向にて相互に離間するとともに前記ロータ軸の径方向にて前記2つのベアリング面とそれぞれ当接可能な2つの当接面と、
前記2つの第1対向面とそれぞれ対向する2つの第1側面と、
前記第1対向面と前記第1側面との間隔よりも小さい間隔を存して前記2つの第2対向面とそれぞれ対向する2つの第2側面と、
前記動翼の翼根部が前記ロータ軸に形成された前記翼溝に組み付けられたときに、前記ロータ軸の径方向にて、前記2つの突起部それぞれの外周面の隣に位置し、前記翼プロフィル部に連なるプラットホーム部の一部となる2つの鍔部とを有する
ことを特徴とするタービン用ロータアセンブリ。 - 前記当接面を形成する位置における前記翼根部の、該当接面を含めた、前記ロータ軸の軸線方向での長さは前記プラットホーム部の長さの1.2倍以下であることを特徴とする請求項1に記載のタービン用ロータアセンブリ。
- 前記当接面を形成する位置における前記翼根部の、該当接面を含めた、前記ロータ軸の軸線方向での長さは前記プラットホーム部の長さ以下であることを特徴とする請求項2に記載のタービン用ロータアセンブリ。
- 前記2つの突起部は、作動流体の流れ方向にて上流側に位置する第1の突起部と、下流側に位置する第2の突起部とからなり、
前記動翼は、前記ロータ軸の径方向にて前記第1の突起部の外周面の隣に配置される第1鍔部と、前記ロータ軸の径方向にて前記第2の突起部の外周面の隣に配置される第2鍔部とを有し、
前記ロータ軸の径方向において、少なくとも前記第1鍔部の長さは、前記ロータ軸の外周面から前記第1の突起部の外周面までの長さよりも短いことを特徴とする請求項1乃至3の何れか1項に記載のタービン用ロータアセンブリ。 - 前記ロータ軸はドラム形であることを特徴とする請求項1乃至4の何れか1項に記載のタービン用ロータアセンブリ。
- 請求項1乃至5の何れか1項に記載のタービン用ロータアセンブリと、
前記タービン用ロータアセンブリを囲むハウジングと、
前記ハウジングに取り付けられた複数の静翼と
を備えることを特徴とするタービン。 - 請求項1乃至5の何れか1項に記載のタービン用ロータアセンブリに用いられることを特徴とする動翼。
- ロータ軸の外周面から内部へ穿孔される周方向断面T字状の翼溝に周方向へ嵌合される翼根部がT字形状を有する動翼であって、
前記動翼は、
前記翼溝を規定する前記ロータ軸の径方向に延びる2つのロータ軸径方向穿孔面とそれぞれ対向する2つの第1側面と、
前記翼溝を規定する前記ロータ軸の軸方向に延び、ベアリング面となるロータ軸外周面側穿孔面と当接可能な当接面と、
前記ロータ軸の外周面から前記ロータ軸径方向に突出する突起部の、ロータ軸の軸線方向にて相互に離間し、前記翼溝のロータ軸径方向の壁面の一部を構成する2つのロータ軸径方向内側環状面とそれぞれ対向し、それら間隔が、前記2つの第1側面間の間隔より大きい2つの第2側面と、
前記突起部の、ロータ軸の径方向にて外側に位置するロータ軸径方向頂部外周面の隣に位置し、前記動翼のプラットホーム部を形成する顎部とを有する
ことを特徴とする動翼。
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE112015005132.5T DE112015005132T5 (de) | 2014-11-12 | 2015-11-11 | Turbinenrotoraufbau, Turbine und Rotorschaufel |
KR1020177008302A KR101935185B1 (ko) | 2014-11-12 | 2015-11-11 | 터빈용 로터 어셈블리, 터빈, 및 동익 |
CN201580043835.8A CN106574503B (zh) | 2014-11-12 | 2015-11-11 | 涡轮用转子装配体、涡轮以及动叶 |
US15/506,896 US10557355B2 (en) | 2014-11-12 | 2015-11-11 | Turbine rotor assembly, turbine, and rotor blade |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2014229788A JP6434780B2 (ja) | 2014-11-12 | 2014-11-12 | タービン用ロータアセンブリ、タービン、及び、動翼 |
JP2014-229788 | 2014-11-12 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2016076374A1 true WO2016076374A1 (ja) | 2016-05-19 |
Family
ID=55954452
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/JP2015/081793 WO2016076374A1 (ja) | 2014-11-12 | 2015-11-11 | タービン用ロータアセンブリ、タービン、及び、動翼 |
Country Status (6)
Country | Link |
---|---|
US (1) | US10557355B2 (ja) |
JP (1) | JP6434780B2 (ja) |
KR (1) | KR101935185B1 (ja) |
CN (1) | CN106574503B (ja) |
DE (1) | DE112015005132T5 (ja) |
WO (1) | WO2016076374A1 (ja) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP7051656B2 (ja) * | 2018-09-28 | 2022-04-11 | 三菱重工コンプレッサ株式会社 | タービンステータ、蒸気タービン、及び仕切板 |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH01131801U (ja) * | 1988-03-03 | 1989-09-07 | ||
JPH0763004A (ja) * | 1993-08-23 | 1995-03-07 | Mitsubishi Heavy Ind Ltd | タービン動翼 |
JP2014040829A (ja) * | 2012-08-22 | 2014-03-06 | General Electric Co <Ge> | 一体回転制御特徴要素を備えたタービンバケット |
Family Cites Families (23)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB359350A (en) * | 1930-03-03 | 1931-10-22 | Ltd Co Formerly Skoda Works | Connection of rotarys for combustion turbines |
US2295012A (en) * | 1941-03-08 | 1942-09-08 | Westinghouse Electric & Mfg Co | Turbine blading |
US2809801A (en) * | 1952-04-18 | 1957-10-15 | Ingersoll Rand Co | Turbine rotor construction |
JPS54145806A (en) | 1978-05-04 | 1979-11-14 | Toyota Motor Corp | Two-cycle engine |
JPS61212603A (ja) * | 1985-03-16 | 1986-09-20 | Hitachi Zosen Corp | タ−ビン翼車 |
JPS63168201A (ja) | 1986-12-29 | 1988-07-12 | Kawasaki Steel Corp | H形鋼の粗ユニバ−サル圧延機 |
JPH01131801A (ja) | 1987-11-16 | 1989-05-24 | Toshiba Corp | 脱気器器内圧力制御装置 |
FR2644524A1 (fr) * | 1989-03-15 | 1990-09-21 | Snecma | Aubes a pied marteau a positionnement angulaire ameliore |
GB2265671A (en) * | 1992-03-24 | 1993-10-06 | Rolls Royce Plc | Bladed rotor for a gas turbine engine |
US5271718A (en) * | 1992-08-11 | 1993-12-21 | General Electric Company | Lightweight platform blade |
JPH10184307A (ja) | 1996-12-25 | 1998-07-14 | Mitsubishi Heavy Ind Ltd | タービンの動翼 |
JPH10299406A (ja) * | 1997-04-21 | 1998-11-10 | Mitsubishi Heavy Ind Ltd | 動 翼 |
US6375429B1 (en) | 2001-02-05 | 2002-04-23 | General Electric Company | Turbomachine blade-to-rotor sealing arrangement |
CN2653132Y (zh) * | 2002-06-25 | 2004-11-03 | 哈尔滨汽轮机厂有限责任公司 | 汽轮机装配式隔板 |
DE10305912B4 (de) * | 2003-02-13 | 2014-01-30 | Alstom Technology Ltd. | Hybrid- Schaufel für thermische Turbomaschinen |
US8167566B2 (en) * | 2008-12-31 | 2012-05-01 | General Electric Company | Rotor dovetail hook-to-hook fit |
JP4929316B2 (ja) * | 2009-07-13 | 2012-05-09 | 三菱重工業株式会社 | 回転体 |
US8517688B2 (en) | 2010-09-21 | 2013-08-27 | General Electric Company | Rotor assembly for use in turbine engines and methods for assembling same |
US8662826B2 (en) | 2010-12-13 | 2014-03-04 | General Electric Company | Cooling circuit for a drum rotor |
US8899933B2 (en) | 2012-01-03 | 2014-12-02 | General Electric Company | Rotor blade mounting |
US9347326B2 (en) | 2012-11-02 | 2016-05-24 | General Electric Company | Integral cover bucket assembly |
US20140182293A1 (en) * | 2012-12-31 | 2014-07-03 | United Technologies Corporation | Compressor Rotor for Gas Turbine Engine With Deep Blade Groove |
DE102014101852A1 (de) * | 2013-02-25 | 2014-08-28 | General Electric Company | Rotortrommel-Schwalbenschwanzbauteil und zugehöriges Rotortrommelsystem |
-
2014
- 2014-11-12 JP JP2014229788A patent/JP6434780B2/ja active Active
-
2015
- 2015-11-11 KR KR1020177008302A patent/KR101935185B1/ko active IP Right Grant
- 2015-11-11 CN CN201580043835.8A patent/CN106574503B/zh active Active
- 2015-11-11 WO PCT/JP2015/081793 patent/WO2016076374A1/ja active Application Filing
- 2015-11-11 US US15/506,896 patent/US10557355B2/en active Active
- 2015-11-11 DE DE112015005132.5T patent/DE112015005132T5/de active Pending
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH01131801U (ja) * | 1988-03-03 | 1989-09-07 | ||
JPH0763004A (ja) * | 1993-08-23 | 1995-03-07 | Mitsubishi Heavy Ind Ltd | タービン動翼 |
JP2014040829A (ja) * | 2012-08-22 | 2014-03-06 | General Electric Co <Ge> | 一体回転制御特徴要素を備えたタービンバケット |
Also Published As
Publication number | Publication date |
---|---|
DE112015005132T5 (de) | 2017-08-10 |
KR20170046169A (ko) | 2017-04-28 |
KR101935185B1 (ko) | 2019-01-03 |
US10557355B2 (en) | 2020-02-11 |
JP6434780B2 (ja) | 2018-12-05 |
CN106574503B (zh) | 2018-09-11 |
US20170284209A1 (en) | 2017-10-05 |
JP2016094842A (ja) | 2016-05-26 |
CN106574503A (zh) | 2017-04-19 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
JP6408888B2 (ja) | タービンバケット閉鎖組立体及びその組立方法 | |
JP6152266B2 (ja) | 先端シュラウドを一列に並べる装置 | |
JP5085987B2 (ja) | タービンを組立てる方法及びシステム | |
JP5972374B2 (ja) | 軸流流体機械 | |
JP2011140945A (ja) | 蒸気タービン静止部品シール | |
US9347326B2 (en) | Integral cover bucket assembly | |
EP3190267B1 (en) | Structure for multi-stage sealing of turbine | |
JP2013241932A (ja) | 間隙制御能力を有するターボ機械およびそのシステム | |
JP2011140943A (ja) | 逆圧力勾配シール機構 | |
JP6712873B2 (ja) | シール構造及びターボ機械 | |
JP6096639B2 (ja) | 回転機械 | |
JP7187464B2 (ja) | タービンの先端バランススリット | |
JP6506533B2 (ja) | タービンノズルを固定する方法及びシステム | |
US7866949B2 (en) | Methods and apparatus for fabricating a rotor for a steam turbine | |
JP6434780B2 (ja) | タービン用ロータアセンブリ、タービン、及び、動翼 | |
JP2009191850A (ja) | 蒸気タービンエンジンとその組立方法 | |
JP6521273B2 (ja) | 蒸気タービン | |
US20130034445A1 (en) | Turbine bucket having axially extending groove | |
EP2514928B1 (en) | Compressor inlet casing with integral bearing housing | |
JP7349248B2 (ja) | 回転機械、及びシールリング | |
JP6833598B2 (ja) | ノズルダイアフラム、蒸気タービン | |
US20140037439A1 (en) | Turbomachine exhaust diffuser | |
KR20190108637A (ko) | 터빈을 변형하는 방법 | |
JP5956086B2 (ja) | 軸流タービン | |
JP5909081B2 (ja) | ターボ機械のシーリング組立体及びその組立方法 |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
121 | Ep: the epo has been informed by wipo that ep was designated in this application |
Ref document number: 15858500 Country of ref document: EP Kind code of ref document: A1 |
|
WWE | Wipo information: entry into national phase |
Ref document number: 15506896 Country of ref document: US |
|
ENP | Entry into the national phase |
Ref document number: 20177008302 Country of ref document: KR Kind code of ref document: A |
|
WWE | Wipo information: entry into national phase |
Ref document number: 112015005132 Country of ref document: DE |
|
122 | Ep: pct application non-entry in european phase |
Ref document number: 15858500 Country of ref document: EP Kind code of ref document: A1 |