WO2012128310A1 - タービンロータ及びタービンロータの製造方法 - Google Patents
タービンロータ及びタービンロータの製造方法 Download PDFInfo
- Publication number
- WO2012128310A1 WO2012128310A1 PCT/JP2012/057303 JP2012057303W WO2012128310A1 WO 2012128310 A1 WO2012128310 A1 WO 2012128310A1 JP 2012057303 W JP2012057303 W JP 2012057303W WO 2012128310 A1 WO2012128310 A1 WO 2012128310A1
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- WIPO (PCT)
- Prior art keywords
- turbine rotor
- members
- hardness member
- welding
- high hardness
- Prior art date
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Classifications
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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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
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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
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K31/00—Processes relevant to this subclass, specially adapted for particular articles or purposes, but not covered by only one of the preceding main groups
- B23K31/02—Processes relevant to this subclass, specially adapted for particular articles or purposes, but not covered by only one of the preceding main groups relating to soldering or welding
- B23K31/027—Making tubes with soldering or welding
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K33/00—Specially-profiled edge portions of workpieces for making soldering or welding connections; Filling the seams formed thereby
- B23K33/004—Filling of continuous seams
- B23K33/006—Filling of continuous seams for cylindrical workpieces
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K9/00—Arc welding or cutting
- B23K9/0026—Arc welding or cutting specially adapted for particular articles or work
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K9/00—Arc welding or cutting
- B23K9/02—Seam welding; Backing means; Inserts
- B23K9/028—Seam welding; Backing means; Inserts for curved planar seams
- B23K9/0282—Seam welding; Backing means; Inserts for curved planar seams for welding tube sections
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K9/00—Arc welding or cutting
- B23K9/16—Arc welding or cutting making use of shielding gas
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K9/00—Arc welding or cutting
- B23K9/235—Preliminary treatment
-
- 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
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
-
- 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
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
- F01D5/063—Welded rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K2101/00—Articles made by soldering, welding or cutting
- B23K2101/001—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
- F05D2230/00—Manufacture
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
- F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
Definitions
- the present invention relates to a turbine rotor formed by joining two different members in the axial direction of a turbine rotor by welding.
- a turbine rotor that constitutes a turbine such as a steam turbine differs in the temperature of the steam that passes depending on the position along the axial direction of the turbine rotor. Therefore, as this turbine rotor, a so-called dissimilar material welding rotor in which a plurality of different members are brought into contact in the axial direction and joined by welding is conventionally used.
- the surface of the member on the side close to the welding torch is prevented from being oxidized by the inert gas injected from the welding torch.
- an inert gas is injected on the back side of the member, or the back wave is surrounded on the back side of the member.
- a method of forming a space and filling the inside of the space with an inert gas has been used (see, for example, Patent Document 2).
- a cavity is formed inside the turbine rotor on the back side of the welded portion, and the inside of the cavity is filled with an inert gas in advance.
- an inspection hole formed so as to reach the cavity from the surface of the member is used. The inspection hole is used for inspecting the finished state of the back side of the member by inserting a fiberscope or the like into the inspection hole during or after the welding operation. Then, an inert gas is sent into the cavity through the inspection hole.
- the present invention has been made in view of such circumstances, and an object of the present invention is to provide a turbine rotor in which two different members are welded by bringing the tips of the two members into contact with each other in the axial direction of the turbine rotor. It is an object of the present invention to provide means for filling the inside with an inert gas without degrading the quality of the turbine rotor after welding.
- a turbine rotor according to the present invention includes a first member and a second member joined to the first member, and the first and second members extend in an axial direction of the turbine rotor.
- a groove for welding is formed at the boundary between the first and second members, a gas introduction hole for introducing gas into the turbine rotor through the bottom of the groove, It is characterized by being sealed by welding.
- the turbine rotor of the present invention when the first and second members are welded, an inert gas is introduced into the cavity inside the turbine rotor through the gas introduction hole in order to prevent oxidation of the back wave generated in the members.
- the weld metal is filled in the gas introduction hole, so that stress concentration hardly occurs in the peripheral portion where the gas introduction hole used to exist. Accordingly, it is possible to prevent the strength of the turbine rotor from being lowered.
- the material of the first member is different from that of the second member, and the boundary between the first and second members in the groove portion is close to either one of the two members. Good.
- the gas introduction hole is formed at the bottom portion of the groove portion. It can be formed at a position away from the boundary. In this way, if the gas introduction hole is formed at a position away from the boundary, the drill for machining the hole does not slide at the boundary and the position accuracy of the hole is not lowered, and the gas introduction is performed at a desired position. A service hole can be formed. Furthermore, since the position accuracy of the hole is high, it is possible to accurately make a hole at a predetermined drilling position. This ensures that the hole is closed when the first member and the second member are welded.
- the material of the first member is different from that of the second member, and the boundary exists near one of the first and second members having high hardness.
- the joint surfaces of the two members are formed in a shape that fits to each other.
- the positions of the two members fitted in the joint surface are fixed. Therefore, since a drilling operation and a welding operation can be performed with high accuracy, a hole can be accurately formed at a predetermined drilling position. Further, the hole can be melted and reliably closed during the welding operation.
- a method for manufacturing a turbine rotor according to the present invention is a method for manufacturing a turbine rotor by welding a first member and a second member having a thermal conductivity different from that of the first member.
- the second member is arranged so that both members extend in the axial direction of the turbine rotor and one of the first and second members having high thermal conductivity is above the other member.
- the hot air generated during the welding operation from the lateral direction rises, so that the upper member is disposed on the upper side.
- the formed member is heated more strongly than the member disposed on the lower side.
- the member disposed on the upper side has higher thermal conductivity than the member disposed on the lower side, and dissipates more heat. For this reason, a large temperature difference does not occur between the upper member and the lower member, and the entire gas introduction hole can be reliably closed during the welding operation.
- the inside is filled with an inert gas without deteriorating the quality of the turbine rotor after welding. be able to.
- FIG. 1 is an overall configuration diagram illustrating a steam turbine 1 including a turbine rotor 10 according to a first embodiment.
- the steam turbine 1 includes a casing 2, a regulating valve 3, a turbine rotor 10, a plurality of stationary blades 4, a plurality of moving blades 5, and a bearing portion 6.
- the adjustment valve 3 adjusts the amount and pressure of the steam S flowing into the casing 2.
- the turbine rotor 10 is rotatably provided inside the casing 2 and transmits power to a machine such as a generator (not shown).
- the plurality of stationary blades 4 are provided on the inner peripheral surface of the casing 2.
- the plurality of rotor blades 5 are provided on the outer peripheral surface of the turbine rotor 10.
- the bearing portion 6 supports the turbine rotor 10 so as to be rotatable about an axis.
- FIG. 2 is a schematic side view showing a part of the turbine rotor 10.
- the turbine rotor 10 includes a rotor main body 11, a welded portion 12, and a cavity portion 13.
- the rotor body 11 extends in the axial direction of the turbine rotor 10.
- the welded portion 12 is provided at a predetermined position in the axial direction of the rotor body 11.
- the cavity 13 is formed inside the rotor body 11.
- the rotor main body 11 has a high hardness member (first member) 14 and a low hardness member (second member) 15 as shown in FIG.
- the high hardness member 14 has a substantially cylindrical shape and extends in the axial direction.
- the low hardness member 15 has a substantially cylindrical shape like the low hardness member 15 and extends in the axial direction.
- the high hardness member 14 is a member having relatively higher hardness than the low hardness member 15. As shown in FIG. 2, the high hardness member 14 is formed with a first notch portion 141 by notching one end portion of the end portion in the radial direction in the longitudinal direction of the high hardness member 14.
- the low hardness member 15 is a member having a relatively low hardness as compared with the high hardness member 14. As shown in FIG. 2, the low hardness member 15 is also formed with a second notch 151 by notching one end of the end in the longitudinal direction in the longitudinal direction of the low hardness member 15. As shown in FIGS. 2 and 3, the second notch 151 has an outer diameter of the second notch 151 substantially equal to the outer diameter of the first notch 141 of the high hardness member 14, and the second notch The length L1 in the axial direction of 151 is formed longer than the length L2 in the axial direction of the first notch 141.
- the high hardness member 14 9% chromium steel (a steel material containing 9% chromium, the same applies hereinafter) is used, while the low hardness member 14 is used.
- 9% chromium steel a steel material containing 9% chromium, the same applies hereinafter
- the low hardness member 14 is used.
- 2.25% chromium steel or 3.5% nickel steel may be used.
- 12% chromium steel may be used as the high hardness member 14, while 2.25% chromium steel or 3.5% nickel steel may be used as the low hardness member 15.
- the nickel base superalloy is used as the high hardness member 14, 2.25% chromium steel, 9% chromium steel, or 12% chromium steel may be used as the low hardness member 15.
- the high hardness member 14 may be stainless steel, while the low hardness member 15 may be 2.25% chrome steel, 9% chrome steel, or 12% chrome steel.
- the combination of the high hardness member 14 and the low hardness member 15 is not limited to this, Arbitrary combinations can be employ
- FIG. 3 is a schematic cross-sectional view showing the periphery of the groove portion 16.
- the boundary 17 between the high hardness member 14 and the low hardness member 15 is higher in hardness than the center position C (dashed line shown in FIG. 3) in the groove width direction of the groove portion 16. It is positioned so as to approach the member 14 side by a predetermined distance X.
- the weld 12 connects the high hardness member 14 and the low hardness member 15.
- the welded portion 12 has a groove portion 16 formed by combining the first cutout portion 141 and the second cutout portion 151, and uses a welding torch T to reduce the hardness of the welded portion 12. It is formed by welding the hardness member 15.
- the hollow portion 13 is a space for filling an inert gas that prevents oxidation of the back wave 19 during welding work. As shown by a broken line in FIG. 2, the hollow portion 13 is formed by combining a first concave portion 131 formed in the high hardness member 14 and a second concave portion 132 formed in the low hardness member 15. .
- the operator brings the high hardness member 14 and the low hardness member 15 into contact with each other. That is, as shown in FIG. 3A, the operator places one end of the high hardness member 14 and one end of the low hardness member 15 so that the first notch 141 and the second notch 151 face each other. Abut.
- the groove portion 16 is formed by the first cutout portion 141 and the second cutout portion 151.
- the length L1 in the axial direction of the second notch 151 is formed longer than the length L2 in the axial direction of the first notch 141. Therefore, the boundary 17 between the high hardness member 14 and the low hardness member 15 exists so as to be closer to the high hardness member 14 side than the center position C in the groove width direction of the groove portion 16.
- the operator forms a gas introduction hole 18 at the bottom of the groove portion 16. That is, the operator sets the drill D at the center position C in the groove width direction of the groove portion 16 as shown in FIG. 3 (a), and the groove portion 16 as shown in FIG. 3 (b). Penetrate the bottom. At this time, the boundary 17 between the high hardness member 14 and the low hardness member 15 exists so as to be closer to the high hardness member 14 side than the center position C of the groove portion 16. Therefore, the drill D passes through the position deviated from the boundary 17 and penetrates the low hardness member 15 to form the gas introduction hole 18.
- FIG. 6 is a diagram for explaining a problem that occurs when the boundary 17 is located at the center position C of the groove portion 16.
- the boundary 17 between the two members 14 and 15 is located at the center position C of the groove portion 16, as shown in FIG. It slips on 17 and flows.
- FIG. 6B there is a case where it is formed at a position shifted from the original drilling position.
- FIG. 6C even if the welding operation of the two members 14 and 15 is performed, a part of the gas introduction hole 18 remains without being blocked.
- the inert gas inside the cavity portion 13 leaks outside from the gas introduction hole 18, and the back wave 19 is oxidized at the time of welding and the welded portion.
- the problem of insufficient strength occurs.
- the drilling position of the gas introduction hole 18 and the boundary 17 between the two members 14 and 15 are likely to coincide with each other at the center position of the groove portion 16 in the groove width direction. This problem is likely to occur.
- the operator introduces an inert gas into the cavity 13. That is, the operator fills the cavity 13 formed inside the rotor body 11 with an inert gas such as argon gas through a tube (not shown) inserted through the gas introduction hole 18.
- an inert gas such as argon gas
- the operator welds the high hardness member 14 and the low hardness member 15. That is, as shown in FIG. 2, the operator inserts the tip of the welding torch T into the groove portion 16 from the lateral direction, and performs, for example, TIG welding on the boundary 17 between the high hardness member 14 and the low hardness member 15. .
- the periphery of the boundary 17 is melted to form the welded portion 12, and the high hardness member 14 and the low hardness member 15 are joined to each other by the welded portion 12.
- the gas introduction hole 18 is sealed by melting the periphery of the gas introduction hole 18 close to the boundary 17.
- the part formed in the exterior of the rotor main body 11 among the welding parts 12 is the part formed in the exterior of the rotor main body 11 among the welding parts 12 by the inert gas (not shown) injected from the welding torch T. Is prevented from being oxidized.
- the back wave 19 formed inside the rotor body 11 in the welded portion 12 is formed inside the rotor body 11 in the welded portion 12 by the inert gas filled in the cavity portion 13. Oxidation of the part is prevented.
- the welded portion 12 is shown only for the bottom portion of the groove portion 16, but at the end of the welding operation, the welded portion 12 is shown as a two-dot chain line in the drawing. It is formed up to the position that fills the whole. Thus, the turbine rotor 10 is completed.
- the turbine rotor 20 of the present embodiment is different from the turbine rotor 10 of the first embodiment only in the configuration of the rotor body 21. Since the other configuration and the manufacturing method are the same as those of the first embodiment, the same reference numerals as those of the first embodiment are used, and the description thereof is omitted here.
- FIG. 4 is a schematic cross-sectional view showing the periphery of the groove portion 16 in the turbine rotor 20 of the second embodiment.
- the rotor body 21 of the present embodiment is the same as the rotor body 21 of the first embodiment in that it has a high hardness member 14 and a low hardness member 15, but the joint surface between the high hardness member 14 and the low hardness member 15.
- the shape is different. That is, as shown in FIG. 4A, a stepped step portion 22 is formed at one end of the high hardness member 14. A stepped step portion 23 is also formed at one end of the low hardness member 15. The step portion 22 of the high hardness member 14 and the step portion 23 of the low hardness member 15 are fitted to each other.
- FIG. 4B is a diagram showing a modification of the second embodiment.
- the convex portion 24 is formed at one end of the high hardness member 14, while the concave portion 25 having a shape that fits the convex portion 24 of the high hardness member 14 is formed at one end of the low hardness member 15. Yes.
- the effect it is the same as the fitting by the level
- FIG. 4C is a diagram showing another modification of the second embodiment.
- the concave portion 26 is formed at one end portion of the high hardness member 14, while the convex portion 27 having a shape that fits into the concave portion 26 of the high hardness member 14 is formed at one end portion of the low hardness member 15. .
- the effect it is the same as the fitting by the level
- the turbine rotor 30 of the present embodiment differs from the turbine rotor 10 of the first embodiment in the configuration of the rotor body 31 and the manufacturing method thereof. Since the other points are the same as those in the first embodiment, the same reference numerals as those in the first embodiment are used, and description thereof is omitted here.
- FIG. 5 is a schematic cross-sectional view showing the periphery of the groove portion 16 in the turbine rotor 30 of the third embodiment.
- the rotor body 31 of the present embodiment is the same as the rotor body 31 of the first embodiment in that it has a high hardness member 14 and a low hardness member 15. However, it differs from the first embodiment in that the thermal conductivity of the high hardness member 14 and the low hardness member 15 is different. More specifically, the high hardness member 14 has a relatively high thermal conductivity, and the low hardness member 15 has a relatively low thermal conductivity.
- the operator places the low-hardness member 15 having low thermal conductivity on the lower side and the high-hardness member 14 having high thermal conductivity. The tips of both members 14 and 15 are brought into contact with each other so as to be positioned on the upper side. Then, similarly to the first embodiment, the operator forms the gas introduction hole 18 at the bottom of the groove portion 16, fills the cavity portion 13 with the inert gas, and the high hardness member 14 and the low hardness member 15.
- the turbine rotor 30 is manufactured by performing operations in the order of welding.
- the hot air generated during the welding operation from the lateral direction rises, so that the high hardness member 14 disposed on the upper side is lowered with the low air disposed on the lower side. Compared with the hardness member 15, it is heated more strongly.
- the high hardness member 14 has a higher thermal conductivity than the low hardness member 15 and dissipates more heat as indicated by arrows Y1 and Y2 in FIG. A large temperature difference with the member 15 does not occur.
- the high hardness member 14 and the low hardness member 15 are welded, the high hardness member 14 and the low hardness member 15 can be melted uniformly, so that the gas introduction hole 18 is reliably sealed. be able to.
- the thermal conductivity of the high hardness member 14 is relatively high, and the thermal conductivity of the low hardness member 15 is relatively low.
- the conductivity may be relatively lowered, and the thermal conductivity of the low hardness member 15 may be relatively increased.
- the same effect as described above can be obtained by disposing the high hardness member 14 having low thermal conductivity on the lower side and the low hardness member 15 having high thermal conductivity on the upper side. It is done.
- the configuration in which the drill D is particularly easy to flow has been described by taking, as an example, the case where two different members constituting the rotor main bodies 11, 21, 31 are members having different hardnesses.
- the two different members may be members having the same hardness.
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- Mechanical Engineering (AREA)
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Abstract
Description
本願は、2011年3月23日に、日本に出願された特願2011-064657号に基づき優先権を主張し、その内容をここに援用する。
以下、図面を参照し、本発明の実施の形態について説明する。まず、本発明の第1実施形態に係るタービンロータの構成について説明する。図1は、第1実施形態に係るタービンロータ10を備えた蒸気タービン1を示す全体構成図である。蒸気タービン1は、ケーシング2と、調整弁3と、タービンロータ10と、複数の静翼4と、複数の動翼5と、軸受部6とを備える。調整弁3は、ケーシング2に流入する蒸気Sの量と圧力を調整する。タービンロータ10は、ケーシング2の内部に回転可能に設けられ、図示しない発電機等の機械に動力を伝達する。複数の静翼4は、ケーシング2の内周面に設けられる。複数の動翼5は、タービンロータ10の外周面に設けられる。軸受部6は、タービンロータ10を軸回りに回転可能に支持する。
次に、本発明の第2実施形態に係るタービンロータ20の構成について説明する。本実施形態のタービンロータ20は、第1実施形態のタービンロータ10と比較すると、ロータ本体21の構成だけが異なっている。それ以外の構成及び製造方法は第1実施形態と同じであるため、第1実施形態と同じ符号を用い、ここでは説明を省略する。
次に、本発明の第3実施形態に係るタービンロータ30の構成について説明する。本実施形態のタービンロータ30は、第1実施形態のタービンロータ10と比較すると、ロータ本体31の構成及びその製造方法が異なっている。それ以外の点については第1実施形態と同じであるため、第1実施形態と同じ符号を用い、ここでは説明を省略する。
2 ケーシング
3 調整弁
4 静翼
5 動翼
6 軸受部
10 タービンロータ
11 ロータ本体
12 溶接部
13 空洞部
14 高硬度部材
15 低硬度部材
16 開先部
17 境界
18 ガス導入用穴
19 裏波
20 タービンロータ
21 ロータ本体
22 段差部
23 段差部
24 凸部
25 凹部
26 凹部
27 凸部
30 タービンロータ
31 ロータ本体
131 第1凹部
132 第2凹部
141 第1切欠部
151 第2切欠部
C 中心位置
D ドリル
L1 長さ(第1切欠部)
L2 長さ(第2切欠部)
S 蒸気
T 溶接トーチ
X 所定距離
Y1 矢印
Y2 矢印
Claims (5)
- 第一部材と、
前記第一部材に接合された第二部材とを備え、前記第一、第二部材が軸方向に延在するタービンロータであって、
前記第一、第二部材の境界に、溶接用の開先部が形成され、前記開先部の底部を貫通し、前記タービンロータの内部にガスを導入するためのガス導入用穴が、溶接によって封止されているタービンロータ。 - 前記第一部材の材質は前記第二部材と異なり、
前記開先部における前記第一、第二部材の境界が、両部材のいずれか一方に寄せて存在する請求項1に記載のタービンロータ。 - 前記第一部材の材質は前記第二部材と異なり、
前記境界が前記第一、第二部材のうち硬度の高い一方の部材に寄せて存在する請求項2に記載のタービンロータ。 - 前記2つの部材の接合面それぞれが、互いに嵌合する形状に形成される請求項1から3のいずれか1項に記載のタービンロータ。
- 第一部材と、前記第一部材とは熱伝導度の異なる第二部材とを溶接してタービンロータを製造する方法であって、
前記第一、第二部材を、両部材がタービンロータの軸方向に延在し、かつ前記第一、第二部材のうち熱伝導度の高い一方の部材を他方の部材よりも上になるように配置する工程と、
前記第一、第二部材の境界に形成された溶接用の開先部の底部に、前記タービンロータの内部にガスを導入するためのガス導入用穴を、前記底部を貫通するように形成する工程と、
前記開先部において前記第一部材に前記第二部材を溶接する工程とを備えるタービンロータの製造方法。
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US14/004,471 US20130343893A1 (en) | 2011-03-23 | 2012-03-22 | Turbine rotor and production method thereof |
CN201280014202.0A CN103459779B (zh) | 2011-03-23 | 2012-03-22 | 涡轮转子及涡轮转子的制造方法 |
EP12761470.9A EP2690259B1 (en) | 2011-03-23 | 2012-03-22 | Welded turbine rotor and method for producing the turbine rotor |
KR1020137024801A KR101539876B1 (ko) | 2011-03-23 | 2012-03-22 | 터빈 로터 및 터빈 로터의 제조 방법 |
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CN106001923B (zh) * | 2016-06-15 | 2018-06-29 | 湖南天雁机械有限责任公司 | 一种涡轮增压器的涡轮转子激光复合加工方法 |
KR101872808B1 (ko) | 2017-04-28 | 2018-06-29 | 두산중공업 주식회사 | 길이조절구조를 포함하는 가스터빈 로터, 및 이를 포함하는 가스터빈 |
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- 2012-03-22 CN CN201280014202.0A patent/CN103459779B/zh active Active
- 2012-03-22 US US14/004,471 patent/US20130343893A1/en not_active Abandoned
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KR101539876B1 (ko) | 2015-07-27 |
JP2012202225A (ja) | 2012-10-22 |
JP5822496B2 (ja) | 2015-11-24 |
EP2690259A1 (en) | 2014-01-29 |
CN103459779A (zh) | 2013-12-18 |
EP2690259A4 (en) | 2014-11-19 |
US20130343893A1 (en) | 2013-12-26 |
CN103459779B (zh) | 2016-04-06 |
KR20130129287A (ko) | 2013-11-27 |
EP2690259B1 (en) | 2019-12-04 |
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