US20110217175A1 - Turbine rotor blade - Google Patents
Turbine rotor blade Download PDFInfo
- Publication number
- US20110217175A1 US20110217175A1 US12/673,494 US67349409A US2011217175A1 US 20110217175 A1 US20110217175 A1 US 20110217175A1 US 67349409 A US67349409 A US 67349409A US 2011217175 A1 US2011217175 A1 US 2011217175A1
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- United States
- Prior art keywords
- blade
- turbine rotor
- turbine
- root
- platform
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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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
- 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
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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
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/4932—Turbomachine making
- Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member
Definitions
- the present invention relates to a turbine rotor blade applied to a gas turbine, a steam turbine, and the like.
- a turbine rotor blade As a known turbine rotor blade applied to a gas turbine, a steam turbine, and the like, there is a turbine rotor blade that is provided with a blade root that is slotted into a blade groove formed on the circumferential portion of a turbine disc to hold the whole blade, a blade portion that is exposed to high-temperature gas, a platform that supports this blade portion, a shank that connects the blade root and the platform, and a shroud that extends in the circumferential direction from the end of the blade portion (see, for example, Patent Citation 1).
- the present invention has been conceived in light of the circumstances described above, and an object thereof is to provide a turbine rotor blade with which the blade root of the final (last) turbine rotor blade can be slotted into the blade groove on the turbine disc easily and rapidly even if the plan-view shape of the shroud of the turbine rotor blade is complex.
- the present invention employs the following solutions.
- a turbine rotor blade is a turbine rotor blade provided with a blade root that is slotted into a blade groove formed on a circumferential portion of a turbine disc to hold the whole blade, a blade portion that is exposed to high-temperature gas, a platform that supports this blade portion, a shank that connects the blade root and the platform, and a shroud that extends along the circumferential direction from an end of the blade portion; the turbine rotor blade has a cut-out portion that is cut out to a predetermined depth, either at the leading edge or the trailing edge of the blade root, along the lengthwise direction thereof, from the end of the blade root to an intermediate part of the shank.
- the turbine rotor blade can be set between a normal blade and a normal blade that have been slotted into the blade grooves on the turbine disc to a predetermined depth (for example, 5 mm) merely by moving the end surface that is formed by the cut-out portion and that extends in the lengthwise direction in a plane that includes the end surfaces forming the circumferential portion of the turbine disc (in other words, moving radially inward from radially outward), when the blade root is slotted into the blade groove formed on the circumferential portion of the turbine disc to be assembled.
- a predetermined depth for example, 5 mm
- the blade root of the turbine rotor blade and the blade roots of the normal blades can be slotted (are capable of being slotted) into the blade grooves on the turbine disc easily and rapidly.
- the turbine rotor according to one aspect of the present invention is provided with the turbine rotor blade with which, when the blade root is slotted into the blade groove formed on the circumferential portion of the turbine disc to be assembled, the end surface that is formed by the cut-out portion and that extends in the lengthwise direction can be moved in the plane that includes the end surfaces forming the circumferential portion of the turbine disc (in other words, moved radially inward from radially outward); therefore, simplification of the procedure for assembling the turbine rotor blade and the normal blades on the turbine disc can be achieved, a reduction in the time required for assembly can be achieved, and a reduction in production costs can be achieved.
- a method for constructing the turbine rotor according to the above-mentioned aspect is a method for constructing a turbine rotor by slotting at least one turbine rotor blade provided with a blade root that is slotted into a blade groove formed on a circumferential portion of a turbine disc to hold the whole blade, a blade portion that is exposed to high-temperature gas, a platform that supports this blade portion, a shank that connects the blade root and the platform, a shroud that extends along the circumferential direction from the end of the blade portion, and a cut-out portion that is cut out to a predetermined depth, either at the leading edge or the trailing edge of the blade root, along the lengthwise direction thereof from the end of the blade root to an intermediate part of the shank; and a plurality of normal blades provided with a blade root that is slotted into a blade groove formed on the circumferential portion of the turbine disc to hold the whole blade, a blade portion that is exposed to high-temperature gas, a platform that supports this blade
- the turbine rotor blade can be set between the normal blade and the normal blade that have been slotted into the blade grooves on the turbine disc to a predetermined depth (for example, 5 mm) merely by moving the end surface that is formed by the cut-out portion and that extends in the lengthwise direction in the plane that includes the end surfaces forming the circumferential portion of the turbine disc (in other words, moving radially inward from radially outward), when the blade root is slotted into the blade groove formed on the circumferential portion of the turbine disc to be assembled.
- a predetermined depth for example, 5 mm
- the turbine rotor blade according to the one aspect of the present invention at least as the final (last) blade to be slotted into the turbine disc, the blade root of the turbine rotor blade and the blade roots of the normal blades can be slotted (are capable of being slotted) into the blade grooves on the turbine disc easily and rapidly.
- simplification of the procedure for assembling the turbine rotor blade and the normal blades on the turbine disc can be achieved, a reduction in the time required for assembly can be achieved, and a reduction in production costs can be achieved.
- the turbine rotor blade according to the present invention affords an advantage in that it is possible to easily and rapidly slot the blade root of the final (last) turbine rotor blade into the blade groove on the turbine disc, even if the plan-view shape of the shroud of the turbine rotor blade is complex.
- FIG. 1A is a side view showing a turbine rotor blade according to an embodiment of the present invention.
- FIG. 1B is a plan view showing a turbine rotor blade according to an embodiment of the present invention.
- FIG. 2 is a perspective view of the turbine rotor blade shown in FIGS. 1A and 1B , viewed from the front side.
- FIG. 3A is a side view showing a normal blade without a cut-out portion shown in FIGS. 1A , 1 B, and 2 .
- FIG. 3B is a plan view showing a normal blade without a cut-out portion shown in FIGS. 1A , 1 B, and 2 .
- FIG. 4 is a perspective view of the normal blade shown in FIGS. 3A and 3B viewed from the front side.
- FIG. 5 is a perspective view for explaining an assembly procedure onto the turbine disc.
- FIG. 6 is a perspective view for explaining an assembly procedure onto the turbine disc.
- FIGS. 1A , 1 B, and 2 An embodiment of a turbine rotor blade according to the present invention will be described below with reference to FIGS. 1A , 1 B, and 2 .
- FIG. 1A is a side view showing the turbine rotor blade according to this embodiment
- FIG. 1B is a plan view showing the turbine rotor blade according to this embodiment
- FIG. 2 is a perspective view of the turbine rotor blade according to this embodiment viewed from the front side.
- the turbine rotor blade 1 is applied to a gas turbine provided with, for example, a compression unit (not shown) that compresses combustion air, a combustion unit (not shown) that combusts fuel by injecting the fuel into the high-pressure air sent from this compression unit, generating high-temperature combustion gas, and a turbine unit (not shown) that is located downstream of this combustion unit and is driven by the combustion gas discharged from the combustion unit.
- a compression unit not shown
- a combustion unit that combusts fuel by injecting the fuel into the high-pressure air sent from this compression unit, generating high-temperature combustion gas
- a turbine unit not shown
- the turbine rotor blade 1 is provided with a Christmas tree-shaped blade root (bottom) 3 that is slotted into a blade groove 2 a (see FIGS. 5 and 6 ) formed on the circumferential portion of a turbine disc 2 (see FIGS.
- the turbine rotor blade 1 has, either at the leading edge or the trailing edge of the blade root 3 , a cut-out portion 8 that is cut out uniformly (to a predetermined depth (for example, 5 mm)) along the lengthwise direction (vertical direction in FIGS. 1A and 2 ) of the turbine rotor blade 1 from the end (lower end) of the blade root 3 to an intermediate part of the shank 6 .
- An end surface 8 a that is formed by this cut-out portion 8 and extends in the lengthwise direction (vertical direction in FIGS.
- the cut-out portion 8 of the turbine rotor blade 1 is formed so that, in a state where the blade root 13 of a turbine blade 11 without the cut-out portion 8 (hereinafter referred to as “normal blade”), such as those shown in FIGS. 3A , 3 B, and 4 , is slotted into the blade groove 2 a on the turbine disc 2 to a predetermined depth (for example, 5 mm), as shown in FIG. 5 , the turbine rotor blade 1 can be set between a normal blade 11 and a normal blade 11 by moving the end surface 8 a that is formed by the cut-out portion 8 and that extends in the lengthwise direction in a plane that includes the end surfaces 2 b forming the circumferential portion of the turbine disc 2 .
- normal blade the blade root 13 of a turbine blade 11 without the cut-out portion 8
- reference signs 4 , 5 , 6 , and 7 are a blade portion, a platform, a shank, and a shroud, respectively, and because descriptions thereof have been described using FIGS. 1A , 1 B, and 2 , the descriptions thereof will be omitted here.
- the reference sign 20 in FIGS. 5 and 6 indicates a turbine rotor that is provided with at least one turbine rotor blade 1 , a plurality of normal blades 11 , and the turbine disc 2 .
- the thus-configured turbine rotor blade 1 can be set between the normal blade 11 and the normal blade 11 that have been slotted into the blade grooves 2 a on the turbine disc 2 to a predetermined depth (for example, 5 mm) merely by moving the end surface 8 a that is formed by the cut-out portion 8 and that extends in the lengthwise direction in the plane that includes the end surfaces 2 b forming the circumferential portion of the turbine disc 2 (in other words, moving radially inward from radially outward), when the blade root 3 is slotted into the blade groove 2 a formed on the circumferential portion of the turbine disc 2 to be assembled.
- a predetermined depth for example, 5 mm
- the turbine rotor blade 1 even if the plan-view shapes of the shrouds 7 of the turbine rotor blade 1 and the normal blades 11 are complex (regardless of the plan-view shapes), by using the turbine rotor blade 1 according to this embodiment at least as the final (last) blade to be slotted into the turbine disc 2 , the blade root 3 of the turbine rotor blade 1 and the blade roots 13 of the normal blades 11 can be slotted (are capable of being slotted) into the blade grooves 2 a on the turbine disc 2 easily and rapidly.
- the turbine rotor 20 is provided with the turbine rotor blade 1 with which, when the blade roots 3 and 13 are slotted into the blade grooves 2 a formed on the circumferential portion of the turbine disc 2 to be assembled, the end surface 8 a that is formed by the cut-out portion 8 of the turbine rotor blade 1 and extends in the lengthwise direction can be moved in the plane that includes the end surfaces 2 b forming the circumferential portion of the turbine disc 2 (in other words, moved radially inward from radially outward); therefore, simplification of the procedure for assembling the turbine rotor blade 1 and the normal blades 11 on the turbine disc 2 can be achieved, a reduction in the time required for assembly can be achieved, and a reduction in production costs can be achieved.
- the present invention is not only applicable to a gas turbine, but may also be applied to a steam turbine or a fluid rotary machine having other similar configurations.
Abstract
It is possible to easily and rapidly slot a blade root of a final (last) turbine rotor blade into a blade groove on a turbine disc even when the plan-view shape of a shroud of the turbine rotor blade is complex. A turbine rotor blade that is provided with a blade root that is slotted into a blade groove formed on a circumferential portion of the turbine disc to hold the whole blade, a blade portion that is exposed to high-temperature gas, a platform that supports this blade portion, a shank that connects the blade root and the platform, and a shroud that extends along the circumferential direction from the end of the blade portion has a cut-out portion cut out to a predetermined depth, either at the leading-edge or the trailing-edge of the blade root, along the lengthwise direction thereof from the end of the blade root to an intermediate part of the shank.
Description
- The present invention relates to a turbine rotor blade applied to a gas turbine, a steam turbine, and the like.
- As a known turbine rotor blade applied to a gas turbine, a steam turbine, and the like, there is a turbine rotor blade that is provided with a blade root that is slotted into a blade groove formed on the circumferential portion of a turbine disc to hold the whole blade, a blade portion that is exposed to high-temperature gas, a platform that supports this blade portion, a shank that connects the blade root and the platform, and a shroud that extends in the circumferential direction from the end of the blade portion (see, for example, Patent Citation 1).
- Patent Citation 1: Japanese Unexamined Patent Application, Publication No. 2006-283681
- In recent years, however, it has been required to reduce the leakage loss (leakage of gas) at the end of the blade portion to improve the turbine efficiency, and to make a blade frame of the blade portion smaller by reducing the vibration of the end of the blade portion. Therefore, the plan-view shape of a shroud has become complex, and with a method in which the blade roots of the turbine rotor blades are individually slotted into the blade grooves on the turbine disc, as in the art, there has been a problem in that it is difficult to slot the blade root of the final (last) turbine rotor blade into the blade groove on the turbine disc since the shroud of the final (last) turbine rotor blade interferes with the shrouds of the adjacent turbine rotor blades positioned at both sides when the blade root of the final (last) turbine rotor blade is slotted into the blade groove on the turbine disc.
- There has been a further problem in that, if the length of the turbine rotor blade (blade height) is as short (low) as, for example, 200 mm or less (more specifically, if L (blade height)/D (chord length) is ⅓ or more), the blade root of the final (last) turbine rotor blade cannot be slotted into the blade groove on the turbine disc.
- The present invention has been conceived in light of the circumstances described above, and an object thereof is to provide a turbine rotor blade with which the blade root of the final (last) turbine rotor blade can be slotted into the blade groove on the turbine disc easily and rapidly even if the plan-view shape of the shroud of the turbine rotor blade is complex.
- In order to solve the problems described above, the present invention employs the following solutions.
- A turbine rotor blade according to one aspect of the present invention is a turbine rotor blade provided with a blade root that is slotted into a blade groove formed on a circumferential portion of a turbine disc to hold the whole blade, a blade portion that is exposed to high-temperature gas, a platform that supports this blade portion, a shank that connects the blade root and the platform, and a shroud that extends along the circumferential direction from an end of the blade portion; the turbine rotor blade has a cut-out portion that is cut out to a predetermined depth, either at the leading edge or the trailing edge of the blade root, along the lengthwise direction thereof, from the end of the blade root to an intermediate part of the shank.
- According to the turbine rotor blade of one aspect of the present invention, the turbine rotor blade can be set between a normal blade and a normal blade that have been slotted into the blade grooves on the turbine disc to a predetermined depth (for example, 5 mm) merely by moving the end surface that is formed by the cut-out portion and that extends in the lengthwise direction in a plane that includes the end surfaces forming the circumferential portion of the turbine disc (in other words, moving radially inward from radially outward), when the blade root is slotted into the blade groove formed on the circumferential portion of the turbine disc to be assembled.
- In other words, even if the plan-view shape of the shrouds of the turbine rotor blade and the normal blades are complex (regardless of the plan-view shapes of the shrouds), by using the turbine rotor blade according to the above-mentioned aspect at least as the final (last) blade to be slotted into the turbine disc, the blade root of the turbine rotor blade and the blade roots of the normal blades can be slotted (are capable of being slotted) into the blade grooves on the turbine disc easily and rapidly.
- The turbine rotor according to one aspect of the present invention is provided with the turbine rotor blade with which, when the blade root is slotted into the blade groove formed on the circumferential portion of the turbine disc to be assembled, the end surface that is formed by the cut-out portion and that extends in the lengthwise direction can be moved in the plane that includes the end surfaces forming the circumferential portion of the turbine disc (in other words, moved radially inward from radially outward); therefore, simplification of the procedure for assembling the turbine rotor blade and the normal blades on the turbine disc can be achieved, a reduction in the time required for assembly can be achieved, and a reduction in production costs can be achieved.
- A method for constructing the turbine rotor according to the above-mentioned aspect is a method for constructing a turbine rotor by slotting at least one turbine rotor blade provided with a blade root that is slotted into a blade groove formed on a circumferential portion of a turbine disc to hold the whole blade, a blade portion that is exposed to high-temperature gas, a platform that supports this blade portion, a shank that connects the blade root and the platform, a shroud that extends along the circumferential direction from the end of the blade portion, and a cut-out portion that is cut out to a predetermined depth, either at the leading edge or the trailing edge of the blade root, along the lengthwise direction thereof from the end of the blade root to an intermediate part of the shank; and a plurality of normal blades provided with a blade root that is slotted into a blade groove formed on the circumferential portion of the turbine disc to hold the whole blade, a blade portion that is exposed to high-temperature gas, a platform that supports this blade portion, a shank that connects the blade root and the platform, and a shroud that extends along the circumferential direction from the end of the blade portion, into the turbine disc to complete the turbine rotor; the method for constructing the turbine rotor includes a step of positioning the turbine rotor blade between the normal blades by moving the turbine rotor blade radially inward from radially outward, between the normal blades whose blade roots have been slotted into the blade grooves on the turbine disc to a predetermined depth, and thereafter, slotting the blade roots of the turbine rotor blade and the normal blades into the blade grooves on the turbine disc by moving the turbine rotor blade and the normal blades in the axis line direction of the turbine rotor.
- With the method for constructing the turbine rotor according to the above-mentioned aspect, the turbine rotor blade can be set between the normal blade and the normal blade that have been slotted into the blade grooves on the turbine disc to a predetermined depth (for example, 5 mm) merely by moving the end surface that is formed by the cut-out portion and that extends in the lengthwise direction in the plane that includes the end surfaces forming the circumferential portion of the turbine disc (in other words, moving radially inward from radially outward), when the blade root is slotted into the blade groove formed on the circumferential portion of the turbine disc to be assembled.
- In other words, even if the plan-view shapes of the shrouds of the turbine rotor blade and the normal blades are complex (regardless of the plan-view shapes of the shrouds), by using the turbine rotor blade according to the one aspect of the present invention at least as the final (last) blade to be slotted into the turbine disc, the blade root of the turbine rotor blade and the blade roots of the normal blades can be slotted (are capable of being slotted) into the blade grooves on the turbine disc easily and rapidly.
- Accordingly, simplification of the procedure for assembling the turbine rotor blade and the normal blades on the turbine disc can be achieved, a reduction in the time required for assembly can be achieved, and a reduction in production costs can be achieved.
- The turbine rotor blade according to the present invention affords an advantage in that it is possible to easily and rapidly slot the blade root of the final (last) turbine rotor blade into the blade groove on the turbine disc, even if the plan-view shape of the shroud of the turbine rotor blade is complex.
-
FIG. 1A is a side view showing a turbine rotor blade according to an embodiment of the present invention. -
FIG. 1B is a plan view showing a turbine rotor blade according to an embodiment of the present invention. -
FIG. 2 is a perspective view of the turbine rotor blade shown inFIGS. 1A and 1B , viewed from the front side. -
FIG. 3A is a side view showing a normal blade without a cut-out portion shown inFIGS. 1A , 1B, and 2. -
FIG. 3B is a plan view showing a normal blade without a cut-out portion shown inFIGS. 1A , 1B, and 2. -
FIG. 4 is a perspective view of the normal blade shown inFIGS. 3A and 3B viewed from the front side. -
FIG. 5 is a perspective view for explaining an assembly procedure onto the turbine disc. -
FIG. 6 is a perspective view for explaining an assembly procedure onto the turbine disc. -
- 1 turbine rotor blade
- 2 turbine disc
- 2 a blade groove
- 3 blade root
- 4 blade portion
- 5 platform
- 6 shank
- 7 shroud
- 8 cut-out portion
- 11 normal blade
- 13 blade root
- 20 turbine rotor
- An embodiment of a turbine rotor blade according to the present invention will be described below with reference to
FIGS. 1A , 1B, and 2. -
FIG. 1A is a side view showing the turbine rotor blade according to this embodiment, andFIG. 1B is a plan view showing the turbine rotor blade according to this embodiment.FIG. 2 is a perspective view of the turbine rotor blade according to this embodiment viewed from the front side. - The
turbine rotor blade 1 according to this embodiment is applied to a gas turbine provided with, for example, a compression unit (not shown) that compresses combustion air, a combustion unit (not shown) that combusts fuel by injecting the fuel into the high-pressure air sent from this compression unit, generating high-temperature combustion gas, and a turbine unit (not shown) that is located downstream of this combustion unit and is driven by the combustion gas discharged from the combustion unit. - As shown in
FIGS. 1A , 1B, and 2, theturbine rotor blade 1 is provided with a Christmas tree-shaped blade root (bottom) 3 that is slotted into ablade groove 2 a (seeFIGS. 5 and 6 ) formed on the circumferential portion of a turbine disc 2 (seeFIGS. 5 and 6 ) to hold (support) the whole body of theturbine rotor blade 1, ablade portion 4 that is exposed to high-temperature gas, aplatform 5 that supports thisblade portion 4, ashank 6 that connects theblade root 3 and theplatform 5, and ashroud 7 that extends along the circumferential direction from the end (tip) of theblade portion 4 and that prevents resonance of theturbine rotor blade 1 and reduces the leakage loss (leakage of gas) at the end of theblade portion 4. - As shown in
FIGS. 1A and 2 , theturbine rotor blade 1 according to this embodiment has, either at the leading edge or the trailing edge of theblade root 3, a cut-out portion 8 that is cut out uniformly (to a predetermined depth (for example, 5 mm)) along the lengthwise direction (vertical direction inFIGS. 1A and 2 ) of theturbine rotor blade 1 from the end (lower end) of theblade root 3 to an intermediate part of theshank 6. Anend surface 8 a that is formed by this cut-out portion 8 and extends in the lengthwise direction (vertical direction inFIGS. 1A and 2 ) is formed so as to become substantially parallel toend surfaces 2 b formed on the circumferential portion of theturbine disc 2 when theturbine rotor blade 1 is assembled with theturbine disc 2; and theend surface 8 a extends to the intermediate part of theshank 6. - In other words, the cut-out portion 8 of the
turbine rotor blade 1 is formed so that, in a state where theblade root 13 of aturbine blade 11 without the cut-out portion 8 (hereinafter referred to as “normal blade”), such as those shown inFIGS. 3A , 3B, and 4, is slotted into theblade groove 2 a on theturbine disc 2 to a predetermined depth (for example, 5 mm), as shown inFIG. 5 , theturbine rotor blade 1 can be set between anormal blade 11 and anormal blade 11 by moving theend surface 8 a that is formed by the cut-out portion 8 and that extends in the lengthwise direction in a plane that includes the end surfaces 2 b forming the circumferential portion of theturbine disc 2. - Then, as shown in
FIG. 6 , after theturbine rotor blade 1 is set between thenormal blade 11 and thenormal blade 11, theturbine blade 1 and thenormal blades 11 are moved, as a whole, along the axial direction of theturbine disc 2, thereby slotting allblade roots turbine blade 1 and thenormal blades 11 into theblade grooves 2 a formed on the circumferential portion of theturbine disc 2. - In
FIGS. 3A , 3B, and 4,reference signs FIGS. 1A , 1B, and 2, the descriptions thereof will be omitted here. - The
reference sign 20 inFIGS. 5 and 6 indicates a turbine rotor that is provided with at least oneturbine rotor blade 1, a plurality ofnormal blades 11, and theturbine disc 2. - The thus-configured
turbine rotor blade 1 can be set between thenormal blade 11 and thenormal blade 11 that have been slotted into theblade grooves 2 a on theturbine disc 2 to a predetermined depth (for example, 5 mm) merely by moving theend surface 8 a that is formed by the cut-out portion 8 and that extends in the lengthwise direction in the plane that includes the end surfaces 2 b forming the circumferential portion of the turbine disc 2 (in other words, moving radially inward from radially outward), when theblade root 3 is slotted into theblade groove 2 a formed on the circumferential portion of theturbine disc 2 to be assembled. - In other words, even if the plan-view shapes of the
shrouds 7 of theturbine rotor blade 1 and thenormal blades 11 are complex (regardless of the plan-view shapes), by using theturbine rotor blade 1 according to this embodiment at least as the final (last) blade to be slotted into theturbine disc 2, theblade root 3 of theturbine rotor blade 1 and theblade roots 13 of thenormal blades 11 can be slotted (are capable of being slotted) into theblade grooves 2 a on theturbine disc 2 easily and rapidly. - According to the
turbine rotor 20 of this embodiment, theturbine rotor 20 is provided with theturbine rotor blade 1 with which, when theblade roots blade grooves 2 a formed on the circumferential portion of theturbine disc 2 to be assembled, theend surface 8 a that is formed by the cut-out portion 8 of theturbine rotor blade 1 and extends in the lengthwise direction can be moved in the plane that includes the end surfaces 2 b forming the circumferential portion of the turbine disc 2 (in other words, moved radially inward from radially outward); therefore, simplification of the procedure for assembling theturbine rotor blade 1 and thenormal blades 11 on theturbine disc 2 can be achieved, a reduction in the time required for assembly can be achieved, and a reduction in production costs can be achieved. - The present invention is not only applicable to a gas turbine, but may also be applied to a steam turbine or a fluid rotary machine having other similar configurations.
- The present invention is not limited to the embodiments described above; various modifications and alterations are permissible as required, so long as they do not depart from the technical idea of the present invention.
Claims (3)
1. A turbine rotor blade provided with a blade root that is slotted into a blade groove formed on a circumferential portion of a turbine disc to hold the whole blade, a blade portion that is exposed to high-temperature gas, a platform that supports this blade portion, a shank that connects the blade root and the platform, and a shroud that extends along the circumferential direction from an end of the blade portion, the turbine rotor blade comprising:
a cut-out portion that is cut out to a predetermined depth, either at the leading-edge or the trailing-edge of the blade root, along the lengthwise direction thereof, from the end of the blade root to an intermediate part of the shank.
2. A turbine rotor comprising:
at one turbine rotor blade according to claim 1 ;
a plurality of normal blades provided with a blade root that is slotted into a blade groove formed on the circumferential portion of the turbine disc to hold the whole blade, a blade portion that is exposed to high-temperature gas, a platform that supports this blade portion, a shank that connects the blade root and the platform, and a shroud that extends along the circumferential direction from the end of the blade portion; and
the turbine disc.
3. A method for constructing a turbine rotor by slotting:
at least one turbine rotor blade provided with a blade root that is slotted into a blade groove formed on a circumferential portion of a turbine disc to hold the whole blade, a blade portion that is exposed to high-temperature gas, a platform that supports this blade portion, a shank that connects the blade root and the platform, a shroud that extends along the circumferential direction from the end of the blade portion, and a cut-out portion that is cut out to a predetermined depth, either at the leading edge or the trailing edge of the blade root, along the lengthwise direction thereof from the end of the blade root to an intermediate part of the shank; and
a plurality of normal blades provided with a blade root that is slotted into a blade groove formed on the circumferential portion of the turbine disc to hold the whole blade, a blade portion that is exposed to high-temperature gas, a platform that supports this blade portion, a shank that connects the blade root and the platform, and a shroud that extends along the circumferential direction from the end of the blade portion; into the turbine disc to complete the turbine rotor, the method for constructing the turbine rotor comprising,
a step of positioning the turbine rotor blade between the normal blades by moving the turbine rotor blade radially inward from radially outward, between the normal blades whose blade roots have been slotted into the blade grooves on the turbine disc to a predetermined depth, and thereafter, slotting the blade roots of the turbine rotor blade and the normal blades into the blade grooves on the turbine disc by moving the turbine rotor blade and the normal blades in the axis line direction of the turbine rotor.
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
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JP2008-006895 | 2008-01-16 | ||
JP2008006895 | 2008-01-16 | ||
PCT/JP2009/050160 WO2009090908A1 (en) | 2008-01-16 | 2009-01-08 | Turbine rotor blade |
Publications (1)
Publication Number | Publication Date |
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US20110217175A1 true US20110217175A1 (en) | 2011-09-08 |
Family
ID=40885299
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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US12/673,494 Abandoned US20110217175A1 (en) | 2008-01-16 | 2009-01-08 | Turbine rotor blade |
Country Status (7)
Country | Link |
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US (1) | US20110217175A1 (en) |
EP (1) | EP2230385A4 (en) |
JP (1) | JP4939613B2 (en) |
CN (1) | CN101743380B (en) |
RU (1) | RU2010104753A (en) |
WO (1) | WO2009090908A1 (en) |
ZA (1) | ZA201001031B (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20130224049A1 (en) * | 2012-02-29 | 2013-08-29 | Frederick M. Schwarz | Lightweight fan driving turbine |
US10648354B2 (en) * | 2016-12-02 | 2020-05-12 | Honeywell International Inc. | Turbine wheels, turbine engines including the same, and methods of forming turbine wheels with improved seal plate sealing |
US11814985B2 (en) * | 2021-11-30 | 2023-11-14 | Doosan Enerbility Co., Ltd. | Turbine blade, and turbine and gas turbine including the same |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2551460A1 (en) * | 2011-07-29 | 2013-01-30 | Siemens Aktiengesellschaft | Blade group |
US10704400B2 (en) * | 2018-10-17 | 2020-07-07 | Pratt & Whitney Canada Corp. | Rotor assembly with rotor disc lip |
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- 2009-01-08 US US12/673,494 patent/US20110217175A1/en not_active Abandoned
- 2009-01-08 JP JP2009550004A patent/JP4939613B2/en not_active Expired - Fee Related
- 2009-01-08 CN CN200980000565.7A patent/CN101743380B/en not_active Expired - Fee Related
- 2009-01-08 RU RU2010104753/06A patent/RU2010104753A/en not_active Application Discontinuation
- 2009-01-08 WO PCT/JP2009/050160 patent/WO2009090908A1/en active Application Filing
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Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20130224049A1 (en) * | 2012-02-29 | 2013-08-29 | Frederick M. Schwarz | Lightweight fan driving turbine |
US10309232B2 (en) * | 2012-02-29 | 2019-06-04 | United Technologies Corporation | Gas turbine engine with stage dependent material selection for blades and disk |
US10648354B2 (en) * | 2016-12-02 | 2020-05-12 | Honeywell International Inc. | Turbine wheels, turbine engines including the same, and methods of forming turbine wheels with improved seal plate sealing |
US10851660B2 (en) | 2016-12-02 | 2020-12-01 | Honeywell International Inc. | Turbine wheels, turbine engines including the same, and methods of forming turbine wheels with improved seal plate sealing |
US11015472B2 (en) | 2016-12-02 | 2021-05-25 | Honeywell International Inc. | Turbine wheels, turbine engines including the same, and methods of forming turbine wheels with improved seal plate sealing |
US11814985B2 (en) * | 2021-11-30 | 2023-11-14 | Doosan Enerbility Co., Ltd. | Turbine blade, and turbine and gas turbine including the same |
Also Published As
Publication number | Publication date |
---|---|
JPWO2009090908A1 (en) | 2011-05-26 |
JP4939613B2 (en) | 2012-05-30 |
EP2230385A4 (en) | 2011-03-16 |
RU2010104753A (en) | 2012-02-27 |
CN101743380A (en) | 2010-06-16 |
WO2009090908A1 (en) | 2009-07-23 |
EP2230385A1 (en) | 2010-09-22 |
ZA201001031B (en) | 2011-08-31 |
CN101743380B (en) | 2014-01-01 |
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Legal Events
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AS | Assignment |
Owner name: MITSUBISHI HEAVY INDUSTRIES, LTD., JAPAN Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:TOCHITANI, NAOTO;DANNO, SHOHEI;YAMASHITA, SHOKI;REEL/FRAME:024514/0429 Effective date: 20100216 |
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STCB | Information on status: application discontinuation |
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