JP5422304B2 - Turbine blade mold and turbine blade manufacturing method - Google Patents

Description

  The present invention relates to a turbine blade mold used for casting of a moving blade and a stationary blade of a turbine, particularly a gas turbine, and a method for manufacturing the turbine blade.

  Generally, turbine blades such as moving blades and stationary blades used in turbines such as industrial gas turbines have a complicated shape such as a three-dimensional shape. Therefore, the turbine blade is manufactured using a precision casting technique called a lost wax method (see, for example, Patent Document 1).

The lost wax method is a casting method that utilizes the melting of a model made of wax (wax), and is described as a molten metal (hereinafter referred to as “hot water”) in a mold having a space in which the wax model is faithfully transferred. ).
The mold is made by immersing the wax model in a slurry called slurry, which is a mixture of refractory liquid binder and refractory powder, then sprinkling the refractory sand and drying it for a while. It is formed. Therefore, the thickness of the mold is adjusted by the number of the above steps.

Japanese Patent Publication No. 6-55339

The wax used for the wax model has a large linear expansion coefficient, and the porosity of the mold changes depending on the humidity and the outside air temperature. In other words, the physical properties of wax models and molds are likely to change depending on the surrounding environment and are easily affected by the surrounding environment. Further, the thickness of the mold changes every time the mold is created, and the thickness may vary depending on the location even in the same mold.
Such changes in the physical property values of the wax and the mold and variations in the thickness of the mold have caused the following problems.

  That is, it affects the temperature distribution in the solidification process of the cast product, or affects the restraint of the cast product by the mold (mold restraint). When casting a precision casting product that requires high dimensional accuracy, such as a turbine blade in a gas turbine, there is a possibility that the dimensional accuracy is distorted due to these effects, which may cause a serious problem.

  In the deformation analysis of a cast product (turbine blade) in the casting process using finite element method (FEM) analysis, the thermal stress based on the temperature difference in the cross section (blade cross section) of the cast product and the mold and cast product As a result of the superposition of the thermal stress based on the difference in linear expansion coefficient, a non-uniform residual stress is generated in the cast product, and the deformation due to this residual stress can be obtained.

  The present invention has been made to solve the above-described problem, and provides a turbine blade mold and a turbine blade manufacturing method capable of suppressing deformation in a precision casting that can be deformed by thermal stress. For the purpose.

In order to achieve the above object, the present invention provides the following means.
The turbine blade mold of the present invention is a turbine blade mold for casting a turbine blade having a leading edge, a trailing edge, a concavely curved pressure surface and a convexly curved suction surface, and the shape of the turbine blade is An airfoil space having a predetermined distance from the airfoil space in a cross-sectional view of the airfoil space, and from a region corresponding to the pressure surface of the airfoil space through a portion corresponding to the trailing edge. And a mold main body having a heat insulating space extending in a span direction of the turbine blade and extending to a region corresponding to the suction surface.

According to the present invention, since the heat insulating space is disposed so as to cover the portion corresponding to the trailing edge in the airfoil space, the region where the heat insulating space in the mold body is provided is the other region. In comparison, the thermal conductivity is lowered.
For this reason, when the airfoil space is filled (cast) with hot metal, which is a molten metal, variation in temperature drop in the entire turbine blade is suppressed. In other words, the temperature drop in the vicinity of the trailing edge, which has a smaller heat capacity compared to other parts of the turbine blade, is moderate compared to the case where no heat insulation space is provided. Is suppressed.

  A turbine blade mold according to the present invention is a turbine blade mold for casting a turbine blade having a leading edge, a trailing edge, a concavely curved pressure surface, and a convexly curved suction surface. A mold body having an airfoil space having a shape is provided, and an outer surface of the mold body covering a region corresponding to the trailing edge of the airfoil space corresponds to the trailing edge from a region corresponding to the pressure surface. A groove portion extending to a region corresponding to the suction surface through a portion to be provided is provided at an interval in the span direction of the turbine blade.

  According to the present invention, since the groove portion is provided, the rigidity in the span direction in the portion covering the rear edge of the mold body is lowered. Therefore, even if the turbine blade cast into the airfoil space is solidified and contracted during the solidification process, thermal stress is hardly generated at the trailing edge portion of the turbine blade.

  Specifically, since the linear expansion coefficient of the mold body is smaller than that of the cast turbine blade, the solidification shrinkage of the turbine blade during the solidification process is restricted by the mold body. In particular, the rear edge portion having a small cross-sectional area as compared with other portions is likely to be solidified and contracted by the mold body, so that thermal stress tends to occur.

  Therefore, in the turbine blade mold of the present invention, a groove is provided in a portion covering the rear edge of the mold body, and the rigidity in the span direction of the portion of the mold body is reduced, whereby the solidification at the trailing edge portion of the turbine blade by the mold body. The restraint force of contraction is reduced. This makes it difficult for thermal stress to occur at the trailing edge of the turbine blade.

  The depth of the groove in the groove is preferably a depth that reduces the rigidity of the mold body and does not damage the mold body in the groove when the turbine blade is cast. For example, the thickness of the mold body About half the depth.

  The turbine blade manufacturing method of the present invention includes a mold forming step of forming the turbine blade mold of the present invention, a casting step of filling molten metal in the airfoil space of the turbine mold, It is characterized by having.

  According to the present invention, it is possible to suppress the deformation of the turbine blade by casting the turbine blade using the turbine blade mold of the present invention.

  According to the turbine blade mold and the turbine blade manufacturing method of the present invention, the airfoil space is disposed at a predetermined interval, and the region corresponding to the pressure surface of the airfoil space is passed through the portion corresponding to the trailing edge. The heat insulation space that extends to the area corresponding to the suction surface and extends in the span direction of the turbine blade is provided, so that the deformation in the turbine blade that is a precision cast product that can be deformed by thermal stress can be suppressed. Play.

  According to the turbine blade mold and the turbine blade manufacturing method of the present invention, the portion corresponding to the trailing edge from the region corresponding to the pressure surface is formed on the outer surface of the mold body covering the region corresponding to the trailing edge of the airfoil space. Since the groove portion extending to the area corresponding to the suction surface is provided, it is possible to suppress the deformation in the turbine blade, which is a precision cast product that can be deformed by thermal stress.

It is a schematic diagram explaining the structure of the casting_mold | template which concerns on the 1st Embodiment of this invention. It is AA sectional view of FIG. 1 explaining the structure of the casting_mold | template of FIG. It is a schematic diagram explaining the formation process of the casting_mold | template of FIG. FIG. 2 is a cross-sectional view for explaining a mold forming process of FIG. 1. It is a schematic diagram explaining the structure of the casting_mold | template of the 2nd Embodiment of this invention. FIG. 6 is a cross-sectional view taken along the line BB of FIG. It is a schematic diagram explaining another Example of the 2nd Embodiment of this invention. It is a schematic diagram explaining another Example of the 2nd Embodiment of this invention. It is a schematic diagram explaining another Example of the 2nd Embodiment of this invention. It is a schematic diagram explaining relative arrangement | positioning of the airfoil space and runner in the casting_mold | template of reference embodiment of this invention. It is a schematic diagram explaining the structure of the common casting_mold | template which has a pair of airfoil space.

[First Embodiment]
Hereinafter, a turbine blade mold and a turbine blade manufacturing method (casting method) according to a first embodiment of the present invention will be described with reference to FIGS. 1 to 4.
FIG. 1 is a schematic diagram for explaining the configuration of a mold according to the present embodiment. 2 is a cross-sectional view taken along the line AA of FIG. 1 for explaining the configuration of the mold of FIG.

The mold (turbine blade mold) 1 of this embodiment is used for casting of turbine blades such as turbine rotor blades and turbine stationary blades of gas turbines, and particularly when cast by the lost wax method. It is used.
As shown in FIG. 1 and FIG. 2, the mold 1 has an airfoil space 2, a heat insulating space 3, a gate 4, a runner 5, an upper seal 6, and a lower seal 7 inside. A mold body 8 is mainly provided.

The airfoil space 2 is a space formed inside the mold body 8 and has an inner surface shape that is the same as the outer shape of the turbine blade, and is filled with hot metal that is a molten metal when the turbine blade is cast. It is. Further, the airfoil space 2 is also a space that communicates with the upper side seal 6 and the lower side seal 7.
The airfoil space 2 includes a space leading edge 21, a space trailing edge (part corresponding to the trailing edge) 22, a space pressure surface (region corresponding to the pressure surface) 23, and a space suction surface (corresponding to the suction surface). A region) 24 and a space mounting portion 25 are mainly provided.

The space leading edge 21 and the space trailing edge 22 are portions corresponding to the leading edge and the trailing edge of the turbine blade, respectively, of the inner surface shape in the airfoil space 2, and are the leading edge portion and the trailing edge of the cast turbine blade. The edge portion is formed.
The space positive pressure surface 23 and the space negative pressure surface 24 are a positive pressure surface that is a curved surface on the ventral side curved in a concave shape of the turbine blade and a curved surface on the back side that is curved in a convex shape among the inner surface shapes in the airfoil space 2. A portion corresponding to a certain suction surface, which forms a pressure surface portion and a suction surface portion of a cast turbine blade.

The space attachment portion 25 is a portion corresponding to a turbine blade attachment portion on the inner surface of the airfoil space 2 and forms a cast turbine blade attachment portion. The space attachment portion 25 is disposed at the end of the airfoil space 2 on the side of the gate 4 (upper side in FIG. 1). Therefore, a portion corresponding to the tip of the turbine blade in the airfoil space 2 is disposed at the lower end of FIG.
Upper space 6 communicates with space mounting portion 25, and lower surface 7 communicates with the lower end of airfoil space 2.

  The heat insulating space 3 is a space formed inside the mold body 8 and is a space formed so as to cover the vicinity of the space trailing edge 22 in the airfoil space 2. Further, the heat insulating space 3 is a space communicating with the outside of the mold body 8.

As shown in the sectional view of the airfoil space 2 in FIG. 2, the heat insulating space 3 is arranged at a predetermined interval from the airfoil space 2. In other words, a part of the mold body 8 having a predetermined thickness is disposed between the heat insulating space 3 and the airfoil space 2.
Further, the heat insulating space 3 is a space extending from the space pressure surface 23 of the airfoil space 2 to the space suction surface 24 via the space trailing edge 22 and, as shown in FIG. This is a space extending in the vertical direction of FIG.

The gate 4 is a space formed in the mold body 8 and is a space that opens upward, and is a portion into which hot water is poured during casting. A runner 5 and an upper skirt 6 communicate with the gate 4.
The gate 4 is the uppermost space among the spaces provided in the mold body 8. Therefore, the hot water poured into the gate 4 is filled into other spaces such as the airfoil space 2 by gravity.

  The runner 5 is a space formed inside the mold body 8 and extends in the vertical direction along the airfoil space 2. The upper end portion of the runner 5 is communicated with the gate 4 and the upper cough 6, and the lower end portion is communicated with the lower cuff 7.

The upper side seal 6 and the lower side seal 7 are spaces formed inside the mold body 8, and are spaces that guide hot water to the airfoil space 2.
One end portion of the upper seal 6 is communicated with the runner 5 and the sprue 4, and the other end portion is communicated with the space attaching portion 25 of the airfoil space 2.
One end portion of the lower side seal 7 communicates with the runner 5, and the other end portion communicates with the tip of the airfoil space 2.

The mold main body 8 forms the wall surfaces of the airfoil space 2, the heat insulation space 3, the gate 4, the runner 5, the upper seal 6 and the lower seal 7, and constitutes the outer shape of the mold 1.
The mold body 8 has a so-called shell structure in which layers formed by a dipping process and a drying process described later are stacked.

Next, a method for casting a turbine blade using the mold 1 having the above-described configuration will be described.
First, a mold forming process for forming the above-described mold 1 is performed, and then a casting process for casting a turbine blade using the formed mold 1 is performed.

FIG. 3 is a schematic diagram for explaining a forming process of the mold of FIG. FIG. 4 is a cross-sectional view for explaining a process of forming the mold of FIG.
In the mold forming step, as shown in FIGS. 3 and 4, the airfoil model M2 having the shape of the airfoil space 2, the gate 4, the runner 5, the upper cough 6, and the lower cuff 7, and the heat insulating space 3 The heat insulating model M3 having the shape is formed.
The airfoil model M2 and the heat insulation model M3 are modeled using wax that dissolves or disappears when heated. In addition, as a wax used for modeling, the well-known thing used for the lost wax method can be used, and it does not specifically limit.

  Then, the wing shape model M2 is immersed in a muddy material called a slurry in which a refractory liquid binder and refractory powder are mixed, and the wing shape model M2 in which refractory sand is immersed is sprinkled. The drying process for drying for a while is repeated a predetermined number of times. As a result, a part of the mold body 8 is formed around the airfoil model M2. The part of the mold body 8 is a state in which only the vicinity of the airfoil model M2 in the mold body 8 is formed, and the outer surface portion of the mold body 8 is not yet formed.

  The number of repetitions of the dipping process and the drying process here is such a thickness that the mold body 8 between the airfoil space 2 and the heat insulation space 3 is not damaged when casting the turbine blade using the mold 1. The number of times is desirable.

And as shown in FIG. 4, the heat insulation model M3 is adhere | attached on a part of casting_mold | template main body 8 as shown in FIG.
Thereafter, the dipping process and the drying process are repeatedly performed with the heat insulation model M3 adhered, and the mold body 8 is formed to a predetermined thickness. As described above, since the mold body 8 has a structure in which layers formed by the dipping process and the drying process are laminated, it is also called a shell mold.

When the mold body 8 is formed, a dewaxing process for removing the airfoil model M2 and the heat insulation model M3 contained therein is performed. Specifically, the mold body 8 including the airfoil model M2 and the heat insulation model M3 is heated, and the wax forming the airfoil model M2 and the heat insulation model M3 is melted to flow out of the mold body 8, or the wax is removed. Removal is performed by disappearing.
Thereby, the airfoil space 2 and the heat insulation space 3 are formed in the mold body 8.
Thereafter, the mold body 8 is fired as necessary, and the mold 1 as shown in FIGS. 1 and 2 is completed.

When the mold 1 is completed, a casting process for casting the turbine blade is performed.
Specifically, a metal constituting the turbine blade, for example, a nickel-based alloy is melted in a melting furnace to prepare hot water that is a molten metal.

The hot water is taken out from the melting furnace, poured into the pouring gate 4 of the mold 1 shown in FIG. 1, and flows from the pouring gate 4 into the upper seal 6 and the runner 5. At this time, the mold 1 is preheated.
The hot water that has flowed into the upper foil 6 flows into the airfoil space 2. On the other hand, the hot water that has flowed into the runner 5 flows into the airfoil space 2 via the lower side seal 7. In this way, hot water is filled into the airfoil space 2.

The hot water filled in the airfoil space 2 and the like is gradually cooled and solidified by releasing heat to the outside through the mold 1.
At this time, since the heat insulating space 3 is arranged so as to cover the vicinity of the space trailing edge 22 in the airfoil space 2, heat is not easily released to the outside from the vicinity of the space trailing edge 22 compared to other portions. It has become. Therefore, the temperature drop in the vicinity of the trailing edge of the turbine blade, which has a smaller heat capacity compared to other parts, becomes slow and gentle, and variations in temperature drop across the entire turbine blade can be suppressed.

  When the solidification of the hot water filled in the airfoil space 2 is completed, the one in which the turbine blades, the upper seal, the lower seal, and the runner are integrated is taken out from the mold 1. Then, the upper side cuff, the lower side cuff, the runner and the like are separated from the turbine blade.

According to said structure, since the heat insulation space 3 will be arrange | positioned so that the space rear edge 22 in the airfoil space 2 may be covered, the area | region in which the heat insulation space 3 in the mold main body 8 is provided is other than that Compared with the region, the thermal conductivity is low.
Therefore, when the airfoil space 2 is filled (cast) with hot metal, which is a molten metal, variation in temperature drop in the entire turbine blade is suppressed. In other words, the temperature drop in the vicinity of the trailing edge, which has a smaller heat capacity compared to other parts of the turbine blade, is moderate as compared to the case where the space trailing edge 22 is not provided. The variation of is suppressed. As a result, it is possible to suppress deformation of a precision casting having a cross-sectional shape like a turbine blade of a gas turbine.

In the above-described embodiment, casting is performed in a state where the mold 1 is preheated, but this preheating temperature may be about the temperature of the hot water poured (pouring temperature), and is not particularly limited.
By increasing the preheating temperature in this way, it is possible to prevent a rapid temperature drop of the hot water during pouring. Therefore, the thermal stress due to the temperature difference generated in the cross section of the cast turbine blade can be relieved and residual deformation can be suppressed.
Further, by increasing the preheating temperature, it is possible to relieve the thermal stress due to the difference in thermal elongation between the mold 1 and the cast turbine blades when the mold 1 and the poured hot water cool to room temperature (for example, room temperature).

[Second Embodiment]
Next, a second embodiment of the present invention will be described with reference to FIGS.
The basic configuration of the mold of this embodiment is the same as that of the first embodiment, but the configuration of the mold main body in the vicinity of the trailing edge of the mold is different from that of the first embodiment. Therefore, in this embodiment, only the configuration in the vicinity of the space rear edge in the mold body will be described with reference to FIGS.
FIG. 5 is a schematic diagram illustrating the configuration of the mold according to the present embodiment. 6 is a cross-sectional view taken along the line B-B in FIG. 5 for explaining the configuration of the mold in FIG. 5.
In addition, about the component same as 1st Embodiment, the same code | symbol is attached | subjected and the description is abbreviate | omitted.

  As shown in FIGS. 5 and 6, the mold 101 includes a mold main body 108 having an airfoil space 2, a gate 4, a runner 5, an upper squeeze 6, and a lower seki 7 inside. It is mainly provided. In other words, the heat insulating space 3 is not formed inside compared with the mold 1 in the first embodiment.

The mold main body 108 forms the wall surfaces of the airfoil space 2, the heat insulation space 3, the gate 4, the runner 5, the upper seal 6 and the lower seal 7, and constitutes the outer shape of the mold 101.
The mold body 108 has a so-called shell structure in which layers formed by a dipping process and a drying process described later are stacked.
As shown in FIG. 5, a slit portion (groove portion) 103 is provided on the outer surface of the mold body 108 in the vicinity of the space rear edge 22.

The slit portion 103 is a groove extending from the space pressure surface 23 to the space suction surface 24 via the space trailing edge 22 and is provided at intervals in the span direction (vertical direction in FIG. 5) of the airfoil space 2. Is.
In the present embodiment, the description will be made by applying to the case where the depth of the groove of the slit portion 103 is about half the thickness of the mold body 108.

  The depth of the groove in the slit portion 103 is preferably a depth that reduces the rigidity of the mold body 108 and does not damage the mold body 108 in the slit portion 103 when casting the turbine blade. It is not limited.

Next, a method for casting a turbine blade using the mold 101 having the above-described configuration will be described.
Note that the mold forming process for forming the mold 101 described above does not require the thermal insulation model M3 to be embedded in the mold main body 108, as compared with the mold forming process in the first embodiment. Further, a step of forming the slit portion 103 after the mold body 108 is formed to a predetermined thickness is added. As a method of forming the slit portion 103, a known processing method such as cutting can be used, and there is no particular limitation.

In addition, the casting process for casting the turbine blade using the formed mold 101 is the same as that in the first embodiment, and thus the description thereof is omitted.
When casting is performed, the mold 101 is preheated using a preheating furnace and cast in a casting furnace.

  According to the above configuration, by providing the slit portion 103, the rigidity in the span direction at the portion covering the space rear edge 22 of the mold main body 108 is lowered. Therefore, even if the turbine blade cast into the airfoil space 2 is solidified and contracted during the solidification process, thermal stress is hardly generated at the trailing edge portion of the turbine blade.

  Specifically, since the linear expansion coefficient of the mold body 108 is smaller than that of the cast turbine blade, the solidification shrinkage of the turbine blade in the solidification process is restricted by the mold body 108. In particular, since the rear edge portion having a small cross-sectional area compared to other portions is easily solidified and contracted by the mold body 108, thermal stress is likely to occur.

  Therefore, in the mold 101 of the present embodiment, the slit portion 103 is provided in the portion of the mold body 108 that covers the space rear edge 22, and the rigidity in the span direction at the space rear edge 22 of the mold body 108 is reduced. The binding force of solidification shrinkage in the trailing edge portion of the turbine blade is reduced. This makes it difficult for thermal stress to occur at the trailing edge of the turbine blade.

FIG. 7 is a schematic diagram for explaining another example of the present embodiment.
As in the above-described embodiment, casting may be performed after the mold 101 is preheated in a preheating furnace, or as shown in FIG. 7, the portion of the mold 101 having a small heat capacity, that is, the space trailing edge 22 The vicinity may be heated using a burner or a heat generating material. By doing in this way, the uneven temperature fall in the turbine blade immediately after casting can be suppressed, and a thermal stress can be reduced.

FIG. 8 is a schematic diagram for explaining still another example of the present embodiment.
Furthermore, as shown in FIG. 8, a heat insulating material 104 having heat resistance may be disposed in the vicinity of the space leading edge 21 and the space trailing edge 22 in the mold 101, and is not particularly limited.
The place where the heat insulating material 104 is disposed is obtained with reference to the result of heat conduction analysis, for example. The thickness of the heat insulating material 104 can be determined with reference to the heat capacity in the mold 101. In FIG. 8 , one heat insulating material 104 is disposed in the vicinity of the space front edge 21 and in the vicinity of the space rear edge 22. An example in which three heat insulating materials 104 are arranged is shown.

By doing in this way, the uneven temperature fall in the turbine blade immediately after casting can be suppressed, and a thermal stress can be reduced. As a result, deformation at the time of solidification in the turbine blade can be suppressed.
In addition, what is arrange | positioned at the casting_mold | template 101 is not restricted to the heat insulating material 104, A heat insulating material may be sufficient.

FIG. 9 is a schematic diagram illustrating still another example of the present embodiment.
Furthermore, casting may be performed in a state where the mold 101 is supported using the support jig 110 shown in FIG. 9 and the mold 101 is floated inside. By doing in this way, the contact of the casting_mold | template 101 and the ground can be eliminated, and the rapid fall of the temperature of the casting_mold | template 101 by the contact with the ground can be prevented.

The support jig 110 is provided with a base 111, a support column 112, an upper support portion 113, and a lower support portion 114.
The base 111 is disposed on the lowermost side of the support jig 110 and supports the support jig 110 itself and the mold 101. A column 112 is attached to the base 111.
The column 112 is a columnar member extending upward from the base 111 and supports the mold 101 together with the upper support 113 and the lower support 114.

The upper support portion 113 is a beam-like member that protrudes laterally from the upper end portion or the vicinity of the end portion of the support column 112, and supports the periphery of the gate 4 in the mold 101.
The lower support portion 114 is a member disposed near the center of the support column 112 and supports the periphery of the lower end portion of the runner 5 in the mold 101.

[ Reference embodiment]
Next, a reference embodiment of the present invention will be described with reference to FIGS.
The basic configuration of the mold of this reference embodiment is the same as that of the first embodiment, but the relative arrangement of the airfoil space and the runner is different from that of the first embodiment. Therefore, in this reference embodiment, only the relative arrangement of the airfoil space and the runner will be described with reference to FIGS. 10 and 11, and description of other components and the like will be omitted.
Figure 10 is a schematic view illustrating the relative arrangement of the airfoil space and runner in the mold of the present reference embodiment.
In addition, about the same component as 1st Embodiment, the same code | symbol is attached | subjected and the description is abbreviate | omitted.

As shown in FIG. 10, the mold 201 is mainly provided with at least a pair of airfoil spaces 2 and 2, a runner 5, and a mold main body 208 provided therein.
The runner 5 is disposed in the vicinity of the space trailing edge 22 in the pair of airfoil spaces 2 and 2. Further, the pair of airfoil spaces 2 and 2 are arranged rotationally symmetric about the runner 5.

FIG. 11 is a schematic diagram illustrating the configuration of a general mold having a pair of airfoil spaces.
Here, the configuration of a general mold 1A having a pair of airfoil space 2,2, be described in comparison with the template 201 of the present reference embodiment.
As shown in FIG. 11, the mold 1A has a pair of airfoil spaces 2, 2, a pouring gate 4 and a runner 5, and a pair of upper and lower sew 6 and 7 inside. 8A is mainly provided.

The mold 1 </ b> A differs from the mold 201 in the relative arrangement position of the pair of airfoil spaces 2 and 2 and one runner 5.
Specifically, in the mold 1A, the pair of airfoil spaces 2 and 2 and the one runner 5 are arranged apart from each other, whereas in the mold 201, the pair of airfoil spaces 2 and 2 are disposed. The runway 5 is different in the vicinity of the space rear edge 22 in FIG.

Next, a method for casting a turbine blade using the mold 201 having the above-described configuration will be described.
The mold forming process for forming the above-described mold 201 is the same as that of the first embodiment except that the heat insulation model M3 does not need to be embedded in the mold body 208 as compared with the mold forming process in the first embodiment. Since it is the same, the description is omitted.
Further, the casting process for casting the turbine blade using the formed mold 101 is also the same as that in the first embodiment, and the description thereof is omitted.

According to said structure, the radiant heat transfer from the hot water with which the runway 5 was filled is transmitted to the rear edge of the cast turbine blade. Therefore, compared with the case where the runway 5 and the space trailing edge 22 are not arranged close to each other, the temperature drop at the trailing edge of the cast turbine blade is slow and gentle.
Specifically, because the trailing edge of the turbine blade has a smaller heat capacity than the other parts, the temperature drop at the trailing edge after casting the turbine blade is faster than the other parts. It was. Therefore, by applying heat radiated from the hot water filled in the runner 5 to the rear edge portion, the temperature drop at the rear edge becomes moderate. As a result, variation in temperature drop in the entire turbine blade is suppressed, and deformation can be suppressed.

  Furthermore, by arranging the runner 5 in the center and the space trailing edge 22 close to the both sides, the radiant heat transfer from the hot water filled in the runner 5 is transmitted to each of the turbine blades cast into each. It becomes easy to be transmitted to the trailing edge. Therefore, the temperature drop at the trailing edge of the cast turbine blade is slow and gentle, and the variation in the temperature drop across each turbine blade is further suppressed.

1,10 1 mold (mold for turbine blade)
2 Airfoil space 3 Thermal insulation space 8, 10 8 Mold body 22 Space trailing edge (part corresponding to trailing edge)
23 Spatial pressure surface (area corresponding to pressure surface)
24 Spatial suction surface (area corresponding to suction surface)
103 Slit (groove)

Claims (3)

A turbine blade mold for casting a turbine blade having a leading edge, a trailing edge, a concavely curved pressure surface, and a convexly curved suction surface,
An airfoil space having the shape of the turbine blade;
In a cross-sectional view of the airfoil space, the airfoil space is disposed at a predetermined interval, and corresponds to the suction surface from a region corresponding to the pressure surface of the airfoil space through a portion corresponding to the trailing edge. And a heat insulating space extending in the span direction of the turbine blade,
A mold for a turbine blade, characterized in that a mold main body having an inside is provided. A turbine blade mold for casting a turbine blade having a leading edge, a trailing edge, a concavely curved pressure surface, and a convexly curved suction surface,
A mold body having an airfoil space having the shape of the turbine blade is provided therein,
An outer surface of the mold main body that covers a region corresponding to the trailing edge of the airfoil space extends from a region corresponding to the pressure surface to a region corresponding to the suction surface through a portion corresponding to the trailing edge. A mold for turbine blades, characterized in that grooves are provided at intervals in the span direction of the turbine blade.   A mold forming step for forming the turbine blade mold according to claim 1 or 2,
  A casting step of filling the airfoil space of the turbine mold with hot metal that is a molten metal;
A method for manufacturing a turbine blade, comprising:

Images