Feeding patch at hot spot of stationary blade spoiler of gas turbine and preparation method of feeding patch

Abstract

The invention relates to the field of precision casting, and particularly discloses a feeding patch at a hot spot of a gas turbine stationary blade spoiler and a preparation method of the feeding patch, the feeding patches are arranged on the outer surface of a blade body close to the two ends of a blade crown and a blade root and located at the end part of the spoiler, and a hot spot circle on a blade section profile curve is projected to an initial section to form a hot spot circle; a hot spot ball is arranged at the center position of the projected hot spot circle, the hot spot position of the end face of the spoiler is determined, a plurality of feeding channel pitch circle sketches are rolled out according to 1.1 times of the radius along the molded surface of the inner cavity of the blade, and the patch thickness contour, the patch width contour and the feeding patch shape are determined; according to the method, the hot spot position of the spoiler can be accurately determined, and the thickness and width contours of the patch can be accurately determined, so that the feeding channel is opened, the spoiler in the stationary blade of the gas turbine is sequentially solidified, the feeding problem of the hot spot of the spoiler is fundamentally solved, the feeding effect is good, the casting quality and the qualification rate of the stationary blade of the gas turbine are improved, and the production cost is reduced. The method is suitable for the design of gas turbine stationary blade inner cavity spoiler hot spot feeding.

Description

Technical Field

[0001] The invention relates to the field of precision casting, specifically a shrinkage compensation device for a hot spot on a gas turbine stator spoiler and a preparation method thereof. Background Art

[0002] The stators in a gas turbine are also called guide vanes or nozzle vanes. They are fixed blades whose main function is to guide the direction of the airflow, effectively convert the kinetic energy of the airflow into pressure energy (in the compressor) or convert the thermal energy of high-temperature and high-pressure gas into kinetic energy (in the turbine), and guide the airflow to impact the moving blades of the next stage at a suitable angle.

[0003] Large-scale gas turbine stator blades have a complex inner cavity structure, in which a thick and large hot node is often formed at the intersection of the inner cavity spoiler structure and the blade body. During the casting process of the gas turbine stator blade, shrinkage defects are very likely to occur at this hot node. For structures where the inner cavity spoiler is not led out to the inner cavity outlet of the blade, the continuity of the hot node will be lost at the end of the spoiler, and shrinkage defects are more likely to occur due to the poor shrinkage compensation channel. For the above shrinkage defect problem, the conventional casting solution is to change the solidification order by step-wrapping the blade body with cotton and digging holes in the asbestos at the shrinkage position. However, in the actual casting process, after the wax mold of the stator blade is formed, the outer contour has been expanded, and it is difficult to accurately locate the hot node at the spoiler and perform cotton wrapping and digging holes. At the same time, asbestos has little effect on improving the shrinkage compensation effect of the hot node here, and cannot solve this type of problem well. Therefore, the present application proposes a shrinkage compensation patch and preparation method for the hot node of the gas turbine stator spoiler to solve the above problems. Summary of the Invention

[0004] In response to the existing problems, the present invention provides a shrinkage compensation device for a hot node of a gas turbine stator spoiler and a preparation method thereof, which can effectively solve the problems raised in the background technology.

[0005] In order to solve the above problems, the invention adopts the following technical solutions: A shrinkage compensation device for hot spots on a gas turbine stator blade spoiler comprises a gas turbine stator blade, wherein the gas turbine stator blade comprises a blade body, a blade crown and a blade root, a spoiler is provided inside the blade body, and shrinkage compensation devices are provided at both ends of the outer surface of the blade body near the blade crown and the blade root where the spoiler ends.

[0006] A method for preparing a shrinkage compensation patch at a hot spot of a gas turbine stator spoiler comprises the following steps: S1. Draw a 3D model of the gas turbine stator blade, and intercept the blade cross-sectional profile curve perpendicular to the spoiler direction in the 3D model of the gas turbine stator blade. Draw the thermal pitch circle of the spoiler on the blade cross-sectional profile curve, and record the diameter of the thermal pitch circle; S2. Take the starting section of the supplement at the end position of the spoiler and the distance between the starting section and the end position of the spoiler is the radius of the hot pitch circle; S3, projecting the thermal node circle on the blade cross-section profile curve onto the starting cross-section, and setting a thermal node sphere at the center of the projected thermal node circle to determine the thermal node position of the spoiler end face; S4. The center of the superheated pitch ball is used as the vertical center plane of the spoiler. The longitudinal cross-sectional profile of the spoiler blade is taken. Multiple pitch circle sketches of the feeding channel are rolled out along the inner cavity surface of the blade at a radius of 1.1 times. S5. Draw tangent lines on the longitudinal blade cross-section to determine the thickness of the patch. S6. Record the diameter of each pitch circle and set pitch balls at the center of each pitch circle in accordance with the pitch circle diameter. Take the transverse cross-sectional profile of the pitch circle, draw the external tangent of the transverse profile, and determine the compensation width profile. S7. Determine the shrinkage subsidy of the spoiler hot section based on the thickness and width profile of the subsidy, extend the shrinkage subsidy to the edge plate, and roll out the shrinkage channel to the shrinkage riser according to the thickness of the subsidy to determine the shape of the shrinkage subsidy.

[0007] As a further solution of the invention: the thermal pitch circle of the spoiler made on the cross-sectional contour line of the blade in step S1 includes the blade basin side and the blade back side, and the diameter sizes of the thermal pitch circles are recorded respectively.

[0008] As a further solution of the invention: the starting cross section in step S2 is determined by the thermal pitch circle radius of the blade basin side and the blade back side respectively.

[0009] As a further solution of the invention: the starting section in step S2 is set on the side of the turbine stator away from the end position of the spoiler.

[0010] As a further solution of the invention: the center of the center plane superheating node ball in step S4 is set along the length direction of the spoiler.

[0011] Compared with the prior art, the beneficial effects of the invention are: the present invention can accurately determine the position of the hot node of the spoiler, and can accurately determine the thickness and width profile of the patch, thereby opening up the shrinkage feeding channel to enable the spoiler in the gas turbine stator to achieve sequential solidification, fundamentally solving the shrinkage feeding problem of the hot node of the spoiler, with good shrinkage effect, improving the casting quality and pass rate of the gas turbine stator, and is suitable for the design of shrinkage feeding of the hot node of the spoiler in the inner cavity of the gas turbine stator. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Figure 1 This is a schematic diagram of the structure of the shrinkage compensation at the hot node of the turbine stator spoiler in the present invention; Figure 2 It is a schematic diagram of the hot pitch circle in the blade cross-section profile curve in the preparation method of the shrinkage compensation at the hot node of the gas turbine stator spoiler of the present invention; Figure 3Schematic diagram of determining the location of the hot node in the method for preparing the shrinkage compensation patch at the hot node of the gas turbine stator spoiler of the present invention; Figure 4 Schematic diagram of determining the pitch circle of the feeding channel in the method for preparing the feeding patch at the hot node of the gas turbine stator spoiler of the present invention; Figure 5 A schematic diagram of determining the thickness profile of the compensation in the method for preparing the compensation compensation at the hot node of the gas turbine stator spoiler of the present invention; Figure 6 A schematic diagram of determining the width profile of the compensation in the method for preparing the compensation compensation at the hot node of the gas turbine stator spoiler of the present invention; Figure 7 The present invention is a schematic diagram of determining the shape of the shrinkage compensation patch in the preparation method of the shrinkage compensation patch at the hot node of the gas turbine stator spoiler.

[0013] In the picture: 1. Leaf body; 2. Leaf root; 3. Leaf crown; 4. Substrate. DETAILED DESCRIPTION

[0014] In order to enable those skilled in the art to better understand the solutions of the present invention, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts should fall within the scope of protection of the present invention.

[0015] As described in the background technology, large-scale gas turbine stator blades have a complex inner cavity structure, in which a thick and large hot node is often formed at the intersection of the inner cavity spoiler structure and the blade body. During the casting process of the gas turbine stator blade, shrinkage defects are very likely to occur at this hot node. For structures where the inner cavity spoiler is not led out to the inner cavity outlet of the blade, the continuity of the hot node will be lost at the end position of the spoiler, and shrinkage defects are more likely to occur due to the poor shrinkage compensation channel. The conventional casting solution is to change the solidification order by step-wrapping the blade body with cotton and digging holes in the asbestos at the shrinkage position. However, in the actual casting process, after the stator blade wax is molded into a shell, the outer contour has been expanded, and it is difficult to accurately locate the hot node at the spoiler and perform cotton wrapping and digging holes. At the same time, asbestos has little effect on improving the shrinkage compensation effect of the hot node here, and cannot solve this type of problem well.

[0016] In order to solve this technical problem, the present invention provides a shrinkage compensation device and a preparation method for a hot spot on a gas turbine stator spoiler, which are applied in the field of precision casting.

[0017] Specifically, a shrinkage compensation device for hot spots on a gas turbine blade spoiler comprises a gas turbine blade, wherein the gas turbine blade comprises a blade body, a blade crown and a blade root, a spoiler is provided inside the blade body, and shrinkage compensation devices are provided at both ends of the outer surface of the blade body near the blade crown and the blade root where the spoiler ends.

[0018] A method for preparing a shrinkage compensation patch at a hot spot of a gas turbine stator spoiler comprises the following steps: S1. Draw a 3D model of the gas turbine stator blade, and intercept the blade cross-sectional profile curve perpendicular to the spoiler direction in the 3D model of the gas turbine stator blade. Draw the thermal pitch circle of the spoiler on the blade cross-sectional profile curve, and record the diameter of the thermal pitch circle; S2. Take the starting section of the supplement at the end position of the spoiler and the distance between the starting section and the end position of the spoiler is the radius of the hot pitch circle; S3, projecting the thermal node circle on the blade cross-section profile curve onto the starting cross-section, and setting a thermal node sphere at the center of the projected thermal node circle to determine the thermal node position of the spoiler end face; S4. The center of the superheated pitch ball is used as the vertical center plane of the spoiler. The longitudinal cross-sectional profile of the spoiler blade is taken. Multiple pitch circle sketches of the feeding channel are rolled out along the inner cavity surface of the blade at a radius of 1.1 times. S5. Draw tangent lines on the longitudinal blade cross-section to determine the thickness of the patch. S6. Record the diameter of each pitch circle and set pitch balls at the center of each pitch circle in accordance with the pitch circle diameter. Take the transverse cross-sectional profile of the pitch circle, draw the external tangent of the transverse profile, and determine the compensation width profile. S7. Determine the shrinkage subsidy of the spoiler hot section based on the thickness and width profile of the subsidy, extend the shrinkage subsidy to the edge plate, and roll out the shrinkage channel to the shrinkage riser according to the thickness of the subsidy to determine the shape of the shrinkage subsidy.

[0019] The shrinkage compensation patch at the hot node of the gas turbine stator blade spoiler and the preparation method provided by the present invention can accurately determine the hot node position of the spoiler and can precisely determine the thickness and width profile of the compensation patch, thereby opening up the shrinkage compensation channel to enable the spoiler in the gas turbine stator blade to achieve sequential solidification, fundamentally solving the shrinkage compensation problem of the hot node of the spoiler, having a good shrinkage compensation effect, improving the casting quality and pass rate of the gas turbine stator blade, and being suitable for the design of shrinkage compensation of the hot node of the spoiler in the inner cavity of the gas turbine stator blade.

[0020] In order to enable those skilled in the art to better understand the solutions of the present invention, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings.

[0021] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features and technical solutions therein may be combined with each other.

[0022] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, it does not require further definition or explanation in subsequent drawings.

[0023] Example 1 like Figure 2 As shown, this embodiment provides a shrinkage subsidy at the hot node of the spoiler of a gas turbine stator blade, which includes a gas turbine stator blade, which includes a blade body, a blade crown and a blade root. A spoiler is provided in the blade body, and a hot node is formed in the part of the spoiler near the end of the blade crown and the blade root. Shrinkage subsidies are provided on the outer surface of the blade body near the blade crown and the blade root at both ends where the spoiler ends. The shrinkage subsidies are provided at the hot node position, and the shrinkage subsidy is used to open the shrinkage channel to achieve sequential solidification, thereby fundamentally solving the shrinkage problem of the spoiler hot node.

[0024] Example 2 This embodiment provides a method for preparing a shrinkage compensation patch at a hot spot of a gas turbine stator spoiler, which comprises the following steps: S1. Draw a 3D model of the gas turbine stator blade, and intercept the blade cross-section profile curve perpendicular to the spoiler direction in the 3D model of the gas turbine stator blade. Draw the thermal pitch circle of the spoiler on the blade cross-section profile curve. The thermal pitch circle includes the blade basin side and the blade back side, and record the diameter dimensions D1 and D2 of the thermal pitch circle respectively, as shown in the figure. Figure 2 As shown; S2. Take the starting section of the supplement at the end position of the spoiler, and the distance between the starting section and the end position of the spoiler is the radius of the hot pitch circle. The distance between the starting section and the end position of the spoiler is half of the diameter size D1 and D2 on the blade basin side and the blade back side respectively, and the starting section is set on the side of the turbine stator away from the end position of the spoiler; S3, project the thermal node circle on the blade cross-section profile curve onto the starting cross-section, and set the thermal node ball at the center of the projected thermal node circle to determine the thermal node position of the spoiler end face, such as Figure 3 As shown; S4. The center of the overheating node ball is used as the vertical center plane of the spoiler. The center of the overheating node ball on the center plane is set along the length direction of the spoiler. The longitudinal blade cross-sectional profile of the spoiler is taken. Multiple feeding channel pitch circle sketches are rolled out along the inner cavity surface of the blade at a radius of 1.1 times, as shown in the figure below. Figure 4 As shown; S5. Make tangent lines on each pitch circle on the longitudinal blade cross-section to determine the thickness of the patch, such as Figure 5 As shown; S6. Record the diameter of each pitch circle and set the pitch balls at the center of each pitch circle in accordance with the pitch circle diameter. Take the transverse cross-section profile of the pitch circle, make the external tangent of the transverse profile, and determine the compensation width profile, such as Figure 6 As shown; S7. Determine the shrinkage subsidy of the spoiler hot section based on the thickness and width profile of the subsidy. Extend the shrinkage subsidy to the edge plate and roll out the shrinkage channel to the shrinkage riser according to the thickness of the subsidy. Determine the shape of the shrinkage subsidy, such as Figure 7 shown.

[0025] According to steps S1-S7, shrinkage patches are prepared on the base side and the back side of the blade at the spoiler hot node position, and the shrinkage patches are fixed in the wax mold tree according to the size and position of the shrinkage patches. After the tree is completed, casting is carried out. After cooling, the shrinkage patches on the blade body are electrospark machined to remove the patches on the casting, thereby obtaining the casting structure.

[0026] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variations thereof are intended to cover non-exclusive inclusion, so that a process, method, article or apparatus that includes a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or apparatus.

[0027] While embodiments of the invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions, and alterations may be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A gas turbine stator blade spoiler hot spot compensation, comprising a gas turbine stator blade, the gas turbine stator blade comprising a blade body, a blade crown and a blade root, the blade body being provided with a spoiler, characterized in that: Shrinkage compensation is provided at both ends of the outer surface of the blade body close to the blade crown and the blade root, where the spoiler ends.

2. A method for preparing a shrinkage compensation patch at a hot spot of a gas turbine stator spoiler, characterized in that: The steps include: S1. Draw a 3D model of the gas turbine stator blade, and intercept the blade cross-sectional profile curve perpendicular to the spoiler direction in the 3D model of the gas turbine stator blade. Draw the thermal pitch circle of the spoiler on the blade cross-sectional profile curve, and record the diameter of the thermal pitch circle; S2. Take the starting section of the supplement at the end position of the spoiler and the distance between the starting section and the end position of the spoiler is the radius of the hot pitch circle; S3, projecting the thermal node circle on the blade cross-section profile curve onto the starting cross-section, and setting a thermal node sphere at the center of the projected thermal node circle to determine the thermal node position of the spoiler end face; S4. The center of the superheated pitch ball is used as the vertical center plane of the spoiler. The longitudinal cross-sectional profile of the spoiler blade is taken. Multiple pitch circle sketches of the feeding channel are rolled out along the inner cavity surface of the blade at a radius of 1.1 times. S5. Draw tangent lines on the longitudinal blade cross-section to determine the thickness of the patch. S6. Record the diameter of each pitch circle and set pitch balls at the center of each pitch circle in accordance with the pitch circle diameter. Take the transverse cross-sectional profile of the pitch circle, draw the external tangent of the transverse profile, and determine the compensation width profile. S7. Determine the shrinkage subsidy of the spoiler hot section based on the thickness and width profile of the subsidy, extend the shrinkage subsidy to the edge plate, and roll out the shrinkage channel to the shrinkage riser according to the thickness of the subsidy to determine the shape of the shrinkage subsidy.

3. The method for preparing a shrinkage compensation device for a hot spot of a gas turbine stator spoiler according to claim 2, characterized in that: The thermal pitch circle of the spoiler made on the cross-sectional contour line of the blade in step S1 includes the blade basin side and the blade back side, and the diameters of the thermal pitch circles are recorded respectively.

4. The method for preparing a shrinkage compensation device for a hot spot of a gas turbine stator spoiler according to claim 3, characterized in that: The starting cross section in step S2 is determined by the thermal pitch circle radius of the blade pot side and the blade back side respectively.

5. The method for preparing a shrinkage compensation device for a hot spot of a gas turbine stator spoiler according to claim 4, characterized in that: The starting section in step S2 is set on the side of the engine stator blade away from the end position of the spoiler.

6. The method for preparing a shrinkage compensation device for a hot spot of a gas turbine stator spoiler according to claim 1, characterized in that: The center of the center plane superheating node ball in step S4 is set along the length direction of the spoiler.

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