CN214844305U - Ceramic core shrinkage rate test die for turbine blade - Google Patents
Ceramic core shrinkage rate test die for turbine blade Download PDFInfo
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- CN214844305U CN214844305U CN202120132097.7U CN202120132097U CN214844305U CN 214844305 U CN214844305 U CN 214844305U CN 202120132097 U CN202120132097 U CN 202120132097U CN 214844305 U CN214844305 U CN 214844305U
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Abstract
The invention is suitable for the technical field of ceramic cores of turbine blades, and provides a mold for testing the shrinkage rate of a ceramic core, which comprises: the core shrinkage test sample piece comprises a core shrinkage test sample forming die and a wax mold die matched with the core forming die, wherein the core forming die is used for manufacturing a core shrinkage test sample, and the wax mold die is used for preparing a casting shrinkage test sample piece based on a core. The thickness of the core structure manufactured by the shrinkage rate test die is different in the first direction, the length of the core structure manufactured by the shrinkage rate test die is different in the second direction, the change of the thickness, the length and the width of each measuring part of the core is measured in the processes of core biscuit forming, sintering and casting, the forming shrinkage rate, the sintering shrinkage rate and the casting shrinkage rate of the core can be calculated according to the measured values, and the shrinkage rate results have important reference values for the process development of the turbine blade core.
Description
Technical Field
The invention belongs to the technical field of shrinkage rate testing, and particularly relates to a ceramic core shrinkage rate testing mold and a ceramic core shrinkage rate testing method for turbine blades.
Background
Turbine blades are the core thermal component of an aircraft engine gas turbine, and their temperature capability determines the turbine inlet temperature and the engine fuel efficiency. The turbine blade usually adopts hollow structure in order to improve the ability of bearing the temperature, and ceramic core is the key adaptor that realizes turbine blade hollow structure, and in order to guarantee the qualification rate of turbine blade inner chamber size, the ceramic core that the size satisfies the design requirement is one of the prerequisite.
The forming shrinkage, sintering shrinkage and casting shrinkage are the crucial technical indexes of the ceramic core production process, and the existing turbine blade ceramic core shrinkage test method refers to the part 2 of the HB 5353.2-2004 investment casting ceramic core performance test method: the measurement of firing shrinkage "was carried out by using a standard sample having a very simple shape. However, the turbine blade has the defects that the thickness difference of the structure of the turbine blade is large, the length difference of the turbine blades of different models is large, the difference of the characteristic structural characteristics of the turbine blade and the shape of a standard sample specified by HB5353.2 is large, the forming shrinkage rate and sintering shrinkage rate results of the standard sample are greatly different from the actual situation of the ceramic core of the turbine blade, and the ceramic core production process is not suitable.
Disclosure of Invention
The invention provides a mold and a method for testing the shrinkage rate of a ceramic core for a turbine blade, and aims to solve the technical problem of the existing shrinkage rate.
The invention is realized in such a way that a ceramic core shrinkage test die for a turbine blade comprises: the device comprises a core forming die and a wax die matched with the core forming die, wherein the core forming die is used for manufacturing a core shrinkage rate test sample, and the wax die is used for manufacturing a casting shrinkage rate test sample piece based on the core;
the core forming mold comprises a base cavity and a main body cavity communicated with the base cavity, wherein a plurality of test cavities are arranged on the main body cavity, the thicknesses of the test cavities are different in a first direction, the lengths of the test cavities are different in a second direction, a plane for forming a reference surface on the core is arranged on the base, the first direction is parallel to the plane, and the second direction is perpendicular to the plane;
the different thicknesses of the plurality of test cavities in the first direction are a simplified distribution based on a thickness variation characteristic of the ceramic core structure for the turbine blade in the first direction, and the different length variations of the plurality of test cavities in the second direction are a simplified distribution based on a length variation characteristic of the ceramic core structure for the turbine blade in the second direction;
the shape of the wax pattern mold corresponds to the shape of the core forming mold to cast a casting shrinkage test sample piece for testing the core casting shrinkage based on the core shrinkage test standard.
Preferably, the plurality of test cavities are arranged in a stepped structure with gradually decreasing thickness in the first direction.
Preferably, the plurality of test cavities comprises: the test device comprises a first test cavity, a second test cavity, a third test cavity and a fourth test cavity.
Preferably, the thickness of the first testing cavity is 8mm, the thickness of the second testing cavity is 5mm, the thickness of the third testing cavity is 3mm, and the thickness of the fourth testing cavity is 0.5 mm.
Preferably, a spacer for forming a shrinkage groove on the core is disposed between the second test cavity and the third test cavity.
The invention also provides a ceramic core shrinkage rate test method based on the test mould, which comprises the following steps:
s1, manufacturing a core biscuit as a core shrinkage test sample through the core forming die, wherein the core biscuit is provided with a plurality of measuring parts corresponding to the ceramic core structure for the turbine blade;
s2, respectively measuring the thickness and the length of the plurality of measuring parts of each core biscuit to obtain biscuit measuring values, and calculating the molding shrinkage rate of the core biscuit according to the ratio of the biscuit measuring values to the mold measuring values;
s3, sintering the multiple core biscuit blanks to obtain a corresponding number of sintering cores;
s4, respectively measuring the thickness and the length of the plurality of measuring parts of each sintering core to obtain sintering measured values, and calculating the ratio of the sintering measured values to the biscuit measured values to obtain the sintering shrinkage rate of the sintering core;
s5, placing the plurality of sintering cores into the wax mold to manufacture a wax mold, and manufacturing a plurality of metal castings serving as casting shrinkage rate test sample pieces by adopting a precision casting method based on the wax mold;
and S6, respectively measuring the thickness and the length of each metal casting corresponding to the plurality of measuring parts of the core to obtain casting measured values, and calculating the casting shrinkage rate of the core according to the ratio of the casting measured values to the sintering measured values.
Preferably, the plurality of measurement portions include a simplified distribution in the first direction according to a thickness variation characteristic of the ceramic core structure for the turbine blade in the first direction, and include a simplified distribution in the second direction according to a length variation characteristic of the ceramic core structure for the turbine blade in the second direction.
Preferably, the biscuit measurement is an arithmetic mean of measurements taken on a plurality of core biscuits;
the sintering measurement value is an arithmetic average value obtained after measuring a plurality of sintering cores;
the casting measurement value is an arithmetic average value of a plurality of casting shrinkage test samples.
Preferably, in step S6, the casting measurement is obtained by using a three-coordinate scan or a blue scan.
Preferably, in step S2, the calculating the molding shrinkage of the core biscuit based on the ratio of the biscuit measurement to the mold measurement comprises:
obtaining the molding shrinkage rate of the biscuit mold core in the length direction in different thickness areas;
obtaining the molding shrinkage rates of the biscuit mold core with different thicknesses;
obtaining the molding shrinkage rate of the biscuit type core in the width direction;
in the step S4, obtaining the sintering shrinkage of the sintered core according to the sintering measurement value includes:
obtaining the molding shrinkage rate of the sintering mold core in the length direction in different thickness areas;
obtaining the molding shrinkage rates of the sintering mold core with different thicknesses;
obtaining the molding shrinkage rate of the sintering type core string in the width direction;
the step S6, wherein obtaining the casting shrinkage of the casting core based on the casting measurement includes:
obtaining the molding shrinkage rate of the casting core in the length direction in different thickness areas;
obtaining the molding shrinkage rates of the casting core with different thicknesses;
and obtaining the molding shrinkage rate of the casting core in the width direction.
Compared with the prior art, the invention has the following beneficial effects: the thickness of the core structure manufactured by the shrinkage rate test die is different in the first direction, the length of the core structure manufactured by the shrinkage rate test die is different in the second direction, the thickness, the length and the width of each measuring part of the core are measured in the core manufacturing, sintering and casting processes, and the corresponding forming shrinkage rate, sintering shrinkage rate and casting shrinkage rate can be calculated according to the measured values, and the shrinkage rate results have important reference values for the process development of the turbine blade core.
Drawings
Fig. 1 is a schematic structural view of a core forming mold according to the present invention;
FIG. 2 is a schematic view of a wax pattern mold according to the present invention;
FIG. 3 is a schematic structural view of a wax pattern mold assembly core provided by the present invention;
FIG. 4 is a schematic view of a core structure provided by the present invention based on the manufacture of a core-forming mold;
FIG. 5 is a cross-sectional view of a core provided by the present invention;
FIG. 6 is a schematic structural view (in cross-section) of a metal casting provided by the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
Example one
The invention provides a ceramic core shrinkage rate test die for a turbine blade, which comprises the following components in percentage by weight as shown in figures 1-3: the core forming mold comprises a core forming mold 10 and a wax mold 20 matched with the core forming mold 10, wherein the core forming mold 10 is used for manufacturing a core 30 as a shrinkage rate test sample, and the wax mold 20 is used for manufacturing a metal casting based on the core 30 as a casting shrinkage rate test sample.
In this embodiment, the core forming mold 10 includes a base cavity 11 and a body cavity 12 communicated with the base cavity 11, the body cavity 12 is provided with a plurality of test cavities, thicknesses of the plurality of test cavities are different in a first direction, lengths of the plurality of test cavities are different in a second direction, the base cavity 11 is provided with a plane for forming a reference plane on the core, the first direction is parallel to the plane, and the second direction is perpendicular to the plane.
In this embodiment, the different thicknesses of the plurality of test cavities in the first direction are a simplified distribution based on a thickness variation characteristic of the ceramic core structure for the turbine blade in the first direction, and the different length variations of the plurality of test cavities in the second direction are a simplified distribution based on a length variation characteristic of the ceramic core structure for the turbine blade in the second direction. It should be noted that the thickness or length change characteristic of the ceramic core used in the turbine blade is generally smoothly tapered, and the plurality of test cavities of the present embodiment are designed to form a core having a plurality of measurement portions, and the structure is simplified, not a smoothly tapered structure, but a stepped simplified structure.
In this embodiment, the shape of the wax pattern mold 20 corresponds to the shape of the core molding mold 10, so that a metal casting is cast based on the core 30 as a casting shrinkage rate test sample, so that the formed metal casting also has a stepped thickness variation structure like the core 30.
Specifically, in the present embodiment, the plurality of test cavities are arranged in a stepped structure having a gradually decreasing thickness in the first direction based on the shape of the ceramic core and the structure for the turbine blade.
As an alternative embodiment, the plurality of test cavities of the core-forming mold 10 includes: with such a structure, as shown in fig. 4 and 5, the first test cavity 121, the second test cavity 122, the third test cavity 123, and the fourth test cavity 124 may form a first measurement portion 321, a second measurement portion 322, a third measurement portion 323, and a fourth measurement portion 324 on the core 30, wherein the first measurement portion 321, the second measurement portion 322, the third measurement portion 323, and the fourth measurement portion 324 have thicknesses gradually decreasing in the first direction and lengths different in the second direction depending on the structure of the core molding die 10. Of course, the structure is a sampling measurement based on the shape of the turbine blade, and the number of samples may be more or less than the four measurement portions of the present embodiment.
In this embodiment, the thickness of the first test cavity is 8mm, the thickness of the second test cavity is 5mm, the thickness of the third test cavity is 3mm, and the thickness of the fourth test cavity is 0.5 mm.
In this embodiment, a spacer (not shown) for forming the shrinkage cavity 35 on the core 30 is disposed between the second test cavity 122 and the third test cavity 123.
In this embodiment, in order to simplify the measurement manner and improve the measurement accuracy, the first test cavity 121, the second test cavity 122, the third test cavity 123 and the fourth test cavity 124 are square structures, so that the core 30 formed in this way has a regular structural shape, which is convenient for measurement and ensures the measurement accuracy.
Example two
Based on the embodiment, the invention also provides a method for testing the shrinkage rate of the ceramic core, which comprises the following steps:
s1, manufacturing a plurality of core blanks as core shrinkage rate test samples through the core forming die, wherein the core blanks are provided with a plurality of measuring parts corresponding to the ceramic cores for the turbine blades;
s2, respectively measuring the thickness and the length of the plurality of measuring parts of each core biscuit to obtain biscuit measuring values, and calculating the molding shrinkage rate of the core biscuit according to the ratio of the biscuit measuring values to the mold measuring values;
s3, sintering the multiple core biscuit blanks to obtain a corresponding number of sintered cores, and cooling and shaping;
s4, respectively measuring the thickness and the length of the plurality of measuring parts of each sintering core to obtain sintering measured values, and calculating the sintering shrinkage rate of the sintering core according to the ratio of the sintering measured values to the biscuit measured values;
s5, placing the plurality of sintered cores into the wax mold to manufacture a wax mold, and manufacturing a plurality of metal castings based on the wax mold;
and S6, respectively measuring the thickness and the length of the plurality of measuring parts of the casting core on each metal casting to obtain casting measured values, and calculating the ratio of the casting measured values to the sintering measured values to obtain the casting shrinkage rate of the casting core.
The plurality of measurement portions include a simplified distribution in the first direction based on a thickness variation characteristic of the ceramic core structure for the turbine blade in the first direction, and include a simplified distribution in the second direction based on a length variation characteristic of the ceramic core structure for the turbine blade in the second direction.
In step S1, the process of manufacturing a plurality of core biscuits includes:
s11, injecting the ceramic slurry into a core forming mold according to the parameters of 40bar of mold filling pressure, 110 ℃ of material temperature, 45 ℃ of mold temperature, 80cc/S of flow rate, 10S of mold filling time and 15S of pressure maintaining time;
s12, opening the mold to take out the core, standing for at least 3h for shaping and cooling to obtain a core biscuit, wherein the core structure of the first embodiment is taken as an example, the core biscuit comprises a first measuring part 321, a second measuring part 322, a third measuring part 323 and a fourth measuring part 324, and the first measuring part 321, the second measuring part 322, the third measuring part 323 and the fourth measuring part 324 have the dimensions L1-L9 shown in fig. 3 and 4.
The step S2 specifically includes
S21, measuring the sizes of the core biscuit from L1 to L9 by using a vernier caliper to obtain a measured value of the core biscuit; considering manufacturing errors, repeating the steps S11 and S12, obtaining at least 5 core biscuits, and measuring the dimensions of the 5 core biscuits L1 to L9, respectively, and taking an arithmetic average;
s22, dividing the arithmetic mean of the dimension measurements of the core blanks L1, L2 and L3 by the design value (or the measured value of the mold) of the dimension to obtain the molding shrinkage rate of the core in the length direction in different thickness areas;
s23, dividing the arithmetic mean of the dimension measurement of the core biscuit L4, L5, L6 and L7 by the design value of the dimension to obtain the molding shrinkage of the core with different thicknesses;
s23, the molding shrinkage in the core width direction is obtained by dividing the arithmetic mean of the measurements of the dimensions of the core biscuit L9 by the design value of the dimensions.
The step S3 specifically includes:
and S31, sintering the core biscuit according to a preset process, and cooling and shaping to obtain the sintered core.
And S32, removing surface burrs and residual filling powder.
The step S4 specifically includes:
s41, respectively measuring the sizes of L1 to L9 of the 5 sintering cores by using a vernier caliper, and taking the arithmetic mean value of the 5 cores;
s42, dividing the arithmetic mean of the size measurements of the sintering cores L1, L2 and L3 by the arithmetic mean of the measurement of the biscuit of the size to obtain the sintering shrinkage of the core in the length direction of different thickness areas;
s43, dividing the arithmetic mean of the size measurement of the sintering cores L4, L5, L6 and L7 by the arithmetic mean of the biscuit measurement of the size to obtain the sintering shrinkage of the cores with different thicknesses;
s44, the arithmetic mean of the measurements of the size of the sintered core L9 is divided by the arithmetic mean of the measurements of the green compact of that size, and the sintering shrinkage in the direction of the core string width is obtained.
The step S5 specifically includes:
s51, placing the sintered core obtained in the step S4 into a wax mold 20 shown in figure 3, and preparing 5 wax molds by using model wax according to parameters of 'mold filling pressure 10bar, mold filling temperature 70 ℃, flow rate 50cc/S, mold temperature 27 ℃, mold filling time 15S and pressure maintaining time 30S';
s52, combining 5 wax molds into a wax tree, and then performing shell making, roasting, pouring, depoling and cutting to obtain a hollow metal casting (casting shrinkage test sample) with the inner cavity shape as shown in figure 6.
The step S6 specifically includes:
s61, dissecting the casting, measuring the sizes of positions corresponding to the sizes of the cores L1-L9 on the casting by using a three-coordinate or blue light scanning method and the like, and taking the arithmetic mean value of 5 castings;
s62, dividing the arithmetic mean of the size measurements of the castings L1, L2 and L3 by the corresponding arithmetic mean of the measurement of the sintering core to obtain the casting shrinkage rate of the core in the length direction of different thickness areas;
s63, dividing the measured arithmetic mean of the L4, L5, L6 and L7 of the casting by the corresponding measured arithmetic mean of the sintering core to obtain the casting shrinkage of the core with different thicknesses;
s64, dividing the arithmetic mean of the size measurement of the L8 of the casting by the arithmetic mean of the size measurement of the sintering core to obtain the casting shrinkage rate of the core in the length direction based on the plane B;
s65, dividing the arithmetic mean of the L9 size measurement of the casting by the arithmetic mean of the size measurement of the sintered core to obtain the casting shrinkage in the direction of the core chord width.
The invention can effectively measure the shrinkage rate of the core in the chord width direction, the shrinkage rates of different thicknesses, the shrinkage rates of areas with different thicknesses in the length direction and the casting shrinkage rate of the area with different thicknesses in the length direction based on a certain characteristic, and the shrinkage rate results have very important reference values for the process development of the turbine blade core.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.
Claims (5)
1. A ceramic core shrinkage test mold for turbine blades, comprising: the device comprises a core forming die and a wax die matched with the core forming die, wherein the core forming die is used for manufacturing a core shrinkage rate test sample, and the wax die is used for manufacturing a casting shrinkage rate test sample piece based on the core;
the core forming die comprises a base cavity and a main body cavity communicated with the base cavity, wherein the main body cavity is provided with a plurality of test cavities, the thicknesses of the test cavities are different in a first direction, the lengths of the test cavities are different in a second direction, the base is provided with a plane for forming a reference surface on the core, the first direction is parallel to the plane, and the second direction is perpendicular to the plane;
the different thicknesses of the plurality of test cavities in the first direction are a simplified distribution based on a thickness variation characteristic of the ceramic core structure for the turbine blade in the first direction, and the different length variations of the plurality of test cavities in the second direction are a simplified distribution based on a length variation characteristic of the ceramic core structure for the turbine blade in the second direction;
the shape of the wax pattern mold corresponds to the shape of the core forming mold to test the core casting shrinkage based on the core shrinkage test standard casting shrinkage test sample.
2. The ceramic core shrinkage test mold for turbine blades according to claim 1, wherein the plurality of test cavities are arranged in a stepped structure having a thickness gradually decreasing in a first direction.
3. The ceramic core shrinkage test mold for turbine blades according to claim 1 or 2, wherein the plurality of test cavities includes: the test device comprises a first test cavity, a second test cavity, a third test cavity and a fourth test cavity.
4. The ceramic core shrinkage test mold for turbine blades according to claim 3, wherein the first test cavity has a thickness of 8mm, the second test cavity has a thickness of 5mm, the third test cavity has a thickness of 3mm, and the fourth test cavity has a thickness of 0.5 mm.
5. The ceramic core shrinkage test mold for turbine blades according to claim 3, wherein a spacer for forming a shrinkage groove on the core is provided between the second test cavity and the third test cavity.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115356372A (en) * | 2022-10-24 | 2022-11-18 | 中国空气动力研究与发展中心计算空气动力研究所 | Time-varying thermal response test method and system for novel material in flight test |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115356372A (en) * | 2022-10-24 | 2022-11-18 | 中国空气动力研究与发展中心计算空气动力研究所 | Time-varying thermal response test method and system for novel material in flight test |
| CN115356372B (en) * | 2022-10-24 | 2023-03-10 | 中国空气动力研究与发展中心计算空气动力研究所 | Time-varying thermal response testing method and system for novel material in flight test |
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