CN214703405U - High-temperature test piece for gas turbine blade - Google Patents
High-temperature test piece for gas turbine blade Download PDFInfo
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- CN214703405U CN214703405U CN202120444087.7U CN202120444087U CN214703405U CN 214703405 U CN214703405 U CN 214703405U CN 202120444087 U CN202120444087 U CN 202120444087U CN 214703405 U CN214703405 U CN 214703405U
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Abstract
The utility model relates to the technical field of turbine blades, in particular to a high-temperature test piece for a gas turbine blade, which comprises a thermocouple groove, a gas film hole, a test blade, a blade upper end part, a blade middle end part and a blade lower end part; the left side of the upper end part of each blade is provided with a raised vertical flat plate, two holes are formed in the vertical flat plate, a horizontal flat plate is fixedly connected with the vertical flat plate, and the upper end surface of the horizontal flat plate is provided with at least one groove; the left side of the lower end part of each blade is provided with a raised vertical flat plate, the left side of the lower end part of each blade is fixedly connected with a horizontal flat plate, and the upper end surface of each horizontal flat plate is provided with at least one groove; the middle end part of the blade is a cylinder and is positioned between the upper end part of the blade and the lower end part of the blade; the air film hole is arranged on the outer surface of the middle end part of the blade; thermocouple grooves are formed in the upper end portion of the blade, the lower end portion of the blade and the middle end portion of the blade. The utility model provides a thermocouple measurement station position is accurate, has shortened the testpieces manufacturing cycle.
Description
Technical Field
The utility model relates to a turbine blade's technical field especially relates to a gas turbine blade high temperature test spare.
Background
The turbine stator blade of the gas turbine works in high-temperature gas, the gas temperature (above 1300 ℃) of the F-grade gas turbine exceeds the melting point temperature of the metal material of the blade body, and the cooling technology of the gas turbine blade can effectively reduce the metal temperature and prolong the service life of the blade under the same condition. The cooling effect test of the gas turbine blade is an evaluation test aiming at the surface temperature distribution condition of the blade with a special cooling structure under the condition of simulating the actual working condition of the gas turbine before the blade is put into use. In the test, a test blade model carrying a specific cooling structure is placed in a high-temperature gas environment simulating an actual working environment, the temperature of the blade measuring position is collected through temperature measuring points which are arranged on the surface of the blade model in advance, the temperature is collected and processed, and finally the cooling effect of the blade cooling structure is obtained through evaluation.
The blade cooling effect test result is an important means for evaluating the cooling performance of the blade under the real operating condition. The working life of the blade under the actual working condition is determined by the cooling effect of the test blade model. Therefore, in the test, the factors such as the dimensional accuracy of the cooling structure of the blade model, the surface quality of the blade after the measuring points are arranged, the channel layout of the measuring points in the test and the like need to be strictly ensured so as to ensure that the test model is close to the blade under the actual working condition as much as possible. Otherwise, errors of cooling gas flow distribution, heat exchange effect between the blades and high-temperature gas and working state under the test state can be caused, and then reliability of the test result is reduced. Based on the nature of the blade cooling test, additional thermocouple temperature measurement points are required to test the blade model. The main way today is to form several channels at the measurement site of the blade model by machining, and to embed the thermocouple temperature sensors into the channels and perform fixing and surface repair before testing. The existing gas turbine blade cooling test model is mainly manufactured by a 3D printing technology, in the forming process, the size error caused by the expansion and contraction effect in the material solidification process greatly influences the consistency of the final forming size of the gas turbine blade and a design model, the surface roughness of the inner wall surface of the 3D formed gas turbine blade cooling test model is difficult to guarantee, and the reliability of the test result is seriously influenced; meanwhile, when the thermocouple channel is machined by a later-stage machining means, the machining difficulty is obviously increased due to the characteristics of small channel size, dense layout and complex trend, and the product is reworked or even scrapped.
Chinese patent CN102565119A discloses a method for measuring the cooling effect and the heat insulation effect of a turbine blade with a thermal barrier coating, which comprises the following steps: a thermocouple is buried in a groove formed in the surface of a real turbine blade which is not sprayed with a thermal barrier coating, a first round of cooling effect test is carried out in a selected test state, then the thermal barrier coating is sprayed on the blade, and a second round of test is carried out under the condition that the test state of the blade is consistent with that of the first round of blade; therefore, the comparative test can obtain the cooling effect of the blade with the thermal barrier coating and the heat insulation effect of the thermal barrier coating on the real blade, and provides a basis for verifying or perfecting the design of the thermal barrier coating of the blade. The invention has the advantages that: the method can conveniently measure the cooling effect of the blade with the thermal barrier coating, can visually compare the cooling effect of the blade without the thermal barrier coating and obtain the heat insulation effect of the thermal barrier coating on the real blade, thereby conveniently verifying and evaluating the design conditions of the blade and the thermal barrier coating.
Chinese patent CN202928778U discloses an orifice plate structure for studying gas turbine blade air film cooling flow field and temperature field, including experiment spare and test piece, set up the protruding piece of draw-in groove on the experiment spare, set up the concave piece of draw-in groove on the test piece, experiment spare and test piece pass through the protruding piece of draw-in groove and the concave piece of draw-in groove (13) joint are in the same place, be provided with air film cooling hole and organic glass pipe on the experiment spare, air film cooling hole below is connected the same rather than the pipe diameter organic glass pipe, the test piece includes black paint, stainless steel thin slice, electric heating piece and organic glass piece, black paint is scribbled on the stainless steel thin slice.
Although the above-mentioned patent that has disclosed all relate to the technical field of turbine blade, the technical scheme is different from this invention, based on the technical problem appearing above, this invention has provided a gas turbine blade high-temperature test piece and manufacturing approach, this invention adopts thermocouple channel to design and carry on the way that 3D prints and makes on the blade model, thermocouple measuring point position is totally accurate to guarantee at first, can carry on numerical analysis to the three-dimensional digital model, the measuring point temperature that the numerical calculation can carry on the complete comparison analysis with test value, second 3D profiled test piece blade precision is high, the test piece manufacturing cycle is shortened greatly; the air film hole is processed in a post-processing mode, so that the technological process and precision parameters of the air film hole are kept consistent with those of batch products, meanwhile, the quality consistency of the punched hole is very good, and the reliability of test data is ensured; the surface quality of the inner cavity can be modified, the defects of the 3D printing technology are further overcome, and the test precision is further improved; the invention can better ensure the surface integrity of the test piece and the pneumatic characteristic of the test piece, and simultaneously, the smooth and complete outer surface can also be used for special tests such as temperature indicating paint spraying and the like, thereby greatly enriching the application of test measurement and the acquisition of test data, avoiding the reduction of the surface quality of the test piece caused by the process of fixing the thermocouple after the thermocouple is installed in the channel and filling the channel, and only being capable of carrying out the single test.
SUMMERY OF THE UTILITY MODEL
In order to solve the technical problem, the utility model provides a gas turbine blade high temperature test spare's structure.
In order to realize the utility model discloses a purpose, the utility model discloses a following technical scheme:
a high-temperature test piece for a gas turbine blade comprises a thermocouple groove, a gas film hole, an upper end part of the blade, a lower end part of the blade and a middle end part of the blade; the left side of the upper end part of the blade is provided with a raised vertical flat plate, the left side of the upper end part of the blade is fixedly connected with a horizontal flat plate, and the upper end surface of the horizontal flat plate is provided with at least one groove; the left side of the lower end part of each blade is provided with a raised vertical flat plate, two holes are formed in the vertical flat plate, a horizontal flat plate is fixedly connected with the vertical flat plate, and the upper end face of the horizontal flat plate is provided with at least one groove; the middle end part of the blade is a cylinder and is positioned between the upper end part of the blade and the lower end part of the blade; the surfaces of the upper end part of the blade, the middle end part of the blade and the lower end part of the blade are distributed with air film holes; and thermocouple grooves are formed in the upper end part of the blade, the lower end part of the blade and the middle end part of the blade.
Further, the upper end part and the lower end part of the blade are fixed on two sides of the middle end part of the blade, and the upper end part and the lower end part of the blade are arranged in a mirror image mode by taking the middle end part of the blade as a reference.
Further, the vertical flat plate and the horizontal flat plate at the upper end part of the blade are fixedly connected in an L shape.
Furthermore, the lower end plane of the upper end part of the blade is fixedly connected with the upper end surface of the middle end part of the blade, and the lower end surface of the middle end part of the blade is fixedly connected with the lower end plane of the lower end part of the blade.
Further, the sectional shape of the thermocouple groove is rectangular, wherein the size ranges of the width and the height are both 0.4 mm-1.0 mm, or the sectional shape of the thermocouple groove is a round tube shape, wherein the size range of the diameter is 0.4 mm-1.0 mm.
Furthermore, the number of the thermocouple grooves is at least one, and a gap is arranged between every two thermocouple grooves.
Further, the gas film holes are arranged between the thermocouple grooves and are at least one.
Further, the thermocouple grooves are all arranged on the outer surface of the blade or one section of the thermocouple groove is arranged on the outer surface of the blade, and the other section is arranged in a semi-open mode.
Compared with the prior art, the invention has the beneficial effects that:
(1) according to the invention, the thermocouple channel is designed on the blade model and is manufactured by 3D printing, firstly, the thermocouple measuring point position is completely and accurately ensured, numerical analysis can be carried out on the three-dimensional digital model, the measuring point temperature of numerical calculation can be completely compared and analyzed with a test value, secondly, the blade precision of a 3D molded test piece is high, and the manufacturing period of the test piece is greatly shortened;
(2) the quality consistency of the punched holes of the air film holes is very good, and the reliability of test data is ensured;
(3) the invention can modify the surface quality of the inner cavity, further overcomes the defects of the 3D printing technology and further improves the test precision;
(4) the invention can better ensure the surface integrity of the test piece and the pneumatic characteristic of the test piece, and simultaneously, the smooth and complete outer surface can also be used for special tests such as temperature indicating paint spraying and the like, thereby enriching the application of test measurement and the acquisition of test data, and avoiding the situation that the surface quality of the test piece is reduced and only a single test can be carried out due to the process of fixing the thermocouple after the thermocouple is installed in the thermocouple channel and burying the channel.
Drawings
Fig. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic structural view in the first embodiment;
FIG. 3 is a partially enlarged view illustrating the first embodiment;
FIG. 4 is a partially enlarged view illustrating a second embodiment;
the reference numbers are as follows: 1. a thermocouple well; 2. a gas film hole; 3. an upper end portion of the blade; 4. a blade middle end; 5. a lower end portion of the blade; 6. a horizontal plate; 7. a vertical plate.
Detailed Description
In order to make the objects and technical solutions of the present invention clearer, the technical solutions of the present invention will be clearly and completely described below with reference to the following embodiments.
Example 1
According to the high-temperature test piece of the gas turbine blade shown in the figures 1-3, the high-temperature test piece of the gas turbine blade comprises a thermocouple groove 1, a gas film hole 2, a blade upper end part 3, a blade middle end part 4 and a blade lower end part 5, wherein a raised vertical flat plate 7 is arranged on the left side of the blade upper end part 3, two holes are formed in the vertical flat plate 7, a horizontal flat plate 6 is fixedly connected with the vertical flat plate 7, and at least one groove is formed in the upper end face of the horizontal flat plate 6; a raised vertical flat plate 7 is arranged on the left side of the lower end part 5 of the blade, two holes are formed in the vertical flat plate 7, a horizontal flat plate 6 is fixedly connected with the vertical flat plate 7, and at least one groove is formed in the upper end face of the horizontal flat plate 6; the middle end part 4 of the blade is a cylinder and is positioned between the upper end part 3 of the blade and the lower end part 5 of the blade; the air film hole 2 is arranged on the outer surface of the middle end part 4 of the blade; and thermocouple grooves 1 are formed in the upper end part 3 of the blade, the lower end part 5 of the blade and the middle end part 4 of the blade.
The blade upper end part 3 and the blade lower end part 5 are fixed on two sides of the blade middle end part 4, and the blade upper end part 3 and the blade lower end part 5 are arranged in a mirror image mode by taking the blade middle end part 4 as a reference. The vertical flat plate 7 and the horizontal flat plate 6 of the upper end part 3 of the blade are fixedly connected in an L shape. The lower end plane of the blade upper end part 3 is fixedly connected with the upper end surface of the blade middle end part 4, and the lower end surface of the blade middle end part 4 is fixedly connected with the lower end plane of the blade lower end part 5. The section of the thermocouple groove 1 is rectangular, wherein the size ranges of the width and the height are both 0.4 mm-1.0 mm, or the section of the thermocouple groove 1 is in the shape of a round tube, wherein the size range of the diameter is 0.4 mm-1.0 mm. The number of the thermocouple grooves 1 is at least one, and a space is reserved between every two thermocouple grooves. The gas film holes 2 are positioned between the thermocouple grooves 1 and are arranged into at least one. The thermocouple well 1 is entirely disposed below the test blade wall surface.
The manufacturing method of the high-temperature test piece of the gas turbine blade in the embodiment comprises the following steps: firstly, arranging a thermocouple groove 1 at a measuring position of a test blade model without a gas film hole 2 structure, and further obtaining a test blade model with a thermocouple groove 1; then designing on a digital three-dimensional model and directly utilizing a high-temperature alloy powder 3D printing and forming technology to obtain the test blade metal entity test piece with the thermocouple groove 1; then, processing the test piece of the metal entity of the test blade by an electric spark or laser drilling technology to obtain a gas film hole 2 structure; and burying the thermocouple and carrying out burying repair on the thermocouple groove 1 to finally obtain a test piece finished product. At the beginning, the test blade model is firstly divided into two parts and 3D printing is carried out, and then the two test blade models are combined into a complete test piece in a welding mode. The advantage of printing test piece segmentation two halves lies in can further polishing and control 3D printing test piece inner wall roughness, and the parameter that strictly guarantees test piece and cooling test result relevant keeps unanimous with final casting blade, promotes the accuracy of cooling test result. 3D printing can be performed without dividing the two halves when high-precision simulation testing is not required. The thermocouple groove 1 is completely arranged below the wall surface of the blade, the integrity and the smoothness of the surface of the blade of the testing machine can be better guaranteed by the scheme, the surface quality is reduced due to the fixing of the thermocouple on the wall surface and the secondary joint filling, the surface quality of the inner cavity can be modified, the defects of the 3D printing technology are further overcome, and the testing precision is further improved.
Example 2
According to the high-temperature test piece for the gas turbine blade shown in fig. 1, 2 and 4, the difference between the embodiment and the embodiment 1 is that a section of the thermocouple groove 1 is arranged below the wall surface of the test blade, and a section of the thermocouple groove 1 is arranged in a semi-open mode, which is mainly used for facilitating adjustment in the process of thermocouple threading. Meanwhile, the surface integrity of the test piece can be better ensured, the pneumatic characteristic of the test piece is ensured, and the smooth and complete outer surface can also be used for special tests such as temperature indicating paint spraying and the like, so that the application of test measurement and the acquisition of test data are greatly enriched, the situation that the surface quality of the test piece is greatly reduced due to the fact that a fixed thermocouple and a buried channel process are arranged behind a channel mounted thermocouple, and only a single test can be carried out is avoided.
The above description is only for the embodiments of the present invention, and the description is specific and detailed, but not construed as limiting the scope of the present invention. It should be noted that, for those skilled in the art, without departing from the spirit of the present invention, several changes and modifications can be made, which all fall within the scope of the present invention.
Claims (8)
1. A high-temperature test piece for a gas turbine blade is characterized by comprising a thermocouple groove, a gas film hole, an upper end part of the blade, a lower end part of the blade and a middle end part of the blade; the left side of the upper end part of the blade is provided with a raised vertical flat plate, the left side of the upper end part of the blade is fixedly connected with a horizontal flat plate, and the upper end surface of the horizontal flat plate is provided with at least one groove; the left side of the lower end part of each blade is provided with a raised vertical flat plate, two holes are formed in the vertical flat plate, a horizontal flat plate is fixedly connected with the vertical flat plate, and the upper end face of the horizontal flat plate is provided with at least one groove; the middle end part of the blade is a cylinder and is positioned between the upper end part of the blade and the lower end part of the blade; the surfaces of the upper end part of the blade, the middle end part of the blade and the lower end part of the blade are distributed with air film holes; and thermocouple grooves are formed in the upper end part of the blade, the lower end part of the blade and the middle end part of the blade.
2. The gas turbine blade high-temperature test piece as claimed in claim 1, wherein the blade upper end portion and the blade lower end portion are fixed to both sides of the blade middle end portion, and the blade upper end portion and the blade lower end portion are arranged in a mirror image with reference to the blade middle end portion.
3. The gas turbine blade high-temperature test piece as claimed in claim 1, wherein the vertical flat plate and the horizontal flat plate at the upper end of the blade are fixedly connected in an L shape.
4. The gas turbine blade high-temperature test piece as claimed in claim 1, wherein the lower end plane of the upper end part of the blade is fixedly connected with the upper end plane of the middle end part of the blade, and the lower end plane of the middle end part of the blade is fixedly connected with the lower end plane of the lower end part of the blade.
5. The gas turbine blade high temperature test piece as set forth in claim 1, wherein the thermocouple well has a rectangular cross-sectional shape in which a width and a height are both in a size range of 0.4mm to 1.0mm, or a circular cross-sectional shape in which a diameter is in a size range of 0.4mm to 1.0 mm.
6. The gas turbine blade high-temperature test piece as claimed in claim 1, wherein the number of the thermocouple grooves is at least one, and a space is provided between every two thermocouple grooves.
7. The gas turbine blade high temperature test piece according to claim 1, wherein the film holes are located between the thermocouple grooves and are provided as at least one.
8. The gas turbine blade high temperature test piece as set forth in claim 1, wherein the thermocouple groove is provided entirely on the blade outer surface or a segment of the thermocouple groove is provided on the blade outer surface, the segment being provided in a semi-open manner.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120444087.7U CN214703405U (en) | 2021-03-01 | 2021-03-01 | High-temperature test piece for gas turbine blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120444087.7U CN214703405U (en) | 2021-03-01 | 2021-03-01 | High-temperature test piece for gas turbine blade |
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| Publication Number | Publication Date |
|---|---|
| CN214703405U true CN214703405U (en) | 2021-11-12 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120444087.7U Active CN214703405U (en) | 2021-03-01 | 2021-03-01 | High-temperature test piece for gas turbine blade |
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| CN (1) | CN214703405U (en) |
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2021
- 2021-03-01 CN CN202120444087.7U patent/CN214703405U/en active Active
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| GR01 | Patent grant | ||
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| CP01 | Change in the name or title of a patent holder |
Address after: No. 1188, Dongxin Road, Hangzhou, Zhejiang, 310022 Patentee after: Hangzhou Steam Turbine Holding Co.,Ltd. Patentee after: Zhejiang Gas Turbine Machinery Co.,Ltd. Address before: No. 1188, Dongxin Road, Hangzhou, Zhejiang, 310022 Patentee before: HANGZHOU TURBINE POWER GROUP CO.,LTD. Patentee before: Zhejiang Chuang Turbine Machinery Co.,Ltd. |
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| CP01 | Change in the name or title of a patent holder |