CN112983557A - High-temperature test piece for gas turbine blade and manufacturing method thereof - Google Patents
High-temperature test piece for gas turbine blade and manufacturing method thereof Download PDFInfo
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- CN112983557A CN112983557A CN202110226366.0A CN202110226366A CN112983557A CN 112983557 A CN112983557 A CN 112983557A CN 202110226366 A CN202110226366 A CN 202110226366A CN 112983557 A CN112983557 A CN 112983557A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/003—Arrangements for testing or measuring
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P10/00—Technologies related to metal processing
- Y02P10/25—Process efficiency
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- Engineering & Computer Science (AREA)
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- General Engineering & Computer Science (AREA)
- Architecture (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to the technical field of turbine blades, in particular to a high-temperature test piece of a gas turbine blade and a manufacturing method thereof, wherein the high-temperature test piece comprises a thermocouple groove, a gas film hole and a test blade; the test blade comprises an upper end part, a middle end part and a lower end part; s1: arranging thermocouple grooves on a test blade model without a gas film hole structure to obtain a test blade with a thermocouple groove; s2: designing a three-dimensional model and obtaining a test blade metal entity test piece with a thermocouple groove in S1 by using a 3D printing and forming technology; s3: processing a test piece of a metal entity of a test blade by an electric spark or laser drilling technology to obtain a gas film hole structure; s4: and burying the thermocouple and carrying out landfill repair on the thermocouple groove to obtain a test piece finished product. The air film hole in the invention adopts 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.
Description
Technical Field
The invention relates to the technical field of turbine blades, in particular to a high-temperature test piece of a gas turbine blade and a manufacturing method thereof.
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 cooling test model of the gas turbine blade is mainly manufactured by adopting a 3D printing technology. In the process of forming the blade cooling hole structure by using a 3D printing technology, the consistency of the final forming size of the air film hole and a design model is greatly influenced by a size error caused by the expansion with heat and contraction with cold in the material solidification process, and the surface roughness of the inner wall surface of the 3D formed air film hole structure is difficult to ensure; 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.
Disclosure of Invention
In order to solve the technical problems, the invention provides a high-temperature test piece of a gas turbine blade and a manufacturing method thereof.
In order to realize the purpose of the invention, the invention adopts the 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 air film holes penetrate through the outer surface of the blade and the surface of the inner cavity; 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, and the blade test piece with the thermocouple grooves is printed in a 3D mode.
Furthermore, a raised vertical flat plate is arranged on the left side of the upper end part of the blade, two holes are formed in the vertical flat plate, a horizontal flat plate is fixedly connected with the vertical flat plate, and at least one groove is formed in the upper end face of the horizontal flat plate.
Furthermore, a raised vertical flat plate is arranged on the left side of the lower end part of each blade, two holes are formed in the vertical flat plate, a horizontal flat plate is fixedly connected with the vertical flat plate, and at least one groove is formed in the upper end face of the horizontal flat plate.
Furthermore, 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, the middle end part of the blade is a cylinder and is positioned between the upper end part and the lower 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.
Furthermore, the section 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 section of the thermocouple groove is in the shape of a round tube, wherein the size range of the diameter is 0.4 mm-1.0 mm, so that the forming quality of the thermocouple groove is effectively ensured, and the processing time is shortened.
Furthermore, the thermocouple grooves are spaced in pairs.
Further, the thermocouple well is located between different gas film hole columns.
A manufacturing method of a high-temperature test piece of a gas turbine blade comprises the following steps:
s1: arranging thermocouple grooves at measuring positions of the test blade model without the air film hole structure, and further obtaining the test blade model with the thermocouple grooves;
s2: designing on a digital three-dimensional model and directly obtaining a test blade metal solid test piece with a thermocouple groove in S1 by using a 3D printing and forming technology;
s3, processing the test blade metal entity test piece by an electric spark or laser drilling technology to obtain a gas film hole structure, and ensuring that the inner wall surface roughness and the key dimension parameters of the gas film hole structure of the test blade are consistent with the precision parameters of the mass precision casting blade entity;
s4: and burying the thermocouple and carrying out landfill repair on the thermocouple groove to finally obtain a test piece finished product.
Further, in S1, the test blade model is divided into two halves and 3D printed, the inner surface roughness is secondarily processed, and the two half test blade models are combined into a complete test piece by welding.
Furthermore, the thermocouple groove is completely arranged below the wall surface of the blade or a section of the thermocouple groove is arranged below the surface of the blade to form a hidden through channel, and the 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, a mode that a thermocouple channel is designed on a blade model and 3D printing manufacturing is carried out is adopted, firstly, the positions of thermocouple measuring points are completely and accurately ensured, numerical analysis can be carried out on a three-dimensional digital model, the temperature of the measuring points calculated by 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 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;
(3) when the influence of the surface roughness of the inner cavity of the blade on the flow resistance and heat exchange of cooling air needs to be fully considered, the blade can be divided into two parts for printing, and the surface of the inner cavity is subjected to sand blasting and polishing, namely the quality of the surface of the inner cavity is modified and used for adjusting the roughness of the inner wall to be consistent with the roughness of the inner wall of the finally cast blade, so that the defects of a 3D printing technology are further overcome, and the test precision is improved;
(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 purpose and technical solution of the present invention clearer, the following will clearly and completely describe the technical solution of the present invention with reference to the embodiments.
Example 1
According to the high-temperature test piece for the gas turbine blade shown in the figures 1 and 2, the high-temperature test piece comprises a thermocouple groove 1, a gas film hole 2, an upper end part 3 of the blade, a middle end part 4 of the blade and a lower end part 5 of the blade, wherein a vertical flat plate 7 is arranged on the left side of the upper end part 3 of the blade, two holes are formed in the vertical flat plate 7, a horizontal flat plate 7 is fixedly connected with the vertical flat plate, and at least one groove is formed in the upper end face of the horizontal flat plate 7; the blade lower end part 5 and the blade upper end part 3 have the same structure; 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 penetrates through the outer surface of the blade and the surface of the inner cavity; the thermocouple groove 1 is arranged on 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, and the blade test piece with the thermocouple groove 1 is printed in a 3D mode.
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 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 thermocouple grooves 1 are spaced from each other. The film holes 2 are located between the thermocouple wells 1.
The manufacturing method of the high-temperature test piece of the gas turbine blade shown in FIG. 3 comprises the following steps: s1: 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; s2: designing on a digital three-dimensional model and directly obtaining a test blade metal entity test piece with the thermocouple groove 1 in S1 by using a 3D printing and forming technology; s3, processing the test piece of the test blade metal entity through an electric spark or laser drilling technology to obtain a gas film hole 2 structure; s4: and burying the thermocouple and carrying out burying repair on the thermocouple groove 1 to finally obtain a test piece finished product. When a high-precision simulation test is needed, the test blade model is firstly divided into two halves and 3D printing is carried out in S1, and then the two halves of the test blade model are combined into a complete test piece in a welding mode, or the two halves of the test blade model are not required to be divided for 3D printing when the high-precision simulation test is not needed. 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. At the moment, the thermocouple groove 1 is completely designed under the wall surface of the blade, the scheme can better ensure the surface integrity and the smoothness of the blade of the testing machine, and the surface quality is reduced due to the fixing of the thermocouple on the wall surface and the secondary joint filling.
Example 2
According to the high-temperature test piece for the gas turbine blade and the manufacturing method thereof shown in fig. 1, fig. 2 and fig. 4, the difference of the present embodiment from embodiment 1 is that in the manufacturing method of the test piece, a section of the thermocouple groove 1 is designed under the wall surface of the test blade, and a section is in a semi-open manner, which is mainly used for facilitating adjustment during thermocouple threading.
The above are merely embodiments of the present invention, which are described in detail and with particularity, and therefore should not be construed as limiting the scope of the invention. It should be noted that, for those skilled in the art, various changes and modifications can be made without departing from the spirit of the present invention, and these changes and modifications are within the scope of the present invention.
Claims (10)
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 air film holes penetrate through the outer surface of the blade and the surface of the inner cavity; 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, and the blade test piece with the thermocouple grooves is printed in a 3D mode.
2. The gas turbine blade high-temperature test piece as claimed in claim 1, wherein a raised vertical flat plate is arranged on the left side of the upper end of the blade, two holes are formed in the vertical flat plate, a horizontal flat plate is fixedly connected with the vertical flat plate, and at least one groove is formed in the upper end face of the horizontal flat plate.
3. The gas turbine blade high-temperature test piece as claimed in claim 1, wherein a raised vertical flat plate is arranged on the left side of the lower end part of the blade, two holes are formed in the vertical flat plate, a horizontal flat plate is fixedly connected with the vertical flat plate, and at least one groove is formed in the upper end face of the horizontal flat plate.
4. The gas turbine blade high temperature test piece as set forth 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 middle end portion is a cylinder located between the blade upper end portion and the blade lower end portion, and the blade upper end portion and the blade lower end portion are arranged in a mirror image with the blade middle end portion as a reference.
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 thermocouple grooves are spaced apart from each other.
7. The gas turbine blade high temperature test piece of claim 1, wherein the thermocouple well is located between different film holes.
8. A method for manufacturing a high-temperature test piece for a gas turbine blade according to any one of claims 1 to 5, comprising the steps of:
s1: arranging thermocouple grooves at measuring positions of the test blade model without the air film hole structure, and further obtaining the test blade model with the thermocouple grooves;
s2: designing on a digital three-dimensional model and directly obtaining a test blade metal solid test piece with a thermocouple groove in S1 by using a 3D printing and forming technology;
s3, processing the test piece of the test blade metal entity by adopting an electric spark or laser drilling technology to obtain an air film hole structure;
s4: and burying the thermocouple and carrying out landfill repair on the thermocouple groove to finally obtain a test piece finished product.
9. The method for manufacturing a high-temperature test piece of a gas turbine blade as claimed in claim 6, wherein when performing the high-precision simulation test, the test blade model is divided into two halves and 3D printed in S1, the inner surface roughness is secondarily processed, and then the two halves of the test blade model are combined into a complete test piece by welding.
10. The method for manufacturing a high-temperature test piece for a gas turbine blade as claimed in claim 6, wherein the thermocouple groove is entirely provided on the outer surface of the blade or the thermocouple groove is provided with a section below the outer surface of the blade to form a hidden through channel, and the section is provided in a semi-open manner.
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| CN202110226366.0A CN112983557B (en) | 2021-03-01 | 2021-03-01 | High-temperature test piece for gas turbine blade and manufacturing method thereof |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113588234A (en) * | 2021-07-14 | 2021-11-02 | 北京航空航天大学 | Comprehensive cold effect testing method and system for rotation of turbine movable blades |
| CN113770643A (en) * | 2021-10-21 | 2021-12-10 | 华瑞（江苏）燃机服务有限公司 | Large-area repairing method for blade with cooling hole |
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| CN113770643A (en) * | 2021-10-21 | 2021-12-10 | 华瑞（江苏）燃机服务有限公司 | Large-area repairing method for blade with cooling hole |
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| CN112983557B (en) | 2022-12-02 |
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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. |