CN115570105A - Method for manufacturing double-wall turbine blade - Google Patents
Method for manufacturing double-wall turbine blade Download PDFInfo
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- CN115570105A CN115570105A CN202211451891.3A CN202211451891A CN115570105A CN 115570105 A CN115570105 A CN 115570105A CN 202211451891 A CN202211451891 A CN 202211451891A CN 115570105 A CN115570105 A CN 115570105A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/02—Sand moulds or like moulds for shaped castings
- B22C9/04—Use of lost patterns
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/22—Moulds for peculiarly-shaped castings
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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
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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Abstract
The invention relates to the field of aviation design and manufacture, and discloses a method for manufacturing a double-wall turbine blade, which comprises the steps of calculating an empirical correlation according to the design size and the cooling design requirement of the double-wall turbine blade and the flow coefficient and the heat exchange coefficient of an impact turbulence structure of a double-wall belt under the given design boundary condition, and calculating to obtain the size of a cooling structure meeting the cooling design requirement of a blade; and preparing a blade core which can be cast into a structure with the turbulence columns and the inner wall cooling channel according to the sizes of the impact holes, the turbulence columns and the cooling channel which meet the correlation formula, and then performing double-wall turbine blade casting molding by adopting a dewaxing method. According to the method, the empirical correlation is calculated according to the flow coefficient and the heat exchange coefficient, the cooling structure size meeting the design requirement of blade cooling is obtained under the given design boundary condition, the micro-scale structure of the double-wall turbine blade core is obtained in an optimized mode, the double-wall turbine blade is obtained through the lost wax casting, and the double-wall turbine blade structure with a more efficient cooling effect can be obtained.
Description
Technical Field
The invention relates to the technical field of aero-engines, in particular to a method for manufacturing a double-wall turbine blade.
Background
In high performance aircraft engines, since the turbine inlet gas temperature far exceeds the tolerance limit of the turbine blade material, effective cooling measures must be taken to ensure reliable operation of the turbine blade in high temperature, high pressure, and high rotational speed environments. At present, the turbine blade of the aero-engine generally adopts the technologies of ultra-high temperature heat-resistant alloy, single crystal metallographic structure, composite air film cooling type hollow structure and the like to meet the performance requirements of the turbine blade under high temperature and high pressure. The complexity of the material and the mechanism causes the qualification rate of the precision casting blank of the prior hollow turbine blade to be lower, and is only 10 percent. The key technology for manufacturing the high-efficiency air-cooling blade lies in the manufacture of a ceramic core, and the ceramic core must have good refractoriness, room temperature strength, high temperature thermal stability, porosity and decoring performance.
The actual wall of present high performance turbine blade is thinner, adopts double-walled structure moreover, compares with traditional hollow blade, and ceramic core structure is more complicated, and the wall thickness is thinner, and the difference is bigger, need adopt more advanced more complicated microchannel cooling design, and higher casting pressure satisfies more efficient cooling demand. Meanwhile, the core of the cast blade is large in deformation and difficult to control in the manufacturing process, the deformation of the core is easily caused by positioning, and the small-sized turbulence column and other micro-channel cooling structures are easy to crack, deform and even break in the manufacturing process, so that the quality and the qualification rate of the turbine blade are seriously influenced.
Disclosure of Invention
In view of the above, the present invention provides a method for manufacturing a double-walled turbine blade, which determines the size of a core suitable for the double-walled turbine blade by introducing a flow coefficient and a heat exchange coefficient calculation empirical correlation, and has a better cooling effect while meeting the strength requirement.
A method of manufacturing a double-walled turbine blade comprising the steps of:
step 1, determining the base material and size of a double-wall turbine blade core and the cooling design parameters of a blade according to the design size and the cooling design requirement of the double-wall turbine blade, wherein the cooling design parameters comprise the temperature and pressure of cold air at the inlet of a cooling channel of the blade, the flow of the cold air and the outlet pressure of a film hole on the surface of the blade;
wherein, when the turbulence columns are arranged in order, the following calculation formula is adopted for verification:
C d =0.218582Re 0.129919 Kn 0.042870 （H/D） 0.384319
Nu=0.020332Re 0.879857 （H/D） -0.192851
the following calculation formula is adopted for verification during the cross arrangement of the turbulence columns:
C d =0.205671Re 0.134878 Kn 0.042011 （H/D） 0.398420
Nu=0.019616Re 0.879260 （H/D） -0.168356
C d nu is the Nurse number for the flow coefficient,Rereynolds number, kn Knudsen number, H/D impact distance and aperture ratio;
and 4, preparing a blade core which can be cast into a structure with the flow disturbing columns and the inner wall cooling channel according to the size of the associated core, the flow disturbing columns and the size of the cooling channel in the step 3, and then carrying out casting molding on the double-wall turbine blade by adopting a dewaxing method.
Further, simulating the double-wall turbine blade which meets the correlation requirement and corresponds to the sizes of the core, the turbulence column and the cooling channel in the step 3 to obtain a temperature field of the blade, and judging whether the temperature and the stress of the blade are in the temperature resistance and strength ranges of the material; if not, the geometric parameter value is adjusted until the double-wall combined cooling structure meets the requirement.
Further, before the lost wax casting in the step 4, the core placed in the casting mold is subjected to reinforcement pretreatment, and the method specifically comprises the following steps:
A. pre-selecting the front edge and the rear edge of the mold core and the flat part of the curved surface of the mold core, and applying a mold core positioning tool;
B. pre-waxing is carried out on the weak part of the core strength, and the weak part of the core strength is determined by ANSYS software calculation;
C. and carrying out wax mold press forming on the core subjected to the preposed wax hanging treatment, and arranging wax mold supporting parts at the upper edge plate and the lower edge plate of the wax mold.
Further, in the step B, design temperature, vibration, air flow and cold efficiency coefficient parameters are input into ANSYS software, intensity calculation is carried out by adopting a mid-zone node generalized plane strain unit 183, the weak part of the double-wall turbine blade is determined in the region with the equivalent stress of more than 420MPa or the mechanical stress of more than 160MPa, and the weak part is strengthened by adopting a method of leading wax coating at the corresponding position of the weak part.
Furthermore, the wax coating filling thickness is controlled within the range of 0.3mm-1.0mm, and the cooling time is not less than 8h.
Further, the supporting member is square, round or irregular in shape, and the cross-sectional area ranges from 2.25mm 2 -6mm 2 。
Compared with the prior art, the invention has the beneficial effects that:
1. the core size suitable for the double-wall turbine blade is determined by introducing the flow coefficient and the heat exchange coefficient to calculate the empirical correlation, so that the cooling effect is better while the strength requirement is met;
2. by the aid of a preposed wax hanging filling method before the core presses the wax mould, efficient cooling is guaranteed, and meanwhile the defects of deformation or breakage and the like of the micro-scale structure in the casting process are avoided; by arranging the wax mould supporting piece structure, the wall thickness uniformity and deformation in the casting process are reduced; the positioning of the wax mould and the core is reliable and the deformation is small by arranging the core positioning tool at the front edge, the rear edge, the curved surface flat part and the like of the core.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 is a schematic view of the micro-scale channel cooling pattern of the double-walled turbine blade in example 1 or 2;
FIG. 2 is a schematic view of a core positioning tool according to embodiment 1 or 2;
FIG. 3 is a schematic view showing a structure of a wax pattern supporting member in embodiment 1 or 2;
wherein, 1, a mold core; 2. an impact hole; 3. a turbulence column; 4. positioning a tool; 5. a support member; 6. wax pattern; 7. and (5) air film holes.
Detailed Description
The embodiments of the present application will be described in detail below with reference to the accompanying drawings.
The following embodiments of the present application are described by specific examples, and other advantages and effects of the present application will be readily apparent to those skilled in the art from the disclosure of the present application. It is to be understood that the embodiments described are only a few embodiments of the present application and not all embodiments. The application is capable of other and different embodiments and its several details are capable of modifications and various changes in detail without departing from the spirit of the application. It is to be noted that the features in the following embodiments and examples may be combined with each other without conflict. All other embodiments obtained by a person of ordinary skill in the art based on the embodiments in the present application without making any creative effort belong to the protection scope of the present application.
Example 1
Referring to fig. 1-3, a method of manufacturing a double-walled turbine blade includes the steps of:
step 1, determining base materials and sizes of a double-wall turbine blade core 1 and cooling design parameters of a blade according to the design size and cooling design requirements of a double-wall turbine blade, wherein the cooling design parameters comprise cold air temperature Tc and pressure Pc of an inlet of a cooling channel in the blade, cooling air flow Mc and outlet pressure Pg of a gas film hole 7 on the surface of the blade;
and 3, under given design boundary conditions (the cold air temperature Tc and the pressure Pc at the inlet of the blade cooling channel, the flow rate Mc of cooling air and the outlet pressure Pg of a film hole 7 on the surface of the blade), calculating the internal flow and temperature field of the blade:
the method comprises the steps of firstly calculating to obtain cooling air flow according to the pressure difference (Pc-Pg) of an inlet and an outlet of a cooling channel and a flow coefficient calculation formula, then calculating to obtain the internal heat exchange coefficient of the cooling channel according to the heat exchange coefficient calculation experience correlation, and then loading internal and external boundary conditions on a calculation model of the blade on the basis to sequentially complete the temperature field and strength calculation of the blade. The double-wall impact turbulent flow cooling structure which meets the design requirements (cold air flow, blade temperature and strength) of blade cooling is obtained through continuous iteration until calculation;
wherein, when the turbulence columns 3 are arranged in order, the following calculation formula is adopted for verification:
C d =0.218582Re 0.129919 Kn 0.042870 （H/D） 0.384319
Nu=0.020332Re 0.879857 （H/D） -0.192851
the following calculation formula is adopted for verification when the turbulence columns are in 3-row-crossing layout:
C d =0.205671Re 0.134878 Kn 0.042011 （H/D） 0.398420
Nu=0.019616Re 0.879260 （H/D） -0.168356
C d is the flow coefficient, nu is the Nussel number,Rethe Reynolds number, kn the Knudsen number, and H/D the ratio of impact distance to aperture;
and 4, preparing the blade core 1 which can be cast into a structure with the flow disturbing columns 3 and the inner wall cooling channel according to the size of the core 1, the flow disturbing columns 3 and the size of the cooling channel which meet the relevant formula in the step 3, and then carrying out double-wall turbine blade casting molding by adopting a lost wax method.
In the embodiment, an empirical correlation is calculated according to the flow coefficient and the heat exchange coefficient, whether the size of the core 1, the turbulence column 3 and the cooling channel meet the correlation requirement is calculated and verified, the micro-scale structure of the double-wall turbine blade core 1 is obtained through optimization, the double-wall turbine blade is obtained through the lost wax casting, and the double-wall turbine blade structure with a more efficient cooling effect can be obtained.
And 4, before the casting by the lost wax method, carrying out reinforcement pretreatment on the mold core 1 placed in a casting mold, and specifically comprising the following steps:
A. pre-selecting the front edge and the rear edge of the mold core 1 and the flat curved part of the mold core 1, and applying a positioning tool 4 of the mold core 1;
B. pre-waxing is carried out on the weak part of the strength of the mold core 1, and the weak part of the strength of the mold core 1 is determined by ANSYS software calculation;
C. and carrying out compression molding on the core 1 subjected to the preposed wax hanging treatment by using a wax mold 6, and arranging support parts 5 of the core 1 at the upper edge plate and the lower edge plate of the wax mold 6.
Through the steps, the process of waxing the weak part of the mold core 1 in advance enables the mold core to obtain a more efficient cooling effect of the double-wall blade of the turbine at higher casting pressure, improves the casting qualified rate, and meets the requirement of manufacturing strength. Meanwhile, the mold core 1 is supported by optimally designing the mold core 1 supporting tool and arranging the supporting piece 5 at the flat part of the curved surface to support the mold core 1, so that various defects in the casting process can be reduced, and the qualified rate of finished products is improved.
Example 2
Referring to fig. 1 to fig. 3, the present embodiment provides a method for manufacturing a double-walled turbine blade, and the specific technical solution is as follows:
1. core material determination
The base material of the core 1 is the basis for the manufacture of acceptable double-walled turbine blades. In the embodiment, the matrix material alpha-Al of the core 1 is selected 2 O 3 The purity is more than or equal to 96 percent, the content is controlled to be more than or equal to 88 weight percent, and the granularity range is 30 um-53 um. The mineralizer can be mullite or SiO 2 The content is controlled to be more than or equal to 1.8wt%, and the rest components are plasticizer materials.
2. Design of high-efficiency impact-turbulence column combined cooling structure mold core
The core 1 design of the impingement-turbulator combined cooling structure with efficient cooling performance is the key to the double-walled turbine blade design, as shown in fig. 1. In the embodiment, aiming at a combined cooling structure with the diameter of 2 impact holes being 0.4-0.6 mm, the distance between 2 impact holes being 2-3 times of the hole diameter, the height of a double-wall impact cavity being 0.5-1.0 mm and the diameter of a turbulence column 3 being 0.45-0.65 mm, under the given design boundary condition, an empirical correlation is calculated according to the flow coefficient and the heat exchange coefficient, and the calculation formula of the cross arrangement layout of the turbulence column 3 is adopted to verify whether the size of a core 1 and the sizes of the turbulence column 3 and a cooling channel meet the correlation requirement or not;
C d =0.205671Re 0.134878 Kn 0.042011 （H/D） 0.398420
Nu=0.019616Re 0.879260 （H/D） -0.168356
C d for the flux coefficient, nu is the nussel number: nu = h × D/K, where h is the convective heat transfer coefficient, K is the thermal conductivity of the cooling air,Rereynolds number: re =ρvD/μIn whichv、ρ、μThe flow velocity, density and viscosity coefficient of the cooling air are respectively, and D is the aperture of the impact hole 2; kn is knudsen number: kn =λD, in the formulaλIs the molecular mean free path of the cooling air; H/D is the impact distance to aperture ratio; reynolds number in the present exampleReThe value range is 1000-10000, the Kn number of the knudsen is 1.2 multiplied by 10 -5 -3.5×10 -5 The value range of the impact distance and the aperture ratio H/D is 2-3.
According to the correlation, preliminarily determining the size of the core 1 meeting the correlation requirement, and the sizes of the turbulence column 3 and the cooling channel as the size of the double-wall combined cooling structure core 1; in the embodiment, the double-wall turbine blade corresponding to the size of the core 1, the turbulence column 3 and the cooling channel which meet the correlation requirement is simulated to obtain the temperature field of the blade, and whether the temperature and the stress of the blade are in the temperature resistance and strength ranges of the material is judged; if not, the geometric parameter value is adjusted until the double-wall combined cooling structure meets the requirements, so that the material performance requirements are further met, and a more efficient cooling effect of the double-wall blade of the turbine is obtained.
Through the steps, the sizes of the core 1, the turbulence columns 3 and the cooling channels which meet the correlation requirements are finally determined.
3. Core forming
Preparing a core 1 which can be cast into the turbulence column 3 and the inner wall cooling channel according to the size of the core 1, the turbulence column 3 and the size of the cooling channel which meet the correlation formula, the temperature resistance of the material and the strength range; the present embodiment may use a stereolithography technique or other similar technique (e.g., 3D printing) to mold the core 1 in its initial state from the core 1 model.
4. Core sintering
The shrinkage problem of the core 1 during sintering greatly affects the yield of the final double-walled turbine blade part. Thus, the following sintering parameters of the core 1 are used in this embodiment: the formed core 1 is sintered and formed at 1260-1290 ℃ for 4-10h by adopting the heating rate of 50-100 ℃/h. By the molding method with the preferably determined parameters, the shrinkage rate of the core 1 can be stably controlled within 0.5-0.8%. By combining the shrinkage rate, the size adaptability of the mold core 1 is amplified in advance, and the final molding precision requirement can be met.
5. Positioning of cores
The core 1 structural style that this embodiment can form a multiple layer structure core 1, generally, when multiple layer core 1 carries out the suppression of wax matrix 6 (being about to the core 1 cladding inside wax matrix 6, after follow-up casting blade through the lost wax method, adopt acid, alkali or other auxiliaries that can corrode core 1 to get rid of the core, obtain the blade that has cooling channel, vortex post 3, shock hole 2 and other cooling structure), because the location between the multiple layer core 1 only depends on partial vortex post 3 structure etc. to go on, notice simultaneously, the turbine blade vortex post 3 size of double wall is less, be difficult to satisfy the location and the little deformation requirement in the manufacturing process, the problem such as core leakage often appears under-casting, eccentric core in the casting process.
By adopting the strength evaluation and damage tolerance evaluation method aiming at the double-wall blade, the blade allows a certain crack propagation life, so that the crack cannot rapidly propagate under the condition that the stress level of the front edge and the rear edge is relatively small. In this embodiment, the front and rear edges and the flat curved portions of the core 1 are selected, and the positioning tool 4 for the multilayer core 1 is designed.
As shown in FIG. 2, the positioning tool 4 is arranged at the front and rear edge positions of the blade of the core 1 and the flat position of the curved surface of the core 1, so that the flow disturbing columns 3 with increased quantity are combined to compress the multilayer core 1 while ensuring reliable positioning, the strength is ensured, and the deformation is reduced. The anchor points can be set to be 6-8 according to different situations.
6. Core waxing fill
Generally, the size of the turbulence column 3 on the turbine blade core 1 is 1.2mm or more, and for a double-wall turbine blade, the size of an opening is too large, so that the overall structural strength is influenced; at the same time, oversized sizing does not meet the more efficient cooling requirements of double-walled turbine blades. In the embodiment, before the step of pressing the wax mold 6 by the core 1, the core 1 with the multi-layer structure is filled with pre-waxing, particularly at the weak part of the core 1, typically the structure such as the turbulence column 3 and the wall surface, the support and the like with the thickness of 0.3mm-0.8 mm. In the embodiment, design temperature, vibration, air flow and cold efficiency coefficient parameters are input into ANSYS software, the in-band node generalized plane strain unit plane183 is used for strength calculation, the area with the equivalent stress of more than 420MPa or the mechanical stress of more than 160MPa is determined to be the weak part of the double-wall turbine blade, and the position corresponding to the weak part is reinforced by adopting a pre-wax-coating method, so that the core 1 is prevented from deforming, cracking and breaking. The wax mould 6 formed by the method is used for reinforcing and protecting the weak part, so that the weak structural strength of the core 1 is enhanced, the deformation is reduced, and the defects of deformation, fracture and the like caused by higher casting pressure in the manufacturing process of the double-wall turbine blade are prevented. In the embodiment, the wax-coating filling thickness is generally controlled within the range of 0.3mm-1.0mm, and the cooling time is not less than 8h.
7. Wax mould supporting piece
The double-wall turbine blade is relatively thin in wall thickness, the strength of the traditional structural design is difficult to maintain under high casting pressure, and the upper and lower edge plates and other structures are easy to deform in the manufacturing process, so that the parts are out of tolerance and scrapped. Therefore, the present embodiment is designed as follows: the supporting piece 5 of the core 1 is arranged at the upper edge plate and the lower edge plate of the wax mould 6 and is used for supporting the weak structure of the wax mould 6, as shown in figure 3, the shape adopts a square shape, a round shape or a special shape, and the cross section area range is 2.25mm 2 -6mm 2 . After the design is adopted, the integral strength and the structure of the wax mould 6 are enhanced, and the casting qualified rate is obviously improved.
8. Wax mould casting
The present embodiment adopts the lost wax method to carry out the casting molding of the double-wall turbine blade.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (6)
1. A method of manufacturing a double-walled turbine blade, comprising the steps of:
step 1, determining a base material and a size of a double-wall turbine blade core and cooling design parameters of a blade according to the design size and the cooling design requirement of the double-wall turbine blade, wherein the cooling design parameters comprise the temperature and the pressure of cold air at an inlet of a cooling channel of the blade, the flow rate of the cold air and the outlet pressure of an air film hole on the surface of the blade;
step 2, determining or selecting a double-wall impact cavity height H and an initial impact turbulent flow cooling structure according to the wall thickness design of the blade, wherein the impact turbulent flow cooling structure comprises an impact hole aperture D, a hole pitch P, turbulent flow columns and a cooling channel size;
step 3, under the given design boundary condition, carrying out calculation of the internal flow and temperature field of the blade, and calculating an empirical correlation according to the flow coefficient and the heat exchange coefficient to obtain a double-wall impact turbulent flow cooling structure meeting the cooling design requirement of the blade;
wherein, when the turbulence columns are arranged in order, the following calculation formula is adopted for verification:
C d =0.218582Re 0.129919 Kn 0.042870 （H/D） 0.384319
Nu=0.020332Re 0.879857 （H/D） -0.192851
the following calculation formula is adopted for verification during the cross arrangement of the turbulence columns:
C d =0.205671Re 0.134878 Kn 0.042011 （H/D） 0.398420
Nu=0.019616Re 0.879260 （H/D） -0.168356
C d is the flow coefficient, nu is the Nussel number,Rereynolds number, kn Knudsen number, H/D impact distance and aperture ratio;
and 4, preparing a blade core which can be cast into a structure with the flow disturbing columns and the inner wall cooling channel according to the size of the core, the flow disturbing columns and the size of the cooling channel which meet the correlation in the step 3, and then carrying out double-wall turbine blade casting molding by adopting a lost wax method.
2. The method for manufacturing the double-wall turbine blade according to claim 1, wherein the double-wall turbine blade corresponding to the sizes of the core, the turbulence column and the cooling channel which meet the correlation requirement is simulated in the step 3 to obtain a temperature field of the blade, and whether the temperature and the stress of the blade are in the temperature resistance and strength ranges of the material is judged; if not, the geometric parameter value is adjusted until the double-wall combined cooling structure meets the requirement.
3. The method for manufacturing a double-walled turbine blade according to claim 1, wherein the step 4 of reinforcing the core placed in the casting mold before the lost wax casting is performed comprises the steps of:
A. pre-selecting the front edge and the rear edge of the mold core and the flat part of the curved surface of the mold core, and applying a mold core positioning tool;
B. pre-waxing is carried out on the weak part of the core strength, and the weak part of the core strength is determined by ANSYS software calculation;
C. and carrying out wax mold press forming on the core subjected to the preposed wax hanging treatment, and arranging wax mold supporting parts at the upper edge plate and the lower edge plate of the wax mold.
4. The method for manufacturing the double-walled turbine blade as claimed in claim 1, wherein in the step B, the design temperature, vibration, air flow and cold efficiency coefficient parameters are inputted in ANSYS software, the in-band node generalized plane strain unit plane183 is used for performing strength calculation, the area with the equivalent stress of 420MPa or more or the mechanical stress of 160MPa or more is determined as the weak point of the double-walled turbine blade, and the weak point is reinforced by adopting a pre-wax-coating method at the position corresponding to the weak point.
5. The method for manufacturing a double-walled turbine blade as claimed in claim 4, wherein the wax-coated filling thickness is controlled to be in the range of 0.3mm to 1.0mm, and the cooling time is not less than 8 hours.
6. A method of manufacturing a double-walled turbine blade as claimed in claim 3 wherein the support member is square, circular or profiled in cross-sectional area in the range of 2.25mm 2 -6mm 2 。
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Citations (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB318131A (en) * | 1928-08-28 | 1930-08-25 | Etienne Leyondre | Improvements in foundry moulding machines |
| US5636440A (en) * | 1994-09-07 | 1997-06-10 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Process for manufacturing a hollow blade for a turbo-machine |
| US20070116569A1 (en) * | 2005-11-23 | 2007-05-24 | United Technologies Corporation | Microcircuit cooling for vanes |
| CN103920862A (en) * | 2014-04-30 | 2014-07-16 | 重庆立致和节能科技有限公司 | Die-casting machine asynchronous servo energy-saving control method and system |
| CN104298886A (en) * | 2014-10-20 | 2015-01-21 | 上海电机学院 | Icing 3-D numerical simulation method of aeroengine rotating part |
| CN104907492A (en) * | 2015-05-07 | 2015-09-16 | 西安交通大学 | Making method of surface double-walled hollow turbine blade |
| CN105057642A (en) * | 2015-08-03 | 2015-11-18 | 哈尔滨理工大学 | Simulation method of casting grain structure formation related numerical value |
| CN105593648A (en) * | 2013-07-12 | 2016-05-18 | 约翰·C·卡拉马诺斯 | Fluid control measuring device |
| CN108350746A (en) * | 2015-11-05 | 2018-07-31 | 三菱日立电力系统株式会社 | The manufacturing method of turbo blade and gas turbine, the intermediate processed goods of turbo blade, turbo blade |
| US20180340424A1 (en) * | 2017-05-26 | 2018-11-29 | General Electric Company | Airfoil and method of fabricating same |
| CN109964006A (en) * | 2016-11-14 | 2019-07-02 | 西门子股份公司 | More metal shells that part for combustion turbine engine is cast |
| CN110076292A (en) * | 2019-05-27 | 2019-08-02 | 中国航发北京航空材料研究院 | A kind of investment casting method of duplex block cast directional solidification turborotor |
| CN110732637A (en) * | 2019-09-25 | 2020-01-31 | 西安交通大学 | turbine blade air film hole precision forming method |
| CN210523750U (en) * | 2019-05-31 | 2020-05-15 | 中航装甲科技有限公司 | Ceramic core for preparing hollow blade |
| EP3653839A1 (en) * | 2018-11-16 | 2020-05-20 | Siemens Aktiengesellschaft | Turbine aerofoil |
| CN111914461A (en) * | 2020-09-08 | 2020-11-10 | 北京航空航天大学 | Intelligent assessment method for one-dimensional cold efficiency of turbine guide vane |
-
2022
- 2022-11-21 CN CN202211451891.3A patent/CN115570105B/en active Active
Patent Citations (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB318131A (en) * | 1928-08-28 | 1930-08-25 | Etienne Leyondre | Improvements in foundry moulding machines |
| US5636440A (en) * | 1994-09-07 | 1997-06-10 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Process for manufacturing a hollow blade for a turbo-machine |
| US20070116569A1 (en) * | 2005-11-23 | 2007-05-24 | United Technologies Corporation | Microcircuit cooling for vanes |
| CN105593648A (en) * | 2013-07-12 | 2016-05-18 | 约翰·C·卡拉马诺斯 | Fluid control measuring device |
| CN103920862A (en) * | 2014-04-30 | 2014-07-16 | 重庆立致和节能科技有限公司 | Die-casting machine asynchronous servo energy-saving control method and system |
| CN104298886A (en) * | 2014-10-20 | 2015-01-21 | 上海电机学院 | Icing 3-D numerical simulation method of aeroengine rotating part |
| CN104907492A (en) * | 2015-05-07 | 2015-09-16 | 西安交通大学 | Making method of surface double-walled hollow turbine blade |
| CN105057642A (en) * | 2015-08-03 | 2015-11-18 | 哈尔滨理工大学 | Simulation method of casting grain structure formation related numerical value |
| CN108350746A (en) * | 2015-11-05 | 2018-07-31 | 三菱日立电力系统株式会社 | The manufacturing method of turbo blade and gas turbine, the intermediate processed goods of turbo blade, turbo blade |
| CN109964006A (en) * | 2016-11-14 | 2019-07-02 | 西门子股份公司 | More metal shells that part for combustion turbine engine is cast |
| US20180340424A1 (en) * | 2017-05-26 | 2018-11-29 | General Electric Company | Airfoil and method of fabricating same |
| EP3653839A1 (en) * | 2018-11-16 | 2020-05-20 | Siemens Aktiengesellschaft | Turbine aerofoil |
| CN110076292A (en) * | 2019-05-27 | 2019-08-02 | 中国航发北京航空材料研究院 | A kind of investment casting method of duplex block cast directional solidification turborotor |
| CN210523750U (en) * | 2019-05-31 | 2020-05-15 | 中航装甲科技有限公司 | Ceramic core for preparing hollow blade |
| CN110732637A (en) * | 2019-09-25 | 2020-01-31 | 西安交通大学 | turbine blade air film hole precision forming method |
| CN111914461A (en) * | 2020-09-08 | 2020-11-10 | 北京航空航天大学 | Intelligent assessment method for one-dimensional cold efficiency of turbine guide vane |
Non-Patent Citations (2)
| Title |
|---|
| 朱强华等: "肋开孔高度对大宽高比矩形通道流动传热的影响", 《推进技术》 * |
| 贺宜红;刘存良;宋辉;朱惠人;周志翔;: "不同湍流度下吹风比对涡轮导向叶片吸力面气膜冷却的影响" * |
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