CN205165753U - A ceramic core for making aeroengine and gas turbine blade - Google Patents
A ceramic core for making aeroengine and gas turbine blade Download PDFInfo
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- CN205165753U CN205165753U CN201520913031.6U CN201520913031U CN205165753U CN 205165753 U CN205165753 U CN 205165753U CN 201520913031 U CN201520913031 U CN 201520913031U CN 205165753 U CN205165753 U CN 205165753U
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Abstract
The utility model provides a ceramic core for making aeroengine and gas turbine blade, the curved surface equipartition of establishing hollow inner panel in the ceramic core around, has quantity the same two to be listed as the recess, still is equipped with three rows evenly distributed's through -hole on the preceding curved surface, is equipped with exhaust tail seam and exhaust tail seam positioning end in the one end of being close to the through -hole, upper portion is equipped with well cylinder / round platform positioning head and wedge structure positioning head, and the lower part is equipped with little cylinder / round platform positioning head and big cylinder / round platform positioning head, winding or paste double -sided tape on the upper and lower two sides of exhaust tail seam positioning end and periphery, little cylinder / round platform positioning head, well cylinder / round platform positioning head and big cylinder / round platform positioning head. The utility model discloses a qualification rate that is used for aeroengine and gas turbine's ceramic core, can show the manufacturing degree of difficulty of the pottery nature that reduces core, and effective control ceramic core's size reduces disconnected core that core and shell arouse because of line, coefficient of volumetric expansion nonconformity, leaks core and eccentric problem, has improved ceramic core greatly .
Description
Technical field
The utility model belongs to casting technology field, is specifically related to a kind of ceramic core for the manufacture of aero-engine and gas turbine blades.
Background technology
Blade is the critical component of aero-engine, in the aero-engine in modern times manufactures, in order to form the complicated cavity of blade, ensures blade dimensions and the accuracy of form and position, and the main investment casting method that adopts manufactures hollow blade.In manufacture process, shell, core and alloy itself are separately independently, but in process of setting, the complex-shaped surface mould that shell and core form finally by aluminium alloy filling to form metal blade foundry goods, with regard to technique generally speaking, they are again non-individual bodies.Along with aluminium alloy temperature reduces in metal liquid solidification process, shell, core and aluminium alloy are by respective line, coefficient of volume expansion contraction distortion; Because their line, the coefficient of volume expansion are inconsistent, this contraction distortion is govern mutually, produces stress and concentrates; When this stress exceedes the limit that core can bear, be just released, the casting flaw showing as Blade roughcast is exactly disconnected core, leaks core, or causes the wall thickness instability (or being referred to as core shift) of blade.Along with the progress of technology, researchers have invented the method that shell and core are located, and core designs free end and effectively can avoid disconnected core, leak core problem.But researchers are when making free end; the mode of the manual brushing liquid wax of usual dependence or volatile paint has been come; the drawback of such mode of operation is inefficiency; and size be difficult to control and uneven; when ceramic core press wax process bear high pressure, the impact of high speed wax liquid and cast and directional solidification process bear high-temperature liquid metal impact and for a long time thermal stress time; often there will be the problem of ceramic core core shift, the metallurgical imperfection showing foundry goods is that Blade roughcast wall thickness does not meet design drawing and requires to scrap.
Summary of the invention
For prior art Problems existing, the utility model provides a kind of ceramic core for the manufacture of aero-engine and gas turbine blades, significantly can reduce the manufacture difficulty of pottery core, the size of effective control ceramic core, reduce disconnected core that core and shell cause because line, the coefficient of volume expansion are inconsistent, leak core and core shift problem, the qualification rate of raising ceramic core.The technical solution of the utility model is as follows:
A kind of ceramic core for the manufacture of aero-engine and gas turbine blades, inside establish hollow inner panel, front and back curved surface is evenly equipped with two identical row grooves of quantity, front curve is also provided with the equally distributed through hole of three row, be provided with exhaust tail seam and exhaust tail seam positioning end in the one end near through hole, wherein exhaust tail seam quantity is 8 ~ 15; Top is provided with middle cylinder/round platform positioning head and wedge structure positioning head, and bottom is provided with small column/round platform positioning head and big column/round platform positioning head; Described hollow inner panel is positioned at the centre of two row grooves on same curved surface; The upper and lower surface of described exhaust tail seam positioning end and periphery, small column/round platform positioning head, middle cylinder/round platform positioning head and big column/round platform positioning head are wound around or sticking two-faced adhesive tape band, and being wound around or pasting thickness is 0.05 ~ 0.4mm.
The quantity of described through hole is 54 ~ 114, and diameter is φ 1 ~ 6mm, and through hole two ends are rounding R0.2 ~ R2 peripherally.
The described exhaust tail seam upper and lower surface of positioning end and the head of periphery, small column/round platform positioning head, middle cylinder/round platform positioning head and big column/round platform positioning head and end face are wound around or paste the thick two-sided tape of 0.05 ~ 0.4mm, concrete mode is: on the upper and lower surface and periphery of exhaust tail seam positioning end, paste 0.25 ~ 0.3mm; Small column/round platform positioning head pastes 0.25 ~ 0.3mm, end face is wound around 0.15 ~ 0.2mm, and the distance being wound around the end bottom distance ceramic core end face of two-sided tape is 4 ~ 6mm; Middle cylinder/round platform positioning head pastes 0.35 ~ 0.4mm, end face is wound around 0.15 ~ 0.2mm, and the distance of the end bottom of sticking two-faced adhesive tape band distance ceramic core end face is 4 ~ 6mm; The upper stickup 0.05 ~ 0.1mm of big column/round platform positioning head, end face is wound around 0.05 ~ 0.1mm, and the distance of the end face of the end bottom of sticking two-faced adhesive tape band distance ceramic core is 4 ~ 6mm.
Described two-sided tape thickness in monolayer is 0.05mm.
Feature of the present utility model and beneficial effect are:
Ceramic core for the manufacture of aero-engine and gas turbine blades of the present utility model, significantly can reduce the manufacture difficulty of pottery core, the size of effective control ceramic core, reduce disconnected core that core and shell cause because line, the coefficient of volume expansion are inconsistent, leak core and core shift problem, substantially increase the qualification rate of ceramic core.
Accompanying drawing explanation
The structural representation of Fig. 1 ceramic core for the manufacture of aero-engine and gas turbine blades of the present utility model, wherein 1: bottom small column/round platform positioning head; 2: bottom big column/round platform positioning head; 3: cylinder/round platform positioning head in top; 4: upper wedge structure positioning head; 5: groove; 6: hollow inner panel; 7: through hole; 8: exhaust tail stitches; 9: exhaust tail seam positioning end; 10: two-sided tape.
Fig. 2 is the front view of the ceramic core for the manufacture of aero-engine and gas turbine blades of the present utility model.
Fig. 3 is the D-D face sectional view of ceramic core in Fig. 2, wherein I: the region of exhaust tail seam positioning end sticking two-faced adhesive tape band.
Fig. 4 is the sectional view in cylinder/round platform positioning head A-A face in ceramic core top in Fig. 2, and the stickup thickness wherein on cylinder/round platform positioning head is 0.4mm, and the winding thickness on end face is 0.2mm.
Fig. 5 is the sectional view in ceramic core bottom small column in Fig. 2/round platform positioning head B-B face, and the stickup thickness on wherein small column/round platform positioning head is 0.3mm, and the winding thickness on end face is 0.2mm.
Fig. 6 is the partial view of the sectional view in ceramic core bottom big column in Fig. 2/round platform positioning head C-C face, and the stickup thickness on wherein big column/round platform positioning head is 0.1mm, and the winding thickness on end face is 0.1mm.
Fig. 7 is the partial enlarged drawing of in Fig. 3 I, and wherein the upper and lower surface of exhaust tail seam positioning end pastes 0.25mm, and periphery pastes 0.3mm.
Detailed description of the invention
Below in conjunction with drawings and Examples, the utility model is described in further detail.
Embodiment 1
A kind of ceramic core for the manufacture of aero-engine and gas turbine blades, as shown in Fig. 1 ~ 3, inside establish hollow inner panel 6, front and back curved surface is evenly equipped with two identical row grooves 5 of quantity, front curve is also provided with the equally distributed through hole 7 of three row, be provided with exhaust tail seam 8 and exhaust tail seam positioning end 9 in the one end near through hole, wherein exhaust tail stitches 8 quantity is 13; Top is provided with middle cylinder/round platform positioning head 3 and wedge structure positioning head 4, and bottom is provided with small column/round platform positioning head 1 and big column/round platform positioning head 2; Described hollow inner panel 6 is positioned at the centre of two row grooves 5 on same curved surface; The upper and lower surface of described exhaust tail seam positioning end 9 and periphery, small column/round platform positioning head, middle cylinder/round platform positioning head and big column/round platform positioning head are wound around or sticking two-faced adhesive tape band 10, and being wound around or pasting thickness is 0.05 ~ 0.4mm.
The quantity of described through hole 7 is 114, and diameter is φ 1.5mm, and through hole two ends are rounding R0.5 peripherally.
The described exhaust tail seam upper and lower surface of positioning end 9 and the head of periphery, small column/round platform positioning head 1, middle cylinder/round platform positioning head 3 and big column/round platform positioning head 2 and end face are wound around or paste the thick two-sided tape 10 of 0.05 ~ 0.4mm, as shown in Fig. 4 ~ 7, concrete mode is: paste 0.25mm at the upper and lower surface of exhaust tail seam positioning end, periphery pastes 0.3mm; Stickup thickness on small column/round platform positioning head is 0.3mm, and the winding thickness on end face is 0.2mm, and the distance of the end bottom of sticking two-faced adhesive tape band distance ceramic core end face is 5mm; Stickup thickness on middle cylinder/round platform positioning head is 0.4mm, and the winding thickness on end face is 0.2mm, and the distance of the end bottom of sticking two-faced adhesive tape band distance ceramic core end face is 5mm; Stickup thickness on big column/round platform positioning head is 0.1mm, and the winding thickness on end face is 0.1mm, and the distance of the end face of the end bottom of sticking two-faced adhesive tape band distance ceramic core is 5mm.
Described two-sided tape thickness in monolayer is 0.05mm.
Claims (4)
1. the ceramic core for the manufacture of aero-engine and gas turbine blades, it is characterized in that establishing hollow inner panel in described ceramic core, front and back curved surface is evenly equipped with two identical row grooves of quantity, front curve is also provided with the equally distributed through hole of three row, be provided with exhaust tail seam and exhaust tail seam positioning end in the one end near through hole, wherein exhaust tail seam quantity is 8 ~ 15; Top is provided with middle cylinder/round platform positioning head and wedge structure positioning head, and bottom is provided with small column/round platform positioning head and big column/round platform positioning head; Described hollow inner panel is positioned at the centre of two row grooves on same curved surface; The upper and lower surface of described exhaust tail seam positioning end and periphery, small column/round platform positioning head, middle cylinder/round platform positioning head and big column/round platform positioning head are wound around or sticking two-faced adhesive tape band, and being wound around or pasting thickness is 0.05 ~ 0.4mm.
2. a kind of ceramic core for the manufacture of aero-engine and gas turbine blades according to claim 1, it is characterized in that the quantity of described through hole is 54 ~ 114, diameter is φ 1 ~ 6mm, and through hole two ends are rounding R0.2 ~ R2 peripherally.
3. a kind of ceramic core for the manufacture of aero-engine and gas turbine blades according to claim 1, it is characterized in that the described exhaust tail seam upper and lower surface of positioning end and the head of periphery, small column/round platform positioning head, middle cylinder/round platform positioning head and big column/round platform positioning head and end face being wound around or pasting the thick two-sided tape of 0.05 ~ 0.4mm, concrete mode is: on the upper and lower surface and periphery of exhaust tail seam positioning end, paste 0.25 ~ 0.3mm; Small column/round platform positioning head pastes 0.25 ~ 0.3mm, end face is wound around 0.15 ~ 0.2mm, and the distance being wound around the end bottom distance ceramic core end face of two-sided tape is 4 ~ 6mm; Middle cylinder/round platform positioning head pastes 0.35 ~ 0.4mm, end face is wound around 0.15 ~ 0.2mm, and the distance of the end bottom of sticking two-faced adhesive tape band distance ceramic core end face is 4 ~ 6mm; The upper stickup 0.05 ~ 0.1mm of big column/round platform positioning head, end face is wound around 0.05 ~ 0.1mm, and the distance of the end face of the end bottom of sticking two-faced adhesive tape band distance ceramic core is 4 ~ 6mm.
4. a kind of ceramic core for the manufacture of aero-engine and gas turbine blades according to claim 1, is characterized in that described two-sided tape thickness in monolayer is 0.05mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520913031.6U CN205165753U (en) | 2015-11-17 | 2015-11-17 | A ceramic core for making aeroengine and gas turbine blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520913031.6U CN205165753U (en) | 2015-11-17 | 2015-11-17 | A ceramic core for making aeroengine and gas turbine blade |
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| Publication Number | Publication Date |
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| CN205165753U true CN205165753U (en) | 2016-04-20 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201520913031.6U Active CN205165753U (en) | 2015-11-17 | 2015-11-17 | A ceramic core for making aeroengine and gas turbine blade |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114535505A (en) * | 2022-03-01 | 2022-05-27 | 中国航发北京航空材料研究院 | Method and device for manufacturing turbine blade with inner cavity |
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2015
- 2015-11-17 CN CN201520913031.6U patent/CN205165753U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114535505A (en) * | 2022-03-01 | 2022-05-27 | 中国航发北京航空材料研究院 | Method and device for manufacturing turbine blade with inner cavity |
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