CN114109536A - Engine impeller cover and machining process thereof - Google Patents
Engine impeller cover and machining process thereof Download PDFInfo
- Publication number
- CN114109536A CN114109536A CN202111345394.0A CN202111345394A CN114109536A CN 114109536 A CN114109536 A CN 114109536A CN 202111345394 A CN202111345394 A CN 202111345394A CN 114109536 A CN114109536 A CN 114109536A
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- China
- Prior art keywords
- casting
- wall
- foundry goods
- rib
- impeller cover
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000003754 machining Methods 0.000 title claims description 3
- 238000005266 casting Methods 0.000 claims abstract description 88
- 230000003014 reinforcing effect Effects 0.000 claims abstract description 15
- 238000005516 engineering process Methods 0.000 claims abstract description 9
- 238000013016 damping Methods 0.000 claims abstract description 6
- 238000000034 method Methods 0.000 claims description 16
- 238000010438 heat treatment Methods 0.000 claims description 3
- 238000009987 spinning Methods 0.000 claims description 3
- 238000005728 strengthening Methods 0.000 claims description 3
- 230000000694 effects Effects 0.000 abstract description 2
- 239000000463 material Substances 0.000 abstract description 2
- 239000011248 coating agent Substances 0.000 description 5
- 238000000576 coating method Methods 0.000 description 5
- 239000010410 layer Substances 0.000 description 4
- 239000000853 adhesive Substances 0.000 description 3
- 230000001070 adhesive effect Effects 0.000 description 3
- 208000037656 Respiratory Sounds Diseases 0.000 description 2
- 238000005495 investment casting Methods 0.000 description 2
- 239000003973 paint Substances 0.000 description 2
- 239000006004 Quartz sand Substances 0.000 description 1
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 239000011324 bead Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000001746 injection moulding Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000012188 paraffin wax Substances 0.000 description 1
- 238000005498 polishing Methods 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 239000002994 raw material Substances 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- 239000002356 single layer Substances 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 239000001993 wax Substances 0.000 description 1
Images
Classifications
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/04—Antivibration arrangements
Abstract
The invention relates to an engine impeller cover and a processing technology thereof, comprising a first casting and a second casting, wherein the inner wall of the first casting is provided with a channel, the outer wall of the first casting is integrally formed with a first thread convex rib, the inner wall of the second casting is integrally formed with a second thread convex rib, the first thread convex rib is matched with the second thread convex rib, a spiral channel is formed between the first convex rib and the second thread convex rib, a conical pipe is arranged at the top between the first casting and the second casting, the top of the inner wall of the conical pipe is welded with the top surface of the first casting, the bottom of the inner wall of the conical pipe is welded with the top surface of the second casting, the top surface of the conical pipe is provided with a damping ring, the first casting, the second casting and the conical pipe form an annular cavity with a right-angled triangle interface, a reinforcing rib ring is accommodated in the annular cavity, the reinforcing rib ring comprises a connecting ring and a right-angled reinforcing sheet on the connecting ring and the integrally formed rib and the connecting ring, the connecting ring is clamped in the abutting surfaces of the conical pipe, the inner wall of the top and the first casting, and the invention has the technical effects that the impeller cover of the engine can be lighter under the same material, and cracks are difficult to generate on the inner wall.
Description
Technical Field
The invention relates to the technical field of engine impeller covers, in particular to an engine impeller cover and a processing technology thereof.
Background
The preparation of precision casting needs to be carried out by procedures of injection molding, coating paint, adhering quartz sand, dewaxing, baking and the like, the technological process is that raw materials which are prepared according to a certain proportion are processed to form a mould shell after certain treatment, finally, casting is carried out on the mould shell to form a final casting part, then, the casting part is dewaxed to obtain a mould shell, a wax mould is directly prepared by paraffin in the existing investment casting process, self-transferring paint is used as a transferring coating, then, a layer of adhesive is coated on the surface of the transferring coating, and then, a layer of shell is compounded on the outer layer of the adhesive, and the bonding performance of the transferring coating and the bonding performance of the adhesive determine that the transferring coating can be peeled off in the dewaxing process.
The existing impeller cover can be influenced by aerodynamic force, so that vibration can be generated, and under the condition that the impeller cover is made of conventional materials and is used at the working temperature of 160 ℃ throughout the year, if the strength of the inner surface of the impeller cover is not high enough, the shell is easy to crack in the using process or the carrying process, and the aviation safety is influenced.
Disclosure of Invention
The invention aims to provide an engine impeller cover and a processing technology thereof, which have the effect of detecting whether a person wears shoes with nails on feet or pushes a heavy object into a fragile special maintenance sports field or not at an inlet.
The above object of the present invention is achieved by the following technical solutions:
an engine impeller cover and a processing technology thereof comprise a first casting and a second casting, wherein the first casting is an inner pipe, the inner wall of the first casting is provided with a cylindrical vertical passage, the outer wall of the first casting is integrally formed with a first thread rib, the second casting is an outer pipe, the inner wall of the second casting is integrally formed with a second thread rib, the first thread rib is matched with the second thread rib, a spiral passage is formed between the first rib and the second thread rib, a conical pipe is arranged at the top between the first casting and the second casting, the top of the inner wall of the conical pipe is welded with the top surface of the first casting, the bottom surface of the inner wall of the conical pipe is welded with the top surface of the second casting, the top surface of the conical pipe is provided with a damping ring, and the first casting, the second casting and the conical pipe are formed with an annular cavity with a right-angled triangle interface, the annular cavity is internally provided with a reinforcing rib ring, the reinforcing rib ring comprises a connecting ring and reinforcing rib sheets which are integrally formed with the connecting ring in a right-angle shape, and the connecting ring is clamped in the abutting surfaces of the conical pipe, the inner wall of the top and the first casting.
Preferably, the first casting is poured into a round tube shape, the inner wall of the first casting is formed by a spinning process, and the first threaded convex edge on the outer wall of the first casting is carved.
Preferably, the second casting is poured into a round pipe shape, the second threaded convex edge on the inner wall of the second casting is machined, and the outer wall of the second casting is formed through a stamping process and polished.
Preferably, the second casting is clamped and fixed, the first casting is placed right above the second casting, the outer side wall of the first casting is heated, the first casting is pressed into the second casting after heating, the reinforcing rib ring is clamped on the top surfaces of the first casting and the second casting, and the conical pipe is welded on the top surfaces of the first casting and the second casting.
Preferably, the spiral channel is circular in cross-section.
In conclusion, the invention has the beneficial effects that:
such aircraft engine impeller cover is generally under the same condition, and structural strength is high, is difficult to take place the internal stress because air resistance is too big and produce the crackle, and is longer than the individual layer engine impeller cover life-span, sets up the circular cone pipe simultaneously and sets up cavity and centre gripping strengthening rib in circular cone bottom to make circular cone pipe casting cost lower and structural strength higher, be provided with the damping ring on the circular cone pipe simultaneously, can make the impeller cover be difficult to more produce the crackle.
Drawings
Fig. 1 is a schematic view of the overall structure of the door control device.
The reference numbers are, 1, the first casting, respectively; 2. a second casting; 21. a conical tube; 22. a shock-absorbing ring; 3. the reinforcing rib ring.
Detailed Description
In order to facilitate understanding of those skilled in the art, the present invention will be further described with reference to the following examples and drawings, which are not intended to limit the present invention. The present invention is described in detail below with reference to the attached drawings.
The present invention will be described in further detail with reference to the accompanying drawings.
Referring to fig. 1, an engine impeller cover and a processing technology thereof comprise a first casting 1 and a second casting 2, wherein the first casting 1 is an inner pipe, a cylindrical vertical passage is arranged on the inner wall of the first casting 1, a first thread rib is integrally formed on the outer wall of the first casting 1, the second casting 2 is an outer pipe, a second thread rib is integrally formed on the inner wall of the second casting 2, the first thread rib is matched with the second thread rib, a spiral passage is formed between the first rib and the second thread rib, a conical pipe 21 is arranged at the top between the first casting 1 and the second casting 2, the top of the inner wall of the conical pipe 21 is welded with the top surface of the first casting 1, the bottom surface of the inner wall of the conical pipe 21 is welded with the top surface of the second casting 2, a damping ring 22 is arranged on the top surface of the conical pipe 21, and an annular cavity with a right-angled triangle interface is formed by the first casting 1, the second casting 2 and the conical pipe 21, the annular cavity is internally provided with a reinforcing rib ring 3, the reinforcing rib ring 3 comprises a connecting ring and reinforcing rib sheets which are integrally formed with the connecting ring in a right-angle shape, and the connecting ring is clamped in the conical pipe 21, the inner wall of the top and the abutting surface of the first casting 1.
The working principle is as follows: the aircraft engine impeller cover is generally high in structural strength under the same condition, internal stress is not prone to generating cracks due to overlarge air resistance, the service life of the aircraft engine impeller cover is longer than that of a single-layer engine impeller cover, the conical pipe 21 is arranged, and the bottom of the conical pipe 21 is provided with the cavity and the clamping reinforcing ribs, so that the casting cost of the conical pipe 21 is lower, the structural strength is higher, and meanwhile the damping ring 22 is arranged on the conical pipe 21, so that the impeller cover is not prone to generating cracks.
The method comprises the steps of pouring a first casting 1 into a circular tube shape, forming the inner wall of the first casting 1 by adopting a spinning process, and carving the first threaded convex edge on the outer wall of the first casting 1. By adopting the process to process the first casting 1, the inner wall of the first casting 1 is compacter, and the density is higher and the high temperature resistance is higher.
Pour into the pipe form with second foundry goods 2 earlier, process the second screw thread bead of second foundry goods 2 inner wall again, pass through the stamping process shaping with 2 outer walls of second foundry goods and carry out the polishing again, adopt such structure can make 2 surfaces of second foundry goods more smooth.
First 2 centre gripping of second foundry goods are fixed, place first foundry goods 1 directly over second foundry goods 2, then heat 1 lateral wall of first foundry goods, press first foundry goods 1 into inside the second foundry goods 2 after the heating, then with the joint of strengthening rib ring 3 in first foundry goods 1 and 2 top surfaces of second foundry goods, then weld circular cone 21 in the top surface of first foundry goods 1 and second foundry goods 2.
The spiral channel is circular in cross section.
Although the present invention has been described with reference to the above preferred embodiments, it should be understood that various changes, substitutions and alterations can be made herein without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (5)
1. An engine impeller cover and a processing technology thereof are characterized in that: comprises a first casting (1) and a second casting (2), wherein the first casting (1) is an inner tube, the inner wall of the first casting (1) is provided with a cylindrical vertical passage, the outer wall of the first casting (1) is provided with a first thread rib through integral forming, the second casting (2) is an outer tube, the inner wall of the second casting (2) is provided with a second thread rib through integral forming, the first thread rib is matched with the second thread rib, a spiral passage is formed between the first rib and the second thread rib, a conical tube (21) is arranged at the top between the first casting (1) and the second casting (2), the top of the inner wall of the conical tube (21) is welded with the top surface of the first casting (1), the bottom of the inner wall of the conical tube (21) is welded with the top surface of the second casting (2), and a damping ring (22) is arranged on the top surface of the conical tube (21), the first casting (1), the second casting (2) and the conical pipe (21) are provided with an annular cavity of which the interface is a right-angled triangle, a reinforcing rib ring (3) is accommodated in the annular cavity, the reinforcing rib ring (3) comprises a connecting ring and reinforcing rib sheets which are integrally formed with the connecting ring and are in right-angle shapes, and the connecting ring is clamped in the abutting surfaces of the conical pipe (21), the top inner wall and the first casting (1).
2. The process for machining the engine and the impeller cover thereof according to claim 1, wherein the process comprises the following steps: the method comprises the steps of pouring a first casting (1) into a circular tube shape, forming the inner wall of the first casting (1) by adopting a spinning process, and engraving a first threaded convex edge on the outer wall of the first casting (1).
3. The engine impeller cover and the processing technology thereof according to claim 2, characterized in that: the second casting (2) is poured into a round pipe shape, the second threaded convex edge on the inner wall of the second casting (2) is machined, and the outer wall of the second casting (2) is formed through a stamping process and polished.
4. The engine impeller cover and the processing technology thereof according to claim 3, characterized in that: fix second foundry goods (2) centre gripping earlier, put first foundry goods (1) directly over second foundry goods (2), then heat first foundry goods (1) lateral wall, press first foundry goods (1) into second foundry goods (2) inside after the heating, then with strengthening rib ring (3) joint in first foundry goods (1) and second foundry goods (2) top surface, then weld circular cone pipe (21) in the top surface of first foundry goods (1) and second foundry goods (2).
5. The engine impeller cover and the processing technology thereof according to claim 4, characterized in that: the spiral channel is circular in cross section.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111345394.0A CN114109536A (en) | 2021-11-15 | 2021-11-15 | Engine impeller cover and machining process thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111345394.0A CN114109536A (en) | 2021-11-15 | 2021-11-15 | Engine impeller cover and machining process thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114109536A true CN114109536A (en) | 2022-03-01 |
Family
ID=80396054
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111345394.0A Pending CN114109536A (en) | 2021-11-15 | 2021-11-15 | Engine impeller cover and machining process thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114109536A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050269443A1 (en) * | 2004-03-29 | 2005-12-08 | Airbus France | Air intake structure for aircraft engine |
| US20080279688A1 (en) * | 2007-05-11 | 2008-11-13 | Jensen Joseph M | Heated engine nose cone using spiral channels |
| CN105599906A (en) * | 2016-01-28 | 2016-05-25 | 南京航空航天大学 | Aero-engine rectification cover hood anti-icing device adopting loop type heat pipe and anti-icing method of aero-engine rectification cover hood anti-icing device |
| CN110318883A (en) * | 2019-07-10 | 2019-10-11 | 西北工业大学 | A kind of aero-engine calotte single hole impingement heat transfer structure in helical curve channel |
-
2021
- 2021-11-15 CN CN202111345394.0A patent/CN114109536A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050269443A1 (en) * | 2004-03-29 | 2005-12-08 | Airbus France | Air intake structure for aircraft engine |
| US20080279688A1 (en) * | 2007-05-11 | 2008-11-13 | Jensen Joseph M | Heated engine nose cone using spiral channels |
| CN105599906A (en) * | 2016-01-28 | 2016-05-25 | 南京航空航天大学 | Aero-engine rectification cover hood anti-icing device adopting loop type heat pipe and anti-icing method of aero-engine rectification cover hood anti-icing device |
| CN110318883A (en) * | 2019-07-10 | 2019-10-11 | 西北工业大学 | A kind of aero-engine calotte single hole impingement heat transfer structure in helical curve channel |
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