CN111946461A - Wing shaft for aerospace engine and manufacturing process thereof - Google Patents
Wing shaft for aerospace engine and manufacturing process thereof Download PDFInfo
- Publication number
- CN111946461A CN111946461A CN202010730257.8A CN202010730257A CN111946461A CN 111946461 A CN111946461 A CN 111946461A CN 202010730257 A CN202010730257 A CN 202010730257A CN 111946461 A CN111946461 A CN 111946461A
- Authority
- CN
- China
- Prior art keywords
- pressure air
- shaft
- air cavity
- wing shaft
- guide shaft
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- 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
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
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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
-
- 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
- B22C9/24—Moulds for peculiarly-shaped castings for hollow articles
Abstract
The invention relates to the technical field of space engines and discloses a wing shaft for a space engine and a manufacturing process thereof, wherein one end of the wing shaft is provided with a guide shaft, a central axis position in the flaming guide shaft is provided with a flaming hole, a high-pressure air cavity is arranged below the guide shaft, and the high-pressure air cavity and the guide shaft are integrally cast and molded; the high-pressure air cavity is internally provided with a gas storage chamber for storing high-pressure gas, the fire spraying hole is communicated with the high-pressure air cavity, and the bottom of the high-pressure air cavity is provided with an air inlet hole; the joint of the guide shaft and the high-pressure air chamber forms a buffering surface for gas to enter the fire-spraying hole. The high-pressure gas cavity is used for storing high-pressure gas, flame is sprayed out through the fire spraying holes, the pressure of the gas is buffered through the buffering surface, and the service life of the wing shaft is prolonged; because the guide shaft and the high-pressure air cavity of the wing shaft are integrally formed by casting, no welding seam or unstable structure part exists, the structural stability is good, and the service life of the wing shaft is long.
Description
Technical Field
The invention relates to the technical field of aerospace engines, in particular to a wing shaft for an aerospace engine and a manufacturing process thereof.
Background
The wing shaft of the aerospace engine is an important component for controlling the advancing direction of a rocket, and the existing wing shaft is usually manufactured in a manufacturing mode of sectional forging, then machining to a designed size, and then welding two sections into a whole.
In the rocket launching and advancing process, the welding part can not bear the high-temperature and high-pressure state under the working state that the wing shaft is at the temperature of over 1200 ℃ and the pressure of 10 MPa, and if the wing shaft is under the high-temperature and high-pressure state for a long time, crack defects are easy to appear at the welding seam, so that the rocket launching and advancing process is simple and convenient. The service life of the existing wing shaft is short.
When the wing shaft is in a working state, a large amount of high-pressure high-temperature gas needs to be stored in the wing shaft, and the structure of the wing shaft needs to bear long-time high-pressure impact, so that the structure of the wing shaft needs to be reasonably designed.
Disclosure of Invention
The invention provides a wing shaft for an aerospace engine and a manufacturing process thereof, which improve the existing wing shaft structure and the manufacturing process thereof, improve the performance of the wing shaft and prolong the service life of the wing shaft.
The technical scheme of the invention is realized as follows: a wing shaft for an aerospace engine is characterized in that a guide shaft is arranged at one end of the wing shaft, a fire spraying hole is formed in the central axis position inside the fire spraying guide shaft, a high-pressure air cavity is arranged below the guide shaft, and the high-pressure air cavity and the guide shaft are integrally cast and molded; the high-pressure gas cavity is internally provided with a gas storage chamber for storing high-pressure gas, the flame spray hole is communicated with the high-pressure gas cavity, and the bottom of the high-pressure gas cavity is provided with a gas inlet hole; the joint of the guide shaft and the high-pressure air chamber forms a buffer surface for gas to enter the fire-spraying hole.
As a preferable technical scheme, the aperture of the fire hole is far smaller than the maximum inner diameter of the high-pressure air cavity, and the outer diameter of the guide shaft is smaller than the outer diameter of the high-pressure air cavity.
As a preferable technical scheme, the longitudinal section of the high-pressure air cavity is in a shape with a wide upper part and a narrow lower part.
As a preferred technical scheme, the buffer surface is an inclined surface which forms a certain included angle with the horizontal plane.
As a preferred technical scheme, a reinforcing part for reinforcing the mechanical strength of the high-pressure air cavity is arranged on the outer wall of the high-pressure air cavity.
A manufacturing process of a wing shaft of an aerospace engine comprises the following steps:
step 1, manufacturing a mandrel according to the design size of a high-pressure air cavity of a wing shaft;
step 2, coating protective materials on the outer part of the mandrel, and pressing a wax mold on the outer side of the mandrel according to the design size of the wing shaft;
step 3, spraying refractory sand to the outer side of the wax mold to form a mold shell, and roasting and hardening the mold shell;
step 4, pouring molten metal smelted into liquid into the mould shell, cooling and forming the molten metal to form a blank, and removing mandrel materials in the blank;
and 5, performing finish machining on the outer surface of the blank body, and machining a fire spraying hole at the top end of the blank body.
According to the preferable technical scheme, the mandrel is a loose refractory sand mixture which is easy to remove, and a protective layer formed by solidifying fine sand is wrapped on the outer side of the mandrel.
The invention has the beneficial effects that: the high-pressure gas cavity is used for storing high-pressure gas, flame is sprayed out through the fire spraying holes, the pressure of the gas is buffered through the buffering surface, and the service life of the wing shaft is prolonged; because the guide shaft and the high-pressure air cavity of the wing shaft are integrally formed by casting, no welding seam or unstable structure part exists, the structural stability is good, and the service life of the wing shaft is long.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a schematic structural view of the present invention;
fig. 2 is a cross-sectional view taken at a-a in fig. 1.
In the drawings, 1-guide shaft; 11-flame holes; 2-high pressure air cavity; 21-an air intake; 22-a buffer surface; 23-reinforcement.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments, and the description of the embodiments is provided to help understanding of the present invention, but not to limit the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present application, it is to be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the present application and for simplicity in description, and are not intended to indicate or imply that the referenced devices or elements must have a particular orientation, be constructed in a particular orientation, and be operated in a particular manner, and are not to be construed as limiting the present application. Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, features defined as "first", "second", may explicitly or implicitly include one or more of the described features. In the description of the present application, "a plurality" means two or more unless specifically limited otherwise.
As shown in fig. 1 and 2, a wing shaft for an aerospace engine, wherein one end of the wing shaft is provided with a guide shaft 1, a fire spraying hole 11 is formed in the central axis position inside the fire spraying guide shaft 1, a high-pressure air cavity 2 is arranged below the guide shaft 1, and the high-pressure air cavity 2 and the guide shaft 1 are integrally cast and formed; the high-pressure gas cavity 2 is internally provided with a gas storage device for storing high-pressure gas, the fire spraying hole 11 is communicated with the high-pressure gas cavity 2, and the bottom of the high-pressure gas cavity 2 is provided with a gas inlet 21; the joint of the guide shaft 1 and the high-pressure gas chamber 2 forms a buffer surface 22 for gas to enter the fire hole 11.
Preferably, the diameter of the flame hole 11 is much smaller than the maximum inner diameter of the high pressure air chamber 2, and the outer diameter of the guide shaft 1 is smaller than the outer diameter of the high pressure air chamber 2.
Preferably, the longitudinal section of the high pressure air chamber 2 is in a shape with a wide top and a narrow bottom, in this embodiment, the shape of the high pressure air chamber 2 is trapezoidal, and in the present invention, the shape of the high pressure air chamber 2 may also be triangular, or both side walls of the high pressure air chamber 2 may also be arc-shaped protruding outwards.
Because the buffer surface 22 is required to bear a larger pressure when the flame is sprayed out, in order to improve the compression resistance of the buffer surface 22, the buffer surface 22 is an inclined surface forming a certain included angle with the horizontal plane.
Preferably, the outer wall of the high pressure air chamber 2 is provided with a reinforcement 23 for enhancing the mechanical strength of the high pressure air chamber 2.
The manufacturing process of the wing shaft comprises the following steps:
step 1, manufacturing a mandrel according to the design size of a high-pressure air cavity of a wing shaft; the core shaft is a loose refractory sand mixture which is easy to remove, and the outer side of the core shaft is wrapped with a protective layer formed by solidifying fine sand.
Step 2, coating protective materials on the outer part of the mandrel, and pressing a wax mold on the outer side of the mandrel according to the design size of the wing shaft;
step 3, spraying refractory sand to the outer side of the wax mold to form a mold shell, and roasting and hardening the mold shell;
step 4, pouring molten metal smelted into liquid into the mould shell, cooling and forming the molten metal to form a blank, and removing mandrel materials in the blank;
and 5, performing finish machining on the outer surface of the blank body, and machining a fire spraying hole at the top end of the blank body.
The present invention is not limited to the above preferred embodiments, and any modifications, equivalent substitutions, improvements, etc. within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (7)
1. A wing shaft for an aerospace engine, characterized in that: one end of the wing shaft is provided with a guide shaft, a fire spraying hole is formed in the central axis position inside the fire spraying guide shaft, a high-pressure air cavity is arranged below the guide shaft, and the high-pressure air cavity and the guide shaft are integrally cast and molded; the high-pressure gas cavity is internally provided with a gas storage chamber for storing high-pressure gas, the flame spray hole is communicated with the high-pressure gas cavity, and the bottom of the high-pressure gas cavity is provided with a gas inlet hole; the joint of the guide shaft and the high-pressure air chamber forms a buffer surface for gas to enter the fire-spraying hole.
2. A wing shaft for an aerospace engine according to claim 1, wherein: the aperture of the flame spray hole is far smaller than the maximum inner diameter of the high-pressure air cavity, and the outer diameter of the guide shaft is smaller than the outer diameter of the high-pressure air cavity.
3. A wing shaft for an aerospace engine according to claim 1, wherein: the longitudinal section of the high-pressure air cavity is in a shape with a wide upper part and a narrow lower part.
4. A wing shaft for an aerospace engine according to claim 1, wherein: the buffer surface is an inclined surface forming a certain included angle with the horizontal surface.
5. A wing shaft for an aerospace engine according to claim 1, wherein: and the outer wall of the high-pressure air cavity is provided with a reinforcing part for reinforcing the mechanical strength of the high-pressure air cavity.
6. A manufacturing process of a wing shaft of an aerospace engine is characterized by comprising the following steps:
step 1, manufacturing a mandrel according to the design size of a high-pressure air cavity of a wing shaft;
step 2, coating protective materials on the outer part of the mandrel, and pressing a wax mold on the outer side of the mandrel according to the design size of the wing shaft;
step 3, spraying refractory sand to the outer side of the wax mold to form a mold shell, and roasting and hardening the mold shell;
step 4, pouring molten metal smelted into liquid into the mould shell, cooling and forming the molten metal to form a blank, and removing mandrel materials in the blank;
and 5, performing finish machining on the outer surface of the blank body, and machining a fire spraying hole at the top end of the blank body.
7. The process for manufacturing a wing shaft of an aerospace engine according to claim 6, wherein: the core shaft is a loose refractory sand mixture which is easy to remove, and the outer side of the core shaft is wrapped with a protective layer formed by solidifying fine sand.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010730257.8A CN111946461A (en) | 2020-07-27 | 2020-07-27 | Wing shaft for aerospace engine and manufacturing process thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010730257.8A CN111946461A (en) | 2020-07-27 | 2020-07-27 | Wing shaft for aerospace engine and manufacturing process thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111946461A true CN111946461A (en) | 2020-11-17 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010730257.8A Pending CN111946461A (en) | 2020-07-27 | 2020-07-27 | Wing shaft for aerospace engine and manufacturing process thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111946461A (en) |
Citations (13)
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| JPH0542895A (en) * | 1991-08-13 | 1993-02-23 | Mitsubishi Heavy Ind Ltd | Complex control device of thrust direction and steering for missile |
| EP0878688A1 (en) * | 1995-05-26 | 1998-11-18 | Hughes Missile Systems Company | Missile jet vane control system and method |
| RU2251013C2 (en) * | 2003-07-08 | 2005-04-27 | Открытое акционерное общество Научно-производственное объединение "Искра" | Rocket engine jet vane |
| CN101216274A (en) * | 2008-01-15 | 2008-07-09 | 靳殷实 | Electric shock bomb |
| CN101910002A (en) * | 2007-11-29 | 2010-12-08 | 阿斯特里姆有限公司 | Spacecraft afterbody device |
| SE1000179A1 (en) * | 2010-02-25 | 2011-08-26 | Bae Systems Bofors Ab | Garnet provided with folding wings and control device |
| US9040886B1 (en) * | 2013-05-08 | 2015-05-26 | The Boeing Company | Adaptive aerodynamic control system for projectile maneuvering |
| EP2659219B1 (en) * | 2010-12-30 | 2016-08-17 | Israel Aerospace Industries Ltd. | Projectile |
| CN207331689U (en) * | 2017-08-22 | 2018-05-08 | 华北水利水电大学 | Rocket bores earth anchor |
| CN108372936A (en) * | 2018-03-02 | 2018-08-07 | 北京星际荣耀空间科技有限公司 | A kind of rocket efficient and light weight moves airvane and its manufacturing method entirely |
| CN108791820A (en) * | 2018-05-08 | 2018-11-13 | 兰州空间技术物理研究所 | A kind of flat steering engine mechanism for aileron |
| CN111059965A (en) * | 2019-12-27 | 2020-04-24 | 中国航天科工集团八五一一研究所 | Small-diameter missile wing piece unfolding mechanism with limiting and self-locking functions |
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| JPH0542895A (en) * | 1991-08-13 | 1993-02-23 | Mitsubishi Heavy Ind Ltd | Complex control device of thrust direction and steering for missile |
| EP0878688A1 (en) * | 1995-05-26 | 1998-11-18 | Hughes Missile Systems Company | Missile jet vane control system and method |
| RU2251013C2 (en) * | 2003-07-08 | 2005-04-27 | Открытое акционерное общество Научно-производственное объединение "Искра" | Rocket engine jet vane |
| CN101910002A (en) * | 2007-11-29 | 2010-12-08 | 阿斯特里姆有限公司 | Spacecraft afterbody device |
| CN101216274A (en) * | 2008-01-15 | 2008-07-09 | 靳殷实 | Electric shock bomb |
| SE1000179A1 (en) * | 2010-02-25 | 2011-08-26 | Bae Systems Bofors Ab | Garnet provided with folding wings and control device |
| EP2659219B1 (en) * | 2010-12-30 | 2016-08-17 | Israel Aerospace Industries Ltd. | Projectile |
| US9040886B1 (en) * | 2013-05-08 | 2015-05-26 | The Boeing Company | Adaptive aerodynamic control system for projectile maneuvering |
| CN207331689U (en) * | 2017-08-22 | 2018-05-08 | 华北水利水电大学 | Rocket bores earth anchor |
| CN108372936A (en) * | 2018-03-02 | 2018-08-07 | 北京星际荣耀空间科技有限公司 | A kind of rocket efficient and light weight moves airvane and its manufacturing method entirely |
| CN108791820A (en) * | 2018-05-08 | 2018-11-13 | 兰州空间技术物理研究所 | A kind of flat steering engine mechanism for aileron |
| CN210773705U (en) * | 2019-10-08 | 2020-06-16 | 中国人民武装警察部队工程大学 | Empennage stable type barrier-breaking tear-gas shells |
| CN111059965A (en) * | 2019-12-27 | 2020-04-24 | 中国航天科工集团八五一一研究所 | Small-diameter missile wing piece unfolding mechanism with limiting and self-locking functions |
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Application publication date: 20201117 |