CN215109041U - Low pressure guide vane based on additive manufacturing - Google Patents
Low pressure guide vane based on additive manufacturing Download PDFInfo
- Publication number
- CN215109041U CN215109041U CN202121293966.0U CN202121293966U CN215109041U CN 215109041 U CN215109041 U CN 215109041U CN 202121293966 U CN202121293966 U CN 202121293966U CN 215109041 U CN215109041 U CN 215109041U
- Authority
- CN
- China
- Prior art keywords
- thick bamboo
- shell
- blade shell
- central body
- edge section
- 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.)
- Active
Links
Images
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The utility model belongs to the technical field of guide blade, a low pressure guide blade based on additive manufacturing is disclosed, including cup jointing outer edge section of thick bamboo and inner edge section of thick bamboo together, even integrated into one piece has outer blade shell and interior blade shell between outer edge section of thick bamboo and the inner edge section of thick bamboo, the upper and lower both ends of interior blade shell inner chamber run through outer edge section of thick bamboo and inner edge section of thick bamboo respectively, the inner chamber grafting central body of interior blade shell, one side parallel and level that interior edge section of thick bamboo was kept away from to central body and outer edge section of thick bamboo, one side parallel and level that outer edge section of thick bamboo was kept away from to central body and inner edge section of thick bamboo, distance between central body head side and interior blade shell inner chamber is greater than the distance between central body tail side and interior blade shell inner chamber, the central body basin side is greater than distance between dorsal part and interior blade shell inner chamber, fixed mounting has the bracing piece between central body and the interior blade shell. The utility model discloses a setting of center body isotructure can the cooling air that reasonable distribution got into the guide vane inner chamber, promotes heat exchange capacity, guarantees guide vane's operational reliability.
Description
Technical Field
The application belongs to the technical field of guide vanes, and particularly relates to a low-pressure guide vane based on additive manufacturing.
Background
The guide vane is an important component of a turbine section in a gas turbine engine, and the guide vane rotating at high speed is responsible for sucking high-temperature and high-pressure airflow into a combustor to maintain the operation of the engine. In order to ensure stable operation in extreme environments of high temperature and high pressure, the guide vanes are often forged by high temperature alloy, and cooled by forming an air film by air circulating inside, thereby ensuring reliability in operation.
Traditional low pressure guide vane is obtained through casting or machine tooling, the molding is more difficult when making structures such as accurate air film hole and split joint, the low pressure guide vane who makes through the mode of vibration material disk among the prior art can accomplish comparatively complicated molding and reduce the manufacturing degree of difficulty, but low pressure guide vane is at work, the temperature of the head side and the basin side of blade is higher, the temperature of dorsal side and caudal side is lower, the cooling air that gets into the low pressure guide vane inner chamber can not rationally be distributed, lead to heat exchange capacity poor, in order to solve above-mentioned problem, we propose the low pressure guide vane based on vibration material disk.
SUMMERY OF THE UTILITY MODEL
The utility model aims at the above-mentioned problem that exists, propose low pressure guide vane based on additive manufacturing.
Low pressure guide blade based on vibration material disk, including cup jointing an outer edge section of thick bamboo and an inner edge section of thick bamboo together, even integrated into one piece has outer blade shell and interior blade shell between an outer edge section of thick bamboo and the inner edge section of thick bamboo, and interior blade shell is located the inboard of outer blade shell, an outer edge section of thick bamboo and an inner edge section of thick bamboo are run through respectively to the upper and lower both ends of interior blade shell inner chamber, and the inner chamber grafting of interior blade shell is equipped with the central body, and the one side parallel and level of an inner edge section of thick bamboo is kept away from to central body and outer edge section of thick bamboo, and the one side parallel and level of an outer edge section of thick bamboo is kept away from to central body and inner edge section of thick bamboo, and the distance between central body head side and interior blade shell inner chamber is greater than the distance between central body caudal side and interior blade shell inner chamber, and fixed mounting has the bracing piece between central body and the interior blade shell, bracing piece dislocation set.
Furthermore, the gas film holes are uniformly formed in the back side, the basin side and the head side of the inner blade shell, the number of the gas film holes in the basin side of the inner blade shell is more than that in the back side of the inner blade shell, and the diameter of the gas film holes from the head side to the tail side of the inner blade shell is gradually reduced.
Furthermore, the cross section of the air film hole is of a horn-shaped structure, and the diameter of the opening of the air film hole close to the outer blade shell is larger than that of the opening of the air film hole close to the central body.
Furthermore, the back side and the basin side of the outer blade shell are uniformly provided with split slits, the number of the split slits on the basin side of the outer blade shell is more than that of the split slits on the back side of the outer blade shell, and the distance between the split slits is gradually increased from the head side to the tail side of the outer blade shell.
Further, the split slot is inclined from inside to outside toward the trailing side of the outer blade shell.
Furthermore, a guide plate is uniformly and integrally formed between the outer blade shell and the inner blade shell.
Furthermore, the tail side of the outer blade shell is uniformly provided with a guide outlet, and the tail side of the inner cavity of the outer blade shell is integrally formed with turbulence columns which are arranged in a staggered manner.
Compared with the prior art, the utility model has the advantages of it is following:
the utility model discloses a setting of center body isotructure can the cooling air that reasonable distribution got into the guide vane inner chamber, promotes heat exchange capacity, guarantees guide vane's operational reliability.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments described in the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic front view of a single guide vane of the present invention;
FIG. 2 is a schematic top view of a single guide vane of the present invention;
fig. 3 is a schematic sectional view of the structure of fig. 1 along the direction a-a.
In the figure: 1. the outer edge barrel, 2. the outer blade shell, 3. the split slit, 4. the air film hole, 5. the guide plate, 6. the inner blade shell, 7. the turbulence column, 8. the guide outlet, 9. the support rod, 10. the central body, 11. the inner edge barrel.
Detailed Description
The present invention will be described in detail below with reference to embodiments shown in the drawings. However, the present invention is not limited to the above embodiments, and structural, method, or functional changes made by those skilled in the art according to the present invention are all included in the scope of the present invention.
The utility model discloses a low pressure guide vane based on vibration material disk, refer to fig. 1-3 and show, including cup jointing outer fringe section of thick bamboo 1 and inner edge section of thick bamboo 11 together, outer fringe section of thick bamboo 1 cup joints in the outside of inner edge section of thick bamboo 11, and outer fringe section of thick bamboo 1 and inner edge section of thick bamboo 11 are tube-shaped structure, and the circumference surface both ends of outer fringe section of thick bamboo 1 and the circumference internal surface both ends integrated into one piece of inner edge section of thick bamboo 11 have connection structure, can install location outer fringe section of thick bamboo 1 and inner edge section of thick bamboo 11 on turbine engine machine casket through connection structure.
The supporting rod 9 plays a role in supporting and fixing the central body 10, and the input amount of cooling air is distributed and guided when the cooling air enters the inner cavity of the inner blade shell 6 through the position relation between the central body 10 and the inner cavity of the inner blade shell 6, so that the amount of the cooling air entering a high-temperature area is large, the amount of the cooling air entering a low-temperature area is small, and the distribution is more reasonable.
Inside vane shell 6's dorsal part, air film hole 4 has evenly been seted up to pelvic side and cephalad, air film hole 4 can be with interior vane shell 6 and the central body 10 between leading-in cooling air input outside vane shell 2 and the interior vane shell 6 between form the air film for cooling, the air film hole 4 quantity of 6 pelvic sides of interior vane shell is more than inside vane shell 6 dorsal air film hole 4 quantity, inside vane shell 6 reduces from the air film hole 4 diameter of cephalad to caudal side gradually, the volume that makes cooling air get into 2 cephalad and pelvic side of outside vane shell is great, cooling air distributes more rationally.
The cross section of the air film hole 4 is of a horn-shaped structure, and the opening diameter of the air film hole 4 close to the outer blade shell 2 is larger than that of the air film hole 4 close to the central body 10, so that when cooling air enters between the outer blade shell 2 and the inner blade shell 6, the cooling air is dispersed more rapidly and is contacted with the outer blade shell 2 more fully.
The back side and the basin side of the outer blade shell 2 are uniformly provided with the partial cleft seams 3, the number of the partial cleft seams 3 on the basin side of the outer blade shell 2 is more than that of the partial cleft seams 3 on the back side of the outer blade shell 2, the distance between the partial cleft seams 3 is gradually increased from the head side to the tail side of the outer blade shell 2, through the arrangement of the partial cleft seams 3, the cooling air of the high-temperature area part of the outer blade shell 2 can be guided out, the discharge flow of the cooling air of the high-temperature area is increased, the heat exchange efficiency is improved, meanwhile, the discharged cooling air is converged with the outside air, and the vortex-type heat exchanger has certain vortex processing capacity.
The side slit 3 is inclined from the inside to the outside towards the tail side of the outer blade shell 2, so that hot air on the outer side can not enter the outer blade shell 2 from the side slit 3.
Even integrated into one piece has guide plate 5 between outer blade shell 2 and the interior blade shell 6, and the delivery port 8 has evenly been seted up to the caudal side of outer blade shell 2, is convenient for promote heat transfer ability through guide plate 5 and can derive the afterbody of cooling air to outer blade shell 2 behind the heat transfer between outer blade shell 2 and the interior blade shell 6 and discharge through delivery port 8, joins with outside air, has certain vortex throughput.
The trailing side integrated into one piece of 2 inner chambers of outer blade shell has vortex post 7, and vortex post 7 dislocation set can increase the discharge resistance of heat transfer back cooling air through the vortex post 7 of dislocation, makes the contact of cooling air and outer blade shell 2 more abundant, and the heat transfer effect is better.
Specifically, the outer edge cylinder 1 and the inner edge cylinder 11 can be installed and positioned on a turbine engine casing through a connecting structure, when a low-pressure guide blade is driven by a turbine engine to rotate, cooling air enters an inner cavity of an inner blade shell 6, input quantity of the cooling air is distributed and guided through the position relation between a central body 10 and the inner cavity of the inner blade shell 6, the cooling air is distributed through an air film hole 4 and enters between an outer blade shell 2 and the inner blade shell 6 to form a cooling air film for heat exchange, heat exchange capacity is improved conveniently through a guide plate 5, the cooling air after heat exchange between the outer blade shell 2 and the inner blade shell 6 can be guided out to the tail part of the outer blade shell 2 through a guide outlet 8 and is discharged out to be converged with external air, certain turbulence processing capacity is achieved, meanwhile, cooling air in a high-temperature region part of the outer blade shell 2 can be guided out through a cleavage slit 3, and discharge flow rate of the cooling air in the high-temperature region is increased, the heat exchange efficiency is improved, and the discharged cooling air is converged with the outside air, so that certain turbulent flow treatment capacity is achieved.
It is obvious to a person skilled in the art that the invention is not restricted to details of the above-described exemplary embodiments, but that it can be implemented in other specific forms without departing from the spirit or essential characteristics of the invention. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art.
Claims (7)
1. Low pressure guide blade based on vibration material disk, including cup jointing outer fringe section of thick bamboo (1) and inner edge section of thick bamboo (11) together, even integrated into one piece has outer blade shell (2) and inner blade shell (6) between outer fringe section of thick bamboo (1) and the inner edge section of thick bamboo (11), and inner blade shell (6) are located the inboard of outer blade shell (2), its characterized in that, the both ends of inner blade shell (6) inner chamber run through outer fringe section of thick bamboo (1) and inner edge section of thick bamboo (11) respectively, the inner chamber grafting of inner blade shell (6) is equipped with central body (10), central body (10) and outer fringe section of thick bamboo (1) keep away from one side parallel and level of inner edge section of thick bamboo (11), central body (10) head side and the distance between inner blade shell (6) inner chamber are greater than central body (10) tail side and the distance between inner blade shell (6) inner chamber, the distance between the basin side of the central body (10) and the inner cavity of the inner blade shell (6) is larger than the distance between the back side of the central body (10) and the inner cavity of the inner blade shell (6), a support rod (9) is fixedly installed between the central body (10) and the inner blade shell (6), and the support rods (9) are arranged in a staggered mode.
2. The low-pressure guide vane based on additive manufacturing according to claim 1, characterized in that the back side, the basin side and the head side of the inner vane shell (6) are evenly provided with the air film holes (4), the number of the air film holes (4) on the basin side of the inner vane shell (6) is more than that of the air film holes (4) on the back side of the inner vane shell (6), and the diameter of the air film holes (4) on the head side to the tail side of the inner vane shell (6) is gradually reduced.
3. The additive manufacturing based low pressure guide vane according to claim 2, characterized in that the cross section of the film hole (4) is a trumpet-shaped structure, and the opening diameter of the film hole (4) close to the outer vane shell (2) is larger than the opening diameter of the film hole (4) close to the center body (10).
4. The low-pressure guide vane based on additive manufacturing according to claim 1, wherein the back side and the basin side of the outer vane shell (2) are uniformly provided with the partial splitting slits (3), the number of the partial splitting slits (3) on the basin side of the outer vane shell (2) is greater than that of the partial splitting slits (3) on the back side of the outer vane shell (2), and the distance between the partial splitting slits (3) is gradually increased from the head side to the tail side of the outer vane shell (2).
5. The additive manufacturing based low pressure guide vane of claim 4, wherein the split slit (3) is inclined from inside to outside towards the trailing side of the outer vane shell (2).
6. The low-pressure guide vane based on additive manufacturing according to claim 1, characterized in that a flow deflector (5) is uniformly integrated between the outer vane shell (2) and the inner vane shell (6).
7. The low-pressure guide vane based on additive manufacturing is characterized in that the tail side of the outer vane shell (2) is uniformly provided with a guide outlet (8), the tail side of the inner cavity of the outer vane shell (2) is integrally formed with flow disturbing columns (7), and the flow disturbing columns (7) are arranged in a staggered mode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121293966.0U CN215109041U (en) | 2021-06-10 | 2021-06-10 | Low pressure guide vane based on additive manufacturing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121293966.0U CN215109041U (en) | 2021-06-10 | 2021-06-10 | Low pressure guide vane based on additive manufacturing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215109041U true CN215109041U (en) | 2021-12-10 |
Family
ID=79305566
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202121293966.0U Active CN215109041U (en) | 2021-06-10 | 2021-06-10 | Low pressure guide vane based on additive manufacturing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN215109041U (en) |
-
2021
- 2021-06-10 CN CN202121293966.0U patent/CN215109041U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110030036B (en) | Impact split-joint air film cooling structure of turbine blade tail edge | |
| CN110410158B (en) | Turbine rotor blade of gas turbine | |
| CN113090335A (en) | Impact air-entraining film double-wall cooling structure for turbine rotor blade | |
| JPH1089006A (en) | Cooling type blade | |
| CN205382958U (en) | Turbine blade and aeroengine | |
| CN111706409B (en) | Corrugated air film hole with branch hole | |
| CN110206591A (en) | A kind of groove-type cooling air guiding device for turbine rotor blade gas supply | |
| CN215109041U (en) | Low pressure guide vane based on additive manufacturing | |
| CN114109514B (en) | Turbine blade pressure surface cooling structure | |
| CN114109515B (en) | Turbine blade suction side cooling structure | |
| CN201474728U (en) | Turbo cooling blade | |
| CN113550794A (en) | Multi-cavity efficient cooling structure and cooling method for turbine rotor blade | |
| CN111425261A (en) | Turbine blade cooling structure suitable for integrated printing and forming and engine | |
| CN216788487U (en) | Air film hole turbine blade with flow guide structure | |
| WO2020199370A1 (en) | Aero-engine turbine blade having cooling structure | |
| CN114017131B (en) | Variable geometry low pressure turbine guide vane half-layer plate cooling structure | |
| CN113944515B (en) | Turbine blade with front edge split cooling | |
| CN109736898A (en) | A kind of blade inlet edge gaseous film control pore structure of staggeredly compound angle | |
| CN211008774U (en) | Novel turbine blade rotational flow cooling structure | |
| CN112780354B (en) | Tail edge crack-splitting cooling structure and method suitable for turbine blade and turbine blade | |
| CN208619175U (en) | A kind of anticorrosive high-strength titanium alloy blade of aviation engine | |
| CN113586482A (en) | Multi-wing centrifugal fan | |
| CN112922676A (en) | Internal back basin rotary cooling channel of turbine blade | |
| CN114592922B (en) | Double-wall cooling and air film cooling combined turbine blade | |
| CN220226985U (en) | Blade for gas turbine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |