CN112032109A - Blade - Google Patents
Blade Download PDFInfo
- Publication number
- CN112032109A CN112032109A CN202010969857.XA CN202010969857A CN112032109A CN 112032109 A CN112032109 A CN 112032109A CN 202010969857 A CN202010969857 A CN 202010969857A CN 112032109 A CN112032109 A CN 112032109A
- Authority
- CN
- China
- Prior art keywords
- blade
- butt joint
- cavity
- damping
- wall surface
- 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
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
- F04D29/544—Blade shapes
-
- 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
- F01D25/06—Antivibration arrangements for preventing blade vibration
-
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/668—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical vibrations
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The present application relates to a blade having a cavity therein and comprising: and the damping blocks are arranged in the cavity. It can be understood that above-mentioned blade is a hollow blade, and when taking place the vibration, set up each damping piece in its cavity and can take place the vibration thereupon, but the vibration of each damping piece dissipation a large amount of energy to can reduce the vibration of blade, with this reduce the possibility that has the welding seam to initiate the crackle on the blade, avoid the blade to damage.
Description
Technical Field
The application belongs to the technical field of structural design of engine guide vanes, and particularly relates to a vane.
Background
The guide vanes of the fan engine with small bypass ratio are designed to be hollow structures so as to meet the requirement of weight reduction of the engine.
At present, hollow guide vane is mostly welded structure, has many places welding seam, and at engine during operation, receives the hollow guide vane of multiple load effect and can take place violent vibration, and crack takes place to damage easily in its welding seam department.
The present application has been made in view of the above-mentioned technical drawbacks.
It should be noted that the above background disclosure is only for the purpose of assisting understanding of the inventive concept and technical solutions of the present invention, and does not necessarily belong to the prior art of the present patent application, and the above background disclosure should not be used for evaluating the novelty and inventive step of the present application without explicit evidence to suggest that the above content is already disclosed at the filing date of the present patent application.
Disclosure of Invention
It is an object of the present application to provide a blade to overcome or mitigate at least one aspect of the technical disadvantages known to exist.
The technical scheme of the application is as follows:
a blade having a cavity therein, and comprising:
and the damping blocks are arranged in the cavity.
According to at least one embodiment of the present application, in the blade, the cavity wall surface has a plurality of damping grooves;
each damping block is correspondingly arranged in one damping groove and is in clearance fit with the corresponding damping groove.
According to at least one embodiment of the present application, in the above-mentioned blade, the intersection of each damping slot wall surface and the inner cavity wall surface is in smooth transition with a small fillet.
According to at least one embodiment of the present application, in the above-described blade, the damping mass has a spherical or ellipsoidal shape.
According to at least one embodiment of the present application, in the blade, the damping mass is a hollow structure.
According to at least one embodiment of the present application, the blade further includes:
a first butt joint member having a first butt joint surface; the first butt joint surface is provided with a first annular butt joint part;
a second butt joint piece having a second butt joint surface; the second butt joint surface is provided with a second annular butt joint part; the first annular butt joint part and the second annular butt joint part are in butt joint to form a blade; a cavity is formed between the first butt joint piece and the second butt joint piece; the first annular butt joint portion and the second annular butt joint portion surround the cavity.
According to at least one embodiment of the present application, in the blade described above, the first annular butt portion and the second annular butt portion are diffusion welded.
According to at least one embodiment of the present application, in the blade, the first butt piece outer side wall surface and the first cavity wall surface are designed to have an equal thickness;
the outer side wall surface of the second butt joint piece and the wall surface of the second cavity are designed to be equal in thickness.
According to at least one embodiment of the present application, in the above vane, the first abutting surface has a first cavity thereon;
the second butt joint surface is provided with a second cavity; a cavity is formed between the first concave cavity and the second concave cavity.
According to at least one embodiment of the present application, in the blade, the first cavity wall surface has a plurality of first damping grooves;
the wall surface of the second concave cavity is provided with a plurality of second damping grooves;
each damping block corresponds to one first damping groove and one second damping groove, part of the damping block sinks into the corresponding first damping groove, and part of the damping block sinks into the corresponding second damping groove and is in clearance fit with the corresponding first damping groove and the corresponding second damping groove.
Drawings
FIG. 1 is a cross-sectional view of a bucket provided by an embodiment of the present application;
FIG. 2 is a schematic diagram of a spherical damping block provided in an embodiment of the present application;
FIG. 3 is a schematic diagram of an ellipsoidal damping block provided in an embodiment of the present application;
FIG. 4 is a schematic diagram of a hollow damping block provided in an embodiment of the present application;
FIG. 5 is a schematic view of a first docking member provided in accordance with an embodiment of the present application;
FIG. 6 is a schematic view of a second docking member provided in accordance with an embodiment of the present application;
wherein:
1-a damping block; 2-a first docking member; 3-second docking piece.
For the purpose of better illustrating the embodiments, certain features of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; further, the drawings are for illustrative purposes, and terms describing positional relationships are limited to illustrative illustrations only and are not to be construed as limiting the patent.
Detailed Description
In order to make the technical solutions and advantages of the present application clearer, the technical solutions of the present application will be further clearly and completely described in the following detailed description with reference to the accompanying drawings, and it should be understood that the specific embodiments described herein are only some of the embodiments of the present application, and are only used for explaining the present application, but not limiting the present application. It should be noted that, for convenience of description, only the parts related to the present application are shown in the drawings, other related parts may refer to general designs, and the embodiments and technical features in the embodiments in the present application may be combined with each other to obtain a new embodiment without conflict.
In addition, unless otherwise defined, technical or scientific terms used in the description of the present application shall have the ordinary meaning as understood by one of ordinary skill in the art to which the present application belongs. The terms "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", and the like used in the description of the present application, which indicate orientations, are used only to indicate relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and when the absolute position of the object to be described is changed, the relative positional relationships may be changed accordingly, and thus, should not be construed as limiting the present application. The use of "first," "second," "third," and the like in the description of the present application is for descriptive purposes only to distinguish between different components and is not to be construed as indicating or implying relative importance. The use of the terms "a," "an," or "the" and similar referents in the context of describing the application is not to be construed as an absolute limitation on the number, but rather as the presence of at least one. The use of the terms "comprising" or "including" and the like in the description of the present application is intended to indicate that the element or item preceding the term covers the element or item listed after the term and its equivalents, without excluding other elements or items.
Further, it is noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and the like are used in the description of the invention in a generic sense, e.g., connected as either a fixed connection or a removable connection or integrally connected; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected through the inside of two elements, and those skilled in the art can understand their specific meaning in this application according to the specific situation.
The present application is described in further detail below with reference to fig. 1 to 6.
A blade having a cavity therein, and comprising:
and a plurality of damping blocks 1 arranged in the cavity.
For the blades disclosed in the above embodiments, it will be understood by those skilled in the art that the hollow blade has a cavity therein, and the shape of the hollow blade can be designed accordingly, so that the shape of the hollow blade is matched with the shape of the hollow guide blade on the fan engine with small bypass ratio, so as to be able to be used as a hollow guide blade in the engine with small bypass ratio.
For the blade disclosed in the above embodiment, as can be further understood by those skilled in the art, when the blade is loaded and vibrates, each damping block 1 in the cavity vibrates therewith, and the vibration of each damping block 1 can dissipate a large amount of energy, so that the vibration of the blade can be reduced, the possibility of cracks on the welding seam on the blade can be reduced, and the blade can be prevented from being damaged.
In some alternative embodiments, in the above blade, the cavity wall surface has a plurality of damping grooves;
each damping block 1 is correspondingly arranged in one damping groove and is in clearance fit with the corresponding damping groove.
For the blade disclosed in the above embodiment, as can be understood by those skilled in the art, each damping block 1 is correspondingly arranged in a plurality of damping grooves on the wall surface of the cavity of the blade, so that on one hand, the contact area between each damping block 1 and the wall surface of the cavity of the blade can be increased, thereby reducing the impact of vibration of each damping block 1 on the wall surface of the cavity of the blade and preventing the wall surface of the cavity of the blade from being damaged; on the other hand, each damping block 1 can be limited in the corresponding damping groove, so that the damping blocks 1 are prevented from colliding with each other and being damaged when vibrating, and the capability of reducing the vibration effect of the blade is weakened.
In some optional embodiments, in the above-mentioned blade, the intersection of the wall surface of each damping slot and the wall surface of the inner cavity has a small round angle smooth transition, so as to avoid tip stress concentration at the intersection during the vibration process of the damping block 1, which may cause damage.
In some alternative embodiments, in the above-described blade, the damping mass 1 is spherical or ellipsoidal.
In some alternative embodiments, in the above-mentioned blade, the damping mass 1 is a hollow structure.
For the blade disclosed in the above embodiment, as can be understood by those skilled in the art, each damping block 1 is a hollow structure, so that on one hand, the vibration effect of the damping block 1 can be enhanced, the dissipation of energy is increased, and the vibration of the blade is effectively reduced; on the other hand, the mass of the blade can be reduced, so that the overall mass of the blade can be reduced, and the current weight reduction requirement can be met.
In some optional embodiments, the blade further includes:
a first butt piece 2 having a first butt surface; the first butt joint surface is provided with a first annular butt joint part;
a second butt joint member 3 having a second butt joint surface; the second butt joint surface is provided with a second annular butt joint part; the first annular butt joint part and the second annular butt joint part are in butt joint to form a blade; a cavity is arranged between the first butt joint piece 2 and the second butt joint piece 3; the first annular butt joint portion and the second annular butt joint portion surround the cavity.
For the blade disclosed in the above embodiments, it can be understood by those skilled in the art that the blade body is formed by butting a first butting part 2 and a second butting part 3, and a first annular butting part on the first butting part 1 and a second annular butting part on the second butting part 3 are butted to form the blade, which means that after the first annular butting part on the first butting part 2 and the second annular butting part on the second butting part 3 are butted, the first butting part 2 and the second butting part 3 form a whole, and the shape of the whole conforms to the shape of the blade, specifically, the shape of the whole conforms to the shape of a hollow guide blade on a fan engine with a small bypass ratio.
In some alternative embodiments, the first annular butt region and the second annular butt region are diffusion welded to each other in the blade.
In some optional embodiments, in the above-mentioned blade, the outer side wall surface of the first butt piece 2 and the first cavity wall surface are designed to have an equal thickness, so as to ensure the strength of the first butt piece 2;
the outer side wall surface of the second butt joint piece 3 and the wall surface of the second cavity are designed to be equal in thickness, so that the strength of the second butt joint piece 3 is guaranteed.
In some alternative embodiments, the blade has a first cavity on the first mating surface;
the second butt joint surface is provided with a second cavity; a cavity is formed between the first concave cavity and the second concave cavity.
In some alternative embodiments, in the above vane, the first cavity wall has a plurality of first damping grooves;
the wall surface of the second concave cavity is provided with a plurality of second damping grooves;
each damping block 1 corresponds to a first damping groove and a second damping groove, part of the damping block sinks into the corresponding first damping groove, part of the damping block sinks into the corresponding second damping groove, and the damping block is in clearance fit with the corresponding first damping groove and the corresponding second damping groove, namely, each damping groove can comprise a first damping groove and a second damping groove.
The embodiments are described in a progressive manner in the specification, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
Having thus described the present application in connection with the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present application is not limited to those specific embodiments, and that equivalent modifications or substitutions of related technical features may be made by those skilled in the art without departing from the principle of the present application, and those modifications or substitutions will fall within the scope of the present application.
Claims (10)
1. A blade having a cavity therein, comprising:
a plurality of damping masses (1) arranged within the cavity.
2. The blade of claim 1,
the wall surface of the cavity is provided with a plurality of damping grooves;
each damping block (1) is correspondingly arranged in one damping groove and is in clearance fit with the corresponding damping groove.
3. The blade of claim 2,
and the intersection part of the wall surface of each damping groove and the wall surface of the inner cavity is in small round angle smooth transition.
4. The blade of claim 1,
the damping block (1) is spherical or ellipsoidal.
5. The blade of claim 1,
the damping block (1) is of a hollow structure.
6. The blade of claim 1,
further comprising:
a first butt joint member (2) having a first butt joint surface; the first butt joint surface is provided with a first annular butt joint part;
a second butt joint member (3) having a second butt joint surface; the second butt joint surface is provided with a second annular butt joint part; the first annular butt joint part and the second annular butt joint part are in butt joint to form a blade; the cavity is formed between the first butt joint piece (2) and the second butt joint piece (3); the first annular docking station and the second annular docking station encircle the cavity.
7. The blade of claim 6,
and the first annular butt joint part and the second annular butt joint part are connected by diffusion welding.
8. The blade of claim 6,
the outer side wall surface of the first butt joint piece (2) and the wall surface of the first cavity adopt an equal-thickness design;
the outer side wall surface of the second butt joint piece (3) and the wall surface of the second cavity are designed to be equal in thickness.
9. The blade of claim 6,
the first butt joint surface is provided with a first cavity;
the second butt joint surface is provided with a second cavity; the cavity is formed between the first cavity and the second cavity.
10. The blade of claim 9,
the first cavity wall surface is provided with a plurality of first damping grooves;
the second cavity wall surface is provided with a plurality of second damping grooves;
each damping block (1) corresponds to one first damping groove and one second damping groove, part of the damping blocks sinks into the corresponding first damping groove, and part of the damping blocks sinks into the corresponding second damping groove and is in clearance fit with the corresponding first damping groove and the corresponding second damping groove.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010969857.XA CN112032109A (en) | 2020-09-15 | 2020-09-15 | Blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010969857.XA CN112032109A (en) | 2020-09-15 | 2020-09-15 | Blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112032109A true CN112032109A (en) | 2020-12-04 |
Family
ID=73589426
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010969857.XA Pending CN112032109A (en) | 2020-09-15 | 2020-09-15 | Blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112032109A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112648137A (en) * | 2021-01-19 | 2021-04-13 | 兰州理工大学 | Wind power blade multi-particle series speed amplification type vibration reduction device and connection method |
Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB893787A (en) * | 1959-07-03 | 1962-04-11 | United Aircraft Corp | Improvements relating to damped bodies and methods of manufacturing them |
| GB2418460A (en) * | 2004-09-22 | 2006-03-29 | Rolls Royce Plc | Aerofoil with low density |
| US20070128042A1 (en) * | 2005-12-06 | 2007-06-07 | United Technologies Corporation | Hollow fan blade for gas turbine engine |
| EP2418354A1 (en) * | 2010-08-10 | 2012-02-15 | Siemens Aktiengesellschaft | Method for producing an internally cooled turbine blade and gas turbine with a turbine blade produced according to the method |
| CN202468447U (en) * | 2011-11-25 | 2012-10-03 | 中国航空工业集团公司沈阳发动机设计研究所 | Adsorption type hollow stator blade adopting T-shaped groove structure |
| CN103089317A (en) * | 2011-10-31 | 2013-05-08 | 中航商用航空发动机有限责任公司 | Hollow fan blade and manufacturing method thereof |
| CN103089323A (en) * | 2011-10-31 | 2013-05-08 | 中航商用航空发动机有限责任公司 | Hollow fan blade and manufacturing method thereof |
| CN107152313A (en) * | 2017-06-13 | 2017-09-12 | 西安交通大学 | A kind of steam turbine last stage hollow blade based on 3d printings and preparation method thereof |
| RU2667220C1 (en) * | 2017-10-24 | 2018-09-17 | Николай Борисович Болотин | Fan blade of gas turbine engine |
| CN109058157A (en) * | 2018-08-16 | 2018-12-21 | 泛仕达机电股份有限公司 | A kind of centrifugal impeller and its hollow blade |
| CN109210000A (en) * | 2017-06-30 | 2019-01-15 | 中国航发商用航空发动机有限责任公司 | Aero-engine and its fan blade |
| CN211116138U (en) * | 2019-11-18 | 2020-07-28 | 刘志龙 | Novel hollow blade of aero-engine |
-
2020
- 2020-09-15 CN CN202010969857.XA patent/CN112032109A/en active Pending
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB893787A (en) * | 1959-07-03 | 1962-04-11 | United Aircraft Corp | Improvements relating to damped bodies and methods of manufacturing them |
| GB2418460A (en) * | 2004-09-22 | 2006-03-29 | Rolls Royce Plc | Aerofoil with low density |
| US20070128042A1 (en) * | 2005-12-06 | 2007-06-07 | United Technologies Corporation | Hollow fan blade for gas turbine engine |
| EP2418354A1 (en) * | 2010-08-10 | 2012-02-15 | Siemens Aktiengesellschaft | Method for producing an internally cooled turbine blade and gas turbine with a turbine blade produced according to the method |
| CN103089317A (en) * | 2011-10-31 | 2013-05-08 | 中航商用航空发动机有限责任公司 | Hollow fan blade and manufacturing method thereof |
| CN103089323A (en) * | 2011-10-31 | 2013-05-08 | 中航商用航空发动机有限责任公司 | Hollow fan blade and manufacturing method thereof |
| CN202468447U (en) * | 2011-11-25 | 2012-10-03 | 中国航空工业集团公司沈阳发动机设计研究所 | Adsorption type hollow stator blade adopting T-shaped groove structure |
| CN107152313A (en) * | 2017-06-13 | 2017-09-12 | 西安交通大学 | A kind of steam turbine last stage hollow blade based on 3d printings and preparation method thereof |
| CN109210000A (en) * | 2017-06-30 | 2019-01-15 | 中国航发商用航空发动机有限责任公司 | Aero-engine and its fan blade |
| RU2667220C1 (en) * | 2017-10-24 | 2018-09-17 | Николай Борисович Болотин | Fan blade of gas turbine engine |
| CN109058157A (en) * | 2018-08-16 | 2018-12-21 | 泛仕达机电股份有限公司 | A kind of centrifugal impeller and its hollow blade |
| CN211116138U (en) * | 2019-11-18 | 2020-07-28 | 刘志龙 | Novel hollow blade of aero-engine |
Non-Patent Citations (2)
| Title |
|---|
| 宋金虎: "《液压与气动技术》", 31 August 2016, 北京理工大学出版社 * |
| 谢苗: "《液压元件设计》", 31 July 2017, 煤炭工业出版社 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112648137A (en) * | 2021-01-19 | 2021-04-13 | 兰州理工大学 | Wind power blade multi-particle series speed amplification type vibration reduction device and connection method |
| CN112648137B (en) * | 2021-01-19 | 2021-12-24 | 兰州理工大学 | Wind power blade multi-particle series speed amplification type vibration reduction device and connection method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP2007198293A (en) | Stationary blade ring for axial flow compressor | |
| US20110204122A1 (en) | Hollow structures formed with friction stir welding | |
| CN112032109A (en) | Blade | |
| EP3597325B1 (en) | Member bonding method and bonded body | |
| EP2149690A3 (en) | Turbine rotor | |
| JP3378145B2 (en) | Manufacturing method of welded structure | |
| EP2236762A3 (en) | Turbine Nozzle Assembly with Mechanical and Weld Fabrication | |
| CN106555776B (en) | Turbofan and its fan blade | |
| JP2006283760A (en) | Rotor for revolving machine, especially for steam turbine | |
| US20140112709A1 (en) | Dissimilar material joint, structure in which dissimilar material joint is used, and method of producing the same | |
| RU169109U1 (en) | Cantilevered spine | |
| JP2010537920A (en) | Contour shape of crane boom | |
| CN210793506U (en) | Strong beam, deck structure and ship | |
| JP2005500458A (en) | Method for producing hollow blade for stationary blade or moving blade component | |
| JP6024602B2 (en) | Rear pillar structure | |
| CN104863821B (en) | Compressor base frame | |
| JP5713628B2 (en) | Frame | |
| CN103890318B (en) | Flowing rotor, particularly turbine wheel | |
| CN105383250B (en) | Twist-beam suspension | |
| JP2003119825A (en) | Handrail of construction machine | |
| JP2004528521A5 (en) | ||
| CN103132556A (en) | Cast support seat | |
| JP6984495B2 (en) | Fillet welded joint and its manufacturing method | |
| CN220782563U (en) | Electron beam welding frame beam structure | |
| JP7398778B2 (en) | Resin molding equipment |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20201204 |