CN114961875A - Pressure side exhaust air cooling turbine movable blade tail edge structure - Google Patents

Pressure side exhaust air cooling turbine movable blade tail edge structure Download PDF

Info

Publication number
CN114961875A
CN114961875A CN202210595179.4A CN202210595179A CN114961875A CN 114961875 A CN114961875 A CN 114961875A CN 202210595179 A CN202210595179 A CN 202210595179A CN 114961875 A CN114961875 A CN 114961875A
Authority
CN
China
Prior art keywords
exhaust
trailing edge
turbine
blade
pressure side
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
Application number
CN202210595179.4A
Other languages
Chinese (zh)
Inventor
牛夕莹
李国强
孙鹏
刘言明
李宗全
毛冬岩
李越
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
703th Research Institute of CSIC
Original Assignee
703th Research Institute of CSIC
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by 703th Research Institute of CSIC filed Critical 703th Research Institute of CSIC
Priority to CN202210595179.4A priority Critical patent/CN114961875A/en
Publication of CN114961875A publication Critical patent/CN114961875A/en
Pending legal-status Critical Current

Links

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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The invention provides a pressure side exhaust air cooling turbine guide vane tail edge structure, and relates to a tail edge structure for discharging cooling air through a pressure side of a turbine rotor blade tail edge. The invention aims to provide a movable blade tail edge exhaust structure which can effectively reduce the thickness of a movable blade tail edge of a turbine, reduce the loss of a trailing trace of the movable blade of the turbine and improve the aerodynamic performance of the movable blade of the turbine. Therefore, the problem of large tail loss of the movable blade in the traditional tail edge middle slit exhaust mode is solved. The invention is used for reducing the wake loss of the turbine moving blade of the gas turbine and improving the aerodynamic performance of the turbine moving blade.

Description

Pressure side exhaust air cooling turbine movable blade tail edge structure
Technical Field
The present invention relates to a pressure side exhaust air cooling turbine blade trailing edge structure, and more particularly, to a trailing edge structure which can effectively reduce a loss of a turbine blade trailing edge and improve a turbine blade aerodynamic performance by discharging cooling air through a turbine blade trailing edge pressure side.
Background
The gas turbine has the advantages of high power density, high starting speed, flexible fuel and the like, is widely applied to the fields of industrial and offshore platform power generation, natural gas transportation, petrochemical industry, metallurgy and the like, and can also be used as a main power device of airplanes, ships and ground vehicles.
In order to achieve higher cycle efficiency and higher power in modern high-performance gas turbines, the initial temperature of the gas (turbine inlet temperature) is continuously increased. With the increasing inlet temperature of the turbine, the operating temperature of the turbine is far higher than the melting point temperature of the blade material, for example, the inlet gas temperature of the turbine of the most advanced gas turbine which is put into operation at present reaches 1600 ℃, and the inlet temperature of the turbine of the advanced aircraft engine is more than 1800 ℃. There are three main measures to ensure that a gas turbine blade can operate safely and reliably for long periods of time in such high temperature environments: firstly, constantly improve the heat-resisting grade of turbine blade material, secondly adopt advanced cooling technology in order to reduce the blade temperature, thirdly constantly improve turbine blade thermal barrier coating's thermal-insulated effect. In recent years, the increase in turbine inlet temperature has been attributed primarily to the increase in turbine cooling design levels, and secondarily to the development of high performance heat resistant alloys and coating materials and advances in manufacturing process levels. It is clear that turbine blade cooling plays a crucial role in increasing turbine inlet temperature and improving gas turbine performance.
In recent years, with the continuous progress of design technology and the continuous development of computational fluid mechanics, a full three-dimensional optimization design means is continuously applied to a turbine cooling design process, a turbine cooling design system, a design means and a method are continuously enriched and perfected, the advanced design technology and a cooling structure continuously promote the increase of the turbine inlet temperature, and the shape of a turbine blade cooling channel is more complicated. In order to meet the requirements of energy conservation and emission reduction, the performance of modern gas turbines is continuously improved, the cooling and pneumatic performance of the turbines are required to be continuously improved, and the service life and the reliability of turbine blades are continuously improved. However, cooling techniques based on conventional turbine blade trailing edge exhaust structures have difficulty in improving turbine blade aerodynamic performance while reducing blade trailing edge temperatures.
Although both scholars and researchers at home and abroad have conducted a great deal of research on efficient cooling and aerodynamic design of turbine blades and have a certain understanding on improving cooling and aerodynamic performance of the turbine blades and revealing the internal cooling flow mechanism of the turbine blade bodies, the research does not pay attention to how to improve blade profile loss of the turbine blades while improving cooling of the turbine blade bodies, and reports on reducing metal temperature of the turbine blade trailing edges and improving aerodynamic performance of the turbine blades through a pressure side exhaust structure of the turbine blade trailing edges are also fresh. Researchers desire an advanced trailing edge design that can both meet cooling requirements and effectively improve the aerodynamic performance of turbine buckets.
Disclosure of Invention
The invention aims to provide a movable blade tail edge exhaust structure which can effectively reduce the thickness of a movable blade tail edge of a turbine, reduce the loss of a trailing trace of the movable blade of the turbine and improve the aerodynamic performance of the movable blade of the turbine. Thereby solving the problem of large tail loss of the movable blade in the traditional tail edge middle slit exhaust mode.
The purpose of the invention is realized as follows: the exhaust grating structure comprises a long exhaust tail edge, a short exhaust tail edge, exhaust connecting ribs and exhaust gratings, wherein a single-side open cooling air exhaust channel is formed between the long exhaust tail edge and the short exhaust tail edge, the single-side open cooling air exhaust channel is divided into individual exhaust gratings by the exhaust connecting ribs uniformly distributed in the height direction of a blade, so that a final turbine movable blade tail edge cooling air exhaust channel is formed, cooling air inside the turbine movable blades is exhausted into the blade grating channel after cooling the movable blade tail edges from the tail edges of the individual exhaust gratings, and the pressure-side exhaust air-cooled turbine movable blade tail edge structure exhaust grating 5 is arranged on the pressure side (blade basin side) of the turbine movable blade.
Furthermore, the long exhaust tail edge, the short exhaust tail edge and the exhaust connecting rib are connected into a whole in sequence.
Furthermore, the long exhaust tail edge is obtained by following the pressure surface profile of the movable blade.
Further, the long exhaust tail edge and the shorter exhaust tail edge extend to the pressure side (the blade basin side) within 5 mm.
Further, the included angle (A) between the long exhaust tail edge and the short exhaust tail edge is within 15 degrees.
Further, the trailing edge radius of the long exhaust trailing edge is 0.5 mm.
Further, the trailing edge radius of the short exhaust trailing edge is 0.4 mm.
Compared with the prior art, the invention has the beneficial effects that: compared with the traditional exhaust structure form of the split seam in the middle of the tail edge of the turbine movable blade, the exhaust structure form of the pressure side can reduce the thickness of the tail edge of the turbine movable blade, thereby reducing the blade profile loss of the turbine movable blade, improving the aerodynamic performance of the turbine movable blade, improving the efficiency of the turbine and the whole machine set and reducing the energy consumption.
By adopting the turbine movable blade, compared with the middle split joint tail edge exhaust structure, the trailing loss is reduced by 50% under the condition that the temperature of the tail edge of the movable blade is not changed on the premise that the flow rate of cooling air at the tail edge of the movable blade is the same.
Drawings
FIG. 1 is a schematic view of a turbine bucket trailing edge exhaust configuration of the present invention;
FIG. 2 is a schematic cross-sectional view of a turbine bucket trailing edge exhaust configuration of the present invention;
FIG. 3 is a schematic view of a turbine cascade channel with a turbine bucket trailing edge bleed structure of the present invention;
FIG. 4 is a schematic view of the size and angle of the turbine bucket trailing edge exhaust structure of the present invention;
FIG. 5 is a schematic view of a conventional turbine bucket trailing edge middle slot exhaust structure.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
The first embodiment is as follows: the present embodiment is described with reference to fig. 1 to 3, and the pressure side exhaust air-cooled turbine rotor blade trailing edge structure of the present embodiment includes a long exhaust trailing edge 1, a short exhaust trailing edge 2, and an exhaust connecting rib 3, wherein a cooling air exhaust passage 4 with one side open is formed between the long exhaust trailing edge 1 and the short exhaust trailing edge 2, the cooling air exhaust passage 4 with one side open is divided into exhaust grilles 5 by the exhaust connecting rib 3 uniformly distributed in the blade height direction, and a final turbine rotor blade trailing edge cooling air exhaust passage 6 is formed, cooling air inside the turbine rotor blade is discharged from the exhaust grilles 5, and the cooling rotor blade short exhaust trailing edge 2, the exhaust connecting rib 3, and the long exhaust trailing edge 1 are discharged into the blade grille passage.
The second embodiment is as follows: the present embodiment will be described with reference to fig. 1, and the long exhaust trailing edge 1, the short exhaust trailing edge 2, and the exhaust bead 3 of the present embodiment are integrally connected in this order. So set up, compare conventional turbine movable vane trailing edge structure, can strengthen the connection between the long exhaust trailing edge 1 of movable vane and the short exhaust trailing edge 2, form a body structure, improve turbine movable vane trailing edge stress state to reinforcing turbine movable vane intensity improves the reliability and the life-span of turbine movable vane.
Other components and connections are the same as in the first embodiment.
The third concrete implementation mode: the present embodiment will be described with reference to fig. 2 to 5, and the long exhaust trailing edge 1 of the present embodiment is obtained by following the rotor blade pressure surface profile 7. So set up, movable vane blade molded lines can realize more smooth transition between short exhaust trailing edge 2 and long exhaust trailing edge 1, avoids appearing the structure of similar step abrupt transition, on the one hand, can reduce because the step appears and lead to flowing smoothly, the loss of blade profile flow increases, and on the other hand is favorable to improving the wave system structure of trailing edge annex, reduces the shock wave loss to comprehensively reduce blade profile and flow loss.
Other compositions and connections are the same as in the first or second embodiments.
The fourth concrete implementation mode: the present embodiment will be described with reference to fig. 2 to 5, in which the long trailing edge 1 and the short trailing edge 2 of the present embodiment have a protrusion length (L) of 5mm or less on the blade back side. So set up, the short exhaust trailing edge 2 extension length of long exhaust trailing edge 1 is less to can reduce the heating area, thereby reduce near turbine movable vane trailing edge metal temperature, improve turbine movable vane blade life-span. Compared with the traditional exhaust structure form of the split seam in the middle of the tail edge of the turbine movable blade, the exhaust structure form of the pressure side can reduce the thickness of the tail edge of the turbine movable blade, thereby reducing the blade profile loss of the turbine movable blade, improving the aerodynamic performance of the turbine movable blade, improving the efficiency of the turbine and the whole machine set and reducing the energy consumption.
Other compositions and connection relationships are the same as in the first, second or third embodiment.
The fifth concrete implementation mode: the present embodiment will be described with reference to fig. 2 to 5, and the angle (a) between the long exhaust trailing edge 1 and the short exhaust trailing edge 2 of the present embodiment is within 15 degrees. So set up, can make smooth-going transition between short exhaust trailing edge 2 and the long exhaust trailing edge 1, avoid because the angle is too big to lead to appearing the step behind the short exhaust trailing edge 2 and arouse great wake loss, be favorable to reducing the thickness of long exhaust trailing edge 1, compare the middle crack exhaust structure form of cleft of traditional turbine movable vane trailing edge, the loss of turbine movable vane type reduces, and turbine movable vane aerodynamic performance obtains improving.
Other compositions and connection relationships are the same as those in the first, second, third or fourth embodiment.
The sixth specific implementation mode: the present embodiment will be described with reference to fig. 2 and 3, and the long exhaust trailing edge 1 of the present embodiment has a trailing edge radius of 0.5 mm. Compared with the blade profile of the traditional turbine movable blade tail edge middle slit exhaust structure, the blade tail edge radius is reduced, the ratio of the tail edge thickness to the chord length is reduced by more than 50%, the width of the blade tail trace is narrowed, the flow loss of the blade profile is reduced, and the turbine aerodynamic efficiency is improved.
Other compositions and connection relationships are the same as in the first, second, third, fourth or fifth embodiment.
The seventh embodiment: the present embodiment will be described with reference to fig. 2 and 3, and the trailing edge radius of the short exhaust trailing edge 2 of the present embodiment is 0.4 mm. So set up, reduced near short exhaust trailing edge 2 blade profile wake loss, on the other hand is favorable to short exhaust trailing edge 2 and long exhaust trailing edge 1 smooth-going transition and shortens the extension length, reduces contained angle (A) to improve turbine movable vane aerodynamic performance.
Other compositions and connection relationships are the same as in the first, second, third, fourth, fifth or sixth embodiment.
The working principle is illustrated by figures 1-4:
the turbine movable blade tail edge cooling air exhaust device comprises a long exhaust tail edge 1, a short exhaust tail edge 2 and an exhaust connecting rib 3, wherein a cooling air exhaust channel 4 with an open single side is formed between the long exhaust tail edge 1 and the short exhaust tail edge 2, the cooling air exhaust channel 4 with the open single side is divided into exhaust grids 5 by the exhaust connecting rib 3 uniformly distributed in the blade height direction, a final turbine movable blade tail edge cooling air exhaust channel 6 is formed, cooling air inside a turbine movable blade is exhausted from the exhaust grids 5, and the cooling movable blade short exhaust tail edge 2, the exhaust connecting rib 3 and the long exhaust tail edge 1 are exhausted into the grid channels. After the tail edge structure of the air-cooled turbine movable vane exhausting at the pressure side is adopted, on one hand, the connection between the long exhaust tail edge 1 and the short exhaust tail edge 2 of the movable vane is strengthened through the exhaust connecting rib 3 to form an integral structure, and the stress state of the tail edge of the turbine movable vane is improved, so that the strength of the turbine movable vane is enhanced, and the reliability and the service life of the turbine movable vane are improved; on the other hand, compare the middle crack exhaust structural style that splits of traditional turbine movable vane tail edge, the pressure side exhaust can reduce turbine movable vane tail edge thickness to reduce turbine movable vane blade profile loss, improve turbine movable vane aerodynamic performance, improve turbine and complete machine unit efficiency, reduce energy consumption.
In summary, the present invention relates to a pressure-side exhaust air-cooled turbine vane trailing edge structure, and more particularly, to a trailing edge structure for discharging cooling air through a turbine bucket trailing edge pressure side. The invention aims to provide a movable blade tail edge exhaust structure which can effectively reduce the thickness of a movable blade tail edge of a turbine, reduce the loss of a trailing trace of the movable blade of the turbine and improve the aerodynamic performance of the movable blade of the turbine. Therefore, the problem of large tail loss of the movable blade in the traditional tail edge middle slit exhaust mode is solved. The invention is used for reducing the wake loss of the turbine moving blade of the gas turbine and improving the aerodynamic performance of the turbine moving blade.

Claims (7)

1. The utility model provides a pressure side exhaust's air-cooled turbine movable vane trailing edge structure which characterized in that: including long exhaust trailing edge, short exhaust trailing edge and exhaust splice bar, form the open cooling air exhaust passage of unilateral between long exhaust trailing edge and the short exhaust trailing edge, the open cooling air exhaust passage of unilateral is split into exhaust grille one by one along blade height direction evenly distributed's exhaust splice bar, and exhaust grille arranges at turbine movable vane blade pressure side, and then forms ultimate turbine movable vane trailing edge cooling air exhaust passage, and the inside cooling air of turbine movable vane discharges from exhaust grille one by one from the trailing edge, discharges into the cascade passageway behind cooling movable vane short exhaust trailing edge, exhaust splice bar and long exhaust trailing edge.
2. The pressure side exhaust air cooled turbine bucket trailing edge structure of claim 1, wherein: the long exhaust tail edge and the short exhaust tail edge are connected into a whole through an exhaust connecting rib.
3. The pressure side exhaust air cooled turbine bucket trailing edge structure of claim 2, wherein: the long exhaust tail edge is obtained by extending along the molded line of the pressure surface of the movable vane blade.
4. The pressure side exhaust air cooled turbine bucket trailing edge structure of claim 3, wherein: the length of the long exhaust tail edge and the shorter exhaust tail edge extending to the back side of the blade is within 5 mm.
5. The pressure side exhaust air cooled turbine bucket trailing edge structure of claim 4, wherein: the included angle between the long exhaust tail edge and the short exhaust tail edge is within 15 degrees.
6. The pressure side exhaust air cooled turbine bucket trailing edge structure of claim 5, wherein: the tail edge radius of the long exhaust tail edge is 05 mm.
7. The pressure side exhaust air cooled turbine bucket trailing edge structure of claim 6, wherein: the trailing edge radius of the short exhaust trailing edge is 0.4 mm.
CN202210595179.4A 2022-05-29 2022-05-29 Pressure side exhaust air cooling turbine movable blade tail edge structure Pending CN114961875A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202210595179.4A CN114961875A (en) 2022-05-29 2022-05-29 Pressure side exhaust air cooling turbine movable blade tail edge structure

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202210595179.4A CN114961875A (en) 2022-05-29 2022-05-29 Pressure side exhaust air cooling turbine movable blade tail edge structure

Publications (1)

Publication Number Publication Date
CN114961875A true CN114961875A (en) 2022-08-30

Family

ID=82971637

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202210595179.4A Pending CN114961875A (en) 2022-05-29 2022-05-29 Pressure side exhaust air cooling turbine movable blade tail edge structure

Country Status (1)

Country Link
CN (1) CN114961875A (en)

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6318963B1 (en) * 1999-06-09 2001-11-20 Rolls-Royce Plc Gas turbine airfoil internal air system
US7862299B1 (en) * 2007-03-21 2011-01-04 Florida Turbine Technologies, Inc. Two piece hollow turbine blade with serpentine cooling circuits
EP2980357A1 (en) * 2014-08-01 2016-02-03 Siemens Aktiengesellschaft Gas turbine aerofoil trailing edge
CN105569740A (en) * 2016-03-03 2016-05-11 哈尔滨工程大学 Turbine with blade wavy concave tailing edge slot cooling structures
CN107035421A (en) * 2017-06-01 2017-08-11 西北工业大学 A kind of turbine blade tail flow-disturbing with array pin rib partly splits seam cooling structure
CN110925027A (en) * 2019-11-29 2020-03-27 大连理工大学 Turbine blade trailing edge tapered inclined exhaust split structure

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6318963B1 (en) * 1999-06-09 2001-11-20 Rolls-Royce Plc Gas turbine airfoil internal air system
US7862299B1 (en) * 2007-03-21 2011-01-04 Florida Turbine Technologies, Inc. Two piece hollow turbine blade with serpentine cooling circuits
EP2980357A1 (en) * 2014-08-01 2016-02-03 Siemens Aktiengesellschaft Gas turbine aerofoil trailing edge
CN105569740A (en) * 2016-03-03 2016-05-11 哈尔滨工程大学 Turbine with blade wavy concave tailing edge slot cooling structures
CN107035421A (en) * 2017-06-01 2017-08-11 西北工业大学 A kind of turbine blade tail flow-disturbing with array pin rib partly splits seam cooling structure
CN110925027A (en) * 2019-11-29 2020-03-27 大连理工大学 Turbine blade trailing edge tapered inclined exhaust split structure

Similar Documents

Publication Publication Date Title
CA2548168C (en) Turbine airfoil with variable and compound fillet
CN101915130A (en) Three-dimensional nozzle ring vane of variable geometry turbocharger and design method thereof
CN111734577B (en) Slit type wind turbine blade device and slit method
CN114718659B (en) Turbine blade tip clearance flow control method coupling radial ribs and circumferential grooves
CN112974734B (en) Manufacturing method of integrally formed swept combined blade
CN109578085B (en) Method for weakening unsteady acting force of turbine movable blade through guide blade inclination
CN102434223B (en) Low-pressure stage final blade of large-flow air-cooled steam turbine
CN115126547B (en) Air-cooled turbine movable blade trailing edge structure for suction side exhaust
CN112177680B (en) High-pressure turbine blade structure with resistance-reducing pit array
CN114961875A (en) Pressure side exhaust air cooling turbine movable blade tail edge structure
CN115059518B (en) Air-cooled turbine guide vane trailing edge structure of suction side exhaust
CN111577531A (en) Shark gill type blade drag reduction structure for wind driven generator, blade and manufacturing method
CN115075891A (en) Air-cooled turbine guide vane trailing edge structure with pressure side exhaust
CN102182519A (en) Self-jet flow secondary flow control structure of turbine stator vane
CN115098958B (en) Air-cooled turbine guide vane modeling method for exhausting air at suction side
CN115169022B (en) Method for molding air-cooled turbine movable blade exhausted from pressure side
CN115203833B (en) Air-cooled turbine movable blade modeling method for suction side exhaust
CN115130234B (en) Air-cooled turbine guide vane modeling method for pressure side exhaust
CN103557034B (en) Second stage guide vane applicable to turbine of heavy low calorific value fuel machine
CN109101722B (en) Composite forming design method for turbine blade
CN109117552B (en) Turbine blade variable load flow pattern design method
CN201786744U (en) Blades of cooling fan of engine
CN115098959B (en) Gas turbine high-pressure turbine guide vane design method
CN216446976U (en) Medium-pressure last-stage 315mm moving blade based on small enthalpy drop blade profile
CN116220826A (en) Reversing turbine movable blade profile with low reversing blowing loss

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

Application publication date: 20220830

RJ01 Rejection of invention patent application after publication