CN115930260B - Auxiliary power unit air bleed structure and aircraft engine - Google Patents
Auxiliary power unit air bleed structure and aircraft engine Download PDFInfo
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- CN115930260B CN115930260B CN202211430382.2A CN202211430382A CN115930260B CN 115930260 B CN115930260 B CN 115930260B CN 202211430382 A CN202211430382 A CN 202211430382A CN 115930260 B CN115930260 B CN 115930260B
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- 238000002485 combustion reaction Methods 0.000 abstract description 15
- 230000005284 excitation Effects 0.000 abstract description 12
- 230000006866 deterioration Effects 0.000 abstract 1
- 230000000694 effects Effects 0.000 description 9
- 230000006872 improvement Effects 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 230000000903 blocking effect Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000002474 experimental method Methods 0.000 description 2
- 230000002035 prolonged effect Effects 0.000 description 2
- 239000007858 starting material Substances 0.000 description 2
- 241001391944 Commicarpus scandens Species 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 239000003921 oil Substances 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
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- 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
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
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Abstract
The application discloses an air entraining structure of an auxiliary power device and an aeroengine, wherein the air entraining structure of the auxiliary power device comprises: the casing is of a double-layer casing structure and comprises an inner casing and an outer casing positioned at the periphery of the inner casing, and an inner casing cavity is formed between the outer casing and the inner casing. An inner shell air vent is formed in the inner shell, an outer shell air vent is formed in the outer shell, and the outer shell air vent supplies air for a main engine air supply channel through the air vent. The flame tube is positioned in the inner shell, the outer wall of the flame tube is provided with a flame tube air inlet hole, an air inlet runner is formed between the inner shell and the outer wall of the flame tube, and the included angle between the opening direction of the air inlet hole of the inner shell and the air inlet direction of the air inlet runner is not more than 75 °. The aeroengine comprises the bleed air structure. The application is used for solving the technical problems of combustion performance deterioration and strong excitation generation of the bleed air structure caused by uneven air flow of the bleed air structure of the engine auxiliary power device in the prior art.
Description
Technical Field
The application relates to the technical field of aeroengines, in particular to an air entraining structure of an auxiliary power device and an aeroengine.
Background
The starting of the aeroengine firstly needs to realize initial operation by means of external force, and helps to establish a continuous working state of air flow in the flow channel. On high thrust, high power aircraft engines, this external force is typically provided by compressed air pushing the air turbine starter to rotate. The auxiliary power device is a device for providing compressed air, is a small gas turbine engine, and the use of the auxiliary power device not only meets the requirement of quick starting of a high-thrust/power engine, but also reduces the dependence of an airplane on ground supporting equipment, and simultaneously increases the safety in flight, so that the auxiliary power device is one of the necessary onboard equipment on a modern airplane.
The auxiliary power device commonly used at present comprises a core compressor for outputting compressed air and a load compressor for outputting compressed air. For this auxiliary power unit, which outputs compressed air from the core compressor, it draws part of the compressed air from the combustor flow path, which acts to provide bleed air to the air turbine starter to start the main engine (ground and air). For the auxiliary power device, the bleed air distribution condition of the bleed air structural design can be effectively changed, so that the performance of the auxiliary power device is greatly influenced.
The design of the bleed air structure at the present stage is less, and a circular seam bleed air structure is usually adopted, as shown in fig. 2. The air flow enters the combustion chamber casing from the air compressor at the left end, then is divided into two parts, one part enters the air guiding cavity through the air guiding gap between the air guiding baffle plate and the casing, then provides air guiding for the main engine from the main air guiding channel, and the other part enters the combustion chamber through the opening on the flame tube for combustion. In the circumferential seam air-entraining mode, the main air-entraining channel is only positioned at a specific circumferential position, so that the air-entraining air flow is necessarily uneven in the circumferential direction, and the air flow entering the flame tube to participate in combustion is also uneven in the circumferential direction, so that the combustion performance is deteriorated and the practical efficiency is reduced. In addition, the outer ring of the air entraining baffle plate with the structure cannot be fixed, and the air entraining baffle plate can generate strong excitation under the influence of uneven airflow, so that failure modes such as cracks and the like are easy to generate.
Content of the application
The application aims to solve the technical problems that in the prior art, the combustion performance of the air entraining structure is deteriorated and strong excitation is generated due to uneven air flow of the air entraining structure of the auxiliary power device of the engine, so that the air entraining structure of the auxiliary power device and the aeroengine are provided.
In order to solve the technical problems, the technical scheme of the application is as follows, the bleed air structure of the auxiliary power device comprises:
The engine case is of a double-layer shell structure and comprises an inner shell and an outer shell positioned at the periphery of the inner shell, wherein an inner cavity of the engine case is formed between the outer shell and the inner shell;
The flame tube is positioned in the inner shell, a flame tube air inlet hole is formed in the outer wall of the flame tube, an air inlet runner is formed between the inner shell and the flame tube outer wall, and an included angle between the opening direction of the air inlet hole of the inner shell and the air inlet direction of the air inlet runner is not more than 75 °.
Preferably, the air inlet direction of the air inlet runner is parallel to the central axis direction of the casing, and an included angle between the opening direction of the air inlet hole of the inner casing and the central axis of the casing is 15 ° -75 °.
Preferably, the inner shell air vent is provided with a plurality of inner shell air vent holes, a plurality of rows of inner shell air vent holes are radially distributed on the inner shell along the central axis direction of the casing, and a plurality of inner shell air vent holes on the same row are uniformly distributed along the circumferential direction of the inner shell.
Preferably, the outer shell air vent is provided with a plurality of air vents, and the plurality of air vents are uniformly distributed along the circumferential direction of the outer shell.
Preferably, the aperture size of the inner housing air vent is 0.5mm to 2mm, and the aperture of the outer housing air vent is larger than the aperture of the inner housing air vent.
Preferably, a diffuser is arranged at the air inlet end of the casing, and a circumferentially continuous air inlet flow passage is formed between the diffuser and the inner shell.
Preferably, one end of the casing, which is far away from the diffuser, is inclined towards the central axis direction of the casing to form a reduced diameter section, the outer shell air bleed hole is arranged on the outer shell positioned on the reduced diameter section, and the air bleed pipe is connected on the outer wall of the outer shell positioned on the reduced diameter section.
Preferably, the inner housing and the outer housing in the reduced diameter section have the same inclination direction.
Preferably, the air bleed pipe is of a variable cross-section annular vortex structure, and the pipe diameter of one end of the air bleed pipe, which is close to the outlet end of the air bleed pipe, is larger than the pipe diameter of one end, which is far away from the outlet end of the air bleed pipe.
There is also provided an aeroengine comprising the bleed air arrangement of any of the auxiliary power units described above.
The technical scheme of the application has the following advantages:
1. According to the invention, the inner shell air-bleed hole of the inner shell can effectively reduce the excitation effect caused by the initial vibration and the non-uniformity of the air-bleed, and the service life of the auxiliary power device is prolonged; the inner shell body has blocking and drainage effects on air flow, and has better drainage effect on the air flow compared with the existing air entraining baffle plate, the inner shell body is more stable in structure, shock excitation is not easy to occur due to the impact of the air flow, and the working stability and the service life of the air entraining structure of the auxiliary power device are further improved.
2. The included angle between the opening direction of the air hole of the inner shell and the central axis of the casing is 15 ° -75 degrees, so that the direction of the air-entraining air flow is guaranteed to be approximately consistent with the direction of the air hole of the inner shell, the air-entraining air flow can flow along the air hole of the inner shell, the smoothness of the air-entraining air flow is guaranteed, the excitation intensity generated when the air flow impacts the inner shell can be reduced, and the air flow can smoothly enter the air-entraining pipe.
3. The inner shell arranged in an inclined manner can better resist the impact of air flow, and can also have a flatter drainage effect on the air flow.
4. The air-entraining distribution of the air-entraining structure of the auxiliary power device is improved through the aperture size, distribution and quantity of the air-entraining holes, so that the internal tissue combustion of the flame tube is more reasonable, the combustion efficiency can be improved, the better outlet temperature distribution can be obtained, and the shaft work output efficiency of the auxiliary power device and the service life of turbine blades can be improved.
Drawings
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings that are needed in the description of the embodiments or the prior art will be briefly described, and it is obvious that the drawings in the description below are some embodiments of the present application, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic view of the overall structure of a bleed air structure of an auxiliary power unit in accordance with an embodiment of the present application;
FIG. 2 is a schematic illustration of a bleed air configuration of a prior art auxiliary power unit;
FIG. 3 is a schematic view of the overall structure of a casing according to an embodiment of the present application;
Fig. 4 is a schematic view of the overall structure of the outer casing according to the embodiment of the present application.
The reference numerals indicate that 1, an outer shell, 1-1, an outer shell air vent, 2, an inner shell, 2-1, an inner shell air vent, 3, an air vent, 3-1, an air vent outlet end, 4, a flame tube, 4-1, a flame tube air inlet hole, 5, a diffuser, 6, a buffer runner, 7, a casing inner cavity and 8, an air inlet runner.
Detailed Description
The following description of the embodiments of the present application will be made apparent and fully in view of the accompanying drawings, in which some, but not all embodiments of the application are shown. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
In the description of the present application, unless explicitly stated or limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected, mechanically connected, electrically connected, directly connected, indirectly connected via an intervening medium, or in communication between two elements. The specific meaning of the above terms in the present application will be understood in specific cases by those of ordinary skill in the art.
Example 1
The air entraining structure of the auxiliary power device comprises a casing and a flame tube 4.
The casing is double-deck shell structure, as shown in fig. 1 and 3, and the casing includes integrated inner shell 2 and shell 1, and shell 1 is located the periphery of inner shell 2, exists hollow region between shell 1 and the inner shell 2, and this region is casing inner chamber 7, and the air current can circulate in casing inner chamber 7.
An inner shell air vent 2-1 is formed in the inner shell 2, an outer shell air vent 1-1 is formed in the outer shell 1, the inner shell air vent 2-1 is communicated with the outer shell air vent 1-1 through a casing inner cavity 7, the outer shell air vent 1-1 is used for supplying air through an air bleed pipe 3 as a main engine air supply channel, and one end, connected with the main engine, of the air bleed pipe 3 is used for supplying air through an air bleed pipe outlet end 3-1.
The flame tube 4 is positioned in the inner shell 2, the outer wall of the flame tube 4 is provided with a flame tube air inlet 4-1, an air inlet channel 8 is formed between the inner shell 2 and the outer wall of the flame tube 4, and the air inlet channel 8 is communicated with the inner cavity 7 of the casing through the air inlet hole 2-1 of the inner shell.
As shown in fig. 1, the right end of the air intake runner 8 is an air intake end, the left end of the air intake runner 8 is an air outlet end, the flow direction of the air flow in the air intake runner 8 is from right to left, the opening direction of the air intake hole 2-1 of the inner shell is substantially the same as the air intake direction of the air intake runner 8, the opening direction of the air intake hole 2-1 of the inner shell and the air intake direction of the air intake runner 8 form a certain inclination angle, and the inclination range is not more than 75 °.
The air entraining structure of the auxiliary power device provided by the embodiment comprises the following working processes that air flow is introduced from the air inlet end of an air inlet runner 8, flows from right to left, enters a casing inner cavity 7 after passing through an inner casing air introducing hole 2-1, enters an air entraining pipe 3 after passing through an outer casing air introducing hole 1-1, finally supplies air to a main engine air supply channel through the air entraining pipe 3, and finally achieves the purpose of air entraining of the main engine, and the other part of air flow enters a flame tube 4 through a flame tube air inlet hole 4-1 to complete combustion or blending.
It should be noted that, for the air flow passing through the inner casing air vent 2-1, the inner casing 2 and the outer casing 1 are integrated, and the opening angle of the inner casing air vent 2-1 is consistent with the air flow direction, the air flow is uniformly dispersed by the inner casing air vent 2-1 after passing through the inner casing air vent 2-1, so that the air flow is prevented from flowing in the casing in disorder, the order of the air flow is increased, the inner casing air vent 2-1 can effectively reduce the excitation effect caused by the initial vibration and the non-uniformity of the air bleed, the damage of parts caused by the strong excitation generated in the casing is avoided, and the service life of the auxiliary power device is prolonged. The inner shell 2 has blocking and drainage effects on air flow, and compared with the existing air entraining baffle, the inner shell 2 has better air flow drainage effect, and the inner shell 2 is not easy to break by air flow. The air flow entering the flame tube 4 is the residual air quantity after the initial air flow passes through the air introducing hole 2-1 of the inner shell. Since the uniformity of the distribution of the air flow through the air introduction holes 2-1 of the inner housing is improved, the distribution of the residual air amount of the initial air flow into the tissue combustion area through the air introduction holes 4-1 of the burner tube is also improved. The oil gas in the flame tube 4 is uniformly proportioned, the tissue combustion in the flame tube 4 is reasonable, and the fuel oil combustion is more sufficient, so that the combustion efficiency of the flame tube 4 of the auxiliary power device is improved and the outlet temperature distribution is improved. The improvement of the combustion efficiency can improve the output efficiency of the shaft work of the auxiliary power device, and the improvement of the outlet temperature distribution can further improve the service life of the turbine blade outputting the shaft work. The practical efficiency and the service life of the auxiliary power device can be improved finally.
Example 2
As a further modification of embodiment 1, as shown in fig. 1, the air inlet end of the casing is provided with a diffuser 5, and a circumferentially continuous air inlet channel 8 is formed between the diffuser 5 and the inner casing 2. When the air flow passes through the diffuser 5, the diffuser 5 plays a role in primary guiding of pressurization on the air flow, so that the air flow can enter the air inlet flow passage 8 more stably.
The central axial directions of the outer shell 1 and the inner shell 2 of the casing are horizontal lines, the air inlet direction of the air inlet runner 8 is also the horizontal direction, and the included angle between the opening direction of the air inlet hole 2-1 of the inner shell and the central axis of the casing is 15 ° -75 °. Through multiple experiments, the direction of the opening of the air introduction hole 2-1 of the inner shell is set within the range of 15-75 degrees, so that the excitation effect of air flow in the casing can be effectively reduced.
As shown in fig. 3, a plurality of inner casing air-guiding holes 2-1 are provided on the inner casing 2, and the inner casing air-guiding holes 2-1 are radially distributed in a plurality of rows along the central axis direction of the casing (i.e. a plurality of groups of inner casing air-guiding holes 2-1 are provided on the inner casing 2 in fig. 3, on the left and right sides), and the plurality of inner casing air-guiding holes 2-1 on the same row are uniformly distributed along the circumferential direction of the inner casing 2. Through the orderly arrangement of the plurality of groups of the inner shell air introduction holes 2-1 at intervals, the air flow entering the inner cavity 7 of the casing through the inner shell air introduction holes 2-1 can be more uniform, the uniformity and the stability of the air flow in the casing can be further improved, and the excitation effect of the air flow in the casing can be further reduced.
The aperture size of the inner shell air vent 2-1 is 0.5mm to 2mm, the number of the single-ring inner shell air vent 2-1 ranges from 100 to 360, and the inner shell air vent 2-1 is distributed in a radial direction and is arranged in 5 to 15 rows. The aperture of the outer shell air vent 1-1 is larger than that of the inner shell air vent 2-1. Through experiments, when the aperture of the air introduction hole 2-1 of the inner shell is adjusted within the interval of 0.5mm to 2mm, the excitation action of the casing is obviously changed along with the change of the aperture, and when the aperture is smaller than 0.5mm or larger than 2mm, the excitation action of the casing is not obviously changed along with the change of the aperture. Therefore, the diameter of the inner casing vent hole 2-1 is set to 0.5mm to 2mm, and the size of the aperture is adjusted in this range, which contributes to a more remarkable improvement.
The outer shell air vent 1-1 is provided with a plurality of, and a plurality of outer shell air vents 1-1 are evenly distributed along the circumference of the outer shell 1 and are arranged at positions close to the left end face. The position of the outer shell 1, which is close to the left end face, is provided with an annular buffer flow channel 6, the buffer flow channel 6 is communicated with the inner cavity 7 of the casing through an outer shell air-guiding hole 1-1, and the outer shell air-guiding hole 1-1, which is close to the air-guiding pipe 3, is larger than the outer shell air-guiding hole 1-1, which is far away from the air-guiding pipe 3. The air-entraining pipe 3 is communicated with the inner cavity 7 of the casing through the buffer runner 6 and the air-entraining hole 1-1 of the outer casing, the air-entraining pipe 3 is of a variable-section annular vortex structure, and the pipe diameter of one end of the air-entraining pipe 3 close to the air-entraining pipe outlet end 3-1 is larger than that of one end far away from the air-entraining pipe outlet end 3-1. The pressure difference at the two sides of the outer shell air guiding hole 1-1 close to the air guiding pipe 3 is relatively larger, and the aperture of the corresponding size is matched through the pressure difference of different positions, so that the air inflow of the outer shell air guiding hole 1-1 at each position is relatively uniform, and the uniformity of air guiding distribution is greatly improved.
Example 3
The embodiment provides an aero-engine, including the bleed air structure of auxiliary power unit that embodiment 1 or embodiment 2 provided, bleed air is carried out as the main engine to the bleed air structure of auxiliary power unit of embodiment 1 or embodiment 2 for the aero-engine that this embodiment provided has not only satisfied the demand that high-thrust/high-power engine started fast, has reduced the aircraft and has supported the dependence of equipment on ground, has also increased the security in flight simultaneously.
It is apparent that the above examples are given by way of illustration only and are not limiting of the embodiments. Other variations or modifications of the above teachings will be apparent to those of ordinary skill in the art. It is not necessary here nor is it exhaustive of all embodiments. While still being apparent from variations or modifications that may be made by those skilled in the art are within the scope of the application.
Claims (7)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211430382.2A CN115930260B (en) | 2022-11-15 | 2022-11-15 | Auxiliary power unit air bleed structure and aircraft engine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202211430382.2A CN115930260B (en) | 2022-11-15 | 2022-11-15 | Auxiliary power unit air bleed structure and aircraft engine |
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| Publication Number | Publication Date |
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| CN115930260A CN115930260A (en) | 2023-04-07 |
| CN115930260B true CN115930260B (en) | 2025-01-28 |
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109974032A (en) * | 2019-03-21 | 2019-07-05 | 中国航发湖南动力机械研究所 | A kind of bleed structure of auxiliary power unit |
| CN110998189A (en) * | 2017-08-21 | 2020-04-10 | 赛峰飞机发动机公司 | Combustor module for an aircraft turbine engine including markings to aid identification during endoscopy of the combustor |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP6422412B2 (en) * | 2015-09-10 | 2018-11-14 | 三菱日立パワーシステムズ株式会社 | Gas turbine combustor |
| CN115031259B (en) * | 2022-03-18 | 2023-06-02 | 北京航空航天大学 | Combustion chamber of a gas turbine and design method thereof |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110998189A (en) * | 2017-08-21 | 2020-04-10 | 赛峰飞机发动机公司 | Combustor module for an aircraft turbine engine including markings to aid identification during endoscopy of the combustor |
| CN109974032A (en) * | 2019-03-21 | 2019-07-05 | 中国航发湖南动力机械研究所 | A kind of bleed structure of auxiliary power unit |
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