CN203097955U - Air guiding assembly of gas turbine engine - Google Patents
Air guiding assembly of gas turbine engine Download PDFInfo
- Publication number
- CN203097955U CN203097955U CN 201220721124 CN201220721124U CN203097955U CN 203097955 U CN203097955 U CN 203097955U CN 201220721124 CN201220721124 CN 201220721124 CN 201220721124 U CN201220721124 U CN 201220721124U CN 203097955 U CN203097955 U CN 203097955U
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- Prior art keywords
- base portion
- annular
- gas turbine
- turbine engine
- air entraining
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- Expired - Lifetime
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Abstract
An air guiding assembly of a gas turbine engine comprises a first turbine disc, a second turbine disc, a supporting ring, damping rings and air guiding pipes, wherein the first turbine disc limits a circumferential-direction groove which faces the down stream of gas, the second turbine disc is adjacent to the first turbine disc, an air inlet hole is limited on a drum cylinder which is arranged on the second turbine disc, the drum cylinder is used for being connected with the first turbine disc, a circumferential-direction flange is arranged on the second turbine disc, the supporting ring comprises an annular base portion, a first annular side wall and a second annular side wall, the first annular side wall and the second annular side wall extend outward from the annular base portion, the first annular side wall is adaptive to the circumferential-direction groove, the second annular side wall is arranged on the circumferential-direction flange, a plurality of installation holes are limited at intervals in positions, between the first annular side wall and the second annular side wall, of the base portion, the damping rings are arranged in the installation holes respectively in an adaptive mode, and the air guiding pipes are arranged in the damping rings respectively in an adaptive mode. Through the air guiding assembly of the gas turbine engine, a tangential speed and a flow coefficient of air which flows out of the air guiding pipes are reduced, the scale of turbulence is reduced, therefore loss of air guiding inlet pressure is reduced, and air guiding flow and cooling efficiency are guaranteed.
Description
Technical field
The utility model relates to a kind of bleed assembly of gas turbine engine.
Background technique
At present, fuel gas temperature has reached more than 1500 degrees centigrade before the turbine of gas turbine, and this has surpassed the operating temperature that the turbine part material can bear.For this reason, the turbine part of gas turbine need be introduced pressurized air from compressor part and cool off as cooling medium, can proper functioning to guarantee turbine part.Specifically, perforate from the compressor rotor drum barrel wall from the gap of runner bleed radial flow between adjacent two-stage wheel disc, enters turbine part through the guiding of axial sleeve then and cools off.Yet, the air turbulence degree of introducing inner chamber from compressor passage is big, loss aerodynamic energy and the cooling bleed air inlet pressure, make the inlet and outlet pressure difference of bleed cooling increase, cause flow loss, cooling effectiveness reduces, even the level bleed from behind of having to, and has reduced the efficient of whole gas turbine.
The model utility content
In order to address the above problem, the utility model is installed the radially air entraining pipe that annular is arranged between rotor disk, the air of introducing from runner can only flow through from these air entraining pipes, the tangential introduction of air speed and the flow coefficient that flow out from air entraining pipe are minimized, turbulivity reduces, thereby reduced the loss of bleed air inlet pressure, guaranteed bleed flow and cooling effectiveness.
Particularly, the utility model discloses a kind of bleed assembly of gas turbine engine, it is characterized in that the bleed assembly comprises: be positioned at first wheel disc of the compressor mover blade of combustion gas upstream, it is limited with out the circumferential recess to the combustion gas downstream; Be positioned at second wheel disc of the compressor mover blade in combustion gas downstream, it is adjacent with first wheel disc, is limited with inlet hole on the drum barrel that is used for being connected with first wheel disc of second wheel disc, and second wheel disc also has circumferential flange at the opposite side of circumferential recess; Support ring, it has annular base, from outward extending first annular sidewall of annular base and second annular sidewall relative with first annular sidewall, wherein, first annular sidewall fits in the circumferential recess, second annular sidewall is installed on the circumferential flange, and base portion is also turned up the soil at interval between first annular sidewall and second annular sidewall and is limited with a plurality of mounting holes; Damping ring, it is installed in the mounting hole adaptedly; And air entraining pipe, it is installed in the damping ring adaptedly.
Particularly, damping ring comprises base portion and the cylindric ring main body portion that extends straight up from base portion, and wherein, the base portion of damping ring abuts on the interior edge face of support ring.
Particularly, air entraining pipe comprises base portion and the cylindrical pipe main body portion that extends straight up from base portion, and wherein, the base portion of air entraining pipe abuts on the base portion of damping ring, and tube body portion cover is set in the ring main body portion of damping ring.
More specifically, the interior edge face of support ring is formed with annular groove, and it is used to hold the base portion of damping ring and the base portion of air entraining pipe.
More specifically, the bleed assembly also comprises annular collar, and it is set in the described support ring and radially supports described air entraining pipe.
More specifically, annular collar comprises base portion and the wall portion of extending from the base portion outward radial, wall portion is positioned between the cell wall of annular groove of the ora terminalis of base portion of the base portion of damping ring and air entraining pipe and support ring, the abutting on the lower surface of base portion of air entraining pipe to the small part outer surface of the base portion of annular collar.
More specifically, the upper and lower surface of the base portion of the upper and lower surface of the base portion of the diapire of annular groove, damping ring and air entraining pipe is the plane.
More specifically, the upper and lower surface of the base portion of annular collar is cambered surface.
Preferably, be limited with the vibration damping groove on the damping ring.
More preferably, the vibration damping groove is radially.
Preferably, the base portion of support ring also is limited with a plurality of grooves between first annular sidewall and second annular sidewall.
The utility model has been considered manufacturability fully, has reduced manufacture cost effectively, has improved manufacturing efficiency.Particularly, support ring and collar all are simple shape and the solid of rotation that is easy to process, for example can be easy to machined into and be shaped.Curved upper surface has also been avoided in the design of air entraining pipe and damp tube, and planar upper surface makes the processing of pedestal and the processing of pipe once to shape on lathe, has saved operation like this and has reduced difficulty of processing.The utility model has been saved operation, processes easylier, has reduced the cost of manufacturing.
Description of drawings
In order to explain the utility model, its illustrative embodiments will be described with reference to the drawings hereinafter, in the accompanying drawing:
Fig. 1 schematically shows the sectional view of bleed assembly on the engine axis direction of gas turbine engine of the present utility model;
Fig. 2 schematically shows the bleed assembly of gas turbine engine of the present utility model at the sectional view that is basically perpendicular on the motor axial direction;
Fig. 3 schematically shows the perspective view that support ring, damping ring, air entraining pipe and the annular collar of the bleed assembly of gas turbine engine of the present utility model are combined together;
Fig. 4 schematically shows the partial enlarged drawing that support ring, damping ring, air entraining pipe and annular collar in the bleed assembly of gas turbine engine of the present utility model are combined together.
Similar features among the different figure is by similar reference character indication.
Embodiment
In the detailed description of following mode of execution, the accompanying drawing that reference constitutes the part of this description describes.Accompanying drawing shows specific mode of execution in the mode of example, and the utility model is implemented in these mode of executions.Shown mode of execution be not for limit according to all mode of executions of the present utility model.The mode of execution that is appreciated that other can be utilized, and change structural or logicality can be made under the prerequisite that does not break away from scope of the present utility model.For accompanying drawing, the term of directivity, for example D score, " on ", " downstream ", " upstream ", " vertically ", " radially ", " outward ", " interior " etc., use with reference to the orientation of described accompanying drawing.Because the assembly of mode of execution of the present utility model can be implemented with multiple orientation, these directional terminology are to be used for illustrative purposes, rather than the purpose of restriction.Therefore, following embodiment is not the meaning as restriction, and scope of the present utility model is limited by appending claims.
Referring to Fig. 1-Fig. 4, the utility model discloses a kind of bleed assembly 100 of gas turbine engine, wherein, this bleed assembly 100 comprises:
Be positioned at first wheel disc 102 of the compressor mover blade of combustion gas upstream;
Be positioned at second wheel disc 104 of the compressor mover blade in combustion gas downstream, it is adjacent with first wheel disc 102;
Wherein, be limited with inlet hole 108 on the drum barrel 106 that is used for being connected of second wheel disc 104 with first wheel disc 102, circumferential recess 110, the second wheel discs 104 that first wheel disc 102 is limited with out to second wheel disc 104 also have circumferential flange 112 at the opposite side of circumferential recess 110;
Particularly, support ring 114 integral body are colyliform, and a plurality of mounting holes are evenly distributed on the base portion 114a of support ring 114, preferably, have 12 mounting holes.Be formed with a plurality of installation base 114d on the second annular sidewall 114c, by installation base the second annular sidewall 114c be installed on the circumferential flange 112 such as the fastening piece of bolt.The interior edge face of this support ring 114 is formed with annular groove.In addition, as shown in Figure 3, this base portion 114a also has the upwards even groove 114e that arranges of a plurality of weeks to be used to alleviate the overall weight of support ring 114 between the first annular sidewall 114b and second annular sidewall 114.
This damping ring 116 comprises base portion 116a and from the upwards basic cylindric ring main body portion 116b that vertically extends of this base portion 116a, is limited with a plurality of groove 116c that radially extend on this ring main body portion 116b.This air entraining pipe 118 also comprises base portion 118a and from the upwardly extending cylindrical pipe main body portion of this base portion 118a 118b.The length of the 118b of tube body portion of air entraining pipe 118 is greater than the ring main body portion 116b of damping ring 116, and the external diameter of the 118b of tube body portion of this air entraining pipe 118 equals the internal diameter of the ring main body portion 116b of (or being slightly larger than) this damping ring 116 substantially.Annular collar 120 comprises base portion 120a and the 120b of wall portion that extends from this base portion 120a outward radial.
When being installed to damping ring 116 and air entraining pipe 118 on the support ring 114, earlier the 118b of tube body portion of air entraining pipe 118 is set in the ring main body portion 116b of damping ring 116 and makes the radial outer end face of base portion 118a of air entraining pipe 118 abut on the radial inner end face of base portion 116a of damping ring 116, then, the damping ring 116 that is arranged with air entraining pipe 118 passed the mounting hole of support ring 114 and make the radial outer end face of base portion 116a of damping ring 116 abut on the wall of annular groove of support ring 114, then, the 120b of wall portion of annular collar 120 is positioned between the ora terminalis of base portion 118a of the base portion 116a of the radially wall of annular groove of support ring 114 and damping ring 116 and air entraining pipe 118, simultaneously, the base portion 120a's of this annular collar 120 is resisted against on the lower surface of base portion 118a of this support ring 114 and this air entraining pipe 118 to the small part outer surface.
After above-mentioned assembling finishes, present builtup member 200 as shown in Figure 3, then, this builtup member 200 is installed between adjacent first wheel disc 102 and second wheel disc 104 again.Particularly, this first annular sidewall 114b and circumferential recess 110 is adaptive, simultaneously, the installation base 114d on the second annular sidewall 114c is alignd with flange on second wheel disc 104 and link together with fastening piece such as bolt.
Preferably, the radially upper surface of the base portion 118a of the radially upper and lower surface of the base portion 116a of the diapire of the annular groove of this support ring 114, damping ring 116 and air entraining pipe 118 is the plane.More preferably, the radially lower surface of the base portion 118a of air entraining pipe 118 is a cambered surface.
When aforementioned gas turbine engine is worked, the air that enters motor from engine inlets enters into gas compressor for compression via fan, the pressurized air of gas compressor enters into the cavity that is limited jointly by first wheel disc 102 and second wheel disc 104 via the inlet hole 108 on second wheel disc 104, then, flow out above-mentioned bleed assembly 100 by air entraining pipe 118, under the guiding of sleeve 122, flow to the downstream of gas turbine then.By this, can the parts in the downstreams such as turbine part in the wheel disc of gas compressor later stages and hot junction be cooled off.In the bleed process, the groove 116c of the damping ring 116 of bleed assembly 100 can absorb the vibrational energy of sucking pipe 118 to bring into play its damping effect.Simultaneously, because first wheel disc 102 and second wheel disc 104 are the compressor rotor wheel disc, so when engine operation, compressor rotor rotates around axis L, damping ring 116 and air entraining pipe 118 can under centrifugal force affact on the interior edge face of support ring 114, and, the diapire of annular groove, on the base portion 116a of damping ring 116, on the base portion 118a of lower surface and air entraining pipe 118, lower surface is the plane, so air entraining pipe 118, damping ring 116 can sealing be pressed on the diapire of annular groove preferably, like this, under engine behavior, annular collar 120 is not brought into play supporting effect.Under the motor off working state, owing to there is not action of centrifugal force, damp tube 116 and air entraining pipe 118 need annular collar 120 to provide support diametrically.
Those skilled in the art should be appreciated that if friction tight words between damping ring 116 and the support ring 114, and annular collar 120 is omissible.
The those skilled in the art in those present technique fields can be by research specification, disclosed content and accompanying drawing and appending claims, and understanding and enforcement are to other changes of the mode of execution of disclosure.In the claims, word " comprises " element and the step of not getting rid of other, and wording " one " is not got rid of plural number.In the practical application of model utility, the function of a plurality of technical characteristicss of being quoted during a part possibility enforcement of rights requires.Any reference character in the claim should not be construed as the restriction to scope.
The utility model is limited to the illustrative embodiments that presents never in any form in specification and accompanying drawing.All combinations of the mode of execution that illustrates and describe (part) are interpreted as clearly to incorporate within this specification and be interpreted as clearly and fall in the scope of the present utility model.And in the scope of summarizing as claims of the present utility model, a lot of distortion are possible.In addition, any reference mark in claims should be configured to limit scope of the present utility model.
Claims (11)
1. the bleed assembly of a gas turbine engine is characterized in that, described bleed assembly comprises:
Be positioned at first wheel disc of the compressor mover blade of combustion gas upstream, it is limited with out the circumferential recess to the combustion gas downstream;
Be positioned at second wheel disc of the compressor mover blade in combustion gas downstream, it is adjacent with described first wheel disc, be limited with inlet hole on the drum barrel that is used for being connected with described first wheel disc of described second wheel disc, described second wheel disc also has circumferential flange at the opposite side of described circumferential recess;
Support ring, it has annular base, from outward extending first annular sidewall of described annular base and second annular sidewall relative with described first annular sidewall, wherein, described first annular sidewall fits in the described circumferential recess, described second annular sidewall is installed on the described circumferential flange, and described base portion is also turned up the soil at interval between described first annular sidewall and described second annular sidewall and is limited with a plurality of mounting holes;
Damping ring, it is installed in the described mounting hole adaptedly; And
Air entraining pipe, it is installed in the described damping ring adaptedly.
2. the bleed assembly of gas turbine engine according to claim 1, it is characterized in that, described damping ring comprises base portion and the cylindric ring main body portion that extends straight up from described base portion, and wherein, the base portion of described damping ring abuts on the interior edge face of described support ring.
3. the bleed assembly of gas turbine engine according to claim 2, it is characterized in that, described air entraining pipe comprises base portion and the cylindrical pipe main body portion that extends straight up from described base portion, wherein, the base portion of described air entraining pipe abuts on the base portion of described damping ring, and described tube body portion cover is set in the ring main body portion of described damping ring.
4. the bleed assembly of gas turbine engine according to claim 3 is characterized in that, the interior edge face of described support ring is formed with annular groove, and it is used to hold the base portion of described damping ring and the base portion of described air entraining pipe.
5. the bleed assembly of gas turbine engine according to claim 4 is characterized in that, described bleed assembly also comprises annular collar, and it is set in the described support ring and radially supports described air entraining pipe.
6. the bleed assembly of gas turbine engine according to claim 5, it is characterized in that, described annular collar comprises base portion and the wall portion of extending from described base portion outward radial, described wall portion is positioned radially between the cell wall of annular groove of the ora terminalis of base portion of the base portion of described damping ring and described air entraining pipe and described support ring, the abutting on the lower surface of base portion of described air entraining pipe to the small part outer surface of the base portion of described annular collar.
7. the bleed assembly of gas turbine engine according to claim 6 is characterized in that, the upper and lower surface of the upper and lower surface of the diapire of described annular groove, the base portion of described damping ring and the base portion of described air entraining pipe is the plane.
8. the bleed assembly of gas turbine engine according to claim 7 is characterized in that, the upper and lower surface of the base portion of described annular collar is cambered surface.
9. according to the bleed assembly of each described gas turbine engine of claim 1-8, it is characterized in that, be limited with the vibration damping groove on the described damping ring.
10. the bleed assembly of gas turbine engine according to claim 9 is characterized in that, described vibration damping groove is radially.
11. the bleed assembly according to each described gas turbine engine of claim 1-8 is characterized in that, the base portion of described support ring also is limited with a plurality of grooves between described first annular sidewall and described second annular sidewall.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220721124 CN203097955U (en) | 2012-12-24 | 2012-12-24 | Air guiding assembly of gas turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220721124 CN203097955U (en) | 2012-12-24 | 2012-12-24 | Air guiding assembly of gas turbine engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203097955U true CN203097955U (en) | 2013-07-31 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220721124 Expired - Lifetime CN203097955U (en) | 2012-12-24 | 2012-12-24 | Air guiding assembly of gas turbine engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203097955U (en) |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105156214A (en) * | 2015-07-09 | 2015-12-16 | 中国航空工业集团公司沈阳发动机设计研究所 | Disc cavity gas collecting device for heavy-duty gas turbine |
| CN105934562A (en) * | 2013-11-26 | 2016-09-07 | 通用电气公司 | Rotor off-take assembly |
| CN107023394A (en) * | 2017-04-07 | 2017-08-08 | 中国航发沈阳发动机研究所 | Tubular type compressor rotor air entraining device with damping |
| CN109209980A (en) * | 2017-06-30 | 2019-01-15 | 中国航发商用航空发动机有限责任公司 | A kind of deflector for axial flow compressor |
| CN111315961A (en) * | 2017-11-14 | 2020-06-19 | 赛峰飞机发动机公司 | Supporting device of radial centripetal air extraction mechanism |
| CN111379736A (en) * | 2020-04-03 | 2020-07-07 | 中国航发沈阳发动机研究所 | Air entraining structure of air compressor |
| CN112088252A (en) * | 2018-05-09 | 2020-12-15 | 赛峰飞机发动机公司 | Turbine and method of collecting airflow in a turbine |
| CN112503029A (en) * | 2019-09-16 | 2021-03-16 | 中国航发商用航空发动机有限责任公司 | Aircraft engine compressor and turbine reducing assembly |
| CN114109511A (en) * | 2021-11-12 | 2022-03-01 | 中国航发沈阳发动机研究所 | Novel disk center connecting structure and double-spoke-plate turbine disk with same |
| CN114542640A (en) * | 2020-11-24 | 2022-05-27 | 中国航发商用航空发动机有限责任公司 | Damping vibration attenuation device and aircraft engine |
| CN114542641A (en) * | 2020-11-24 | 2022-05-27 | 中国航发商用航空发动机有限责任公司 | Damping vibration attenuation device and aircraft engine |
| CN114651132A (en) * | 2019-09-05 | 2022-06-21 | 联合发动机制造集团股份公司 | Bleed air device in a turbojet compressor rotor |
| CN114776927A (en) * | 2022-04-16 | 2022-07-22 | 中国航发沈阳发动机研究所 | Aeroengine bleed pipe damping vibration attenuation structure |
| CN115493018A (en) * | 2022-11-21 | 2022-12-20 | 中国航发四川燃气涡轮研究院 | Vibration reduction structure for air entraining pipe of tubular vortex reducer of aircraft engine |
-
2012
- 2012-12-24 CN CN 201220721124 patent/CN203097955U/en not_active Expired - Lifetime
Cited By (23)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105934562B (en) * | 2013-11-26 | 2020-11-17 | 通用电气公司 | Rotor bleed assembly |
| CN105934562A (en) * | 2013-11-26 | 2016-09-07 | 通用电气公司 | Rotor off-take assembly |
| US10577966B2 (en) | 2013-11-26 | 2020-03-03 | General Electric Company | Rotor off-take assembly |
| CN105156214A (en) * | 2015-07-09 | 2015-12-16 | 中国航空工业集团公司沈阳发动机设计研究所 | Disc cavity gas collecting device for heavy-duty gas turbine |
| CN107023394A (en) * | 2017-04-07 | 2017-08-08 | 中国航发沈阳发动机研究所 | Tubular type compressor rotor air entraining device with damping |
| CN107023394B (en) * | 2017-04-07 | 2019-03-22 | 中国航发沈阳发动机研究所 | Tubular type compressor rotor air entraining device with damping |
| CN109209980A (en) * | 2017-06-30 | 2019-01-15 | 中国航发商用航空发动机有限责任公司 | A kind of deflector for axial flow compressor |
| CN111315961B (en) * | 2017-11-14 | 2022-06-10 | 赛峰飞机发动机公司 | Supporting device of radial centripetal air extraction mechanism |
| CN111315961A (en) * | 2017-11-14 | 2020-06-19 | 赛峰飞机发动机公司 | Supporting device of radial centripetal air extraction mechanism |
| CN112088252A (en) * | 2018-05-09 | 2020-12-15 | 赛峰飞机发动机公司 | Turbine and method of collecting airflow in a turbine |
| CN112088252B (en) * | 2018-05-09 | 2022-08-02 | 赛峰飞机发动机公司 | Turbine and method of collecting airflow in a turbine |
| CN114651132A (en) * | 2019-09-05 | 2022-06-21 | 联合发动机制造集团股份公司 | Bleed air device in a turbojet compressor rotor |
| CN112503029A (en) * | 2019-09-16 | 2021-03-16 | 中国航发商用航空发动机有限责任公司 | Aircraft engine compressor and turbine reducing assembly |
| CN111379736B (en) * | 2020-04-03 | 2021-09-03 | 中国航发沈阳发动机研究所 | Air entraining structure of air compressor |
| CN111379736A (en) * | 2020-04-03 | 2020-07-07 | 中国航发沈阳发动机研究所 | Air entraining structure of air compressor |
| CN114542641A (en) * | 2020-11-24 | 2022-05-27 | 中国航发商用航空发动机有限责任公司 | Damping vibration attenuation device and aircraft engine |
| CN114542640A (en) * | 2020-11-24 | 2022-05-27 | 中国航发商用航空发动机有限责任公司 | Damping vibration attenuation device and aircraft engine |
| CN114542640B (en) * | 2020-11-24 | 2024-04-05 | 中国航发商用航空发动机有限责任公司 | Damping vibration attenuation device and aeroengine |
| CN114542641B (en) * | 2020-11-24 | 2024-04-05 | 中国航发商用航空发动机有限责任公司 | Damping vibration attenuation device and aeroengine |
| CN114109511A (en) * | 2021-11-12 | 2022-03-01 | 中国航发沈阳发动机研究所 | Novel disk center connecting structure and double-spoke-plate turbine disk with same |
| CN114776927A (en) * | 2022-04-16 | 2022-07-22 | 中国航发沈阳发动机研究所 | Aeroengine bleed pipe damping vibration attenuation structure |
| CN114776927B (en) * | 2022-04-16 | 2024-04-09 | 中国航发沈阳发动机研究所 | Damping vibration attenuation structure of air guide pipe of aeroengine |
| CN115493018A (en) * | 2022-11-21 | 2022-12-20 | 中国航发四川燃气涡轮研究院 | Vibration reduction structure for air entraining pipe of tubular vortex reducer of aircraft engine |
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Legal Events
| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address |
Address after: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee after: AECC COMMERCIAL AIRCRAFT ENGINE Co.,Ltd. Address before: 201109 Shanghai city Minhang District Hongmei Road No. 5696 Room 101 Patentee before: AVIC Commercial Aircraft Engine Co.,Ltd. |
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| CP03 | Change of name, title or address | ||
| CX01 | Expiry of patent term |
Granted publication date: 20130731 |
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| CX01 | Expiry of patent term |