CN103711608A - Engine airflow passage structure and fanjet - Google Patents
Engine airflow passage structure and fanjet Download PDFInfo
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- CN103711608A CN103711608A CN201210380591.0A CN201210380591A CN103711608A CN 103711608 A CN103711608 A CN 103711608A CN 201210380591 A CN201210380591 A CN 201210380591A CN 103711608 A CN103711608 A CN 103711608A
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Abstract
The invention discloses an engine airflow passage structure and a fanjet and relates to the technical field of aircraft engines, solving the technical problem of low erodynamic efficiency of engines due to high internal flow losses of transitional sections in the prior art. The engine airflow passage structure comprises a hub, a cartridge, turbine blades, a supporting plate and a fairing device. The turbine blades are fixedly connected with the hub, and tip clearances are reserved between tips of the turbine blades and the inner wall of the cartridge. The supporting plate is disposed between the hub and the cartridge. The fairing device is fixedly arranged on the cartridge between the turbine blades and the supporting plate, and is used for fairing airflow flowing from the tip clearances to the supporting plate and preventing the airflow from flow separation around the supporting plate. The fanjet comprises a low-pressure turbine, a high-pressure turbine and the engine airflow passage structure. With the engine airflow passage structure and the fanjet, the internal flow looses of the transitional sections can be reduced and the erodynamic efficiency of aircraft engines can be improved.
Description
Technical field
The present invention relates to aero engine technology field, the turbofan engine that is specifically related to a kind of airflow channel structure of motor and the airflow channel structure of this motor is set.
Background technique
In the future for a long period of time, large Bypass Ratio Turbofan Engine will remain the optimal selection of airliner power.The thrust that the fan of large Bypass Ratio Turbofan Engine produces accounts for 60% ~ 80% of motor gross thrust, and therefore, it is vital for the civilian motor of large bypass ratio that the low-pressure turbine of maintenance drive fan works in higher efficient state.
At present, the bypass ratio of civilian motor has developed into 9 ~ 10, and the diameter of fan has surpassed 3 meters.Under this condition, on the one hand, the high voltage component of motor still works in higher rotating speed (10000r/min ~ 15000r/min), this just requires the diameter of high-pressure turbine less, on the other hand, be subject to the restriction that fan leaf point tangential velocity can not be too large, in the situation that not adopting speed change gear, the rotating speed of low pressure parts very low (2500r/min ~ 5500r/min), and in order to meet acting ability and the high efficiency requirement of low-pressure turbine 6 as shown in Figure 1, just must strengthen diameter and the Ye Gao of low-pressure turbine 6.The greatest differences of high- pressure turbine 3,6 pairs of diameters of low-pressure turbine and leaf high request, causes large bypass ratio motor to arrange large expansion angle changeover portion between high-pressure turbine 3, low-pressure turbine 6.Wheel hub 1, casing 2, changeover portion casing a, changeover portion support plate 40, low-pressure turbine 6, the turbine moving blade 31 of high-pressure turbine 3 and the turbine stator vane 32 of high-pressure turbine 3 in Fig. 1, have been illustrated.
The main task of large expansion angle changeover portion design is to suppress changeover portion internal flow separation, reduce flow losses, the factor that affects changeover portion internal flow is a lot, is mainly the adverse pressure gradient that high-pressure turbine 3 exit flow conditions and large expansion angle structure cause itself as depicted in figs. 1 and 2.High-pressure turbine 3 last stage movable vanes are typically designed to approach and axially give vent to anger, this design one can reduce aerodynamic loss, moreover when high-pressure turbine 3 exit flows are flowed through changeover portion support plate 40, the angle of attack of changeover portion support plate 40 leading edges changes in a very little scope, be difficult for occurring flow separation.But owing to inevitably having gap between turbine moving blade 31 and casing (runner wall) 2, therefore, at turbine moving blade 31 blade tips, exist the leakage flow from pressure side to suction surface, form tip leakage vortex.In Fig. 2, helix has illustrated changeover portion support plate 40 flow direction of air-flow around.
At least there is following technical problem in prior art:
As depicted in figs. 1 and 2, in the motor providing in prior art, tip leakage vortex has not only increased flow losses, make simultaneously air-flow off-axis that gap between turbine moving blade 31 blade tips and casing 2 flows out to, between itself and axial direction, there is axial flow angle (or weighing up stream angle), in Fig. 2, illustrated the direction 8 of the air-flow that forms this axial flow angle, in the radial height high near turbine moving blade 31 blade tips approximately 20% leaf, this flow angle off-axis is to reaching 10 ° ~ 30 °.This part fluid, when arriving changeover portion support plate 40, forms the very large angle of attack in changeover portion support plate 40 leading edges, makes changeover portion support plate 40 near a side generation flow separation of casing 2, has increased changeover portion internal flow loss, has reduced the pneumatic efficiency of motor.
Summary of the invention
The object of the invention is the turbofan engine that proposes a kind of airflow channel structure of motor and the airflow channel structure of this motor is set, solve prior art and existed changeover portion internal flow loss larger, caused the technical problem that engine air efficiency of movement is lower.
For achieving the above object, the invention provides following technological scheme:
The airflow channel structure of the motor that the embodiment of the present invention provides, comprises wheel hub, casing, turbine moving blade, support plate and rectifying device, wherein:
Described turbine moving blade is fixedly connected with described wheel hub, and has tip clearance between the blade tip of described turbine moving blade and the inwall of described casing;
Described support plate is between described wheel hub and described casing;
Described rectifying device is fixedly arranged on the described casing between described turbine moving blade and described support plate;
Described rectifying device, for carrying out rectification to suppress described air-flow described panel area generation flow separation to flowed to the air-flow of described support plate by described tip clearance.
At one alternatively in embodiment, described rectifying device comprise be fixedly connected with described casing or with described casing be at least one guide vane of integral type structure.
At one, alternatively in embodiment, described guide vane is welded on the inwall of described casing.
At one, alternatively in embodiment, described rectifying device comprises at least two guide vanes, and at least two described guide vanes are evenly distributed on described casing along the circumferential direction of described casing.
At one, alternatively in embodiment, described guide vane is of a size of 10%～30% of described turbine moving blade radial height in the radial direction at described casing.
At one alternatively in embodiment, described guide vane is of a size of 30%～80% of maximum gap size between described turbine moving blade and described support plate on described casing axial direction.
At one, alternatively in embodiment, the spacing dimension between described guide vane and described turbine moving blade on described casing axial direction is 1/10～1/5 of described turbine moving blade and the spacing dimension of described support plate on described casing axial direction.
At one, alternatively in embodiment, the spacing dimension between described guide vane and described support plate on described casing axial direction is 1/10～1/5 of described turbine moving blade and the spacing dimension of described support plate on described casing axial direction.
At one, alternatively in embodiment, the spacing dimension between described guide vane and described support plate on described casing axial direction is 1/10～2/5 of described turbine moving blade and the spacing dimension of described support plate on described casing axial direction.
At one, alternatively in embodiment, the ratio of the number of described guide vane and the number of described turbine moving blade is 1.5～5.
At one, alternatively in embodiment, described guide vane is Curved plate.
At one, alternatively in embodiment, described guide vane shape is close to turbine or compressor blade.
At one, alternatively in embodiment, described guide vane is solid construction.
At one, alternatively in embodiment, the material of described guide vane is identical with the material of the material of described turbine moving blade, described casing or the material of described support plate.
The turbofan engine that the embodiment of the present invention provides, comprises the airflow channel structure of the motor that the arbitrary technological scheme of low-pressure turbine, high-pressure turbine and the present invention provides, wherein:
Described casing is the changeover portion casing of described turbofan engine;
Described turbine moving blade is the moving vane of described high-pressure turbine;
Described support plate is the changeover portion support plate of described turbofan engine;
Described changeover portion support plate go out flow path direction towards the influent stream mouth of described low-pressure turbine.
Based on technique scheme, the embodiment of the present invention at least can produce following technique effect:
The present invention's tip clearance in turbogenerator is in inevitable situation, by rectifying device being set to carry out rectification to suppress air-flow in a panel area generation flow separation to flowed to the air-flow of support plate by tip clearance specially, thereby make through the air velocity distribution of support plate more even, when moving vane that turbine moving blade is high-pressure turbine, the off-axis that the rectifying device (being preferably the small-sized guide vane of a row) of arranging at high-pressure turbine outlet rear causes tip clearance to air-flow rectification after, this segment fluid flow has been reversed back axially, thereby reduced the air-flow angle of attack of changeover portion support plate leading edge, reduced the flow separation of changeover portion support plate annex, and make changeover portion exit flow even flow field.Due to after rectifying device rectification, the flow field of changeover portion import be improved significantly, near the flow separation of changeover portion support plate is inhibited, changeover portion pitot loss significantly reduces, thereby improve the aeroperformance of changeover portion, solve prior art and existed changeover portion internal flow loss larger, caused the technical problem that engine air efficiency of movement is lower.
Meanwhile, due to the improvement of changeover portion inlet flow conditions in turbofan engine provided by the invention, make the flow field of changeover portion outlet become more even, thereby improved the inlet air flow condition of low-pressure turbine, and then also improved the aeroperformance of low-pressure turbine.
The setting of rectifying device provided by the invention can effectively reduce the loss of changeover portion, improve the flow conditions in downstream, the preferred technical solution of the present invention has farthest reduced to the design of the factors such as the blade profile of water conservancy diversion stator, size the aerodynamic loss that guide vane itself brings.
Accompanying drawing explanation
Accompanying drawing described herein is used to provide a further understanding of the present invention, forms the application's a part, and schematic description and description of the present invention is used for explaining the present invention, does not form inappropriate limitation of the present invention.In the accompanying drawings:
Fig. 1 is a schematic diagram of the airflow channel structure of motor in prior art;
Fig. 2 is another schematic diagram of the airflow channel structure of motor in prior art;
A schematic diagram of the airflow channel structure of the motor that Fig. 3 provides for the embodiment of the present invention;
Another schematic diagram of the airflow channel structure of the motor that Fig. 4 provides for the embodiment of the present invention;
The axial flow angle of the air-flow being flowed out by tip clearance in the airflow channel structure of the motor that Fig. 5 provides for the embodiment of the present invention before rectifying device rectification with rectifying device rectification after contrast schematic diagram;
Mark in figure: 1, wheel hub; 2, casing; A, changeover portion casing; 3, high-pressure turbine; 31, turbine moving blade; 32, turbine stator vane; 4, support plate; 40, changeover portion support plate; 5, rectifying device; 6, low-pressure turbine; 8, form the direction of the air-flow at axial flow angle; 81, after rectification, axially flow angle changes line; 82, rectification front axle changes line to flow angle; 9, tip clearance.
Embodiment
Below by accompanying drawing Fig. 3～Fig. 5 and the mode of enumerating optional embodiments more of the present invention, technological scheme of the present invention (comprising optimal technical scheme) is described in further detail.It should be noted that: any technical characteristics in the present embodiment, any technological scheme is all the technical characteristics of plurality of optional or one or more in optional technological scheme, cannot exhaustive all alternative technical characteristicss of the present invention and alternative technological scheme in order to describe succinct need in presents, also the mode of execution that is not easy to each technical characteristics all emphasizes that it is one of optional numerous embodiments, so those skilled in the art should know: any technical characteristics and any technological scheme in the present embodiment all do not limit the scope of the invention, protection scope of the present invention should comprise that those skilled in the art do not pay the thinkable any alternate embodiments of creative work.
The embodiment of the present invention provides a kind of changeover portion internal flow loss of can effectively reducing, and the airflow channel structure of the higher motor of pneumatic efficiency and the turbofan engine that the airflow channel structure of this motor is set.
Below in conjunction with Fig. 3～Fig. 5, technological scheme provided by the invention is carried out to more detailed elaboration, the technological scheme of arbitrary technological means provided by the invention being replaced or two or more technological means provided by the invention being combined mutually and obtain all should be within protection scope of the present invention.
As shown in Fig. 3～Fig. 5, the airflow channel structure of the motor that the embodiment of the present invention provides, comprises wheel hub 1, casing 2, turbine moving blade 31, support plate 4 and rectifying device 5, wherein:
The present invention is in turbogenerator in the inevitable situation of tip clearance 9, by rectifying device 5 being set specially to carry out rectification and flow separation occurs to suppress air-flow at support plate 4 flowed to the air-flow of support plate 4 by tip clearance 9, thereby make through the air velocity distribution of support plate 4 more even around.
In the present embodiment rectifying device 5 comprise be fixedly connected with casing 2 or with casing 2 be at least one guide vane of integral type structure, guide vane is preferably on the inwall that is welded in casing 2.
Guide vane is not only simple in structure, lightweight, occupy little space, and be convenient to arrange, manufacture, and the flow losses that the air-flow flowing through is caused is also little.
Certainly, use other rectifying devices 5 such as baffle, swirler with the technological scheme that substitutes guide vane also within protection scope of the present invention.
In the present embodiment, rectifying device 5 comprises at least two guide vanes, and at least two guide vanes are evenly distributed on casing 2 along the circumferential direction of casing 2.
This structure can so that guide vane can rectification scope larger, the technique effect that can obtain is more outstanding, can make the air-flow of tip clearance 9 outflows in the whole circumferential direction of air-flow path all obtain rectification.
Certainly, the technological scheme that guide vane is set to non-uniform Distribution is also within protection scope of the present invention.
In the present embodiment, guide vane is of a size of 10%～30% of turbine moving blade 31 radial heights in the radial direction at casing 2.Because guide vane is exclusively used in, to flowed to the air-flow of support plate 4 by tip clearance 9, carries out rectification and at support plate 4, flow separation occurs to suppress air-flow around, so guide vane is closely related in casing 2 size in the radial direction in casing 2 size and tip clearance 9 in the radial direction, conventionally determines the radial dimension of guide vane in the scope of radial direction according to blade tip leakage flow.
Certainly, the technological scheme that guide vane is of a size of other numerical value in the radial direction at casing 2 is also within protection scope of the present invention.
In the present embodiment, guide vane is of a size of 30%～80% of maximum gap size between turbine moving blade 31 and support plate 4 on casing 2 axial directions.
The flow losses that guide vane causes the air-flow through over commutation when casing 2 axial directions are above-mentioned dimensional range are less.
Certainly, guide vane on casing 2 axial directions, be other numerical value technological scheme also within protection scope of the present invention.
In the present embodiment, between guide vane and turbine moving blade 31, the spacing dimension on casing 2 axial directions is turbine moving blade 31 and 1/10～1/5 of the spacing dimension of support plate 4 on casing 2 axial directions.
Spacing dimension between guide vane and turbine moving blade 31 on casing 2 axial directions too hour, exist turbine moving blade 31 in rotation process, to clash into the possibility of guide vane, and that this spacing dimension can cause not passing through the air-flow of guide vane rectification when too large is more, namely reveal air-flow more, so when this spacing dimension is above-mentioned numerical value, not only can avoid turbine moving blade 31 to clash into, and it is less to reveal air-flow.Certainly, the technological scheme that this spacing dimension is other numerical value is also within protection scope of the present invention.
In the present embodiment, between guide vane and support plate 4, the spacing dimension on casing 2 axial directions is turbine moving blade 31 and 1/10～1/5 of the spacing dimension of support plate 4 on casing 2 axial directions, is preferably turbine moving blade 31 and 1/10～2/5 of the spacing dimension of support plate 4 on casing 2 axial directions.The flow losses that when this spacing dimension is above-mentioned dimensional range, the air-flow through over commutation caused are less.Certainly, the technological scheme that this spacing dimension is other numerical value is also within protection scope of the present invention.
In the present embodiment, the ratio of the number of the number of guide vane and turbine moving blade 31 is 1.5～5, is preferably 2.5.
When the number of guide vane is more, the flow losses that the air-flow through over commutation is caused are larger, otherwise when number is less, more without the air-flow of over commutation, rectification effect is not ideal enough.When the ratio of the number of guide vane and the number of turbine moving blade 31 is above-mentioned scope, can guarantee that under rectification effect ideal situation, the flow losses that the air-flow through over commutation is caused are less.
In the present embodiment, guide vane is Curved plate.Blade shape is preferably and adopts turbine or compressor blade blade profile, and the loss that this blade shape produces air-flow is less, has good water conservancy diversion effect simultaneously.
In the present embodiment, guide vane can be solid construction.Solid construction intensity is higher, and and casing 2 between connection area larger.
Certainly, guide vane is hollow-core construction, or part area is that solid construction part area is that the technological scheme of hollow-core construction is also within protection scope of the present invention.
In the present embodiment, the material of guide vane is identical with the material of the material of turbine moving blade 31, the material of casing 2 or support plate 4.It is identical with the material of casing 2 that the material of guide vane is preferably, and now, when guide vane is connected with the mode of the use welding of casing 2, formed linkage structure is more firm.
Certainly, guide vane and casing 2 for example, by the technological scheme of removably connect structure or other Placements (bonding) also within protection scope of the present invention.
As shown in Fig. 3～Fig. 5, the turbofan engine that the embodiment of the present invention provides, comprises the airflow channel structure of the motor that low-pressure turbine 6, high-pressure turbine 3 and the arbitrary technological scheme of the present invention provide, wherein:
The changeover portion casing a that casing 2 is turbofan engine.
The changeover portion support plate that support plate 4 is turbofan engine.
Changeover portion support plate go out flow path direction towards the influent stream mouth of low-pressure turbine 6.
In Fig. 3, also illustrated: turbine stator vane 32.
The rectifying device 5(that high-pressure turbine 3 outlet rears are arranged is preferably the small-sized guide vane of a row) off-axis that can cause tip clearance 9 to air-flow carry out rectification, this segment fluid flow is reversed back axially, thereby the axial flow angle that has suppressed as shown in Figure 5 the air-flow that flowed out by tip clearance, Fig. 4 has illustrated the direction 8 that forms the air-flow at axial flow angle, from Fig. 5, after rectification, axially flow angle change line 81 and rectification front axle can be found out to flow angle change line 82: the height of the radial direction along turbine moving blade 31 blades compared with the axial flow angle of high position obviously than rectification before the axial flow angle of same position little, reduced thus the air-flow angle of attack of changeover portion support plate leading edge, reduced the flow separation of changeover portion support plate annex, and make changeover portion exit flow flow field more even.Due to after rectifying device 5 rectifications, the flow field of changeover portion import be improved significantly, near flow separation changeover portion support plate is inhibited, changeover portion pitot loss significantly reduces, thereby improves the aeroperformance of changeover portion.
Certainly, in the airflow channel structure of motor provided by the invention, turbine moving blade 31 can be also the moving vane of low-pressure turbine 6.The airflow channel structure of motor provided by the invention also can be applied in other motors or mechanical device outside turbofan engine.
The disclosed arbitrary technological scheme of the invention described above unless otherwise stated, if it discloses number range, so disclosed number range is preferred number range, any it should be appreciated by those skilled in the art: preferred number range is only the obvious or representative numerical value of technique effect in many enforceable numerical value.Because numerical value is more, cannot be exhaustive, so the present invention just discloses part numerical value to illustrate technological scheme of the present invention, and the above-mentioned numerical value of enumerating should not form the restriction to the invention protection domain.
Simultaneously, if the invention described above discloses or has related to component or the structural member of connection fastened to each other, so, unless otherwise stated, being fixedly connected with (or title sets firmly, is connected) can be understood as: can dismantle and be fixedly connected with (for example using bolt or screw to connect), also can be understood as: non-removable being fixedly connected with (for example rivet, weld), certainly, connection fastened to each other also can for example, be replaced (obviously cannot adopt except integrally formed technique) by integral type structure (use casting technique is integrally formed to be created).
In addition, in the disclosed arbitrary technological scheme of the invention described above applied for the term that represents position relationship or shape unless otherwise stated its implication comprise and its approximate, similar or approaching state or shape.Arbitrary parts provided by the invention can be both to be assembled by a plurality of independent constituent elements, the produced separate part of the technique that also can be one of the forming.
Finally should be noted that: above embodiment is only in order to illustrate that technological scheme of the present invention is not intended to limit; Although the present invention is had been described in detail with reference to preferred embodiment, those of ordinary skill in the field are to be understood that: still can modify or part technical characteristics is equal to replacement the specific embodiment of the present invention; And not departing from the spirit of technical solution of the present invention, it all should be encompassed in the middle of the technological scheme scope that the present invention asks for protection.
Claims (12)
1. an airflow channel structure for motor, is characterized in that, comprises wheel hub, casing, turbine moving blade, support plate and rectifying device, wherein:
Described turbine moving blade is fixedly connected with described wheel hub, and has tip clearance between the blade tip of described turbine moving blade and the inwall of described casing;
Described support plate is between described wheel hub and described casing;
Described rectifying device is fixedly arranged on the described casing between described turbine moving blade and described support plate;
Described rectifying device, for carrying out rectification to suppress described air-flow described panel area generation flow separation to flowed to the air-flow of described support plate by described tip clearance.
2. the airflow channel structure of motor according to claim 1, is characterized in that, described rectifying device comprise be fixedly connected with described casing or with described casing be at least one guide vane of integral type structure.
3. the airflow channel structure of motor according to claim 2, is characterized in that, described guide vane is welded on the inwall of described casing.
4. the airflow channel structure of motor according to claim 2, is characterized in that, described rectifying device comprises at least two guide vanes, and at least two described guide vanes are evenly distributed on described casing along the circumferential direction of described casing.
5. the airflow channel structure of motor according to claim 4, is characterized in that, described guide vane is of a size of 10%～30% of described turbine moving blade radial height in the radial direction at described casing.
6. the airflow channel structure of motor according to claim 2, is characterized in that, described guide vane is of a size of 30%～80% of maximum gap size between described turbine moving blade and described support plate on described casing axial direction.
7. the airflow channel structure of motor according to claim 2, it is characterized in that, the spacing dimension between described guide vane and described turbine moving blade on described casing axial direction is 1/10～1/5 of described turbine moving blade and the spacing dimension of described support plate on described casing axial direction.
8. the airflow channel structure of motor according to claim 2, it is characterized in that, the spacing dimension between described guide vane and described support plate on described casing axial direction is 1/10～1/5 of described turbine moving blade and the spacing dimension of described support plate on described casing axial direction.
9. the airflow channel structure of motor according to claim 2, is characterized in that, the ratio of the number of described guide vane and the number of described turbine moving blade is 1.5～5.
10. the airflow channel structure of motor according to claim 2, is characterized in that, described guide vane is Curved plate.
The airflow channel structure of 11. motors according to claim 2, is characterized in that, described guide vane is solid construction;
The material of described guide vane is identical with the material of the material of described turbine moving blade, described casing or the material of described support plate.
12. 1 kinds of turbofan engines, is characterized in that, comprise the airflow channel structure of the arbitrary described motor of low-pressure turbine, high-pressure turbine and claim 1-11, wherein:
Described casing is the changeover portion casing of described turbofan engine;
Described turbine moving blade is the moving vane of described high-pressure turbine;
Described support plate is the changeover portion support plate of described turbofan engine;
Described changeover portion support plate go out flow path direction towards the influent stream mouth of described low-pressure turbine.
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| CN201210380591.0A CN103711608B (en) | 2012-10-09 | 2012-10-09 | The airflow channel structure of electromotor and fanjet |
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| CN201210380591.0A CN103711608B (en) | 2012-10-09 | 2012-10-09 | The airflow channel structure of electromotor and fanjet |
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| CN105179028A (en) * | 2015-04-22 | 2015-12-23 | 北京航空航天大学 | Turbine back-bearing-force casing and gate-leaf integrated structure |
| CN105927584A (en) * | 2016-04-25 | 2016-09-07 | 西北工业大学 | Axial-flow compressor rotor with flow-guiding small blades |
| CN111794808A (en) * | 2020-06-24 | 2020-10-20 | 中船重工龙江广瀚燃气轮机有限公司 | First-stage large meridian expansion guider casing of power turbine for fuel-drive compressor unit |
| CN115450701A (en) * | 2022-11-01 | 2022-12-09 | 上海交通大学 | Radial flow turbine blade vibration suppression flow control method based on wall surface grooving treatment |
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| CN105927584A (en) * | 2016-04-25 | 2016-09-07 | 西北工业大学 | Axial-flow compressor rotor with flow-guiding small blades |
| CN111794808A (en) * | 2020-06-24 | 2020-10-20 | 中船重工龙江广瀚燃气轮机有限公司 | First-stage large meridian expansion guider casing of power turbine for fuel-drive compressor unit |
| CN115450701A (en) * | 2022-11-01 | 2022-12-09 | 上海交通大学 | Radial flow turbine blade vibration suppression flow control method based on wall surface grooving treatment |
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| Publication number | Publication date |
|---|---|
| CN103711608B (en) | 2016-07-13 |
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Address after: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee after: China Hangfa commercial aviation engine limited liability company 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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