CN109973244A - From driving by-pass air duct to change shape flabellum compression set - Google Patents
From driving by-pass air duct to change shape flabellum compression set Download PDFInfo
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- CN109973244A CN109973244A CN201910391377.7A CN201910391377A CN109973244A CN 109973244 A CN109973244 A CN 109973244A CN 201910391377 A CN201910391377 A CN 201910391377A CN 109973244 A CN109973244 A CN 109973244A
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- air duct
- pass air
- flabellum
- rotating member
- duct
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- 241000883990 Flabellum Species 0.000 title claims abstract description 61
- 230000008859 change Effects 0.000 title claims abstract description 19
- 230000006835 compression Effects 0.000 title claims abstract description 17
- 238000007906 compression Methods 0.000 title claims abstract description 17
- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 35
- 244000126211 Hericium coralloides Species 0.000 claims description 3
- 230000008901 benefit Effects 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 7
- 230000003044 adaptive effect Effects 0.000 description 3
- 230000007246 mechanism Effects 0.000 description 3
- 230000008450 motivation Effects 0.000 description 2
- 238000005457 optimization Methods 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000001141 propulsive effect Effects 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/072—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with counter-rotating, e.g. fan rotors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/075—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type controlling flow ratio between flows
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/077—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The device more particularly to fanjet by-pass air duct continuously adjusted the present invention relates to fanjet bypass ratio is to a turn fan ring compression set.It is a kind of to drive by-pass air duct to change shape flabellum compression set certainly, main duct including engine, being set to the duct on the outside of the main duct is third by-pass air duct, it is equipped in the inlet guide vane in third by-pass air duct and between stator blade two rows of to turning rotating member, two rows are respectively upstream rotating member and downstream rotating member to rotating member is turned, and upstream rotating member and downstream rotating member pass through turntable bearing respectively and be arranged on the duct casing of third by-pass air duct.Present invention employs two rows to turning fan ring structure, make third by-pass air duct pressure ratio and flow at identical conditions, the revolving speed of rotor structure is effectively reduced and reduces third by-pass air duct size, to reduce noise, power consumption and design difficulty, the working range for expanding turbofan significantly larger plays the change circulation advantage of this type of engine.
Description
Technical field
The device more particularly to fanjet by-pass air duct continuously adjusted the present invention relates to fanjet bypass ratio to turn
Fan ring compression set.
Background technique
One Typical requirements of next-generation aviation gas turbine Duct-Burning Turbofan are to become circulation.Variable cycle engine is by changing
Become geometry, size and the position of certain components and realize the change of the loop parameters such as pressure ratio, flow and bypass ratio, makes to send out
Motivation has optimal performance under various working conditions, so that flying height and Mach number to aircraft etc. has good adaptation
Property.
The U.S. patent Nos US4043121 of Thomas et al., topic are " birotor variable cycle engines ", are disclosed
A kind of engine of band blade tip fan (Flade) controls air by adjusting the adjustable vane outside blade tip fan in duct
Flow realizes the changeability of cycle of engine.
In United States Patent (USP) US005809772A, a kind of double outer culverts of band core engine driving fan (CDFS) configuration are disclosed
Variable cycle engine.It is that fan is divided into front/rear two parts with the main distinction of the conventional single duct fanjet in structure,
Leading portion fan is driven by low-pressure turbine shaft, and back segment fan is connected in high-pressure shaft, and back segment fan is core engine driving fan, preceding/
Rear fan respectively has a by-pass air duct.Pass through the preposition area of duct after the model selection valve and CDFS in duct after leading portion fan
Adjustable injector (VABI), which is adjusted, makes engine all have optimal bypass ratio in wide working range.
In United States Patent (USP) US20100180572A1, discloses while containing turbofan outside three with CDFS and Flade configuration
Engine, contain outside third in blade tip fan by the direct-connected driving of main duct fan blade, configure in motor head.Chinese patent
CN1619129A discloses the engine of tail Flade blade tip fan, wherein Flade blade tip fan and low-pressure turbine movable vane or
The connection of free turbine blade, configures in engine rear end.Contain turbofan outside this type three also referred to as adaptively to follow
Ring engine or intelligent engine.Increased third by-pass air duct, the flow path not only may be used on the basis of double outer culvert variable cycle engines
To increase the bypass ratio adjustable range of engine, optimize the flow matches of air inlet/engine, it may also be used for high energy weapon heat pipe
The effects of managing and be stealthy.
Since by-pass air duct Flade blade tip fan and inner duct blade use direct-connected mode, designs and bring for engine
It is many unfavorable: one is blade strength difficult design, limits the tangential velocity selection of blade；The second is being of coupled connections makes to control
System is more complicated, and the freedom degree of adjusting becomes smaller, and is unfavorable for the expansion of engine working range；The third is the performance of each duct is not
It can take into account, significantly limit more duct engines and play change circulation advantage.
Summary of the invention
It is a kind of using rotor and to a turn fan rotor it is an object of the invention to avoid the deficiencies in the prior art from providing
Blade integrated design, compact-sized, controlling mechanism independently, with main duct system mechanics decouples, and adjusts the big electricity of freedom degree
The by-pass air duct of Magnetic driving is to change shape flabellum compressibility.
To achieve the above object, the technical scheme adopted by the invention is as follows: it is a kind of from driving by-pass air duct to change shape flabellum pressure
Compression apparatus, the main duct including engine, the duct being set on the outside of the main duct is third by-pass air duct, in third by-pass air duct
Two rows are equipped between interior inlet guide vane and stator blade to rotating member is turned, two rows are respectively upstream to rotating member is turned
Rotating member and downstream rotating member, upstream rotating member and downstream rotating member are arranged outside third by turntable bearing respectively
On the duct casing of duct.
Further, it is described it is two rows of include upstream flabellum and downstream flabellum to rotating member is turned, upstream flabellum and downstream
Flabellum is separately positioned on two ring holder inner walls, and the ring holder has inside and outside wall, outside ring holder
Wall is equipped with calutron；Ring holder is arranged on the outer casing of third by-pass air duct by a pair of of turntable bearing, and described
Motor stator is additionally provided on the corresponding outer casing of calutron；The magnetic pole of the calutron and motor stator circumferentially array
Arrangement, calutron are opposite with the polarity of motor stator.The rotation that the upstream flabellum and ring holder, calutron form
Component is upstream rotating member, and the rotating member that the downstream flabellum and ring holder, calutron form is downstream rotation
Component.
Further, the bearing clearance of the turntable bearing is less than tip clearance, and tip clearance refers to upstream flabellum under
Swim the interior casing gap of flabellum and third by-pass air duct.
Further, it is described it is two rows of include upstream flabellum and downstream flabellum to rotating member is turned, upstream flabellum and downstream
Flabellum is separately positioned on two ring holder outer walls, and the ring holder has inside and outside wall, in ring holder
Wall is equipped with calutron；Ring holder is arranged on the interior casing of third by-pass air duct by a pair of of turntable bearing, and described
It is additionally provided with motor stator on the corresponding interior casing of calutron, the magnetic pole of the calutron and motor stator circumferentially array
Arrangement, calutron are opposite with the polarity of motor stator.The rotation that the upstream flabellum and ring holder, calutron form
Component is upstream rotating member, and the rotating member that the downstream flabellum and ring holder, calutron form is downstream rotation
Component.
Further, the bearing clearance of the turntable bearing is less than tip clearance, and tip clearance refers to upstream flabellum under
Swim the outer casing gap of flabellum and third by-pass air duct.
Further, the calutron is permanent magnet or motor-spin-coil.
Further, the turntable bearing is cylinder roller bearing.
Further, guide vane cooperation is two rows of to the progress setting angle adjustment of rotating member revolving speed is turned, and makes institute
The upstream flabellum for stating upstream rotating member obtains the optimal incoming flow angle of attack.
Further, described to be equipped with comb tooth to the gap turned between rotating member and casing, labyrinth gas seals reduce air
Leakage flow.
Further, the flow of the third by-pass air duct changes in the range of 0~60% complete machine flow；The third
When outer culvert flow is 0, contains outside third and be in close state, aircraft is in supersonic cruising or maneuvering condition at this time；When outside third
When culvert flow is 60% complete machine flow, engine is in the state of big bypass ratio, i.e. aircraft is in subsonics cruising condition.In reality
In-flight, flow can be contained outside third by adjusting come so that engine meets working performance requirement.
The beneficial effects of the present invention are: present invention employs two rows to fan ring structure is turned, third by-pass air duct pressure ratio can be made
At identical conditions with flow, be effectively reduced rotor structure revolving speed and reduce third by-pass air duct size, thus reduce noise,
Power consumption and design difficulty.Third by-pass air duct can be improved under identical revolving speed to the fan ring structure turned using two rows
Pressure ratio and flow, and downstream is made, closer to axial direction, circumferential direction to be effectively reduced to the flow angle rotated at means outlet
Speed, it might even be possible to cancelling guide vane.
It is different from traditional by-pass air duct Flade blade tip fan, present invention employs rotor and to a turn fan ring flabellum one
Bodyization design forms by-pass air duct that translator independently drives to a fan ring compressibility is turned, and has that compact-sized, controlling mechanism is only
The features such as vertical, with the decoupling of main duct system mechanics, can be realized continuously adjusting on a large scale for engine bypass ratio, effectively optimization hair
The matching of motivation and air intake duct reduces or even eliminates spillage drag, expands the working range of turbofan significantly, is applicable in
In performance requirement is high, working range is wide, more duct fan gas turbine engines more than operating mode, becomes circulating gas turbine wind
Fan engine, adaptive cycle engine and intelligent engine can larger play the change circulation advantage of this type of engine.
The present invention realizes individual motor driving, so that controlling mechanism is independent, has bigger adjusting freedom degree；In not increasing
The design difficulty of duct blade；It can be configured at the axially different position in by-pass air duct according to the topology layout feature of engine, it is real
Existing structural layout optimization.Meanwhile multiple-working mode selection is realized, it can satisfy aircraft and add in subsonic speed cruise, transonic speed
To engine high performance requirements under the multi-states such as speed and supersonic cruising.In low power states such as aircraft subsonic speed cruises, start
Machine model selection valve and front/rear adjustable area culvert channel injector are opened, and third by-pass air duct works in high revolving speed fan ring is turned
Operating condition, engine are run with big bypass ratio state, and engine propulsive efficiency is higher at this time, fuel consumption rate is lower.It is climbed in aircraft
Under the high power operating condition of liter, acceleration and supersonic flight, engine turns down each VABI, and more air is promoted to enter core engine
Interior, adaptive cycle engine operates in thrust priority status.
Detailed description of the invention
Fig. 1 is that have adaptive variable cycle engine general structure schematic diagram of the invention；
Fig. 2 is the front enlarged structure schematic diagram of engine overall structure in Fig. 1；
Fig. 3 is the rear portion enlarged structure schematic diagram of engine overall structure in Fig. 1；
Fig. 4 is the structural schematic diagram of the embodiment of the present invention 1；
Fig. 5 is the composed structure schematic diagram of ring holder, flabellum and calutron in embodiment 1；
Fig. 6 is the structural schematic diagram of the embodiment of the present invention 2；
Fig. 7 is the composed structure schematic diagram of ring holder, flabellum and calutron in embodiment 2.
Specific embodiment
The principle and features of the present invention will be described below with reference to the accompanying drawings, and the given examples are served only to explain the present invention, and
It is non-to be used to limit the scope of the invention.
Embodiment 1: as shown in figure 1, figure 2, figure 3, figure 4 and figure 5, a kind of to be filled from driving by-pass air duct annular to flabellum compression is turned
It sets, is equipped with inside, centre, three, outside runner at 12 rear portion of conventional fan, interior side runner is connected with core engine driving fan 13
Logical, intermediate flow channel is connected with the entrance of the second by-pass air duct 14, and outer side runner is connected with the entrance of the first by-pass air duct 8, and second
The outlet of by-pass air duct 14 is connected by preceding variable area culvert channel injector 9 with the first by-pass air duct 8, in entering for the first by-pass air duct 8
Model selection valve 6 is additionally provided at mouthful；13 rear portion of core engine driving fan be the inside, two, outside annular channel,
The interior annular runner is connected with high-pressure compressor 15, and the intermediate annular runner is connected with the second by-pass air duct 14
It is logical, it is sequentially communicated at 15 rear portion of high-pressure compressor equipped with combustion chamber 10, high-pressure turbine 16, low-pressure turbine 17；Outside described second
The exit of duct 14, as engine tail portion, are equipped with inside and outside two runners, and inner flow passage passes through rear variable area duct injection
Device 11 is connected with the outlet of main duct, and outer flow passage is connected with the outlet of third by-pass air duct 7.Third by-pass air duct 7 is arranged in institute
The outside for stating main duct is equipped with two rows of to rotating between the inlet guide vane 1 in third by-pass air duct 7 and stator blade 5
Component, two rows of is respectively upstream rotating member and downstream rotating member to rotating member is turned, and upstream rotating member and downstream rotate
Component passes through turntable bearing 20 respectively and is arranged on the duct casing of third by-pass air duct 7.
It is described it is two rows of include upstream flabellum 4 and downstream flabellum 21 to rotating member is turned, upstream flabellum 4 and downstream flabellum 21
It is separately positioned on two 18 inner walls of ring holder, the ring holder 18 has inside and outside wall, in ring holder 18
Outer wall is equipped with calutron 19；Ring holder is arranged on the outer casing of third by-pass air duct 7 by a pair of of turntable bearing, with
Motor stator 3 is additionally provided on the corresponding outer casing of the calutron；The equal edge of magnetic pole of the calutron 19 and motor stator 3
Circumferential array arrangement, calutron 19 are opposite with the polarity of motor stator 3.The calutron 19 is that permanent magnet or motor turn
Subcoil.The bearing clearance of the turntable bearing 20 is less than tip clearance, and tip clearance refers to upstream flabellum 4 and downstream flabellum 21
With the interior casing gap of third by-pass air duct 7.The guide vane 1 cooperates two rows to carry out setting angle to rotating member revolving speed is turned
Adjustment, makes the upstream flabellum 4 of the upstream rotating member obtain the optimal incoming flow angle of attack.
Described is equipped with comb tooth to the gap turned between rotating member and casing, and labyrinth gas seals reduce air leakage flow.
The flow of the third by-pass air duct 7 changes in the range of 0~60% complete machine flow；When culvert flow is 0 outside the third, the
Contain outside three and be in close state, aircraft is in supersonic cruising or maneuvering condition at this time, compared with double duct engine operations
State；When containing flow outside third is 60% complete machine flow, engine is in the state of big bypass ratio, i.e. aircraft is patrolled in subsonics
Boat state.In practical flight, flow can be contained outside third by adjusting come so that engine meets working performance requirement.
Embodiment 2: it is as shown in Figure 6, Figure 7, same as Example 1, unlike: it is described two rows of to turning rotating member packet
Upstream flabellum 4 and downstream flabellum 21 are included, upstream flabellum 4 and downstream flabellum 21 are separately positioned on two 18 outer walls of ring holder
On, the ring holder 18 has inside and outside wall, and calutron 19 is equipped on 18 inner wall of ring holder；Annular brace
Frame 18 passes through a pair of of turntable bearing 20 and is arranged on the interior casing of third by-pass air duct 7, interior casing corresponding with the calutron
On be additionally provided with motor stator 3, the magnetic pole of the calutron 19 and motor stator 3 circumferentially array arrangement, calutron 19
It is opposite with the polarity of motor stator 3.The bearing clearance of the turntable bearing be less than tip clearance, tip clearance refer to flabellum 4 with
The outer casing gap of third by-pass air duct 7.
The foregoing is merely presently preferred embodiments of the present invention, is not intended to limit the invention, it is all in spirit of the invention and
Within principle, any modification, equivalent replacement, improvement and so on be should all be included in the protection scope of the present invention.
Claims (10)
1. a kind of by-pass air duct of driving certainly is to change shape flabellum compression set, which is characterized in that the main duct including engine, setting
Duct on the outside of the main duct is third by-pass air duct, in the inlet guide vane in third by-pass air duct and between stator blade
Equipped with two rows to rotating member is turned, two rows of is respectively upstream rotating member and downstream rotating member, upstream rotation to rotating member is turned
Turn component and downstream rotating member passes through turntable bearing respectively and is arranged on the duct casing of third by-pass air duct.
2. the by-pass air duct of driving certainly as described in claim 1 is to change shape flabellum compression set, which is characterized in that the two rows
It include upstream flabellum and downstream flabellum to rotating member is turned, upstream flabellum and downstream flabellum are separately positioned on two ring holders
On inner wall, the ring holder has inside and outside wall, and calutron is equipped on ring holder outer wall；Ring holder
It is arranged on the outer casing of third by-pass air duct by a pair of of turntable bearing, is additionally provided on outer casing corresponding with the calutron
Motor stator；The magnetic pole of the calutron and motor stator circumferentially array arrangement, the pole of calutron and motor stator
Property is opposite.
3. the by-pass air duct of driving certainly as claimed in claim 2 is to change shape flabellum compression set, which is characterized in that the turntable
The bearing clearance of bearing is less than tip clearance, and tip clearance refers between upstream flabellum and downstream flabellum and the interior casing of third by-pass air duct
Gap.
4. the by-pass air duct of driving certainly as described in claim 1 is to change shape flabellum compression set, which is characterized in that the two rows
It include upstream flabellum and downstream flabellum to rotating member is turned, upstream flabellum and downstream flabellum are separately positioned on two ring holders
On outer wall, the ring holder has inside and outside wall, and calutron is equipped on ring holder inner wall；Ring holder
It is arranged on the interior casing of third by-pass air duct by a pair of of turntable bearing, is additionally provided on interior casing corresponding with the calutron
Motor stator, the magnetic pole of the calutron and motor stator circumferentially array arrangement, the pole of calutron and motor stator
Property is opposite.
5. the by-pass air duct of driving certainly as claimed in claim 4 is to change shape flabellum compression set, which is characterized in that the turntable
The bearing clearance of bearing is less than tip clearance, and tip clearance refers between upstream flabellum and downstream flabellum and the outer casing of third by-pass air duct
Gap.
6. the by-pass air duct of driving certainly as described in claim 2 to 5 is any is to change shape flabellum compression set, which is characterized in that institute
The calutron stated is permanent magnet or motor-spin-coil.
7. the by-pass air duct of driving certainly as described in claim 2 to 5 is any is to change shape flabellum compression set, which is characterized in that institute
The turntable bearing stated is cylinder roller bearing.
8. the by-pass air duct of driving certainly as described in claim 2 to 5 is any is to change shape flabellum compression set, which is characterized in that institute
The guide vane cooperation stated is two rows of to the progress setting angle adjustment of rotating member revolving speed is turned, and makes the upstream of the upstream rotating member
Flabellum obtains the optimal incoming flow angle of attack.
9. it is as described in claim 1 from driving by-pass air duct to change shape flabellum compression set, which is characterized in that it is described to turning
Gap between rotating member and casing is equipped with comb tooth, and labyrinth gas seals reduce air leakage flow.
10. the by-pass air duct of driving certainly as described in claim 1,2,3,4,5,9 is any is to change shape flabellum compression set, feature
It is, the flow of the third by-pass air duct changes in the range of 0~60% complete machine flow；Containing flow outside the third is 0
When, third is contained outside to be in close state, and aircraft is in supersonic cruising or maneuvering condition at this time；It is 60% when containing flow outside third
When complete machine flow, engine is in the state of big bypass ratio, i.e. aircraft is in subsonics cruising condition.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910391377.7A CN109973244B (en) | 2019-05-12 | 2019-05-12 | Self-driven outer duct counter-rotating annular fan blade compression device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910391377.7A CN109973244B (en) | 2019-05-12 | 2019-05-12 | Self-driven outer duct counter-rotating annular fan blade compression device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109973244A true CN109973244A (en) | 2019-07-05 |
| CN109973244B CN109973244B (en) | 2024-07-05 |
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| CN201910391377.7A Active CN109973244B (en) | 2019-05-12 | 2019-05-12 | Self-driven outer duct counter-rotating annular fan blade compression device |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111237084A (en) * | 2020-02-17 | 2020-06-05 | 王镇辉 | Electric-driven jet aircraft engine and aircraft |
| CN111561392A (en) * | 2020-05-11 | 2020-08-21 | 中国航发沈阳发动机研究所 | Intermediary cartridge receiver structure |
| CN111594316A (en) * | 2020-05-11 | 2020-08-28 | 中国航发沈阳发动机研究所 | Intermediary cartridge receiver assembly |
| CN112583200A (en) * | 2020-11-19 | 2021-03-30 | 浙江京惠机电有限公司 | Rotor and fan blade integrated structure of outer rotor motor |
| CN113565649A (en) * | 2021-08-16 | 2021-10-29 | 中国科学院工程热物理研究所 | Three-duct ACE engine with Flade fan and core machine driving fan stages |
| CN114087088A (en) * | 2020-08-24 | 2022-02-25 | 中国航发商用航空发动机有限责任公司 | Aeroengine test casing and aeroengine test system |
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