CN115523054A - Double-runner fan structure with adjustable inner and outer culvert guide vanes and aero-engine - Google Patents
Double-runner fan structure with adjustable inner and outer culvert guide vanes and aero-engine Download PDFInfo
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- CN115523054A CN115523054A CN202211258112.8A CN202211258112A CN115523054A CN 115523054 A CN115523054 A CN 115523054A CN 202211258112 A CN202211258112 A CN 202211258112A CN 115523054 A CN115523054 A CN 115523054A
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- 230000006835 compression Effects 0.000 abstract description 3
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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
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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
- F02K3/075—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
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Abstract
The invention discloses a double-flow-channel fan structure with adjustable inner and outer culvert guide vanes and an aero-engine, wherein the double-flow-channel fan structure comprises a casing assembly, an inlet flow adjusting assembly, a double-flow-channel fan disc and an outlet rectifying assembly; the inlet flow regulating assembly is used for regulating the flow entering the inner duct and the outer duct; the double-channel fan disc is used for dividing airflow into inner bypass airflow and outer bypass airflow; the outlet rectification assembly is used for respectively rectifying the outlet airflows of the inner duct and the outer duct. The invention provides a compression part structure of an aero-engine, which realizes independent control of internal and external culvert runner flow by using a single rotor, and has a simple structure; the single rotor has no rotating speed matching problem, and the flow state in the inner and outer ducts can be independently controlled; the bypass flow has a larger adjusting range; in the limit, the inner duct flow only vortex shaft mode can be achieved by fully closing the outer duct vane angle; the air current between two ducts can not mutual interference, can guarantee to flow stably.
Description
Technical Field
The invention relates to the technical field, in particular to a double-flow-channel fan structure with adjustable inner and outer culvert guide vanes and an aero-engine.
Background
Among the aircraft engines, the engines commonly used are turboshaft engines and turbofan engines. The helicopter provided with the turboshaft engine is limited by factors such as resistance, engine power, backward blade airflow separation, forward blade shock wave, noise and the like, so that the requirement of high-speed running cannot be met. And the fixed wing aircraft provided with the turbofan engine can still keep high propulsion efficiency in the high-speed running process.
In order to enable the aircraft to realize hovering and extremely-low-speed advancing and high-speed advancing with high propelling efficiency, the advantages of the turboshaft and turbofan engine are integrated, and the engine can be designed into a combined mode of the turboshaft and the turbofan to meet the wider working requirement of the aircraft. In order to realize the combined mode of the turboshaft and the turbofan, the engine needs to be designed into a double-duct structure, so that the exhaust parameter control of different ducts is realized.
In the prior art, a conventional double-duct scheme is mainly realized through a double-rotor system, and the purpose of controlling the flow rate of different ducts is achieved through controlling the rotating speed of different rotors. As shown in fig. 1, a conventional double-duct includes an outer casing 1, a fan disc rotor 2, an inner casing 3, and a compressor rotor 4, a flow passage is divided into an inner duct and an outer duct by the outer casing 1 and the inner casing 3, the fan disc rotor 1 and the compressor rotor 2 are two independent rotating components, and flow rates and other flow parameters of the inner duct and the outer duct are adjusted by controlling a rotation speed.
However, such a dual duct structure requires the use of a dual rotor structure system, which increases the structural complexity and difficulty of implementation; the rotation speed of the double-rotor system is difficult to match, and the flow control of the inner duct and the outer duct is difficult to realize independently; in addition, the flow regulating range of the outer duct is limited, and the vortex shaft mode of zero flow of the outer duct cannot be realized; besides, the air flows of the inner culvert and the outer culvert are communicated with each other, so that the possibility of mutual influence of the air flows of the inner culvert and the outer culvert exists. Both of these factors greatly affect the performance of the engine.
Disclosure of Invention
The invention mainly aims to provide a double-flow-channel fan structure with adjustable inner and outer culvert guide vanes and an aero-engine, aiming at reducing the complexity of the structure, realizing independent pressurization and rectification of the inner and outer culverts, realizing independent control of the flow of the inner and outer culverts and realizing a zero-flow vortex shaft mode of the outer culvert, and avoiding mutual interference of air flows of the inner and outer culverts so as to improve the performance of the engine.
In order to achieve the above object, the present invention provides a double-flow fan structure with adjustable inner and outer culvert guide vanes, comprising:
a casing assembly formed with an inner duct and an outer duct;
an inlet flow regulating assembly mounted on the casing assembly at the inlet of the inner duct and the outer duct for regulating the flow into the inner duct and the outer duct; and
a double-flow fan disc rotatably disposed in the inner duct and the outer duct to divide an air flow into an inner duct air flow and an outer duct air flow and to flow in the inner duct and the outer duct, respectively, when rotating; and
and the outlet rectification component is arranged on the casing component and is positioned at the outlets of the inner duct and the outer duct so as to be used for respectively rectifying the outlet airflow of the inner duct and the outlet airflow of the outer duct.
Optionally, the casing assembly includes a first casing, a second casing and a third casing, and the first casing, the second casing and the third casing are sequentially disposed at intervals from inside to outside and form the inner duct and the outer duct.
Optionally, the second casing and the third casing are connected by a support plate, and the support plate is arranged in a hollow manner.
Optionally, the inlet flow regulating assembly comprises:
the device comprises a first casing, a second casing, a support plate, a culvert inlet guide vane, a culvert outlet guide vane and a culvert inlet guide vane, wherein one end of the culvert inlet guide vane is rotatably arranged on the first casing, the other end of the culvert inlet guide vane passes through the second casing and penetrates through the support plate to be rotatably arranged on the third casing, and the culvert inlet guide vane is arranged in the culvert and is used for adjusting the flow entering the culvert by changing the angle of the vane; and
the inlet guide vane of the culvert is arranged in the outer duct to adjust the flow entering the outer duct by changing the angle of the blade.
Optionally, the double-flow-channel fan disc comprises a disc body, and an inner culvert blade, a splitter cone and an outer culvert blade which are arranged on the disc body and sequentially connected from inside to outside; the flow dividing cone is arranged between the inner duct and the outer duct and is used for dividing airflow into inner duct airflow and outer duct airflow; the culvert blades are arranged in the culvert and used for adjusting the airflow of the culvert; the bypass blade is arranged in the bypass and used for adjusting the airflow of the bypass.
Optionally, two sides of the diverging cone are respectively sealed against the second casing and the outlet rectification assembly.
Optionally, both sides of the flow-dividing cone are provided with sealing elements, and the sealing elements are sealing labyrinth teeth or sealing brush wires so as to respectively abut against the second casing and the outlet rectifying assembly in the rotating process.
Optionally, the casing assembly further comprises a fourth casing, the fourth casing being flush-connected with the third casing.
Optionally, the outlet fairing assembly comprises an inner culvert fairing ring, outer culvert outlet fairing blades and an inner culvert outlet guide vane ring; the culvert rectifier ring is arranged on the culvert outlet guide vane inner ring and is arranged in the culvert so as to rectify outlet airflow of the culvert by setting blade angles; two ends of the outer culvert outlet rectifying blade are respectively and rotatably arranged on the fourth casing and the inner ring of the outer culvert outlet guide vane, and the inner ring of the outer culvert outlet guide vane is adjacent to the double-runner fan disc; the bypass outlet rectifying blade is used for rectifying the outlet airflow of the bypass by changing the blade angle.
In order to achieve the above object, the present invention further provides an aircraft engine, including the dual-flow fan structure with adjustable inner and outer culvert guide vanes, where the dual-flow fan structure with adjustable inner and outer culvert guide vanes includes:
the casing assembly is provided with an inner duct and an outer duct;
an inlet flow regulating assembly mounted on the casing assembly at the inlet of the inner duct and the outer duct for regulating the flow into the inner duct and the outer duct; and
a double-flow fan disc rotatably disposed in the inner duct and the outer duct to divide an air flow into an inner duct air flow and an outer duct air flow and to flow in the inner duct and the outer duct, respectively, when rotating; and
and the outlet rectification component is arranged on the casing component and is positioned at the outlets of the inner duct and the outer duct so as to be used for respectively rectifying the outlet airflow of the inner duct and the outlet airflow of the outer duct.
In the technical scheme of the invention, the double-flow-channel fan structure with adjustable inner and outer culvert guide vanes comprises a casing assembly, an inlet flow adjusting assembly, a double-flow-channel fan disc and an outlet rectifying assembly; the casing assembly is provided with an inner duct and an outer duct; the inlet flow adjusting assembly is arranged on the casing assembly and positioned at the inlets of the inner duct and the outer duct, and is used for adjusting the flow entering the inner duct and the outer duct; the double-flow-channel fan disc is rotatably arranged in the inner duct and the outer duct and is used for dividing airflow into inner duct airflow and outer duct airflow and enabling the inner duct airflow and the outer duct airflow to flow in the inner duct and the outer duct respectively when the double-flow-channel fan disc rotates; and the outlet rectification component is arranged on the casing component and is positioned at the outlets of the inner duct and the outer duct so as to be used for respectively rectifying the outlet airflow of the inner duct and the outer duct.
It can be understood that the double-flow-passage fan structure of the invention uses a single rotor, realizes the flow of air flow in different culverts from inside to outside, and is simpler and easier to realize in structure compared with the prior double-rotor scheme; the single rotor has no rotating speed matching problem, and the flow state in the inner duct and the outer duct can be independently controlled only by adjusting the guide vane angle of the inner duct and the outer duct; compared with the existing double-rotor scheme, the bypass flow has a larger adjusting range; in the limit, the inner duct flow only vortex shaft mode can be achieved by fully closing the outer duct vane angle; and the inner culvert airflow and the outer culvert airflow are isolated through the sealing structure, so that the airflows between the two culverts cannot interfere with each other, and the stable flowing can be ensured.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.
FIG. 1 is a schematic view of a conventional dual duct structure in the prior art;
FIG. 2 is a schematic structural view of an embodiment of a dual-flow fan structure with adjustable inner and outer culvert guide vanes according to the present invention;
FIG. 3 is a schematic structural view of an inlet flow regulating assembly in an embodiment of a dual-flow fan structure with adjustable inner and outer culvert guide vanes according to the present invention;
FIG. 4 is a schematic structural diagram of a dual-flow fan disc in an embodiment of the dual-flow fan structure with adjustable inner and outer culvert guide vanes of the present invention;
FIG. 5 is a schematic sealing diagram of a first side of a dual-flow fan disc in an embodiment of the dual-flow fan structure with adjustable inner and outer culvert guide vanes;
FIG. 6 is a sealing schematic view of a second side of a dual-flow fan disc in an embodiment of the dual-flow fan structure with adjustable inner and outer culvert guide vanes of the present invention;
FIG. 7 is a schematic structural diagram of an outlet rectification component in an embodiment of a dual-flow-channel fan structure with adjustable inner and outer culvert guide vanes according to the present invention.
The reference numbers illustrate:
10. a case assembly; 20. an inlet flow regulation assembly; 30. a dual flow fan tray; 40. an outlet rectification component; 10a, a bypass; 10b, an outer duct; 11. a first case; 12. a second case; 13. a third case; 14. a fourth case; 15. a support plate; 21. an inner culvert inlet guide vane; 22. an external culvert inlet guide vane; 31. a tray body; 32. a culvert blade; 33. a spreader cone; 34. a culvert blade; 331. a seal member; 41. a culvert rectifier ring; 42. outer culvert outlet rectifying blades; 43. an outer culvert outlet guide vane inner ring.
The implementation, functional features and advantages of the present invention will be further described with reference to the accompanying drawings.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that, if directional indications (such as upper, lower, left, right, front, rear, 8230; \8230;) are involved in the embodiment of the present invention, the directional indications are only used to explain the relative positional relationship between the components in a specific posture (as shown in the figure), the motion situation, etc., and if the specific posture is changed, the directional indications are correspondingly changed.
In addition, if there is a description relating to "first", "second", etc. in the embodiments of the present invention, the description of "first", "second", etc. is for descriptive purposes only and is not to be construed as indicating or implying relative importance or to implicitly indicate the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In addition, if appearing throughout the text, "and/or" is meant to include three juxtaposed aspects, taking "A and/or B" as an example, including either the A aspect, or the B aspect, or both A and B satisfied aspects. In addition, technical solutions between various embodiments may be combined with each other, but must be realized by a person skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination should not be considered to exist, and is not within the protection scope of the present invention.
The invention provides a double-flow-channel fan structure with adjustable inner and outer culvert guide vanes, which is suitable for an aeroengine and is not limited in the position.
Referring to fig. 2, in an embodiment of the present invention, the double-flow-passage fan structure with adjustable inner and outer bypass guide vanes includes a casing assembly 10, an inlet flow adjusting assembly 20, a double-flow-passage fan disc 30 and an outlet rectification assembly 40; a casing assembly 10 formed with an inner duct 10a and an outer duct 10b; an inlet flow regulating assembly 20 mounted on the casing assembly 10 at the inlet of the inner duct 10a and the outer duct 10b for regulating the flow into the inner duct 10a and the outer duct 10b; a dual flow fan disk 30 rotatably disposed in the inner duct 10a and the outer duct 10b for dividing an air flow into a culvert air flow and making them flow in the inner duct 10a and the outer duct 10b, respectively, when rotating; and the outlet rectification assembly 40 is installed on the casing assembly 10 and is positioned at the outlet of the inner duct 10a and the outer duct 10b, so as to respectively rectify the outlet airflow of the inner duct 10a and the outer duct 10b.
In this embodiment, the casing assembly 10 may include three layers of casings, and the three layers of casings are sequentially arranged at intervals from inside to outside to form an independent inner duct 10a and an independent outer duct 10b, and the specific structure of the casing assembly 10 is not limited herein.
The inlet flow conditioning assembly 20 may include two guide vanes or other flow directing elements, with the two guide vanes providing the inner duct 10a and the outer duct 10b, respectively, that vary the flow, velocity, etc. entering the duct by varying the blade angle. Of course, multiple sets of guide vanes or guide elements may also be provided according to requirements, which is not specifically limited herein.
The double-flow fan disc 30 may include a flow dividing part and a flow guiding part to divide the air flow in the duct into the bypass air flow and the bypass air flow, and the flow guiding part may be two or more, and is respectively disposed in the bypass 10a and the bypass 10b, so as to do work on the bypass air flow and the bypass air flow in work, and the specific structure of the double-flow fan disc 30 is not limited here.
The outlet rectification component 40 may include two rectification devices respectively disposed in the inner duct 10a and the outer duct 10b to respectively rectify the outlet airflows of the inner duct 10a and the outer duct 10b, and of course, a plurality of rectification devices may also be disposed, which is not limited herein.
It can be understood that the double-flow-passage fan structure of the invention uses a single rotor, realizes the flow of air flow in different culverts from inside to outside, and is simpler and easier to realize in structure compared with the prior double-rotor scheme; the problem of rotating speed matching does not exist in a single rotor, and the flow state in the inner duct and the flow state in the outer duct can be independently controlled only by adjusting the guide vane angle of the inner duct and the guide vane angle of the outer duct; compared with the existing double-rotor scheme, the bypass flow has a larger adjusting range; in the limit, a vortex shaft mode with only the inner duct 10a flow can be achieved by fully closing the outer duct 10b vane angle; and, interior culvert air current accessible obturation structure keeps apart, and the air current between two ducts can not cause mutual interference, can guarantee to flow stably.
In order to reduce the complexity of the structure and to facilitate implementation, referring to fig. 2 and 3, in an embodiment, the casing assembly 10 may include a first casing 11, a second casing 12, and a third casing 13, where the first casing 11, the second casing 12, and the third casing 13 are sequentially disposed at intervals from inside to outside and form the inner duct 10a and the outer duct 10b.
In this embodiment, the second casing 12 and the third casing 13 may be connected by a support plate 15, and the support plate 15 is hollow.
Further, in the present embodiment, referring primarily to FIG. 3, the inlet flow conditioning assembly 20 may include a content inlet guide vane 21 and an outer content inlet guide vane 22. One end of the culvert inlet guide vane 21 is rotatably arranged on the first casing 11, the other end of the culvert inlet guide vane 21 passes through the second casing 12 and passes through the support plate 15 to be rotatably arranged on the third casing 13, and the culvert inlet guide vane 21 is arranged in the culvert 10a to be used for adjusting the flow entering the culvert 10a by changing the angle of the blade. Both ends of the bypass inlet guide vane 22 are rotatably disposed on the second casing 12 and the third casing 13, respectively, and the bypass inlet guide vane 22 is disposed in the bypass 10b for adjusting the flow rate entering the bypass 10b by changing the blade angle.
The number of the support plates 15 may be the same as that of the culvert inlet guide vanes 21, one or more through holes may be formed in the support plates 15 to form a culvert inlet, and the second casing 12 and the third casing 13 may be connected into an integral structure through the support plates 15. The support plate 15 is designed into a hollow structure, and a blade handle of the culvert inlet guide blade 21 can penetrate through the support plate 15 and is positioned and restrained through a positioning bushing. The third casing 13 may be provided with positioning holes having the same number as the bypass inlet guide vanes 22, and the two ends of the bypass inlet guide vanes 22 may also be positioned and constrained by positioning bushings.
In the working process, the control of the culvert flow and the culvert flow is respectively realized by adjusting the blade angles of the culvert inlet guide vanes 21 and the culvert inlet guide vanes 22. In particular, when the bypass inlet guide vanes 22 are in a fully closed state, the aircraft engine compression section may be switched from the turbofan mode of operation to the turboshaft mode of operation to effect a switch of the aircraft from a high speed travel state to a hover or very low speed travel state.
Referring to fig. 2 and 4, in an embodiment, the dual-flow-passage fan disc 30 may include a disc body 31, and a culvert blade 32, a diverging cone 33, and a culvert blade 34 that are disposed on the disc body 31 and sequentially connected from inside to outside. The spreader cone 33 is arranged between the inner duct 10a and the outer duct 10b and is used for separating the airflow into inner-culvert airflow and outer-culvert airflow; the culvert blades 32 are arranged in the culvert 10a and used for adjusting the airflow of the culvert 10 a; the bypass vanes 34 are disposed in the bypass 10b and serve to adjust the flow rate of the airflow in the bypass 10b.
Referring to fig. 2 and 4, in the present embodiment, the bottom of the splitter cone 33 can be flush with the second casing 12 to form a duct partition wall, so as to separate the inner duct 10a and the outer duct 10b independently, thereby avoiding the mutual interference caused by the communication between the two ducts, reducing the material consumption of the casing, and saving the cost.
It should be noted that the splitter cone 33 divides the air flow into a culvert and a culvert in the rotor part, the culvert blades 34 apply work to the culvert air flow in the work, and the culvert blades 32 apply work to the culvert air flow.
In addition, in the present embodiment, referring to fig. 2, 4 to 6, two sides of the diverging cone 33 can be respectively sealed against the second casing 12 and the outlet rectification component 40. More specifically, sealing pieces 331 such as a labyrinth or a brush are respectively arranged at the front end and the rear end of the diversion cone 33, and the labyrinth sealing or the brush sealing effect is realized by the rotation of the double-flow-passage fan disc 30, so that the mutual influence between the inner and outer contained airflows is isolated.
Referring mainly to fig. 4, in this embodiment, a U-shaped opening may be formed on a side wall of the diverging cone 33 located in the bypass 10b to improve the diverging effect of the diverging cone 33.
To improve the ease of assembly, in an embodiment, with reference to fig. 2 and 7, the casing assembly 10 may further include a fourth casing 14, and the fourth casing 14 is flush with the third casing 13.
In the present embodiment, the outlet fairing assembly 40 can include an inner culvert fairing ring 41, outer culvert outlet fairing blades 42, and an outer culvert outlet guide vane inner ring 43; the culvert rectifier ring 41 is arranged at the lower end of the culvert outlet guide vane inner ring 43 and is arranged in the inner culvert 10a, so that the outlet airflow of the inner culvert 10a is rectified by setting the blade angle; both ends of the bypass outlet rectifying blade 42 are rotatably arranged on the fourth casing 14 and the bypass outlet guide vane inner ring 43 respectively, and the bypass outlet guide vane inner ring 43 is adjacent to the double-channel fan disc 30; the bypass outlet straightening vanes 42 are used for straightening the outlet airflow of the bypass 10b by changing the vane angle.
The fourth casing 14 may be provided with positioning holes having the same number as the number of the bypass outlet rectifying blades 42, and two ends of the bypass outlet rectifying blades 42 may be respectively positioned and constrained by positioning bushings. The culvert rectifier ring 41 can be of a blisk ring structure and is fixedly connected with other stator parts through mounting edges.
The double-flow-channel fan structure of the invention matches the flow change of the bypass airflow by adjusting the blade angle of the bypass outlet rectifying blade 42, thereby realizing the rectification of the bypass outlet airflow. And moreover, the blade angle of the content rectifier is designed to rectify the airflow at the content outlet, so that the airflow with required parameters is provided for a rear-stage compression part or a combustion chamber.
The invention further provides an aero-engine, which comprises the double-flow-channel fan structure with the adjustable inner and outer culvert guide vanes, the specific structure of the double-flow-channel fan structure with the adjustable inner and outer culvert guide vanes refers to the embodiments, and the aero-engine provided by the invention comprises all the schemes of all the embodiments of the double-flow-channel fan structure with the adjustable inner and outer culvert guide vanes, so that the double-flow-channel fan structure at least has the same technical effects as the double-flow-channel fan structure with the adjustable inner and outer culvert guide vanes, and the technical effects are not explained in different places.
The above description is only an alternative embodiment of the present invention, and not intended to limit the scope of the present invention, and all modifications and equivalents of the present invention, which are made by the contents of the present specification and the accompanying drawings, or directly/indirectly applied to other related technical fields, are included in the scope of the present invention.
Claims (10)
1. The utility model provides an interior outer double-flow-passage fan structure of containing adjustable stator which characterized in that includes:
the casing assembly is provided with an inner duct and an outer duct;
an inlet flow regulating assembly mounted on the casing assembly at the inlet of the inner duct and the outer duct for regulating the flow into the inner duct and the outer duct; and
a double-flow fan disc rotatably disposed in the inner duct and the outer duct to divide an air flow into an inner duct air flow and an outer duct air flow and to flow in the inner duct and the outer duct, respectively, when rotating; and
and the outlet rectification component is arranged on the casing component and is positioned at the outlets of the inner duct and the outer duct so as to be used for respectively rectifying the outlet airflow of the inner duct and the outlet airflow of the outer duct.
2. The adjustable inner and outer culvert guide vane dual flow fan structure as claimed in claim 1, wherein said casing assembly comprises a first casing, a second casing and a third casing, said first casing, said second casing and said third casing being spaced apart in sequence from inside to outside and forming said inner duct and said outer duct.
3. The dual-flow fan structure with adjustable inner and outer culvert vanes as claimed in claim 2 wherein said second casing and said third casing are connected by support plates, said support plates being hollow.
4. The adjustable dual flow fan structure of inner and outer culvert vanes of claim 3 wherein said inlet flow conditioning assembly comprises:
the culvert inlet guide vane is arranged in the culvert and used for adjusting the flow entering the culvert by changing the angle of the vane; and
the inlet guide vane of the culvert is arranged in the outer duct to adjust the flow entering the outer duct by changing the angle of the blade.
5. The double-runner fan structure with adjustable inner and outer culvert guide vanes as claimed in claim 2, wherein said double-runner fan plate comprises a plate body and inner culvert blades, a diverging cone and outer culvert blades arranged on said plate body and connected in sequence from inside to outside; the spreader cone is arranged between the inner culvert and the outer culvert and is used for separating the airflow into inner culvert airflow and outer culvert airflow; the culvert blades are arranged in the culvert and used for adjusting the airflow of the culvert; the bypass blade is arranged in the bypass and used for adjusting the airflow of the bypass.
6. The adjustable double-runner fan structure with inner and outer culvert vanes of claim 5 wherein two sides of said splitter cone are sealed against said second casing and said outlet fairing assembly, respectively.
7. The dual-runner fan structure with adjustable inner and outer culvert guide vanes as claimed in claim 6, wherein both sides of said splitter cone are provided with sealing pieces, said sealing pieces are sealing labyrinth or sealing brush wires to abut against said second casing and said outlet fairing assembly respectively during rotation.
8. The adjustable inside and outside culvert guide vane dual flow fan structure of claim 2, wherein said case assembly further comprises a fourth case, said fourth case flush connected with said third case.
9. The dual-flow fan structure with adjustable inner and outer culvert guide vanes of claim 8, wherein said outlet fairing assembly includes an inner culvert fairing ring, an outer culvert outlet fairing blade, and an outer culvert outlet guide vane inner ring; the inner culvert rectifying ring is arranged on the inner culvert outlet guide vane ring and is arranged in the inner culvert so as to rectify the outlet airflow of the inner culvert by setting the blade angle; two ends of the outer culvert outlet rectifying blade are respectively and rotatably arranged on the fourth casing and the inner ring of the outer culvert outlet guide vane, and the inner ring of the outer culvert outlet guide vane is adjacent to the double-runner fan disc; the bypass outlet rectifying blade is used for rectifying the outlet airflow of the bypass by changing the blade angle.
10. An aircraft engine, characterized in that it comprises a double-flow fan structure with adjustable inner and outer culvert guide vanes according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211258112.8A CN115523054A (en) | 2022-10-13 | 2022-10-13 | Double-runner fan structure with adjustable inner and outer culvert guide vanes and aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211258112.8A CN115523054A (en) | 2022-10-13 | 2022-10-13 | Double-runner fan structure with adjustable inner and outer culvert guide vanes and aero-engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115523054A true CN115523054A (en) | 2022-12-27 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211258112.8A Pending CN115523054A (en) | 2022-10-13 | 2022-10-13 | Double-runner fan structure with adjustable inner and outer culvert guide vanes and aero-engine |
Country Status (1)
| Country | Link |
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| CN (1) | CN115523054A (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4791783A (en) * | 1981-11-27 | 1988-12-20 | General Electric Company | Convertible aircraft engine |
| US5988980A (en) * | 1997-09-08 | 1999-11-23 | General Electric Company | Blade assembly with splitter shroud |
| US6209311B1 (en) * | 1998-04-13 | 2001-04-03 | Nikkiso Company, Ltd. | Turbofan engine including fans with reduced speed |
| US20060236675A1 (en) * | 2005-04-20 | 2006-10-26 | Mtu Aero Engines Gmbh | Jet engine with compact arrangement of fan |
| US20090000270A1 (en) * | 2007-06-28 | 2009-01-01 | United Technologies Corp. | Gas Turbines with Multiple Gas Flow Paths |
| CN106988926A (en) * | 2017-05-22 | 2017-07-28 | 西北工业大学 | Whirlpool axle turbofan combined cycle engine |
| CN206694149U (en) * | 2017-05-22 | 2017-12-01 | 西北工业大学 | Whirlpool axle turbofan combined cycle engine |
| CN112727635A (en) * | 2020-12-31 | 2021-04-30 | 中国航空发动机研究院 | Double-culvert engine |
-
2022
- 2022-10-13 CN CN202211258112.8A patent/CN115523054A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4791783A (en) * | 1981-11-27 | 1988-12-20 | General Electric Company | Convertible aircraft engine |
| US5988980A (en) * | 1997-09-08 | 1999-11-23 | General Electric Company | Blade assembly with splitter shroud |
| US6209311B1 (en) * | 1998-04-13 | 2001-04-03 | Nikkiso Company, Ltd. | Turbofan engine including fans with reduced speed |
| US20060236675A1 (en) * | 2005-04-20 | 2006-10-26 | Mtu Aero Engines Gmbh | Jet engine with compact arrangement of fan |
| US20090000270A1 (en) * | 2007-06-28 | 2009-01-01 | United Technologies Corp. | Gas Turbines with Multiple Gas Flow Paths |
| CN106988926A (en) * | 2017-05-22 | 2017-07-28 | 西北工业大学 | Whirlpool axle turbofan combined cycle engine |
| CN206694149U (en) * | 2017-05-22 | 2017-12-01 | 西北工业大学 | Whirlpool axle turbofan combined cycle engine |
| CN112727635A (en) * | 2020-12-31 | 2021-04-30 | 中国航空发动机研究院 | Double-culvert engine |
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