CN114060313A - Multi-duct front and rear fan of aircraft engine - Google Patents
Multi-duct front and rear fan of aircraft engine Download PDFInfo
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- CN114060313A CN114060313A CN202111308716.4A CN202111308716A CN114060313A CN 114060313 A CN114060313 A CN 114060313A CN 202111308716 A CN202111308716 A CN 202111308716A CN 114060313 A CN114060313 A CN 114060313A
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- fan
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- inner casing
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- 230000005540 biological transmission Effects 0.000 description 6
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/325—Rotors specially for elastic fluids for axial flow pumps for axial flow fans
Abstract
The application belongs to the technical field of design of fans around many ducts of aeroengine, concretely relates to fan around many ducts of aeroengine, include: an outer case; an inner case disposed within the outer case; the multistage stator blades are arranged between the outer casing and the inner casing along the axial direction; the multistage rotor blades are distributed between the outer casing and the inner casing and are distributed at intervals with the stator blades at all stages; the splitter ring is arranged between the rear sections of the outer casing and the inner casing, surrounds the stator blades and the rotor blades at the position between the outer casing and the inner casing, forms a fan rear section flow channel with the inner casing, and forms a fan outer duct with the outer casing; the front parts of the flow passage at the rear section of the fan and the outer duct of the fan are provided with first-stage adjustable stator blades.
Description
Technical Field
The application belongs to the technical field of design of multi-duct front and rear fans of aero-engines, and particularly relates to a multi-duct front and rear fan of an aero-engine.
Background
The fan of the aircraft engine mainly comprises an outer casing, an inner casing arranged in the outer casing, and a plurality of stages of stator blades and rotor blades arranged between the outer casing and the inner casing.
In order to enhance the self-adaptive capacity of the aircraft engine and bring convenience to the extraction of cold source airflow and the thermal management of the aircraft engine, the stealth design of the aircraft engine is carried out, a splitter ring is arranged between an outer casing and an inner casing of the rear section of a fan of the aircraft engine, the splitter ring surrounds multi-stage stator blades and rotor blades of the rear section of the fan of the aircraft engine, a fan rear section flow passage is formed between the splitter ring and the inner casing, and a fan outer duct is formed between the splitter ring and the outer casing, so that a multi-duct front and rear fan is formed.
In the present aircraft engine multi-duct front and rear fan, in order to facilitate the adjustment of the air flow in the fan outer duct and the fan rear section flow channel, a first-stage adjustable stator blade is added at the front end in the fan rear section flow channel, and the circulation capacity of the fan rear section flow channel is changed by adjusting the angle of the stator blade, so as to realize the adjustment of the air flow in the fan outer duct and the fan rear section flow channel, as shown in fig. 1, the technical scheme has the following defects:
1) the primary adjustable stator blade is additionally arranged at the front end in the flow passage at the rear section of the fan, so that the overall mass and length of the aircraft engine can be greatly increased, the total pressure loss of the fan can be increased, and the efficiency of the fan is influenced;
2) the space between the fan rear-section flow channel and the fan outer duct is narrow, so that the arrangement of an angle adjusting mechanism for additionally arranging a first-stage adjustable stator blade at the front end in the fan rear-section flow channel is inconvenient, the angle adjusting mechanism for the first-stage adjustable stator blade is arranged on the outer side of an outer casing, and the transmission is carried out between the angle adjusting mechanism and the first-stage adjustable stator blade by virtue of a transmission shaft with a longer length, so that the accurate adjustment of the angle of the first-stage adjustable stator blade is difficult to realize;
3) in order to rectify the airflow flowing to the fan outer duct, the stator blade is arranged at the front end in the fan outer duct, the first-stage adjustable stator blade is additionally arranged at the front end in the fan rear-stage flow passage, the flow capacity of the fan rear-stage flow passage can be changed by adjusting the angle of the stator blade, and the airflow angle at the inlet of the front end in the fan outer duct can also be changed in a large range.
The present application has been made in view of the above-mentioned technical drawbacks.
It should be noted that the above background disclosure is only for the purpose of assisting understanding of the inventive concept and technical solutions of the present invention, and does not necessarily belong to the prior art of the present patent application, and the above background disclosure should not be used for evaluating the novelty and inventive step of the present application without explicit evidence to suggest that the above content is already disclosed at the filing date of the present application.
Disclosure of Invention
It is an object of the present application to provide an aircraft engine multi-ducted front-rear fan that overcomes or mitigates at least one of the technical disadvantages of the known prior art.
The technical scheme of the application is as follows:
an aircraft engine multi-duct front-rear fan comprising:
an outer case;
an inner case disposed within the outer case;
the multistage stator blades are arranged between the outer casing and the inner casing along the axial direction;
the multistage rotor blades are distributed between the outer casing and the inner casing and are distributed at intervals with the stator blades at all stages;
the splitter ring is arranged between the rear sections of the outer casing and the inner casing, surrounds the stator blades and the rotor blades at the position between the outer casing and the inner casing, forms a fan rear section flow channel with the inner casing, and forms a fan outer duct with the outer casing; the front parts of the flow passage at the rear section of the fan and the outer duct of the fan are provided with first-stage adjustable stator blades.
According to at least one embodiment of the application, in the multi-duct front and rear fan of the aircraft engine, the stator blades have three stages, wherein one stage is positioned in a flow passage of the rear section of the fan;
the rotor blades have two stages, one of which is located in the flow passage of the rear section of the fan.
According to at least one embodiment of the application, in the above-mentioned aircraft engine multi-duct front and rear fan, further include:
the stator blade of the first-stage fan outer duct is arranged at the front end in the fan outer duct.
The application has at least the following beneficial technical effects:
the utility model provides a fan around many ducts of aeroengine, it lies in fan back end runner in fan back end among the fan around many ducts of aeroengine, the anterior one-level stator blade of fan outer duct designs for adjustable stator blade, it is about to repack the one-level stator blade of fan back end runner rear end play oral area position department into adjustable stator blade around many ducts of aeroengine, the accessible is to the regulation of this stage stator blade angle, realize the outer duct of fan, the regulation of air flow in the fan back end runner, this kind of fan around many ducts of aeroengine can not increase aeroengine holistic quality and length, can guarantee the efficiency of fan, easily realize the accurate regulation to adjustable stator blade angle, can reduce the possibility that the air current takes place to leak, and can not increase the total pressure loss of fan outer duct B.
Drawings
FIG. 1 is a schematic view of a multi-duct front and rear fan of a current aircraft engine;
FIG. 2 is a schematic view of a multi-duct front and rear fan of an aircraft engine provided by an embodiment of the application;
wherein:
1-an outer casing; 2-inner casing; 3-stator blades; 4-rotor blades; 5-a shunt ring; 6-outer ducted stator blades of the fan;
a-a fan rear section runner;
b-a fan outer duct.
For the purpose of better illustrating the embodiments, certain features of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; further, the drawings are for illustrative purposes, and terms describing positional relationships are limited to illustrative illustrations only and are not to be construed as limiting the patent.
Detailed Description
In order to make the technical solutions and advantages of the present application clearer, the technical solutions of the present application will be further clearly and completely described in the following detailed description with reference to the accompanying drawings, and it should be understood that the specific embodiments described herein are only some of the embodiments of the present application, and are only used for explaining the present application, but not limiting the present application. It should be noted that, for convenience of description, only the parts related to the present application are shown in the drawings, other related parts may refer to general designs, and the embodiments and technical features in the embodiments in the present application may be combined with each other to obtain a new embodiment without conflict.
In addition, unless otherwise defined, technical or scientific terms used in the description of the present application shall have the ordinary meaning as understood by one of ordinary skill in the art to which the present application belongs. The terms "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", and the like used in the description of the present application, which indicate orientations, are used only to indicate relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and when the absolute position of the object to be described is changed, the relative positional relationships may be changed accordingly, and thus, should not be construed as limiting the present application. The use of "first," "second," "third," and the like in the description of the present application is for descriptive purposes only to distinguish between different components and is not to be construed as indicating or implying relative importance. The use of the terms "a," "an," or "the" and similar referents in the context of describing the application is not to be construed as an absolute limitation on the number, but rather as the presence of at least one. The word "comprising" or "comprises", and the like, when used in this description, is intended to specify the presence of stated elements or items, but not the exclusion of other elements or items.
Further, it is noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and the like are used in the description of the invention in a generic sense, e.g., connected as either a fixed connection or a removable connection or integrally connected; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected through the inside of two elements, and those skilled in the art can understand their specific meaning in this application according to the specific situation.
The present application is described in further detail below with reference to fig. 1-2.
An aircraft engine multi-duct front-rear fan comprising:
an outer case 1;
an inner case 2 disposed inside the outer case 1;
the multistage stator blades 3 are arranged between the outer casing 1 and the inner casing 2 along the axial direction;
the multistage rotor blades 4 are distributed between the outer casing 1 and the inner casing 2 and distributed at intervals with the stator blades 3 at each stage;
the splitter ring 5 is arranged between the rear sections of the outer casing 1 and the inner casing 2, surrounds the stator blades 3 and the rotor blades 4 at the position between the outer casing 1 and the inner casing 2, forms a fan rear section flow channel A with the inner casing 2, and forms a fan outer duct B with the outer casing 1; the front parts of the fan rear section flow passage A and the fan outer duct B are provided with first-stage adjustable stator blades.
For the aero-engine multi-duct front and rear fan disclosed in the above embodiment, as can be understood by those skilled in the art, the first-stage stator blade 3 located in the front portion of the fan rear-section flow channel a and the fan outer duct B in the aero-engine multi-duct front and rear fan is designed as an adjustable stator blade, that is, the first-stage stator blade 3 located in the rear end outlet portion of the fan front-section flow channel in the aero-engine multi-duct front and rear fan is modified into the adjustable stator blade, the inlet airflow angle of the fan rear-section flow channel a is changed by adjusting the angle of the first-stage stator blade 3, the circulation capacity of the fan rear-section flow channel a is changed, and further the regulation of the airflow in the fan outer duct B and the fan rear-section flow channel a is realized.
For the aero-engine multi-duct front and rear fan disclosed in the above embodiment, it can be understood by those skilled in the art that a first-stage adjustable stator blade is not additionally arranged at the front end in the fan rear-section flow passage a, so that the overall mass and length of the aero-engine are not increased, and the efficiency of the fan can be ensured, in addition, the first-stage stator blade 3 at the outlet position at the rear end of the fan rear-section flow passage in the aero-engine multi-duct front and rear fan is modified into an adjustable stator blade, the angle adjusting mechanism of the adjustable stator blade can be arranged outside the outer casing 1, and the transmission shaft with a longer length is not required to be used for transmission with the adjustable stator blade, so that the precise adjustment of the angle of the adjustable stator blade is easy to realize, and the transmission shaft does not need to pass through the splitter ring 5, so that the possibility of air flow leakage can be reduced, and the transmission shaft does not need to pass through the fan outer duct B, the total pressure loss of the fan outer duct B cannot be increased.
The angle adjusting mechanism for the adjustable stator blades in the multi-duct front and rear fan of the aircraft engine disclosed in the above embodiments may be selected by a person skilled in the art according to actual practice within a known range or designed separately, and will not be described and limited in more detail herein.
In some optional embodiments, in the above-mentioned aircraft engine multi-duct front and rear fan, the stator blade 3 has three stages, wherein one stage is located in the flow passage a of the rear section of the fan;
the rotor blades 4 have two stages, one of which is located in the flow passage a of the rear section of the fan.
In some optional embodiments, in the above-mentioned aircraft engine multi-duct front-rear fan, further includes:
the stator blade 6 of the first-stage fan outer duct is arranged at the front end in the fan outer duct B.
For the aero-engine multi-duct front and rear fan disclosed in the above embodiment, as can be understood by those skilled in the art, the first-stage stator blade 3 at the outlet position at the rear end of the fan rear-section flow passage in the aero-engine multi-duct front and rear fan is used as the adjustable stator blade, and the adjustment of the air flow in the fan outer duct B and the fan rear-section flow passage a is realized by adjusting the angle of the first-stage stator blade 3, instead of the adjustment of the angle of the first-stage adjustable stator blade additionally arranged at the front end in the fan rear-section flow passage a, so that the adjustment of the air flow in the fan outer duct B and the fan rear-section flow passage a is realized, the air flow at the inlet position at the front end in the fan outer duct B cannot be changed in a large range, and the fan outer duct stator blade 6 does not need to be selected as a blade profile with a wide usable attack angle range, and the design and the processing are easy.
The embodiments are described in a progressive manner in the specification, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
Having thus described the present application in connection with the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present application is not limited to those specific embodiments, and that equivalent modifications or substitutions of related technical features may be made by those skilled in the art without departing from the principle of the present application, and those modifications or substitutions will fall within the scope of the present application.
Claims (3)
1. The utility model provides a fan around many ducts of aeroengine which characterized in that includes:
an outer casing (1);
an inner case (2) disposed within the outer case (1);
the multi-stage stator blades (3) are arranged between the outer casing (1) and the inner casing (2) along the axial direction;
the multi-stage rotor blades (4) are distributed between the outer casing (1) and the inner casing (2) and are distributed at intervals with the stator blades (3) at each stage;
the splitter ring (5) is arranged between the rear sections of the outer casing (1) and the inner casing (2), surrounds the stator blades (3) and the rotor blades (4) at the positions between the outer casing (1) and the inner casing (2), forms a fan rear section flow channel (A) with the inner casing (2), and forms a fan outer duct (B) with the outer casing (1); the front parts of the fan rear section flow passage (A) and the fan outer duct (B) are provided with first-stage adjustable stator blades.
2. The aircraft engine multi-duct forward-aft fan of claim 1,
the stator blade (3) has three stages, wherein one stage is positioned in the flow passage (A) at the rear section of the fan;
the rotor blades (4) have two stages, wherein one stage is positioned in the flow passage (A) of the rear section of the fan.
3. The aircraft engine multi-duct forward-aft fan of claim 1,
further comprising:
and the stator blade (6) of the primary fan outer duct is arranged at the front end in the fan outer duct (B).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111308716.4A CN114060313A (en) | 2021-11-05 | 2021-11-05 | Multi-duct front and rear fan of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111308716.4A CN114060313A (en) | 2021-11-05 | 2021-11-05 | Multi-duct front and rear fan of aircraft engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114060313A true CN114060313A (en) | 2022-02-18 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111308716.4A Pending CN114060313A (en) | 2021-11-05 | 2021-11-05 | Multi-duct front and rear fan of aircraft engine |
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| Country | Link |
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| CN (1) | CN114060313A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114542518A (en) * | 2022-02-23 | 2022-05-27 | 中国航发沈阳发动机研究所 | Double-duct compressor |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1975130A (en) * | 2005-11-29 | 2007-06-06 | 通用电气公司 | Turbofan gas turbine engine with variable fan outlet guide vanes |
| CN105673251A (en) * | 2016-01-13 | 2016-06-15 | 中国航空动力机械研究所 | Fan pressure boosting stage and turbofan engine |
| CN206503781U (en) * | 2016-12-06 | 2017-09-19 | 中国航发商用航空发动机有限责任公司 | Adjustable guide vane structure for aero-engine |
| CN107191412A (en) * | 2017-07-24 | 2017-09-22 | 北京航空航天大学 | A kind of multi stage axial flow compressor of the adaptive blowing suction of front stage stator |
| CN109386381A (en) * | 2017-08-11 | 2019-02-26 | 中国航发商用航空发动机有限责任公司 | Flow splitter design method |
| CN111911461A (en) * | 2020-08-28 | 2020-11-10 | 中国航发沈阳发动机研究所 | Stator blade angle adjusting mechanism and stator casing structure thereof |
-
2021
- 2021-11-05 CN CN202111308716.4A patent/CN114060313A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1975130A (en) * | 2005-11-29 | 2007-06-06 | 通用电气公司 | Turbofan gas turbine engine with variable fan outlet guide vanes |
| CN105673251A (en) * | 2016-01-13 | 2016-06-15 | 中国航空动力机械研究所 | Fan pressure boosting stage and turbofan engine |
| CN206503781U (en) * | 2016-12-06 | 2017-09-19 | 中国航发商用航空发动机有限责任公司 | Adjustable guide vane structure for aero-engine |
| CN107191412A (en) * | 2017-07-24 | 2017-09-22 | 北京航空航天大学 | A kind of multi stage axial flow compressor of the adaptive blowing suction of front stage stator |
| CN109386381A (en) * | 2017-08-11 | 2019-02-26 | 中国航发商用航空发动机有限责任公司 | Flow splitter design method |
| CN111911461A (en) * | 2020-08-28 | 2020-11-10 | 中国航发沈阳发动机研究所 | Stator blade angle adjusting mechanism and stator casing structure thereof |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114542518A (en) * | 2022-02-23 | 2022-05-27 | 中国航发沈阳发动机研究所 | Double-duct compressor |
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