CN105673251A - Fan pressure boosting stage and turbofan engine - Google Patents
Fan pressure boosting stage and turbofan engine Download PDFInfo
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- CN105673251A CN105673251A CN201610020500.0A CN201610020500A CN105673251A CN 105673251 A CN105673251 A CN 105673251A CN 201610020500 A CN201610020500 A CN 201610020500A CN 105673251 A CN105673251 A CN 105673251A
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- fan
- level
- stator
- supercharging
- duct
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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
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- 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 invention discloses a fan pressure boosting stage and a turbofan engine. The fan pressure boosting stage comprises a first-stage fan rotor, an inner duct and an outer duct; an inlet of the fan rotor is connected to an air inlet; an inlet of the inner duct is connected to an outlet of the fan rotor, an outlet of the inner duct is connected to an inlet of a compressor, fan inner duct stators and multiple pressure boosting stage bodies are arranged in the inner duct, and the fan inner duct stators are located between the inlet of the inner duct and the pressure boosting stage bodies; and an inlet of the outer duct is connected to the outlet of the fan rotor, the outer duct is arranged on the periphery of the inner duct, and fan outer duct stators are arranged in the outer duct. According to the turbofan engine, through the design of a first-stage fan and the multiple pressure boosting stage bodies, the turbofan engine has the good high altitude adaptability. Along with increase of the flight height of an aircraft, the performance of the turbofan engine is reduced relatively slow, and the better performance can still be kept at the flight height such as about 19 km.
Description
Technical field
The present invention relates to aero engine technology field, specifically, it relates to a kind of fan forced level and there is the fanjet of this fan forced level.
Background technology
Aircraft when being applied to high-altitude long-endurance uses fanjet usually, namely requires that fanjet can provide long-time stable flight performance for aircraft in high-altitude. Owing to the pressure of high-altitude air, temperature and density are all lower, also mean that Reynolds number is low. When Reynolds number is less than critical Reynolds number 3.5 × 105Time, fanjet performance degradation, and existing fanjet cannot meet the good segmented assembling in air required by the navigation of high-altitude and cruise for a long time required lower specific fuel oil consumption and satisfactory stability.
Summary of the invention
A main purpose of the present invention is to overcome at least one defect of above-mentioned prior art, it is provided that a kind of good fan forced level of segmented assembling in air.
Another main purpose of the present invention is to overcome at least one defect of above-mentioned prior art, it is provided that the fanjet that a kind of segmented assembling in air is better and specific fuel oil consumption is lower.
For achieving the above object, the present invention adopts following technical scheme:
According to an aspect of the present invention, a kind of fan forced level is provided, for setting, in fanjet, described fanjet has inlet mouth, fan forced level and pneumatic plant, described fan forced level comprises one-level fan rotor, main duct and outer duct; The entrance of described fan rotor is connected to described inlet mouth; The entrance of described main duct is connected to the outlet of described fan rotor, its outlet is connected to the entrance of described pneumatic plant, being provided with fan intension stator and multistage supercharging level in described main duct, described fan intension stator is between described main duct entrance and supercharging level; The entrance of described outer duct is connected to the outlet of described fan rotor, and described outer duct is located at the periphery of described main duct, contains stator outside being provided with fan in described outer duct.
One of them according to the present invention implements mode, and described fan rotor is wide string blade.
One of them according to the present invention implements mode, and the span-chord ratio of described wide string blade is 1.3～1.7.
One of them according to the present invention implements mode, and the outer culvert rate of supercharging of described fan forced level is 1.5～2.0, and its intension rate of supercharging is 2.3～2.8.
One of them according to the present invention implements mode, and the duct ratio of described fan forced level is 3.0～3.5.
One of them according to the present invention implements mode, two-stage supercharging level it is provided with in described main duct, it is respectively the first supercharging level and the 2nd supercharging level, described first supercharging level is between described fan intension stator and the 2nd supercharging level, and described 2nd supercharging level is between described first supercharging level and the outlet of main duct.
One of them according to the present invention implements mode, and described first supercharging level comprises first step rotor and first step stator, and described first step rotor is between described fan intension stator and described first step stator; And/or, described 2nd supercharging level comprises second stage rotor and second stage stator, and described second stage rotor is between described first step stator and described second stage stator.
One of them according to the present invention implements mode, and containing stator outside described fan is tandem stator.
One of them according to the present invention implements mode, and the air-flow in described outer duct realizes 40 °～50 ° by described tandem stator and turns back.
According to another aspect of the present invention, it is provided that a kind of fanjet, wherein, described fanjet comprises inlet mouth, pneumatic plant, combustion chamber, turbine and described fan forced level.
As shown from the above technical solution, the present invention proposes the advantage of fanjet and positively effect are:
The fanjet that the present invention proposes, by the design of the one-level fan of its fan forced level and multistage supercharging level, makes this fanjet have good segmented assembling in air. Along with the increase of aircraft altitude, the performance degradation of this fanjet is comparatively slow, and the flight at such as about 19km highly still can keep good performance.
Accompanying drawing explanation
Considering the following detailed explanation to the preferred embodiment of the present invention in conjunction with the drawings, the various targets of the present invention, feature and advantage will become more apparent. Accompanying drawing is only the exemplary diagram of the present invention, and not necessarily is drawn in proportion. In the accompanying drawings, same Reference numeral represents same or similar parts all the time. Wherein:
Fig. 1 is aerodynamic arrangement's schematic diagram of a kind of fanjet according to an illustrative embodiments.
Wherein, description of reference numerals is as follows:
1. fan rotor; 2. main duct; 21. fan intension stators; 22. first supercharging levels; 221. first step rotors; 222. first step stators; 23. the 2nd supercharging levels; 231. second stage rotors; 232. second stage stators; 3. outer duct; Stator is contained outside 31. fans; Stator is contained outside 311. first; Stator is contained outside 312. the 2nd.
Embodiment
The exemplary embodiments embodying feature of present invention and advantage will describe in the following description in detail. Iting should be understood that the present invention can have various changes in different embodiments, it does not all depart from the scope of the present invention, and explanation and accompanying drawing wherein is being the use explained in essence, and is not used to restriction the present invention.
In the following describes of the different illustrative embodiments to the present invention, carrying out with reference to accompanying drawing, described accompanying drawing forms the part of the present invention, and wherein shows the different example arrangement of the many aspects that can realize the present invention, system and step by way of example. It will be understood that other specified scheme of parts, structure, exemplary means, system and step can be used, and structure and function amendment can be carried out when not deviateing the scope of the invention. And, although term " entrance ", " outlet ", " periphery " etc. can be used in this specification sheets to describe different example feature and the element of the present invention, but these terms are used for herein only for convenience, such as with reference to the accompanying drawings described in the direction of example. The specific three dimensional direction that any content in this specification sheets all should not be construed as Structure of need just falls within the scope of the present invention.
Please refer to Fig. 1, Fig. 1 representatively illustrates aerodynamic arrangement's schematic diagram of the principle that can embody the fanjet that the present invention proposes, aerodynamic arrangement's schematic diagram of the main fan forced level representing this fanjet.Wherein, in the following description to this illustrative embodiments, it is described for a kind of fanjet. But; those skilled in the art it is easily understood that; owing to fanjet also comprises the structures such as pneumatic plant, combustion chamber and turbine usually; therefore; in order to the fanjet that the present invention is proposed; particularly its fan forced level is combined with said structure and forms fanjet, and to above-mentioned fanjet particularly its fan forced level make multiple remodeling, interpolation, replacement, deletion or other change, these change still the present invention propose fanjet principle scope in.
Fan forced level implements mode
As shown in Figure 1, in the present embodiment, the fan forced level that the present invention proposes may be used for being arranged in fanjet, this fanjet has inlet mouth, fan forced level, pneumatic plant (in such as pressure pneumatic plant or hpc) and other structures (such as combustion chamber and turbine etc.), and inlet mouth, pneumatic plant and other structures are not shown. Wherein, this fan forced level mainly comprises one-level fan rotor 1, main duct 2 and outer duct 3.
As shown in Figure 1, in the present embodiment, fan rotor 1 can be preferably wide string blade, and the entrance of fan rotor 1 is connected to inlet mouth, with enter fanjet by inlet mouth air-flow after this fan rotor 1 rotating boosting, be further divided into two strands of air-flows and flow to main duct 2 and outer duct 3 respectively. Wherein, in the present embodiment, the span-chord ratio of this wide string blade is preferably 1.3～1.7, to improve Reynolds number further, thus reduces the too low impact on fanjet of Reynolds number. But, those skilled in the art it is easily understood that, in order to the effect improving Reynolds number by the optimization design of fan rotor 1 being reached, and the quantity and decoration form to the fan rotor 1 of said fans supercharging level makes multiple remodeling, interpolation, replacement, deletion or other changes, in the scope of the principle of the fan forced level that these changes still propose in the present invention.
As shown in Figure 1, in the present embodiment, the entrance of main duct 2 is connected to the outlet of fan rotor 1, and its outlet is connected to the entrance of pneumatic plant (in such as pressure pneumatic plant or hpc), and is provided with fan intension stator 21 and two-stage supercharging level in this main duct 2. Wherein, fan intension stator 21 is between main duct 2 entrance and this two-stage supercharging level, and the intension rate of supercharging of this fan forced level can be preferably 2.3～2.8. Two-stage supercharging level is respectively the first supercharging level 22 and the 2nd supercharging level 23, first supercharging level 22 between fan intension stator 21 and the 2nd supercharging level 23, and the 2nd supercharging level 23 is between the first supercharging level 22 and the outlet of main duct 2. Specifically, first supercharging level 22 comprises first step rotor 221 and first step stator 222, first step rotor 221 is between fan intension stator 21 and first step stator 222,2nd supercharging level 23 comprises second stage rotor 231 and second stage stator 232, and second stage rotor 231 is between first step stator 222 and second stage stator 232. But, those skilled in the art it is easily understood that, in order to by the fan intension stator 21 of main duct 2 and inside thereof and the optimization design of each supercharging level, and reach the effect that when making fanjet adapt to high-altitude long-endurance, flight requires, and to the main duct 2 of said fans supercharging level particularly the fan intension stator 21 of its inside and the quantity of supercharging level and decoration form make multiple remodeling, interpolation, replacement, deletion or other changes, in the scope of the principle of the fan forced level that these changes still propose in the present invention.
As shown in Figure 1, in the present embodiment, the entrance of outer duct 3 is connected to the outlet of fan rotor 1, and this outer duct 3 is located at the periphery of main duct 2. Wherein, the outer culvert rate of supercharging of this fan forced level can be preferably 1.5～2.0, and contains stator 31 outside being provided with fan in this outer duct 3. In the present embodiment, this fan intension stator 21 can be preferably tandem stator, namely fan intension stator 21 is arranged by tandem the first outer culvert stator 311 and the 2nd outer stator 312 of containing form, so that flowing through the air-flow in outer duct 3 to realize 40 °～50 ° turn back greatly by above-mentioned tandem stator, meanwhile, the design of tandem stator also has the feature that pitot loss is little and working range is big. But, those skilled in the art it is easily understood that, in order to the optimization design by containing stator 31 outside the fan of external duct 3 and inside thereof, and reach the effect that when making fanjet adapt to high-altitude long-endurance, flight requires, and contain the quantity of stator 31 outside fan to the outer duct 3 of said fans supercharging level particularly its inside and decoration form makes multiple remodeling, interpolation, replacement, deletion or other changes, in the scope of the principle of the fan forced level that these changes still propose in the present invention.
It should be noted that, in the present embodiment, the duct ratio of the fan forced level that the present invention proposes can be preferably 3.0～3.5, owing to the outer culvert efficiency impact choosing external duct 3 of duct ratio is relatively big, above-mentioned preferred duct can make fanjet still have higher outer culvert efficiency under high altitude conditions than ratio.
At this it is noted that shown in accompanying drawing and the fan forced level described in this manual be only to adopt an example in the fan forced level of many kinds of the principle of the invention. It should be clearly understood that the principle of the present invention is only limitted to absolutely not shown in accompanying drawing or any details of fan forced level of describing in this specification sheets or any parts of fan forced level.
For example, it is not intended to principle according to the invention, in the present embodiment, the fan rotor 1 of above-mentioned such as wide string blade can be designed by Cavilalion factor technology, to obtain the more excellent complete three-dimensional blade of performance, it is to increase its efficiency, strengthen surge nargin and expand working range.
But, not in each enforcement mode of the present invention, it is necessary to by Cavilalion factor technology, the pneumatic structure of fan rotor 1 is designed. Those skilled in the art it is easily understood that, in order to the effect improving Reynolds number by the optimization design of fan rotor 1 being reached, and the method for design of the fan rotor 1 of said fans supercharging level is made multiple remodeling, interpolation, replacement, deletion or other changes, in the scope of the principle of the fan forced level that these changes still propose in the present invention.
Mode implemented by fanjet
Hereinafter one of them illustrative embodiments of the fanjet that the present invention proposes is described.
In the present embodiment, the fanjet that the present invention proposes mainly comprises the fan forced level that inlet mouth, pneumatic plant (in such as pressure pneumatic plant or hpc), combustion chamber, turbine and the present invention propose. Wherein, the entrance of fan rotor is connected to inlet mouth, with enter fanjet by inlet mouth air-flow after this fan rotor rotating boosting, be further divided into two strands of air-flows and flow to main duct and outer duct respectively. The entrance of the main duct of fan forced level is connected to the outlet of fan rotor, its outlet is connected to the entrance of pneumatic plant (in such as pressure pneumatic plant or hpc), the entrance of the outer duct of fan forced level is also connected to the outlet of fan rotor, and its outlet transfers axis to.
Based on the detailed explanation of the fan forced level that the present invention is proposed and the above-mentioned illustrative embodiments of fanjet, below the roughly workflow of the roughly workflow of this fanjet, particularly its fan forced level is further described.
Air-flow is by the inlet mouth of fanjet, and namely fan import enters this fan forced level. Air-flow is via, after fan rotor 1 rotating boosting, being divided into two strands of air-flows and flow to main duct 2 and outer duct 3 respectively. Outside in duct 3, air-flow, via containing stator 31 rectification expansion pressure outside fan, forwards axis to. In main duct 2, air-flow expands pressure through fan intension stator 21 rectification, then successively by the first step rotor 221 of two-stage supercharging level, first step stator 222, second stage rotor 231 and second stage stator 232 supercharging rectification, next stage pneumatic plant (in such as pressure pneumatic plant or hpc) is flowed to. When flight height is at more than 10km, upper air current pressure, temperature, decrease in density, Reynolds number reduces. Owing to air current flow is had important impact by Reynolds number, when Reynolds number is less than 3.5 × 105Time air-flow be easily separated, cause pneumatic plant performance degradation. For fan particularly fan rotor 1, the outer culvert flow of high aerial outer duct 3 reduces more obvious. If therefore during multistage fan, Reynolds number reduces the impact of its performance relatively big, and the fanjet that the present invention proposes adopts the form of one-level fan and two-stage supercharging level, can reduce the impact of Reynolds number. And, owing to fan rotor 1 is as import level, Reynolds number is maximum on its impact, the fan rotor 1 of the fanjet that the present invention proposes adopts span-chord ratio to be preferably the wide string blade of 1.3～1.7, Reynolds number can be improved thus reduce its impact, and the Cavilalion factor designing technique of the advanced person of this width string blade employing, it is possible to the complete three-dimensional blade that acquisition efficiency height, surge nargin are big and working range is wide. Further, contain stator 31 outside fan and adopt tandem stator, it is possible to realizing 40 °～50 °, air-flow in outer duct 3 and turn back greatly, pitot loss is little, working range is big, be conducive to improving stability.
As shown from the above technical solution, the present invention proposes the advantage of fanjet and positively effect are:
The fanjet that the present invention proposes, by the design of the one-level fan of its fan forced level and multistage supercharging level, makes this fanjet have good segmented assembling in air. Along with the increase of aircraft altitude, the performance degradation of this fanjet is comparatively slow, and the flight at such as about 19km highly still can keep good performance. In addition, the fan forced level that the present invention proposes have passed through ground experiment checking, experimental performance is good, and through engine high-altitude verification experimental verification, result shows, the segmented assembling in air of fan forced level is good, higher surge nargin is still had at about 19km, efficiency remains on higher level, when proving that it is applicable to high-altitude long-endurance, and can be successfully applied in fanjet.
Below describe in detail and/or illustrate the illustrative embodiments of the fanjet that the present invention proposes. But embodiments of the present invention are not limited to particular implementation as described herein, on the contrary, each implements the integral part of mode and/or step can be used separately with other integral part as described herein and/or step independent sum. Implement each integral part of mode and/or each step also can implement other integral part of mode with other and/or step is combined for one.When introducing described and/or illustrated key element/integral part/wait here, term " ", " one " and " above-mentioned " etc. in order to expression exist one or more key element/integral part/etc. Term " comprises ", " comprising " and " having " in order to also can exist except representing the open meaning that included and referring to the key element/integral part except listing/wait other key element/integral part/etc. In addition, term " first " in claim book and specification sheets and " the 2nd " etc. only use as mark, are not the numerical limit to its object.
Although being described by the fanjet that the present invention proposes according to different specific embodiments, but those skilled in the art will recognize that and the enforcement of the present invention can be changed in the spirit and scope of claim.
Claims (10)
1. a fan forced level, for setting, in fanjet, described fanjet has inlet mouth, fan forced level and pneumatic plant, it is characterised in that, described fan forced level comprises:
One-level fan rotor (1), its entrance is connected to described inlet mouth;
Main duct (2), its entrance is connected to the outlet of described fan rotor (1), its outlet is connected to the entrance of described pneumatic plant, being provided with fan intension stator (21) and multistage supercharging level in described main duct (2), described fan intension stator (21) is positioned between described main duct (2) entrance and supercharging level; And
Outer duct (3), its entrance is connected to the outlet of described fan rotor (1), and described outer duct (3) is located at the periphery of described main duct (2), outside being provided with fan in described outer duct (3), contain stator (31).
2. fan forced level according to claim 1, it is characterised in that, described fan rotor (1) is wide string blade.
3. fan forced level according to claim 2, it is characterised in that, the span-chord ratio of described wide string blade is 1.3～1.7.
4. fan forced level according to claim 1, it is characterised in that, the outer culvert rate of supercharging of described fan forced level is 1.5～2.0, and its intension rate of supercharging is 2.3～2.8.
5. fan forced level according to claim 1, it is characterised in that, the duct ratio of described fan forced level is 3.0～3.5.
6. fan forced level according to claim 1, it is characterized in that, two-stage supercharging level it is provided with in described main duct (2), it is respectively the first supercharging level (22) and the 2nd supercharging level (23), described first supercharging level (22) is positioned between described fan intension stator (21) and the 2nd supercharging level (23), and described 2nd supercharging level (23) is positioned between described first supercharging level (22) and the outlet of main duct (2).
7. fan forced level according to claim 6, it is characterized in that, described first supercharging level (22) comprises first step rotor (221) and first step stator (222), and described first step rotor (221) is positioned between described fan intension stator (21) and described first step stator (222); And/or
Described 2nd supercharging level (23) comprises second stage rotor (231) and second stage stator (232), and described second stage rotor (231) is positioned between described first step stator (222) and described second stage stator (232).
8. fan forced level according to claim 1, it is characterised in that, contain stator (31) outside described fan for tandem stator.
9. fan forced level according to claim 8, it is characterised in that, the air-flow in described outer duct (3) realizes 40 °～50 ° by described tandem stator and turns back.
10. a fanjet, it is characterised in that, described fanjet comprises the fan forced level as described in inlet mouth, pneumatic plant, combustion chamber, turbine and item as arbitrary in claim 1～9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610020500.0A CN105673251A (en) | 2016-01-13 | 2016-01-13 | Fan pressure boosting stage and turbofan engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610020500.0A CN105673251A (en) | 2016-01-13 | 2016-01-13 | Fan pressure boosting stage and turbofan engine |
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| Publication Number | Publication Date |
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| CN105673251A true CN105673251A (en) | 2016-06-15 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
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| CN201610020500.0A Pending CN105673251A (en) | 2016-01-13 | 2016-01-13 | Fan pressure boosting stage and turbofan engine |
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Cited By (9)
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| CN106593694A (en) * | 2016-12-23 | 2017-04-26 | 李可 | Radial turbofan jet engine |
| CN108612597A (en) * | 2016-12-09 | 2018-10-02 | 中国航发商用航空发动机有限责任公司 | A kind of fan layout structure for aero-engine |
| CN109386384A (en) * | 2017-08-14 | 2019-02-26 | 劳斯莱斯有限公司 | Gas-turbine unit |
| CN113090412A (en) * | 2021-06-08 | 2021-07-09 | 中国航发上海商用航空发动机制造有限责任公司 | Supercharging stage device and turbofan engine |
| CN113092118A (en) * | 2021-06-09 | 2021-07-09 | 中国航发上海商用航空发动机制造有限责任公司 | Full-scale fan-booster stage performance test device and test method |
| CN113217226A (en) * | 2021-06-02 | 2021-08-06 | 中国航发湖南动力机械研究所 | Paddle-fan-turbine integrated engine |
| CN114060313A (en) * | 2021-11-05 | 2022-02-18 | 中国航发沈阳发动机研究所 | Multi-duct front and rear fan of aircraft engine |
| CN114562386A (en) * | 2022-02-18 | 2022-05-31 | 中国人民解放军总参谋部第六十研究所 | Compact compound compression system |
| CN115585074A (en) * | 2022-09-13 | 2023-01-10 | 中国人民解放军总参谋部第六十研究所 | Meridian flow channel for compact type double-duct compression system |
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| CN108612597A (en) * | 2016-12-09 | 2018-10-02 | 中国航发商用航空发动机有限责任公司 | A kind of fan layout structure for aero-engine |
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| CN113217226B (en) * | 2021-06-02 | 2022-08-02 | 中国航发湖南动力机械研究所 | Paddle-fan-turbine integrated engine |
| CN113217226A (en) * | 2021-06-02 | 2021-08-06 | 中国航发湖南动力机械研究所 | Paddle-fan-turbine integrated engine |
| CN113090412A (en) * | 2021-06-08 | 2021-07-09 | 中国航发上海商用航空发动机制造有限责任公司 | Supercharging stage device and turbofan engine |
| CN113092118A (en) * | 2021-06-09 | 2021-07-09 | 中国航发上海商用航空发动机制造有限责任公司 | Full-scale fan-booster stage performance test device and test method |
| CN113092118B (en) * | 2021-06-09 | 2021-09-28 | 中国航发上海商用航空发动机制造有限责任公司 | Full-scale fan-booster stage performance test device and test method |
| CN114060313A (en) * | 2021-11-05 | 2022-02-18 | 中国航发沈阳发动机研究所 | Multi-duct front and rear fan of aircraft engine |
| CN114562386A (en) * | 2022-02-18 | 2022-05-31 | 中国人民解放军总参谋部第六十研究所 | Compact compound compression system |
| CN115585074A (en) * | 2022-09-13 | 2023-01-10 | 中国人民解放军总参谋部第六十研究所 | Meridian flow channel for compact type double-duct compression system |
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