CN112727635A - Double-culvert engine - Google Patents
Double-culvert engine Download PDFInfo
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- CN112727635A CN112727635A CN202011614652.6A CN202011614652A CN112727635A CN 112727635 A CN112727635 A CN 112727635A CN 202011614652 A CN202011614652 A CN 202011614652A CN 112727635 A CN112727635 A CN 112727635A
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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
- F02K3/06—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 front fan
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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
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/46—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/462—Fluid-guiding means, e.g. diffusers adjustable especially adapted for elastic fluid pumps
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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
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention provides a double-culvert engine, which comprises an inner culvert, a first outer culvert and a second outer culvert, wherein the inner culvert is connected with the first outer culvert; the first guide vane comprises a first fan guide vane positioned in front of the inner duct and the first outer duct and a first blade tip fan guide vane positioned in the second outer duct; the second guide vanes comprise second fan guide vanes positioned at the inlet of the inner duct and second tip fan guide vanes positioned in the first outer duct; the first fan guide vane, the first blade tip fan guide vane, the second fan guide vane and the second blade tip fan guide vane can be respectively and independently adjusted, so that the air suction capacity of the inner duct and the air suction capacity of the outer duct can be adjusted in a matched mode, the flexible distribution of the flow of the inner duct and the flow of the outer duct of the engine is realized, and the free switching of the circulation modes of the engine under different tasks is supported. The invention adopts a sectional guide vane independent adjustment mode, can reduce an inner culvert flow adjustment structure and an outer culvert flow adjustment structure, reduces the design complexity of the engine, and can reduce the air flow mixing among a plurality of ducts in the engine and the flow loss caused by the air flow mixing.
Description
Technical Field
The invention relates to the field of aircraft engines, in particular to a double-bypass engine.
Background
Along with the continuous improvement of the complexity of the combat mission and the continuous expansion of the flight envelope, the aero-engine needs to have multiple power functions and higher propelling efficiency, so that the comprehensive performance of the engine in the full-flight envelope is optimal.
Conventional fixed ducted engines can only perform well over a limited range of flight than aircraft engines. For example, the turbojet engine has better supersonic velocity performance, large unit thrust and low oil consumption rate during high-Mach-number flight; the turbofan engine has good subsonic performance and low oil consumption rate during low Mach number flight. The variable cycle engine can have high altitude, high speed and large thrust and low altitude, low speed and low oil consumption capabilities by adjusting the bypass parameters of the engine. The self-adaptive engine is a further development of a variable cycle engine, an outer duct is added to form a three-outer-duct structure, the engine duct ratio is adjusted in a wide range by matching with a mode selection valve, a front duct ejector, a rear duct ejector and other adjusting structures, and the task adaptability of the engine is improved. Currently, various adaptive engine configuration schemes have been proposed in conjunction with specific tuning structures.
On the basis of a self-adaptive engine configuration, a contra-rotating fan is introduced in the patent US20050047942, and duct ejectors are respectively arranged between the contra-rotating fan and a core machine driving fan and between the core machine driving fan and a high-pressure compressor so as to enhance the engine duct ratio adjusting capacity.
On the basis of the self-adaptive engine configuration, the patent US20111067792A1 cancels a core machine driving fan, and adopts a variable fan system and a self-adaptive core machine with an axial flow/centrifugal combined high-pressure compressor, so that the adjusting capability of the internal and external bypass flow and the pressure ratio of the engine is enhanced.
On the basis of the self-adaptive engine configuration, a rear fan is arranged behind a low-pressure turbine and driven by a rear turbine connected with the rear fan, the rear fan blades extend upwards to a rear fan duct, and flow distribution of different ducts of the engine is realized by adjusting the rear fan and a front fan blade tip fan.
However, the current adaptive engine and its improved configuration scheme still have the following disadvantages:
1) and passive air-bleeding adjusting structures such as a mode selection valve and a front bypass ejector are mostly adopted, the compression capacity of the rotating blades is limited, the active distribution capacity of the inner bypass flow and the outer bypass flow is weaker, and the change range of the bypass ratio is limited.
2) The three-culvert structure is widely adopted, airflow mixing among a plurality of culverts in the engine and flow loss caused by the airflow mixing are increased, the structural form of the engine is complex, the structural design difficulty is high, and practical application and development are limited.
Disclosure of Invention
In order to solve at least one of the above technical problems, the present invention provides a dual culvert engine, so as to achieve the technical purposes of enhancing the active flow distribution capacity of the inner and outer culverts, reducing the mixing loss of the air flow of the inner and outer culverts, reducing the flow regulation structure of the inner and outer culverts, and simplifying the overall structure of the engine. The purpose of the invention is realized by adopting the following technical scheme:
a double-culvert engine comprises an inner culvert, a first outer culvert and a second outer culvert, wherein a fan is arranged at an inlet of the engine and comprises a first fan blade tip fan and a second fan blade tip fan; the first fan tip fan comprises a first movable blade and a first guide blade, the first movable blade comprises a first fan movable blade positioned in front of the inner duct and the first outer duct and a first tip fan movable blade extending to the second outer duct, and the first guide blade comprises a first fan guide blade positioned in front of the inner duct and the first outer duct and a first tip fan guide blade positioned in the second outer duct; the second fan tip fan comprises a second movable blade and a second guide blade, the second movable blade comprises a second fan movable blade positioned at the inlet of the inner duct and a second tip fan movable blade extending to the first outer duct, and the second guide blade comprises a second fan guide blade positioned at the inlet of the inner duct and a second tip fan guide blade positioned in the first outer duct; the second fan blade tip fan is arranged on the rear side of the first fan blade tip fan, and the second fan blade tip fan and the first fan blade tip fan form a nested fan blade tip fan together; the first fan guide vane, the first blade tip fan guide vane, the second fan guide vane and the second blade tip fan guide vane can be respectively and independently adjusted.
Further, the fan includes an intermediate stage fan positioned between the first fan tip fan and the second fan tip fan, the intermediate stage fan including intermediate stage buckets and intermediate stage guide vanes. Further, the tail end of the inner duct is also provided with a rear duct ejector, and the rear duct ejector is used for mixing the airflow of the first outer duct and the airflow of the inner duct.
Furthermore, the area of the rear duct ejector is adjustable.
Furthermore, an afterburner is arranged at the rear side of the rear duct ejector.
Furthermore, a throat and a main nozzle with adjustable nozzle area are arranged on the rear side of the afterburner.
Furthermore, the tail end of the second outer duct is also provided with an outer duct spray pipe with an adjustable nozzle area.
Further, a high-pressure compressor, a combustion chamber, a high-pressure turbine and a low-pressure turbine are sequentially arranged in the inner duct at the rear side of the second fan blade tip fan; the high-pressure turbine is used for driving the high-pressure compressor, and the low-pressure turbine is used for driving the fan.
Further, the high-pressure compressor is provided with a stator blade with an adjustable angle.
Further, the inlet of the low-pressure turbine is provided with an angle-adjustable guider.
Compared with the prior art, the invention has the advantages that: the invention provides a double-culvert engine, which comprises an inner culvert, a first outer culvert and a second outer culvert, wherein the inner culvert is connected with the first outer culvert; a fan is arranged at the inlet of the engine; the fan comprises a first fan tip fan and a second fan tip fan; the first fan tip fan comprises a first movable blade and a first guide blade, the first movable blade comprises a first fan movable blade positioned in front of the inner duct and the first outer duct and a first tip fan movable blade extending to the second outer duct, and the first guide blade comprises a first fan guide blade positioned in front of the inner duct and the first outer duct and a first tip fan guide blade positioned in the second outer duct; the second fan tip fan comprises a second movable blade and a second guide blade, the second movable blade comprises a second fan movable blade positioned at the inlet of the inner duct and a second tip fan movable blade extending to the first outer duct, and the second guide blade comprises a second fan guide blade positioned at the inlet of the inner duct and a second tip fan guide blade positioned in the first outer duct; the second fan blade tip fan is arranged on the rear side of the first fan blade tip fan, and the second fan blade tip fan and the first fan blade tip fan form a nested fan blade tip fan together; the first fan guide vane, the first blade tip fan guide vane, the second fan guide vane and the second blade tip fan guide vane can be respectively and independently adjusted, so that the air suction capacity of the inner duct and the air suction capacity of the outer duct can be adjusted in a matched mode, the flexible distribution of the flow of the inner duct and the flow of the outer duct of the engine is realized, and the free switching of the circulation modes of the engine under different tasks is supported. The invention adopts a sectional guide vane independent adjustment mode, can reduce an inner culvert flow adjustment structure and an outer culvert flow adjustment structure, reduces the design complexity of the engine, and can reduce the air flow mixing among a plurality of ducts in the engine and the flow loss caused by the air flow mixing.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the invention and together with the description serve to explain the principles of the invention.
FIG. 1 is a schematic overall view of a dual culvert engine of the present invention;
FIG. 2 is a partial schematic view of the dual-culvert engine of FIG. 1.
Reference numerals:
1. a fan; 2. a high pressure compressor; 3. a combustion chamber; 4. a high pressure turbine; 5. a low pressure turbine; 11. a first fan tip fan; 111. a first fan blade; 112. a first tip fan blade; 113. a first fan vane; 114. a first tip fan vane; 12. a second fan tip fan; 121. a second fan blade; 122. a second tip fan blade; 123. a second fan vane; 124. a second tip fan vane; 13. a first outer duct; 14. a second outer duct; 6. an afterburner; 7. a main nozzle; 8. an outer duct nozzle; 9. a rear duct ejector; 101. an engine inlet air stream; 102. a first culvert airflow; 103. a second culvert airflow; 104. the core gas stream.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and embodiments. It is to be understood that the specific embodiments described herein are for purposes of illustration only and are not to be construed as limitations of the invention. It should be noted that, for convenience of description, only the portions related to the present invention are shown in the drawings.
In addition, the embodiments of the present invention and the features of the embodiments may be combined with each other without conflict. The present invention will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.
Referring to fig. 1-2, to solve the above technical problems, the present invention provides a dual bypass engine, which includes a fan 1, a core engine, a low pressure turbine 5, an afterburner 6, a main nozzle 7, an bypass nozzle 8, an bypass, a first bypass 13, and a second bypass 14. The fan 1 is driven by a low-pressure turbine 5, the core machine comprises a high-pressure compressor 2, a combustion chamber 3 and a high-pressure turbine 4, the high-pressure compressor 2 is driven by the high-pressure turbine 4, the combustion chamber 3 is located between the high-pressure compressor 2 and the high-pressure turbine 4, and air flow is discharged from a main spray pipe 7 and an outer duct spray pipe 8.
The fan 1 is arranged at an inlet of the engine, and the fan 1 comprises a first fan tip fan 11 and a second fan tip fan 12. The two components together form the nested fan blade tip fan.
The first fan tip fan 11 is located at the engine inlet. The first fan tip fan 11 includes a first bucket and a first guide vane. The first blade comprises a first fan blade 111 located before the inner and first outer duct 13 and a first tip fan blade 112 extending to the second outer duct 14. Correspondingly, the first guide vane is divided into two sections, including a first fan guide vane 113 located in front of the inner duct and the first outer duct 13 and a first tip fan guide vane 114 located in the second outer duct 14, and the first fan guide vane 113 and the first tip fan guide vane 114 are independently adjustable. The first tip fan blades 112 and the first tip fan guide vanes 114 of the first fan tip fan 11 are located in the second ducted portion 14, and the suction capacity of the second ducted portion 14 can be adjusted. The first fan blade 111 and the first fan guide vane 113 of the first fan tip fan 11 are located in front of the first outer duct 13 and the inner duct, and the air suction capacity of the flow passage in which the first fan blade and the first fan guide vane are located may be adjusted.
The second fan tip fan 12 is located at the first outduct 13 and the inlcuet. Second fan tip fan 12 includes a second bucket and a second vane. The second blades comprise a second fan blade 121 at the endoprosthesis inlet and a second tip fan blade 122 extending to the first extraduct 13. Correspondingly, the second guide vane is divided into two sections, including a second fan guide vane 123 at the inlet of the inner duct and a second tip fan guide vane 124 at the inlet of the first outer duct 13, and the second fan guide vane 123 and the second tip fan guide vane 124 are independently adjustable. The second tip fan blades 122 and second tip fan guide vanes 124 of the second fan tip fan 12 are located in the first bypass duct 13, and the air suction capacity of the first bypass duct 13 may be adjusted. The second fan blades 121 and the second fan guide vanes 123 of the second fan tip fan 12 are located in front of the inner duct, and the air suction capacity of the flow passage in which they are located can be adjusted.
The sectional guide vanes of the front and rear fan blade tip fans can be respectively and independently adjusted; the blade tip fan of the first fan blade tip fan and the guide blade thereof are positioned in the second outer duct 14, so that the air suction capacity of the second outer duct can be adjusted, and the second outer duct 14 can be completely closed; the blade tip fan of the second fan blade tip fan and the guide blades thereof are positioned in the first outer culvert 13, so that the air suction capacity of the first outer culvert can be adjusted, and the first outer culvert 13 can be completely closed; in addition, the fans and the guide vanes of the two-stage fan blade tip fan can adjust the air suction capacity of a flow channel where the fans are located, and the air suction capacity of the first outer culvert and the air suction capacity of the second outer culvert are adjusted to jointly change the flow distribution of the inner culvert and the outer culvert of the engine, so that the engine can freely switch the circulation mode under different tasks.
The nested fan blade tip fan is adopted to construct the double-bypass engine, the air-bleeding type adjusting structures such as a core machine driving fan, a mode selection valve, a front duct ejector and the like of the existing variable-cycle/self-adaptive engine are cancelled, a core machine driving fan casing and a supporting structure thereof are omitted, the casing is prevented from being arranged in an engine outer duct, the form of the outer duct is greatly simplified, the radial size of the engine is reduced, the structure is more compact, the overall structural form of the engine is obviously simplified, and the weight reduction of the engine can be effectively realized; the dual bypass configuration reduces passive intermingling of gas flow between the ducts and the resulting flow losses.
Through the active adjustment of the first fan blade tip fan 11 and the second fan blade tip fan 12 on the internal and external bypass air suction capacities, compared with the existing variable-cycle/adaptive engine configuration, the required flow adjustment range of the high-pressure compressor 2 is reduced, and the design requirement of the high-pressure compressor 2 is lowered.
In a preferred embodiment, the fan 1 comprises an intermediate stage fan located between the first fan tip fan 11 and the second fan tip fan 12, the intermediate stage fan comprising intermediate stage blades and intermediate stage vanes. Therefore, the engine has a multi-stage air compression structure, and the air compression capacity of the inner duct and the first outer duct 13 is further improved.
Referring to fig. 1, a high-pressure compressor 2, a combustion chamber 3, a high-pressure turbine 4 and a low-pressure turbine 5 are further sequentially arranged in the inner duct at the rear side of the second fan blade tip fan 12; the high-pressure turbine 4 is used for driving the high-pressure compressor 2, and the low-pressure turbine 5 is used for driving the fan 1. The tail end of the inner duct is also provided with a rear duct ejector 9, and the rear duct ejector 9 is used for mixing the airflow of the first outer duct 13 with the airflow of the inner duct. And an afterburner 6 is arranged at the rear side of the rear duct ejector 9. And a main nozzle for discharging airflow after the afterburner 6 is arranged at the rear side of the afterburner 6. The end of the second bypass 14 is provided with a bypass nozzle 8 for discharging the airflow of the second bypass 14. When the engine is operating, the engine inlet airflow 101 is compressed and pressurized at the first fan tip fan 11 and then divided into a second bypass airflow 103 and a first fan tip fan 11 rear airflow. The second bypass airflow 103 is discharged from the bypass nozzles 8 via the second bypass 14. The airflow from the first fan tip fan 11 enters the second fan tip fan 12, is compressed and pressurized at the second fan tip fan 12, and then is divided into a first bypass airflow 102 and a core airflow 104, which enter a first bypass 13 and an inner bypass, respectively. The first bypass airflow 102 flows through the first bypass 13, then is mixed with the core airflow 104, enters the afterburner 6, finally enters the main nozzle 7 for further expansion, and then is discharged.
In addition, the double-culvert engine further comprises the following adjusting structure: the high-pressure compressor 2 is provided with a fixed blade with an adjustable angle, the inlet of the low-pressure turbine 5 is provided with a guider with an adjustable angle, the area of the rear duct ejector 9 is adjustable, the throat and nozzle area of the main nozzle 7 are adjustable, and the nozzle area of the outer duct nozzle 8 is adjustable. The adjusting structure is matched with the nested fan blade tip fan, so that the internal and external culvert flow of the engine can be adjusted.
According to the double-bypass engine adopting the nested fan blade tip fan, the segmented guide vanes and other matched adjusting structures of the nested fan blade tip fan are adjusted, the active allocation capacity of the internal bypass flow and the external bypass flow is enhanced, the working state of the engine can be adjusted according to task requirements, power modes such as turbojet, single-bypass turbofan and double-bypass turbofan are freely switched, and the full-envelope comprehensive propulsion efficiency of the engine is improved to be optimal. The power mode of the double-bypass engine adopting the nested fan blade tip fan comprises the following three modes:
a vortex spray mode. The first tip fan guide vanes 114 are turned down, the first fan guide vanes 113 are turned on, the air suction capacity of the second bypass duct 14 is weakened, and the flow rate of the second bypass airflow 103 is reduced; the second tip fan guide vane 124 is closed and the second fan guide vane 123 is opened, so that the air suction capacity of the first bypass 13 is weakened, and the flow of the first bypass airflow 102 is reduced; and correspondingly adjusting other adjusting structures according to the requirements, matching with the fan adjustment, and correspondingly adjusting the flow of the core airflow 104 to obtain the working state of the engine meeting the task requirements. In the turbojet mode, the flow rates of the first bypass airflow 102 and the second bypass airflow 103 both approach zero, the bypass ratio approaches zero, and the minimum bypass ratio state can be realized.
Single culvert turbofan mode. The first tip fan guide vanes 114 are turned down, the first fan guide vanes 113 are turned on, the air suction capacity of the second bypass duct 14 is weakened, and the flow rate of the second bypass airflow 103 is reduced; the second tip fan guide vanes 124 are opened, the second fan guide vanes 123 are closed, the air suction capacity of the first bypass 13 is enhanced, and the flow of the first bypass airflow 102 is increased; and correspondingly adjusting other adjusting structures according to the requirements, matching with the fan adjustment, and correspondingly adjusting the flow of the core airflow 104 to obtain the working state of the engine meeting the task requirements. The first bypass airflow 102 is large in flow rate and the second bypass airflow 103 is close to zero in the single bypass turbofan mode, and a middle bypass ratio state can be achieved.
Double culvert turbofan mode. The first tip fan guide vanes 114 are opened, the first fan guide vanes 113 are closed, the air suction capacity of the second bypass duct 14 is enhanced, and the flow rate of the second bypass airflow 103 is increased; the second tip fan guide vanes 124 are opened, the second fan guide vanes 123 are closed, the air suction capacity of the first bypass 13 is enhanced, and the flow of the first bypass airflow 102 is increased; and correspondingly adjusting other adjusting structures according to the requirements, matching with the fan adjustment, and correspondingly adjusting the flow of the core airflow 104 to obtain the working state of the engine meeting the task requirements. The first bypass airflow 102 and the second bypass airflow 103 have large flow rates in the double bypass turbofan mode, and the maximum bypass ratio state can be realized.
In summary, the segmented guide vanes of the front-stage fan blade tip fan and the rear-stage fan blade tip fan of the double-bypass engine provided by the invention are respectively and independently adjusted, so that the air suction capacities of the inner duct and the outer duct can be adjusted in a matching manner, the flexible distribution of the flow of the inner bypass and the outer bypass of the engine is realized, and the free switching of the circulation modes of the engine under different tasks is supported.
In the description herein, reference to the description of the terms "one embodiment/mode," "some embodiments/modes," "example," "specific example," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment/mode or example is included in at least one embodiment/mode or example of the application. In this specification, the schematic representations of the terms used above are not necessarily intended to be the same embodiment/mode or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments/modes or examples. Furthermore, the various embodiments/aspects or examples and features of the various embodiments/aspects or examples described in this specification can be combined and combined by one skilled in the art without conflicting therewith.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating 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 the description of the present application, "plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
It will be understood by those skilled in the art that the foregoing embodiments are merely for clarity of description and are not intended to limit the scope of the invention. Other variations or modifications will occur to those skilled in the art based on the foregoing disclosure and are within the scope of the invention.
Claims (10)
1. The utility model provides a two culvert engines, includes the outer duct of interior duct, first outer duct and second, its characterized in that: a fan is arranged at the inlet of the engine and comprises a first fan blade tip fan and a second fan blade tip fan;
the first fan tip fan comprises a first movable blade and a first guide blade, the first movable blade comprises a first fan movable blade positioned in front of the inner duct and the first outer duct and a first tip fan movable blade extending to the second outer duct, and the first guide blade comprises a first fan guide blade positioned in front of the inner duct and the first outer duct and a first tip fan guide blade positioned in the second outer duct;
the second fan tip fan comprises a second movable blade and a second guide blade, the second movable blade comprises a second fan movable blade positioned at the inlet of the inner duct and a second tip fan movable blade extending to the first outer duct, and the second guide blade comprises a second fan guide blade positioned at the inlet of the inner duct and a second tip fan guide blade positioned in the first outer duct;
the first fan guide vane, the first blade tip fan guide vane, the second fan guide vane and the second blade tip fan guide vane can be respectively and independently adjusted.
2. A dual culvert engine as defined in claim 1, further characterized by: the fan includes an intermediate stage fan positioned between the first fan tip fan and the second fan tip fan, the intermediate stage fan including intermediate stage blades and intermediate stage guide vanes.
3. A dual culvert engine as defined in claim 1, further characterized by: the tail end of the inner duct is also provided with a rear duct ejector, and the rear duct ejector is used for mixing the airflow of the first outer duct and the airflow of the inner duct.
4. A dual culvert engine as defined in claim 3 further characterized by: the area of the rear duct ejector is adjustable.
5. A dual culvert engine as defined in claim 3 further characterized by: the rear side of the rear duct ejector also comprises an afterburner.
6. A dual culvert engine as defined in claim 5, further characterized by: and the rear side of the afterburner is also provided with a throat and a main nozzle with adjustable nozzle area.
7. A dual culvert engine as defined in claim 5, further characterized by: the tail end of the second outer duct is also provided with an outer duct spray pipe with an adjustable nozzle area.
8. A dual culvert engine as defined in any one of claims 1-7, further characterized by: a high-pressure compressor, a combustion chamber, a high-pressure turbine and a low-pressure turbine are sequentially arranged in the inner duct at the rear side of the second fan blade tip fan; the high-pressure turbine is used for driving the high-pressure compressor, and the low-pressure turbine is used for driving the fan.
9. A dual culvert engine as defined in claim 8, further characterized by: the high-pressure compressor is provided with a stationary blade with an adjustable angle.
10. A dual culvert engine as defined in claim 8, further characterized by: and the inlet of the low-pressure turbine is provided with a guider with an adjustable angle.
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113864083A (en) * | 2021-10-12 | 2021-12-31 | 中国航发湖南动力机械研究所 | Novel variable-cycle gas turbine engine |
| CN114215788A (en) * | 2021-11-30 | 2022-03-22 | 中国航发沈阳发动机研究所 | Counter-rotating stamping gas compressor |
| CN114251188A (en) * | 2021-12-22 | 2022-03-29 | 北京航空航天大学 | Spray pipe structure based on self-adaptive variable-cycle engine |
| CN114876665A (en) * | 2022-05-13 | 2022-08-09 | 中国航空发动机研究院 | Variable cycle engine compression system |
| CN115263598A (en) * | 2022-07-28 | 2022-11-01 | 北京航空航天大学 | Double-variable-duct wide-speed-range high-flux rheological cycle engine configuration |
| CN115523054A (en) * | 2022-10-13 | 2022-12-27 | 中国航发湖南动力机械研究所 | Double-runner fan structure with adjustable inner and outer culvert guide vanes and aero-engine |
| CN116201656A (en) * | 2023-03-10 | 2023-06-02 | 中国科学院工程热物理研究所 | Turbojet propulsion power system suitable for hypersonic cruising of unmanned aerial vehicle |
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| CN113864083A (en) * | 2021-10-12 | 2021-12-31 | 中国航发湖南动力机械研究所 | Novel variable-cycle gas turbine engine |
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| CN115263598A (en) * | 2022-07-28 | 2022-11-01 | 北京航空航天大学 | Double-variable-duct wide-speed-range high-flux rheological cycle engine configuration |
| CN115523054A (en) * | 2022-10-13 | 2022-12-27 | 中国航发湖南动力机械研究所 | Double-runner fan structure with adjustable inner and outer culvert guide vanes and aero-engine |
| CN116201656A (en) * | 2023-03-10 | 2023-06-02 | 中国科学院工程热物理研究所 | Turbojet propulsion power system suitable for hypersonic cruising of unmanned aerial vehicle |
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