CN113586282B - Multistage turbofan engine with series supercharging function - Google Patents
Multistage turbofan engine with series supercharging function Download PDFInfo
- Publication number
- CN113586282B CN113586282B CN202110911970.7A CN202110911970A CN113586282B CN 113586282 B CN113586282 B CN 113586282B CN 202110911970 A CN202110911970 A CN 202110911970A CN 113586282 B CN113586282 B CN 113586282B
- Authority
- CN
- China
- Prior art keywords
- turbofan
- driving unit
- stage
- engine
- pressurizing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/003—Arrangements for testing or measuring
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
- F02K1/82—Jet pipe walls, e.g. liners
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Architecture (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a multistage turbofan engine with a series supercharging function, belonging to the technical field of aviation turbofan engines. The invention solves the problem that the blade efficiency of the conventional open type single-stage propeller engine is low when the load is large and the air flow speed is high, improves the overall output efficiency of the engine through the continuous turbocharging capacity of the pressurizing duct and the multistage turbofan driving unit which are closed in the middle and the pressurizing jet flow function of the tail pressurizing nozzle, and can improve the interstage pressurizing efficiency and reduce the weight of the engine through the reverse contra-rotation of two adjacent stages of blades under the condition of not increasing the static blades. A high efficiency drive power system for a new helicopter or related aircraft having turbine fan blades enclosed within an acceleration duct.
Description
Technical Field
The invention relates to the technical field of aviation turbofan engines, in particular to a multistage turbofan engine with a series supercharging function.
Background
The driving devices of common helicopters, quad-rotor unmanned planes and the like are generally open single-propeller or double-propeller rotor systems. The lift generated by the propeller is approximately inversely related to the velocity of the airflow downward through the propeller. When the velocity of the vertically downward air flow through the helicopter propellers is excessive, it results in a rapid decrease in the lift of the propellers and in the efficiency of the engine, thereby affecting and limiting the further increase in the load carrying capacity and endurance of a conventional helicopter or multi-rotor drone. To this end, a multi-stage turbofan engine with a series supercharging function is proposed.
Chinese utility model patent application publication No. CN209483501U, published 2019, 10 and 11 discloses a multi-stage electric turbofan jet engine, which has the following disadvantages: between two opposite motor turbine blades, the structure rotation direction is not reversed; the moving direction is not reversely contra-rotating during working; in the technical scheme, the circumferential high-speed rotation of airflow is prevented by the stator blade fans, and the arrangement of a large number of stator blade fans increases the weight of the engine and reduces the thrust-weight ratio and the continuous supercharging efficiency of the engine. To this end, a multi-stage turbofan engine with a series supercharging function is proposed.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: how to solve because of the setting of a large amount of quiet leaf fans, increased the weight of engine itself, reduced the thrust-weight ratio of engine and the problem of lasting supercharging efficiency, provide a multistage turbofan engine with series connection pressure boost function.
The invention solves the technical problems by the following technical scheme, and the invention comprises a pressurizing duct, a multi-stage turbofan and a tail pressurizing nozzle, wherein the pressurizing duct comprises a low-pressure airflow inlet, a medium-pressure accelerating channel and a high-pressure accelerating channel which are sequentially arranged;
each stage of turbo fan in the low-pressure airflow inlet, the medium-pressure accelerating channel and the high-pressure accelerating channel comprises two or more than two paired turbo fans which are close to each other, and the moving directions of the paired turbo fan blades are in a reverse counter-rotating state during working.
Further, the multi-stage turbofan engine further includes a plurality of driving units for driving each stage of the turbofan, and directly controls the rotational speed and output power of each stage of the turbofan.
Furthermore, each stage of turbofan comprises four turbofan bodies, namely a first turbofan body, a second turbofan body, a third turbofan body and a fourth turbofan body which are sequentially arranged from head to tail, the driving unit comprises a first driving unit, a middle driving unit and a second driving unit which are sequentially arranged from head to tail, the first turbofan body is connected with the first driving unit, the second turbofan body and the third turbofan body are respectively connected with the middle driving unit, and the fourth turbofan body is connected with the second driving unit.
Furthermore, a supporting plate is arranged between the first driving unit and the pressurizing duct, the first driving unit is connected with the pressurizing duct through the supporting plate, fixed blades are arranged between the middle driving unit and the pressurizing duct, the middle driving unit and the second driving unit are connected with the pressurizing duct through the fixed blades, the rotating directions of blade structures of the first turbofan and the second turbofan are opposite, the rotating directions of blade structures of the second turbofan and the fixed blade structures on the middle driving unit are opposite, the rotating directions of blade structures of the third turbofan and the fourth turbofan are opposite, and the rotating directions of blade structures of the fourth turbofan and the fixed blade structures on the second driving unit are opposite.
Furthermore, the multi-stage turbofan engine further comprises a driving unit for driving each stage of turbofan in the multi-stage turbofan, a transmission structure is arranged between the driving unit and each stage of turbofan, and the driving unit indirectly controls the rotating speed and the output power of each stage of turbofan through the transmission structure.
Further, the driving unit is a motor driving unit or a chemical fuel driving unit.
Furthermore, the pressurizing duct is any one of a linear airflow pressurizing channel, an arc curve channel and a right-angle turning type airflow continuous pressurizing channel.
Furthermore, the outer surface of the pressurizing duct is coated with an electromagnetic wave absorbing material.
Furthermore, the nozzle outlet structure of the tail pressurizing nozzle is designed into a Laval nozzle form.
Furthermore, the cross-sectional area a of the tail supercharging nozzle is adjusted, tested and finally fixed according to the formula (1), and the adjustment is aimed at enabling the engine to give a fixed rated input total power PinputIn the state (2), the most efficient output efficiency η:
wherein:
eta is given rated input total power PinputIn the state (2), the engine output efficiency;
Poutputoutputting power for the engine;
vmeanis the average flow rate of gas through the engine pressurization duct;
rho is the gas density at the minimum section of the tail pressurizing nozzle;
q is the volume flow of the air flow passing through the engine pressurizing duct in unit time;
a is the sectional area of the smallest section of the tail pressurizing nozzle.
Compared with the prior art, the invention has the following advantages: the multistage turbofan engine with the series supercharging function solves the problem that a conventional open type single-stage propeller engine is low in blade efficiency when the load is large and the air flow speed is high, and improves the overall output efficiency of the engine through the continuous turbocharging capacity of the pressurization duct and the multistage turbofan driving unit which are closed in the middle and the supercharging jet flow function of the tail supercharging nozzle; under the condition of not increasing the fixed blades, the interstage supercharging efficiency is improved and the total weight of the engine is reduced through the reverse contrarotation of two adjacent stages of blades; the high-efficiency driving power system can be used for a novel helicopter or a related aircraft with turbine fan blades enclosed in an accelerating duct, and is worthy of being popularized and used.
Drawings
FIG. 1 is a schematic view of the internal structure of a multi-stage turbofan engine having a series supercharging function according to an embodiment of the present invention;
FIG. 2 is an enlarged view of the internal structure of the low pressure gas stream inlet of the present invention with a portion of the housing removed.
Detailed Description
The following examples are given for the detailed implementation and specific operation of the present invention, but the scope of the present invention is not limited to the following examples.
As shown in fig. 1 and 2, the present embodiment provides a technical solution: a multi-stage turbofan engine with a series supercharging function comprises a pressurization duct 1, an airflow inlet 4, multi-stage turbofan 3 and a tail supercharging nozzle 7, wherein the airflow inlet 4 is arranged at the foremost end of the pressurization duct 1, the tail supercharging nozzle 7 is connected to the tail of the pressurization duct 1, the multi-stage turbofan 3 is installed and distributed in the pressurization duct 1 in a series mode, the airflow sectional area of the tail supercharging nozzle 7 is smaller than the airflow inlet 4 and the sectional area of the pressurization duct 1, and the tail supercharging nozzle 7 can perform throttling supercharging on airflow in the pressurization duct 1;
each stage of turbofan in the low-pressure airflow inlet, the medium-pressure accelerating channel and the high-pressure accelerating channel comprises two or more than two paired turbofan 11, 12, 13 and 14 which are close to each other, and the paired turbofan blades are in a reverse contra-rotating state in the moving direction during working. That is, the moving direction of the blades of the turbo fans 11 and 12 is in the counter-rotating state during operation, and the moving direction of the blades of the turbo fans 13 and 14 is also in the counter-rotating state during operation, and it is not necessary to add additional stationary blade guide blades therebetween.
In the present embodiment, the turbofan 11, 12, 13, 14 is connected to the respective drive unit 15, 2, 16, the drive unit 15 is connected to the external pressurizing duct 1 through the support plate 8, the drive unit 2 is connected to the external pressurizing duct 1 through the stationary blade 9, the drive unit 16 is connected to the external pressurizing duct 1 through the stationary blade 10, the blade structure rotation directions of the turbofan 11, 12 are opposite, the blade structure rotation directions of the turbofan 12 are opposite to the rear stationary blade 9 structure rotation directions, the blade structure rotation directions of the turbofan 13, 14 are opposite, and the blade structure rotation directions of the turbofan 14 are opposite to the rear stationary blade 10 structure rotation directions.
In the embodiment, the multistage turbofan engine further comprises a single motor driving unit or a single chemical fuel driving unit, and the rotating speed and the output power of each stage turbofan are indirectly controlled through a gear or pulley transmission mode.
In this embodiment, the pressurizing duct 1 may be a linear airflow pressurizing passage, an arc curve passage, or a right-angle turning airflow continuously pressurizing passage.
In this embodiment, the outer surface of the pressurizing duct 1 is coated with an electromagnetic wave absorbing material, so that the surface of the pressurizing duct 1 has a function of absorbing radar waves.
In the present embodiment, the cross-sectional airflow area a of the rear supercharging nozzle 7 is adjusted, tested and finally fixed according to the formula (1), and the adjustment is aimed at enabling the engine to have a fixed rated total input power PinputIn the state (2), the most efficient output efficiency η:
wherein:
eta-given nominal input total power PinputIn the state (2), the engine output efficiency;
Poutput-engine output power;
vmean-mean flow velocity of gases through the engine duct;
rho is the gas density at the minimum section of the tail nozzle;
q is the volume flow of the air flow passing through the engine bypass in unit time;
a is the sectional area of the minimum part of the section of the tail nozzle.
Example two
As shown in fig. 1, the pressurizing duct 1 in the present embodiment includes a low-pressure airflow inlet 4, a medium-pressure accelerating passage 5, and a high-pressure accelerating passage 6, and the low-pressure airflow inlet 4, the medium-pressure accelerating passage 5, and the high-pressure accelerating passage 6 are sequentially and integrally formed. The tail part of the pressurizing duct 1 is connected with a tail pressurizing nozzle 7, and the tail pressurizing nozzle is used for converting high-pressure air flow in the pressurizing duct 1 into high-speed low-pressure air flow which is sprayed out from the tail pressurizing nozzle 7. The nozzle outlet structure of the aft booster nozzle 7 may be designed in the form of a laval nozzle to enhance jet propulsion efficiency. The multistage turbofan 3 in the pressurizing duct 1 is installed pairwise, and each pair of blades are in a reverse counter-rotating state when working, so that the self-rotating speed of airflow in the duct is reduced, and the pressurizing efficiency of each stage of turbofan is improved. For example, the moving direction of the blades of the turbo fans 11 and 12 is in a counter-rotating state, and the moving direction of the blades of the turbo fans 13 and 14 is in a counter-rotating state, and it is not necessary to add additional stationary blade guide blades in the middle.
At a given rated input power P of each turbofaninputIn this case, the minimum cross-sectional area a of the rear pressurizing nozzle 7 is adjusted. According to the formula
Adjusting the cross-sectional area A (v)mean-average flow rate of gas through the engine duct; ρ — the gas density at the minimum of the nozzle cross-section at the tail) to achieve the highest power output efficiency η. As the jet flow sectional area a of the tail supercharging nozzle gradually increases from zero, the engine output efficiency η is in a variable relationship of first rising and then falling. Therefore, the maximum output efficiency eta can be found through the test of constantly changing the sectional area A, and then the most efficient and optimal working state of the series supercharged multi-stage turbofan engine can be found by fixing the corresponding nozzle sectional area A at the moment.
The working principle is as follows: in the engine pressurizing duct 1, high-pressure airflow pressurized by the multistage turbofan 3 is converted into high-speed airflow again through a contraction tail nozzle with a proper sectional area, and the high-speed airflow is ejected out through the tail nozzle at a high speed, so that the whole efficient working process of the engine with air inlet, multistage pressurization and pressure release ejection is finally completed.
In summary, the multi-stage turbofan engine with the series supercharging function according to the above embodiment can increase the airflow compression ratio passing through the rear stage turbofan rotor, and reduce the airflow speed, so that the multi-stage turbofan driving unit of the engine works in a state of passing through the most efficient airflow with low flow rate and high compression ratio, thereby increasing the overall output efficiency of the multi-stage turbofan system; the blades are sealed in the engine pressurizing duct, so that the blades are protected and prevented from being damaged by foreign matters, meanwhile, the turbine blades arranged in the sealed channel can protect people, animals, buildings and the like around an aircraft provided with the engine relative to an ordinary propeller exposed outside, and personnel or other property events around the aircraft are prevented from being scratched by the high-speed rotor due to improper operation; a plurality of turbine rotors are connected in series in a closed accelerating and pressurizing duct in a closed mode, the duct can be designed into a straight line mode, an arc-shaped curve mode and the like, an aircraft provided with the engine does not have exposed propellers, and the appearance is attractive; by coating the electromagnetic wave absorbing material on the outer surface, the radar reflection cross section of the engine is reduced, so that the engine has stealth capability for radar detection, and is worthy of popularization and application.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art within the scope of the present invention.
Claims (2)
1. A multi-stage turbofan engine with a series supercharging function is characterized by comprising a pressurizing duct, a multi-stage turbofan and a tail supercharging nozzle, wherein the pressurizing duct comprises a low-pressure airflow inlet, a medium-pressure accelerating channel and a high-pressure accelerating channel which are sequentially arranged;
each stage of turbo fan in the low-pressure airflow inlet, the medium-pressure accelerating channel and the high-pressure accelerating channel comprises two or more turbo fans which are closely arranged in pairs, and the moving directions of the turbo fan blades arranged in pairs are in a reverse counter-rotating state during working;
the multi-stage turbofan engine also comprises a plurality of driving units for driving each stage of turbofan in the multi-stage turbofan, and the driving units directly control the rotating speed and the output power of each stage of turbofan;
each stage of turbofan comprises four turbofan bodies, namely a first turbofan body, a second turbofan body, a third turbofan body and a fourth turbofan body which are sequentially arranged from head to tail, the driving unit comprises a first driving unit, a middle driving unit and a second driving unit which are sequentially arranged from head to tail, the first turbofan body is connected with the first driving unit, the second turbofan body and the third turbofan body are respectively connected with the middle driving unit, and the fourth turbofan body is connected with the second driving unit.
2. The multi-stage turbofan engine having a series boosting function of claim 1 wherein: the first driving unit and the pressurizing duct are provided with a supporting plate therebetween, the first driving unit and the pressurizing duct are connected through the supporting plate, the middle driving unit, the second driving unit and the pressurizing duct are provided with fixed blades therebetween, the middle driving unit, the second driving unit and the pressurizing duct are connected through the fixed blades, the rotating directions of blade structures of the first turbofan and the second turbofan are opposite, the rotating directions of blades of the second turbofan are opposite to those of the fixed blade structures on the middle driving unit, the rotating directions of blade structures of the third turbofan and the fourth turbofan are opposite, and the rotating directions of blades of the fourth turbofan are opposite to those of the fixed blade structures on the second driving unit.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210399729.5A CN114704407A (en) | 2021-08-10 | 2021-08-10 | Multistage turbofan engine |
| CN202110911970.7A CN113586282B (en) | 2021-08-10 | 2021-08-10 | Multistage turbofan engine with series supercharging function |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110911970.7A CN113586282B (en) | 2021-08-10 | 2021-08-10 | Multistage turbofan engine with series supercharging function |
Related Child Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210399729.5A Division CN114704407A (en) | 2021-08-10 | 2021-08-10 | Multistage turbofan engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113586282A CN113586282A (en) | 2021-11-02 |
| CN113586282B true CN113586282B (en) | 2022-06-07 |
Family
ID=78256602
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110911970.7A Active CN113586282B (en) | 2021-08-10 | 2021-08-10 | Multistage turbofan engine with series supercharging function |
| CN202210399729.5A Pending CN114704407A (en) | 2021-08-10 | 2021-08-10 | Multistage turbofan engine |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210399729.5A Pending CN114704407A (en) | 2021-08-10 | 2021-08-10 | Multistage turbofan engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (2) | CN113586282B (en) |
Family Cites Families (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2195712B (en) * | 1986-10-08 | 1990-08-29 | Rolls Royce Plc | A turbofan gas turbine engine |
| DE3738703A1 (en) * | 1987-05-27 | 1988-12-08 | Mtu Muenchen Gmbh | COMBINED, SWITCHABLE JET ENGINE FOR DRIVING PLANES AND SPACES |
| US4936748A (en) * | 1988-11-28 | 1990-06-26 | General Electric Company | Auxiliary power source in an unducted fan gas turbine engine |
| US5010729A (en) * | 1989-01-03 | 1991-04-30 | General Electric Company | Geared counterrotating turbine/fan propulsion system |
| USH2032H1 (en) * | 1999-10-01 | 2002-07-02 | The United States Of America As Represented By The Secretary Of The Air Force | Integrated fan-core twin spool counter-rotating turbofan gas turbine engine |
| US20080175703A1 (en) * | 2007-01-09 | 2008-07-24 | Sonic Blue Aerospace | Electric turbine bypass fan and compressor for hybrid propulsion |
| US8313280B2 (en) * | 2006-10-12 | 2012-11-20 | United Technologies Corporation | Method and device to avoid turbo instability in a gas turbine engine |
| US9476385B2 (en) * | 2012-11-12 | 2016-10-25 | The Boeing Company | Rotational annular airscrew with integrated acoustic arrester |
| CN103921931A (en) * | 2014-04-28 | 2014-07-16 | 龙川 | Duct wing system and aircraft using same |
| GB201412189D0 (en) * | 2014-07-09 | 2014-08-20 | Rolls Royce Plc | A nozzle arrangement for a gas turbine engine |
| US20180118364A1 (en) * | 2016-11-03 | 2018-05-03 | The Boeing Company | System and method for augmenting a primary powerplant |
| CN106586001A (en) * | 2016-11-30 | 2017-04-26 | 中国电子科技集团公司第三十八研究所 | Multimode and multi-based unmanned aerial vehicle with tailed flying wing configuration |
| CN108518289A (en) * | 2018-05-17 | 2018-09-11 | 南京航空航天大学 | A kind of blade tip jet is from driving wheel-type Duct-Burning Turbofan |
| CN109899177B (en) * | 2018-08-08 | 2023-02-17 | 珠海市蓝鹰贸易有限公司 | Multi-core aircraft with afterburner turbofan aviation power system and aircraft |
| CN209483501U (en) * | 2019-02-28 | 2019-10-11 | 杜元君 | Multi-stage motor turbofan |
| CN112849393B (en) * | 2021-01-24 | 2023-01-24 | 西北工业大学 | Miniaturized duct aircraft |
-
2021
- 2021-08-10 CN CN202110911970.7A patent/CN113586282B/en active Active
- 2021-08-10 CN CN202210399729.5A patent/CN114704407A/en active Pending
Also Published As
| Publication number | Publication date |
|---|---|
| CN113586282A (en) | 2021-11-02 |
| CN114704407A (en) | 2022-07-05 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US11988099B2 (en) | Unducted thrust producing system architecture | |
| WO2021164549A1 (en) | Electric energy-driven jet aircraft engine and aircraft | |
| US20060034691A1 (en) | Supersonic compressor | |
| US20100232953A1 (en) | Hybrid compressor | |
| CN113236441B (en) | Turboshaft fan bimodal engine and adjusting method thereof | |
| JP2013506082A (en) | Convertible fan engine with 2-block compressor | |
| US10174763B1 (en) | Variable pitch fan for gas turbine engine | |
| WO2013009643A2 (en) | Supersonic compressor | |
| US5246188A (en) | Wing turbines in conjuction with propulsion systems for aircraft and helicopters | |
| CN209800119U (en) | Self-driven outer duct contra-rotating annular fan blade compression device | |
| Broichhausen et al. | Supersonic and transonic compressors: past, status and technology trends | |
| US11608743B1 (en) | Low-noise blade for an open rotor | |
| GB2193999A (en) | Gas turbine engine with variable bypass means | |
| US20030210980A1 (en) | Supersonic compressor | |
| CN113586282B (en) | Multistage turbofan engine with series supercharging function | |
| CN112483275B (en) | Propeller and aircraft | |
| CN114856856A (en) | High-lift-limit low-oil-consumption medium bypass ratio variable cycle engine | |
| CN205064122U (en) | Aviation air injection motor | |
| CN113738533B (en) | Independent driving turbofan system of series-connection supercharged electric turbine engine | |
| CN209800118U (en) | Self-driven outer duct annular fan blade compression device | |
| CN113847165B (en) | Series connection supercharging type electric turbine engine double-output-shaft motor turbofan system | |
| CA2658412C (en) | Hybrid compressor | |
| CN219840723U (en) | Distributed propulsion variable cycle engine | |
| GB2379483A (en) | Augmented gas turbine propulsion system | |
| CN113864084B (en) | Stepped sectional turbofan system of series supercharged electric turbine engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |