CN116576040A - Middle-variable bypass ratio turbofan engine configuration based on double-fan structure - Google Patents
Middle-variable bypass ratio turbofan engine configuration based on double-fan structure Download PDFInfo
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Classifications
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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
- 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
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
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- 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
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/057—Control or regulation
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/075—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type controlling flow ratio between flows
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- 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
- F02K3/077—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 the plant being of the multiple flow type, i.e. having three or more flows
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- 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
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- Combustion & Propulsion (AREA)
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Abstract
The invention provides a medium-variable bypass ratio turbofan engine structure based on a double-fan structure, in particular to a double-fan and adjustable-nozzle turbofan engine structure with inlet adjustable blades, and a low-pressure fan and a high-pressure fan are arranged by adopting the double-fan structure and respectively intake and boost air, so that the bypass ratio adjusting range is enlarged, and the working change range of a single-stage fan is reduced; the variable diversion cone and the adjustable blades of the high-pressure fan inlet are arranged, and the flow ratio of the outer culvert runner and the inner culvert runner is adjusted by controlling the angles of the variable diversion cone and the adjustable blades, so that different culvert ratios are realized, which is the key point for realizing medium variable culvert ratios; by arranging the second culvert and introducing partial flow of the inner culvert into the outer culvert, the adjusting range of the culvert ratio is further enlarged, and the medium change culvert ratio in the range of 3-6 is realized, so that the high-altitude cruise unmanned aerial vehicle has the advantages of large adjusting range of the culvert ratio, strong high-altitude climbing capability and low high-altitude cruising fuel consumption rate, and is suitable for the power requirement of high-altitude long-endurance unmanned aerial vehicles.
Description
Technical Field
The invention belongs to the technical field of aeroengines, in particular to the technical field of aero turbofan engines, relates to a medium-duct-ratio turbofan engine structure, and particularly relates to a double-fan double-duct pneumatic layout structure form applied to a medium-duct-ratio double-shaft turbofan engine.
Background
The unmanned aerial vehicle (High Altitude Long Endurance Unmanned Aerial Vehicle, HALE UAV) is an unmanned aerial vehicle capable of flying at high altitude and leaving air for a long time, generally, the flying height of the unmanned aerial vehicle is above 15000 meters, and the leaving air time can reach days or longer, and has higher stealth performance. Compared with the traditional manned plane or satellite, the unmanned plane for high altitude long endurance has the advantages of low cost, high flexibility, reusability, capability of carrying various loads and the like, and can meet the requirements of military and civil fields for long-time, large-range and high-precision monitoring and reconnaissance, communication coverage, meteorological observation, environment monitoring, search and rescue and the like. In order to improve the information acquisition capability, the task execution efficiency and the battlefield viability of the unmanned aerial vehicle, the flying height of the unmanned aerial vehicle is higher and higher, the requirement on the time for reserving the air is longer and longer, and the stealth requirement is higher and higher.
In order to realize longer air time and stronger stealth performance, higher requirements are put forward on the performance and design of the engine of the high-altitude long-endurance unmanned aerial vehicle. In order to realize that the longer idle time has higher and higher requirements on the fuel consumption rate of the engine, a low-fuel-consumption engine design is generally required to be adopted so as to prolong the flight time of the unmanned aerial vehicle to the maximum extent. This generally requires the engine to have efficient combustion and thrust output, as well as a low specific fuel consumption. For example, turbofan engines typically have higher efficiency in high-altitude flights because they can take advantage of the rarefaction and airflow of the atmosphere to reduce air drag and energy consumption. In order to achieve stronger stealth performance, a smaller engine size and a fully covered inlet and outlet design are generally needed, so that the overall size and radar reflection sectional area of the unmanned aerial vehicle are reduced, and the stealth performance is improved. To achieve this goal, stringent requirements are often placed on the diameter of the engine so that full coverage of the access opening can be achieved to minimize reflected signals. In addition, factors such as reliability of the engine, maintenance cost, and the like need to be considered.
In order to meet the demanding requirements of high-altitude long-endurance unmanned aerial vehicles, engines need to employ as high a bypass ratio as possible to reduce fuel consumption. The bypass ratio is one of the main performance indexes of the aero-engine, and refers to the ratio of the external bypass air flow to the internal bypass air flow. In general, the higher the bypass ratio, the lower the fuel consumption of the aeroengine, since the greater the air flow entering the propeller, bypassing the engine core, the lower the exhaust speed, the higher the propulsion efficiency, and the lower the fuel consumption, with the same thrust produced. The higher bypass ratio can improve the fuel efficiency and the thrust output of the engine, but the weight and the size of the engine are increased, and under the strict requirements of the size and the weight, the thrust of the engine with the high bypass ratio is limited, so that the unmanned aerial vehicle is easy to realize high-altitude climbing without enough thrust, and the climbing height is limited; in addition, the thrust of the engine cannot support the high-speed flight of the aircraft, so that the thrust level of the engine needs to be greatly improved under the two states, and a medium-change bypass ratio turbofan engine needs to be developed. The small bypass ratio is adopted in the climbing and high-speed flight process of the aircraft, so that a large thrust is provided for supporting the aircraft, and the climbing height and speed of the aircraft are improved; the high-altitude cruise control system has the advantages that a large bypass ratio is adopted in the high-altitude cruise of the aircraft, so that the whole-course fuel consumption is reduced, the air-leaving time of the aircraft is prolonged, and the range is further prolonged.
The change of the bypass ratio of the turbofan engine is realized, and the ratio of the flow of the external culvert to the flow of the internal culvert is mainly required to be changed. Under the condition that the total flow of the inlet is unchanged, increasing the flow of connotation can improve the quality of air working medium entering the combustion chamber and promote the thrust of the engine. In order to realize the change of the internal and external culvert flow of the turbofan engine, the geometric structures of an engine compression system and an exhaust system are required to be changed, so that the purpose of the change of the culvert ratio is achieved, and in the prior art, the adjustment and the change of the culvert ratio of the engine can be realized to a certain extent by using a wide-speed-range variable cycle engine based on an interstage combustion chamber driving low-pressure turbine rotor disclosed in a Chinese patent application CN202210488043.3, a three-culvert ACE engine with a fly fan and a core engine driving fan stage disclosed in a CN202110937625.0 and the like. However, the prior art including the above-mentioned patents still faces certain difficulties and challenges in achieving a change in the bypass ratio of turbofan engines (e.g., achieving a medium change bypass ratio of 3 to 6), mainly expressed in: the turbofan engine has a wider working range, and needs to meet two working states of low speed and high speed, so that key components such as a compression system, a combustion chamber, an expansion system and the like are required to have good adaptability, otherwise, the performance of the engine is affected, and the difficulty of realizing medium-speed bypass ratio is increased. At the same time, the intake air amount and pressure ratio corresponding to the medium bypass ratio range are greatly changed, and a complicated control system is required to accurately adjust the fan and other components to realize different bypass ratios, which clearly increases the difficulty of realizing the medium variable bypass ratio. In addition, the working conditions of the turbofan engine can be changed greatly under different duct ratios, so that the matching performance of all parts of the engine is required to be good, otherwise, the working stability of the engine can be influenced, and the difficulty of realizing the medium-change duct ratio is increased.
Disclosure of Invention
Object of the invention
Aiming at the power requirement of the high-altitude long-endurance unmanned aerial vehicle and the difficulty and challenges faced by the prior art in realizing the medium bypass ratio change adjustment, the invention provides a medium variable bypass ratio turbofan engine configuration based on a double-fan structure, in particular to a double-fan and adjustable-nozzle turbofan engine structure with inlet adjustable blades; the variable diversion cone and the adjustable blades of the high-pressure fan inlet are arranged, and the flow ratio of the outer culvert runner and the inner culvert runner is adjusted by controlling the angles of the variable diversion cone and the adjustable blades, so that different culvert ratios are realized, which is the key point for realizing medium variable culvert ratios; the engine configuration provided by the invention has the advantages of large bypass ratio adjusting range, strong high-altitude climbing capacity and low high-altitude cruising fuel consumption rate, and is suitable for the power requirement of the high-altitude long-endurance unmanned aerial vehicle.
(II) technical scheme
In order to achieve the aim of the invention, the invention adopts the following technical scheme:
the utility model provides a medium change duct ratio turbofan engine structure based on two fan structures, includes at least one intake duct that is located its head, the downstream of intake duct sets up an interior receiver of axial extension along engine rotation center, interior receiver separates the runner into one and is located its radial outside and along the outer culvert runner of axial extension and one and be located its radial inboard and along the interior culvert runner of axial extension, the outside of outer culvert runner is outer culvert receiver, be equipped with a low pressure fan subassembly in the intake duct at least, at least one high pressure fan subassembly and a core machine subassembly have been set gradually along the flow direction in the interior culvert runner, the downstream afterbody of outer culvert receiver sets up an adjustable tail pipe at least, the downstream afterbody of interior culvert receiver sets up a lobe blender at least, its characterized in that,
the inner receiver at least comprises an inlet section positioned at the upstream of the inner receiver and a main body section positioned at the downstream of the inlet section along the flow direction, the high-pressure fan assembly is arranged in the inlet section of the inner receiver, the core assembly is arranged in the main body section of the inner receiver,
and a second duct which is communicated with the inner culvert runner and the outer culvert runner is formed between the inlet section and the main body section of the inner culvert casing, the second duct is positioned between the high-pressure fan assembly and the high-pressure compressor in the core engine assembly in the flow direction,
and the upstream front edge of the inlet section of the inner receiver is provided with a variable diversion cone, the variable diversion cone is connected to the upstream front edge of the inlet section of the inner receiver in a radial angle-adjustable manner through a diversion cone rotating shaft, when the adjustment angle of the variable diversion cone is turned outwards, the air flow entering the outer culvert runner is reduced, and the air flow entering the inner culvert runner is increased, otherwise, when the adjustment angle of the variable diversion cone is turned inwards, the air flow entering the inner culvert runner is reduced, and the air flow entering the outer culvert runner is increased.
Preferably, the low pressure fan assembly includes at least a low pressure fan rotor and a low pressure fan stator downstream of the low pressure fan rotor, and the low pressure fan stator is disposed adjacent to the outlet of the air intake duct.
Preferably, the high-pressure fan assembly is arranged in the inlet section of the connotation flow channel and at least comprises a high-pressure fan inlet guide vane, a high-pressure fan rotor and a high-pressure fan stator which are sequentially arranged along the flow direction.
Further, in the high-pressure fan assembly, the outlet angle of the high-pressure fan inlet guide vane is adjustable, when the engine bypass ratio needs to be lifted to increase the bypass flow and reduce the bypass flow, the high-pressure fan inlet guide vane is adjusted to increase the outlet angle thereof, so that the gas flow entering the downstream high-pressure fan assembly is reduced, and correspondingly, the angle of the variable diversion cone is adjusted to enable the variable diversion cone to turn inwards so as to reduce the gas flow diverted to the bypass flow passage.
Further, when the engine bypass ratio needs to be reduced to increase the internal bypass flow and reduce the external bypass flow, the high-pressure fan inlet guide vane is adjusted to reduce the outlet angle thereof, so that the gas flow entering the downstream high-pressure fan assembly is increased, and the angle of the variable diversion cone is adjusted to enable the variable diversion cone to turn outwards in accordance with the gas flow diverted to the external bypass flow channel.
Preferably, a control valve with an adjustable opening is arranged in the second duct, and the opening of the control valve is adjusted according to the working condition of the engine.
Preferably, the core unit is arranged in the main body section of the connotation flow channel and at least comprises a high-pressure compressor, a combustion chamber, a high-pressure turbine component and a low-pressure turbine component which are sequentially arranged along the flow direction, an axial space between the high-pressure turbine component and the low-pressure turbine component is a high-pressure turbine transition section, the high-pressure turbine component is in transmission connection with the high-pressure fan component and the high-pressure compressor through a high-pressure shaft and provides driving power, and the low-pressure turbine component is in transmission connection with the low-pressure fan component through a low-pressure shaft and provides driving power.
Further, the high-pressure turbine assembly at least comprises a high-pressure turbine guide and a high-pressure turbine rotor which are sequentially arranged along the flow direction, the high-pressure turbine rotor is in transmission connection with the rotor parts of the high-pressure fan assembly and the high-pressure compressor through a high-pressure shaft and provides driving power, the low-pressure turbine assembly at least comprises a first-stage low-pressure turbine and a second-stage low-pressure turbine which are sequentially arranged along the flow direction, the first-stage low-pressure turbine at least comprises a first-stage low-pressure turbine guide and a first-stage low-pressure turbine rotor which are sequentially arranged along the flow direction, the second-stage low-pressure turbine at least comprises a second-stage low-pressure turbine guide and a second-stage low-pressure turbine rotor which are sequentially arranged along the flow direction, and the first-stage low-pressure turbine rotor and the second-stage low-pressure turbine rotor are in transmission connection with the low-pressure shaft and the rotor parts of the low-pressure fan assembly through the low-pressure shaft and provide driving power.
The invention relates to a medium-variable bypass ratio turbofan engine configuration based on a double-fan structure, which comprises the following working processes: in the running process of the engine, air is sucked through a low-pressure fan arranged in an air inlet channel, after being pressurized by the low-pressure fan, the air is divided into two parts by a variable diversion cone, one part of the air enters an outer culvert channel, the other part of the air enters an inner culvert channel, the air flow is regulated to flow direction by a high-pressure fan inlet guide vane in an inlet section of the inner culvert channel, then the air enters a high-pressure fan rotor and a stator for pressurization, then the air is further diverted, one part of the air continuously flows forwards to enter a high-pressure compressor, one part of the air enters the outer culvert channel through a second culvert channel, the air flow after being pressurized by the high-pressure compressor enters a combustion chamber, the air enters a high-pressure turbine for doing work after the combustion lifting temperature, then enters the low-pressure turbine for doing work, tail gas is mixed with the air flow in the outer culvert channel in a lobe mixer, and the uniformly mixed air flow is sprayed out through an adjustable spray pipe to generate thrust.
(III) technical effects
Compared with the prior art, the medium-variable bypass ratio turbofan engine configuration based on the double-fan structure has the following beneficial and remarkable technical effects:
(1) The structure of the medium-variable bypass ratio turbofan engine based on the double-fan structure ensures that the engine has higher bypass ratio adjusting potential and wider working range by adopting the double-fan structure, and is beneficial to realizing the medium-variable bypass ratio.
(2) The middle-variable bypass ratio turbofan engine structure based on the double-fan structure can obviously reduce the difficulty of realizing the middle-variable bypass ratio by arranging the adjustable diversion cone and the adjustable blades at the inlet of the high-pressure fan, which is a simple and effective means for realizing different bypass ratios.
(3) The medium-variable bypass ratio turbofan engine configuration based on the double-fan structure can further enlarge the bypass ratio adjusting range by arranging the second bypass, and provides possibility for realizing the medium-variable bypass ratio in the range of 3-6.
(4) The medium-variable bypass ratio turbofan engine configuration based on the double-fan structure can realize continuous adjustment of the bypass ratio, and meets the fine control requirement of the high-altitude long-endurance unmanned aerial vehicle on the bypass ratio.
(5) The medium-variable bypass ratio turbofan engine configuration based on the double-fan structure can realize relatively independent control of the low-pressure fan and the high-pressure fan, is beneficial to realizing the required bypass ratio change, and ensures the working performance of the engine.
(6) The middle-variable bypass ratio turbofan engine structure based on the double-fan structure can effectively reduce the difficulty of realizing the middle-variable bypass ratio by adopting the technical means of the double-fan structure, the arrangement of the adjustable flow dividing device and the like, realizes fine and adjustable bypass ratio within the range of 3-6, and has important application value for the power requirements of high-altitude long-endurance unmanned aerial vehicles and the like.
Drawings
FIG. 1 is a schematic illustration of a medium bypass ratio turbofan engine configuration based on a dual fan configuration of the present invention;
FIG. 2 is a schematic diagram of a medium bypass ratio turbofan engine rotor system of the present invention;
FIG. 3 is a schematic flow path diagram of a medium bypass ratio turbofan engine compression system of the present invention;
FIG. 4 is a schematic illustration of the medium change bypass ratio turbofan engine high pressure fan inlet guide vane modulation of the present invention.
Reference numerals illustrate:
the turbine comprises a rotation center 1, a low-pressure shaft 2, a high-pressure shaft 3, a low-pressure fan rotor 4, a low-pressure fan stator 5, a variable diversion cone 6, a diversion cone rotation shaft 7, an outer culvert channel 8, a high-pressure fan inlet guide vane 9, a high-pressure fan rotor 10, a high-pressure fan stator 11, a second culvert 12, a high-pressure compressor 13, a combustion chamber 14, a high-pressure turbine guide 15, a high-pressure turbine rotor 16, a high-pressure turbine transition section 17, a primary low-pressure turbine guide 18, a primary low-pressure turbine rotor 19, a secondary low-pressure turbine guide 20, a secondary low-pressure turbine rotor 21, a lobe blender 22, an adjustable tail nozzle 23 and an inclusion channel 24.
Detailed Description
For a better understanding of the present invention, the following examples are set forth to illustrate the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the drawings are illustrative and intended to explain the present invention and should not be construed as limiting the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention. The following describes the structure and technical scheme of the present invention in detail with reference to the accompanying drawings, and an embodiment of the present invention is given.
As shown in fig. 1 to 3, the structure of the medium-variable bypass ratio turbofan engine based on the double-fan structure at least comprises an air inlet channel positioned at the head part of the engine, an inner receiver extending along the axial direction of the engine rotation center 1 is arranged at the downstream of the air inlet channel, the inner receiver divides the flow channel into an outer bypass channel 8 positioned at the radial outer side of the inner receiver and extending along the axial direction of the inner receiver, an inner bypass channel 24 positioned at the radial inner side of the inner receiver and extending along the axial direction of the inner receiver, the outer side of the outer bypass channel 8 is the outer receiver, at least one low-pressure fan assembly is arranged in the air inlet channel, the low-pressure fan assembly at least comprises a low-pressure fan rotor 4 and a low-pressure fan stator 5 positioned at the downstream of the low-pressure fan rotor 4, and the outlet position of the low-pressure fan stator 5 adjacent to the air inlet channel is arranged. The inner side of the inner culvert runner 24 is provided with at least one high-pressure fan component and one core machine component in sequence along the flow direction, the downstream tail part of the outer culvert casing is provided with at least one adjustable tail nozzle 23, and the downstream tail part of the inner culvert casing is provided with at least one lobe blender 22. The high-pressure fan assembly is disposed in the inlet section of the inclusion flow passage 24 and includes at least a high-pressure fan inlet guide vane 9, a high-pressure fan rotor 10 and a high-pressure fan stator 11 disposed in this order in the flow direction. The core machine component is arranged in the main body section of the inclusion flow channel 24 and at least comprises a high-pressure compressor 13, a combustion chamber 14, a high-pressure turbine component and a low-pressure turbine component which are sequentially arranged along the flow direction, wherein the axial space between the high-pressure turbine component and the low-pressure turbine component is a high-pressure turbine transition section 17 and a low-pressure turbine transition section 17, the high-pressure turbine component is in transmission connection with the high-pressure fan component and the high-pressure compressor 13 through a high-pressure shaft 3 and provides driving power, and the low-pressure turbine component is in transmission connection with the low-pressure fan component through a low-pressure shaft 2 and provides driving power. The high-pressure turbine assembly at least comprises a high-pressure turbine guide 15 and a high-pressure turbine rotor 16 which are sequentially arranged along the flow direction, the high-pressure turbine rotor 16 is in transmission connection with a rotor part of the high-pressure fan assembly and the high-pressure compressor 13 through a high-pressure shaft 3 and provides driving power, the low-pressure turbine assembly at least comprises a first-stage low-pressure turbine and a second-stage low-pressure turbine which are sequentially arranged along the flow direction, the first-stage low-pressure turbine at least comprises a first-stage low-pressure turbine guide 18 and a first-stage low-pressure turbine rotor 19 which are sequentially arranged along the flow direction, the second-stage low-pressure turbine at least comprises a second-stage low-pressure turbine guide 20 and a second-stage low-pressure turbine rotor 21 which are sequentially arranged along the flow direction, and the first-stage low-pressure turbine rotor 19 and the second-stage low-pressure turbine rotor 21 are both in transmission connection with the low-pressure shaft 2 and the rotor part of the low-pressure fan assembly through the low-pressure shaft 2 and provide driving power.
In the intermediate-variable bypass ratio turbofan engine configuration based on the double-fan structure of the present invention, the inner casing includes at least an inlet section located upstream thereof and a main section located downstream of the inlet section in the flow direction, the high-pressure fan assembly is disposed in the inlet section of the inner casing, the core assembly is disposed in the main section of the inner casing, and a second bypass 12 communicating the inner bypass 24 and the outer bypass 8 is formed between the inlet section and the main section of the inner casing, the second bypass 12 is located between the high-pressure fan assembly and the high-pressure compressor 13 in the core assembly in the flow direction, and the upstream front edge of the inlet section of the inner casing is provided with a variable split cone 6, the variable split cone 6 is connected to the upstream front edge of the inlet section of the inner casing by a split cone rotation shaft 7 in a radially angularly adjustable manner, when the variable split cone 6 is turned outside, the air flow entering the outer bypass 8 is decreased and the air flow entering the inner bypass 24 is increased, whereas when the variable split cone 6 is turned outside, the air flow entering the inner bypass 24 is decreased.
The invention relates to a medium-variable bypass ratio turbofan engine configuration based on a double-fan structure, which has the following working principle: in the running process of the engine, air is sucked through the low-pressure fan 4, after being pressurized through the low-pressure fan 4, the air is divided into two parts by the variable diversion cone 6, one part of the air enters the outer culvert channel 8, the other part of the air enters the inner culvert channel 24, the air flow is regulated to flow direction through the high-pressure fan inlet guide vane 9, then enters the high-pressure fan rotor 10 and the stator 11 for pressurization, then the air is further diverted, one part of the air enters the high-pressure air compressor 13, one part of the air enters the outer culvert channel 8 through the second culvert channel 12, the air flow after being pressurized by the high-pressure air compressor 13 enters the combustion chamber 14, after being heated and lifted by combustion, enters the high-pressure turbine for doing work 16, then enters the low-pressure turbines 19 and 20 for doing work, tail gas is mixed with the air flow 8 in the outer culvert channel in the lobe mixer 22, and the uniformly mixed air flow is sprayed out through the adjustable spray pipe 23, and thrust is generated.
Fig. 2 is a rotor structure of such an engine. The low-pressure fan 4 and the low-pressure turbine 19 are connected by the low-pressure shaft 2, and the work required by the low-pressure fan 4 is provided by the low-pressure turbine 19; the high-pressure fan 10, the high-pressure compressor 13 and the high-pressure turbine 16 are connected by the high-pressure shaft 3, the work of the high-pressure fan 10 and the high-pressure compressor 13 is provided by the high-pressure turbine 16, and the rotating speeds are the same.
FIG. 3 is a flow path of a compression system of a medium bypass ratio turbofan engine. A variable tap 6 is provided behind the low pressure fan and has a rotatable shaft 7 which can be adjusted according to different connotation inlet air flows to achieve a better tap angle of attack and reduce the flow losses of the tap and the transition section attachments. An adjustable inlet guide vane 9 is arranged in front of the high-pressure fan 10, and the inlet air flow direction of the low-pressure fan is adjusted by adjusting the outlet angle of the adjustable inlet guide vane 9 as shown in fig. 4. A second duct 12 is arranged between the high-pressure fan 10 and the high-pressure compressor 13, and the high-pressure fan has an automatic adjusting function under the condition of different angles of inlet guide vanes, so that reasonable matching of the high-pressure compressor is realized. When the bypass ratio is changed, the adjustable spray pipe 23 reasonably adjusts the size of the tail spray pipe according to different exhaust conditions, so that the optimal aerodynamic performance of the engine is realized.
In the medium-variable bypass ratio turbofan engine configuration based on the double-fan structure, the outlet angle of the high-pressure fan inlet guide vane 9 is adjustable, when the bypass ratio of the engine needs to be lifted to increase the bypass flow and reduce the bypass flow, the high-pressure fan inlet guide vane 9 is adjusted to increase the outlet angle thereof, so that the flow rate of gas flowing into a downstream high-pressure fan assembly is reduced, and correspondingly, the angle of the variable diversion cone 6 is adjusted to enable the variable diversion cone to be turned inwards so as to reduce the flow rate of gas diverted to the bypass flow passage 24. On the contrary, when the engine bypass ratio needs to be reduced to increase the internal bypass flow and reduce the external bypass flow, the high-pressure fan inlet guide vane 9 is adjusted to reduce the outlet angle thereof, so that the gas flow entering the downstream high-pressure fan assembly is increased, and correspondingly, the angle of the variable diversion cone 6 is adjusted to enable the variable diversion cone to turn outwards, so that the gas flow diverted to the external bypass flow channel 8 is reduced. FIG. 4 presents a schematic view of high pressure fan inlet guide vane adjustment. As can be seen from the figure, when the outlet angle of the inlet guide vane 9 is changed, the inlet speed triangle of the high-pressure fan is changed, for example, compared with the inlet angle of the upper high-pressure fan rotor which is 0 degrees and the inlet angle of the lower high-pressure fan rotor which is 30 degrees, the inlet geometric angle +.1 of the high-pressure fan rotor blade is unchanged, the bent angle +.2 is unchanged, the tangential speed U is unchanged, but the angle +.3 of the inlet airflow C1 is changed, the original 0-degree change is 30 degrees, the flow of the high-pressure fan is changed, the flow is mainly determined by Cm, and according to the triangle relation, cm > Cm' can be found, so the flow can be reduced; in addition, the pressure ratio of the high-pressure fan is reduced, which is mainly determined by u×Δwu, and it can be found from the geometric relationship that U is unchanged and Δwu > - Δwu', so that the pressure ratio is reduced. In this example, the bypass ratio of the engine may achieve a tuning variation of 6 to 4.5.
In summary, the medium-variable bypass ratio turbofan engine structure based on the double-fan structure has higher bypass ratio adjusting potential and wider working range by adopting the double-fan structure, is beneficial to realizing medium-variable bypass ratio, is a simple and effective means for realizing different bypass ratios by arranging the adjustable diversion cone and the adjustable blades at the inlet of the high-pressure fan, can remarkably reduce the difficulty of realizing medium-variable bypass ratio, can further increase the bypass ratio adjusting range by arranging the second bypass, provides possibility for realizing medium-variable bypass ratio in the range of 3-6, can realize continuous adjustment of bypass ratio, meets the fine control requirement of unmanned aerial vehicle on bypass ratio in high-altitude long-voyage, can realize relatively independent low-pressure fan and high-pressure fan control, is beneficial to realizing required bypass ratio change, ensures the working performance of the engine, can effectively reduce the difficulty of realizing medium-variable bypass ratio, and realizes important requirements for fine-variable bypass ratio in the range of 3-6, and has great power and no important requirements for man-machine applications in the range of fine-variable bypass ratio.
The object of the present invention is fully effectively achieved by the above-described embodiments. Those skilled in the art will appreciate that the present invention includes, but is not limited to, those illustrated in the drawings and described in the foregoing detailed description. While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not limited to the disclosed embodiment, but on the contrary, is intended to cover various modifications and equivalent arrangements included within the scope of the appended claims.
Claims (8)
1. The utility model provides a medium change duct ratio turbofan engine structure based on two fan structures, includes at least one intake duct that is located its head, the downstream of intake duct sets up an interior receiver of axial extension along engine rotation center, interior receiver separates the runner into one and is located its radial outside and along the outer culvert runner of axial extension and one and be located its radial inboard and along the interior culvert runner of axial extension, the outside of outer culvert runner is outer culvert receiver, be equipped with a low pressure fan subassembly in the intake duct at least, at least one high pressure fan subassembly and a core machine subassembly have been set gradually along the flow direction in the interior culvert runner, the downstream afterbody of outer culvert receiver sets up an adjustable tail pipe at least, the downstream afterbody of interior culvert receiver sets up a lobe blender at least, its characterized in that,
the inner receiver at least comprises an inlet section positioned at the upstream of the inner receiver and a main body section positioned at the downstream of the inlet section along the flow direction, the high-pressure fan assembly is arranged in the inlet section of the inner receiver, the core assembly is arranged in the main body section of the inner receiver,
and a second duct which is communicated with the inner culvert runner and the outer culvert runner is formed between the inlet section and the main body section of the inner culvert casing, the second duct is positioned between the high-pressure fan assembly and the high-pressure compressor in the core engine assembly in the flow direction,
and the upstream front edge of the inlet section of the inner receiver is provided with a variable diversion cone, the variable diversion cone is connected to the upstream front edge of the inlet section of the inner receiver in a radial angle-adjustable manner through a diversion cone rotating shaft, when the adjustment angle of the variable diversion cone is turned outwards, the air flow entering the outer culvert runner is reduced, and the air flow entering the inner culvert runner is increased, otherwise, when the adjustment angle of the variable diversion cone is turned inwards, the air flow entering the inner culvert runner is reduced, and the air flow entering the outer culvert runner is increased.
2. The dual fan configuration-based medium bypass ratio turbofan engine configuration of claim 1 wherein the low pressure fan assembly includes at least a low pressure fan rotor and a low pressure fan stator downstream of the low pressure fan rotor and wherein the low pressure fan stator is disposed adjacent an outlet location of the inlet duct.
3. The dual fan structure based medium bypass ratio turbofan engine configuration of claim 1 wherein the high pressure fan assembly is disposed within an inlet section of the inner culvert runner and includes at least a high pressure fan inlet guide vane, a high pressure fan rotor, and a high pressure fan stator disposed in sequence in a flow direction.
4. The dual fan configuration-based medium bypass ratio turbofan engine configuration of claim 3 wherein in the high pressure fan assembly the outlet angle of the high pressure fan inlet guide vanes is adjustable, and when it is desired to increase bypass flow and decrease bypass flow by elevating engine bypass ratio, the high pressure fan inlet guide vanes are adjusted to increase their outlet angle to reduce the flow of gas to the high pressure fan assembly downstream thereof, and in response thereto, the angle of the variable diversion cone is adjusted to turn inwardly to reduce the flow of gas diverted to the bypass flow.
5. The dual fan configuration based medium bypass ratio turbofan engine configuration of claim 4 wherein when it is desired to reduce engine bypass ratio to increase bypass flow and decrease bypass flow, the high pressure fan inlet guide vanes are adjusted to decrease their outlet angle to increase the flow of gas to the high pressure fan assembly downstream thereof, and in response thereto, the angle of the variable diverging cone is adjusted to flip outwardly to decrease the flow of gas diverted to the bypass flow passage.
6. The medium variable bypass ratio turbofan engine configuration based on the double fan structure according to claim 1, wherein an opening-adjustable control valve is arranged in the second bypass, and the opening of the control valve is adjusted according to the working condition of the engine.
7. The dual fan architecture based moderate bypass ratio turbofan engine configuration of claim 1 wherein the core assembly is disposed within the main section of the inner culvert runner and includes at least a high pressure compressor, a combustion chamber, a high pressure turbine assembly, a low pressure turbine assembly disposed in sequence in a flow direction, an axial space between the high pressure turbine assembly and the low pressure turbine assembly being a high and low pressure turbine transition section, the high pressure turbine assembly being drivingly connected to the high pressure fan assembly, the high pressure compressor and providing drive power through a high pressure shaft, the low pressure turbine assembly being drivingly connected to the low pressure fan assembly through a low pressure shaft and providing drive power.
8. The dual fan architecture based moderate bypass ratio turbofan engine configuration of claim 7 wherein the high pressure turbine assembly includes at least a high pressure turbine pilot, a high pressure turbine rotor disposed in sequence in a flow direction, the high pressure turbine rotor being drivingly connected to the high pressure fan assembly via a high pressure shaft and the rotor portion of the high pressure compressor and providing driving power, the low pressure turbine assembly includes at least a first low pressure turbine and a second low pressure turbine disposed in sequence in a flow direction, the first low pressure turbine includes at least a first low pressure turbine pilot, a first low pressure turbine rotor disposed in sequence in a flow direction, and the second low pressure turbine includes at least a second low pressure turbine pilot, a second low pressure turbine rotor disposed in sequence in a flow direction, the first low pressure turbine rotor, the second low pressure turbine rotor being drivingly connected to the low pressure shaft and the rotor portion of the low pressure fan assembly via the low pressure shaft and providing driving power.
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