CN115583335A - Loss reduction device, boundary layer suction fan and aircraft - Google Patents
Loss reduction device, boundary layer suction fan and aircraft Download PDFInfo
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- CN115583335A CN115583335A CN202110758076.0A CN202110758076A CN115583335A CN 115583335 A CN115583335 A CN 115583335A CN 202110758076 A CN202110758076 A CN 202110758076A CN 115583335 A CN115583335 A CN 115583335A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
- B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
- B64C21/06—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for sucking
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Abstract
The invention discloses a loss reduction device, a boundary layer suction fan and an aircraft, wherein the loss reduction device is applied to the fan, and the fan comprises: nacelle, interior cartridge receiver and fan blade, the nacelle cover is located the outside of interior cartridge receiver forms the interval, the device that decreases is including: a root relief extending radially outward from an outer wall of the inner case into the gap and rotating around the inner case; a top impairment body extending radially inward from an inner wall of the nacelle into the gap and rotating around the inner barrel; a second gap is formed between the extending end of the root damage reducing body and the extending end of the top damage reducing body; the air flows through the loss reduction device and then to the fan blades. The loss reducing device can effectively reduce the low-energy fluid accumulation of boundary layers near the tops and the roots of the fan blades, improve the inlet airflow quality and the aerodynamic efficiency of the fan, and effectively solve the problem that the boundary layer is sucked into the fan and has low working efficiency.
Description
Technical Field
The invention relates to a loss reduction device, a boundary layer suction fan and an aircraft.
Background
The international civil aviation organization and related scientific research institutions have increasingly strict requirements on indexes such as oil consumption, environmental protection and the like of future aircrafts. According to reports NASA and the european union hope that by a time period of 2035 years (N +3 time frame), fuel consumption of the aircraft is reduced by 70%. Which has not been achieved by aircraft engines based on conventional fuel configurations. In recent years, advanced countries in europe and the united states of america have proposed a new aerodynamic layout and an aircraft/engine propulsion system concept using new energy, starting from new angles such as aircraft configuration and energy use mode. In these new aircraft configurations, boundary layer suction type propulsion systems (pulse fan concepts) with boundary layer suction electric fans (BLI fans) installed at the tail of the aircraft are currently the focus of research.
The basic idea of this configuration is to add a fan at the tail of a conventional aircraft, which is typically driven directly by the electricity generated by the operation of a conventional gas turbine engine. When the tail fan works, the gas boundary layer gradually accumulated on the surface of the aircraft body under the action of viscosity can be effectively sucked, so that the accumulation of the boundary layer of the aircraft body is reduced, the resistance of the aircraft is effectively reduced, and the aim of reducing the voyage oil consumption is finally fulfilled. Foreign countries often turn the fan into a boundary layer suction fan (BLI fan) due to the boundary layer suction effect of the tail fan. On the other hand, the boundary layer suction fan also provides approximately 20% to 30% of the thrust, so that with a constant total thrust requirement of the aircraft, the thrust requirement of a conventional gas turbine engine is reduced, and therefore the fan diameter thereof can also be reduced, making it easier to meet the size constraint limits at the maximum diameter of the nacelle.
The foreign GE, air passenger and other aircraft and engine companies all propose related patents of boundary layer suction fans installed at the tail of the airframe on the basis of the concept. Because the boundary layer suction function of the boundary layer suction fan is equivalent to indirectly increasing the bypass ratio of the traditional gas turbine engine, according to data, compared with the common aircraft configuration under the same technical condition, the aircraft configuration provided with the boundary layer suction fan can save about 9-14% of fuel consumption, and the economic efficiency is very considerable.
Although boundary layer suction fans have considerable fuel economy benefits, boundary layer suction fans still have some room for improvement in engineering applications. Most typically, for example, the boundary layer suction fan inlet flow will continue to experience radial distortion about the root and low boundary layer energy flow in a portion of the span, i.e., continue to operate in both radial and circumferential distortion environments, due to upstream disturbances from the airframe and vertical tail boundary layers. Evaluation according to the relevant data shows that the efficiency of the trailing boundary layer suction fan drops by about 4 percentage points compared to the case of uniform inlet conditions.
Disclosure of Invention
The invention aims to overcome the defect of low working efficiency of a boundary layer suction fan in the prior art, and provides a loss reducing device, the boundary layer suction fan and an aircraft.
The invention solves the technical problems through the following technical scheme:
an abatement device for a fan, the fan comprising: nacelle, interior cartridge receiver and fan blade, the nacelle cover is located the outside of interior cartridge receiver forms the interval, its characterized in that, the impairment device is including: a root relief extending radially outward from an outer wall of the inner barrel into the gap and rotating around the inner barrel; a top bluff body extending radially inward from an inner wall of the nacelle into the compartment and rotating around the inner barrel; a second gap is provided between the protruding end of the root lesion and the protruding end of the tip lesion; air flows through the impairment device towards the fan blades.
In this scheme, adopt above-mentioned structural style, the loss reduction device not only cost is relatively lower, easily dismouting to this loss reduction device can reduce the fan blade top effectively and near the boundary layer low energy fluid accumulation of blade root, improves the import air current quality and the aerodynamic efficiency of fan, has effectively solved the problem that boundary layer suction fan work efficiency is low, is favorable to reducing the engine oil consumption, reduces carbon and discharges, improves the economic nature of aircraft.
Preferably, the damage reducing device further comprises a first driving part and a second driving part; the first driving part is fixedly connected with the nacelle, and the first driving part enables the top damage reducing body to rotate around the inner casing; the second driving part is fixedly connected with the inner casing, and the root loss reducing body rotates around the inner casing through the second driving part.
In this scheme, adopt above-mentioned structural style, the relatively independent drive design of root detracts from the body and the top detracts from the body on the loss reduction device for the adjustment mode to root detracts from the body and the top detracts from the body is more nimble in the actual process, is favorable to making the loss reduction device and fan blade obtain best matching effect when working in coordination.
Preferably, the first driving portion surrounds and is fixed to the inner wall of the nacelle, the top impairment body is fixedly mounted on the inner wall of the first driving portion, and the first driving portion enables the extending end of the top impairment body to surround the root impairment body for rotation.
Preferably, first drive division includes motor stator and electric rotor, the inner wall of nacelle encircles and is fixed with motor stator, motor stator's inner wall encircles and is equipped with electric rotor, electric rotor can the motor stator internal rotation, electric rotor's inner wall evenly is fixed with a plurality ofly along its circumferencial direction top impairment body, electric rotor makes the end that stretches out of top impairment body centers on interior machine casket is rotatory.
In this scheme, adopt above-mentioned structural style, first drive division adopts annular motor and sets up and install in the nacelle inner wall, makes the structural style and the arrangement form of first drive division obtain simplifying like this, and first drive division can not produce the interference to the condition of admitting air of fan simultaneously.
Preferably, the second driving portion includes a first motor and a first transmission shaft, the first motor is fixedly installed in the inner casing, an end of the first transmission shaft is fixedly connected to the first motor, a plurality of root loss reducing bodies are uniformly and fixedly installed on an outer wall of the first transmission shaft along a circumferential direction, and an extending end of each root loss reducing body rotates around the inner casing.
In this scheme, adopt above-mentioned structural style, the root subtracts the face layer kinetic energy that decreases the body and can make near the interior casket and increase, and face layer thickness reduces, is favorable to improving the aerodynamic efficiency of fan to the root subtracts the body and has independent second drive division to drive it, is favorable to making to the root subtracts the regulation mode that decreases the body more nimble.
Preferably, the impairment assembly further comprises a second motor and a second drive shaft, the second motor rotating the fan blades between the intervals via the second drive shaft.
In the scheme, by adopting the structural form, the fan blades play the roles of sucking the boundary layer of the machine body and generating forward thrust, and the fan blades are driven by the independent second motor, so that the working states of the fan blades can be flexibly configured according to the experimental or calculation result and the thrust requirement.
Preferably, the damage reducing device further comprises a second transmission shaft, the second transmission shaft is sleeved outside the first transmission shaft, one end of the second transmission shaft is fixedly connected with the first motor, the other end of the second transmission shaft extends towards the root damage reducing body, a plurality of fan blades are fixedly installed on the outer wall of the extending end of the second transmission shaft along the circumferential direction, and the fan blades are rotated between the intervals by the second transmission shaft.
Preferably, the second transmission shaft is coaxially sleeved outside the first transmission shaft.
In this scheme, adopt above-mentioned structural style, can reduce the quantity of motor, save the space in the quick-witted casket in, be favorable to making and have better integrated level between loss reduction device and the fan.
Preferably, the fan further includes a speed reduction portion, the first transmission shaft includes a first shaft and a second shaft, one end of the first shaft is fixedly connected to the first motor, the other end of the first shaft is fixedly connected to an input end of the speed reduction portion, an output end of the speed reduction portion is fixedly connected to one end of the second shaft, a plurality of root loss reduction bodies are uniformly and fixedly mounted on the outer wall of the second shaft in the circumferential direction, and an extending end of each root loss reduction body surrounds the inner casing to rotate.
In this scheme, adopt above-mentioned structural style, speed reduction portion has played the effect of carrying out the speed governing to root reduction body, is favorable to making root reduction body and fan blade obtain the rotational speed of demand separately.
A boundary layer suction fan, characterized in that said boundary layer suction fan employs said loss reducing device.
In the scheme, the loss reducing device adopting the structure form of the boundary layer suction fan is relatively low in cost and easy to disassemble and assemble, the loss reducing device can effectively reduce the low-energy fluid accumulation of boundary layers at the tops of the fan blades and near the blade roots, the quality of inlet airflow and the aerodynamic efficiency of the fan are improved, the problem of low working efficiency of the boundary layer suction fan is effectively solved, the oil consumption of an engine is reduced, the carbon emission is reduced, and the economy of an aircraft is improved.
An aircraft, characterized in that it employs the boundary layer suction fan described above.
In the scheme, the loss reducing device of the boundary layer suction fan at the tail part of the aircraft is relatively low in cost and easy to disassemble and assemble, can effectively reduce the accumulation of low-energy fluid of boundary layers at the tops of the fan blades and near the blade roots, improves the inlet airflow quality and the aerodynamic efficiency of the fan, effectively solves the problem of low working efficiency of the boundary layer suction fan, is beneficial to reducing the oil consumption of an engine, reduces the carbon emission and improves the economy of the aircraft.
On the basis of the common knowledge in the field, the above preferred conditions can be combined randomly to obtain the preferred embodiments of the invention.
The positive progress effects of the invention are as follows:
the loss reducing device is designed and installed in an interval formed by the inner wall of the nacelle of the boundary layer suction fan and the outer wall of the inner casing, the structure of the loss reducing device is relatively low in cost and easy to assemble and disassemble, the low-energy fluid accumulation of the boundary layer at the tops of the fan blades and near the blade roots can be effectively reduced by the loss reducing device, the inlet airflow quality and the aerodynamic efficiency of the fan are improved, the problem of low working efficiency of the boundary layer suction fan is effectively solved, the oil consumption of an engine is favorably reduced, the carbon emission is reduced, and the economy of an aircraft is improved.
Drawings
Fig. 1 is a schematic view of a boundary layer suction fan with an abatement device installed according to an embodiment of the present invention.
Fig. 2 is a schematic structural diagram of a first driving portion according to an embodiment of the invention.
FIG. 3 is a schematic diagram of a boundary layer suction fan according to another embodiment of the present invention.
Fig. 4 is a schematic structural view of an aircraft according to an embodiment of the invention.
Description of reference numerals:
loss reducing device 1
Root damage reducer 11
The top lossy body 12
First driving part 13
Second electric machine 15
Boundary layer suction fan 2
Detailed Description
The present invention will be more clearly and completely described below by way of examples and with reference to the accompanying drawings, but the present invention is not limited thereto.
An embodiment of the present invention provides a damage reducing device 1, as shown in fig. 1 to 4, where the damage reducing device 1 is applied to a fan, and the fan includes: nacelle 21, interior receiver 22 and fan blade 23, nacelle 21 cover is located the outside of interior receiver 22 and is formed the interval, and the loss reduction device 1 includes: a root reducer 11, the root reducer 11 extending radially outward from an outer wall of the inner barrel 22 into the space and rotating around the inner barrel 22; a top bluff body 12, the top bluff body 12 extending radially inward from the inner wall of the nacelle 21 into the gap and rotating around the inner casing 22; a second gap is formed between the extending end of the root damage reducer 11 and the extending end of the tip damage reducer 12; air flows through the abatement device 1 towards the fan blades 23.
With the above-described configuration, the loss reducing device 1 is designed and installed in the space formed by the inner wall of the nacelle 21 and the outer wall of the inner casing 22 of the boundary layer suction fan 2, and the loss reducing device 1 includes a plurality of root loss reducing bodies 11 that are uniformly distributed in the circumferential direction of the inner casing 22 and extend radially outward from the outer wall of the inner casing 22 into the space, and a plurality of top loss reducing bodies 12 that are uniformly distributed in the circumferential direction of the nacelle 21 and extend radially inward from the inner wall of the nacelle 21 into the space.
When the loss reducing device 1 works, the root loss reducing bodies 11 rotate around the inner casing 22, and the top loss reducing bodies 12 are positioned on the outer rings of the root loss reducing bodies 11 and rotate around the inner casing 22; in an actual working state of the boundary layer suction fan 2, because the upstream of the boundary layer suction fan 2 is interfered by a machine body and a vertical tail boundary layer, the inlet airflow of the boundary layer suction fan 2 continuously has radial distortion of one circle near the blade root of the fan blade 23 and low-energy boundary layer fluid in a partial area, so the loss reduction device 1 is arranged before the fan blade 23 of the boundary layer suction fan 2, namely the air flows to the fan blade 23 after flowing through the loss reduction device 1.
Aiming at the problem of low-energy fluid accumulation of a boundary layer near the root of a fan blade 23, the height range of a root loss body 11 can be controlled to account for 0-20% of the height of the fan blade 23 of a boundary layer suction fan 2, and aiming at the problem of low-energy fluid accumulation of the boundary layer near the top of the fan blade 23, the height range of a top loss body 12 can be controlled to account for 0-20% of the height of the fan blade 23 of the boundary layer suction fan 2, meanwhile, the specific shapes and height values of the root loss body 11 and the top loss body 12 can be optimized and adjusted correspondingly according to the thickness distribution condition of the boundary layer obtained through experiments or calculation, and the rotating directions and rotating speeds of the root loss body 11 and the top loss body 12 are optimized and matched correspondingly according to the results of the experiments and the CFD numerical calculation, so that the pneumatic efficiency of the boundary layer suction fan 2 is optimal.
The loss reducing device 1 is relatively low in cost and easy to disassemble and assemble, the loss reducing device 1 can effectively reduce low-energy fluid accumulation of boundary layers near the tops of the fan blades 23 and the blade roots, the inlet airflow quality and the aerodynamic efficiency of the fan are improved, the problem that the working efficiency of the boundary layer suction fan 2 is low is effectively solved, the oil consumption of an engine is reduced, carbon emission is reduced, and the economy of an aircraft 3 is improved.
As a preferred embodiment, as shown in fig. 1, the loss tangent device 1 further includes a first driving part 13 and a second driving part 14; the first driving part 13 is fixedly connected with the nacelle 21, and the first driving part 13 enables the top damage reducing body 12 to rotate around the inner casing 22; the second driving portion 14 is fixedly connected to the inner casing 22, and the second driving portion 14 rotates the root reducer 11 around the inner casing 22.
The root damage reducing body 11 and the top damage reducing body 12 are provided with independent driving parts, wherein the first driving part 13 is installed on the nacelle 21 and fixedly connected with the inner wall of the nacelle 21, the second driving part 14 is fixedly installed in the inner casing 22, when the damage reducing device 1 works, a plurality of top damage reducing bodies 12 positioned on the outer ring of the root damage reducing body 11 are driven by the first driving part 13 to rotate around the inner casing 22, the root damage reducing body 11 positioned on the outer side of the inner casing 22 is driven by the second driving part 14 to rotate around the inner casing 22, and meanwhile, the rotating directions and rotating speeds of the root damage reducing body 11 and the top damage reducing body 12 can be correspondingly optimized and matched according to the experiment and the calculation result of CFD numerical values, so that the root and top boundary layer low loss areas of the fan blades 23 of the boundary layer suction fan 2 are relatively minimum, and the aerodynamic efficiency of the suction boundary layer fan 2 is optimal. The relatively independent driving design of the root damage reducing body 11 and the top damage reducing body 12 on the damage reducing device 1 enables the adjusting mode aiming at the root damage reducing body 11 and the top damage reducing body 12 to be more flexible in the actual process, and is beneficial to obtaining the best matching effect when the damage reducing device 1 and the fan blades 23 work cooperatively.
As a preferred embodiment, as shown in fig. 1 and 2, the first driving portion 13 surrounds and is fixed to the inner wall of the nacelle 21, the tip damage reducer 12 is fixedly mounted on the inner wall of the first driving portion 13, and the first driving portion 13 rotates the protruding end of the tip damage reducer 12 around the root damage reducer 11. The first driving part 13 includes a motor stator 131 and a motor rotor 132, the motor stator 131 is surrounded and fixed on the inner wall of the nacelle 21, the motor rotor 132 is surrounded on the inner wall of the motor stator 131, the motor rotor 132 can rotate in the motor stator 131, a plurality of top loss bodies 12 are uniformly fixed on the inner wall of the motor rotor 132 along the circumferential direction, and the motor rotor 132 enables the extending end of the top loss body 12 to rotate around the inner casing 22.
The first driving portion 13 is an annular motor, a motor stator 131 on the annular motor is fixedly connected with the nacelle 21, a motor rotor 132 on the annular motor is installed in the motor stator 131, a plurality of top loss reducing bodies 12 are evenly installed on the inner wall of the motor rotor 132 along the circumferential direction of the inner wall, the top loss reducing bodies 12 extend inwards along the radial direction of the motor rotor 132, when the annular motor works, the motor stator 131 drives the motor rotor 132 to drive the top loss reducing bodies 12 to rotate around the inner casing 22, meanwhile, the height range of the top loss reducing bodies 12 can be controlled to occupy 0% -20% of the height of the boundary layer of the fan blades 23 of the suction fan 2, the specific shape and the height value of the top loss reducing bodies 12 can be optimized and adjusted correspondingly according to the thickness distribution situation of the boundary layer obtained through experiments or calculation, and the rotating direction and the rotating speed of the top loss reducing bodies 12 are optimized and matched correspondingly according to the results of the experiments and the CFD value calculation. The first driving part 13 is a ring-shaped motor and is arranged and installed on the inner wall of the nacelle 21, so that the structural form and the arrangement form of the first driving part 13 are simplified, and meanwhile, the first driving part 13 does not interfere with the air intake condition of the fan.
As a preferred embodiment, as shown in fig. 1, the second driving portion 14 includes a first motor 141 and a first transmission shaft 142, the first motor 141 is fixedly installed in the inner casing 22, an end of the first transmission shaft 142 is fixedly connected to the first motor 141, a plurality of root reducers 11 are uniformly and fixedly installed on an outer wall of the first transmission shaft 142 along a circumferential direction, and an extending end of the root reducers 11 rotates around the inner casing 22.
The root damage reducing body 11 moves through the second driving portion 14, the first motor 141 in the second driving portion 14 is fixedly installed in the inner casing 22, the power output end of the first motor 141 is connected with the first transmission shaft 142, the first transmission shaft 142 and the inner casing 22 are coaxial, the outer wall of the first transmission shaft 142 is fixedly connected with the end portions of the root damage reducing bodies 11 which are uniformly distributed along the circumferential direction, when the first motor 141 works, the first transmission shaft 142 drives the extending end of the root damage reducing body 11 to rotate around the inner casing 22 in an interval, meanwhile, the height range of the root damage reducing body 11 can be controlled to occupy 0% -20% of the height of the fan blades 23 of the boundary layer suction fan 2, the specific shape and height value of the root damage reducing body 11 can be correspondingly optimized and adjusted according to the thickness distribution condition of the boundary layer obtained through experiments or calculation, the rotation direction and rotation speed of the root damage reducing body 11 are correspondingly optimized and matched according to the results of experiments and the calculation of the CFD value, the root damage reducing body 11 can increase the kinetic energy of the boundary layer near the root damage reducing box 22, the thickness of the root damage reducing body is reduced, the pneumatic efficiency of the root damage reducing body is favorable for improving the pneumatic efficiency of the root damage reducing body, and the root damage reducing body 11, and the root damage reducing body is favorable for flexibly and the root damage reducing body 11 in a manner of the root damage reducing method for flexibly driving the root damage of the second driving method.
As a preferred embodiment, as shown in fig. 1, the loss reducer 1 further includes a second motor 15 and a second transmission shaft 16, and the second motor 15 rotates the fan blades 23 between the intervals via the second transmission shaft 16.
The air flows to the fan blades 23 after flowing through the loss reducing device 1, the fan blades 23 rotate through the second motor 15 and the second transmission shaft 16, the second motor 15 is fixedly connected to the inner casing 22, one end of the second transmission shaft 16 is fixedly connected with the power output end of the second motor 15, the other end of the second transmission shaft 16 is coaxially and fixedly connected with a blade disc, the blade disc is fixedly connected with the fan blades 23 uniformly arranged along the circumferential direction of the blade disc, the second motor 15 drives the fan blades 23 to rotate in the interval between the nacelle 21 and the inner casing 22 through the second transmission shaft 16 when working, the fan blades 23 play a role in sucking the boundary layer of the machine body and generating forward thrust, and the fan blades 23 are driven by the independent second motor 15, so that the working state of the fan blades 23 can be flexibly configured according to experimental or calculated results and thrust requirements.
As a preferred embodiment, as shown in fig. 3, the damage reducing device 1 further includes a second transmission shaft 16, the second transmission shaft 16 is sleeved outside the first transmission shaft 142, one end of the second transmission shaft 16 is fixedly connected to the first motor 141, the other end of the second transmission shaft 16 extends toward the root damage reducing body 11, a plurality of fan blades 23 are fixedly installed on an outer wall of an extending end of the second transmission shaft 16 along a circumferential direction, the second transmission shaft 16 enables the fan blades 23 to rotate between intervals, and the second transmission shaft 16 and the first transmission shaft 142 keep coaxial.
In other embodiments, an arrangement scheme that the first motor 141 drives the fan blades 23 and the root damage reducing device 1 simultaneously may be adopted, the first transmission shaft 142 and the second transmission shaft 16 are both fixedly connected to the power output end of the first motor 141 in a coaxial sleeving manner, the second transmission shaft 16 is sleeved outside the first transmission shaft 142, and an interval is formed between the inner wall of the second transmission shaft 16 and the outer wall of the first transmission shaft 142, the extending end of the second transmission shaft 16 is coaxially and fixedly connected with a blade disc, the blade disc is fixedly connected to a plurality of fan blades 23 uniformly arranged along the circumferential direction thereof, the outer wall of the extending end of the first transmission shaft 142 is fixedly connected to the end portions of the plurality of root damage reducing bodies 11 uniformly distributed along the circumferential direction thereof, when the first motor 141 works, the first transmission shaft 142 and the second transmission shaft 16 respectively drive the root damage reducing bodies 11 and the fan blades 23 to perform a rotational motion in the interval between the nacelle 21 and the internal casing 22, such a design may reduce the number of motors, save space in the casing 22, and provide a better integration degree between the damage reducing device 1 and the fan.
As a preferred embodiment, as shown in fig. 3, the fan further includes a speed reducing portion 17, the first transmission shaft 142 includes a first shaft 1421 and a second shaft 1422, one end of the first shaft 1421 is fixedly connected to the first motor 141, the other end of the first shaft 1421 is fixedly connected to an input end of the speed reducing portion 17, an output end of the speed reducing portion 17 is fixedly connected to one end of the second shaft 1422, a plurality of root damage reducing bodies 11 are uniformly and fixedly mounted on an outer wall of the second shaft 1422 along a circumferential direction, and an extending end of the root damage reducing body 11 rotates around the inner casing 22.
In other embodiments, since the arrangement scheme that the first motor 141 drives the fan blades 23 and the root impairment device 1 simultaneously is adopted, the speed reduction portion 17 is further used in the scheme, the first transmission shaft 142 is divided into the first shaft 1421 and the second shaft 1422, the first shaft 1421 transmits the power of the first motor 141 to the speed reduction portion 17, the power is transmitted to the root impairment body 11 through the second transmission shaft 16 after being subjected to speed adjustment by the speed reduction portion 17, and the speed reduction portion 17 plays a role in regulating the speed of the root impairment body 11, so that the root impairment body 11 and the fan blades 23 can obtain respective required rotating speeds.
An embodiment of the present invention provides a boundary layer suction fan 2, and as shown in fig. 1 and 3, the boundary layer suction fan 2 employs the above-described loss reducing device 1.
By adopting the structure form, the loss reducing device 1 is designed and installed in the interval formed by the inner wall of the nacelle 21 and the outer wall of the inner casing 22 of the boundary layer suction fan 2, the loss reducing device 1 comprises a plurality of root loss reducing bodies 11 which are uniformly distributed along the circumferential direction of the inner casing 22 and radially and outwardly extend from the outer wall of the inner casing 22 to the interval, and a plurality of top loss reducing bodies 12 which are uniformly distributed along the circumferential direction of the nacelle 21 and radially and inwardly extend from the inner wall of the nacelle 21 to the interval; when the loss reducing device 1 works, the root loss reducing bodies 11 rotate around the inner casing 22, and the top loss reducing bodies 12 are positioned on the outer rings of the root loss reducing bodies 11 and rotate around the inner casing 22; the loss reducing device 1 with the structure form adopted by the boundary layer suction fan 2 is relatively low in cost and easy to disassemble and assemble, the loss reducing device 1 can effectively reduce low-energy fluid accumulation of boundary layers at the tops of the fan blades 23 and near blade roots, the inlet airflow quality and the aerodynamic efficiency of the fan are improved, the problem of low working efficiency of the boundary layer suction fan 2 is effectively solved, the oil consumption of an engine is reduced, the carbon emission is reduced, and the economy of the aircraft 3 is improved.
An embodiment of the present invention provides an aircraft 3, as shown in fig. 4, where the aircraft 3 employs the boundary layer suction fan 2.
By adopting the structure form, the damage reducing device 1 is designed and installed in the interval formed by the inner wall of the nacelle 21 and the outer wall of the inner casing 22 of the boundary layer suction fan 2 at the tail part of the aircraft 3, the damage reducing device 1 comprises a plurality of root damage reducing bodies 11 which are uniformly distributed along the circumferential direction of the inner casing 22 and radially and outwards extend from the outer wall of the inner casing 22 to the interval, and a plurality of top damage reducing bodies 12 which are uniformly distributed along the circumferential direction of the nacelle 21 and radially and inwards extend from the inner wall of the nacelle 21 to the interval; when the loss reduction device 1 is in operation, the root loss reducing bodies 11 rotate around the inner casing 22, and the top loss reducing bodies 12 rotate around the inner casing 22 at the outer rings of the root loss reducing bodies 11.
The left engine 34 and the right engine 31 on both sides of the aircraft 3 adopt conventional gas turbine engines, low-pressure shafts or high-pressure shafts of the two engines are respectively connected with the left generator 35 and the right generator 32 through mechanisms such as reduction gearboxes and the like to generate electric power, the electric energy generated by the left generator 35 and the right generator 32 is respectively transmitted to the boundary layer suction fan 2 at the tail part through a left engine cable 36 line and a right engine cable 33 line, and the thrust generated by the electric power extracted from the left engine 34 and the right engine 31 acting on the boundary layer suction fan 2 accounts for 10-25% of the total thrust.
The loss reducing device 1 with the structure form that the boundary layer suction fan 2 at the tail part of the aircraft 3 is adopted is relatively low in cost and easy to disassemble and assemble, the loss reducing device 1 can effectively reduce low-energy fluid accumulation of boundary layers near the tops and the blade roots of the fan blades 23, the inlet airflow quality and the pneumatic efficiency of the fan are improved, the problem that the boundary layer suction fan 2 is low in working efficiency is effectively solved, the oil consumption of an engine is reduced, the carbon emission is reduced, and the economy of the aircraft 3 is improved.
While specific embodiments of the invention have been described above, it will be appreciated by those skilled in the art that this is by way of example only, and that the scope of the invention is defined by the appended claims. Various changes or modifications to these embodiments may be made by those skilled in the art without departing from the principle and spirit of this invention, and these changes and modifications are within the scope of this invention.
Claims (11)
1. A loss reduction device applied to a fan, the fan comprising: nacelle, interior cartridge receiver and fan blade, the nacelle cover is located the outside of interior cartridge receiver forms the interval, its characterized in that, the device is decreased including:
a root relief extending radially outward from an outer wall of the inner barrel into the gap and rotating around the inner barrel;
a top bluff body extending radially inward from an inner wall of the nacelle into the compartment and rotating around the inner barrel;
a second gap is provided between the protruding end of the root impairment body and the protruding end of the tip impairment body; air flows through the loss reduction device and then to the fan blades.
2. An abatement device according to claim 1, further comprising a first drive section and a second drive section;
the first driving part is fixedly connected with the nacelle, and the first driving part enables the top damage reducing body to rotate around the inner casing;
the second driving part is fixedly connected with the inner casing, and the root damage reducing body rotates around the inner casing through the second driving part.
3. A loss reducing device according to claim 2, wherein the first driving portion surrounds and is fixed to an inner wall of the nacelle, the inner wall of the first driving portion having the tip loss fixedly mounted thereto, the first driving portion rotating an extended end of the tip loss around the root loss.
4. A loss reducing device according to claim 3, wherein said first driving part includes a motor stator and a motor rotor, said motor stator is fixed to and surrounded by an inner wall of said nacelle, said motor rotor is provided to surround an inner wall of said motor stator, said motor rotor is rotatable within said motor stator, said top loss reducing members are uniformly fixed to an inner wall of said motor rotor in a circumferential direction thereof, and said motor rotor rotates a projecting end of said top loss reducing member around said inner casing.
5. A loss reducing device according to claim 2, wherein the second driving part comprises a first motor and a first transmission shaft, the first motor is fixedly mounted in the inner casing, an end of the first transmission shaft is fixedly connected with the first motor, a plurality of root loss reducing bodies are uniformly and fixedly mounted on an outer wall of the first transmission shaft along a circumferential direction, and a protruding end of the root loss reducing body rotates around the inner casing.
6. An abatement device according to claim 5, further comprising a second motor and a second drive shaft, the second motor rotating the fan blades between the intervals via the second drive shaft.
7. The damage reduction device of claim 5, further comprising a second transmission shaft sleeved outside the first transmission shaft, wherein one end of the second transmission shaft is fixedly connected to the first motor, the other end of the second transmission shaft extends toward the root damage reduction body, a plurality of fan blades are fixedly mounted on an outer wall of an extending end of the second transmission shaft along a circumferential direction, and the second transmission shaft enables the fan blades to rotate between the intervals.
8. An impairment device of claim 7, wherein the second transmission shaft is coaxially sleeved outside the first transmission shaft.
9. An impairment device according to claim 8, wherein the fan further comprises a speed reduction portion, the first transmission shaft comprises a first shaft and a second shaft, one end of the first shaft is fixedly connected to the first motor, the other end of the first shaft is fixedly connected to an input end of the speed reduction portion, an output end of the speed reduction portion is fixedly connected to one end of the second shaft, a plurality of the root impairment bodies are circumferentially and uniformly and fixedly mounted on an outer wall of the second shaft, and an extending end of each root impairment body rotates around the inner casing.
10. A boundary layer suction fan, characterized in that the boundary layer suction fan comprises a loss reducing arrangement according to any one of claims 1-9.
11. An aircraft, characterized in that the aircraft comprises a fan according to any one of claims 1-9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110758076.0A CN115583335A (en) | 2021-07-05 | 2021-07-05 | Loss reduction device, boundary layer suction fan and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110758076.0A CN115583335A (en) | 2021-07-05 | 2021-07-05 | Loss reduction device, boundary layer suction fan and aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN115583335A true CN115583335A (en) | 2023-01-10 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110758076.0A Pending CN115583335A (en) | 2021-07-05 | 2021-07-05 | Loss reduction device, boundary layer suction fan and aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117054037A (en) * | 2023-10-12 | 2023-11-14 | 中国空气动力研究与发展中心低速空气动力研究所 | Boundary layer suction wind tunnel test device for aircraft with mixed wing body layout |
-
2021
- 2021-07-05 CN CN202110758076.0A patent/CN115583335A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117054037A (en) * | 2023-10-12 | 2023-11-14 | 中国空气动力研究与发展中心低速空气动力研究所 | Boundary layer suction wind tunnel test device for aircraft with mixed wing body layout |
| CN117054037B (en) * | 2023-10-12 | 2023-12-29 | 中国空气动力研究与发展中心低速空气动力研究所 | Boundary layer suction wind tunnel test device for aircraft with mixed wing body layout |
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