CN112502854A - Propulsion power system of propeller tip jet self-driven ducted fan - Google Patents

Propulsion power system of propeller tip jet self-driven ducted fan Download PDF

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Publication number
CN112502854A
CN112502854A CN202011329550.XA CN202011329550A CN112502854A CN 112502854 A CN112502854 A CN 112502854A CN 202011329550 A CN202011329550 A CN 202011329550A CN 112502854 A CN112502854 A CN 112502854A
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China
Prior art keywords
blade
self
ducted fan
hollow
nozzle
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黄国平
周扬
朱远昭
夏晨
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Nanjing University of Aeronautics and Astronautics
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Nanjing University of Aeronautics and Astronautics
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Priority to CN202011329550.XA priority Critical patent/CN112502854A/en
Publication of CN112502854A publication Critical patent/CN112502854A/en
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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
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • 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
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/005—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the engine comprising a rotor rotating under the actions of jets issuing from this rotor

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Architecture (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The invention discloses a propeller tip jet self-driven ducted fan propulsion power system, which comprises a core engine and a self-driven ducted fan, wherein the self-driven ducted fan comprises a plurality of hollow blades, the same sides of the hollow blades are provided with shape-preserving nozzles, the core engine and the self-driven ducted fan are communicated through a gas-guiding pipe, gas is conveyed into each hollow blade of the self-driven ducted fan by the core engine through the gas-guiding pipe and is ejected out by the shape-preserving nozzles of the hollow blades to push the hollow blades to rotate and suck air to generate thrust, the design limitation of the conventional large-bypass-ratio turbofan engine is broken through, the bypass ratio of the engine is greatly increased, the problem of matching the rotating speed of the large-bypass-ratio engine is solved by using a gas drive energy conversion mode at the expense of smaller weight and structure, the thrust of the core engine is converted into thrust which can adjust the thrust direction and is several times of the thrust of the ducted fan of, the propulsion power requirements of vertical take-off and landing, thrust diversion and the like of the aircraft can be realized.

Description

Propulsion power system of propeller tip jet self-driven ducted fan
Technical Field
The invention relates to the technical field of aircraft power, in particular to a blade tip jet self-driven ducted fan propulsion power system.
Background
The vertical take-off and landing technology is a technology which is raised since the fifth and sixty years of the last century, can help fixed-wing aircrafts to reduce or basically get rid of the dependence on runways, and can realize quick and safe take-off and landing only by small flat ground, so that the aircraft with the vertical take-off and landing capability does not need special airports and runways, has strong adaptability to terrain, can be dispersedly configured or assembled on naval vessels, is convenient for flexible attack, transfer and camouflage concealment, and can finish high-difficulty actions which cannot be finished by other fixed-wing aircrafts such as hovering; with the development of foreign vertical take-off and landing aircraft concepts, the current most important technical forms include the following 3 types: 1) compound helicopter: when the helicopter is vertically lifted and landed, the top rotor wing is used for generating pulling force like a helicopter, and the horizontal engines arranged on the two sides or the tail part of the fuselage are used for generating pushing force under the condition of flat flight; typical models are for example the X2 high speed helicopter from western corsky, usa, the X3 helicopter from european helicopters; 2) tilt rotor aircraft: the change of the power direction is realized through the integral rotation of the engine, the engine generates upward pulling force approximately vertically when taking off, landing and hovering, and the engine tilts to be approximately horizontal to provide advancing power when flying horizontally; typical models such as the U.S. V-22 osprey tiltrotor aircraft; 3) jet steered fixed wing aircraft: adopt tilting vector spray tube and duct fan structure to realize vertical take-off and landing and fly function, if: rays of the United kingdom, U.S. F35-B. The power system of the first two types of vertical take-off and landing aircrafts is realized by combining the turbine engines (turboshafts/turbines) in the existing form or changing the use rule, the power system of the third type greatly expands the advanced military turbofan engine, the two-stage counter-rotating lift force fan and the vector spray pipe generate and provide vertical lift force, and all functions of a fighter are kept after the aircraft is turned into flat flight, so that the power system is widely regarded.
Because vertical take-off and landing are realized, the take-off weight of the airplane can only be 83% -85% of the thrust of an engine, so that the effective load of the airplane is greatly limited, the oil loading capacity and the range of the airplane are seriously influenced, the oil consumption in the vertical take-off and landing process is very high and occupies 1/3 of the oil loading capacity of the airplane, and the combat radius of the airplane is also greatly limited; no matter the work power of the composite helicopter is switched, the engine of the tilt rotor aircraft turns or the jet steering is carried out on the lift fan and the vector spray pipe of the fixed-wing aircraft, the structure and the control complexity of a power system are required to be greatly increased for realizing the conversion of vertical and horizontal power output, so that the mechanical connection is more complicated, and therefore, a blade tip jet self-driven ducted fan propulsion power system is urgently needed to solve the problems.
Disclosure of Invention
The invention provides a propeller tip jet self-driven ducted fan propulsion power system capable of amplifying the thrust of a core engine, reducing the oil consumption rate and adjusting the thrust direction, which can effectively solve the problems that the existing system has small thrust, high oil consumption rate and complicated and heavy mechanical connection.
In order to achieve the purpose, the invention provides the following technical scheme: a blade tip jet self-driven ducted fan propulsion power system comprises a core engine and a self-driven ducted fan;
the self-driven ducted fan comprises a plurality of hollow blades, wherein the same side of each hollow blade is provided with a shape-retaining nozzle;
the core engine is communicated with the self-driven ducted fan through the air entraining pipe, and air is conveyed into each hollow blade of the self-driven ducted fan through the air entraining pipe by the core engine and is sprayed out by the shape-preserving nozzles of each hollow blade to push the hollow blades to rotate and suck air to generate thrust.
According to the technical scheme, the core engine is a turbofan engine, and an air guide valve is installed in the exhaust section of the turbofan engine.
According to the technical scheme, the hollow blade is internally provided with the inner pipeline of the blade, the inner pipeline of the blade consists of a radial gas transmission section, a turning section, a contraction section and a horizontal gas injection section, gas enters from an opening of the radial gas transmission section, is conveyed to the turning section through the radial gas transmission section, is guided by the turning section and then enters the contraction section, the contraction section accelerates the gas flow to enter the horizontal gas injection section, and the horizontal gas injection section rectifies the gas flow and conveys the rectified gas to the shape-preserving nozzle.
According to the technical scheme, the shape-preserving nozzle is arranged on the surface of the tail edge of the blade of the hollow blade, wherein the projection of the shape-preserving nozzle to the air injection direction is a rectangle with the length-width ratio of 45, and the distance between the opening edge of the shape-preserving nozzle close to the tail edge and the tail edge of the blade is 0.03 time of the airfoil chord length.
According to the technical scheme, the self-driven ducted fan comprises a fan shell, an annular duct is arranged in the fan shell, a fan-shaped expansion section is installed between the air guide pipe and the fan shell, and gas is guided into the annular duct through the fan-shaped expansion section in the circumferential direction.
According to the technical scheme, a hollow shaft seat is coaxially arranged at the center of the fan shell, a supporting pipeline is arranged between the hollow shaft seat and the fan shell, and the hollow shaft seat is used for fixing the hollow shaft seat and communicating the hollow shaft seat with the annular duct;
a hollow hub used for rotating is installed at the end part of the hollow shaft seat, and a plurality of hollow blades are uniformly distributed along the circumferential direction of the hollow hub and are communicated with the hollow hub;
the air in the annular duct is conveyed into the hollow blade through the supporting pipeline, the hollow shaft seat and the hollow blade hub in sequence.
According to the technical scheme, the hollow hub is provided with a pair of bearings which are stressed oppositely, a bearing sleeve divided into two parts is arranged outside each bearing, and the bearing sleeve is connected with the hollow shaft seat and used for supporting the bearings.
According to the technical scheme, a pair of sealing blocks for combined sealing of the sealing end surfaces of the labyrinth type labyrinth comb tooth are arranged between the hollow shaft seat and the hollow propeller hub.
A design method for the above-mentioned propulsion power system includes the following steps:
1) designing Mae jet mach number at the shape-preserving nozzle, controlling the jet speed to be lower than the sonic speed, designing Man number of the pipeline in the blade, wherein the loss in the pipeline is small when the Mach number is low, and designing the total temperature T of the pipeline in the blade according to the characteristics of the blade material;
2) designing required appearance parameters of the ducted fan according to the requirements of an aircraft, wherein the airfoil chord length is c, the distance between the opening edge of the shape-preserving nozzle and the tail edge of the blade is 0.03c, the projection height h of the nozzle in the air injection direction is 45 h;
3) calculating the total torque M provided by the jetg：
Figure BDA0002795348560000041
Wherein dr iseIs the radial infinitesimal distance of the nozzle, integrated over the length of the nozzle, peDensity of jet
Figure BDA0002795348560000042
νeIs the velocity of the jet
Figure BDA0002795348560000043
4) Calculating the Brother force torque M generated by the jetc：
Mc＝2ωvnρnSn∫rndrn
Wherein the pressure of the pipeline in the blade
Figure BDA0002795348560000044
Pressure temperature of pipeline in blade
Figure BDA0002795348560000045
From this, the density and speed of the pipeline in the blade can be obtained
Figure BDA0002795348560000046
drnIs the path direction infinitesimal distance of the inner pipe of the blade, the integral in the length range of the inner pipeline, omega is the rotating speed of the rotor wing, and the total pressure at the nozzle
Figure BDA0002795348560000047
Total pressure p with bleed air*And pressure p at the nozzleeThe relationship of (1) is:
Figure BDA0002795348560000048
wherein, kappa is the total pressure loss coefficient of 0.03-0.06, U1Is the peripheral speed, U, of the nozzle at the radially nearest position to the axis of rotationhIs the peripheral speed at the radius of the hub, from which the nozzle jet flow can be calculated
Figure BDA0002795348560000049
Se is the nozzle area, from which the in-vane line area is calculated
Figure BDA0002795348560000051
5) Calculating the pressure difference resistance at the nozzle: mp
Mp＝(pe-pr)Serem
Wherein p isrIs far field air pressure, remIs the distance from the radial center of the nozzle to the axis;
6) and calculating the effective jet torque according to the results of the steps 3 to 6:
Me＝Mg-Mc+Mp
the required parameters of the self-driven ducted fan under design appearance and working condition are obtained by matching the effective torque equal to the torque required by the rotor.
The parameters required by the self-driven ducted fan comprise total pressure, flow and total temperature of the high-energy fuel gas.
Compared with the prior art, the invention has the beneficial effects that:
1. in the invention, the core engine generates high-energy gas, the air-entraining pipe conveys the high-energy gas to each hollow blade of the self-driven ducted fan, the shape-preserving nozzles with the blade tips of the hollow blades spray out to provide thrust torque, the fan is driven to rotate to suck a large amount of external low-temperature airflow, the design limitation of the conventional turbofan engine with large bypass ratio is broken through, the bypass ratio of the engine is greatly increased, wherein the power of the propulsion system is generated by the pulling force of the ducted fan, the exhaust can be controlled by adjusting the bleed air pipe, the thrust direction is controlled and adjusted by changing the attack angle of the ducted fan, the problem of matching of the rotating speed of the engine with a large ducted ratio is solved by using a gas drive energy conversion mode at the cost of smaller weight and structure, the thrust of the core engine is converted into the thrust direction which can be adjusted and is several times of the thrust of the ducted fan of the prokaryotic core engine, and the propulsion power requirements of vertical take-off and landing, thrust turning and the like of an aircraft can be realized;
in addition, because the working medium of the fan is atmospheric air, the exhaust temperature of the fan is much lower than that of a core engine, high-temperature and high-energy gas is converted into fan suction air to do work, the exhaust temperature of the fan is low, the thermal shock to a vertical take-off and landing site of the aircraft is small, the range of the applicable site of the aircraft is improved, the core engine is connected with the self-driven ducted fan only through an air entraining pipe, the complicated and heavy mechanical connection is omitted, the design and manufacturing cost and the difficulty are reduced, meanwhile, the power system has extremely low limit on the air entraining pipe, a plurality of fans can be simultaneously arranged, the fans can be arranged inside a fuselage and wings according to the design requirements of the aircraft, and the aircraft is more flexibly arranged.
2. In the invention, the core engine is a turbofan engine, and the exhaust gas temperature generated by the turbofan engine is lower than that of a turbojet engine, and the flow is larger, so that the heat bearing requirement on an air conveying channel in the device is reduced, the jet speed can be reduced when the blade tip jets air, and the noise is reduced.
3. In the invention, the shape-preserving nozzle is arranged on the surface of the trailing edge of the blade of the hollow blade, when the nozzle is closed, the shape of the original airfoil is not influenced, the distance between the outlet edge of the nozzle close to the trailing edge and the trailing edge of the blade is 0.03 times of the chord length of the airfoil, the coanda effect is generated after jet blowing, the flow separation phenomenon of the trailing edge of the blade under a large power angle is improved, the flow velocity of a suction surface is improved by mixing jet flow of the suction surface of the blade and main flow, and the pressure difference between the upper surface and the lower surface of the airfoil is increased.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention and not to limit the invention.
In the drawings:
FIG. 1 is a general configuration diagram of a blade tip jet self-driven ducted fan propulsion power system of the present invention;
FIG. 2 is a schematic illustration of a configuration of the propulsion power system of the present invention installed on an aircraft;
FIG. 3 is a schematic structural view of the hollow blade of the present invention;
FIG. 4 is a view of the tip jet self-driven ducted fan of the present invention;
FIG. 5 is a cross-sectional view of the self-powered ducted fan of the present invention;
FIG. 6 is a schematic view of the hollow shaft seat of the present invention;
reference numbers in the figures: 1. a core turbine; 2. a bleed pipe; 201. a fan-shaped expansion section; 3. a self-driven ducted fan; 4. a fan housing; 5. supporting the pipeline; 6. a hollow shaft seat; 7. a sealing block; 8. a bearing; 9. a bearing housing; 10. a hollow hub; 11. a hollow blade; 12. a blade inner pipeline; 13. a gas transmission section; 14. a turning section; 15. a contraction section; 16. a horizontal air injection section; 17. and (4) maintaining the shape of the nozzle.
Detailed Description
The preferred embodiments of the present invention will be described in conjunction with the accompanying drawings, and it will be understood that they are described herein for the purpose of illustration and explanation and not limitation.
Example (b): as shown in fig. 1, a tip jet self-driven ducted fan 3 propulsion power system includes a core engine and a self-driven ducted fan 3;
the core engine is a turbofan engine, the exhaust temperature of gas generated by the turbofan engine is lower than that of a turbojet engine, the flow is larger, an air guide valve is installed in the exhaust section of the turbofan engine, and high-energy gas is guided to an air guide pipe 2 connected with the exhaust section of the engine by the air guide valve in the exhaust section of the turbofan engine;
the self-driven ducted fan 3 comprises a plurality of hollow blades 11, and the same side of each hollow blade 11 is provided with a shape-retaining nozzle 17;
the core engine and the self-driven ducted fan 3 are communicated through the air guide pipe 2, the core engine discharges high-energy gas, the gas is conveyed into each hollow blade 11 of the self-driven ducted fan 3 through the air guide pipe 2 by the core engine, the high-energy gas is sprayed out by the shape-preserving nozzles 17 of each hollow blade 11 to provide thrust torque, the fan is driven to rotate, a large amount of external low-temperature air flow is sucked, the bypass ratio of the original turbofan engine is amplified supernormally, the thrust which is multiple times that of the original turbofan engine is generated, the exhaust temperature is reduced, the structure that the air guide pipe 2 is adopted to convey the high-energy gas can be flexibly arranged in the engine body, and the adjustment and the control of the thrust direction can be realized by adjusting the installation angles of the air guide pipe.
As shown in fig. 2, a blade inner pipe 12 is arranged in a hollow blade 11, the blade inner pipe is composed of a radial gas transmission section 13, a turning section 14, a contraction section 15 and a horizontal gas injection section 16, gas enters from an opening of the radial gas transmission section 13, is conveyed to the turning section 14 through the radial gas transmission section 13, enters the contraction section 15 after being guided by the turning section 14, the contraction section 15 accelerates the gas flow to enter the horizontal gas injection section 16, the horizontal gas injection section 16 rectifies the gas flow and conveys the rectified gas to a shape-preserving nozzle 17, wherein the shape-preserving nozzle 17 is arranged on the surface of the blade tail edge of the hollow blade, the projection of the shape-preserving nozzle 17 to the gas injection direction is a rectangle with the length-width ratio of 45, the distance between the opening edge of the shape-preserving nozzle 17 close to the tail edge and the blade tail edge is 0.03 times of the chord length of an airfoil, the coanda effect is generated after the gas injection, the flow separation phenomenon of the blade tail edge under a large power angle is improved, and is mixed, the flow velocity of the suction surface is improved, and the pressure difference between the upper surface and the lower surface of the wing profile is increased, so that the tension of the blade is increased.
As shown in fig. 3-4, the self-driven ducted fan 3 includes a fan housing 4, an annular duct is disposed in the fan housing 4, a fan-shaped expanding section 201 is disposed between the bleed air pipe 2 and the fan housing 4, air is introduced into the annular duct through the fan-shaped expanding section 201 in a circumferential direction, a hollow shaft seat 6 is coaxially disposed at the center of the fan housing 4, a supporting pipeline 5 is disposed between the hollow shaft seat 6 and the fan housing 4, the hollow shaft seat 6 is supported and fixed by the supporting pipeline 5, the hollow shaft seat 6 is used for fixing the hollow shaft seat 6 and communicating the hollow shaft seat 6 and the annular duct, a hollow propeller hub 10 for rotating is disposed at an end of the hollow shaft seat 6, a tail of the hollow propeller hub 10 is conical, a plurality of hollow blades 11 are uniformly distributed along the circumferential direction of the hollow propeller hub 10 and communicate with the hollow propeller hub 10, air in the annular duct sequentially passes through the supporting pipeline 5, the hollow propeller hub 6 and the, the air is conveyed into a hollow blade 11, as shown in fig. 5, a pair of bearings 8 which are stressed oppositely are arranged on a hollow blade hub 10, a bearing sleeve 9 which is divided into two parts is arranged outside the bearing 8, the bearing sleeve 9 is connected with a hollow shaft seat 6 and used for supporting the bearing 8, and a pair of sealing blocks 7 which are combined and sealed by labyrinth sealing end surfaces are arranged between the hollow shaft seat 6 and the hollow blade hub 10, so that effective air tightness is provided and air injection torque loss is reduced.
A design method for the above-mentioned propulsion power system includes the following steps:
1) designing Mae jet mach number at the shape-preserving nozzle, controlling the jet speed to be lower than the sonic speed, designing Man number of the pipeline in the blade, wherein the loss in the pipeline is small when the Mach number is low, and designing the total temperature T of the pipeline in the blade according to the characteristics of the blade material;
2) designing required appearance parameters of the ducted fan according to the requirements of an aircraft, wherein the airfoil chord length is c, the distance between the opening edge of the shape-preserving nozzle and the tail edge of the blade is 0.03c, the projection height h of the nozzle in the air injection direction is 45 h;
3) calculating the total torque M provided by the jetg：
Figure BDA0002795348560000091
Wherein dr iseIs the radial infinitesimal distance of the nozzle, integrated over the length of the nozzle, peDensity of jet
Figure BDA0002795348560000092
νeIs the velocity of the jet
Figure BDA0002795348560000093
4) Calculating the Brother force torque M generated by the jetc：
Mc＝2ωvnρnSn∫rndrn
Wherein the pressure of the pipeline in the blade
Figure BDA0002795348560000094
Pressure temperature of pipeline in blade
Figure BDA0002795348560000095
From this, the density and speed of the pipeline in the blade can be obtained
Figure BDA0002795348560000096
drnIs the path direction infinitesimal distance of the inner pipe of the blade, the integral in the length range of the inner pipeline, omega is the rotating speed of the rotor wing, and the total pressure at the nozzle
Figure BDA0002795348560000097
Total pressure p with bleed air*And pressure p at the nozzleeThe relationship of (1) is:
Figure BDA0002795348560000098
wherein, kappa is the total pressure loss coefficient of 0.03-0.06, U1Is the peripheral speed, U, of the nozzle at the radially nearest position to the axis of rotationhIs the peripheral speed at the radius of the hub, from which the nozzle jet flow can be calculated
Figure BDA0002795348560000101
Se is the nozzle area, from which the in-vane line area is calculated
Figure BDA0002795348560000102
5) Calculating the pressure difference resistance at the nozzle: mp
Mp＝(pe-pr)Serem
Wherein p isrIs far field air pressure, remIs the distance from the radial center of the nozzle to the axis;
6) and calculating the effective jet torque according to the results of the steps 3 to 6:
Me＝Mg-Mc+Mp
the required parameters of the self-driven ducted fan under design appearance and working condition are obtained by matching the effective torque to be equal to the required torque of the rotor wing, wherein the required parameters of the self-driven ducted fan comprise total pressure, flow and total temperature of high-energy gas.
Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that changes may be made in the embodiments and/or equivalents thereof without departing from the spirit and scope of the invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims (10)

1. The utility model provides a blade point jet-propelled self-driven duct fan propulsion driving system which characterized in that: comprises a core engine and a self-driven ducted fan;
the self-driven ducted fan comprises a plurality of hollow blades, wherein the same side of each hollow blade is provided with a shape-retaining nozzle;
the core engine is communicated with the self-driven ducted fan through the air entraining pipe, and air is conveyed into each hollow blade of the self-driven ducted fan through the air entraining pipe by the core engine and is sprayed out by the shape-preserving nozzles of each hollow blade to push the hollow blades to rotate and suck air to generate thrust.
2. The tip jet self-propelled ducted fan propulsion power system according to claim 1, further comprising: the core engine is a turbofan engine, and an air guide valve is installed in an exhaust section of the turbofan engine.
3. The tip jet self-propelled ducted fan propulsion power system according to claim 1, further comprising: the hollow blade is internally provided with an inner blade pipeline, the inner blade pipeline consists of a radial gas transmission section, a turning section, a contraction section and a horizontal gas injection section, gas enters from an opening of the radial gas transmission section, is conveyed to the turning section through the radial gas transmission section, enters the contraction section after being guided by the turning section, accelerates the gas flow to enter the horizontal gas injection section, and rectifies the gas flow and conveys the rectified gas to the shape-preserving nozzle.
4. The tip jet self-propelled ducted fan propulsion power system according to claim 1, further comprising: the shape-preserving nozzle is arranged on the surface of the tail edge of the blade of the hollow blade, wherein the projection of the shape-preserving nozzle to the air injection direction is a rectangle with the length-width ratio of 45, and the distance between the opening edge of the shape-preserving nozzle close to the tail edge and the tail edge of the blade is 0.03 time of the airfoil chord length.
5. The tip jet self-propelled ducted fan propulsion power system according to claim 1, further comprising: the self-driven ducted fan comprises a fan shell, an annular duct is arranged in the fan shell, a fan-shaped expansion section is installed between the air guide pipe and the fan shell, and gas is guided into the annular duct through the fan-shaped expansion section in the circumferential direction.
6. The tip jet self-propelled ducted fan propulsion power system according to claim 5, wherein: a hollow shaft seat is coaxially arranged in the center of the fan shell, a supporting pipeline is arranged between the hollow shaft seat and the fan shell, and the hollow shaft seat is used for fixing the hollow shaft seat and communicating the hollow shaft seat with the annular duct;
a hollow hub used for rotating is installed at the end part of the hollow shaft seat, and a plurality of hollow blades are uniformly distributed along the circumferential direction of the hollow hub and are communicated with the hollow hub;
the air in the annular duct is conveyed into the hollow blade through the supporting pipeline, the hollow shaft seat and the hollow blade hub in sequence.
7. The tip jet self-propelled ducted fan propulsion power system according to claim 6, further comprising: the hollow hub is provided with a pair of bearings which are stressed oppositely, a bearing sleeve which is divided into two halves is arranged outside the bearings, and the bearing sleeve is connected with the hollow shaft seat and used for supporting the bearings.
8. The tip jet self-propelled ducted fan propulsion power system according to claim 6, further comprising: and a pair of labyrinth type sealing blocks which are sealed are arranged between the hollow shaft seat and the hollow propeller hub.
9. A design method for a propulsion power system as claimed in any one of claims 1 to 9, characterized by comprising the steps of:
1) designing Mae jet mach number at the shape-preserving nozzle, controlling the jet speed to be lower than the sonic speed, designing Man number of the pipeline in the blade, wherein the loss in the pipeline is small when the Mach number is low, and designing the total temperature T of the pipeline in the blade according to the characteristics of the blade material;
2) designing required appearance parameters of the ducted fan according to the requirements of an aircraft, wherein the airfoil chord length is c, the distance between the opening edge of the shape-preserving nozzle and the tail edge of the blade is 0.03c, the projection height h of the nozzle in the air injection direction is 45 h;
3) calculating the total torque M provided by the jetg：
Figure FDA0002795348550000031
Wherein dr iseIs the radial infinitesimal distance of the nozzle, integrated over the length of the nozzle, peDensity of jet
Figure FDA0002795348550000032
νeIs the velocity of the jet
Figure FDA0002795348550000033
4) Calculating the Brother force torque M generated by the jetc：
Mc＝2ωvnρnSn∫rndrn
Wherein the pressure of the pipeline in the blade
Figure FDA0002795348550000034
Pressure temperature of pipeline in blade
Figure FDA0002795348550000035
From this, the density and speed of the pipeline in the blade can be obtained
Figure FDA0002795348550000036
drnIs the path direction infinitesimal distance of the inner pipe of the blade, the integral in the length range of the inner pipeline, omega is the rotating speed of the rotor wing, and the total pressure at the nozzle
Figure FDA0002795348550000037
Total pressure p with bleed air*And pressure p at the nozzleeThe relationship of (1) is:
Figure FDA0002795348550000038
wherein, kappa is the total pressure loss coefficient of 0.03-0.06, U1Is the peripheral speed, U, of the nozzle at the radially nearest position to the axis of rotationhIs the peripheral speed at the radius of the hub, from which the nozzle jet flow can be calculated
Figure FDA0002795348550000039
Se is the nozzle area, from which the in-vane line area is calculated
Figure FDA00027953485500000310
5) Calculating the pressure difference resistance at the nozzle: mp
Mp＝(pe-pr)Serem
Wherein，prIs far field air pressure, remIs the distance from the radial center of the nozzle to the axis;
6) and calculating the effective jet torque according to the results of the steps 3 to 6:
Me＝Mg-Mc+Mp
the required parameters of the self-driven ducted fan under design appearance and working condition are obtained by matching the effective torque equal to the torque required by the rotor.
10. The tip jet self-propelled ducted fan propulsion power system according to claim 9, further comprising: the parameters required by the self-driven ducted fan comprise total pressure, flow and total temperature of the high-energy fuel gas.
CN202011329550.XA 2020-11-24 2020-11-24 Propulsion power system of propeller tip jet self-driven ducted fan Pending CN112502854A (en)

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Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130161444A1 (en) * 2011-12-22 2013-06-27 Pegasus Helicopter, Inc. High efficiency hub for pressure jet helicopters
CN104675556A (en) * 2014-12-26 2015-06-03 南京航空航天大学 Large-bypass-ratio turbofan engine of vane tip jet driven fan
CN210391554U (en) * 2019-04-09 2020-04-24 南京航空航天大学 Blade tip jet type constant frequency output manpower helicopter

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130161444A1 (en) * 2011-12-22 2013-06-27 Pegasus Helicopter, Inc. High efficiency hub for pressure jet helicopters
CN104675556A (en) * 2014-12-26 2015-06-03 南京航空航天大学 Large-bypass-ratio turbofan engine of vane tip jet driven fan
CN210391554U (en) * 2019-04-09 2020-04-24 南京航空航天大学 Blade tip jet type constant frequency output manpower helicopter

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
JIE CHEN,ETAL: "Numerical investigation of ducted fan aerodynamic performance with tip-jet", 《AEROSPACE SCIENCE AND TECHNOLOGY》 *

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Application publication date: 20210316