CN112443423B

CN112443423B - Jet propulsion power system of air-driven ducted fan

Info

Publication number: CN112443423B
Application number: CN202011329529.XA
Authority: CN
Inventors: 黄国平; 周扬; 朱远昭; 夏晨
Original assignee: Nanjing University of Aeronautics and Astronautics
Current assignee: Nanjing University of Aeronautics and Astronautics
Priority date: 2020-11-24
Filing date: 2020-11-24
Publication date: 2022-04-05
Anticipated expiration: 2040-11-24
Also published as: CN112443423A

Abstract

The invention discloses a jet propulsion power system of an air-driven ducted fan, which comprises a core turbine, a ducted fan connected with the core turbine through a bleed air pipe and a blade tip turbine coaxially installed with the ducted fan, the core turbine exhausts gas and transmits the gas to the blade tip turbine, the blade tip turbine expands the gas to do work, the ducted fan is driven to rotate and suck air to generate thrust, the design limitation of the conventional turbofan engine with a large bypass ratio is broken through, the engine bypass ratio is greatly increased, the basic principle that the propulsion efficiency of the turbofan engine with the large bypass ratio is improved is further exerted, and lower oil consumption and higher power output are obtained, and the function of the air-entraining pipe connected between the energy source core turbine and the ducted fan is only the uncomplicated mechanical connection of the airflow channel, the wing-shaped aircraft can be arranged inside a fuselage and a wing according to the design requirements of the aircraft, and the aircraft is more flexibly arranged.

Description

Jet propulsion power system of air-driven ducted fan

Technical Field

The invention relates to the technical field of aircraft power, in particular to a jet propulsion power system of an air-driven ducted fan.

Background

The straight take-off and landing technology is a technology which is developed since the fifties and the sixties of the last century, can help a fixed-wing aircraft reduce or basically get rid of the dependence on a runway, and can realize quick and safe take-off and landing by only needing a small flat ground. Therefore, the airplane with the vertical take-off and landing capability does not need a special airport and runway, has strong terrain adaptability, can be dispersedly configured or assembled on naval vessels, is convenient for flexible attack, transfer and camouflage and concealment, and can finish high-difficulty actions which cannot be finished by other fixed-wing airplanes such as hovering in the air; 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 power direction is realized through the whole rotation of engine, and the engine is approximately perpendicular when taking off and land and hovering produces ascending pulling force, and the engine verts to nearly level provides the power that advances when horizontal flight. 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, American 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 working 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 the power system are greatly increased when the power system of the existing various vertical take-off and landing aircrafts realize the conversion of vertical power output and horizontal power output, so that an air-driven ducted fan jet propulsion power system is urgently needed to solve the problems.

Disclosure of Invention

The invention provides a driving ducted fan jet propulsion power system capable of realizing high thrust and low oil consumption, which can effectively solve the problems of greatly limited load and high oil consumption caused by the complicated mechanical mechanism of the power system of an aircraft in the background technology.

In order to achieve the purpose, the invention provides the following technical scheme: a jet propulsion power system of an air-driven ducted fan comprises a core turbine, a ducted fan connected with the core turbine through a bleed air pipe and a blade tip turbine coaxially mounted with the ducted fan, wherein gas exhausted by the core turbine is transmitted to the blade tip turbine, the blade tip turbine expands to do work on the gas, and the ducted fan is driven to rotate to suck air to generate thrust.

According to the technical scheme, the ducted fan comprises an air inlet volute connected with a blade tip turbine and a rotating shaft located in the center of the ducted fan, a plurality of fan blades are uniformly installed on the rotating shaft in the circumferential direction, the end portions of the fan blades are connected with blade tip turbine blades located in a turbine inner ring and connected with the blade tip turbine, and air enters the blade tip turbine through the air inlet volute and directly drives the blade tip turbine blades and the fan blades to rotate.

According to the technical scheme, the air guide pipe is provided with a throttle valve for adjusting air flow.

According to the technical scheme, the air inlet of the ducted fan is provided with the air inlet device, the front end lip of the inlet of the air inlet device is provided with the rounding, the preset height is increased by the rear end lip of the inlet, and the rear side of the inlet of the air inlet device is provided with the guide plate for inhibiting the flow separation.

According to the technical scheme, the exhaust port of the ducted fan is movably provided with a baffle blade for adjusting the exhaust direction.

According to the technical scheme, an adjusting mechanism is installed at the exhaust outlet of the ducted fan and comprises a plurality of rows of guide vanes, each row of guide vanes comprises a main exhaust guide vane and auxiliary guide vanes which are symmetrically arranged on two sides of the main exhaust guide vane respectively, a rotating disc is installed at one end of each row of guide vanes, and the main exhaust guide vane and the auxiliary guide vanes are connected with the rotating disc;

the crank is arranged on one side of the rotating disc, the rotating disc is rotatably connected with the crank through the adjusting rod, and the rotating disc is driven to rotate through the adjusting rod along with the movement of the crank to adjust the angle of the guide vane.

According to the technical scheme, the guide vane angle adjusting range is-45 degrees to 45 degrees.

Compared with the prior art, the invention has the beneficial effects that:

1. in the invention, the core turbofan engine generates high-energy airflow, the air guide pipe conveys high-energy gas, the blade tip turbine extracts the energy of the high-energy gas to drive the ducted fan to rotate, the ducted fan blades suck ambient air and mix the ambient air with the driving gas with certain kinetic energy to discharge the air to generate the propelling force, the design limitation of the conventional turbofan engine with a large bypass ratio is broken through, the bypass ratio of the engine is greatly increased, the basic principle that the propulsion efficiency of the turbofan engine with the large bypass ratio is further improved is exerted, lower oil consumption and higher power output are obtained, the function of the air guide pipe connected between the energy source core turbine and the ducted fan is only that the airflow channel is not in complicated mechanical connection, the problem that the rotating speed of the large-ducted-ratio fan cannot be matched due to the fact that the diameter of the large-ducted-ratio fan is increased, the rotating speed is reduced and the rotating speed of the driving turbine is high can be solved, and a very complicated gear reduction box or a three-rotor structure is not needed; meanwhile, the air guide pipe is extremely small in limitation, and the air guide pipe can be arranged inside the fuselage and the wings according to the design requirements of the aircraft, so that the aircraft is more flexibly arranged.

2. According to the invention, through the action of the air inlet device, the rounding is arranged at the front end lip of the inlet of the air inlet device, the preset height is increased at the rear end lip of the inlet, the guide plate for inhibiting flow separation is arranged at the rear side of the inlet of the air inlet device, so that the flow and the quality of air sucked by the ducted fan are ensured, the thrust direction is controlled from-45 degrees to 45 degrees through the action of the adjusting mechanism, the flow separation can be effectively reduced under different airflow attack angles, the horizontal-to-vertical transition adjustment of the thrust of the engine can be conveniently realized, and the vertical take-off, the high-speed flat flight and the large-maneuvering flight of the aircraft are realized.

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 block diagram of the aircraft mounted air driven ducted fan propulsion power system of the present invention;

FIG. 2 is a schematic structural view of an air-driven ducted fan propulsion power system of the present invention;

FIG. 3 is a schematic structural view of a ducted fan of the present invention;

FIG. 4 is a structural assembly of the ducted fan of the present invention;

FIG. 5 is a schematic view of the adjustment mechanism of the present invention;

FIG. 6 is a schematic view of the structure of the air intake apparatus of the present invention;

reference numbers in the figures: 1. a core turbine; 2. a bleed pipe; 3. a ducted fan; 4. an air intake volute; 5. a fan blade; 6. a tip turbine; 7. a tip turbine blade; 8. a main exhaust guide vane; 9. an auxiliary exhaust guide vane; 10. a crank; 11. adjusting a rod; 12. rotating the disc; 13. blocking the leaf; 14. an air intake device; 15. a baffle.

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. 1-4, a jet propulsion power system of a gas-driven ducted fan comprises a core turbine 1, a ducted fan 3 connected with the core turbine 1 through an air-guiding pipe 2, and a blade tip turbine 6 coaxially installed with the ducted fan 3, wherein the core turbine 1 discharges high-energy gas and delivers the high-energy gas through the air-guiding pipe 2 which is freely arranged, wherein a throttle valve for adjusting the air flow is installed on the air-guiding pipe 2 to adjust the air flow entering the ducted fan 3, so as to adjust the thrust size of the ducted fan 3, the ducted fan 3 comprises an air-inlet volute 4 connected with the blade tip turbine 6 and a rotating shaft located at the center of the ducted fan 3, a plurality of fan blades 5 are evenly installed on the rotating shaft in the circumferential direction, the end of each fan blade 5 is connected with a blade tip turbine blade 7 connected with the blade tip turbine 6 and located at the inner ring of the turbine, and the gas enters the blade tip turbine 6 through the air-inlet 4, the blade tip turbine 6 does work on gas expansion, directly drives the blade tip turbine blades 7 and the fan blades 5 to rotate, as shown in fig. 6, the blade tip turbine is an independent air inlet device 14 and is installed on an airplane, an air inlet of the ducted fan 3 is connected with the air inlet device 14, air flow enters the ducted fan 3 through the air inlet device 14, wherein a front end lip of an inlet of the air inlet device 14 is subjected to rounding treatment, a preset height is increased at a rear end lip of the inlet, flow loss in front of the ducted fan 3 is reduced, a flow guide plate 15 for inhibiting flow separation is installed on the rear side of the inlet of the air inlet device 14, flow and mass of air sucked by the ducted fan 3 are ensured, the ducted fan 3 sucks a large amount of external low-temperature air flow through the air inlet device 14, the bypass ratio of an original turbofan engine is increased more than normal, oil consumption is generated and is several times of thrust of the original turbofan engine, and lower power output is obtained;

the core turbine 1 can adopt a turbofan engine form, so that the efficiency is high, the temperature and the speed of the discharged driving air are lower than those of a turbojet engine, the requirement on the temperature resistance of materials of the air guide pipe 2, the turbofan air inlet volute 4 and the blade tip turbine blade 7 can be lowered by the driving air with lower temperature, the heat dissipation loss in the conveying process can also be reduced, and the flow loss in the air guide pipe 2 and the air inlet volute 4 of the ducted fan 3 can be reduced by the driving air with lower speed;

as shown in fig. 3-5, a baffle blade 7 is movably installed at the exhaust port of the ducted fan 3, the exhaust direction is adjusted by adjusting the angle of the baffle blade 7, and an adjusting mechanism is arranged, the adjusting mechanism comprises a plurality of rows of guide vanes, each row of guide vanes comprises a main exhaust guide vane 8 and auxiliary exhaust guide vanes 9 which are symmetrically arranged at two sides of the main exhaust guide vane 8 respectively, one end of each row of guide vanes is provided with a rotating disc 12, the main exhaust guide vane 8 and the auxiliary exhaust guide vanes 9 are connected with the rotating disc 12, one side of the rotating disc 12 is provided with a crank 10, and the rotating disc 12 is rotatably connected with the crank 10 through the adjusting rod 11, along with the movement of the crank 10, the adjusting rod drives the rotating disc 12 to rotate, drives the main exhaust guide vane 8 and the auxiliary exhaust guide vane 9 to rotate, guides the airflow to be discharged in different directions, thereby changing the direction of the exhaust jet flow and realizing the continuous adjustment of the angle between the exhaust direction and the downward vertical direction of the aircraft from-45 degrees to 45 degrees;

the exhaust and propulsion directions are continuously adjusted from vertical to horizontal by driving the exhaust blades 8 and the auxiliary exhaust guide vanes 9 through an adjustable mechanism, when the exhaust direction is downward, the ducted fan 3 provides proper upward pulling force to realize vertical take-off of the aircraft, or supports the aircraft to maintain hovering by self weight, or provides enough support to keep the aircraft stably landing, because more than 95% of air exhausted by the ducted fan 3 comes from air which is not heated but is powered by the fan, the exhaust temperature is only slightly higher than the ambient atmosphere, the thermal shock to the field is almost zero when the aircraft vertically takes-off and lands, the requirement and the damage of the vertical take-off and landing aircraft to the field are obviously reduced, when the exhaust direction is close to backward, the exhaust reaction force generates forward thrust to push the aircraft to fly at high speed, and the energy is converted by using air drive at the cost of smaller weight and structure, the problem of big bypass ratio engine speed match is solved, with core machine thrust conversion adjustable thrust direction, the thrust of 3 thrust of the ducted fan of several times prokaryotic core machine, can realize the aircraft VTOL, propulsion power demands such as thrust diversion.

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

1. The utility model provides an air drive ducted fan jet propulsion power system which characterized in that: the bypass type air compressor comprises a core turbine, a bypass fan connected with the core turbine through an air guide pipe and a blade tip turbine coaxially installed with the bypass fan, wherein gas exhausted by the core turbine is transmitted to the blade tip turbine, the blade tip turbine expands to do work on the gas and drives the bypass fan to rotate to suck air to generate thrust, an air inlet device is arranged at an air inlet of the bypass fan, a radius is arranged at a front end lip of an inlet of the air inlet device, a preset height is increased at a rear end lip of the inlet, and a guide plate for inhibiting flow separation is installed on the rear side of the inlet of the air inlet device;

duct fan exhaust port department installs adjustment mechanism, and adjustment mechanism includes multirow stator, every row the stator includes that a slice main exhaust stator and symmetry are respectively at the supplementary stator of main exhaust stator both sides, every row the carousel is all installed to stator one end, main exhaust stator with supplementary stator all links to each other with the carousel, carousel one side is equipped with the crank, and the carousel rotates through adjusting the pole and is connected with the crank rotation, along with the crank activity, drives the carousel rotation through adjusting the pole, adjusts the angle of stator.

2. An air-driven ducted fan jet propulsion power system as claimed in claim 1, wherein: the ducted fan comprises an air inlet volute connected with a blade tip turbine and a rotating shaft located in the center of the ducted fan, a plurality of fan blades are uniformly installed in the circumferential direction of the rotating shaft, the end portion of each fan blade is connected with a blade tip turbine blade located at the inner ring of the turbine and connected with the blade tip turbine, and air enters the blade tip turbine through the air inlet volute and directly drives the blade tip turbine blade and the fan blade to rotate.

3. An air-driven ducted fan jet propulsion power system as claimed in claim 1, wherein: and a throttle valve for adjusting the air flow is arranged on the air guide pipe.

4. An air-driven ducted fan jet propulsion power system as claimed in claim 1, wherein: and a blocking blade for adjusting the exhaust direction is movably arranged at the exhaust port of the ducted fan.

5. An air-driven ducted fan jet propulsion power system as claimed in claim 1, wherein: the guide vane angle adjusting range is-45 degrees to 45 degrees.