阅读说明：本技术 新型桨扇发动机及具有其的推进装置 (Novel paddle fan engine and propulsion device with same ) 是由 黄兴 苏志敏 方权燊 葛严 于 2020-05-28 设计创作，主要内容包括：本发明公开了一种新型桨扇发动机及具有其的推进装置,包括燃气发生器、行星齿轮减速器及对转桨扇部件。燃气发生器包括动力涡轮和驱动转轴,燃气发生器用于将来流空气压缩后导入燃烧室燃烧,以产生高温高压燃气进而驱动动力涡轮旋转做功,驱动转轴与动力涡轮固定,以在动力涡轮的带动下旋转,驱动转轴的外伸端由燃气发生器的喷气端伸出。行星齿轮减速器的输入端与驱动转轴的外伸端固定,对转桨扇部件的输入端分别与行星齿轮减速器的两路输出相连,行星齿轮减速器用于分别驱使对转桨扇部件的前排桨和后排桨呈反向旋转以产生推力,且使前排桨的转速和后排桨的转速分别与动力涡轮的转速匹配。(The invention discloses a novel paddle fan engine and a propelling device with the same. The gas generator comprises a power turbine and a driving rotating shaft, the gas generator is used for compressing incoming flow air and guiding the compressed incoming flow air into a combustion chamber for combustion so as to generate high-temperature and high-pressure gas and further drive the power turbine to rotate to do work, the driving rotating shaft is fixed with the power turbine so as to rotate under the driving of the power turbine, and the extending end of the driving rotating shaft extends out of the air injection end of the gas generator. The input end of the planetary gear reducer is fixed with the extending end of the driving rotating shaft, the input end of the contra-rotating propeller fan component is respectively connected with two paths of outputs of the planetary gear reducer, the planetary gear reducer is used for respectively driving the front-row propeller and the rear-row propeller of the contra-rotating propeller fan component to rotate in opposite directions so as to generate thrust, and the rotating speed of the front-row propeller and the rotating speed of the rear-row propeller are respectively matched with the rotating speed of the power turbine.)

1. The novel paddle fan engine is characterized by comprising a fuel gas generator (10), a planetary gear reducer (20) and a contra-rotating paddle fan component (30);

the gas generator (10) comprises a power turbine (12) and a driving rotating shaft (11), the gas generator (10) is used for compressing flowing air and then guiding the flowing air into a combustion chamber (16) for combustion so as to generate high-temperature and high-pressure gas to drive the power turbine (12) to rotate and do work, the driving rotating shaft (11) is fixed with the power turbine (12) so as to rotate under the driving of the power turbine (12), and the extending end of the driving rotating shaft (11) extends out of the air injection end of the gas generator (10);

the input end of the planetary gear reducer (20) is fixed with the extending end of the driving rotating shaft (11), the input end of the contra-rotating propeller fan component (30) is connected with two outputs of the planetary gear reducer (20) respectively, the planetary gear reducer (20) is used for driving a front-row propeller (31) and a rear-row propeller (32) of the contra-rotating propeller fan component (30) to rotate reversely to generate thrust, and the rotating speed of the front-row propeller (31) and the rotating speed of the rear-row propeller (32) are matched with the rotating speed of the power turbine (12) respectively.

2. The new paddle fan engine of claim 1,

the fuel gas generator (10), the planetary gear reducer (20) and the contra-rotating propeller fan component (30) are sequentially arranged along the airflow flowing direction and are coaxially connected.

3. The new paddle fan engine of claim 1,

the gas generator (10) further comprises an outer casing (13), a low-pressure compressor (14), a high-pressure compressor (15), a combustion chamber (16) and a high-pressure gas turbine (17), wherein the low-pressure compressor (14), the high-pressure compressor (15), the combustion chamber and the high-pressure gas turbine are coaxially arranged in the outer casing (13);

the high-pressure compressor (15) and the high-pressure gas turbine (17) are respectively arranged at the air inlet end and the air outlet end of the combustion chamber (16), and the high-pressure compressor (15) and the high-pressure gas turbine (17) are connected through a high-pressure rotor shaft (18) penetrating through the combustion chamber (16);

the low-pressure compressor (14) and the power turbine (12) are respectively arranged at the air inlet end and the air outlet end of the combustion chamber (16), and the low-pressure compressor (14) and the power turbine (12) are positioned at the outer side of a connecting body formed by the high-pressure compressor (15) and the high-pressure gas turbine (17);

the driving rotating shaft (11) is arranged in the high-pressure rotor shaft (18) along the axial direction of the high-pressure rotor shaft (18), the mounting end of the driving rotating shaft (11) extends out of the high-pressure rotor shaft (18) and then is fixed with the low-pressure compressor (14), and the extending end of the driving rotating shaft (11) extends out of the high-pressure rotor shaft (18) and then penetrates through the power turbine (12) and extends out of the air injection end of the gas generator (10).

4. The new paddle fan engine of claim 1,

the gas generator (10) further comprises an outer casing (13), a low-pressure gas compressor (14), a high-pressure gas compressor (15), a combustion chamber (16), a high-pressure gas turbine (17) and a low-pressure gas turbine, wherein the low-pressure gas compressor (14), the high-pressure gas compressor (15), the combustion chamber (16) and the low-pressure gas turbine are coaxially arranged in the outer casing (13);

the high-pressure compressor (15) and the high-pressure gas turbine (17) are respectively arranged at the air inlet end and the air outlet end of the combustion chamber (16), and the high-pressure compressor (15) and the high-pressure gas turbine (17) are connected through a high-pressure rotor shaft (18) penetrating through the combustion chamber (16);

the low-pressure compressor (14) and the low-pressure gas turbine are respectively arranged at the air inlet end and the air outlet end of the combustion chamber (16), the low-pressure compressor (14) and the low-pressure gas turbine are positioned at the outer side of a connecting body formed by the high-pressure compressor (15) and the high-pressure gas turbine (17), and the low-pressure compressor (14) and the low-pressure gas turbine are connected through a low-pressure rotor shaft penetrating through the high-pressure rotor shaft (18);

the power turbine (12) is arranged at the downstream of the low-pressure gas turbine, the mounting end of the driving rotating shaft (11) is fixed with the power turbine (12), and the extending end of the driving rotating shaft (11) extends out of the air injection end of the gas generator (10).

5. The new paddle fan engine of any of claims 3 or 4,

the planetary gear reducer (20) comprises a sun gear (21) fixed with the extending end of the driving rotating shaft (11), an inner gear ring (22) sleeved outside the sun gear (21), a plurality of planet gears (23) uniformly distributed between the inner gear ring (22) and the sun gear (21) at intervals, and a planet carrier (24) respectively connected with the planet gears (23);

the planetary wheels (23) are respectively externally meshed with the sun wheel (21) so as to revolve around the sun wheel (21) and rotate around the axis of the planetary wheels under the driving of the sun wheel (21);

the planet carrier (24) is driven by a plurality of planet wheels (23) to rotate around the axis of the sun wheel (21), and the rotation direction of the planet carrier (24) and the revolution direction of the planet wheels (23) are the same as the rotation direction of the sun wheel (21);

the inner gear ring (22) is respectively internally meshed with the planet wheels (23) to rotate around the axis of the sun wheel (21) under the driving of the planet wheels (23), and the rotating direction of the inner gear ring (22) is opposite to that of the sun wheel (21);

the contra-rotating propeller fan component (30) is respectively connected with the planet carrier (24) and the inner gear ring (22) so as to enable the front-row propeller (31) and the rear-row propeller (32) to rotate in the opposite direction under the driving of the planet carrier (24) and the inner gear ring (22).

6. The new paddle fan engine of claim 5,

the planet carrier (24) comprises a connecting plate (241) and a plurality of struts (242);

the struts (242) and the planet wheels (23) are arranged in a one-to-one correspondence mode, one end of each strut (242) is fixed to a first fixing surface, facing the sun wheel (21), of the connecting plate (241), and the other end of each strut (242) is rotatably mounted on the corresponding planet wheel (23).

7. The new paddle fan engine of claim 6,

the contra-rotating propeller fan component (30) further comprises a mounting shaft (33) which is coaxially arranged with the planet carrier (24) and is fixedly connected with the planet carrier, and a front propeller mounting cylinder (34) which is sleeved on the excircle of the mounting shaft (33), wherein the front propeller mounting cylinder (34) is fixedly connected with the inner gear ring (22);

a plurality of front-row blades of the front-row paddle (31) are uniformly distributed at intervals along the circumferential direction of the front-row paddle mounting cylinder (34), and the front-row blades are respectively fixedly connected with the outer circumferential wall of the front-row paddle mounting cylinder (34);

the rear row of paddles (32) are located at the downstream of the front row of paddles (31), a plurality of rear row of paddles of the rear row of paddles (32) are arranged along the circumferential direction of the mounting shaft (33) at uniform intervals, and the rear row of paddles are respectively fixedly connected with the peripheral wall of the mounting shaft (33).

8. The new paddle fan engine of claim 7,

the mounting shaft (33) is in a hollow shaft cylinder shape, a first end, close to the planet carrier (24), of the mounting shaft (33) is fixed to a second fixing surface, back to the sun gear (21), of the connecting plate (241), and an annular limiting flange (330) protruding outwards is arranged on the outer circle of the mounting shaft (33);

the front propeller mounting cylinder (34) and the rear row propeller (32) are respectively arranged on two sides of the limiting flange (330), and the end surface of the front propeller mounting cylinder (34) is fixed with the rear end surface, far away from the gas generator (10), of the inner gear ring (22).

9. The new paddle fan engine of claim 8,

contra-rotating propeller fan part (30) still including being coniform fairing cone (35), the big end of fairing cone (35) is fixed install in on the excircle of installation axle (33) second end, just back row oar (32) are located limit flange (330) with between fairing cone (35).

10. A propulsion device, characterised in that it comprises a new paddle fan engine according to any of claims 1-9.

Technical Field

The invention relates to the field of aircraft engines, in particular to a novel paddle fan engine. In addition, the invention also relates to a propulsion device comprising the novel paddle fan engine.

Background

The turbine engine is the main power of the modern aircraft, mainly can be divided into four types of turbojet engines, turbofan engines, turboshaft engines and turboprop engines, and is mainly used for passenger planes, transport planes, fighters, cruise missiles and the like. The paddle fan engine is a new type of turbine engine, has the characteristics of both turbofan engine and turboprop engine, and is characterized in that the paddle fan component is composed of two rows of concentric contra-rotating paddles. This engine can be considered as a turbofan engine without a nacelle, and its blades and fans are very different from the conventional turboprop engine. The paddle fan engine has the capability of flying at a high subsonic speed (Ma0.75-0.9), can save 20-30% of oil compared with the existing civil turbofan engine, and is an important power type of the future civil passenger plane.

Paddle fan engines currently include two types, one being free-turbine direct drive and one being gear driven, where the difference between the two is mainly reflected in the difference in the direct power transmission driving the paddle fan components. The representative of the turbine direct-drive paddle fan engine is GE36 engine of GE company in America, which drives contra-rotating propellers through two sets of contra-rotating free turbine systems, but because the speed of the propellers is slow, the rotating speed of the turbine is reduced, the work capability is reduced, the size is increased, more than ten stages of free turbines are required to be equipped, and therefore, the quality of the engine is greatly improved.

The gear driving type propeller fan engine is represented by a 578DX engine of an Allison company in America, the front row and the rear row of propellers of the engine are respectively driven by an inner gear ring of a planetary gear reducer and a planet carrier so as to realize contra-rotating, and the gear driving type propeller fan engine has the advantages that the equal relation between the rotating speed of a free turbine and the rotating speed of a propeller is broken, so that the free turbine and the propeller can work in high-efficiency rotating speeds, but the gear reducer and other components are still added, the weight is greatly increased, exhaust gas in the engine can only be exhausted from the bottom of the propeller, and the operation of. Although the two structural layouts are different in nature, the two layouts adopt a free turbine part only used for driving the paddle fan part, and particularly, the free turbine direct-drive paddle fan engine comprises more than ten stages of free turbines, so that the engine structure is redundant and complicated.

The invention patent of publication No. CN105980248A proposes a new structure for the paddle fan component of the paddle fan engine (as shown in fig. 1 of the accompanying drawings), but it does not change the overall structural layout of the paddle fan engine, and is only an innovative design for the existing components of the paddle fan engine. The invention patent of publication No. CN 106560606a proposes a new paddle fan engine (as shown in fig. 2), but the basic structure composition of the paddle fan engine is completely different from that of the paddle fan engine, and the paddle fan engine is classified into a contra-rotating compressor turboprop engine according to the classification of the aircraft engine. The invention patent of publication No. CN 109131832a proposes a new blade profile and its arrangement (as shown in fig. 3 of the accompanying drawings), but still does not change the overall structural layout of the blade engine.

The existing paddle fan engines have the following problems due to the fact that the operating rotating speeds of the paddle fan component and the free turbine component are not coordinated: (1) the free turbine part is adopted in both the gear driven type paddle fan engine and the free turbine driven type paddle fan engine, so that the engine is complex in structure, large in mass and long in size; (2) the longer size and the greater mass also result in greater limitations in the installation of the propeller fan engine on the propulsion device.

Disclosure of Invention

The invention provides a novel paddle fan engine and a propelling device with the same, and aims to solve the technical problems that an existing paddle fan engine is complex in structure and heavy in weight.

The technical scheme adopted by the invention is as follows:

a novel paddle fan engine comprises a fuel gas generator, a planetary gear reducer and a contra-rotating paddle fan component; the gas generator comprises a power turbine and a driving rotating shaft, the gas generator is used for compressing incoming flow air and guiding the compressed incoming flow air into a combustion chamber for combustion so as to generate high-temperature and high-pressure gas and further drive the power turbine to rotate to do work, the driving rotating shaft is fixed with the power turbine so as to rotate under the driving of the power turbine, and the extending end of the driving rotating shaft extends out of the air injection end of the gas generator; the input end of the planetary gear reducer is fixed with the extending end of the driving rotating shaft, the input end of the contra-rotating propeller fan component is respectively connected with two paths of outputs of the planetary gear reducer, the planetary gear reducer is used for respectively driving the front-row propeller and the rear-row propeller of the contra-rotating propeller fan component to rotate in opposite directions so as to generate thrust, and the rotating speed of the front-row propeller and the rotating speed of the rear-row propeller are respectively matched with the rotating speed of the power turbine.

Furthermore, the fuel gas generator, the planetary gear reducer and the contra-rotating propeller fan component are sequentially arranged along the airflow flowing direction and are coaxially connected.

Further, the gas generator also comprises an outer casing, a low-pressure gas compressor, a high-pressure gas compressor, a combustion chamber and a high-pressure gas turbine which are coaxially arranged in the outer casing; the high-pressure compressor and the high-pressure gas turbine are respectively arranged at the air inlet end and the air outlet end of the combustion chamber and are connected through a high-pressure rotor shaft penetrating through the combustion chamber; the low-pressure compressor and the power turbine are respectively arranged at the air inlet end and the air outlet end of the combustion chamber and are positioned at the outer side of a connecting body formed by the high-pressure compressor and the high-pressure gas turbine; the driving rotating shaft is arranged in the high-pressure rotor shaft along the axial direction of the high-pressure rotor shaft, the mounting end of the driving rotating shaft extends out of the high-pressure rotor shaft and then is fixed with the low-pressure compressor, and the extending end of the driving rotating shaft extends out of the high-pressure rotor shaft and then penetrates through the power turbine and extends out of the air injection end of the gas generator.

Further, the gas generator also comprises an outer casing, a low-pressure gas compressor, a high-pressure gas compressor, a combustion chamber, a high-pressure gas turbine and a low-pressure gas turbine which are coaxially arranged in the outer casing; the high-pressure compressor and the high-pressure gas turbine are respectively arranged at the air inlet end and the air outlet end of the combustion chamber and are connected through a high-pressure rotor shaft penetrating through the combustion chamber; the low-pressure compressor and the low-pressure gas turbine are respectively arranged at the air inlet end and the air outlet end of the combustion chamber, are positioned at the outer side of a connecting body formed by the high-pressure compressor and the high-pressure gas turbine, and are connected through a low-pressure rotor shaft penetrating through the high-pressure rotor shaft; the power turbine is arranged at the downstream of the low-pressure gas turbine, the mounting end of the driving rotating shaft is fixed with the power turbine, and the extending end of the driving rotating shaft extends out of the air injection end of the gas generator.

Furthermore, the planetary gear reducer comprises a sun gear fixed with the extending end of the driving rotating shaft, an inner gear ring sleeved outside the sun gear, a plurality of planet gears uniformly distributed between the inner gear ring and the sun gear at intervals, and a planet carrier respectively connected with the planet gears; the planetary wheels are respectively externally meshed with the sun wheel so as to revolve around the sun wheel and rotate around the axis of the planetary wheels under the driving of the sun wheel; the planet carrier is driven by the planet wheels to rotate around the axis of the sun wheel, and the rotation direction of the planet carrier and the revolution direction of the planet wheels are the same as the rotation direction of the sun wheel; the inner gear ring is respectively internally meshed with the planet wheels to rotate around the axis of the sun wheel under the driving of the planet wheels, and the rotating direction of the inner gear ring is opposite to that of the sun wheel; the contra-rotating propeller fan part is respectively connected with the planet carrier and the inner gear ring so as to enable the front row of propellers and the rear row of propellers to rotate reversely under the driving of the planet carrier and the inner gear ring.

Further, the planet carrier comprises a connecting plate and a plurality of struts; the pillars are arranged in one-to-one correspondence with the planet wheels, one end of each pillar is fixed to the first fixing face, facing the sun wheel, of the connecting plate, and the other end of each pillar is rotatably mounted on the corresponding planet wheel.

Furthermore, the contra-rotating propeller fan component also comprises an installation shaft which is coaxially arranged with the planet carrier and is fixedly connected with the planet carrier, and a front propeller installation cylinder which is sleeved on the excircle of the installation shaft, wherein the front propeller installation cylinder is fixedly connected with the inner gear ring; a plurality of front-row blades of the front-row paddle are uniformly distributed at intervals along the circumferential direction of the front-paddle mounting cylinder, and the front-row blades are respectively fixedly connected with the outer circumferential wall of the front-paddle mounting cylinder; the back row oar is located the low reaches of front row oar, and the even interval of the circumference along the installation axle of the multi-disc back row oar leaf of back row oar arranges to back row oar leaf respectively with the periphery wall fixed connection of installation axle.

Furthermore, the mounting shaft is in the shape of a hollow shaft cylinder, a first end, close to the planet carrier, on the mounting shaft is fixed with a second fixing surface, back to the sun gear, on the connecting plate, and an annular limiting flange which protrudes outwards is arranged on the excircle of the mounting shaft; the front paddle mounting cylinder and the rear row of paddles are respectively arranged on two sides of the limiting flange, and the end face of the front paddle mounting cylinder is fixed with the rear end face, far away from the fuel gas generator, of the inner gear ring.

Furthermore, to rotating oar fan part still including being coniform fairing cone, the big end of fairing cone is fixed to be installed on the excircle of installation axle second end, and the back row oar is located between limit flange and the fairing cone.

According to another aspect of the present invention there is also provided a propulsion device including a novel paddle fan engine as defined in any one of the above.

The invention has the following beneficial effects:

the structural layout of the novel paddle fan engine is different from a gear driven paddle fan engine and a free turbine driven paddle fan engine, the free turbine structure only used for driving a paddle fan component or a multi-stage contra-rotating free turbine structure and an accessory structure thereof are removed from the structural layout of the paddle fan engine, and the power turbine is connected with the contra-rotating paddle fan component through a planetary gear reducer through the reasonable layout design of the power turbine, so that the components in the paddle fan engine are reduced, the dead weight of the free turbine or the multi-stage contra-rotating free turbine is saved, the structural complexity of the paddle fan engine is reduced, the installation adaptability of the paddle fan engine on a propelling device is improved, meanwhile, the coordinated work of the engine turbine component and the paddle fan component is also ensured, and the excellent performance of the paddle fan engine is further ensured;

compared with the existing propelling device, the propelling device provided by the invention has the advantages that the components in the paddle fan engine are reduced, the dead weight of a free turbine or a multi-stage contra-rotating free turbine is saved, the structural complexity of the paddle fan engine is reduced, the installation adaptability of the paddle fan engine on the propelling device is improved, the coordinated operation of the turbine component and the paddle fan component of the engine is ensured, and the excellent performance of the propelling device is further ensured.

In addition to the objects, features and advantages described above, other objects, features and advantages of the present invention are also provided. The present invention will be described in further detail below with reference to the drawings.

Drawings

The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:

FIG. 1 is a structural drawing of a paddle fan engine disclosed in the patent (CN 105980248A);

FIG. 2 is a structural drawing of a paddle fan engine disclosed in the patent (CN 106560606A);

FIG. 3 is a structural drawing of the paddle fan engine disclosed in the patent (109131832A);

FIG. 4 is a schematic block diagram of the configuration of the novel paddle fan engine of the preferred embodiment of the present invention;

FIG. 5 is a schematic view of the gasifier of FIG. 4;

FIG. 6 is a schematic illustration of the planetary gear reducer and counter-rotating fan assembly installation of FIG. 4.

Description of the figures

10. A gas generator; 11. driving the rotating shaft; 12. a power turbine; 13. an outer case; 14. a low pressure compressor; 15. a high pressure compressor; 16. a combustion chamber; 17. a high pressure gas turbine; 18. a high-pressure rotor shaft; 20. a planetary gear reducer; 21. a sun gear; 22. an inner gear ring; 23. a planet wheel; 24. a planet carrier; 241. a connecting plate; 242. a pillar; 30. a contra-rotating propeller fan component; 31. a front row of paddles; 32. rear row of paddles; 33. installing a shaft; 330. a limiting flange; 34. a front paddle mounting cylinder; 35. a rectifying cone.

Detailed Description

The embodiments of the invention will be described in detail below with reference to the accompanying drawings, but the invention can be embodied in many different forms, which are defined and covered by the following description.

Referring to fig. 4 to 6, the preferred embodiment of the present invention provides a novel paddle fan engine including a gas generator 10, a planetary gear reducer 20, and a counter-rotating paddle fan unit 30. The gas generator 10 comprises a power turbine 12 and a driving shaft 11, the gas generator 10 is used for compressing incoming air and guiding the compressed incoming air into a combustion chamber 16 for combustion so as to generate high-temperature and high-pressure gas and further drive the power turbine 12 to rotate and do work, the driving shaft 11 is fixed with the power turbine 12 so as to rotate under the driving of the power turbine 12, and the extending end of the driving shaft 11 extends out of the air injection end of the gas generator 10. The input end of the planetary gear reducer 20 is fixed to the outward extending end of the driving shaft 11, the input end of the counter-rotating fan component 30 is connected to two outputs of the planetary gear reducer 20, and the planetary gear reducer 20 is used for driving the front row of paddles 31 and the rear row of paddles 32 of the counter-rotating fan component 30 to rotate in opposite directions to generate thrust, and the rotating speed of the front row of paddles 31 and the rotating speed of the rear row of paddles 32 are matched with the rotating speed of the power turbine 12.

When the novel paddle fan engine works, firstly, the gas generator 10 compresses the incoming flow and guides the incoming flow into the combustion chamber 16 to be combusted with fuel oil to generate high-temperature and high-pressure gas, the high-temperature and high-pressure gas drives the power turbine 12 to rotate and do work, the power turbine 12 drives the driving rotating shaft 11 to rotate, the input end of the planetary gear reducer 20 is fixed with the extending end of the driving rotating shaft 11, thereby driving the rotating shaft 11 to drive the planetary gear reducer 20 to act, and the front row paddle 31 and the rear row paddle 32 of the contra-rotating paddle sector component 30 are respectively connected with two paths of outputs of the planetary gear reducer 20, further, under the action of the planetary gear reducer 20, the front row of paddles 31 and the rear row of paddles 32 rotate in opposite directions to generate thrust, and the rotating speed of the front row of paddles 31 and the rotating speed of the rear row of paddles 32 are respectively matched with the rotating speed of the power turbine 12 under the action of the planetary gear reducer 20, thereby allowing both the gasifier 10 and the counter-rotating fan section 30 to operate in their high efficiency speed regions.

The structural layout of the novel paddle fan engine is different from a gear driven paddle fan engine and a free turbine driven paddle fan engine, the free turbine structure only used for driving a paddle fan component or a multi-stage contra-rotating free turbine structure and an accessory structure thereof are removed from the structural layout of the paddle fan engine, and the power turbine 12 and the contra-rotating paddle fan component 30 are connected through a planetary gear reducer 20 through the reasonable layout design of the power turbine 12, so that the components in the paddle fan engine are reduced, the dead weight of the free turbine or the multi-stage contra-rotating free turbine is saved, the structural complexity of the paddle fan engine is reduced, the installation adaptability of the paddle fan engine on a propelling device is improved, the coordinated work of the turbine component and the paddle fan component of the engine is also ensured, and the excellent performance of the paddle fan engine is further ensured.

Preferably, as shown in fig. 4, the gas generator 10, the planetary gear reducer 20, and the counter-rotating fan unit 30 are sequentially arranged in the flow direction of the gas flow and coaxially connected. The structure layout of the novel paddle fan engine shortens the axial length of the paddle fan engine, enables the structure of the paddle fan engine to be compact, and simultaneously ensures the coordinated work of the turbine part and the paddle fan part of the engine.

Alternatively, in a first embodiment of the gas generator 10, as shown in fig. 5, the gas generator 10 further comprises an outer casing 13, a low pressure compressor 14, a high pressure compressor 15, a combustor 16, a high pressure gas turbine 17 and a power turbine 12 coaxially arranged within the outer casing 13. The high-pressure compressor 15 and the high-pressure gas turbine 17 are respectively arranged at the air inlet end and the air outlet end of the combustion chamber 16, and the high-pressure compressor 15 and the high-pressure gas turbine 17 are connected through a high-pressure rotor shaft 18 penetrating through the combustion chamber 16. The low-pressure compressor 14 and the power turbine 12 are respectively arranged at the air inlet end and the air outlet end of the combustion chamber 16, and the low-pressure compressor 14 and the power turbine 12 are positioned at the outer side of a connecting body formed by the high-pressure compressor 15 and the high-pressure gas turbine 17. The driving shaft 11 is disposed in the high-pressure rotor shaft 18 along the axial direction of the high-pressure rotor shaft 18, and the mounting end of the driving shaft 11 extends out of the high-pressure rotor shaft 18 and then is fixed to the low-pressure compressor 14, and the extending end of the driving shaft 11 extends out of the high-pressure rotor shaft 18 and then passes through the power turbine 12 and extends out of the gas injection end of the gas generator 10. The gas generator 10 of the present invention operates on the following principle: incoming air firstly enters from the air inlet end of the gas generator 10, then under the action of the low-pressure compressor 14 and the high-pressure compressor 15, the incoming air is compressed and enters the combustion chamber 16, the incoming air compressed in the combustion chamber 16 is mixed with gas and then combusted to generate high-temperature high-pressure gas, when the high-temperature high-pressure gas is sprayed out from the air outlet end of the gas generator 10, the high-pressure gas turbine 17 and the power turbine 12 are driven to do work in a rotating manner, when the high-pressure gas turbine 17 does work in a rotating manner, the high-pressure compressor 15 is driven to act through the high-pressure rotor shaft 18 to compress the incoming air, when the power turbine 12 does work in a rotating manner, the low-pressure compressor 14 is driven to act through the driving rotating shaft 11 to compress the incoming air, and simultaneously.

Alternatively, in a second embodiment of the gas generator 10, not shown, the gas generator 10 further comprises an outer casing 13, a low-pressure compressor 14, a high-pressure compressor 15, a combustion chamber 16, a high-pressure gas turbine 17, a low-pressure gas turbine and a power turbine 12, which are coaxially arranged within the outer casing 13. The high-pressure compressor 15 and the high-pressure gas turbine 17 are respectively arranged at the air inlet end and the air outlet end of the combustion chamber 16, and the high-pressure compressor 15 and the high-pressure gas turbine 17 are connected through a high-pressure rotor shaft 18 penetrating through the combustion chamber 16. The low-pressure compressor 14 and the low-pressure gas turbine are respectively arranged at the air inlet end and the air outlet end of the combustion chamber 16, the low-pressure compressor 14 and the low-pressure gas turbine are positioned at the outer side of a connecting body formed by the high-pressure compressor 15 and the high-pressure gas turbine 17, and the low-pressure compressor 14 and the low-pressure gas turbine are connected through a low-pressure rotor shaft penetrating through a high-pressure rotor shaft 18. The power turbine 12 is arranged downstream of the low-pressure gas turbine, and the mounting end of the drive shaft 11 is fixed to the power turbine 12, and the overhanging end of the drive shaft 11 extends out of the gas injection end of the gas generator 10. The gas generator 10 of the present invention operates on the following principle: incoming air firstly enters from the air inlet end of the gas generator 10, then under the action of the low-pressure gas compressor 14 and the high-pressure gas compressor 15, the incoming air is compressed and enters the combustion chamber 16, the incoming air and the gas compressed in the combustion chamber 16 are mixed and then combusted to generate high-temperature high-pressure gas, when the high-temperature high-pressure gas is sprayed out from the air outlet end of the gas generator 10, the high-pressure gas turbine 17, the low-pressure gas turbine and the power turbine 12 are driven to respectively rotate to do work, when the high-pressure gas turbine 17 rotates to do work, the high-pressure gas compressor 15 is driven to act through the high-pressure rotor shaft 18 to compress the incoming air, when the low-pressure gas turbine rotates to do work, the low-pressure gas compressor 14 is driven to act through the low-pressure rotor shaft to compress the incoming air, and when the power turbine 12.

Alternatively, as shown in fig. 6, the planetary gear reducer 20 includes a sun gear 21 fixed to the outer end of the drive shaft 11, an inner gear 22 fitted around the sun gear 21, a plurality of planetary gears 23 arranged at regular intervals between the inner gear 22 and the sun gear 21, and a carrier 24 connected to each of the plurality of planetary gears 23. The plurality of planetary gears 23 are externally engaged with the sun gear 21, respectively, to revolve around the sun gear 21 while rotating on their own axes under the drive of the sun gear 21. The planet carrier 24 is driven by the plurality of planet wheels 23 to rotate around the axis of the sun wheel 21, and the rotation direction of the planet carrier 24 and the revolution direction of the planet wheels 23 are the same as the rotation direction of the sun wheel 21. The ring gear 22 is internally meshed with the plurality of planetary gears 23, respectively, to rotate around the axis of the sun gear 21 under the drive of the plurality of planetary gears 23, and the rotation direction of the ring gear 22 is opposite to the rotation direction of the sun gear 21. The contra-rotating propeller fan assembly 30 is connected with the planet carrier 24 and the ring gear 22 respectively to make the front row of propellers 31 and the rear row of propellers 32 rotate reversely under the driving of the planet carrier 24 and the ring gear 22. The operating principle of the planetary gear reducer 20 of the present invention is: the driving rotating shaft 11 drives the sun gear 21 to rotate, the sun gear 21 drives the plurality of planet gears 23 to synchronously revolve around the sun gear 21 and simultaneously rotate around the axes of the sun gear 21, the plurality of planet gears 23 further drive the planet carrier 24 to rotate around the axes of the sun gear 21, the revolving directions of the planet carrier 24 and the planet gears 23 are the same as the rotating direction of the sun gear 21, the plurality of planet gears 23 further drive the inner gear ring 22 to rotate, the rotating direction of the inner gear ring 22 is opposite to the rotating direction of the sun gear 21, and then the inner gear ring 22 and the planet carrier 24 drive the contra-rotating propeller part 30 to act, so that the front row propeller 31 and the rear row propeller 32 respectively rotate in opposite directions under the action of the inner gear ring 22 and.

In this alternative, sun gear 21 and planet wheel 23 are cylindrical gear, and planet wheel 23 can have a plurality ofly, generally 3 ~ 4.

Further, as shown in fig. 6, the carrier 24 includes a connecting plate 241 and a plurality of struts 242. The plurality of struts 242 are respectively arranged in one-to-one correspondence with the plurality of planetary gears 23, one end of each strut 242 is fixed to the first fixing surface of the connecting plate 241 facing the sun gear 21, the other end of each strut 242 is rotatably mounted on the corresponding planetary gear 23, and therefore the planetary gear 23 revolves around the sun gear 21 and rotates around the axis of the planetary gear 23, and the planetary gear 23 drives the planetary carrier 24 to rotate around the axis of the sun gear 21 when acting.

Optionally, as shown in fig. 6, the contra-rotating propeller fan component 30 further includes a mounting shaft 33 coaxially arranged with the planet carrier 24 and fixedly connected thereto, and a front propeller mounting cylinder 34 sleeved on an outer circle of the mounting shaft 33, and the front propeller mounting cylinder 34 is fixedly connected with the inner gear ring 22. The front-row paddle 31 comprises a plurality of front-row blades, the plurality of front-row blades of the front-row paddle 31 are uniformly distributed at intervals along the circumferential direction of the front-row paddle mounting cylinder 34, and the front-row blades are respectively fixedly connected with the outer circumferential wall of the front-row paddle mounting cylinder 34. The rear row of paddles 32 comprises a plurality of rear row of paddles, the rear row of paddles 32 is located at the downstream of the front row of paddles 31, the plurality of rear row of paddles of the rear row of paddles 32 are uniformly arranged at intervals along the circumferential direction of the mounting shaft 33, and the rear row of paddles are respectively and fixedly connected with the outer circumferential wall of the mounting shaft 33.

Further, as shown in fig. 6, the mounting shaft 33 is formed in a hollow cylindrical shape, the weight of the engine is reduced, a first end of the mounting shaft 33 close to the carrier 24 is fixed to a second fixing surface of the connecting plate 241 facing away from the sun gear 21, and an outer circumference of the mounting shaft 33 is provided with a ring-shaped stopper flange 330 protruding outward. The front paddle mounting cylinder 34 and the rear paddle 32 are respectively arranged on two sides of the limiting flange 330, and the end surface of the front paddle mounting cylinder 34 is fixed with the rear end surface of the inner gear ring 22 far away from the gas generator 10. The limiting flange 330 is used for limiting the rear row of paddles 32 and the front paddle mounting cylinder 34 along the axial direction of the mounting shaft 33. The operating principle of the contra-rotating propeller fan part 30 of the present invention is as follows: the end face of the sun gear 21 is concentrically and fixedly connected with the driving rotating shaft 11, so that the gas generator 10 is fixedly connected with the planetary gear reducer 20, the annular end face of the inner gear ring 22 far away from the gas generator 10 is fixedly connected with the front end face of the front paddle mounting cylinder 34, so that the front paddle mounting cylinder 34 can rotate along with the inner gear ring 22, the annular end face of the mounting shaft 33 close to the front row paddle 31 is concentrically and fixedly connected with the first fixing face of the connecting plate 241 of the planet carrier 24, so that the rear row paddle 32 can rotate along with the planet carrier 24, and the connection of the planetary gear reducer 20 and the counter-rotating paddle fan component 30 is realized.

Optionally, as shown in fig. 6, the counter-rotating fan assembly 30 further includes a cone-shaped fairing cone 35, the large end of the fairing cone 35 is fixedly mounted on the outer circle of the second end of the mounting shaft 33, and the rear row of blades 32 are located between the limiting flange 330 and the fairing cone 35. Specifically, as shown in fig. 6, the large end of the fairing cone 35 is provided with an inward concave groove, the fairing cone 35 is installed on the outer circle of the second end of the installation shaft 33 through the concave groove and is located behind the rear row of paddles 32, the fairing cone 35 is used for rectifying the exhaust airflow, and the front row of paddles 31, the limiting flange 330, the rear row of paddles 32 and the fairing cone 35 form a smooth gas flow passage.

Alternatively, a preferred embodiment of the present invention provides a propulsion device comprising a novel paddle fan engine as defined in any one of the above. Compared with the existing propelling device, the propelling device provided by the invention has the advantages that the parts in the propeller fan engine are reduced, the dead weight of a free turbine or a multi-stage contra-rotating free turbine is saved, the structural complexity of the propeller fan engine is reduced, the installation adaptability of the propeller fan engine on the propelling device is improved, the coordinated operation of the turbine part of the engine and the propeller fan part is ensured, and the excellent performance of the propelling device is further ensured.

The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. 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.