CN113958423B

CN113958423B - Bypass ratio adjustable fan for hybrid pure electric aircraft and aero-engine

Info

Publication number: CN113958423B
Application number: CN202111222095.8A
Authority: CN
Inventors: 姚轩宇; 蒋承志; 满运堃; 王爱峰; 温泉
Original assignee: China Aero Engine Research Institute
Current assignee: China Aero Engine Research Institute
Priority date: 2021-10-20
Filing date: 2021-10-20
Publication date: 2022-11-22
Anticipated expiration: 2041-10-20
Also published as: CN113958423A

Abstract

The present disclosure provides an adjustable bypass ratio fan for mixing pure electric aircraft and an aero-engine having the adjustable bypass ratio fan, the adjustable bypass ratio fan includes: the inner ducted fan and the outer ducted fan are sleeved outside the inner ducted fan; the inner duct fan comprises an annular inner duct stator, an inner duct rotor arranged in the inner duct stator and a first magnetic suspension structure arranged between the inner duct stator and the inner duct rotor; the inner culvert rotor is arranged in the inner culvert stator in a suspended manner through a first magnetic suspension structure and is arranged in a rotating manner; the outer ducted fan comprises an outer ducted rotor sleeved outside the inner ducted stator in a sleeved mode, an outer ducted stator sleeved outside the outer ducted rotor in a sleeved mode, and a second magnetic suspension structure arranged between the outer ducted stator and the outer ducted rotor; the outer duct rotor is arranged between the outer duct stator and the inner duct stator in a suspended mode through a second magnetic suspension structure and is arranged in a rotating mode.

Description

Bypass ratio adjustable fan for hybrid pure electric aircraft and aero-engine

Technical Field

The utility model relates to an aeroengine technical field especially relates to an adjustable bypass ratio fan and aeroengine for mixing pure electric vehicles.

Background

The bypass ratio of the traditional engine is fixed and cannot be adjusted according to the real-time working state of the engine, so that the output efficiency of the engine is limited. Therefore, it is necessary to provide an aircraft engine with an adjustable bypass ratio to select different modes to fly at different bypass ratios according to actual conditions, so as to improve the efficiency of the aircraft engine.

Disclosure of Invention

To address at least one of the above technical problems, the present disclosure provides an adjustable bypass ratio fan and an aero-engine for a hybrid electric aircraft.

According to one aspect of the present disclosure, an adjustable bypass ratio fan for a hybrid electric aircraft comprises: the fan comprises an inner ducted fan and an outer ducted fan sleeved outside the inner ducted fan;

the inner duct fan comprises an annular inner duct stator, an inner duct rotor arranged in the inner duct stator and a first magnetic suspension structure arranged between the inner duct stator and the inner duct rotor; the inner culvert rotor is arranged in the inner culvert stator in a suspended manner through a first magnetic suspension structure and is arranged in a rotating manner;

the outer ducted fan comprises an outer ducted rotor sleeved outside the inner ducted stator in a sleeved mode, an outer ducted stator sleeved outside the outer ducted rotor in a sleeved mode, and a second magnetic suspension structure arranged between the outer ducted stator and the outer ducted rotor; the outer duct rotor is arranged between the outer duct stator and the inner duct stator in a suspended mode through a second magnetic suspension structure and is arranged in a rotating mode.

According to at least one embodiment of the present disclosure, at least one end of the inner duct rotor is provided with a guide vane for rectification, and the guide vanes at both ends of the inner duct rotor are both fixedly disposed relative to the inner duct stator.

According to at least one embodiment of the present disclosure, further comprising: the fan ferrule is sleeved outside the inner culvert stator in a sleeving manner; the fan ferrule is fixedly connected with the inner culvert stator; the outer duct rotor ring is sleeved outside the fan ferrule and is arranged in a rotating mode relative to the fan ferrule.

According to at least one embodiment of the present disclosure, the bypass rotor includes a rotor inner ring annularly sleeved outside the fan collar and a plurality of blades uniformly distributed on an outer circumferential surface of the rotor inner ring along a circumferential direction; the inner ring of the rotor is rotationally arranged relative to the fan ferrule; at least one end edge of the fan ferrule extends along the radial direction and forms an annular retainer ring, the outer diameter of the retainer ring is larger than the inner diameter of the rotor inner ring, and the inner diameter of the retainer ring is smaller than the outer diameter of the inner ducted stator.

According to at least one embodiment of the present disclosure, the first magnetic levitation structure includes an inner-duct axial winding, an inner-duct radial winding, an inner-duct axial permanent magnet correspondingly matched with the inner-duct axial winding, and an inner-duct radial permanent magnet correspondingly matched with the radial winding;

both ends of the inner duct stator extend inwards to form a first annular convex edge; the inner duct axial windings are respectively arranged on one sides of the two first annular convex edges facing the inner duct rotor; the inner duct axial permanent magnets are respectively arranged at two ends of the inner duct rotor;

a plurality of inner duct radial windings are uniformly distributed on the inner circular surface of the inner duct stator along the circumferential direction; the outer circular surface of the inner duct rotor is provided with a plurality of inner duct radial windings corresponding to the plurality of inner duct radial windings respectively.

According to at least one embodiment of the present disclosure, each of the inner-duct radial windings includes an inner-duct radial levitation winding and at least one inner-duct radial propulsion winding arranged in the axial direction; the inner duct radial suspension winding is used for enabling the inner duct rotor to be suspended and arranged in the inner duct stator;

the inner duct radial propulsion winding is used for driving the inner duct rotor to rotate.

According to at least one embodiment of the present disclosure, the second magnetic levitation structure comprises an outer-duct axial winding, an outer-duct radial winding, outer-duct axial permanent magnets correspondingly matched with the outer-duct axial winding, and outer-duct radial permanent magnets correspondingly matched with the outer-duct radial winding;

both ends of the outer culvert stator extend inwards to form a second annular convex edge; the outer duct axial winding is respectively arranged on one side of the two second annular convex edges facing the outer duct rotor; the outer duct axial permanent magnets are respectively arranged at two ends of the outer duct rotor;

a plurality of outer duct radial windings are uniformly distributed on the inner circular surface of the outer duct stator along the circumferential direction; the outer circular surface of the outer duct rotor is provided with a plurality of outer duct radial permanent magnets corresponding to the plurality of outer duct radial windings respectively.

An aircraft engine for a hybrid electric aircraft, comprising: the air inlet, the fan with the adjustable bypass ratio, the compressor, the combustion chamber, the power generation system and the tail nozzle are sequentially arranged and communicated along the axial direction;

the adjustable bypass ratio fan is any one of the adjustable bypass ratio fans for the hybrid electric vehicle.

According to at least one embodiment of the present disclosure, the compressor and the power generation system each include a housing and a rotor;

a third magnetic suspension structure is arranged between the shell and the rotor;

the rotor of the compressor is a compressor blade;

the rotor of the power generation system is a turbine.

According to at least one embodiment of the present disclosure, the turbine includes a power turbine and a free turbine;

the power turbine is located between the combustor and the free turbine;

the power turbine is coaxially connected with the air compressor.

The beneficial effects of this disclosure are:

(1) The inner ducted fan and the outer ducted fan work independently, and when the outer ducted fan does not work, the inner ducted fan and the outer ducted fan are ventilation pipelines; when the outer ducted fan works, a ducted fan with a large ducted ratio is formed, so that the function of adjusting the ducted ratio is realized, air is preliminarily compressed, thrust is provided, and the overall efficiency of the aircraft engine is increased;

(2) The bypass ratio of the aero-engine can be adjusted through the adjustable bypass ratio fan, so that higher efficiency can be achieved, and a larger amount of air can be provided for the aero-engine; and a novel engine structure is provided for the integration of the whole structure of the airplane and the engine structure.

(3) The magnetic suspension fan enables mechanical energy to be converted into electric energy through a magnetic suspension fan scheme. Not only can provide partial energy for a battery system, but also can increase the thrust or the air flow by adopting a multi-stage magnetic suspension fan so that the energy use efficiency is higher.

Drawings

The accompanying drawings, which are included to provide a further understanding of the disclosure and are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the disclosure and together with the description serve to explain the principles of the disclosure.

FIG. 1 is a schematic illustration of an aircraft engine for a hybrid electric aircraft, according to an embodiment of the present disclosure.

FIG. 2 is a schematic diagram of a variable bypass ratio fan of the aircraft engine for a hybrid electric aircraft shown in FIG. 1.

FIG. 3 is a front view of the adjustable bypass ratio fan for the hybrid electric aircraft shown in FIG. 2;

FIG. 4 is a schematic diagram of a fan collar of the adjustable bypass ratio fan for the hybrid electric aircraft shown in FIG. 2.

Reference numerals are as follows: 100-fan with adjustable bypass ratio; 110-a fan collar; 111-a retainer ring; 120-an outer ducted fan; 121-an outer ducted stator; 122-an out-ducted rotor; 123-inner rotor ring; 124-outer duct radial winding; 125-leaf; 126-outer duct axial winding; 127-outer duct axial permanent magnet; 128-outer duct radial permanent magnet; 129-a second annular rim; 130-a ducted fan; 131-an inner culvert stator; 132-guide vanes; 133-a endoprosthesis rotor; 134-inner duct axial permanent magnet; 135-inner duct axial winding; 136-inner duct radial suspension winding; 137-inner duct radial propulsion winding; 138-inner duct radial permanent magnet; 139-a first annular rim; 200-a compressor; 300-a combustion chamber; 400-a power generation system; 401-a power turbine; 402-free turbine.

Detailed Description

The present disclosure will be described in further detail with reference to the drawings and embodiments. It is to be understood that the specific embodiments described herein are for purposes of illustration only and are not to be construed as limitations of the present disclosure. It should be further noted that, for the convenience of description, only the portions relevant to the present disclosure are shown in the drawings.

It should be noted that the embodiments and features of the embodiments in the present disclosure may be combined with each other without conflict. The present disclosure will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.

As shown in fig. 2 and 3, according to a first embodiment of the present disclosure, there is provided an adjustable bypass ratio fan 100 for a hybrid electric vehicle, comprising: an inner ducted fan 130, an outer ducted fan 120 sleeved outside the inner ducted fan 130;

the ducted fan 130 includes an annular ducted stator 131, a ducted rotor 133 disposed inside the ducted stator 131, and a first magnetic levitation structure disposed between the ducted stator 131 and the ducted rotor 133; the inner duct rotor 133 is suspended in the inner duct stator 131 by a first magnetic suspension structure and is rotatably disposed;

the outer ducted fan 120 includes an outer ducted rotor 122 annularly sleeved outside the inner ducted stator 131, an outer ducted stator 121 annularly sleeved outside the outer ducted rotor 122, and a second magnetic levitation structure disposed between the outer ducted stator 121 and the outer ducted rotor 122; the outer-ducted rotor 122 is suspended between the outer-ducted stator 121 and the inner-ducted stator 131 by a second magnetic levitation structure and is rotatably disposed.

The inner ducted fan 130 and the outer ducted fan 120 operate independently of each other, and are common ventilation ducts when the outer ducted fan 120 does not operate; when the outer ducted fan 120 works, a ducted fan with a large ducted ratio is formed, the function of adjusting the ducted ratio is realized, air is preliminarily compressed, and thrust is provided.

According to one embodiment of the present disclosure, at least one end of the ducted rotor 133 is provided with guide vanes 132125 for rectification, and the guide vanes 132125 at both ends of the ducted rotor 133 are fixedly disposed with respect to the ducted stator 131. As shown in fig. 3, the guide vanes 132125 are in a cross shape, the guide vanes 132125 are fixed, that is, the guide vanes 132125 do not rotate along with the inner duct rotor 133, and the guide vanes 132125 function to rectify air.

According to an embodiment of the present disclosure, further comprising: a fan collar 110 annularly sleeved outside the inner duct stator 131; the fan collar 110 is fixedly connected with the inner culvert stator 131; the outer ducted rotor 122 is sleeved outside the fan collar 110 and is rotatably disposed relative to the fan collar 110. The fan collar 110 has three functions, which are: 1. fixing the relative positions of the ducted-in fans 130 and ducted-out fans 120; 2. as a buffer structure between the ducted-in fan 130 and the ducted-out fan 120; 3. is the connection between the present disclosure and the aircraft engine, i.e., the present disclosure is secured to the engine case by the fan collar 110.

According to an embodiment of the present disclosure, as shown in fig. 2 and 4, the bypass rotor 122 includes a rotor inner ring 123 sleeved outside the fan collar 110, and a plurality of blades 125 uniformly distributed on an outer circumferential surface of the rotor inner ring 123 in a circumferential direction; the rotor inner ring 123 is rotatably disposed with respect to the fan collar 110; at least one end edge of the fan collar 110 extends in a radial direction and forms an annular retainer ring 111, an outer diameter of the retainer ring 111 is larger than an inner diameter of the rotor inner ring 123, and an inner diameter of the retainer ring 111 is smaller than an outer diameter of the bypass stator 131.

The first magnetic suspension structure and the second magnetic suspension structure can be realized by adopting a magnetic suspension structure in the prior art. For example, the patent application with publication number CN112722242A, entitled coil permanent magnet structure between stator and rotor fans mentioned in the chinese patent application for magnetic levitation ducted fans for electric aircraft. Specifically, according to one embodiment of the present disclosure, both ends of the culvert stator 131 extend inward and form a first annular rim 139; the first annular convex edge 139 is provided with an inner duct axial winding 135 around one side of the inner duct rotor 133; inner-duct axial permanent magnets 134 are arranged at two ends of the inner-duct rotor 133 corresponding to the inner-duct axial windings 135; a plurality of inner duct radial windings are uniformly distributed on the inner circular surface of the inner duct stator 131 along the circumferential direction; the outer circular surface of the inner duct rotor 133 is provided with a plurality of inner duct radial permanent magnets 138 corresponding to the plurality of inner duct radial windings, respectively; the inner duct axial winding 135, the inner duct axial permanent magnet 134, the plurality of inner duct radial windings and the plurality of inner duct radial permanent magnets 138 are of a first magnetic levitation structure. The endoprosthesis radial windings may both keep the endoprosthesis rotor 133 in suspension and drive the endoprosthesis rotor 133 in rotation.

According to one embodiment of the present disclosure, each inner-duct radial winding includes an inner-duct radial levitation winding 136 and at least one inner-duct radial propulsion winding 137 arranged in the axial direction; the inner-duct radial suspension winding 136 is used for enabling the inner-duct rotor 133 to be suspended in the inner-duct stator 131;

the endoprosthesis radial propulsion windings 137 are used to drive the rotation of the endoprosthesis rotor 133.

In the present embodiment, as shown in fig. 2, two inner-duct radial propulsion windings 137 are provided; the culvert radial levitation winding 136 is located between two culvert radial propulsion windings 137.

According to one embodiment of the present disclosure, both ends of the bypass stator 121 extend inward and form a second annular rim 129; the second annular flange 129 is wound with the bypass axial windings 126 on a side facing the bypass rotor 122; both ends of the outer-duct rotor 122 are provided with outer-duct axial permanent magnets 127 corresponding to the outer-duct axial windings 126; a plurality of outer-duct radial windings 124 are uniformly distributed on the inner circular surface of the outer-duct stator 121 along the circumferential direction; the outer circular surface of the outer-duct rotor 122 is provided with a plurality of outer-duct radial permanent magnets 128 corresponding to the plurality of outer-duct radial windings 124, respectively; the outer-duct axial windings 126, the outer-duct axial permanent magnets 127, the plurality of outer-duct radial windings 124, and the plurality of outer-duct radial permanent magnets 128 are a second magnetic levitation structure.

Similar to the endoprosthesis radial winding, the extraducted radial winding 124 may both suspend the extraducted rotor 122 and drive the extraducted rotor 122 to rotate.

As shown in fig. 1, the present disclosure also provides an aircraft engine for a hybrid electric aircraft, comprising: the air inlet, the fan 100 with the adjustable bypass ratio, the compressor 200, the combustion chamber 300, the power generation system 400 and the tail nozzle are sequentially arranged and communicated along the axial direction;

the adjustable bypass ratio fan 100 is any one of the adjustable bypass ratio fans 100 for hybrid electric aircraft described above.

The compressor 200 is disposed between the present disclosure and the combustion chamber 300 for increasing inlet air pressure; the combustor 300 is disposed between the compressor 200 and the turbine and communicates with a fuel supply for combusting fuel to generate an expanded gas. The tail nozzle is arranged behind the power generation system 400, discharges tail gas and provides thrust; the fuel supply means may comprise a fuel tank, a booster pump, a fuel metering valve and a fuel distributor in primary communication via a fuel line, an outlet of the fuel distributor being in communication with an inlet of the combustion chamber 300, the booster pump and the fuel metering valve each being in communication with the engine controller. A booster pump is disposed between the fuel tank and the fuel metering valve for driving the flow of liquid fuel, and a fuel distributor is disposed between the fuel metering valve and the combustion chamber 300 for distributing the amount of fuel; the rotating speed sensors are arranged on the rotors of the inner and outer ducted fans 120 and the power generation system 400 and are used for measuring the rotating speed of each component and transmitting the rotating speed to the engine controller; the temperature sensors are arranged in the stators of the propulsion units at all levels and transmit temperature signals to the engine controller; the storage battery pack is connected with the current bus, and the charge-discharge state control, the thermal management control and the like of the storage battery pack are carried out by controlling the battery management system through the engine controller; the engine controller is in communication connection with the pressure sensor, the rotating speed sensor, the temperature sensor, the booster pump, the fuel metering valve, stators of all the propulsion units (the bypass ratio adjustable fan and the power generation system 400) and the battery pack, and is used for receiving and processing signals of all the sensors and controlling the actions of all the propulsion units and the fuel metering valve. This is in accordance with chinese patent application No. CN113086219A entitled shaftless electric engine for aircraft, control method, an aircraft.

The gas compressor 200 and the power generation system 400 can be realized by adopting a magnetic suspension rotating mechanism in Chinese patent application with the publication number of CN113086219A and the name of shaftless electric engine and control method for an aircraft and the aircraft, and specifically, according to one embodiment of the disclosure, the gas compressor 200 and the power generation system 400 both comprise a shell and a rotor; a third magnetic suspension structure is arranged between the shell and the rotor; the rotor of the compressor 200 is a compressor blade; the rotor of the power generation system 400 is a turbine. The third magnetic levitation structure may be identical to the first magnetic levitation structure or the second magnetic levitation structure.

According to one embodiment of the present disclosure, the turbine includes a power turbine 401 and a free turbine 402;

the power turbine 401 is located between the combustor 300 and the free turbine 402;

the power turbine 401 is coaxially connected to the compressor 200.

The power turbine 401 is disposed between the combustor 300 and the free turbine 402, and is used for performing work by expanding the combustion gas to drive the compressor 200 to rotate, and the free turbine 402 is driven by the expanded combustion gas to generate electricity. That is, the power generation system 400 can both provide propulsion and generate power. The power generation system 400 has two modes: 1. a propulsion mode: generally, when taking off or landing, a control center selects a corresponding working condition mode, and the combustion gas and the energy storage system provide power to enable the rotor to completely provide thrust; 2. a power supply mode: and when the airplane flies in a stable state, part of electric power of electric appliances of the airplane is supplied and a storage battery is charged.

In the description of the present specification, reference to the description of "one embodiment/mode", "some embodiments/modes", "example", "specific example", or "some examples" or the like means that a particular feature, structure, material, or characteristic described in connection with the embodiment/mode or example is included in at least one embodiment/mode or example of the present application. In this specification, the schematic representations of the terms used above are not necessarily intended to be the same embodiment/mode or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments/modes or examples. Furthermore, the various embodiments/aspects or examples and features of the various embodiments/aspects or examples described in this specification can be combined and combined by one skilled in the art without conflicting therewith.

Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or to implicitly indicate the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of the feature. In the description of the present application, "plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.

It will be understood by those skilled in the art that the foregoing embodiments are provided merely for clarity of explanation and are not intended to limit the scope of the disclosure. Other variations or modifications may occur to those skilled in the art, based on the foregoing disclosure, and are still within the scope of the present disclosure.

Claims

1. A fan (100) with adjustable bypass ratio for mixing pure electric aircraft, characterized by comprising: the fan comprises an inner ducted fan (130) and an outer ducted fan (120) sleeved outside the inner ducted fan (130);

the inner duct fan (130) comprises an annular inner duct stator (131), an inner duct rotor (133) arranged in the inner duct stator (131), and a first magnetic suspension structure arranged between the inner duct stator (131) and the inner duct rotor (133); the inner duct rotor (133) is suspended in the inner duct stator (131) through the first magnetic suspension structure and is arranged in a rotating mode;

the ducted-outer fan (120) comprises a ducted-outer rotor (122) sleeved outside the ducted-inner stator (131), a ducted-outer stator (121) sleeved outside the ducted-outer rotor (122), and a second magnetic levitation structure arranged between the ducted-outer stator (121) and the ducted-outer rotor (122); the outer duct rotor (122) is suspended between the outer duct stator (121) and the inner duct stator (131) through the second magnetic suspension structure and is arranged in a rotating mode;

the adjustable bypass ratio fan (100) further comprises: a fan collar (110) sleeved outside the inner duct stator (131); the fan ferrule (110) is fixedly connected with the inner duct stator (131); the outer ducted rotor (122) is sleeved outside the fan ferrule (110) and is rotatably arranged relative to the fan ferrule (110);

the bypass rotor (122) comprises a rotor inner ring (123) sleeved outside the fan ferrule (110) in a sleeving manner and a plurality of blades (125) uniformly distributed on the outer circular surface of the rotor inner ring (123) along the circumferential direction; the rotor inner ring (123) is rotationally arranged relative to the fan collar (110); at least one end edge of the fan collar (110) extends along the radial direction and forms an annular retainer ring (111), the outer diameter of the retainer ring (111) is larger than the inner diameter of the rotor inner ring (123), and the inner diameter of the retainer ring (111) is smaller than the outer diameter of the inner bypass stator (131).

2. The variable bypass ratio fan (100) for a hybrid electric-only aircraft according to claim 1, characterized in that at least one end of the ducted rotor (133) is provided with guide vanes (132) (125) for flow straightening, and the guide vanes (132) (125) at both ends of the ducted rotor (133) are both fixedly disposed with respect to the ducted stator (131).

3. The adjustable bypass ratio fan (100) for a hybrid electric vehicle of claim 1, characterized in that the first magnetic levitation structure comprises an inner bypass axial winding (135), an inner bypass radial winding, an inner bypass axial permanent magnet (134) correspondingly matched to the inner bypass axial winding (135), and an inner bypass radial permanent magnet (138) correspondingly matched to the radial winding;

both ends of the bypass stator (131) extend inwards and form a first annular convex edge (139); the inner duct axial windings (135) are respectively arranged on one side of the two first annular convex edges (139) facing the inner duct rotor (133); the inner duct axial permanent magnets (134) are respectively arranged at two ends of the inner duct rotor (133);

a plurality of inner duct radial windings are uniformly distributed on the inner circular surface of the inner duct stator (131) along the circumferential direction; the outer circular surface of the inner duct rotor (133) is provided with a plurality of inner duct radial permanent magnets (138) corresponding to the inner duct radial windings respectively.

4. The adjustable bypass ratio fan (100) for a hybrid electric-only aircraft according to claim 3, characterized in that each of said bypass radial windings comprises an axially arranged bypass radial levitation winding (136) and at least one bypass radial propulsion winding (137); the inner-duct radial suspension winding (136) is used for enabling the inner-duct rotor (133) to be placed in the inner-duct stator (131) in a suspended mode;

the inner-duct radial propulsion winding (137) is used for driving the inner-duct rotor (133) to rotate.

5. The adjustable bypass ratio fan (100) for a hybrid electric vehicle of claim 1, characterized in that the second magnetic levitation structure comprises an outer bypass axial winding (126), an outer bypass radial winding (124), an outer bypass axial permanent magnet (127) correspondingly matched to the outer bypass axial winding (126), and an outer bypass radial permanent magnet (128) correspondingly matched to the outer bypass radial winding (124);

both ends of the bypass stator (121) extend inwards and form a second annular convex edge (129); the bypass axial windings (126) are respectively arranged on one side of the two second annular flanges (129) facing the bypass rotor (122); the outer-duct axial permanent magnets (127) are respectively arranged at two ends of the outer-duct rotor (122);

a plurality of outer-duct radial windings (124) are uniformly distributed on the inner circular surface of the outer-duct stator (121) along the circumferential direction; the outer circular surface of the outer duct rotor (122) is provided with a plurality of outer duct radial permanent magnets (128) corresponding to the plurality of outer duct radial windings (124).

6. An aircraft engine for a hybrid electric aircraft, comprising: the air inlet, the fan (100) with the adjustable bypass ratio, the compressor (200), the combustion chamber (300), the power generation system (400) and the tail nozzle are sequentially arranged and communicated along the axial direction;

the adjustable bypass ratio fan (100) is the adjustable bypass ratio fan (100) for a hybrid electric-only aircraft of any one of claims 1 to 5.

7. The aircraft engine for a hybrid electric aircraft according to claim 6, characterized in that the compressor (200) and the power generation system (400) each comprise a casing and a rotor;

the rotor of the compressor (200) is a compressor blade;

the rotor of the power generation system (400) is a turbine.

8. The aircraft engine for a hybrid electric aircraft according to claim 7, characterized in that the turbine comprises a power turbine (401) and a free turbine (402);

the power turbine (401) is located between the combustion chamber (300) and the free turbine (402);

the power turbine (401) is coaxially connected with the compressor (200).