阅读说明：本技术 用于翼身融合体飞机的节能型推进系统 (Energy-saving propulsion system for wing-body integrated aircraft ) 是由 刘金超 张志伟 肖翼 袁昌盛 李栋 朱大明 贾志刚 于 2020-07-13 设计创作，主要内容包括：本公开提供了一种用于翼身融合体飞机的节能型推进系统,包括：主发动机、热电转换装置、电力储能装置、两组外置风扇、以及驱动所述外置风扇转动的电动机；本公开在不改变翼身融合体飞机整体气动布局的基础上,通过在飞机两翼设置一定数量的外置风扇来提高推进系统等效涵道比,从而可以降低燃油消耗和减少排放；通过沿主发动机尾喷段壁面布置若干热电转换模块吸收排气余热并通过热电调理模块处理后存储到电力储能装置中,存储的电能稳压后可以分别为外置风扇的电动机、飞发附件设备提供全部或者部分电力,从而将发动机部分排气余热回收转换为电能使用,降低主发动机用于飞发附件系统以及外置风扇设备的功率提取以及燃油消耗。(The present disclosure provides an energy-efficient propulsion system for a wing-body fusion aircraft, comprising: the system comprises a main engine, a thermoelectric conversion device, an electric energy storage device, two groups of external fans and a motor for driving the external fans to rotate; on the basis of not changing the overall aerodynamic layout of the wing-body fusion aircraft, the equivalent bypass ratio of a propulsion system is improved by arranging a certain number of external fans at two wings of the aircraft, so that the fuel consumption and the emission can be reduced; a plurality of thermoelectric conversion modules are arranged along the wall surface of the tail spraying section of the main engine to absorb exhaust waste heat and store the exhaust waste heat in the electric energy storage device after being processed by the thermoelectric conditioning modules, and the stored electric energy can respectively provide all or part of electric power for the motor of the external fan and the flying accessory equipment after being stabilized, so that part of the exhaust waste heat of the engine is recovered and converted into electric energy for use, and the power extraction and the fuel consumption of the main engine for the flying accessory system and the external fan equipment are reduced.)

1. An energy efficient propulsion system for a fused wing-body aircraft, comprising: the system comprises a main engine, a thermoelectric conversion device, an electric energy storage device, two groups of external fans and a motor for driving the external fans to rotate;

the two groups of external fans are respectively arranged on two flying wings of the airplane; the thermoelectric conversion device comprises a thermoelectric conversion module, and the thermoelectric conversion module is mounted on the inner wall surface of the tail jet section of the main engine;

the thermoelectric conversion device is connected with the electric energy storage device through an energy storage cable, and the electric energy storage device is connected with the motor through a motor cable.

2. The propulsion system of claim 1, wherein a plurality of the thermoelectric conversion modules are spaced axially in N sections along the main engine aft jet section, each section including M thermoelectric conversion modules circumferentially disposed along an inner wall of the main engine aft jet section; n is more than or equal to 1, and M is more than or equal to 1.

3. A propulsion system as in claim 1 wherein the thermoelectric conversion device further comprises a thermoelectric conditioning module connected to the thermoelectric conversion module by an internal cable, the thermoelectric conditioning module comprising an electrical energy indicator detection unit and a consumption unit for handling electrical energy consumption of an indicator that is not up to a set point.

4. The propulsion system as claimed in claim 1 wherein the flying wing is hollow and the outboard fan and the motor are mounted within the flying wing, the airflow path of the outboard fan being streamlined.

5. A propulsion system as claimed in claim 1 wherein the electrical energy storage means comprises a plurality of battery packs connected in parallel or in series, and a regulated output circuit connected to the battery packs.

6. A propulsion system as claimed in claim 1 wherein the electrical energy storage device is disposed at a mid-aircraft location.

7. A propulsion system as claimed in claim 1 wherein the number of main engines is two, the main engines being back-supported engines, the two main engines being mounted to the rear of the aircraft and symmetrically arranged about the central axis of the aircraft.

8. The propulsion system of claim 7, wherein the main engine includes an axisymmetric nacelle having a streamlined outer shroud profile, and an engine mount that is a narrow section mount.

9. A propulsion system as claimed in any one of claims 1 to 8 wherein the electrical energy storage means is connected to electrical equipment onboard the aircraft by an onboard equipment supply cable.

10. A propulsion system as claimed in any one of claims 1 to 8 wherein the electrical energy storage means is connected to the engine accessory equipment of the main engine by an engine accessory equipment supply cable.

Technical Field

The present disclosure relates to aircraft propulsion systems, and more particularly to an energy efficient propulsion system for a wing-body fusion aircraft.

Background

The wing-body fusion aircraft is an aircraft with advanced aerodynamic performance, which fuses the wings and the fuselage of the traditional aircraft, and is gradually one of the focuses of civil aviation design research in recent years. Compared with the traditional configuration aircraft, the wing-body integrated aircraft can greatly improve the fuel economy, optimize the structure and reduce the weight, so that the wing-body integrated aircraft has the advantages of high bearing capacity, high pneumatic efficiency, low oil consumption, low emission and the like. At present, corresponding coping development plans are made in developed countries of major aviation in the world aiming at wing-body fusion airplanes, and a new technology comprehensive development situation before the development history of civil aircrafts is formed.

As is well known, a propulsion system is the heart of an airplane, future civil passenger planes will pursue the development concept of green aviation more, and take the development goals of energy conservation, emission reduction and noise reduction, so that the expectations for the economy and low emission of the propulsion system are higher and higher. At present, in order to improve the fuel economy of a wing-body fusion body aircraft, researchers adopt a full electric propulsion technology, a hybrid electric propulsion technology, a distributed propulsion technology and the like, and the technologies are difficult to realize in a short time.

Meanwhile, the traditional gas turbine propulsion system is developed to the present, is more mature, faces the bottleneck of technical development, is influenced by various aspects of technical development of materials, processes and the like, and is difficult to realize the breakthrough of the quality of fuel economy and emission in a short time, namely, the requirement of the wing body fusion aircraft on the propulsion system is more difficult to meet.

BRIEF SUMMARY OF THE PRESENT DISCLOSURE

In order to solve at least one of the above technical problems, the present disclosure provides an energy-saving propulsion system for a wing-body fusion aircraft, which includes:

an energy efficient propulsion system for a fused wingbody aircraft, comprising: the system comprises a main engine, a thermoelectric conversion device, an electric energy storage device, two groups of external fans and a motor for driving the external fans to rotate;

the two groups of external fans are respectively arranged on two flying wings of the airplane; the thermoelectric conversion device comprises a thermoelectric conversion module, and the thermoelectric conversion module is mounted on the inner wall surface of the tail jet section of the main engine;

the thermoelectric conversion device is connected with the electric energy storage device through an energy storage cable, and the electric energy storage device is connected with the motor through a motor cable.

Furthermore, the plurality of thermoelectric conversion modules are distributed into N sections at intervals along the axial direction of the tail spraying section of the main engine, and each section comprises M thermoelectric conversion modules which are circumferentially arranged along the inner wall of the tail spraying section of the main engine; n is more than or equal to 1, and M is more than or equal to 1.

Further, the thermoelectric conversion device also comprises a thermoelectric conditioning module, the thermoelectric conditioning module is connected with the thermoelectric conversion module through an internal cable, and the thermoelectric conditioning module comprises an electric energy index detection unit and a consumption unit for processing the electric energy consumption with the index not reaching the set value.

Furthermore, the flying wing is of a hollow structure, the external fan and the motor are installed inside the flying wing, and an airflow channel of the external fan is streamline.

Further, the electric energy storage device comprises a plurality of battery packs connected in parallel or in series, and a voltage stabilizing output circuit connected with the battery packs.

Further, the electric energy storage device is arranged at a middle position of the aircraft.

Furthermore, the number of the main engines is two, the main engines are back-support engines, and the two main engines are mounted at the rear of the airplane and symmetrically arranged along the axis of the airplane.

Further, the main engine comprises an axisymmetric nacelle and an engine support, wherein the profile of the outer cover of the axisymmetric nacelle is streamline, and the engine support is a narrow-section support.

Further, the electric energy storage device is connected with airborne electric equipment of the airplane through an airborne equipment power supply cable.

Further, the electric energy storage device is connected with the engine accessory equipment of the main engine through an engine accessory equipment power supply cable.

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 energy efficient propulsion system arrangement for a wing-body fusion aircraft according to the present disclosure;

fig. 2 is a schematic view of a thermoelectric conversion device of the present disclosure;

FIG. 3 is an external fan mounting schematic of the present disclosure;

FIG. 4 is a schematic view of an external fan airflow path of the present disclosure;

in the figure:

an onboard electrical device 1; an external fan 2; a motor 3; a main engine 4; a thermoelectric conversion device 5; an electric power storage device 6; an energy storage cable 10; a motor drive shaft 20; a motor cable 30; an onboard device power supply cable 40; an axisymmetrical nacelle 41; the engine accessory device 42; an engine mount 43; a main engine tail spray section 44; an engine accessory equipment power supply cable 50; a thermoelectric conversion module 51; an inner cable 52; a thermoelectric conditioning module 53; an aircraft 100; a flying wing 101; and reinforcing ribs 102.

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.

Referring to fig. 1, the present embodiment provides an energy saving propulsion system for a wing-body fusion aircraft, comprising: the device comprises a main engine 4, a thermoelectric conversion device 5, an electric energy storage device 6, two groups of external fans 2 and a motor 3 for driving the external fans 2 to rotate, wherein the motor 3 is in transmission connection with the external fans 2 through a motor driving shaft 20; the two groups of external fans 2 are respectively arranged on two flying wings 101 of the airplane and symmetrically distributed along the axis of the airplane 100, and each group of external fans 2 comprises at least one external fan 2; the thermoelectric conversion device 5 comprises a thermoelectric conversion module 51, wherein the thermoelectric conversion module 51 is mounted on the inner wall surface of the tail jet section 44 of the main engine; the thermoelectric conversion device 5 is connected with the electric energy storage device 6 through an energy storage cable 10, and the electric energy storage device 6 is connected with the electric motor 3 through an electric motor cable 30.

The bypass ratio of the propulsion system can be effectively improved by arranging the external fan 2, and the fuel consumption is reduced. The problem that the diameter of a fan of a traditional engine cannot be designed to be too large due to the fact that the traditional engine is limited by the incoming flow speed of the blade tip and the structural size is solved, the limitation can be broken through the external fan, the fan diameter of the main engine is indirectly increased, the bypass ratio is improved, and fuel consumption of the aircraft in the cruising state is reduced.

Referring to fig. 1, 3 and 4, the flying wing 101 is a hollow structure, the flying wing 101 is internally supported by a reinforcing rib 102, the external fan 2 and the motor 3 are installed inside the flying wing 101, which is beneficial to further reducing the air resistance section, the airflow channel of the external fan 2 is streamlined, and is similar to the nacelle structure of the main engine 4, and is integrally embedded inside the flying wing 101, the internal flow channel profile is beneficial to reducing the flow loss after the fan, and the external profile of the flying wing 101 is beneficial to reducing the external air resistance.

Referring to fig. 1, the number of the main engines 4 is two, the main engines 4 are back-supported engines, and the two main engines 4 are mounted at the rear of the aircraft and symmetrically arranged along the central axis of the aircraft. The main engine 4 comprises an axisymmetrical nacelle 41 and an engine bracket 43, wherein the outer cover profile of the axisymmetrical nacelle 41 is streamline, and the engine bracket 43 is a narrow-section bracket. To minimize intake resistance and improve aerodynamic efficiency.

The energy-saving propulsion system disclosed by the invention is reasonable in design, simple in structure and easy to realize in technical scheme. Based on the mature large bypass ratio main engine 4 technology, no major changes are made to the internal structure and aerodynamic layout of the conventional propulsion system, and therefore the technical risks of application are relatively small.

Referring to fig. 1 and 2, the thermoelectric conversion device 5 according to the present embodiment is disposed at a tail-jet section of the main engine 4, and converts part of exhaust waste heat of the main engine 4 into electric energy through the thermoelectric conversion module 51 and stores the electric energy into the electric energy storage device 6, so as to achieve waste heat recovery and reuse; the effects of energy conservation and emission reduction are achieved. The self-powered or supplementary power supply of part of equipment of the wing-body fusion body airplane is realized by adopting a thermoelectric conversion technology, so that the comprehensive energy utilization rate of a propulsion system is improved, and the fuel consumption is saved. The fuel consumption of the main engine 4 distributed to the flying accessories and the onboard equipment generator can be effectively reduced, and meanwhile, the stored electric energy can be used at any time according to the requirement, and the device is convenient and fast.

The plurality of thermoelectric conversion modules 51 are distributed at intervals in the axial direction of the main engine tail nozzle section 44, and each section comprises M thermoelectric conversion modules 51 arranged along the circumferential direction of the inner wall of the main engine tail nozzle section 44; n is more than or equal to 1, and M is more than or equal to 1. Through spout the section 44 at the main engine tail and set up multistage thermoelectric conversion module 51 respectively along its axial, can improve the recovery efficiency who spouts section 44 waste heat to the main engine tail, every section thermoelectric conversion module 51 all includes along the engine spout section inner wall axial respectively at least one thermoelectric conversion module 51 a little for waste heat recovery is more comprehensive, improves the recovery efficiency.

Referring to fig. 1 and 4, in this example, the thermoelectric conversion device 5 further includes a thermoelectric conditioning module 53, the thermoelectric conditioning module 53 is connected to the thermoelectric conversion module 51 through an internal cable 52, and the thermoelectric conditioning module 53 includes an electric energy index detection unit and a consumption unit for processing electric energy consumption of which index does not reach a set value. The electric energy obtained by the thermoelectric conversion module 51 is transmitted to the thermoelectric conditioning module 53 through the internal cable 52, the thermoelectric conditioning module 53 is provided with an electric energy index detection unit and an electric energy dissipation unit, the electric energy with the index meeting the set requirement is transmitted to the electric energy storage device 6 through the energy storage cable 10 to be stored after passing through the thermoelectric conditioning module 53, and the electric energy with the index not meeting the set requirement is consumed through the electric energy dissipation unit carried by the thermoelectric conditioning module 53.

Referring to fig. 1 and 4, the power storage device 6 is disposed in a middle position of the aircraft 100, so that the aircraft flight balance is facilitated, and the cable routing is facilitated. The electric energy storage device 6 comprises a plurality of battery packs connected in parallel or in series and a voltage stabilization output circuit connected with the battery packs. The electric power storage device 6 is capable of storing the electric energy recovered by the thermoelectric conversion device 5. Meanwhile, the electric power energy storage device 6 has a voltage stabilization output circuit, and can have a voltage adjustment function, stabilize the unstable electric energy recovered by the thermoelectric conversion device 5, and output the electric energy to the outside when necessary. The electric energy storage device 6 is connected with the onboard electric equipment 1 of the airplane through an onboard equipment power supply cable 40. The electrical energy storage device 6 is connected to the engine accessory devices 42 of the main engine 4 via an engine accessory device power supply cable 50.

The operation process of the propulsion system comprises a thermoelectric conversion storage process and an electric energy recycling process.

The thermoelectric conversion storage process comprises the following steps:

when the wing body fusion body airplane works, the main engine 4 continuously sprays high-temperature gas to the outside, at the moment, the thermoelectric conversion module 51 arranged on the wall surface of the tail spraying section 44 of the main engine converts part of exhaust waste heat into electric energy according to the Seebeck effect principle, the electric energy is transmitted to the thermoelectric conditioning module 53 through the internal cable, and the electric energy with the parameters reaching the set index is transmitted to the electric energy storage device 6 through the energy storage cable 10 to be stored and regulated.

The electric energy recycling process comprises the following steps:

the electric energy output from the electric energy storage device 6 has three routes:

the first path feeding back the main engine 4 along the engine accessory equipment supply cable 50 to provide electrical energy to the engine accessory equipment 42 to replace or save engine accessory power draw;

the second path of power supply cable 40 along the airborne equipment supplies power to the wing-body fusion aircraft and is used for supplying power to systems such as airborne electronic equipment, an air conditioner and the like or supplying power additionally, so that the power output of the aircraft matched by an engine is greatly reduced, and the fuel consumption is reduced;

the third path supplies power to the motor 3 of the external fan 2 along the motor cable 30, the motor 3 drives the external fan 2 to work, the equivalent bypass ratio of the propulsion system is improved, and the fuel consumption of the main engine 4 in the cruising state is reduced.

It will be understood by those skilled in the art that the foregoing embodiments are merely for clarity of illustration of the disclosure 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.