WO2021134543A1

WO2021134543A1 - High-lift for ring-wing fan engine

Info

Publication number: WO2021134543A1
Application number: PCT/CN2019/130686
Authority: WO
Inventors: 李庆远
Original assignee: 李庆远
Priority date: 2019-12-31
Filing date: 2019-12-31
Publication date: 2021-07-08

Abstract

An external duct housing of a turbofan and a ducted fan unmanned aerial vehicle. The cross sections of the external duct housings are distributed on two portions on two sides of the axis of the duct housing as airfoil sections for generating a lift force.

Description

Ring-wing fan engine increases

Field of invention

The invention relates to an increase in the lift of a ring-wing fan engine, in particular to a power device that increases lift and improves energy efficiency by combining a ring-wing and an (outer) duct shell.

Background technique

At the end of World War II, the German Air Force airport was often bombed and could not be used, so it had to bid for the development of Vertical Take-Off and Landing (VTOL) fighter jets. Austrian Heinkel company proposed a ring-wing aircraft program. After the Second World War, NATO faced the torrent of Warsaw Pact steel and set off an upsurge in VTOL development. The French company SNECMA developed the Coléoptère C.450 turbojet ring-wing aircraft, which successfully flew in 1958 and crashed in 1959. Limited to the level of technology at the time, flight control was a major challenge, and it was difficult to increase the wingspan and wing area.

More than 80% of the thrust produced by modern super ducted turbofan engines is produced by external ducted fans, which is more like a gas turbine driven coaxial thrust fan. The electric thrust fan completely omits the connotation, and the thrust fan is driven by the electric motor. For example, a ducted UAV can increase thrust and enhance safety by placing the rotor in the duct, and can take off and land and operate in a very narrow environment.

The (external) ducted casing of turbofan engines and ducted UAVs increases weight and resistance, but cannot directly increase lift. Engine companies such as GE are studying propeller engines (also known as Open Rotors) to put aside external The limitation of the duct shell, the improvement of the duct ratio, and the improvement of the heat engine efficiency can reduce fuel consumption by 30%, and the speed is only slower than that of the turbofan. However, because the air was torn between the two-stage counter-rotating blades, it caused huge noise, and it could even be detected by the submarine anti-submarine network, so it could not be put into commercial use.

Summary of the invention

The cross-sectional shape of the (outer) duct shell of the turbofan engine and ducted UAV in the prior art is an axisymmetric mirror image. When working, the air flow in the duct is fast, and the air flow in the duct is slow. The upper and lower surfaces of the (outer) duct shell generate lift and pressure respectively, and the two cancel each other out, so there is no lift.

It is conceivable to combine the ring wing and turbofan engine, the (outer) duct shell of a ducted UAV, and transform the (outer) duct hull into a ring wing to increase lift and increase the weight utilization of the (outer) duct hull. For ducted UAVs, if the characteristics of the VTOL of the ring-wing aircraft can be used, the ring-wing aircraft will deflect to level flight after take-off and use the ring-wing aircraft to provide part of the lift to improve energy efficiency and dead time.

However, it should be understood that the content of the present invention may not include all aspects and embodiments of the present invention. The content of the present invention is not meant to be restricted or restricted in any way, and the present invention disclosed herein will be understood by one of the following: The technical staff includes obvious improvements and modifications.

Detailed ways

The present invention will now be described more fully hereinafter. However, the present invention can be implemented in many different forms and should not be construed as being limited to the embodiments set forth herein. Hopefully, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the present invention to those skilled in the art.

It should be understood that various changes can be made to the function and arrangement of elements without departing from the spirit and scope set forth in the appended claims. Therefore, the embodiments are examples or implementations of the present invention, rather than the only implementations. The various appearances of "one embodiment," "an embodiment," or "some embodiments" do not necessarily all refer to the same embodiment. Although various features of the invention may be described in the context of a single embodiment, the features may also be provided individually or in any suitable combination. Conversely, although the invention may be described herein in the context of separate embodiments for the sake of clarity, the invention may also be implemented in a single embodiment or any combination of embodiments.

Unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by those of ordinary skill in the art to which the present invention belongs. It will be further understood that terms such as those defined in commonly used dictionaries should be interpreted as having meanings consistent with their meanings in the context of related technologies and the present disclosure, and will not be interpreted as idealized or excessive The formal meaning, unless explicitly defined as such in this article.

Reference terms such as "left", "right", "upper", "lower", "front" and "rear" are intended to be used in the implementation of the present invention in relation to the specific features, structures or elements in the depicted embodiment example. Obviously, such directional terms regarding the actual use of the device have no specific meaning, because the device can be used by a user or multiple users in multiple directions.

In the embodiment of the present invention, the "wing shape" design of the (outer) duct shell section of the turbofan engine and ducted UAV is changed to increase lift, but it cannot make it work like a circular wing aircraft. The French turbojet ring-wing aircraft Coléoptère C.450 has independent air inlets and jet ports, and the jet port extends beyond the tail end of the ring wing. A closer design requires a ring wing outside the (outer) duct shell, which obviously introduces additional weight and resistance.

In addition, civil aviation turbofans are usually hoisted under the lower single wing. Because the engine is getting larger and more grounded, the lower cross section of the engine has to be designed to be flat, and there is no extra space to install the ring wing. Even if it is a simple ducted UAV, this is contrary to the original intention of making full use of the weight of the (outer) duct shell.

However, even if the main wing cannot be replaced, as long as there is lift, the corresponding main wing area, and its corresponding weight and resistance can be reduced, thereby improving energy efficiency, reducing fuel consumption and operating costs. For ducted UAVs, this means an increase in the time spent in the air. After all, the application of drones is not as common as civil aviation transportation.

The above description is only an embodiment of the present invention, and is not intended to limit the scope of the present invention. Various changes and modifications according to the claims and specification of the present disclosure are still within the scope of the claimed invention. In addition, each embodiment and claims may not include all the disclosed advantages or special tightening mechanical clamping properties. In addition, the abstract and title are only used to facilitate searching of patent documents and are not intended to limit the scope of the claimed invention in any way.

Claims

An (outer) duct shell of a turbofan engine and a ducted UAV has the following characteristics: the duct shell section is distributed on two parts on both sides of the duct shell axis, respectively serving as airfoils, both Can produce lift.
An (outer) duct shell of a turbofan engine and a ducted UAV has the following characteristics: the duct shell section is distributed on two parts on both sides of the duct shell axis, respectively serving as airfoils, both Can produce lift.
The duct housing according to claim 3, which has the following characteristics: the cross section of the duct housing is distributed on two parts on both sides of the axis of the duct housing, and can be overlapped with each other after translation, that is, they have exactly the same shape.