Variable fan-jet engine

Abstract

A variable fan-jet engine according to an embodiment of the present disclosure comprises a main body housing for accommodating a fan that provides thrust, and a front duct connected to the front of the main body housing, the front duct comprising: a front duct case connected to the main body housing; a front ring distanced from and in front of the front duct case; one or more front ribs connecting the front duct case and front ring; and front wings provided so as to open and close a side inlet provided between the front duct case and front ring.

Description

Variable fan jet

[0001] The present invention relates to a variable fan jet, and more particularly, to a variable fan jet having a front wing that is operable to open and close a side intake.

[0002] VTOL (Vertical Take-Off and Landing) aircraft are based on advancements in various engineering and aeronautical fields. This technology combines the advantages of vertical take-off and landing aircraft, such as helicopters, with those of traditional fixed-wing aircraft, exploring the potential for innovative solutions in emerging areas, particularly urban air transportation.

[0003] For example, prior art (U.S. Patent Publication No. US 10,071,801 B2) discloses a VTOL aircraft based on a single-propeller aircraft design. This technology enables VTOL capability by adding a vertically-positioned, foldable tail rotor and a front rotor that can tilt from horizontal to vertical. This design offers the speed and fuel efficiency of a fixed-wing aircraft, along with the hovering and flexibility of a rotary aircraft.

[0004] Various embodiments of the present invention are intended to solve the above problems, and provide a variable fan jet having a side intake installed in a front ring of the fan jet and a front wing that is movable to open and close the side intake.

[0005] The present disclosure provides a variable fanjet and an aircraft equipped with a variable fanjet that maximizes power output in hover mode and optimizes airflow efficiency in cruise mode by utilizing a maneuver in which the front wing opens and closes the side intakes.

[0006] The problems to be solved by the present invention are not limited to the problems mentioned above, and other problems not mentioned will be clearly understood by those skilled in the art from the description below.

[0007] A variable fan jet (100) according to one aspect of the present application includes a main body housing (110) that accommodates a fan (140) that provides thrust, and a front duct (120) connected to the front of the main body housing (110), wherein the front duct (120) may include: a front duct case (121) connected to the main body housing (110); a front ring (122) positioned spaced apart from the front of the front duct case (121); one or more front ribs (123) that connect the front duct case (121) and the front ring (122); and a front wing (130) configured to open and close a side intake port (124) formed between the front duct case (121) and the front ring (122).

[0008] In addition, a variable fan jet (100) can be provided in which the fan jet (100) is rotatably installed relative to the fuselage (11) of the aircraft (10) and can be positioned horizontally or vertically, and in a state in which the fan jet (100) is horizontal relative to the fuselage (11) of the aircraft (10), the front wing (130) is positioned to close the side intake (124), and in a state in which the fan jet (100) is vertical relative to the fuselage (11) of the aircraft (10), the front wing (130) is positioned to open the side intake (124).

[0009] In addition, a variable fan jet may be provided in which the upper inner surface (132) of the front wing (130) has a shape corresponding to the outer surface of the front ring (122), the lower inner surface (131) has a shape corresponding to the outer surface of the front duct case (121), and the front wing (130) has a shape in which the lower inner surface (131) contacts the front duct case (121) and the upper inner surface (132) contacts the front ring (122) when the side intake port (124) is closed, and the outer surface of the front wing (130) follows the shape of the outer surface of the main body housing (110), and the front wing (130) is movable to be positioned rearward of the inlet of the side intake port (124) when the side intake port (124) is opened.

[0010] In addition, a variable fan jet may be provided in which the inner surface (121a) of the front duct case (121), which defines the inlet of the side intake (124) in the front duct case (121), has a greater curvature than the outer surface.

[0011] In addition, a variable fan jet may be provided in which the inner surface (122a) of the front ring (122) has a smaller curvature than the outer surface (122b) of the front ring.

[0012] The present disclosure utilizes a variable-geometry fanjet that maximizes power in hover mode and optimizes airflow efficiency in cruise mode by manipulating the front wing to open and close side intakes. This minimizes the complexity of the aircraft structure to which the variable-geometry fanjet is applied, while optimizing weight. As a result, it can lead to dramatic improvements in aircraft performance, including speed and weight.

[0013] The effects of the present invention are not limited to the effects mentioned above, and other effects not mentioned will be clearly understood by those skilled in the art from the description below.

[0014] Various embodiments are described with reference to the drawings, wherein like reference numerals are used to refer to similar elements generally. In the following examples, for purposes of explanation, numerous specific details are set forth to provide a comprehensive understanding of one or more embodiments. However, it will be apparent that such embodiments may be practiced without these specific details.

[0015] FIG. 1 illustrates an aircraft equipped with a fan jet according to various embodiments of the present disclosure.

[0016] FIG. 2 is a side view of an aircraft with a fan jet operating in hovering mode according to various embodiments of the present disclosure.

[0017] FIG. 3 is a side view of an aircraft with a fan jet operating in cruise mode according to various embodiments of the present disclosure.

[0018] FIG. 4 is an exploded perspective view of a fan jet according to various embodiments of the present disclosure.

[0019] FIG. 5 is a plan view of the front duct of a fan jet with the front wing open, as viewed from the front, according to various embodiments of the present disclosure.

[0020] FIG. 6 is a cross-sectional view of a fan jet with its front wing closed according to various embodiments of the present disclosure.

[0021] Referring to FIG. 7, when the front wing opens the side intake, the front wing can be positioned lower than the portion where the side intake is located or rearward in the horizontal direction.

[0022] Figure 8 is an enlarged view of part A of the fan jet illustrated in Figure 7.

[0023] [Explanation of symbols]

[0024] 10: Aircraft 100: Fan Jet

[0025] 11: Airframe 110: Body housing

[0026] 111: Main body case 120: Front duct

[0027] 121: Front duct case 121a: Front duct case inner surface

[0028] 122: Front ring 122a: Front ring inner surface

[0029] 122b: Front ring outer surface 123: Front rib

[0030] 124: Side intake 125: Main intake

[0031] 130: Front wing 131: Lower inner surface

[0032] 132: Top inner 140: Fan

[0033] Various embodiments and / or aspects are now disclosed with reference to the drawings. In the following description, for purposes of explanation, numerous specific details are set forth to provide a thorough understanding of one or more aspects. However, it will be apparent to one skilled in the art that such aspects may be practiced without these specific details. The following description and the accompanying drawings detail specific exemplary aspects of one or more aspects. However, these aspects are exemplary, and any of the various methods within the principles of the various aspects may be utilized, and the description is intended to encompass all such aspects and their equivalents. Specifically, the use of the terms "embodiment," "example," "aspect," and "example" herein is not intended to imply that any aspect or design described therein is preferred or advantageous over other aspects or designs.

[0034] Hereinafter, regardless of the drawing numbers, identical or similar components are assigned the same reference numerals, and redundant descriptions thereof are omitted. Furthermore, when describing the embodiments disclosed in this specification, if a detailed description of a related known technology is judged to obscure the gist of the embodiments disclosed in this specification, the detailed description thereof will be omitted. Furthermore, the attached drawings are only intended to facilitate easy understanding of the embodiments disclosed in this specification, and the technical concepts disclosed in this specification are not limited by the attached drawings.

[0035] Although the terms "first," "second," etc. are used to describe various elements or components, these elements or components are not limited by these terms. These terms are merely used to distinguish one element or component from another. Accordingly, it should be understood that a "first element or component" referred to below may also be a "second element or component" within the technical scope of the present invention.

[0036] Unless otherwise defined, all terms (including technical and scientific terms) used herein may be used in their common sense to those of ordinary skill in the art to which the present invention pertains. Furthermore, terms defined in commonly used dictionaries are not to be interpreted ideally or excessively unless explicitly and specifically defined otherwise.

[0037] Furthermore, the term "or" is intended to mean an inclusive "or" rather than an exclusive "or." That is, unless otherwise specified or clear from context, "X employs A or B" is intended to mean either of the natural inclusive permutations. That is, if X employs A; X employs B; or X employs both A and B, "X employs A or B" can apply to any of these cases. Furthermore, the term "and / or" as used herein should be understood to refer to and include all possible combinations of one or more of the associated items listed.

[0038] Additionally, it should be understood that the terms "comprises" and / or "comprising" imply the presence of a given feature and / or component, but do not preclude the presence or addition of one or more other features, components, and / or groups thereof. Furthermore, unless otherwise specified or clear from context to refer to the singular form, the singular form in the specification and claims should generally be construed to mean "one or more."

[0039] When a component is referred to as being "connected" or "connected" to another component, it should be understood that it may be directly connected or connected to that other component, but that there may be other components intervening. Conversely, when a component is referred to as being "directly connected" or "connected" to another component, it should be understood that there are no other components intervening.

[0040] When an element or layer is referred to as being "on" or "on" another element or layer, this includes not only directly on the other element or layer, but also whether or not there are other intervening elements or layers. Conversely, when an element is referred to as being "directly on" or "directly on" the other element or layer, this means that there are no intervening elements or layers.

[0041] Spatially relative terms such as "below," "beneath," "lower," "above," and "upper" may be used to easily describe the relationship between one component or another as depicted in the drawings. Spatially relative terms should be understood to include different orientations of the component during use or operation in addition to the orientation depicted in the drawings.

[0042] The purposes and effects of the present invention, as well as the technical configurations for achieving them, will become clearer with reference to the embodiments described in detail below, along with the accompanying drawings. In describing the present invention, detailed descriptions of known functions or configurations will be omitted if they are deemed to unnecessarily obscure the gist of the invention. Furthermore, the terms described below are defined based on their functions in the present invention and may vary depending on the intentions or practices of the user or operator.

[0043] However, the present invention is not limited to the embodiments disclosed below and can be implemented in various other forms. These embodiments are provided solely to ensure the completeness of the present invention and to fully inform those skilled in the art of the scope of the disclosure. The present invention is defined solely by the scope of the claims. Therefore, such definitions should be based on the contents of this specification.

[0044] FIG. 1 illustrates an aircraft (10) having a fan jet (100) installed thereon according to various embodiments of the present disclosure.

[0045] FIG. 2 is a side view of an aircraft (10) in which a fan jet (100) operates in hovering mode according to various embodiments of the present disclosure.

[0046] Referring to FIG. 1, a VTOL aircraft (10) (hereinafter, aircraft (10)) equipped with a variable-shaft fan jet may include a body (11) and a plurality of fan jets (100) installed on the body (11). The fan jets (100) function to provide thrust to the aircraft (10), and may be referred to by various names such as a propulsion unit, a propulsion assembly, a tilt rotor, or an electric ducted fan (EDF).

[0047] In various embodiments of the present disclosure, the aircraft (10) may be operable between a hovering mode in which a plurality of fan jets (100) are arranged in a hover array, and a cruise mode in which the fan jets (100) are arranged in a forward array.

[0048] For example, the mission profile of an aircraft (10) according to various embodiments of the present disclosure may be configured as “hovering mode (takeoff) - transition mode - cruise mode - reverse transition mode - hovering mode (landing).”

[0049] For example, referring to FIG. 2(a) showing a hovering mode and FIG. 2(b) showing a cruise mode, upward thrust is required in the hovering mode and forward thrust is required in the cruise mode, so that in the transition mode, the fan jet (100) can rotate from a vertical direction to a horizontal direction with respect to the aircraft (10). Conversely, in the reverse transition mode, the fan jet (100) can rotate from a horizontal direction to a vertical direction with respect to the aircraft (10).

[0050] Each of the plurality of fan jets (100) installed on the aircraft (10) may include a propeller, a tilt mechanism for the aircraft (10), and an engine (or electric motor). The tilt mechanism for allowing the fan jet (100) to transition in a horizontal direction and a vertical direction with respect to the aircraft (10) may be operable in any suitable manner. For this purpose, the fan jet (100) may be installed to be rotatable with respect to the aircraft (10).

[0051] The aircraft (10) can also be operated in a hovering mode with the fan jets (100) stationary at a predetermined attitude for vertical takeoff and vertical landing. The aircraft (10) can additionally be operated by moving one or more of the plurality of fan jets (100) to operate in different attitudes or change angles relative to the airframe (11) so as to generate vertical thrust. The cruise mode can be operated to perform forward flight of the aircraft (10) and conventional take-off and landing (CTOL).

[0052] In other words, in various embodiments of the present disclosure, the hovering mode and the cruise mode of the aircraft (10) are not determined according to the attitude in which the plurality of fan jets (100) are operated in the horizontal or vertical direction. The cruise mode and the hovering mode of the aircraft (10) are not mutually exclusive, and the degree of inclination of the fan jets (100) can be determined in various ways according to the speed of the aircraft (10), the weather environment, and the strength of the wind, and the plurality of fan jets (100) can be operated in a state in which they are inclining at different angles.

[0053] In other words, the aircraft (10) may have multiple fan jets (100) that can tilt in a horizontal direction in cruise mode and can be oriented in a vertical direction in hover mode. However, each of the multiple fan jets (100) may be independently tilted in any suitable direction between cruise mode and hover mode.

[0054] FIG. 3 is a side view of an aircraft (10) in which a fan jet (100) according to various embodiments of the present disclosure operates in cruise mode. FIG. 4 is an exploded perspective view of a fan jet (100) according to various embodiments of the present disclosure.

[0055] FIG. 3 illustrates only the essential components for explaining embodiments of the present invention, and the fan jet (100) may further include other components. For example, the fan jet (100) may further include an engine for rotating the fan (140) and a mechanism for operating the front blade (130) relative to the front duct (120).

[0056] Referring to FIG. 4, the fan jet (100) may include a main body housing (110), a front duct (120), a front wing (130), and a fan (140).

[0057] In one embodiment, the main body housing (110) can accommodate a fan (140). A front duct (120) can be coupled to the front of the main body housing (110). By rotating the fan (140), air introduced (or channeled) through the front duct (120) can pass through the rear of the main body housing (110), thereby generating thrust. One or more main body cases (111) can be coupled to the exterior of the main body housing (110). The main body housing (110), the main body cases (111), and the front duct (120) can be connected to each other through fasteners (e.g., nuts and bolts, rivets, etc.) or welding.

[0058] In one embodiment, the front duct (120) may include a front duct case (121), a front ring (122), and a front rib (123).

[0059] The front duct case (121) may be a part connected to the main body housing (110) and the main body case (111). The front ring (122) is positioned spaced apart from the front of the front duct case (121) and may be connected to the front duct case (121) by a front rib (123).

[0060] FIG. 5 is a plan view of the front duct (120) of a fan jet (100) according to various embodiments of the present disclosure, viewed from the front, with the front wing (130) open.

[0061] Referring to FIG. 5, when the front duct (120) is viewed from the front, the front ring (122) can be positioned at the front of the front duct case (121) so that the front ring (122) is positioned in the internal space of the front duct case (121).

[0062] Referring again to FIG. 4, in one embodiment, a plurality of front ribs (123) may be arranged spaced apart from each other in the circumferential direction of the front duct case (121). For example, the front ribs (123) may be arranged between the front duct case (121) and the front ring (122) at equal intervals. In another example, the front ribs (123) may be arranged between the front duct case (121) and the front ring (122) at different intervals.

[0063] A side intake port (124) may be formed between the front duct case (121) and the front ring (122). The side intake port (124) may be divided into a plurality by the front rib (123).

[0064] Referring again to FIG. 5, the front duct (120) may include a central main intake (125) and a plurality of side intakes (124) arranged around the main intake (125). The main intake (125) may be an opening formed in the center of the front ring (122).

[0065] FIG. 6 is a cross-sectional view of a fan jet (100) with the front wing (130) closed according to various embodiments of the present disclosure.

[0066] When the side intake (124) is closed by the movement of the front wing (130), the fan (140) can generate thrust by using the air intaked through the main intake (125).

[0067] FIG. 7 is a cross-sectional view of a fan jet (100) with the front wing (130) open according to various embodiments of the present disclosure.

[0068] When the side intake (124) is opened by the movement of the front wing (130), the fan (140) can form thrust using the air sucked in through the main intake (125) and the side intake (124).

[0069] Referring to FIGS. 6 and 7, the front duct (120) may include a front duct case (121) connected to the main body housing (110), and a front ring (122) positioned spaced apart from the front of the front duct case (121). The front duct case (121) and the front ring (122) may be connected by a plurality of front ribs (123) that are arranged separately in the circumferential direction of the front ring (122).

[0070] The space between the front duct case (121) and the front ring (122) separated by the front rib (123) can be defined as a side intake (124).

[0071] Air is sucked into the interior of the fan jet (100) through the main intake (125) and / or the side intake (124) at the center of the front ring (122), and vertical thrust or horizontal propulsion force can be formed by the rotation of the fan (140).

[0072] The front duct (120) may include a plurality of front wings (130) configured to open and close the side intakes (124).

[0073] Referring to FIG. 6, when the front wing (130) closes the side intake (124), the outer surface of the front wing (130) can be configured to have a shape that conforms to the outer surface of the main body housing (110) (or main body case (111)).

[0074] This allows the propulsive force generated by the fan jet (100) to be reduced by minimizing air resistance when the fan jet (100) is in a horizontal position in cruise mode.

[0075] In other words, the front wing (130) serves to close the side intake (124). The front wing (130) has a shape that follows the outer surface of the main body housing (110) or the main body case (111), thereby contributing to minimizing air resistance in the cruise mode of the fan jet (100).

[0076] The side intake (124) may be configured to be opened or closed by the front wing (130). The side intake (124) can manage the air intake required during operation of the fan jet (100) or during flight of the aircraft (10).

[0077] That is, by opening and closing the front wing (130) for the side intake (124), the fan jet (100) can increase the efficiency of propulsion by minimizing air resistance in the cruising mode and can control the inflow of air into the side intake (124).

[0078] Referring to FIG. 7, when the front wing (130) opens the side intake (124), the front wing (130) may be positioned below (or rearward in the horizontal direction) the portion where the side intake (124) is located.

[0079] The front wing (130) can close the side intake port (124) by contacting the front duct case (121) and the front ring (122) at the top and bottom, and the front wing (130) can open the side intake port (124) by moving outward from the front duct case (121) and the front ring (122) and then moving downward.

[0080] In one embodiment, the front wing (130) can open or close the side intake (124) by a mechanism (not shown) connected to the front duct case (121) or the main body housing (110). The mechanism for actuating the front wing (130) can have an electric or hydraulic actuator as a driving source.

[0081] When the front wing (130) is in an open state, it is positioned below the position of the side intake (124), thereby improving the vertical thrust of the fan jet (100) through the static lift for the front wing (130).

[0082] Figure 8 is an enlarged view of part A of the fan jet (100) illustrated in Figure 7.

[0083] Referring to Fig. 8, the lower inner surface (131) of the front wing (130) may correspond to the shape of the outer surface of the front duct case (121). The upper inner surface (132) of the front wing (130) may correspond to the outer surface (122b) of the front ring (122).

[0084] In Fig. 8, the front wing (130) can be positioned below the side intake (124) (or inlet) with the side intake (124) open. At this time, since the first air flow (f1) flowing outside the front wing (130) is faster than the second air flow (f2) flowing inside the front wing (130), the front wing (130) can provide static lift in the upward direction.

[0085] In one embodiment, the inner surface (121a) of the front duct case (121) may have a greater curvature (c1) than the outer surface of the front duct case (121) facing it. By having the inner surface (121a) of the front duct case (121) have a greater curvature (c1), the third air flow (f3) sucked into the side intake (124) may have a higher speed, and by increasing the amount of air sucked through the side intake (124), the thrust generated by the fan (140) may also be increased.

[0086] The front ring inner surface (122a) and the front ring outer surface (122b) of the front ring (122) may have different curvatures. In one embodiment, the second curvature (c2) of the front ring inner surface (122a) may have a smaller curvature than the third curvature (c3) of the front ring outer surface (122b). For example, the front ring inner surface (122a) may be substantially flat. By having a difference in the curvature of the inner and outer surfaces of the front ring (122), the front ring (122) may provide additional thrust in the vertical direction.

[0087] A variable fan jet (100) according to one embodiment of the present disclosure includes a main body housing (110) that accommodates a fan (140) that provides thrust, and a front duct (120) connected to the front of the main body housing (110), wherein the front duct (120) may include: a front duct case (121) connected to the main body housing (110); a front ring (122) positioned spaced apart from the front of the front duct case (121); one or more front ribs (123) that connect the front duct case (121) and the front ring (122); and a front wing (130) configured to open and close a side intake (124) formed between the front duct case (121) and the front ring (122).

[0088] In one embodiment of the present disclosure, the fan jet (100) is rotatably installed relative to the fuselage (11) of the aircraft (10) and can be positioned horizontally or vertically, and when the fan jet (100) is in a horizontal direction relative to the fuselage (11) of the aircraft (10), the front wing (130) can be positioned to close the side intake (124), and when the fan jet (100) is in a vertical direction relative to the fuselage (11) of the aircraft (10), the front wing (130) can be positioned to open the side intake (124).

[0089] In one embodiment of the present disclosure, the upper inner surface (132) of the front wing (130) has a shape corresponding to the outer surface of the front ring (122), the lower inner surface (131) has a shape corresponding to the outer surface of the front duct case (121), and the front wing (130) has a shape such that, when the side intake port (124) is closed, the lower inner surface (131) contacts the front duct case (121), the upper inner surface (132) contacts the front ring (122), and the outer surface of the front wing (130) follows the shape of the outer surface of the main body housing (110), and the front wing (130) can be movably positioned rearward of the inlet of the side intake port (124) when the side intake port (124) is opened.

[0090] In one embodiment, the inner surface (121a) of the front duct case (121), which defines the inlet of the side intake (124) in the front duct case (121), may have a greater curvature than the outer surface.

[0091] In one embodiment, the front ring (122) may have a wing shape in which the front ring inner surface (122a) has a smaller curvature than the front ring outer surface (122b).

[0092] In the specific embodiments of the present disclosure described above, components of the electronic device included in the present disclosure are expressed singularly or plurally, depending on the specific embodiment presented. However, the singular or plural expressions for the components are selected to suit the presented situation for convenience of explanation, and the present disclosure is not limited to singular or plural components. Components expressed in plural may be composed of singular elements, or components expressed in singular may be composed of plural elements.

[0093] While the detailed description of this disclosure has described specific embodiments, it should be understood that various modifications are possible without departing from the scope of this disclosure. Therefore, the scope of this disclosure should not be limited to the described embodiments, but should be determined not only by the scope of the claims described below, but also by equivalents thereof.

[0094] The description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be applied to other embodiments without departing from the scope of the present invention. Therefore, the present invention is not intended to be limited to the embodiments disclosed herein, but is to be construed in the broadest scope consistent with the principles and novel features disclosed herein.

[0095] The variable fan jet according to the embodiments of the present application can bring about a dramatic improvement in the performance of the aircraft, such as speed and weight, and is expected to have high industrial applicability in the aircraft field where the fan jet is applied.

Claims

1. In variable fan jets, a main body housing accommodating a fan providing thrust, and Includes a front duct connected to the front of the main body housing, The above forward duct: A front duct case connected to the above main body housing; A front ring positioned spaced apart from the front of the above front duct case; One or more front ribs connecting the front duct case and the front ring; and A front wing configured to open and close a side intake formed between the front duct case and the front ring, Variable fan jet.

2. In paragraph 1, The above fan jet is rotatably installed relative to the aircraft's fuselage and can be positioned horizontally or vertically, When the fan jet is horizontal to the fuselage of the aircraft, the front wing is positioned to close the side intake, The front wing is positioned to open the side intake when the fan jet is vertical to the fuselage of the aircraft. Variable fan jet.

3. In paragraph 2, The upper inner surface of the above front wing has a shape corresponding to the outer surface of the above front ring, and the lower inner surface has a shape corresponding to the outer surface of the above front duct case. The front wing has a shape in which the lower inner surface contacts the front duct case, the upper inner surface contacts the front ring, and the outer surface of the front wing follows the shape of the outer surface of the main body housing, while the side intake is closed. The front wing is movable so as to be positioned rearward of the inlet of the side intake when the side intake is open. Variable fan jet.

4. In paragraph 1, The inner surface of the front duct case, which defines the inlet of the side intake in the front duct case, has a greater curvature than the outer surface. Variable fan jet.

5. In paragraph 4, The inner surface of the front ring of the above front ring may have a wing shape having a smaller curvature than the outer surface of the front ring. Variable fan jet.

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