Engine nacelle fairing with inner supporting framework system

Abstract

The invention belongs to the technical field of engine nacelles, and particularly relates to an engine nacelle fairing with an inner supporting framework system.The engine nacelle fairing is reasonable in design and is mainly composed of a rectifying outer cover, a first inner supporting framework, a second inner supporting framework, an arc-shaped air guide pipe and an annular cover plate; a plurality of sets of first positioning protrusions and second positioning protrusions corresponding to the first positioning protrusions are installed in an annular cavity of the rectification outer cover, and the first inner supporting frameworks or the second inner supporting frameworks are connected in an inserted mode through the first positioning protrusions and the second positioning protrusions corresponding to the first positioning protrusions. The first inner supporting framework, the second inner supporting framework and the arc-shaped air guide pipe can be pre-assembled into an inner supporting framework system, the annular cover plate is used for sealing the annular cavity of the rectification outer cover, in this way, the overall compressive strength of the engine nacelle fairing can be greatly improved, and meanwhile heat generated by working of an engine can be used for achieving freezing prevention of the fairing.

Description

Technical Field

[0001] The present invention belongs to the technical field of engine nacelles, and in particular relates to an engine nacelle fairing with an internal support skeleton system. Background Art

[0002] During flight, an aircraft's engines require large quantities of air to maintain normal operation. The air intake fairing, through its special design, forces airflow in a specific direction, typically rearward, ensuring a stable and efficient air supply to the engine. This optimized airflow not only improves engine thrust efficiency but also reduces drag, ultimately enhancing overall aircraft performance. Furthermore, the air intake fairing serves to protect the engine. During flight, an aircraft may encounter various foreign objects, such as birds and hail. Direct impact with the engine can cause serious damage. The air intake fairing acts as a barrier, preventing these foreign objects from directly contacting critical engine components. Even if foreign objects do strike the fairing, its special design and material selection deflect them in a graceful arc, minimizing damage to the engine. Furthermore, the air intake fairing helps reduce noise, which is quite noisy during engine operation. The air intake fairing, through its streamlined design and optimized airflow channel, can effectively reduce the transmission and reflection of noise, thereby reducing the noise level of the aircraft during flight and improving passenger comfort.

[0003] Traditional engine nacelle fairings have shortcomings. First, they lack an internal support frame system, which means their overall compressive strength is not ideal. Second, they cannot use the heat generated by the engine to protect the fairing from freezing. Therefore, it is necessary to optimize and improve the traditional engine nacelle fairing. Summary of the Invention

[0004] The purpose of the present invention is to overcome the above-mentioned problems existing in the prior art and to provide an engine nacelle fairing with an internal support frame system.

[0005] In order to achieve the above technical objectives and the above technical effects, the present invention is implemented through the following technical solutions: The present invention provides an engine nacelle fairing with an internal support frame system, comprising a fairing outer cover, a first internal support frame, a second internal support frame, an arc-shaped air duct and an annular cover plate. The internal support frame system consisting of the first internal support frame, the second internal support frame and the arc-shaped air duct is installed in the inner cavity of the fairing outer cover, and an annular cover plate is installed at the rear port of the fairing outer cover.

[0006] Furthermore, in the above-mentioned engine nacelle fairing, the fairing outer cover includes a reshaped outer cover body, an annular cavity is provided inside the reshaped outer cover body, a plurality of first positioning protrusions are provided on the inner side wall of the reshaped outer cover body located in the annular cavity along the circumferential direction, and a plurality of second positioning protrusions are provided on the outer side wall of the reshaped outer cover body located in the annular cavity along the circumferential direction, and the first positioning protrusions and the corresponding second positioning protrusions are arranged opposite to each other.

[0007] Furthermore, in the above-mentioned engine nacelle fairing, the cross-section of the annular cavity is semi-elliptical, and the ratio of the major axis to the minor axis in the semi-ellipse is 3 to 5:1.

[0008] Furthermore, in the above-mentioned engine nacelle fairing, the first inner support frame is composed of a first inner support block and a threaded rod welded and installed on its outer end, the cross-sectional shape of the first inner support block matches the cross-sectional shape of the annular cavity, and first positioning slots matching the first positioning protrusion or the second positioning protrusion are provided on both sides of the first inner support block; a plurality of first plug-in holes for facilitating the insertion of the arc-shaped air guide tube are provided on the first inner support block; a first plug-in hole is provided at the tip of the first inner support block, and two rows of first plug-in holes staggered with the positions of the first positioning slots are provided at the rear of the tip of the first inner support block.

[0009] Furthermore, in the above-mentioned engine nacelle fairing, the second inner support frame is composed of a second inner support block and an air guide straight pipe screwed onto its outer end, the cross-sectional shape of the second inner support block matches the cross-sectional shape of the annular cavity, and second positioning slots are provided on both sides of the second inner support block to match the first positioning protrusion or the second positioning protrusion; a plurality of second plug-in holes for facilitating the insertion of the arc-shaped air guide pipe are provided on the second inner support block; a second plug-in hole is provided at the tip of the second inner support block, and two rows of second plug-in holes staggered with the second positioning slots are provided at the rear position of the tip of the second inner support block, and a connecting cavity connected to each second plug-in hole and the air guide straight pipe is provided inside the second inner support block.

[0010] Furthermore, in the above-mentioned engine nacelle fairing, two second inner support frames are installed in the annular cavity of the fairing outer cover and the two second inner support frames are symmetrically distributed. The annular cavity of the fairing outer cover is located between the two second inner support frames and multiple first inner support frames are evenly installed. A number of arc-shaped air guide tubes are installed between two adjacent first inner support frames and between the first inner support frames and the second inner support frames.

[0011] Furthermore, in the above-mentioned engine nacelle fairing, among the two second inner support frames, the straight air guide pipe of one of the second inner support frames is externally connected to the air supply end of the engine's high-pressure compressor, and the air extraction end of the engine's high-pressure compressor can extract high-temperature gas near the tail of the engine; the straight air guide pipe of the other second inner support frame serves as an exhaust pipe; and each of the arc-shaped air guide pipes located in the same loop is connected to each other.

[0012] Furthermore, in the above-mentioned engine nacelle fairing, the material of the first inner support block and the second inner support block is titanium alloy, and the material of the arc-shaped air duct and the straight air duct is aluminum alloy; after the first inner support block and the second inner support block are respectively engaged with the first positioning protrusion and the second positioning protrusion, the engaging position is locked by welding.

[0013] Furthermore, in the above-mentioned engine nacelle fairing, the plate body of the annular cover is provided with a through hole for the threaded rod or the straight air guide pipe to pass through.

[0014] Furthermore, in the above-mentioned engine nacelle fairing, the annular cover plate is made of titanium alloy and is fixed to the opening position of the annular cavity of the fairing outer cover by welding.

[0015] The beneficial effects of the present invention are: The engine nacelle fairing provided by the present invention is reasonably designed, and is mainly composed of a fairing outer cover, a first inner support frame, a second inner support frame, an arc-shaped air duct and an annular cover plate. Multiple groups of first positioning protrusions and corresponding second positioning protrusions are installed in the annular cavity of the fairing outer cover. The first positioning protrusions and the corresponding second positioning protrusions are used to plug in the first inner support frame or the second inner support frame. The first inner support frame, the second inner support frame and the arc-shaped air duct can be pre-assembled into an inner support frame system, and the annular cavity of the fairing outer cover is sealed using the annular cover plate. In this way, the overall compressive strength of the engine nacelle fairing can be greatly improved, and the heat generated by the engine operation can be used to achieve anti-freezing of the fairing.

[0016] Of course, any product implementing the present invention does not necessarily need to achieve all of the above advantages at the same time. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following briefly introduces the drawings required for describing the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0018] Figure 1 It is a structural schematic diagram of the engine nacelle fairing of the present invention; Figure 2This is a schematic diagram of the structure of the engine nacelle fairing of the present invention; Figure 3 Schematic diagram of the structure of the fairing cover in the present invention; Figure 4 A half-section schematic diagram of the fairing cover in the present invention; Figure 5 Schematic diagram of the composition of the internal support skeleton system of the present invention; Figure 6 Schematic diagram of the structure of the first inner support frame in the present invention; Figure 7 Schematic diagram of the structure of the second inner support frame in the present invention; Figure 8 Schematic diagram of the structure of the annular cover plate in the present invention; In the accompanying drawings, the components represented by the reference numerals are as follows: 1- fairing cover, 101- shaping cover body, 102- annular cavity, 103- first positioning protrusion, 104- second positioning protrusion; 2-first inner support frame, 201-first inner support block, 202-first positioning slot, 203-first plug hole, 204-threaded rod; 3-second inner support frame, 301-second inner support block, 302-second positioning slot, 303-second plug hole, 304-air guide straight pipe; 4-arc-shaped airway; 5-annular cover, 501-perforated. DETAILED DESCRIPTION

[0019] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making any creative efforts shall fall within the scope of protection of the present invention.

[0020] like Figures 1-8 As shown, this embodiment provides an engine nacelle fairing with an internal support frame system, comprising a fairing outer shell 1, a first internal support frame 2, a second internal support frame 3, an arcuate air duct 4, and an annular cover plate 5. The internal support frame system consisting of the first internal support frame 2, the second internal support frame 3, and the arcuate air duct 4 is installed in the inner cavity of the fairing outer shell 1, and the annular cover plate 5 is installed at the rear end of the fairing outer shell 1.

[0021] In this embodiment, the fairing hood 1 includes a shaped outer cover body 101, an annular cavity 102 is provided inside the shaped outer cover body 101, and a plurality of first positioning protrusions 103 are provided along the circumferential direction on the inner side wall of the shaped outer cover body 101 located in the annular cavity 102, and a plurality of second positioning protrusions 104 are provided along the circumferential direction on the outer side wall of the shaped outer cover body 101 located in the annular cavity, and the first positioning protrusions 103 and the corresponding second positioning protrusions 104 are arranged opposite to each other.

[0022] In this embodiment, the cross section of the annular cavity 102 is semi-elliptical, and the ratio of the major axis to the minor axis in the semi-elliptical shape is 3 to 5:1.

[0023] In this embodiment, the first inner support skeleton 2 is composed of a first inner support block 201 and a threaded rod 204 welded and installed at its outer end. The cross-sectional shape of the first inner support block 201 cooperates with the cross-sectional shape of the annular cavity 102. Both sides of the first inner support block 201 are provided with first positioning grooves 202 that cooperate with the first positioning protrusion 103 or the second positioning protrusion 104; the first inner support block 201 is provided with a plurality of first plug-in holes 203 for facilitating the insertion of the arc-shaped air guide tube 4; the first inner support block 201 is provided with a first plug-in hole 203 at its tip, and the first inner support block 201 is provided with two rows of first plug-in holes 203 staggered with the positions of the first positioning grooves 202 at the rear position of the tip.

[0024] In this embodiment, the second inner support frame 3 is composed of a second inner support block 301 and a straight air guide tube 304 screwed onto its outer end. The cross-sectional shape of the second inner support block 301 matches the cross-sectional shape of the annular cavity 102. Second positioning slots 302 are provided on both sides of the second inner support block 301 to cooperate with the first positioning protrusion 103 or the second positioning protrusion 104. The second inner support block 301 is provided with a plurality of second insertion holes 303 for convenient insertion of the arc-shaped air guide tube 4; the second inner support block 301 is provided with a second insertion hole 303 at its tip, and two rows of second insertion holes 303 are provided behind the tip of the second inner support block 301, which are staggered relative to the second positioning slots 302. The interior of the second inner support block 301 is provided with a connecting cavity that communicates with each second insertion hole 303 and the straight air guide tube 304.

[0025] In this embodiment, two second inner support frames 3 are installed in the annular cavity 102 of the fairing outer cover 1, and the two second inner support frames 3 are symmetrically distributed. The annular cavity 102 of the fairing outer cover 1 is located between the two second inner support frames 3 and multiple first inner support frames 2 are evenly installed. A number of arc-shaped air guide tubes 4 are installed between two adjacent first inner support frames 2 and between the first inner support frames 2 and the second inner support frames 3.

[0026] In this embodiment, among the two second inner support frames 3, the straight air guide pipe 304 of one of the second inner support frames 3 is externally connected to the air supply end of the engine's high-pressure compressor, and the air extraction end of the engine's high-pressure compressor can extract high-temperature gas near the tail of the engine; the straight air guide pipe 304 of the other second inner support frame 3 serves as an exhaust pipe; and the arc-shaped air guide pipes 4 located in the same loop are connected to each other.

[0027] In this embodiment, the first inner support block 201 and the second inner support block 301 are made of titanium alloy, and the arc-shaped air guide tube 4 and the straight air guide tube 304 are made of aluminum alloy; after the first inner support block 201 and the second inner support block 301 are respectively engaged with the first positioning protrusion 103 and the second positioning protrusion 104, the engaged position is locked by welding.

[0028] In this embodiment, the plate body of the annular cover plate 5 is provided with a through hole 501 for the threaded rod 204 or the straight air guide tube 304 to pass through.

[0029] In this embodiment, the annular cover plate 5 is made of titanium alloy and is fixed to the opening of the annular cavity 102 of the fairing outer cover 1 by welding.

[0030] The specific application of this embodiment is as follows: the engine nacelle fairing is mainly composed of a fairing outer cover 1, a first inner support frame 2, a second inner support frame 3, an arc-shaped air duct 4 and an annular cover plate 5. A plurality of first positioning protrusions 103 and corresponding second positioning protrusions 104 are installed in the annular cavity 102 of the fairing outer cover 1. The first positioning protrusions 103 and the corresponding second positioning protrusions 104 are used to plug in the first inner support frame 2 or the second inner support frame 3. The first inner support frame 2, the second inner support frame 3 and the arc-shaped air duct 4 can be preassembled into an inner support frame system. The annular cavity 102 of the fairing outer cover 1 is sealed by the annular cover plate 5. In this way, the overall compressive strength of the engine nacelle fairing can be greatly improved, and the heat generated by the engine operation can be used to achieve antifreeze of the fairing.

[0031] The preferred embodiments of the present invention disclosed above are merely intended to help illustrate the present invention. These preferred embodiments do not exhaustively describe all details, nor do they limit the present invention to specific embodiments. Obviously, many modifications and variations are possible based on the contents of this specification. These embodiments are selected and described in detail in this specification to better explain the principles and practical applications of the present invention, thereby enabling those skilled in the art to better understand and utilize the present invention. The present invention is limited only by the claims and their full scope and equivalents.

Claims

1. An engine nacelle fairing with an internal support frame system, characterized in that: It includes a fairing outer cover, a first inner support frame, a second inner support frame, an arc-shaped air duct and an annular cover. The inner cavity of the fairing outer cover is installed with an inner support frame system consisting of the first inner support frame, the second inner support frame and the arc-shaped air duct, and the rear port of the fairing outer cover is installed with an annular cover.

2. The engine nacelle fairing according to claim 1, characterized in that: The fairing outer cover includes a shaped outer cover body, an annular cavity is provided inside the shaped outer cover body, a plurality of first positioning protrusions are provided on the inner side wall of the shaped outer cover body located in the annular cavity along the circumferential direction, and a plurality of second positioning protrusions are provided on the outer side wall of the shaped outer cover body located in the annular cavity along the circumferential direction, and the first positioning protrusions and the corresponding second positioning protrusions are arranged opposite to each other.

3. The engine nacelle fairing according to claim 2, characterized in that: The cross section of the annular cavity is semi-elliptical, and the ratio of the major axis to the minor axis in the semi-elliptical shape is 3 to 5:

1.

4. The engine nacelle fairing according to claim 3, characterized in that: The first inner support frame is composed of a first inner support block and a threaded rod welded and installed on its outer end. The cross-sectional shape of the first inner support block matches the cross-sectional shape of the annular cavity. First positioning slots that match the first positioning protrusion or the second positioning protrusion are provided on both sides of the first inner support block; a plurality of first plug-in holes for facilitating the insertion of the arc-shaped air guide tube are provided on the first inner support block; a first plug-in hole is provided at the tip of the first inner support block, and two rows of first plug-in holes staggered with the positions of the first positioning slots are provided at the rear of the tip of the first inner support block.

5. The engine nacelle fairing according to claim 4, characterized in that: The second inner support frame is composed of a second inner support block and an air guide straight pipe screwed onto its outer end. The cross-sectional shape of the second inner support block matches the cross-sectional shape of the annular cavity. Second positioning slots that match the first positioning protrusion or the second positioning protrusion are provided on both sides of the second inner support block; a number of second plug-in holes for convenient insertion of the arc-shaped air guide pipe are provided on the second inner support block; a second plug-in hole is provided at the tip of the second inner support block, and two rows of second plug-in holes staggered with the second positioning slots are provided at the rear position of the tip of the second inner support block; a connecting cavity connected to each second plug-in hole and the air guide straight pipe is provided inside the second inner support block.

6. The engine nacelle fairing according to claim 5, characterized in that: Two second inner support frames are installed in the annular cavity of the fairing outer cover and the two second inner support frames are symmetrically distributed. The annular cavity of the fairing outer cover is located between the two second inner support frames and multiple first inner support frames are evenly installed. Several arc-shaped air guide tubes are installed between adjacent two first inner support frames and between the first inner support frame and the second inner support frame.

7. The engine nacelle fairing according to claim 6, characterized in that: Among the two second inner support frames, the straight air guide pipe of one of the second inner support frames is externally connected to the air delivery end of the engine's high-pressure compressor, and the air extraction end of the engine's high-pressure compressor can extract high-temperature gas near the tail of the engine; the straight air guide pipe of the other second inner support frame serves as an exhaust pipe; the arc-shaped air guide pipes located in the same loop are connected to each other.

8. The engine nacelle fairing according to claim 7, characterized in that: The first inner support block and the second inner support block are made of titanium alloy, and the arc-shaped air guide tube and the straight air guide tube are made of aluminum alloy; after the first inner support block and the second inner support block are respectively clamped with the first positioning protrusion and the second positioning protrusion, the clamping position is locked by welding.

9. The engine nacelle fairing according to claim 8, characterized in that: The plate body of the annular cover plate is provided with a through hole for the threaded rod or the straight air guide pipe to pass through.

10. The engine nacelle fairing according to claim 9, characterized in that: The annular cover plate is made of titanium alloy and is fixed to the annular cavity opening of the fairing cover by welding.

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