CN108087148A

CN108087148A - A kind of infrared stealth jet pipe and with its aircraft

Info

Publication number: CN108087148A
Application number: CN201711309973.3A
Authority: CN
Inventors: 刘帅; 叶留增; 许羚; 杜寅威; 石岩
Original assignee: AECC Shenyang Engine Research Institute
Current assignee: AECC Shenyang Engine Research Institute
Priority date: 2017-12-11
Filing date: 2017-12-11
Publication date: 2018-05-29

Abstract

The invention discloses a kind of infrared stealth jet pipe and with its aircraft.The infrared stealth jet pipe includes first segment and the rectification section being connected with the first segment；Wherein, the first segment includes the first wall, second wall opposite with first wall, the 3rd wall and fourth wall opposite with the 3rd wall；Second wall is to the first wall direction protrusion, so as to form raised section；First is formed between the raised section and the 3rd wall and expands passage；Second is formed between the raised section and the 4th wall and expands passage.The aeroperformance of the infrared stealth jet pipe jet pipe of the application is better than S bending nozzles, and on the premise of can ensureing that hot-end component effectively blocks, reduces jet pipe offset distance, be conducive to body integrated design after aircraft.It can reduce jet pipe offset distance while ensureing that hot-end component effectively blocks, be conducive to body integrated design after aircraft, and improve jet pipe aeroperformance.

Description

Infrared stealthy spray tube and aircraft with same

Technical Field

The invention relates to the technical field of spray pipes, in particular to an infrared stealth spray pipe and an airplane with the infrared stealth spray pipe.

Background

The exhaust system is the most main infrared radiation source of an aircraft, the infrared radiation of the exhaust system mainly comes from tail jet flow and a nozzle thermal cavity, the infrared radiation intensity of the exhaust system can be generally reduced by shielding high-temperature components of the exhaust system, an S-shaped nozzle is a typical nozzle thermal cavity shielding technology, the center line of the nozzle is a double-S-shaped curve, a certain offset distance exists between the center line and the axis of a turbine, gas is deviated from the center line through a 1 st S-shaped bent channel, and the gas returns to the axis position through a 2 nd S-shaped bent channel, so that the high-temperature components such as the turbine blade, a central cone and the like are effectively shielded, and the infrared radiation is.

However, the bending center line characteristic of the nozzle results in larger offset distance of the nozzle, the integrated design difficulty of the rear body of the aircraft is increased, and the performance loss of the nozzle is increased by the bending center line characteristic.

Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.

Disclosure of Invention

It is an object of the present invention to provide an infrared stealth nozzle that overcomes or at least mitigates at least one of the above-mentioned disadvantages of the prior art.

In order to achieve the purpose, the invention provides an infrared stealth spray pipe which comprises a first section 6 and a rectification section connected with the first section; wherein,

the first segment includes a first wall, a second wall opposite the first wall, a third wall, and a fourth wall opposite the third wall;

the second wall is convex towards the first wall, so that a convex section is formed;

a first expansion channel is formed between the convex section and the third wall; a second expansion channel is formed between the convex section and the fourth wall.

Preferably, one end of the rectifying section is connected to one end of the first section;

the end face of the other end of the rectifying section is a spray pipe outlet section.

Preferably, the space between the maximum position of the protrusion of the convex section and the wall surface of the first wall is referred to as a protrusion pole space, and the distance of the protrusion pole space in the first direction is not less than the inlet diameter of the nozzle.

Preferably, the maximum position of the projection section is the maximum position of the projection section in the first direction.

The application also provides an aircraft comprising the infrared stealth nozzle.

The utility model provides an infrared stealthy spray tube' S aerodynamic performance is superior to the S curved spray tube to can guarantee under the prerequisite that hot junction part effectively sheltered from, reduce the spray tube offset distance, be favorable to the design of aircraft afterbody integration. The offset distance of the spray pipe can be reduced while the effective shielding of the hot end part is ensured, the integrated design of the rear body of the aircraft is facilitated, and the aerodynamic performance of the spray pipe is improved.

Drawings

Fig. 1 is a schematic structural diagram of an infrared stealth nozzle according to a first embodiment of the present application.

Fig. 2 is another schematic structural view of the infrared stealth nozzle shown in fig. 1.

Fig. 3 is another schematic structural view of the infrared stealth nozzle shown in fig. 1.

Fig. 4 is another schematic structural view of the infrared stealth nozzle shown in fig. 1.

Fig. 5 is another schematic structural view of the infrared stealth nozzle shown in fig. 1.

Reference numerals:

1	first stage	13	Third wall
				2	Rectifying section	14	The fourth wall
11	First wall	121	Convex section
				12	Second wall	141	Second expansion channel
131	First expansion channel	21	Cross section of jet pipe outlet
				3	Space of raised poles

Detailed Description

In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present invention and for simplifying the description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the scope of the present invention.

Fig. 1 is a schematic structural diagram of an infrared stealth nozzle according to a first embodiment of the present application. Fig. 2 is another schematic structural view of the infrared stealth nozzle shown in fig. 1. Fig. 3 is another schematic structural view of the infrared stealth nozzle shown in fig. 1. Fig. 4 is another schematic structural view of the infrared stealth nozzle shown in fig. 1.

In the present embodiment, the first direction is the B direction shown in fig. 4.

The infrared stealth nozzle shown in fig. 1 to 4 comprises a first section 1 and a rectifying section 2 connected with the first section 1; wherein,

the first segment 1 comprises a first wall 11, a second wall 12 opposite to said first wall 11, a third wall 13 and a fourth wall 14 opposite to the third wall 13;

the second wall 12 is convex in the direction of the first wall, thereby forming a convex section 121;

a first expansion channel 131 is formed between the convex segment 121 and the third wall 13; the protruding section 121 and the fourth wall 14 form a second expansion channel 141 therebetween.

Referring to fig. 3, in the present embodiment, one end of the rectifying section 2 is connected to one end of the first section 1;

the end face of the other end of the fairing section 2 is a nozzle outlet section 21.

Referring to fig. 3, in the present embodiment, the space between the maximum position of the protrusion section and the wall surface of the first wall is referred to as a protrusion pole space 3, and the distance between the protrusion pole space 3 in the first direction is not less than the inlet diameter of the nozzle.

Referring to fig. 3, in the present embodiment, the maximum protrusion position of the convex section is the maximum position of the convex section in the first direction.

Referring to FIGS. 1-4, the length of the convex section 121 is L1, and the width of the nozzle is greater than the width of the convex section, i.e., W ≧ B (B in FIG. 4, W in FIG. 5);

the height and the width of the convex section at the convex pole space 3 reach the maximum, the maximum width of the convex section at the position is not smaller than the diameter of the inlet of the spray pipe, namely B is larger than or equal to D (B in figure 4 and D in figure 2), and the area of the convex pole space 3 is about 80-90% of the area of the inlet of the spray pipe;

referring to fig. 3, the convex segment 121 extends obliquely toward the rectifying segment, the extending portion becomes a descending segment, the length of the segment is L2, the height and width of the convex segment of the segment are gradually reduced to 0 along the axial direction, and the passage area is gradually reduced along the axial direction;

referring to fig. 3, the axis of the fairing section 2 is parallel to the turbine outlet axis and has a length L3;

referring to fig. 4, the first wall of the space of the raised pole is arched, the second wall is in the same horizontal line with the lowest point of the nozzle inlet, and the nozzle outlet section 21 has a larger width-to-height ratio to increase the shielding rate of the nozzle hot cavity.

The utility model provides an infrared stealthy spray tube compares with the curved spray tube of S, when can guaranteeing that hot end part effectively shelters from, reduces the spray tube offset distance, and has improved the pneumatic performance of spray tube. The lower wall height and the width of protruding section increase gradually along the axial and form the protruding utmost point space of convex closure, the convex closure maximum width in protruding utmost point space is greater than spray tube import diameter, in order to guarantee effectively sheltering from to the hot junction part, the first wall in protruding utmost point space is close with the protruding closure shape in protruding utmost point space, and spray tube outlet section 21 has great width-to-height ratio, protruding utmost point space can increase the rate of sheltering from with spray tube outlet section 21 combined action, thereby when guaranteeing that the hot junction part shelters from the effect, the spray tube structural design of big offset has been avoided. The convex hull is wrapped by the outer wall surfaces of two sides of the spray pipe, part of air flow can flow to the outlet of the spray pipe through the second expansion channels and the first expansion channels on two sides of the convex hull, the flow area of the section molded surface 2 is increased, the flow speed of the air flow in the convex section is reduced, the flow loss of the air flow in the convex section 1 is relatively reduced, the flow direction of the air flow is adjusted to be close to the axial direction by the rectifying section 2, and the performance loss of the spray pipe is reduced as much as possible.

Finally, it should be pointed out that: the above examples are only for illustrating the technical solutions of the present invention, and are not limited thereto. Although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.

Claims

1. The infrared stealth spray pipe is characterized by comprising a first section (1) and a rectifying section (2) connected with the first section (1); wherein,

the first segment (1) comprises a first wall (11), a second wall (12) opposite the first wall (11), a third wall (13) and a fourth wall (14) opposite the third wall (13);

the second wall (12) is convex towards the first wall direction, thereby forming a convex section (121);

a first expansion channel (131) is formed between the convex section (121) and the third wall (13); a second expansion channel (141) is formed between the convex section (121) and the fourth wall (14).

2. The infrared stealth lance of claim 1, wherein one end of said fairing section (2) is connected to one end of said first section (1);

the end face of the other end of the rectifying section (2) is a nozzle outlet section (21).

3. The infrared stealth nozzle of claim 2, wherein a wall space from a maximum projection position of the convex section to the first wall is referred to as a maximum projection space (3), and a distance of the maximum projection space (3) in the first direction is not less than an inlet diameter of the nozzle.

4. The infrared stealth nozzle of claim 3, wherein a maximum position of a projection of the raised section is a maximum position of the raised section in the first direction.

5. An aircraft, characterized in that the aircraft comprises an infrared stealth nozzle as claimed in any one of claims 1 to 4.