CN114233511A - Spray pipe with aircraft exhaust stealth vector grid - Google Patents
Spray pipe with aircraft exhaust stealth vector grid Download PDFInfo
- Publication number
- CN114233511A CN114233511A CN202111454526.3A CN202111454526A CN114233511A CN 114233511 A CN114233511 A CN 114233511A CN 202111454526 A CN202111454526 A CN 202111454526A CN 114233511 A CN114233511 A CN 114233511A
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- outlet
- grid
- spray pipe
- vector
- blade
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/06—Varying effective area of jet pipe or nozzle
- F02K1/11—Varying effective area of jet pipe or nozzle by means of pivoted eyelids
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
- F02K1/82—Jet pipe walls, e.g. liners
- F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infra-red radiation suppressors
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
- F02K1/82—Jet pipe walls, e.g. liners
- F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infra-red radiation suppressors
- F02K1/825—Infra-red radiation suppressors
Abstract
The invention relates to a spray pipe with an aircraft exhaust stealth vector grid, belonging to the technical field of aircraft stealth; the spray pipe comprises a spray pipe body, wherein a hidden vector grid is arranged at an outlet of the spray pipe body, the hidden vector grid comprises a flow guide grid and a vector adjusting assembly, the flow guide grid is fixed on the inner peripheral wall of an S-shaped bent section of the outlet of the spray pipe body, and the vector adjusting assembly is connected with the flow guide grid and is positioned outside the outlet of the spray pipe body; the flow guide grid is composed of a plurality of transverse blade grids and a plurality of longitudinal blade grids; the vector adjusting assembly comprises an adjustable cascade, an upper outlet adjusting plate, a lower outlet adjusting plate, an outlet side baffle and a sliding rod; the sliding rod slides along the longitudinal direction to drive the adjustable blade grids to rotate relative to the transverse blade grids of the flow guide grids, and the upper adjusting plate and the lower adjusting plate of the outlet rotate relative to the upper edge and the lower edge of the outlet of the spray pipe. The guide grids and the adjustable blade grids effectively shield the internal parts of the spray pipe and the turbine, so that the turbine has better infrared stealth performance when the center offset distance of the inlet and outlet surfaces is smaller.
Description
Technical Field
The invention belongs to the technical field of aircraft stealth, and particularly relates to a spray pipe with an aircraft exhaust stealth vector grid.
Background
Modern wars put higher demands on infrared stealth capability of aircrafts and radar stealth capability, and jet nozzles of aircraft engines are the main infrared radiation sources and important radar scattering sources on airplanes. The S-shaped spray pipe is a common stealthy spray pipe and is bent to enable the center line of the spray pipe to be S-shaped, so that internal parts of the spray pipe are shielded, and stealthy performance is improved. However, for the prior art, the main problem is that the center offset distance of the inlet and outlet surfaces is required to be larger if the S-shaped spray pipe is used for realizing full shielding of the part, so that the structural weight is increased, and the S-shaped spray pipe is difficult to be matched with an airplane in geometry. On the other hand, the thrust vectoring technology can significantly improve the maneuverability of the aircraft, and is generally realized by arranging a vectoring mechanism at the outlet of a spray pipe.
In order to realize the small-offset full shielding and vector control functions of the S-shaped bent spray pipe at the same time, patent CN103423026A provides a vector cascade for enhancing the stealth capability of the S-shaped bent binary spray pipe, the shielding effect is enhanced through a group of angle-adjustable cascade, and the vector control function is provided, and the patent has the defects that when the vector adjustment is carried out, the attack angle of the cascade is changed, so that certain flow loss is caused, and meanwhile, when the cascade is adjusted, two cascade channels close to the upper wall surface and the lower wall surface cannot keep equal-area circulation, so that local flow loss is easily caused.
Disclosure of Invention
The technical problem to be solved is as follows:
in order to avoid the defects of the prior art, the invention provides the spray pipe with the aircraft exhaust stealth vector grid, which combines the stealth shielding function and the vector control function. The grid is arranged at the outlet of the spray pipe, so that the infrared radiation shielding capability of the spray pipe under a smaller center offset distance is improved; the invisible shielding capability is further enhanced through the adjustable cascade at the rear part of the grating, and simultaneously, the vector control function is realized through a simpler structure.
The technical scheme of the invention is as follows: the utility model provides a spray tube with stealthy vector grid of aircraft exhaust, includes the spray tube body, its characterized in that: the outlet of the spray pipe body is provided with a stealth vector grid, the stealth vector grid comprises a flow guide grid 2 and a vector adjusting assembly, the flow guide grid 2 is fixed on the inner peripheral wall of an S-shaped section 1 of the outlet of the spray pipe body, and the vector adjusting assembly is connected with the flow guide grid 2 and is positioned on the outer side of the outlet of the spray pipe body;
the flow guide grid 2 is composed of a plurality of transverse blade grids and a plurality of longitudinal blade grids, the transverse blade grids are arranged in parallel along the longitudinal direction of the outlet, and the longitudinal blade grids are arranged in parallel along the transverse direction of the outlet; the cross section of the transverse blade cascade is arc-shaped, so that the airflow attack angle of the transverse blade cascade is 0 degree;
the vector adjusting assembly comprises an adjustable cascade 3, an upper outlet adjusting plate 4, a lower outlet adjusting plate 5, an outlet side baffle 6 and a sliding rod 7; the plurality of adjustable blade grids 3 are longitudinally arranged in parallel along the outlet of the spray pipe and are arranged in one-to-one correspondence with the plurality of transverse blade grids of the flow guide grid 2; the front end of each adjustable blade cascade 3 is connected with the rear end of the corresponding transverse blade cascade through a revolute pair; the upper outlet adjusting plate 4 and the lower outlet adjusting plate 5 are respectively hinged to the upper edge and the lower edge of the outlet of the spray pipe, and the two outlet side baffle plates 6 are fixed along the extending direction of the two sides of the outlet of the spray pipe; two vertically arranged slide bars 7 are positioned at two sides of the outlet of the spray pipe and are respectively and rotatably connected with two sides of the plurality of adjustable cascades 3, the outlet upper adjusting plate 4 and the outlet lower adjusting plate 5;
the sliding rod 7 slides along the longitudinal direction to drive the adjustable blade grids 3 to rotate relative to the transverse blade grids of the flow guide grid 2, and the outlet upper adjusting plate 4 and the outlet lower adjusting plate 5 rotate relative to the upper edge and the lower edge of the outlet of the spray pipe, so that the vector control of the air flow can be realized.
The further technical scheme of the invention is as follows: the inlet section of the flow guide grid 2 is vertical to the central line of the spray pipe so as to ensure that the attack angle of the blade grid is 0 degree.
The further technical scheme of the invention is as follows: in the flow guide grid 2, the curvature of the profile of the transverse blade cascade adjacent to the lower wall surface of the S-shaped bent section 1 is consistent with the curvature of the lower wall surface of the S-shaped bent section 1, the curvature of the profile of the transverse blade cascade adjacent to the upper wall surface of the S-shaped bent section 1 is consistent with the curvature of the upper wall surface of the S-shaped bent section 1, and the curvature of the transverse blade cascade in the middle gradually changes from top to bottom.
The further technical scheme of the invention is as follows: the plurality of transverse blade grids are arranged at equal intervals, and the interval between every two adjacent transverse blade grids is 25-30 mm.
The further technical scheme of the invention is as follows: the number of the longitudinal blade grids is more than or equal to 0, and the guide grid 2 is only composed of the transverse blade grids when the number of the longitudinal blade grids is equal to 0.
The further technical scheme of the invention is as follows: the longitudinal blade grids are arranged at equal intervals, and the interval between adjacent longitudinal blade grids is 30-60 mm.
The further technical scheme of the invention is as follows: the front edge of the blade grid of the flow guide grid 2 is arc-shaped or wedge-shaped.
The further technical scheme of the invention is as follows: the surface of the blade grid of the flow guide grid 2 is made of metal or a coating stealth material.
The further technical scheme of the invention is as follows: the flow guide grid 2 is solid or hollow, and the surface of the blade grid is a smooth surface or is provided with air film cooling holes.
The further technical scheme of the invention is as follows: the two slide bars 7 are respectively and rotatably connected with the middle parts of two sides of the plurality of adjustable blade cascades 3, the outlet upper adjusting plate 4 and the outlet lower adjusting plate 5.
Advantageous effects
The invention has the beneficial effects that: the invention has the following advantages that the hidden grating and the adjustable cascade are additionally arranged at the outlet of the S-shaped spray pipe:
1. the curved guide grids and the adjustable blade grids effectively shield the internal parts of the spray pipe and the turbine, so that the turbine has better infrared stealth performance when the center offset distance of the inlet and outlet surfaces is smaller. In order to reduce solid radiation caused by the invisible grids, a low-emissivity material can be coated on the surfaces of the flow guide grids or the flow guide grids can be subjected to air film cooling. As shown in fig. 9 and 10, the angular distributions of the infrared radiation intensity of 3-5 micrometers in the rear direction of the spray pipe in the horizontal direction and the pitching direction in the embodiment 1 are respectively given, as shown in the figure, the infrared radiation intensity of the spray pipe in the forward direction and the backward direction is remarkably reduced no matter in the horizontal direction or the pitching direction, and as can be seen from fig. 10, in the embodiment 1, most angles in the pitching direction of the present invention realize shielding of high temperature components in the spray pipe, the infrared radiation intensity is remarkably reduced, and complete shielding is not realized only in the pitching direction of 5 degrees;
2. because the flow guide grating is of a fixed structure, the attack angle of the airflow of the flow guide grating is not changed in the vector adjustment process, so that the guiding effect on the airflow is enhanced;
3. because the main flow direction in the S-shaped spray pipe is consistent with the direction of the central line, the entrance section of the flow guide grid 2 is vertical to the central line of the spray pipe, so that the attack angle of most of the blade grids can be ensured to be 0 degree, and the flow loss is reduced;
4. the adjustable cascade realizes the vector adjusting function of the S-shaped spray pipe, and the equal-area circulation of each cascade channel is ensured because the upper and lower adjusting plates and the grid plate of the adjustable cascade rotate together;
5. the transverse blade grid spacing of the flow guide grid is 25 mm-30 mm, the longitudinal blade grid spacing is 30 mm-60 mm, the size is 1/2 of the wavelength of the electromagnetic wave of the C waveband, and the flow guide grid has a shielding effect on the electromagnetic wave of the C waveband and the electromagnetic wave of a longer wavelength waveband.
Drawings
FIG. 1 is an overall view of an aircraft exhaust stealth vector grid and a nozzle applied thereto according to the present invention;
FIG. 2 is a partial cutaway view of an aircraft exhaust stealth vector grid and a nozzle applied thereto according to the present invention;
FIG. 3 is a front view of an aircraft exhaust stealth vector grid and its applied nozzle in the direction of the outlet according to the present invention;
FIG. 4 is a cross-sectional view of an aircraft exhaust stealth vector grid and a nozzle used therewith taken along a central symmetry plane in accordance with the present invention;
FIG. 5 is a partial cross-sectional view of an aircraft exhaust stealth vector grid in accordance with the present invention;
FIG. 6 is a schematic view of an aircraft exhaust stealth vector grid according to the present invention;
FIG. 7 is a partial schematic view of a portion of the components of an aircraft exhaust stealth vector grid according to the present invention connected by revolute pairs;
FIG. 8 is a schematic view of the vector adjustment operation of the aircraft exhaust stealth vector grid according to the present invention;
FIG. 9 is a diagram showing a distribution of an infrared integrated radiation intensity in a backward horizontal direction of the nozzle in example 1;
FIG. 10 is a graph of the IR integrated radiation intensity distribution in the pitch direction of the nozzle of example 1.
Description of reference numerals: 1, S bending section; 2. a flow-guiding grille; 3. adjustable cascade; 4. an adjusting plate is arranged on the outlet; 5. an outlet lower adjustment plate; 6. an outlet side baffle; 7. a slide bar.
Detailed Description
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.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like, indicate orientations and positional relationships based on those shown in the drawings, and are used only for convenience of description and simplicity of description, and 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 considered as limiting the present invention.
Referring to fig. 1-5, the spray pipe with the aircraft exhaust stealth vector grid comprises a spray pipe body, wherein the stealth vector grid is arranged at the outlet of the spray pipe body, the stealth vector grid comprises a flow guide grid 2 and a vector adjusting assembly, the flow guide grid 2 is fixed on the inner peripheral wall of an S-shaped section 1 at the outlet of the spray pipe body, and the vector adjusting assembly is connected with the flow guide grid 2 and is positioned outside the outlet of the spray pipe body;
referring to fig. 6 and 7, the flow guiding grid 2 is composed of a plurality of transverse blade cascades and a plurality of longitudinal blade cascades, and the inlet section of the flow guiding grid is perpendicular to the central line of the spray pipe. The plurality of transverse blade grids are arranged in parallel along the longitudinal direction of the outlet, and the plurality of longitudinal blade grids are arranged in parallel along the transverse direction of the outlet; the cross section of the transverse blade cascade is arc-shaped, so that the attack angle of airflow of the transverse blade cascade is 0 degree, and the shielding effect is achieved on the inner part of the spray pipe while the flow guiding effect is achieved;
in the flow guide grid 2, the curvature of the profile of the transverse blade cascade adjacent to the lower wall surface of the S-shaped bent section 1 is consistent with the curvature of the lower wall surface of the S-shaped bent section 1, the curvature of the profile of the transverse blade cascade adjacent to the upper wall surface of the S-shaped bent section 1 is consistent with the curvature of the upper wall surface of the S-shaped bent section 1, and the curvature of the transverse blade cascade in the middle gradually changes from top to bottom.
Referring to fig. 8, the vector adjusting assembly comprises an adjustable cascade 3, an upper outlet adjusting plate 4, a lower outlet adjusting plate 5, an outlet side baffle 6 and a sliding rod 7; the plurality of adjustable blade grids 3 are longitudinally arranged in parallel along the outlet of the spray pipe and are arranged in one-to-one correspondence with the plurality of transverse blade grids of the flow guide grid 2; the front end of each adjustable blade cascade 3 is connected with the rear end of the corresponding transverse blade cascade through a revolute pair; the upper outlet adjusting plate 4 and the lower outlet adjusting plate 5 are respectively hinged to the upper edge and the lower edge of the outlet of the spray pipe, and the two outlet side baffle plates 6 are fixed along the extending direction of the two sides of the outlet of the spray pipe; two vertically arranged slide bars 7 are positioned at two sides of the outlet of the spray pipe and are respectively and rotatably connected with two sides of the plurality of adjustable cascades 3, the outlet upper adjusting plate 4 and the outlet lower adjusting plate 5;
the sliding rod 7 is slid along the longitudinal direction to drive the adjustable blade grids 3 to rotate relative to the transverse blade grids of the flow guide grid 2, so that the vector control of airflow is realized, and the infrared shielding effect of the spray pipe is increased after the rotation; the upper outlet adjusting plate 4 and the lower outlet adjusting plate 5 are driven to rotate relative to the upper edge and the lower edge of the outlet of the spray pipe so as to ensure the circulation capacity of the outlet.
Example 1:
the utility model provides a spray tube with stealthy vector grid of aircraft exhaust which characterized in that: the device comprises an S bending section 1, a flow guide grid 2, an adjustable cascade 3, an outlet upper adjusting plate 4, an outlet lower adjusting plate 5, an outlet side baffle 6 and a slide bar 7;
the flow guide grid 2 is placed at an outlet of the S-shaped bent section 1 and is welded with the inner wall surface of the S-shaped bent section 1; the flow guide grid 2 is composed of a transverse blade grid and a longitudinal blade grid, wherein the profile of the transverse blade grid is of an arc structure, the radius of the transverse blade grid positioned at the lowest part is 1.05m, the radius of the transverse blade grid positioned at the uppermost part is 2.86m, and the radius of the transverse blade grid positioned in the middle is linearly distributed along with the longitudinal distance, so that the flow guide effect is realized, and the shielding effect is achieved on the inner part of the spray pipe; the front end of the adjustable blade grid 3 is connected with the rear end of the transverse blade grid of the flow guide grid 2 through a revolute pair; the middle section of the adjustable blade cascade 3 is connected with the sliding rod 7 through a revolute pair, when the sliding rod 7 longitudinally slides, the adjustable blade cascade 3 is driven to rotate around the revolute pair at the front end, the vector control of airflow is realized, and meanwhile, the infrared shielding effect of the spray pipe is increased after the adjustable blade cascade 3 rotates; the upper outlet adjusting plate 4 and the lower outlet adjusting plate 5 are connected with the sliding rod 7 through a revolute pair in the middle section, and when the sliding rod 7 longitudinally slides, the upper outlet adjusting plate 4 and the lower outlet adjusting plate 5 rotate together with the adjustable blade cascade 3 to ensure the outlet circulation capacity.
The transverse blade grid spacing of the exhaust stealth grid is 26 mm;
the number of the longitudinal blade grids of the exhaust stealth grid is 0;
the emissivity of the wall surface of the exhaust stealth grating is 0.25.
Example 2:
the utility model provides a spray tube with stealthy vector grid of aircraft exhaust which characterized in that: the device comprises an S bending section 1, a flow guide grid 2, an adjustable cascade 3, an outlet upper adjusting plate 4, an outlet lower adjusting plate 5, an outlet side baffle 6 and a slide bar 7;
the flow guide grid 2 is placed at the outlet of the S-shaped bent section 1 and is welded with the wall surface of the S-shaped bent section 1; the flow guide grid 2 consists of 19 transverse blades longitudinally distributed along the spray pipe, the profile of the blade grid is an arc, the radius of the blade grid at the lowest part is 1.05m, the radius of the blade grid at the uppermost part is 2.86m, and the radius of the blade grid at the middle part is linearly distributed along with the longitudinal distance, so that the flow guide effect is realized, and the shielding effect is realized on the interior of the spray pipe; the front end of the adjustable blade grid 3 is connected with the rear end of the flow guide grid 2 through a revolute pair; the middle section of the adjustable blade cascade 3 is connected with the sliding rod 7 through a revolute pair, when the sliding rod 7 longitudinally slides, the adjustable blade cascade 3 is driven to rotate around the revolute pair at the front end, the vector control of airflow is realized, and meanwhile, the infrared shielding effect of the spray pipe is increased after the adjustable blade cascade 3 rotates; the upper outlet adjusting plate 4 and the lower outlet adjusting plate 5 are connected with the sliding rod 7 through a revolute pair in the middle section, and when the sliding rod 7 longitudinally slides, the upper outlet adjusting plate 4 and the lower outlet adjusting plate 5 rotate together with the adjustable blade cascade 3 to ensure the outlet circulation capacity.
The transverse blade grid spacing of the exhaust stealth grid is 30 mm;
the distance between the longitudinal blade grids of the exhaust stealth grid is 30 mm;
the transverse blade grids of the exhaust stealth grid are of hollow structures, and the thickness of the transverse blade grids is 5 mm; the surface of the blade is provided with film cooling holes.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made in the above embodiments by those of ordinary skill in the art without departing from the principle and spirit of the present invention.
Claims (10)
1. The utility model provides a spray tube with stealthy vector grid of aircraft exhaust, includes the spray tube body, its characterized in that: a stealth vector grid is arranged at the outlet of the spray pipe body, the stealth vector grid comprises a flow guide grid (2) and a vector adjusting assembly, the flow guide grid (2) is fixed on the inner peripheral wall of an S-shaped bent section (1) of the outlet of the spray pipe body, and the vector adjusting assembly is connected with the flow guide grid (2) and is positioned outside the outlet of the spray pipe body;
the flow guide grid (2) is composed of a plurality of transverse blade grids and a plurality of longitudinal blade grids, the transverse blade grids are arranged in parallel along the longitudinal direction of the outlet, and the longitudinal blade grids are arranged in parallel along the transverse direction of the outlet; the cross section of the transverse blade cascade is arc-shaped, so that the airflow attack angle of the transverse blade cascade is 0 degree;
the vector adjusting assembly comprises an adjustable cascade (3), an upper outlet adjusting plate (4), a lower outlet adjusting plate (5), an outlet side baffle (6) and a sliding rod (7); the plurality of adjustable blade grids (3) are longitudinally arranged in parallel along the outlet of the spray pipe and are arranged in one-to-one correspondence with the plurality of transverse blade grids of the flow guide grid (2); the front end of each adjustable blade cascade (3) is connected with the rear end of the corresponding transverse blade cascade through a revolute pair; the upper outlet adjusting plate (4) and the lower outlet adjusting plate (5) are respectively hinged to the upper edge and the lower edge of the outlet of the spray pipe, and the two outlet side baffles (6) are fixed along the extending direction of the two sides of the outlet of the spray pipe; two vertically arranged sliding rods (7) are positioned at two sides of the outlet of the spray pipe and are respectively and rotatably connected with two sides of the plurality of adjustable blade cascades (3), the outlet upper adjusting plate (4) and the outlet lower adjusting plate (5);
the sliding rod (7) slides along the longitudinal direction to drive the adjustable blade grids (3) to rotate relative to the transverse blade grids of the flow guide grid (2), and the upper adjusting plate (4) and the lower adjusting plate (5) of the outlet rotate relative to the upper edge and the lower edge of the outlet of the spray pipe, so that the vector control of the air flow can be realized.
2. The nozzle with an aircraft exhaust stealth vector grid according to claim 1, wherein: the inlet section of the flow guide grid (2) is vertical to the central line of the spray pipe so as to ensure that the attack angle of the blade grid is 0 degree.
3. The nozzle with an aircraft exhaust stealth vector grid according to claim 1, wherein: in the flow guide grid (2), the curvature of the profile of the transverse blade grid adjacent to the lower wall surface of the S-shaped bent section (1) is consistent with the curvature of the lower wall surface of the S-shaped bent section (1), the curvature of the profile of the transverse blade grid adjacent to the upper wall surface of the S-shaped bent section (1) is consistent with the curvature of the upper wall surface of the S-shaped bent section (1), and the curvature of the transverse blade grid in the middle gradually changes from top to bottom.
4. The nozzle with an aircraft exhaust stealth vector grid according to claim 1, wherein: the plurality of transverse blade grids are arranged at equal intervals, and the interval between every two adjacent transverse blade grids is 25-30 mm.
5. The nozzle with an aircraft exhaust stealth vector grid according to claim 1, wherein: the number of the longitudinal blade cascades is more than or equal to 0, and the guide grid (2) is only composed of the transverse blade cascades when the number of the longitudinal blade cascades is equal to 0.
6. The nozzle with an aircraft exhaust stealth vector grid according to claim 1, wherein: the longitudinal blade grids are arranged at equal intervals, and the interval between adjacent longitudinal blade grids is 30-60 mm.
7. The nozzle with an aircraft exhaust stealth vector grid according to claim 1, wherein: the front edge of the cascade of the diversion grating (2) is arc-shaped or wedge-shaped.
8. The nozzle with an aircraft exhaust stealth vector grid according to claim 1, wherein: the surface of the blade grid of the flow guide grid (2) is made of metal or a coating stealth material.
9. The nozzle with an aircraft exhaust stealth vector grid according to claim 1, wherein: the flow guide grid (2) is solid or hollow, and the surface of the blade grid is a smooth surface or is provided with air film cooling holes.
10. The nozzle with an aircraft exhaust stealth vector grid according to claim 1, wherein: the two sliding rods (7) are respectively and rotatably connected with the middle parts of two sides of the plurality of adjustable blade cascades (3), the outlet upper adjusting plate (4) and the outlet lower adjusting plate (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111454526.3A CN114233511B (en) | 2021-11-27 | 2021-11-27 | Jet pipe with aircraft exhaust stealth vector grid |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111454526.3A CN114233511B (en) | 2021-11-27 | 2021-11-27 | Jet pipe with aircraft exhaust stealth vector grid |
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| Publication Number | Publication Date |
|---|---|
| CN114233511A true CN114233511A (en) | 2022-03-25 |
| CN114233511B CN114233511B (en) | 2023-07-21 |
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| CN202111454526.3A Active CN114233511B (en) | 2021-11-27 | 2021-11-27 | Jet pipe with aircraft exhaust stealth vector grid |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| WO2004061286A1 (en) * | 2002-12-18 | 2004-07-22 | Lockheed Martin Corporation | Apparatus and method for controlling primary fluid flow using secondary fluid flow injection |
| CN103423026A (en) * | 2013-08-09 | 2013-12-04 | 中国航空工业集团公司沈阳发动机设计研究所 | Vector cascade mechanism capable of enhancing stealth of S-shaped bent two-dimensional nozzle |
| CN103993982A (en) * | 2014-04-25 | 2014-08-20 | 西北工业大学 | Double-S-bend infrared stealth spray pipe structure capable of achieving multi-direction thrust vector control |
| CN105201685A (en) * | 2015-09-17 | 2015-12-30 | 中国航空工业集团公司沈阳发动机设计研究所 | S-shaped binary spraying pipe having vector deflection function |
| CN112160846A (en) * | 2020-09-18 | 2021-01-01 | 中国航发四川燃气涡轮研究院 | Self-air-entraining pneumatic thrust vectoring nozzle with S-shaped curved flow passage |
| CN113279860A (en) * | 2021-06-07 | 2021-08-20 | 西北工业大学 | Inner bulge S-shaped air inlet channel with middle control section and method |
-
2021
- 2021-11-27 CN CN202111454526.3A patent/CN114233511B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2004061286A1 (en) * | 2002-12-18 | 2004-07-22 | Lockheed Martin Corporation | Apparatus and method for controlling primary fluid flow using secondary fluid flow injection |
| CN103423026A (en) * | 2013-08-09 | 2013-12-04 | 中国航空工业集团公司沈阳发动机设计研究所 | Vector cascade mechanism capable of enhancing stealth of S-shaped bent two-dimensional nozzle |
| CN103993982A (en) * | 2014-04-25 | 2014-08-20 | 西北工业大学 | Double-S-bend infrared stealth spray pipe structure capable of achieving multi-direction thrust vector control |
| CN105201685A (en) * | 2015-09-17 | 2015-12-30 | 中国航空工业集团公司沈阳发动机设计研究所 | S-shaped binary spraying pipe having vector deflection function |
| CN112160846A (en) * | 2020-09-18 | 2021-01-01 | 中国航发四川燃气涡轮研究院 | Self-air-entraining pneumatic thrust vectoring nozzle with S-shaped curved flow passage |
| CN113279860A (en) * | 2021-06-07 | 2021-08-20 | 西北工业大学 | Inner bulge S-shaped air inlet channel with middle control section and method |
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| Publication number | Publication date |
|---|---|
| CN114233511B (en) | 2023-07-21 |
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