CN112922744B - Wall-embedded aircraft fuel conveying device - Google Patents
Wall-embedded aircraft fuel conveying device Download PDFInfo
- Publication number
- CN112922744B CN112922744B CN202110243808.2A CN202110243808A CN112922744B CN 112922744 B CN112922744 B CN 112922744B CN 202110243808 A CN202110243808 A CN 202110243808A CN 112922744 B CN112922744 B CN 112922744B
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- Prior art keywords
- aircraft
- nozzle
- wall
- embedded
- fuel
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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
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
- F02C7/222—Fuel flow conduits, e.g. manifolds
Abstract
The invention discloses a wall-embedded aircraft fuel conveying device, and particularly relates to the technical field of aircraft fuel conveying structures. The wall-embedded aircraft fuel conveying device comprises a sandwich structure embedded in a jetting block, wherein the sandwich structure is composed of a sealing plate and a base body welded on the sealing plate by laser, a sandwich flow channel is arranged between the sealing plate and the base body, an inlet nozzle communicated with a fuel storage tank on an aircraft and an outlet nozzle positioned above the inlet nozzle are arranged on the base body, and the outlet nozzle is communicated with a jetting cavity of the aircraft. The technical scheme of the invention solves the problem that the fuel conveying device in the existing wall-embedded aircraft can damage the overall aerodynamic appearance of the aircraft, and can be used for conveying the fuel of the wall-embedded aircraft.
Description
Technical Field
The invention relates to the technical field of aircraft fuel conveying structures, in particular to a wall-embedded aircraft fuel conveying device.
Background
The wall-embedded aircraft uses a ramjet engine as a propulsion power device, and the ramjet engine generally comprises an air inlet channel, an isolation section, a combustion chamber 1, a tail nozzle and other parts.
The aircraft engine is located at the top of the aircraft and receives compressed high-speed incoming flow into the engine combustion chamber during flight, fuel is injected into the combustion chamber 1 through the injection block 2 on the outer wall surface of the combustion chamber 1 and is mixed with the incoming flow of air for combustion, and the fuel is provided by the fuel storage tank 3 located in the abdominal cabin section of the aircraft, so that when the engine works, the fuel is conveyed into the injection block 2 on the outer wall surface of the aircraft combustion chamber 1 from the fuel storage tank 3 in the internal cabin of the aircraft through some conveying device.
The conventional conveying method is to convey fuel to the injection block 2 of the combustion chamber 1 by crossing the outer wall surface through a fuel pipe 4, the structural layout of the conventional conveying method is shown in figure 1, if a conventional pipeline mode is adopted, the exposed fuel pipeline 4 must exist on the outer wall surface of an aircraft, the aerodynamic appearance of the aircraft is damaged, the aerodynamic resistance is increased, even if remedial measures are adopted, a layer of skin is wrapped outside the pipeline, the overall structure is bloated, and the structural complexity is increased.
Disclosure of Invention
The invention aims to provide a wall-embedded aircraft fuel conveying device, which solves the problem that the overall aerodynamic shape of an aircraft can be damaged by the fuel conveying device in the existing wall-embedded aircraft.
In order to achieve the purpose, the technical scheme of the invention is as follows: the wall-embedded aircraft fuel conveying device comprises a sandwich structure embedded in a jetting block, wherein the sandwich structure is composed of a sealing plate and a base body welded on the sealing plate by laser, a sandwich flow channel is arranged between the sealing plate and the base body, an inlet nozzle communicated with a fuel storage tank on an aircraft and an outlet nozzle positioned above the inlet nozzle are arranged on the base body, and the outlet nozzle is communicated with a jetting cavity of the aircraft.
Furthermore, the diameter of the interlayer flow channel is gradually narrowed from the outlet pipe nozzle to the inlet pipe nozzle, and the diameters of the outlet pipe nozzle and the inlet pipe nozzle are both larger than the maximum diameter of the interlayer flow channel.
Furthermore, two annular sealing grooves are formed in the outlet nozzle, and a sealing ring matched with the side wall of the injection cavity is arranged in each annular sealing groove.
Through the arrangement, the sealing performance of the outlet nozzle and the injection cavity can be ensured by utilizing the sealing ring.
Compared with the prior art, the beneficial effect of this scheme:
1. the scheme avoids the damage of the exposed fuel pipeline on the outer wall surface of the aircraft to the aerodynamic appearance of the aircraft by an embedded installation mode on the outer wall surface of the aircraft.
2. Each dismouting of this scheme is convenient, and is easily changed, has good maintainability.
3. The scheme has good sealing performance under the condition of bearing high pressure.
Drawings
FIG. 1 is a schematic diagram of a prior art wall-embedded aircraft fuel delivery apparatus;
FIG. 2 is a schematic structural view of a wall-embedded aircraft fuel delivery apparatus of the present embodiment;
FIG. 3 is a front view of a wall-embedded aircraft fuel delivery apparatus of the present embodiment;
fig. 4 isbase:Sub>A cross-sectional viewbase:Sub>A-base:Sub>A of fig. 3.
Detailed Description
The invention is explained in more detail below by means of specific embodiments:
reference numerals in the drawings of the specification include: the device comprises a combustion chamber 1, a spray injection block 2, a fuel storage tank 3, a fuel pipeline 4, a sandwich structure 5, a sealing plate 6, a base body 7, a sandwich flow channel 8, an outlet nozzle 9, an inlet nozzle 10 and a sealing groove 11.
Examples
As shown in fig. 2 to 4: the utility model provides an embedded aircraft fuel delivery device of wall, is including inlaying sandwich structure 5 of establishing on the embedded aircraft lateral wall of wall, sandwich structure 5's lateral wall is to the lateral wall of aircraft corresponding face to the parallel and level to guarantee leveling of aircraft surface, reached and not changed the purpose of not destroying the aerodynamic appearance of aircraft. Sandwich structure 5 is formed by a cover plate 6 and a base body 7 laser welded to cover plate 6. The shrouding 6, the same position department all opens threaded hole on base member 7 and the aircraft lateral wall, and threaded hole internal thread connects countersunk screw to fix this device on the aircraft with the help of countersunk screw. An interlayer flow passage 8 is arranged between the closing plate 6 and the substrate 7, the diameter of the interlayer flow passage 8 is gradually narrowed from an outlet nozzle 9 to an inlet nozzle 10, the interlayer flow channel 8 can bear 1500K high-temperature airflow for heating, the highest pressure for conveying fuel can reach 15Mpa, and the high-temperature air-flow fuel conveying device is suitable for severe use environments, safe and reliable. The diameter of the outlet nozzle 9 and the diameter of the inlet nozzle 10 are both larger than the maximum diameter of the interlayer flow channel 8. An inlet pipe nozzle 10 communicated with the fuel storage tank 3 on the aircraft and an outlet pipe nozzle 9 positioned above the inlet pipe nozzle 10 are arranged on the base body 7, the inlet pipe nozzle 10 is positioned on the lower side of the base body 7, a standard pipe joint is arranged at the free end of the inlet pipe nozzle 10, and the other end of the pipe joint penetrates through the side wall of the inner cabin of the aircraft and is communicated with the fuel storage tank 3. The outlet nozzle 9 penetrates through the wall surface of the aircraft and is communicated with an injection cavity of the aircraft, and the free end of the outlet nozzle 9 is in interference fit with the injection cavity to ensure the sealing property. Two annular sealing grooves 11 are formed in the outlet nozzle 9, and a sealing ring matched with the side wall of the injection cavity is arranged in each annular sealing groove 11.
By adopting the scheme, the fuel can be conveyed to the injection cavity of the injection block 2 through the fuel storage tank 3, the inlet pipe nozzle 10, the interlayer flow channel 8 and the outlet pipe nozzle 9, and the function of conveying the fuel in the inner cabin to the injection block 2 on the outer wall surface is realized.
The foregoing are merely examples of the present invention and common general knowledge of known specific structures and/or features of the schemes has not been described herein in any greater detail. It should be noted that, for those skilled in the art, without departing from the structure of the present invention, several variations and modifications can be made, which should also be considered as the protection scope of the present invention, and these will not affect the effect of the implementation of the present invention and the utility of the patent. The scope of the claims of the present application shall be determined by the contents of the claims, and the description of the embodiments and the like in the specification shall be used to explain the contents of the claims.
Claims (2)
1. An aircraft fuel delivery device of embedded wall, its characterized in that: the jet nozzle comprises a sandwich structure embedded in a jet block, wherein the sandwich structure consists of a sealing plate and a substrate welded on the sealing plate by laser, a sandwich channel is arranged between the sealing plate and the substrate, the substrate is provided with an inlet nozzle communicated with a fuel storage tank on an aircraft and an outlet nozzle positioned above the inlet nozzle, and the outlet nozzle is communicated with a jet cavity of the aircraft;
the diameter of the interlayer flow channel is gradually narrowed from the outlet pipe nozzle to the inlet pipe nozzle, and the diameters of the outlet pipe nozzle and the inlet pipe nozzle are both larger than the maximum diameter of the interlayer flow channel.
2. A wall-embedded aircraft fuel delivery apparatus according to claim 1, wherein: and two annular sealing grooves are arranged on the outlet nozzle, and a sealing ring matched with the side wall of the injection cavity is arranged in each annular sealing groove.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110243808.2A CN112922744B (en) | 2021-03-05 | 2021-03-05 | Wall-embedded aircraft fuel conveying device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110243808.2A CN112922744B (en) | 2021-03-05 | 2021-03-05 | Wall-embedded aircraft fuel conveying device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112922744A CN112922744A (en) | 2021-06-08 |
| CN112922744B true CN112922744B (en) | 2023-01-06 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110243808.2A Active CN112922744B (en) | 2021-03-05 | 2021-03-05 | Wall-embedded aircraft fuel conveying device |
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| CN112922744A (en) | 2021-06-08 |
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