CN101307773B - Aviation electronic oil fuel pump sealing method - Google Patents
Aviation electronic oil fuel pump sealing method Download PDFInfo
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- CN101307773B CN101307773B CN2008101126656A CN200810112665A CN101307773B CN 101307773 B CN101307773 B CN 101307773B CN 2008101126656 A CN2008101126656 A CN 2008101126656A CN 200810112665 A CN200810112665 A CN 200810112665A CN 101307773 B CN101307773 B CN 101307773B
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- snap ring
- fuel pump
- sealer
- housing
- sealing
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Abstract
The invention discloses a sealing method of an aero electronic fuel pump, belonging to an aero-engine technical field. The sealing method comprises the following five steps: cleaning and grinding, mounting a snap ring, pouring sealant to seal the fuel pump, heating and solidifying the sealant, and checking the state of sealing. A ring-shaped structure with an L-shaped cross section of the snap ring closely combines a shell of the electronic fuel pump and the inner surface of the snap ring by the adhesion and solidification of the sealant, the solidified sealant, with a certain degree of flexibility, can play the role of sealing when the outside temperature changes. Low temperature examining test on the ground and dozens of flight tests prove that the method can ensure the electronic fuel pump works regularly in various climate conditions, the method can be applied to the sealing of congeneric fuel pumps or other pumps.
Description
Technical field
The present invention relates to a kind of encapsulating method of aviation electronic oil fuel pump, belong to the aero engine technology field.
Background technique
The oil-fired system of aircraft is the guarantee of engine reliable work.Oil-fired system mainly comprises fuel pump, fuel tank, pipeline, oil filter and instrument etc., and fuel oil flow to motor from fuel tank by pipeline under the driving of fuel pump.The civilian motor that mostly is external import that the high and medium unmanned aircraft of domestic present use uses is as power plant.Wherein the usage requirement of electronic fuel pump is defined under the 5000m height, and ambient temperature is more than-25 ℃.And the height of domestic use has often reached more than 7000 meters, and ambient temperature reaches-40 ℃, head and shoulders above its former factory rules and regulations fixed.Find in actual use, when the electronic fuel pump of certain h type engine h is lower than-32 ℃ in temperature, it oil leakage phenomenon occurs in conjunction with the side end face, representative engine vehicle fuel pump structure schematic representation as shown in fig. 1, side end face 1 is the bottom surface 3 of oil outlet 2 on the fuel pump and the junction between the housing 4, on the actual fuel pump, the bottom surface 3 of described oil outlet 2 is to be made by nonmetallic material (plastics), and housing 4 is to be made by metallic material (aluminium), that is to say that bottom surface 3 and housing 4 are that the material with different heat expansion coefficient is made, when therefore under high-altitude low temperature environment, using the engine fuel injection pump of the type, inevitably can exist expansion coefficient difference to cause poorly sealed owing to two kinds of materials.Especially under high altitude environment in the fuel pump and the pressure difference of external environment strengthen, the leakage of oil situation further worsens.Fuel pump leakage of oil under high-altitude low temperature environment will cause the reduction of fuel pump ability to work, influence the motor proper functioning.Some parts is in the hot environment during engine operation, and the leakage of fuel oil also brings hidden danger to flight safety.The Domestic market lacks the product that can replace this fuel pump, and therefore, fuel pump low temperature leakage of oil problem has limited the high-altitude of motor and aircraft and used.
Summary of the invention
The objective of the invention is to use the leakage problems of engine fuel injection pump existence at existing high-altitude, a kind of encapsulating method of aviation electronic oil fuel pump is provided, the sealing method is obturaging and certain process step by fixing, the sealer of snap ring, reach and reinforce the fuel pump end face, the purpose of sealing fuel pump.
Encapsulating method of the present invention comprises:
Described snap ring is to have certain thickness loop configuration body, and the two ends of snap ring are through hole, and the diameter D of one of them through hole equals the internal diameter of snap ring, greater than the external diameter of housing; The diameter d of another through hole is less than the internal diameter of snap ring, and greater than the external diameter 0.1～0.5mm of housing, the longitudinal section of snap ring is two relative " L " shapes, and the height setting of snap ring is fair with the base upper surface of fuel pump after installation.
The invention has the advantages that (1) encapsulating method of the present invention can solve fuel pump high-altitude low temperature leakage of oil problem under the prerequisite that does not change original fuel oil pump performance; (2) snap ring that uses in the encapsulating method of the present invention is simple in structure, easy to process; (3) sealer that uses in the encapsulating method of the present invention is general fuel tank sealer, obtains easily, and cost is low.
Description of drawings
Fig. 1 is the structural representation of exemplary electronic fuel pump;
The snap ring structural representation of Fig. 2 for using among the present invention;
Fig. 3 is the longitudinal section of the snap ring structure used among the present invention;
The snap ring scheme of installation of Fig. 4 for using among the present invention;
Fig. 5 is for being placed on the fuel pump to be sealed on the support among the present invention;
Fig. 6 is the fuel pump of good seal among the present invention.
Among the figure: 1-side end face, 2-oil outlet, 3-bottom surface, 4-housing, 401-sealing surfaces, 402-fixed surface, the 5-filler opening, 6-wiring terminal, 7-base, 8-snap ring, 801-snap ring internal surface, the 802-through hole, 803-through hole, 804-snap ring interior angle, 9-support, 10-rack ventilating hole.
Embodiment
The present invention is described in further detail below in conjunction with accompanying drawing.
The present invention is a kind of encapsulating method of aviation electronic oil fuel pump.Described electronic fuel pump has structure as shown in Figure 1, comprise side end face 1, oil outlet 2, bottom surface 3, housing 4, filler opening 5, the base 7 of wiring terminal 6 and wiring terminal, side end face 1 is the place that fuel blow takes place easily, utilize encapsulating method provided by the invention, at first snap ring 8 is enclosed within the bottom position of fuel pump housing 4 along the direction of filler opening 5, snap ring 8 is stuck in the below of housing 4, in snap ring 8, water sealer then, the pouring height of sealer and the upper surface flush of the base 7 of wiring terminal 6, so just just can the side end face 1 that easy generation fuel oil is revealed be enclosed in the sealer, effectively realized the sealing to aviation electronic oil fuel pump, it is as follows specifically to seal step:
(1) cleans the sealing surfaces 401 of fuel pump housing 4 and the oil stain of snap ring 8 internal surfaces 801 with gasoline earlier, clean sealing surfaces 401 and internal surface 801 with acetone again, use the sealing surfaces 401 of anhydrous alcohol wiping snap ring 8 internal surfaces 801 and housing 4 at last.
(2) with raw emery paper with snap ring 8 internal surfaces 801 and housing 4 sealing surfaces 401 hackings, make 401 two surfaces of internal surface 801 and sealing surfaces have coarse surface structure.
Above-mentioned internal surface 801 with snap ring 8 is made method processing snap ring 8 internal surfaces 801 that coarse method also can be used turning,
Make its internal surface 801 fine recesses occur, improve its surperficial roughness.
Described snap ring 8 is to have certain thickness loop configuration, and as Fig. 2, the two ends of snap ring 8 are through hole, and wherein the diameter D of through hole 802 equals the internal diameter of snap ring 8, greater than the external diameter of housing 4; The diameter d of through hole 803 is less than the internal diameter of snap ring 8, as can see from Figure 3, the longitudinal section of snap ring 8 is two relative " L " shapes, above the distance of two remote points be exactly the diameter D of through hole 802, below the distance of two proximal points be exactly the diameter d of through hole 803, snap ring 8 outer surface diameter are C, and the height of snap ring 8 is B, as Fig. 3.Wherein the diameter d of through hole 803 is greater than the external diameter 0.1～0.5mm of housing 4, and base 7 upper surfaces that are connected with wiring terminal 6 on the setting fuel pump and the distance between snap ring 8 lower surfaces are b, as Fig. 1, then has the height B of snap ring 8 identical with the distance b of fuel pump upper end.Under the prerequisite that guarantees snap ring Final 8's degree and rigidity, snap ring 8 thickness should reduce as far as possible, and to reduce weight, for weight reduction with reduce volume, snap ring 8 should be processed into ring.
Described snap ring 8 can be made by duralumin, also can be made by other metallic material.
At first, on the internal surface 801 of the sealing surfaces 401 of fuel pump housing 4 and snap ring 8, be coated with one deck sealer respectively, especially to coat a little sealer at interior angle 804 places of snap ring 8, make that interior angle 804 junction points at fixed surface 402 and snap ring 8 fill up sealer.With snap ring 8 through holes 802 upwards, be enclosed within along filler opening 5 on the housing 4 of fuel pump then, as shown in Figure 4, the through hole 803 on the snap ring 8 just can be stuck in the fixed surface 402 of housing 4.The fuel pump that will install snap ring 8 at last is placed on the pre-designed support that has rack ventilating hole 10 9, as shown in Figure 5, the diameter of rack ventilating hole 10 is less than the external diameter C of snap ring 8, but inner diameter d greater than snap ring 8, therefore after fuel pump being installed, just can be so that snap ring 8 is seated on the support 9, and fuel pump makes fixed surface 402 stable contacts of snap ring interior angle 804 and housing 4 under action of gravity.
Described support 9 also can be any frock that has with support 9 identical functions, as being vice.
After being fixed on fuel pump on the support 9, just sealant pouring and sealing can have been implemented.Pour sealer the inside of snap ring 8 into slowly, with the space between the sealing surfaces 401 of the internal surface 801 of snap ring 8 and housing 4 all fill in even, fill up sealer, the sealer that fills up is no more than the upper surface of wiring terminal base 7, as Fig. 6.
When filling with sealant, to constantly evenly stir, not have bubble.
The sealer that is adopted is the XM22B sealer.
Its housing 4 of electronic fuel pump after the sealing and snap ring 8 internal surfaces 801 and sealer close adhesion, the sealer after the curing has certain elasticity, therefore, can both play the effect of sealing when the cold and hot temperature variation in the external world.Prove that through ground low temperature certification test and tens of flight tests the sealing method can guarantee the proper functioning of electronic fuel pump under various weather conditions, this method can be applied to the sealing of similar fuel pump or other pump housing.
Claims (5)
1. the encapsulating method of an aviation electronic oil fuel pump is characterized in that comprising the steps:
Step 1, cleaning and polishing; Described cleaning is meant earlier cleans the outer surface of fuel pump housing and the oil stain of snap ring internal surface with gasoline, cleans the two surface with acetone again, uses the anhydrous alcohol wiping at last; Described polishing be exactly with raw emery paper with snap ring internal surface and housing outer surface hacking, make two surfaces of internal surface and outer surface have coarse surface structure;
Step 2, installation snap ring; At first, on the internal surface of the outer surface of fuel pump housing and snap ring, be coated with one deck sealer respectively, interior angle place at snap ring coats a little sealer, then snap ring is enclosed within along filler opening on the housing of fuel pump, the fuel pump that will install snap ring at last is placed on the pre-designed support that has the hole;
Step 3, filling sealer, the sealing fuel pump; Pour sealer the inside of snap ring into slowly, with the space between the outer surface of the internal surface of snap ring and housing all fill in even, fill up sealer, the sealer that fills up is no more than the upper surface of wiring terminal base;
Step 4, sealer is heating and curing; With the fuel pump of good seal together with support be placed on heat between or carry out heat preservation solidification in the baking box, solidifying temperature is 47 ℃～49 ℃, be 46～50 hours curing time;
Step 5, inspection sealing situation; Check that the fuel pump outward appearance does not have bulging, sealer is even and do not have bubble, then good seal.
2. the encapsulating method of a kind of aviation electronic oil fuel pump according to claim 1, it is characterized in that: described snap ring is to have certain thickness loop configuration body, the two ends of snap ring are through hole, and the diameter D of one of them through hole equals the internal diameter of snap ring, greater than the external diameter of housing; The diameter d of another through hole is less than the internal diameter of snap ring, and greater than the external diameter 0.1～0.5mm of housing, the longitudinal section of snap ring is two relative " L " shapes, and the height setting of snap ring is fair with the base upper surface of fuel pump after installation.
3. the encapsulating method of a kind of aviation electronic oil fuel pump according to claim 1, it is characterized in that: the described method that makes the snap ring internal surface have coarse surface structure uses the method for turning to make its internal surface fine recesses occur in addition.
4. the encapsulating method of a kind of aviation electronic oil fuel pump according to claim 1, it is characterized in that: described support also comprises with vice and replacing.
5. the encapsulating method of a kind of aviation electronic oil fuel pump according to claim 1, it is characterized in that: described sealer is the XM22B sealer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2008101126656A CN101307773B (en) | 2008-05-26 | 2008-05-26 | Aviation electronic oil fuel pump sealing method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2008101126656A CN101307773B (en) | 2008-05-26 | 2008-05-26 | Aviation electronic oil fuel pump sealing method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101307773A CN101307773A (en) | 2008-11-19 |
| CN101307773B true CN101307773B (en) | 2010-09-08 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2008101126656A Expired - Fee Related CN101307773B (en) | 2008-05-26 | 2008-05-26 | Aviation electronic oil fuel pump sealing method |
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| CN (1) | CN101307773B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102338001B (en) * | 2011-09-13 | 2012-11-21 | 芜湖宇舸瑞汽车电子有限公司 | Oil discharge method used after detecting electric-spray oil pump and oil pump realizing same |
| KR102076961B1 (en) * | 2015-04-10 | 2020-02-13 | 햄린 일렉트로닉스 (쑤저우) 코. 엘티디. | Encapsulated Electrical Device and Manufacturing Method |
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2008
- 2008-05-26 CN CN2008101126656A patent/CN101307773B/en not_active Expired - Fee Related
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| Publication number | Publication date |
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| CN101307773A (en) | 2008-11-19 |
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20100908 Termination date: 20120526 |