CN209441665U - A kind of oil supply system of light-duty sport plane - Google Patents
A kind of oil supply system of light-duty sport plane Download PDFInfo
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- CN209441665U CN209441665U CN201822214848.0U CN201822214848U CN209441665U CN 209441665 U CN209441665 U CN 209441665U CN 201822214848 U CN201822214848 U CN 201822214848U CN 209441665 U CN209441665 U CN 209441665U
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- oil
- tank
- fuel
- engine
- wing
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Abstract
The utility model discloses a kind of oil supply systems of light-duty sport plane, it is related to aircraft oil supply system manufacturing technology field, including the integral tank for being set to the wing root leading edge of wing and being constituted with the up-front covering of wing root and rib, oil liquid separating tank to separating oil and impurity, it is connected to the first fuel passage of integral tank and oil liquid separating tank, connect the second fuel passage of the oil inlet of oil liquid separating tank and engine, the integral tank includes left side wing tank and right side wing tank, further includes the vaporizer that engine two sides are arranged in and connect with engine.Left and right wing tank is connected to by the utility model using tee tube, constitutes integral tank, and circulating for fuel oil is not fully utilized using oil outlet pipe composition in engine oil outlet, achievees the purpose that engine " atypical fuel feeding ".Guarantee the lasting fuel feeding to engine, improve fuel utilization ratio, practicability is higher.
Description
Technical field
The utility model relates to aircraft oil supply system manufacturing technology field more particularly to a kind of fuel feeding of light-duty sport plane
System.
Background technique
It for light-duty sport plane, is easy to jolt during flight, and flight attitude is also unlike big
The such flight attitude of type aircraft is stablized, and the unlimited two point form Fuel System entry design of traditional left and right wing tank, is easy to lead
Cause fuel oil suction inlet hanging, engine oil is discontinuous；Traditional oil supply system designs, and gas can not be arranged in time in oil feed line
Out, it is easy to cause fuel feeding unsmooth, cavitation erosion is easily caused to engine, system run all right is influenced, influences flight safety.Aircraft combustion
While the function of oil system is storage fuel oil, and cope with any flight when meeting light aerocraft flight regulations situation
State is got off the plane the fuel demand of engine, with can be to engine continuous fuel feeding.
Utility model content
The utility model provides a kind of oil supply system of light-duty sport plane, collects oil liquid simultaneously in oil liquid separating tank
It is removed supply engine after impurity, to solve above-mentioned root problem.
The technical solution that the utility model solves the above problems is: providing a kind of oil supply system of light-duty sport plane, wraps
The integral tank for including the wing root leading edge for being set to wing and being constituted with the up-front covering of wing root and rib, to separating oil and miscellaneous
The oil liquid separating tank of matter is connected to the first fuel passage of integral tank and oil liquid separating tank, connects oil liquid separating tank and engine
Oil inlet the second fuel passage, the integral tank includes left side wing tank and right side wing tank, further includes setting
In engine two sides and the vaporizer that is connect with engine.
It preferably, further include the first snorkel of left side wing tip being connected to from left side wing tank and from right side wing
The second snorkel of right side wing tip is connected on the outside of fuel tank.
It preferably, further include the multiple gate gurgle valves at the covering of inboard bottom of setting and more to be connected to draining
The oil exit pipe of valve and integral tank.
Preferably, first fuel passage includes the first fuel oil branched pipe of connection left side wing tank, connection right side
Second fuel oil branched pipe of wing tank, the third fuel oil branched pipe for being connected to oil liquid separating tank, and to concatenate the first fuel oil
Branched pipe, the second fuel oil branched pipe, third fuel oil branched pipe tee tube.
It preferably, further include the first fuel cock valve being arranged on the first fuel oil branched pipe, and setting is in the second combustion
The second fuel cock valve on oil branch pipe.
Preferably, further include be arranged in oil liquid separation trench bottom by pressure valve.
It preferably, further include the oil outlet pipe for being connected to the oil outlet and oil liquid separating tank of engine.
Preferably, the oil outlet pipe includes the first flowline of the oil outlet of one end connection engine, fuel-displaced with first
The four-way pipe of pipe other end connection, the vaporizer of two connection engine two sides and the second flowline of four-way pipe, are connected to four-way
The third flowline to the excess fuel that flows back of pipe and oil liquid separating tank.
The utility model has the beneficial effects that the utility model use it is separately positioned at aircraft or so wing and with wing knot
The fuel tank being configured to connects into an entirety by tee tube, to constitute an integral tank, to reduce aircraft overall weight, and
Setting is communicated to the snorkel of wing tip on the wing tank of the left and right sides, and fuel oil is made preferably to circulate, then using oil
Impurity in liquid separating tank filter fuel, further increases fuel oil quality, then supply engine.In addition, in aircraft engine
Oil outlet engine oil outlet, vaporizer, oil liquid separating tank are concatenated using four-way pipe, to improve the utilization of fuel oil
Rate avoids fuel oil from wasting, and practicability is higher.
Detailed description of the invention
Fig. 1 is a kind of overall structure diagram of light-duty sport plane of specific embodiment of the utility model.
1- integral tank, the left side 11- wing tank, the right side 12- wing tank, the first snorkel of 13-, 14- second ventilate
Pipe, 15- gate gurgle valve, 16- oil exit pipe, 2- oil liquid separating tank, 21- press pressure valve, the first fuel passage of 3-, the first fuel oil of 31- branch
Pipe, 311- the first fuel cock valve, 32- the second fuel oil branched pipe, 321- the second fuel cock valve, 33- third fuel oil branched pipe,
34- tee tube, 4- engine, the second fuel passage of 5-, 6- vaporizer, 7- oil outlet pipe, the first flowline of 71-, 72- four-way
Pipe, the second flowline of 73-, 74- third flowline.
Specific embodiment
In order to illustrate more clearly of the utility model embodiment and technical solution in the prior art, attached drawing will be compareed below
Illustrate specific embodiment of the present utility model.It should be evident that the accompanying drawings in the following description is only the one of the utility model
A little embodiments for those of ordinary skill in the art without creative efforts, can also be according to these
Attached drawing obtains other attached drawings, and obtains other embodiments, and the utility model is not restricted to the embodiment.
Referring to Fig. 1, a kind of oil supply system of light-duty sport plane of the utility model specific embodiment, a kind of light-duty fortune
The oil supply system of dynamic aircraft, including the whole oil for being set to the wing root leading edge of wing and being constituted with the up-front covering of wing root and rib
Case 1 is connected to the first fuel passage of integral tank 1 and oil liquid separating tank 2 to the oil liquid separating tank 2 of separating oil and impurity
3, the second fuel passage 5 of the oil inlet of oil liquid separating tank 2 and engine 4 is connected, the integral tank 1 includes left side wing oil
Case 11 and right side wing tank 12 further include the vaporizer 6 that 4 two sides of engine are arranged in and connect with engine 4.The oil liquid
Separating tank 2 be arranged on the outside of aircraft fire protection wall, and the first fuel passage 3 along the fuselage ring side of cockpit square tube by
It further include that left side machine is connected to from left side wing tank 11 so that the fuel oil in integral tank 1 preferably flows out up to lower arrangement
First snorkel 13 of thriving point and the second snorkel 14 that right side wing tip is connected on the outside of right side wing tank 12, institute
The first snorkel 13 and the second snorkel 14 are stated by the way that air is led to fuel tank, certain pressure difference is formed, so that fuel oil preferably flows
It is logical.It further include the multiple gate gurgle valves 15 at the covering of inboard bottom of setting and more to be connected to gate gurgle valve 15 and whole
The oil exit pipe 16 of fuel tank 1, when that need to carry out fuel tank inspection or exclude extra oil or water and other impurities, by pressing draining
Valve (15) excludes oil liquid or impurity etc..
First fuel passage 3 includes the first fuel oil branched pipe 31 of connection left side wing tank 11, connection right side machine
Second fuel oil branched pipe 32 of wing fuel tank 12, the third fuel oil branched pipe 33 for being connected to oil liquid separating tank 2, and to concatenate first
Fuel oil branched pipe 31, the second fuel oil branched pipe 32, third fuel oil branched pipe 33 tee tube 34.It further include being arranged in the first fuel oil
The first fuel cock valve 311 on branched pipe 31, and the second fuel cock valve being arranged on the second fuel oil branched pipe 32
321.Further include be arranged in 2 bottom of oil liquid separating tank by pressure valve 21, in order to be excluded after oil liquid separating tank 2 separates in time
Impurity.
It further include the oil outlet pipe 7 for being connected to the oil outlet and oil liquid separating tank 2 of engine 4.The oil outlet pipe 7 includes one
First flowline 71 of the oil outlet of end connection engine 4, the four-way pipe 72 being connect with 71 other end of the first flowline, two companies
The vaporizer 6 of logical 4 two sides of engine and the second flowline 73 of four-way pipe 72, are connected to the use of four-way pipe 72 and oil liquid separating tank 2
With the third flowline 74 for the excess fuel that flows back.Fuel oil is sent in engine in the second fuel passage 5 and by engine
After running its extra fuel oil can by be connected to engine oil outlet the first flowline 71 flow out, by four-way pipe 72 into
Row orderly shunts, and part can be entered in the vaporizer 6 of 4 two sides of engine by the second flowline 73, by vaporizer 6
Mixed with air under effect to be formed flammable mixture resupply engine combustion acting.Remaining fuel oil then passes through third flowline
74 flow back into oil liquid separating tank 2, then are transferred to engine 4.
It does not refer to place above, is suitable for the prior art.
Specific embodiment of the utility model is described in detail above.It should be appreciated that those skilled in the art without
It needs creative work according to the present utility model can conceive and makes many modifications and variations.Therefore, all the art
Technical staff's the utility model design is available by logical analysis, reasoning, or a limited experiment in the prior art
Technical solution, all should be in protection scope determined by the claims.
Claims (8)
1. a kind of oil supply system of light-duty sport plane, it is characterised in that: including being set to the wing root leading edge of wing and with wing root
The integral tank (1) that up-front covering and rib are constituted, to the oil liquid separating tank (2) of separating oil and impurity, connection is whole
The first fuel passage (3) of fuel tank (1) and oil liquid separating tank (2) connects the oil inlet of oil liquid separating tank (2) and engine (4)
The second fuel passage (5), the integral tank (1) includes left side wing tank (11) and right side wing tank (12), is also wrapped
Setting is included in engine (4) two sides and the vaporizer (6) that connect with engine (4).
2. a kind of oil supply system of light-duty sport plane according to claim 1, it is characterised in that: further include from left side machine
Wing fuel tank (11) is connected to the first snorkel (13) of left side wing tip and is connected to the right side on the outside of right side wing tank (12)
The second snorkel (14) of side wing tip.
3. a kind of oil supply system of light-duty sport plane according to claim 1, it is characterised in that: further include that setting is multiple
Gate gurgle valve (15) and the more oil extractions to be connected to gate gurgle valve (15) and integral tank (1) at the covering of inboard bottom
It manages (16).
4. a kind of oil supply system of light-duty sport plane according to claim 1, it is characterised in that: first fuel pipe
Road (3) includes the first fuel oil branched pipe (31) of connection left side wing tank (11), is connected to the second of right side wing tank (12)
Fuel oil branched pipe (32), the third fuel oil branched pipe (33) for being connected to oil liquid separating tank (2), and to concatenate the first fuel oil branch
Manage (31), the second fuel oil branched pipe (32), third fuel oil branched pipe (33) tee tube (34).
5. a kind of oil supply system of light-duty sport plane according to claim 4, it is characterised in that: further include setting the
The first fuel cock valve (311) on one fuel oil branched pipe (31), and be arranged on the second fuel oil branched pipe (32) second
Fuel cock valve (321).
6. a kind of oil supply system of light-duty sport plane according to claim 1, it is characterised in that: further include being arranged in oil
Press pressure valve (21) in liquid separating tank (2) bottom.
7. a kind of oil supply system of light-duty sport plane according to claim 1, it is characterised in that: further include that connection is started
The oil outlet of machine (4) and the oil outlet pipe (7) of oil liquid separating tank (2).
8. a kind of oil supply system of light-duty sport plane according to claim 7, it is characterised in that: the oil outlet pipe
(7) include one end connection engine (4) oil outlet the first flowline (71), connect with the first flowline (71) other end
Four-way pipe (72), the vaporizer (6) of two connection engine (4) two sides and the second flowline (73) of four-way pipe (72), connection
The third flowline (74) to the excess fuel that flows back of four-way pipe (72) and oil liquid separating tank (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822214848.0U CN209441665U (en) | 2018-12-27 | 2018-12-27 | A kind of oil supply system of light-duty sport plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822214848.0U CN209441665U (en) | 2018-12-27 | 2018-12-27 | A kind of oil supply system of light-duty sport plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209441665U true CN209441665U (en) | 2019-09-27 |
Family
ID=68016380
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201822214848.0U Active CN209441665U (en) | 2018-12-27 | 2018-12-27 | A kind of oil supply system of light-duty sport plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209441665U (en) |
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2018
- 2018-12-27 CN CN201822214848.0U patent/CN209441665U/en active Active
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