CN109209646A - A kind of gravity switch unit and the aero-engine inverted flight oil return apparatus containing the unit - Google Patents
A kind of gravity switch unit and the aero-engine inverted flight oil return apparatus containing the unit Download PDFInfo
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- CN109209646A CN109209646A CN201811289388.6A CN201811289388A CN109209646A CN 109209646 A CN109209646 A CN 109209646A CN 201811289388 A CN201811289388 A CN 201811289388A CN 109209646 A CN109209646 A CN 109209646A
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- hole
- gravity
- switch unit
- shell
- gravity switch
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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
- F02C7/06—Arrangements of bearings; Lubricating
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Lubrication Details And Ventilation Of Internal Combustion Engines (AREA)
Abstract
A kind of aero-engine inverted flight oil return apparatus the present invention relates to gravity switch unit and containing the unit, oil return apparatus is containing two gravity switch units and lubrication work chamber, gravity switch unit includes shell, it can be slid vertically in shell and switch cylinder equipped with gravity, through-hole I is offered on the wall of shell, through-hole II is offered on the wall of gravity switching cylinder, shell it is upper, lower surface is respectively equipped with sealing plate, adapter tube hole is offered on any sealing plate, two gravity switch unit inverted relatives are be connected to the through-hole I of a gravity switch unit with through-hole II, the through-hole I and through-hole II of another gravity switch unit are staggered closing, two through hole I is sequentially connected scavenge oil pump and oil tank by oil return duct；The adapter tube hole for lubricating the lower return pipe of work chamber and the gravity switch unit of connected state connects, and upper return pipe is connect with the adapter tube hole of the gravity switch unit for the closed state that is staggered.The invention can ensure that aircraft is just flying and oil return when inverted flight.
Description
Technical field
The invention belongs to the lubrication technical fields of engine in mechanical engineering, and in particular to a kind of gravity switch unit and contain
The aero-engine inverted flight oil return apparatus of the unit.
Background technique
Aircraft, especially military aircraft have a requirement of various flight attitudes, and the follow-on mission under different flight attitudes
Ability brings huge challenge to the steady operation of aero gas turbine engine.
In aircraft inverted flight, due to posture, each main fulcrum lubricating oil of engine can not enter lubricating oil oil return by gravity
Pipe, for circulating aero gas turbine engine oil system, prolonged oil return interruption will lead to oil system circulation
It interrupting, cannot achieve the function of oil system, lubricating oil pressure, temperature and circular flow, heat dissipation capacity cannot ensure, so as to cause
The failure of serious main bearing of engine and transmission device.
Summary of the invention
For the above-mentioned deficiency of the prior art, the technical problem to be solved in the present invention is to provide a kind of gravity switch unit and
Aero-engine inverted flight oil return apparatus containing the unit solves the lubricating oil of aircraft its lubricant housings when just flying and inverted flight attitude angle
The problem of how constantly conveying is back to oil tank, acquirement space hold is small, and weight is small, effect convenient for safeguarding.
In order to solve the above technical problems, the present invention adopts the following technical scheme:
A kind of gravity switch unit, including shell, the shell are vertical hollow straight barrel type, can be slid vertically in the shell
Be combined with gravity switching cylinder, gravity switching cylinder is also vertical hollow straight barrel type, gravity switch the outer wall of cylinder with
The inner wall of shell is corresponding；Through-hole I is offered on the wall of shell, offers through-hole II, the through-hole I on the wall of gravity switching cylinder
It is located in same vertical plane with through-hole II, the distance of through-hole I to housing lower surface is equal to through-hole II to gravity and switches under cylinder
The distance on surface is be connected to through-hole I and through-hole II when gravity switches cylinder and the concordant lower surface of shell；Gravity switches cylinder
The height of body is less than the height of shell, and the height difference of the two is less than the minimum range between through-hole I and housing lower surface, is greater than
The sum of through-hole I and radius of through-hole II are to make II phase of through-hole I and through-hole when gravity switching cylinder is concordant with the upper surface of shell
Mutually be staggered closing；The upper and lower surfaces of the shell are sealedly connected with sealing plate respectively, and adapter tube hole is offered on any sealing plate.
The invention further relates to a kind of aero-engine inverted flight oil return apparatus, including two above-mentioned gravity switch units, two
A gravity switch unit is at through-hole I and through-hole II of the inverted relative to make one of gravity switch unit under the effect of gravity
In connected state, the through-hole I and through-hole II of another gravity switch unit are in the closed state that is staggered；Two gravity switch units
Through-hole I is connected to by oil return duct with oil tank, and the oil return duct is equipped with scavenge oil pump；
Further include lubrication work chamber, has been respectively communicated with return pipe, lower return pipe in the upper and lower part of lubrication work chamber
The adapter tube hole for the gravity switch unit that connected state is in through-hole I and through-hole II is connect, upper return pipe and through-hole I and through-hole
The adapter tube hole connection of the II gravity switch unit in the closed state that is staggered.
Aero-engine inverted flight oil return apparatus of the invention includes two gravity switch units, lubricates twice of work chamber
Flow tube is connected to by scavenge oil pump with oil tank after two gravity switch units respectively, no longer relies on gravity oil return merely, but
Oil return when just winged and inverted flight is realized by scavenge oil pump, lubricates the lubricating oil in work chamber because gravity will return always from lower part
Stream is made to lubricate the lower part in work chamber and is passed through corresponding gravity switching list always due to the setting of two gravity switch units
Member is connected to scavenge oil pump, oil tank holding, guarantee oil return, and is lubricated the top in work chamber and passed through corresponding gravity always and cut
It changes unit to be closed, air while avoiding oil return in blowback lubrication work chamber influences oil return effect.
And after 180 ° of rotation, it lubricates work chamber and two gravity switch units is in 180 ° of inversions, lubricate working chamber
Room upper and lower part orientation switching (because lubricating oil always will be from lower return because of gravity), the gravity of two gravity switch units
Switch cylinder under the effect of gravity, also the on off operating mode of corresponding switching through-hole II and through-hole I, remains lubrication work chamber
The return pipe on " top " is connect with the adapter tube hole for the gravity switch unit that through-hole I and through-hole II are in the closed state that is staggered, and is lubricated
The return pipe of work chamber " lower part " is connect with the adapter tube hole for the gravity switch unit that through-hole I and through-hole II are in connected state,
Guarantee that aircraft lubricating oil of its lubricant housings when just flying and inverted flight attitude angle constantly can be transmitted back to oil tank.
Above-mentioned technical proposal is further improved, a gravity switch unit is located at the underface of another gravity switch unit,
Two adapter tube hole is opened in the top upper end of gravity switch unit and the lower end of lower section gravity switch unit respectively.
In this way, occupy less space, and conveniently with the connection of return pipe.
Further, the shell of two gravity switch units is structure as a whole and adjacent sealing plate is total to plate.
In this way, two gravity switch unit manufactures are structure as a whole, globality is more preferable, reduces by two gravity switch units
Centre connection or auxiliary connection fixed respectively.
Further, check valve is respectively equipped on lower return pipe and upper return pipe.
Compared with prior art, the invention has the following beneficial effects:
1, aero-engine inverted flight oil return apparatus of the invention can guarantee aircraft its lubricant housings when just flying and inverted flight attitude angle
Lubricating oil can be constantly transmitted back to oil tank, ensure the normal operation of engine oil system and engine；Due to protecting
The oil return just flown with each lubricant housings of inverted flight attitude angle is demonstrate,proved, aircraft is in the various attitude angles for just flying to convert between inverted flight
When, it can also operate normally.
2, the gravity switch unit structure that aero-engine inverted flight oil return apparatus of the present invention uses is simple, and space hold is small,
Weight is small, suitable for the application on aircraft, and independently of engine and oil tank outside, it is convenient for safeguarding.
Detailed description of the invention
A kind of structural schematic diagram of gravity switch unit of Fig. 1-specific embodiment；
The portion the A partial enlarged view of Fig. 2-Fig. 3；
The structural schematic diagram of Fig. 3-specific embodiment aero-engine inverted flight oil return apparatus；
Wherein, shell 1, through-hole I 11, upper sealing plate 12, lower sealing plate 13 take over hole 14, and gravity switches cylinder 2, through-hole II 21, adapter tube
Mouth 3 lubricates work chamber 4, upper return pipe 41, lower return pipe 42, check valve 43, oil return duct 5, scavenge oil pump 6, oil tank
7。
Specific embodiment
Specific embodiments of the present invention will be described in further detail with reference to the accompanying drawing.
Referring to Fig. 1, a kind of gravity switch unit of specific embodiment, including shell 1, the shell 1 are vertical hollow
Straight barrel type can slide vertically in the shell 1 and be combined with gravity switching cylinder 2, and the gravity switching cylinder 2 is also vertical hollow
Straight barrel type；The outer wall that gravity switches cylinder 2 is corresponding with the inner wall of shell 1, and the height that gravity switches cylinder 2 is less than shell 1
Highly；Through-hole I 11 is offered on the wall of shell 1, offers through-hole II 21, I 11 He of through-hole on the wall of gravity switching cylinder 2
Through-hole II 21 is located in same vertical plane and the distance of through-hole I 11 to 1 lower surface of shell is equal to through-hole II 21 to gravity and switches
The distance of 2 lower surface of cylinder, connect through-hole I 11 and through-hole II 21 when gravity switching cylinder 2 is concordant with the lower surface of shell 1
It is logical.
It is the benchmark for measuring or demarcating that the restriction of the above-mentioned position to each through-hole, which is with the central axes of through-hole,.For weight
Power switches the height difference of cylinder 2 and shell 1, and also further requirement should be less than the minimum between 1 lower surface of through-hole I 11 and shell
Distance, and the sum of the radius for being greater than through-hole I 11 and through-hole II 21 just can guarantee by the requirement of above-mentioned height difference in gravity
Switching cylinder 2 makes through-hole I 11 and through-hole II 21 mutually stagger and be closed when concordant with the upper surface of shell 1；Wherein most narrow spacing
With a distance from edge to 1 lower surface of shell from i.e. through-hole I 11, rather than central axes.
The upper and lower surfaces of the shell 1 are sealedly connected with horizontal upper sealing plate 12 and lower sealing plate 13, upper envelope respectively
The middle part of plate 12 offers adapter tube hole 14, and the adapter tube hole 14 is connected to the inner cavity of shell 1 and gravity switching cylinder 2, upper sealing plate
12 and lower sealing plate 13 make shell 1 become one sealing cavity body structure, while be also used for limitation gravity switching cylinder 2 slide up and down
Stroke.
Wherein, be equipped on 1 outer wall of shell with adapter tube hole 14 and I 11 corresponding position of through-hole the pressure inlet 3 that is connected in order to
External catheter.
When implementation, the horizontal cross sectional geometry of shell 1 can rectangular, round or other shapes, the present invention with no restriction, as long as
It is straight tube form, so that gravity switching cylinder 2 can be slided up and down along its inner wall.Gravity switch cylinder 2 outer wall with
The inner wall of shell 1 is corresponding, plays closed effect, when the lower surface of gravity switching cylinder 2 is abutted with lower sealing plate 13, through-hole
II 21 are connected to the through-hole I 11 of shell 1, and through-hole I 11 and shell 1 and gravity switching 2 inner cavity of cylinder are in connected state.It is inverted
When, due to gravity, gravity switches cylinder 2 and slides along the inner wall of shell 1, upper surface and upper envelope when gravity switching cylinder 2
When plate 12 abuts, the through-hole I 11 of through-hole II 21 and shell 1 is staggered naturally and mutually closes.
Certainly, when the horizontal cross sectional geometry of shell 1 is round, anti-rotation measure is needed, prevents gravity switching cylinder 2 in shell
It rotates to it in body 1.
Referring to fig. 2, Fig. 3, the present invention also provides a kind of aero-engine inverted flight oil return apparatus, including two above-mentioned gravity
Switch unit, two gravity switch units are in inverted relative, and a gravity switch unit is being located at another gravity switch unit just
Lower section in the present embodiment, makes the adapter tube hole 14 of the gravity switch unit of top upward, and through-hole I 11 and through-hole II 21 are in and connect
Logical state, then due to the positional relationship of inverted relative, the adapter tube hole 14 of the gravity switch unit of lower section downward, and due to gravity
Reason, through-hole I 11 and through-hole II 21 are in the closed state that is staggered；The through-hole I 11 of two gravity switch units is led by oil return
Pipe 5 is connected to oil tank 7, and the oil return duct 5 is equipped with scavenge oil pump 6.
Further include lubrication work chamber 4, has been respectively communicated with return pipe, lower part in the upper and lower part of lubrication work chamber 4
Return pipe 42 is connect with the adapter tube hole 14 of the gravity switch unit of top, the gravity switch unit of upper return pipe 41 and lower section
Hole 14 is taken over to connect；It is respectively equipped with check valve 43 on lower return pipe 42 and upper return pipe 41, allows to switch towards gravity single
First one-way flow.
In use, because lubricating oil because gravity will flow back always from its underpart, lubricates under the lubricating oil warp in work chamber 4
Portion's return pipe 42, top gravity switch unit connect from the through-hole I 11 of top gravity switch unit and scavenge oil pump 6 and oil tank 7
It is logical, realize the reflux of lubricating oil；And at this point, upper return pipe 41 is closed by the gravity switch unit of lower section always, avoid back
Air while oily in blowback lubrication work chamber 4, influences oil return effect.
When inverted flight, then entirely lubrication work chamber 4 and two gravity switch units are in 180 ° of inversions, lubricate work chamber
The switching of 4 upper and lower parts orientation, lubricating oil is because gravity will flow back always from its underpart, the gravity switching of two gravity switch units
Cylinder 2 under the effect of gravity, also it is corresponding switching through-hole II 21 and through-hole I 11 on off operating mode, in this way, just be in and just fly phase
Same structural form and the course of work ensure that aircraft lubricating oil of its lubricant housings when just flying and inverted flight attitude angle can be held
Continuous ground is transmitted back to oil tank 7.
By the connection type of embodiment and the use process of introduction it is found that when implementing, as long as two gravity switch units
It is vertical simultaneously to use, it is not necessary to lower placement relationship is presented, can also be placed side by side, if two gravity switch units are
Split type structure takes over hole 14 either being provided with upper sealing plate 12, is also possible to be provided with lower sealing plate 13, has no effect on profit
The lubricating oil reflux course and effect of sliding work chamber 4, it is only necessary to guarantee the return pipe and through-hole I of lubrication work chamber 4 " top "
11 and through-hole II 21 be in be staggered closed state gravity switch unit adapter tube hole 14 connect, lubricate work chamber 4 " lower part "
The adapter tube hole 14 of return pipe and through-hole I 11 and through-hole II 21 the gravity switch unit that is in connected state connect.
When implementation, if two gravity switch units may be used also during fabrication in the positional relationship of turned upside down shown in Fig. 2
The shell 1 of two gravity switch units to be processed as one structure, the lower sealing plate 13 of two such gravity switch unit can be with
One is shared, and globality is more preferable, the intermediate connection of two gravity switch units can be reduced, reduce and fix institute respectively aboard
It is connected using the auxiliary arrived.
It is the restriction of vertical hollow straight barrel type to shell 1 and gravity switching cylinder 2 in the present invention, is to guarantee gravity
Switching cylinder 2 can slide vertically in shell 1, and when implementation, the inner wall of the outer wall of shell 1 and/or gravity switching cylinder 2 is replaced
It is changed to the structure type of nonlinear pattern, also because being in the scope of the claims of the present invention.
Finally, it is stated that the above examples are only used to illustrate the technical scheme of the present invention and are not limiting, although referring to compared with
Good embodiment describes the invention in detail, those skilled in the art should understand that, it can be to skill of the invention
Art scheme is modified or replaced equivalently, and without departing from the objective and range of technical solution of the present invention, should all be covered at this
In the scope of the claims of invention.
Claims (5)
1. a kind of gravity switch unit, it is characterised in that: including shell, the shell is vertical hollow straight barrel type, the shell
It can slide vertically in vivo and be combined with gravity switching cylinder, the gravity switching cylinder is also vertical hollow straight barrel type, and gravity is cut
The outer wall of creeling body and the inner wall of shell are corresponding；Through-hole I is offered on the wall of shell, is offered on the wall of gravity switching cylinder logical
Hole II, the through-hole I and through-hole II are located in same vertical plane, the distance of through-hole I to housing lower surface be equal to through-hole II to
The distance of gravity switching cylinder lower surface is connect through-hole I and through-hole II when gravity switching cylinder is concordant with the lower surface of shell
It is logical；The height that gravity switches cylinder is less than the height of shell, and the height difference of the two is less than between through-hole I and housing lower surface
Minimum range, greater than the sum of through-hole I and radius of through-hole II to make to lead to when gravity switching cylinder is concordant with the upper surface of shell
Hole I and through-hole II mutually stagger closing；The upper and lower surfaces of the shell are sealedly connected with sealing plate respectively, on any sealing plate
Offer adapter tube hole.
2. aero-engine inverted flight oil return apparatus, it is characterised in that: single including two gravity switchings as described in claim 1
Member, two gravity switch units make the through-hole I of one of gravity switch unit under the effect of gravity in inverted relative and lead to
Hole II is in connected state, and the through-hole I and through-hole II of another gravity switch unit are in the closed state that is staggered；The switching of two gravity
The through-hole I of unit is connected to by oil return duct with oil tank, and the oil return duct is equipped with scavenge oil pump；
Further include lubrication work chamber, has been respectively communicated with return pipe, lower return pipe in the upper and lower part of lubrication work chamber
The adapter tube hole for the gravity switch unit that connected state is in through-hole I and through-hole II is connect, upper return pipe and through-hole I and through-hole
The adapter tube hole connection of the II gravity switch unit in the closed state that is staggered.
3. aero-engine inverted flight oil return apparatus according to claim 2, it is characterised in that: a gravity switch unit is located at
The underface of another gravity switch unit, two adapter tube hole are opened in upper end and the lower section weight of top gravity switch unit respectively
The lower end of power switch unit.
4. aero-engine inverted flight oil return apparatus according to claim 3, it is characterised in that: the shell of two gravity switch units
Body is structure as a whole and adjacent sealing plate is total to plate.
5. aero-engine inverted flight oil return apparatus according to claim 2, it is characterised in that: lower return pipe and upper return
Check valve is respectively equipped on pipe.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811289388.6A CN109209646A (en) | 2018-10-31 | 2018-10-31 | A kind of gravity switch unit and the aero-engine inverted flight oil return apparatus containing the unit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811289388.6A CN109209646A (en) | 2018-10-31 | 2018-10-31 | A kind of gravity switch unit and the aero-engine inverted flight oil return apparatus containing the unit |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109209646A true CN109209646A (en) | 2019-01-15 |
Family
ID=64997658
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811289388.6A Pending CN109209646A (en) | 2018-10-31 | 2018-10-31 | A kind of gravity switch unit and the aero-engine inverted flight oil return apparatus containing the unit |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109209646A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112880991A (en) * | 2021-01-14 | 2021-06-01 | 南方科技大学 | Rotor experimental device for simulating maneuvering flight |
-
2018
- 2018-10-31 CN CN201811289388.6A patent/CN109209646A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112880991A (en) * | 2021-01-14 | 2021-06-01 | 南方科技大学 | Rotor experimental device for simulating maneuvering flight |
| CN112880991B (en) * | 2021-01-14 | 2022-11-25 | 南方科技大学 | Rotor experimental device for simulating maneuvering flight |
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