CN204041223U - Aviation piston engine composite valve and there is its aviation piston engine - Google Patents
Aviation piston engine composite valve and there is its aviation piston engine Download PDFInfo
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- CN204041223U CN204041223U CN201420415302.0U CN201420415302U CN204041223U CN 204041223 U CN204041223 U CN 204041223U CN 201420415302 U CN201420415302 U CN 201420415302U CN 204041223 U CN204041223 U CN 204041223U
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- pressurized machine
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Abstract
The utility model provides a kind of aviation piston engine composite valve and has its aviation piston engine.This aviation piston engine composite valve comprises: housing, and be provided with first flow and the second runner in housing, first flow has first-class road junction; Valve sheet, valve sheet is arranged in housing movably, and valve sheet has oil return position and draining position, when valve sheet is in oil return position, valve sheet is fitted in first-class road junction and cuts off first flow and the second runner, when valve sheet is in draining position, valve sheet is away from first-class road junction and make first flow and the second flow passage; Nozzle, nozzle stretches in first flow, and nozzle has central through bore, and central through bore is communicated with first flow and the second runner.The problem that pressurized machine has long-pending oil can be solved by this aviation piston engine composite valve.
Description
Technical field
The utility model relates to space shuttle power systems art, in particular to a kind of aviation piston engine composite valve and the aviation piston engine with it.
Background technique
Have pressurized machine in aviation piston engine, pressurized machine is made up of impeller, diffuser, transmission device, densification device etc.Pressurized machine working principle is, mixed gas from vaporizer is through intake duct, enter the import of impeller, after mixed gas enters impeller, flow out from impeller outer edge through interlobate passage under the pressurization of impeller, enter sub-air chamber by diffuser, be then assigned to each cylinder of aviation piston engine through suction tude.During aviation piston engine work, mixed gas flows into the process of supercharger impeller from vaporizer, and a small amount of unevaporated gasoline can condense into oil droplet and flow in supercharging casing; In addition, if too much with vaporizer acceleration device oiling when aviation piston engine starts, or the blow-by of vaporizer float mechanism pin plug valve, gasoline also can flow in supercharging casing, makes to produce long-pending oil in pressurized machine casing.If the long-pending oil in pressurized machine casing does not deal with, then may flow into lower cylinder and produce hydraulic impact by gasoline when aviation piston engine starts, or aviation piston engine work tempering and breaking out of fire.
Model utility content
The utility model aims to provide a kind of aviation piston engine composite valve and has its aviation piston engine, has the problem of long-pending oil with the pressurized machine solving aviation piston engine of the prior art.
To achieve these goals, according to an aspect of the present utility model, provide a kind of aviation piston engine composite valve, this aviation piston engine composite valve comprises: housing, be provided with first flow and the second runner in housing, first flow has first-class road junction; Valve sheet, valve sheet is arranged in housing movably, and valve sheet has oil return position and draining position, when valve sheet is in oil return position, valve sheet is fitted in first-class road junction and cuts off first flow and the second runner, when valve sheet is in draining position, valve sheet is away from first-class road junction and make first flow and the second flow passage; Nozzle, nozzle stretches in first flow, and nozzle has central through bore, and central through bore is communicated with first flow and the second runner.
Further, housing comprises upper half-shell and housing lower half, and first flow is arranged in upper half-shell, and first-class road junction is on the bottom surface of upper half-shell.
Further, be provided with annular boss in housing lower half, the lumen segmentation of housing lower half is the second runner and interior ring cavity by annular boss, and valve sheet moves between the end face and the bottom surface of upper half-shell of annular boss.
Further, annular boss is provided with radial hole, radial hole penetrates annular boss perisporium and is communicated with the second runner and interior ring cavity.
Further, aviation piston engine composite valve also comprises nozzle carrier, and nozzle carrier is in annular boss, and stretches in first flow, and nozzle carrier has the mounting hole installing nozzle.
Further, be provided with the inclined hole section of first flow between nozzle carrier and upper half-shell, first-class road junction is the opening of inclined hole section on the bottom surface of upper half-shell.
Further, housing lower half is provided with screw plug, screw plug has the first vent of radial extension and axially extended installation groove, and nozzle carrier is fixedly installed on to be installed in groove, and the mounting hole of nozzle carrier is by the first vent and the second flow passage.
According to another aspect of the present utility model, provide a kind of aviation piston engine, aviation piston engine comprises pressurized machine and aviation piston engine composite valve, pressurized machine comprises pressurized machine casing, the diffuser be arranged in pressurized machine casing, the oil leak hole that is arranged on the impeller in pressurized machine casing and is arranged on pressurized machine casing, aviation piston engine composite valve is arranged in oil leak hole, aviation piston engine composite valve is above-mentioned aviation piston engine composite valve, and oil leak hole is communicated with inner chamber and the first flow of pressurized machine casing.
Further, pressurized machine casing is provided with the Oil Guide arm be communicated with oil leak hole, nozzle is connected with fuel sucking pipe, fuel sucking pipe is provided with the oil inlet hole be communicated with first flow, fuel sucking pipe stretches in pressurized machine casing inner chamber, and fuel sucking pipe outlet is positioned at the suction port place of impeller.
Application the technical solution of the utility model, being in oil return position or draining position by controlling valve sheet, long-pending oil can being controlled and whether flow out aviation piston engine composite valve, by nozzle to coordinate with valve sheet can reclaim amass oily, recycling, reduces energy waste.
Accompanying drawing explanation
The accompanying drawing forming a part of the present utility model is used to provide further understanding of the present utility model, and schematic description and description of the present utility model, for explaining the utility model, is not formed improper restriction of the present utility model.In the accompanying drawings:
Fig. 1 shows the structure sectional view of the aviation piston engine composite valve of embodiment of the present utility model; And
The aviation piston engine that Fig. 2 shows embodiment of the present utility model is equipped with the sectional view of the pressurized machine of this composite valve.
Description of reference numerals: 10, first flow; 11, inclined hole section; 20, the second runner; 30, valve sheet; 40, nozzle; 41, central through bore; 42, nozzle carrier; 421, mounting hole; 51, annular boss; 511, interior ring cavity; 512, radial hole; 61, screw plug; 70, fuel sucking pipe; 71, oil inlet hole; 81, diffuser; 82, impeller; 83, oil leak hole; 84, Oil Guide arm.
Embodiment
Hereinafter also describe the utility model in detail with reference to accompanying drawing in conjunction with the embodiments.It should be noted that, when not conflicting, the embodiment in the application and the feature in embodiment can combine mutually.
As illustrated in fig. 1 and 2, according to embodiment of the present utility model, aviation piston engine composite valve comprises housing, valve sheet 30 and nozzle 40, and be provided with first flow 10 and the second runner 20 in housing, first flow 10 has first-class road junction; Valve sheet 30 is arranged in housing movably, and valve sheet 30 has oil return position and draining position, when valve sheet 30 is in oil return position, valve sheet 30 is fitted in first-class road junction and cuts off first flow 10 and the second runner 20, when valve sheet 30 is in draining position, valve sheet 30 is away from first-class road junction and first flow 10 is communicated with the second runner 20; Nozzle 40 stretches in first flow 10, and nozzle 40 has central through bore 41, and central through bore 41 is communicated with first flow 10 and the second runner 20.Housing is for holding and carrying other parts of aviation piston engine composite valve.First flow 10 and the second runner 20 are for ventilation or draining, and valve sheet 30, by oil return position and the oil return of draining position switching control or draining, is coordinated with nozzle 40 by valve sheet 30, realize long-pending oily recovery.When this aviation piston engine composite valve is applied to after on pressurized machine, after long-pending oil can being produced by this aviation piston engine composite valve in pressurized machine, long-pending oil is recycled or draining, ensure that long-pending oil can not leak on other high-temperature component of aviation piston engine, avoid and cause long-pending oil blast.
In this example, for the ease of processing and assembling, housing comprises upper half-shell and housing lower half, and upper half-shell and housing lower half split manufacture, and is convenient to processing, and upper half-shell is fixedly connected with housing lower half and is convenient to assemble.First flow 10 is arranged in upper half-shell, first-class road junction be in upper half-shell towards on the end face of housing lower half, namely also first-class road junction is on the bottom surface of upper half-shell.
Be provided with annular boss 51 in housing lower half, the lumen segmentation of housing lower half is the second runner 20 and interior ring cavity 511 by annular boss 51, and valve sheet 30 moves between the end face and the bottom surface of upper half-shell of annular boss 51.Annular boss 51 can be used for carrying valve sheet 30.
Annular boss 51 is provided with radial hole 512, radial hole 512 penetrates annular boss 51 perisporium and is communicated with the second runner 20 and interior ring cavity 511.
Aviation piston engine composite valve also comprises nozzle carrier 42, and nozzle carrier 42 is in annular boss 51, and stretches in first flow 10, and nozzle carrier 42 has the mounting hole 421 installing nozzle 40.Mounting hole 421 is communicated with interior ring cavity, because interior ring cavity is communicated with the second runner 20 by radial hole 512, thus the mounting hole 421 of nozzle carrier 42 is communicated with between the second runner 20, when ensure that air inlet, valve sheet 30 is in oil return position, and is communicated with between first flow 10 with the second runner 20 and realizes air inlet.
In the present embodiment, be provided with the inclined hole section 11 of first flow 10 between nozzle carrier 42 and upper half-shell, first-class road junction is the opening of inclined hole section 11 on the bottom surface of upper half-shell.Inclined hole section 11 is of value to the long-pending oil of buffering, can carry out water conservancy diversion simultaneously, avoid long-pending oil to flow in interior ring cavity to long-pending oil during draining, ensures that draining is totally unobstructed.
In the present embodiment, in order to ensure composite valve sealing, housing lower half is provided with screw plug 61, screw plug 61 has the first vent of radial extension and axially extended installation groove, nozzle carrier 42 is fixedly installed on to be installed in groove, and the mounting hole 421 of nozzle carrier 42 is communicated with the second runner 20 by the first vent.Screw plug 61 1 aspect can seal housing, ensures tightness, can carry nozzle carrier 42 on the other hand, for nozzle carrier 42 provides support, ensures that the mounting hole 421 of nozzle carrier 42 is ventilated smooth and easy.Nozzle 40 is fixed on nozzle carrier 42, and the central through bore 41 of nozzle 40 is communicated with mounting hole 421.
In the present embodiment, the outer edge of valve sheet 30 is positioned at outside the periphery wall of annular boss 51, guides in the second runner 20 with the long-pending oil released by the needs flowed out from inclined hole section 11, and prevents long-pending oil from flowing in interior ring cavity, ensures that long-pending oil releases unobstructed.
According to the another aspect of embodiment of the present utility model, aviation piston engine comprises pressurized machine and aviation piston engine composite valve, pressurized machine comprises pressurized machine casing, the diffuser 81 be arranged in pressurized machine casing, the oil leak hole 83 that is arranged on the impeller 82 in pressurized machine casing and is arranged on pressurized machine casing, aviation piston engine composite valve is arranged in oil leak hole 83, aviation piston engine composite valve is above-mentioned aviation piston engine composite valve, and oil leak hole 83 is communicated with inner chamber and the first flow 10 of pressurized machine casing.
Pressurized machine casing is provided with the Oil Guide arm 84 be communicated with oil leak hole 83, nozzle 40 is connected with fuel sucking pipe 70, fuel sucking pipe 70 is provided with the oil inlet hole 71 that fuel sucking pipe 70 is communicated with first flow 10, fuel sucking pipe 70 stretches in pressurized machine casing inner chamber, and fuel sucking pipe 70 outlet is positioned at the suction port place of impeller 82.
When pressurized machine works, the long-pending oil accumulated in pressurized machine casing guides and makes it flow in oil leak hole 83 by Oil Guide arm 84, impeller 82 rotates, and negative pressuren zone is formed in the chamber of pressurized machine casing, cause first flow 10 internal pressure to reduce, valve sheet 30 is attracted on the bottom surface of upper half-shell, is in oil return position, and inclined hole section 11 is closed, the long-pending oil flowed out from oil leak hole 83 is closed in first flow 10.In the second runner 20, leaked-in air is by the radial hole 512 annular boss 51, the first through hole on screw plug 61, spray in fuel sucking pipe 70 finally by the central through bore 41 of nozzle 40, due to fuel sucking pipe 70 being provided with oil inlet hole 71, the long-pending oil accumulated in first flow 10 can be inhaled in fuel sucking pipe 70 by oil inlet hole 71, finally aspirated by impeller 82, thus achieve the recycling to long-pending oil, decrease the waste of the energy.
If do not have gasoline to accumulate, then fuel sucking pipe 70 inside still continuous air-breathing, namely the heaviest a part of mixed gas in diffuser 81 bottom is sucked away.
When pressurized machine does not work, because impeller 82 does not rotate, thus valve sheet 30 gravitate and rest on annular boss 51, inclined hole section 11 and the second flow passage, long-pending oil to be flowed in first flow 10 by Oil Guide arm 84 and flows in the second runner 20 by inclined hole section 11, discharges eventually through the second runner 20.Can recycle or discharge the long-pending oil in pressurized machine by said process, ensure pressurized machine normal operation.
In the present embodiment, the housing of aviation piston engine composite valve is fixed in the bottom-right tapped hole in pressurized machine casing rear portion (being also oil leak hole), and the leakage of oil conduit of housing stretches out the lower right of the cowling at aviation piston engine.Because rely on pressure difference to control valve sheet 30 be in oil return position or draining position, therefore, the outlet of leakage of oil conduit faces flight direction, is also that the outlet of leakage of oil conduit is towards direction of advance, and the cowling being positioned at aviation piston engine is outside, is drained in air by long-pending oil.
From above description, can find out, the utility model the above embodiments achieve following technique effect: aviation piston engine composite valve utilizes the pressure difference on the upper and lower surface of valve sheet and self gravitation to control valve sheet and is in oil return position or draining position, to control whether be communicated with inclined hole section and the second runner, also namely controlling long-pending oil is release or reclaim.When valve sheet upper surface pressure is more than or equal to lower surface pressure, valve sheet drops down onto on annular boss due to Action of Gravity Field, inclined hole section and the second flow passage, and long-pending oil is discharged; When valve sheet upper surface pressure is less than lower surface pressure and pressure difference is enough to overcome valve sheet gravity, valve sheet is in oil return position, is adjacent to the lower surface of upper half-shell, disconnects inclined hole section and being communicated with between the second runner, make long-pending oil be in first flow, convenient recovery amasss oil.Aviation piston engine lower cylinder can be avoided thus to produce hydraulic impact, avoid aviation piston engine breaking out of fire because of tempering simultaneously.
The foregoing is only preferred embodiment of the present utility model, be not limited to the utility model, for a person skilled in the art, the utility model can have various modifications and variations.All within spirit of the present utility model and principle, any amendment done, equivalent replacement, improvement etc., all should be included within protection domain of the present utility model.
Claims (9)
1. an aviation piston engine composite valve, is characterized in that, comprising:
Housing, be provided with first flow (10) and the second runner (20) in described housing, described first flow (10) has first-class road junction;
Valve sheet (30), described valve sheet (30) is arranged in described housing movably, and described valve sheet (30) has oil return position and draining position, when described valve sheet (30) is in described oil return position, described valve sheet (30) is fitted in described first-class road junction and cuts off described first flow (10) and described second runner (20), when described valve sheet (30) is in described draining position, described valve sheet (30) is away from described first-class road junction and described first flow (10) is communicated with described second runner (20),
Nozzle (40), described nozzle (40) stretches in described first flow (10), described nozzle (40) has central through bore (41), and described central through bore (41) is communicated with described first flow (10) and described second runner (20).
2. aviation piston engine composite valve according to claim 1, it is characterized in that, described housing comprises upper half-shell and housing lower half, and described first flow (10) is arranged in described upper half-shell, and described first-class road junction is on the bottom surface of described upper half-shell.
3. aviation piston engine composite valve according to claim 2, it is characterized in that, annular boss (51) is provided with in described housing lower half, the lumen segmentation of described housing lower half is described second runner (20) and interior ring cavity (511) by described annular boss (51), and described valve sheet (30) is moved between the end face and the bottom surface of described upper half-shell of described annular boss (51).
4. aviation piston engine composite valve according to claim 3, it is characterized in that, described annular boss (51) is provided with radial hole (512), described radial hole (512) penetrates described annular boss (51) perisporium and is communicated with described second runner (20) and described interior ring cavity (511).
5. aviation piston engine composite valve according to claim 3, it is characterized in that, described aviation piston engine composite valve also comprises nozzle carrier (42), described nozzle carrier (42) is in described annular boss (51), and stretching in described first flow (10), described nozzle carrier (42) has the mounting hole (421) installing described nozzle (40).
6. aviation piston engine composite valve according to claim 5, it is characterized in that, be provided with the inclined hole section (11) of described first flow (10) between described nozzle carrier (42) and described upper half-shell, described first-class road junction is the opening of described inclined hole section (11) on the bottom surface of described upper half-shell.
7. aviation piston engine composite valve according to claim 5, it is characterized in that, described housing lower half is provided with screw plug (61), described screw plug (61) has the first vent of radial extension and axially extended installation groove, described nozzle carrier (42) is fixedly installed in described installation groove, and the mounting hole (421) of described nozzle carrier (42) is communicated with described second runner (20) by described first vent.
8. an aviation piston engine, it is characterized in that, described aviation piston engine comprises pressurized machine and aviation piston engine composite valve, described pressurized machine comprises pressurized machine casing, be arranged on the diffuser (81) in described pressurized machine casing, the oil leak hole (83) being arranged on the impeller (82) in described pressurized machine casing and being arranged on described pressurized machine casing, described aviation piston engine composite valve is arranged in described oil leak hole (83), the aviation piston engine composite valve of described aviation piston engine composite valve according to any one of claim 1 to 7, described oil leak hole (83) is communicated with inner chamber and the described first flow (10) of described pressurized machine casing.
9. aviation piston engine according to claim 8, it is characterized in that, described pressurized machine casing is provided with the Oil Guide arm (84) be communicated with described oil leak hole (83), described nozzle (40) is connected with fuel sucking pipe (70), described fuel sucking pipe (70) is provided with the oil inlet hole (71) be communicated with described first flow (10), described fuel sucking pipe (70) stretches in described pressurized machine casing inner chamber, and described fuel sucking pipe (70) outlet is positioned at the suction port place of described impeller (82).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420415302.0U CN204041223U (en) | 2014-07-25 | 2014-07-25 | Aviation piston engine composite valve and there is its aviation piston engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420415302.0U CN204041223U (en) | 2014-07-25 | 2014-07-25 | Aviation piston engine composite valve and there is its aviation piston engine |
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| Publication Number | Publication Date |
|---|---|
| CN204041223U true CN204041223U (en) | 2014-12-24 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420415302.0U Active CN204041223U (en) | 2014-07-25 | 2014-07-25 | Aviation piston engine composite valve and there is its aviation piston engine |
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| CN (1) | CN204041223U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114151199A (en) * | 2021-10-20 | 2022-03-08 | 中国航发四川燃气涡轮研究院 | Oil discharge device for casing |
-
2014
- 2014-07-25 CN CN201420415302.0U patent/CN204041223U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114151199A (en) * | 2021-10-20 | 2022-03-08 | 中国航发四川燃气涡轮研究院 | Oil discharge device for casing |
| CN114151199B (en) * | 2021-10-20 | 2023-06-02 | 中国航发四川燃气涡轮研究院 | Oil discharging device for casing |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 412002 Dong Jiaduan, Zhuzhou, Hunan Patentee after: China Hangfa South Industrial Co. Ltd. Address before: 412002 Dong Jiaduan, Zhuzhou, Hunan Patentee before: China Southern Airlines Industry (Group) Co., Ltd. |
|
| CP01 | Change in the name or title of a patent holder |