CN202370845U - Working chamber of spacing ring of aviation low-pressure oil pump - Google Patents
Working chamber of spacing ring of aviation low-pressure oil pump Download PDFInfo
- Publication number
- CN202370845U CN202370845U CN2011205407374U CN201120540737U CN202370845U CN 202370845 U CN202370845 U CN 202370845U CN 2011205407374 U CN2011205407374 U CN 2011205407374U CN 201120540737 U CN201120540737 U CN 201120540737U CN 202370845 U CN202370845 U CN 202370845U
- Authority
- CN
- China
- Prior art keywords
- working chamber
- impeller
- spacing ring
- active chamber
- spacer ring
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The utility model provides a working chamber of a spacing ring of an aviation low-pressure oil pump. An impeller used for transmitting mechanical energy to a working fluid is installed in the working chamber of the spacing ring; and the impeller is installed on a transmission shaft in the working chamber. The working chamber is characterized in that the wheel rim of the impeller and blades adopt an integrated structure; an output shaft for installing the impeller and a central axis of the working chamber of the spacing ring are eccentrically arranged; and the minimum distance d and the maximum distance D from the blades to the inner surface of the working chamber of the spacing ring in the radial direction are 0.029-0.109mm and 3.467-3.547mm respectively. Compared with the prior art, the working chamber with the structure can effectively improve the transmission efficiency of the working fluid in the working chamber of the spacing ring.
Description
Technical field
The utility model is a kind of spacer ring active chamber of aviation low pressure fuel pump, belongs to the architecture advances to aviation low pressure fuel pump product.
Background technique
Along with constantly increasing and the diversity of aerial mission of present generation aircraft flying height, had higher requirement in the high-level performance and the reliability aspect of aircraft engine fuel oil system.As the important component part of aeroengine fuel oil supply system, the quality of aviation low pressure fuel pump performance, its life-span length, the height of particularly anti-cavitation ability directly has influence on the performance and the safety of aircraft and motor.The low pressure fuel pump that uses in the air line at present is of a great variety and technical performance is very nearly the same, all causes a lot of troubles for actual production and working service.
Summary of the invention
The deficiency that the utility model exists to above-mentioned existing product just and design a kind of spacer ring of aviation low pressure fuel pump active chamber is provided its objective is the efficiency of transmission that improves working liquid body in the spacer ring active chamber.
The purpose of the utility model realizes through following technological scheme:
The spacer ring active chamber of this kind aviation low pressure fuel pump; The impeller that is used for mechanism can be passed to working liquid body is installed in the active chamber of spacer ring; Impeller is installed on the transmission shaft in the active chamber; It is characterized in that: the wheel rim and the blade of this impeller are integrated, and the central axis of the output shaft of mounted impeller and spacer ring active chamber is eccentric to be provided with, and blade radially is being respectively with the internal surface minimum range d and the ultimate range D of spacer ring active chamber: 0.029～0.109mm and 3.467～3.547mm.
The structural feature of the utility model is that impeller biased heart in active chamber is placed, so the gap between itself and the spacer ring is uneven, can improve in the active chamber efficiency of transmission to working liquid body so effectively.
Description of drawings
Fig. 1 is the working section figure structure schematic representation of the spacer ring active chamber of the said aviation low pressure fuel pump of the utility model
Embodiment
Below will combine accompanying drawing and embodiment that the utility model is done to detail further:
Shown in accompanying drawing 1; The spacer ring active chamber of this kind aviation low pressure fuel pump; In the active chamber 2 of spacer ring 1 impeller that is used for mechanism can be passed to working liquid body is installed; Impeller is installed on the transmission shaft 3 in the active chamber 2; It is characterized in that: the wheel rim of this impeller 4 is integrated with blade 5, and the output shaft 3 of mounted impeller is provided with the central axis of spacer ring 1 active chamber 2 is eccentric, and blade 5 radially is being respectively with the internal surface minimum range d and the ultimate range D of spacer ring 1 active chamber 2: 0.029～0.109mm and 3.467～3.547mm.
Above-mentioned each part of the utility model all adopts alloy steel material processing; Guarantee matrix strength; Blade 5 and the gap between its internal surface in the active chamber 2 are not definite values; Rotation motion in active chamber 2 makes the swept volume of a single chamber cyclically-varying to realize oil suction and oil extraction by the biasing impeller, and promptly bigger position is inhaled into fluid in the gap, and the position less in the gap is discharged from.
Compared with prior art, the utility model structure has improved the efficiency of transmission of working liquid body in the spacer ring active chamber effectively.
Claims (1)
1. the spacer ring active chamber of an aviation low pressure fuel pump; In the active chamber (2) of spacer ring (1) impeller that is used for mechanism can be passed to working liquid body is installed; Impeller is installed on the transmission shaft (3) in the active chamber (2); It is characterized in that: wheel rim of this impeller (4) and blade (5) are integrated; The central axis of the output shaft of mounted impeller (3) and spacer ring (1) active chamber (2) is eccentric to be provided with, and blade (5) radially is being respectively with the internal surface minimum range d and the ultimate range D of spacer ring (1) active chamber (2): 0.029～0.109mm and 3.467～3.547mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011205407374U CN202370845U (en) | 2011-12-20 | 2011-12-20 | Working chamber of spacing ring of aviation low-pressure oil pump |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011205407374U CN202370845U (en) | 2011-12-20 | 2011-12-20 | Working chamber of spacing ring of aviation low-pressure oil pump |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202370845U true CN202370845U (en) | 2012-08-08 |
Family
ID=46594550
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011205407374U Expired - Fee Related CN202370845U (en) | 2011-12-20 | 2011-12-20 | Working chamber of spacing ring of aviation low-pressure oil pump |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202370845U (en) |
-
2011
- 2011-12-20 CN CN2011205407374U patent/CN202370845U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20120808 Termination date: 20181220 |