CN103711710B - A kind of aviation DC electropump clearance adjustment method - Google Patents
A kind of aviation DC electropump clearance adjustment method Download PDFInfo
- Publication number
- CN103711710B CN103711710B CN201310671980.3A CN201310671980A CN103711710B CN 103711710 B CN103711710 B CN 103711710B CN 201310671980 A CN201310671980 A CN 201310671980A CN 103711710 B CN103711710 B CN 103711710B
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- CN
- China
- Prior art keywords
- end cap
- impeller
- pad
- adjustment
- electropump
- 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.)
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/60—Mounting; Assembling; Disassembling
- F04D29/62—Mounting; Assembling; Disassembling of radial or helico-centrifugal pumps
- F04D29/622—Adjusting the clearances between rotary and stationary parts
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/08—Sealings
- F04D29/16—Sealings between pressure and suction sides
- F04D29/165—Sealings between pressure and suction sides especially adapted for liquid pumps
- F04D29/167—Sealings between pressure and suction sides especially adapted for liquid pumps of a centrifugal flow wheel
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention belongs to aero fuel pump technical field, particularly relate to a kind of aviation DC electropump clearance adjustment method.Solution is by installing blocked up technique jack-up pad at fuel pump adjustment link, making end cap by impeller jack-up, is got final product the adjustment spacer thickness of backwards calculation actual demand installation by the height of measuring end cover jack-up.Movement clearance between impeller and end cap is converted into product parts and has interacted measurement by patent of the present invention, and avoid movement clearance and cannot measure the drawback being unfavorable for impeller curved surface measuring, method of measurement is fast, easy.
Description
Technical field
The invention belongs to aero fuel pump technical field, particularly relate to a kind of aviation DC electropump clearance adjustment method.
Background technique
Movement clearance between the impeller of aero fuel pump series products and end cap needs strictly to control, and this gap is positioned at interiors of products, and impeller end face is irregular, is difficult to directly carry out precision adjustment.
The former clearance adjustment method of product is: on end cap, coat band look oil plant, then increase adjusting play thickness gradually, until impeller contacts with end cap just, then subtracts adjustment spacer thickness as required and carrys out control gap.Need during measurement repeatedly to adjust spacer thickness, go to sound out impeller also end cover clearance by close mode, the method is not measured difficulty and is difficult to accurate control impeller and end cover clearance.
Summary of the invention
Object of the present invention: provide a kind of aviation DC electropump clearance adjustment method, to being difficult to direct measuring point and requiring that meticulousr gap fast, simply can complete adjustment.
Technological scheme of the present invention: a kind of aviation DC electropump clearance adjustment method, this aviation DC electropump comprises motor shaft 1, adjustment pad 2, impeller 3, housing 4, end cap 5, screw 6, comprises the following steps:
1, setting impeller 3 with end cap 5 clearance requirement is a;
2, when not installing impeller 3, end cap 5 being installed on housing 4, then dial gauge being fixed on the central authorities of end cap 5 and making zero;
3, take off end cap 5, impeller, on the step of motor shaft 1, then loads in motor shaft 1, is fixed with screw 6 by the technique jack-up pad pad by thickness being b;
4, end cap 5 is installed on housing 4 again, then measures the raising height c of end cap 5 with dial gauge;
5, the thickness deltat of the adjustment pad installed is needed be guaranteed impeller and housing motion gap a of formula Δ=b-c-a;
6, technique jack-up pad is taken out, change the adjustment pad 2 that thickness is Δ into, complete the adjustment in DC electropump gap.
Beneficial effect of the present invention: the invention provides a kind of aviation DC electropump clearance adjustment method, this kind of clearance measurement mode is to being difficult to direct measuring point and requiring that meticulousr gap fast, simply can complete adjustment.1) patent of the present invention avoids the drawback that movement clearance cannot be measured; 2) patent of the present invention avoids the drawback that impeller curved surface is unfavorable for measuring; 3) patent of the present invention makes movement clearance Survey control between impeller and end cap without the need to the design specialized frock clamping of complexity, simplify method of measurement, improve working efficiency.
Accompanying drawing illustrates:
Fig. 1 is the structural representation that the present invention is applied to certain model oil feed pump;
Fig. 2 is use schematic diagram of the present invention;
Wherein, 1-motor shaft, 2-adjusts pad, 3-impeller, 4-fuel pump housing, 5-end cap, 6-screw, a-impeller and end cover clearance, the thickness of b-technique jack-up pad.
Embodiment
Below for certain model fuel feeding pump structure, by embodiment, the present invention is described in further detail.As shown in Figures 1 and 2.
A kind of aviation DC electropump clearance adjustment method, this aviation DC electropump comprises motor shaft 1, adjustment pad 2, impeller 3, housing 4, end cap 5, screw 6, comprises the following steps:
1, setting impeller 3 with end cap 5 clearance requirement is a;
2, when not installing impeller 3, end cap 5 being installed on housing 4, then dial gauge being fixed on the central authorities of end cap 5 and making zero;
3, take off end cap 5, impeller, on the step of motor shaft 1, then loads in motor shaft 1, is fixed with screw 6 by the technique jack-up pad pad by thickness being b;
4, end cap 5 is installed on housing 4 again, then measures the raising height c of end cap 5 with dial gauge;
5, the thickness deltat of the adjustment pad installed is needed be guaranteed impeller and housing motion gap a of formula Δ=b-c-a;
6, technique jack-up pad is taken out, change the adjustment pad 2 that thickness is Δ into, complete the adjustment in DC electropump gap.
Embodiment:
For certain product, the present invention will be further described.Impeller 3 and end cap 5 clearance requirement of this product are a is 0.5mm, according to said method, adjusts:
1, setting impeller 3 with end cap 5 clearance requirement is a=0.5mm;
2, when not installing impeller 3, end cap 5 being installed on housing 4, then dial gauge being fixed on the central authorities of end cap 5 and making zero;
3, take off end cap 5, impeller, on the step of motor shaft 1, then loads in motor shaft 1, is fixed with screw 6 by the technique jack-up pad pad by thickness being b=2mm;
4, end cap 5 is installed on housing 4 again, then measures the raising height c of end cap 5 with dial gauge, measure and obtain c=0.3mm;
5, the thickness deltat=2-0.3-0.5=1.2mm of the adjustment pad installed is needed be guaranteed impeller and housing motion gap a of formula Δ=b-c-a;
6, technique jack-up pad is taken out, change the adjustment pad 2 that thickness is Δ=1.2mm into, complete the adjustment in DC electropump gap.
Claims (1)
1. an aviation DC electropump clearance adjustment method, this aviation DC electropump comprises motor shaft (1), adjustment pad (2), impeller (3), housing (4), end cap (5), screw (6), it is characterized in that, comprise the following steps:
1) setting impeller (3) with end cap (5) clearance requirement is a;
2) when not installing impeller (3), end cap (5) being installed on housing (4), then dial gauge being fixed on the central authorities of end cap (5) and making zero;
3) take off end cap (5), impeller, on the step of motor shaft (1), then loads in motor shaft (1), is fixed with screw (6) by the technique jack-up pad pad by thickness being b;
4) end cap (5) is installed on housing (4) again, then measures the raising height c of end cap (5) with dial gauge;
5) thickness deltat of the adjustment pad installed is needed be guaranteed impeller and housing motion gap a of formula Δ=b-c-a;
6) technique jack-up pad is taken out, change the adjustment pad (2) that thickness is Δ into, complete the adjustment in DC electropump gap.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310671980.3A CN103711710B (en) | 2013-12-10 | 2013-12-10 | A kind of aviation DC electropump clearance adjustment method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310671980.3A CN103711710B (en) | 2013-12-10 | 2013-12-10 | A kind of aviation DC electropump clearance adjustment method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103711710A CN103711710A (en) | 2014-04-09 |
| CN103711710B true CN103711710B (en) | 2016-01-20 |
Family
ID=50404966
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310671980.3A Active CN103711710B (en) | 2013-12-10 | 2013-12-10 | A kind of aviation DC electropump clearance adjustment method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103711710B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106289024B (en) * | 2015-05-25 | 2018-03-02 | 西安航空动力股份有限公司 | A kind of method for measuring the actual end clearance of enclosed gear pump |
| CN113739673A (en) * | 2021-08-20 | 2021-12-03 | 白银有色集团股份有限公司 | Method for measuring clearance in maintenance and installation of precision equipment or large-scale fan |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3771927A (en) * | 1972-03-15 | 1973-11-13 | Purex Corp | Impeller running clearance adjustment device |
| EP1134426A2 (en) * | 2000-03-13 | 2001-09-19 | Ritz Pumpenfabrik GmbH & Co. KG | Centrifugal pump rotor |
| CN201090502Y (en) * | 2007-08-17 | 2008-07-23 | 上海连成（集团）有限公司 | Auxiliary impeller positioning structure for automatic control self-sucking pump without seal |
| CN201437781U (en) * | 2009-06-05 | 2010-04-14 | 佛山市肯富来安德里兹泵有限公司 | Centrifugal pump capable of being convenient to adjust the clearance between front liner plate and impeller |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS595897A (en) * | 1982-07-02 | 1984-01-12 | Sanyo Electric Co Ltd | Adjustment of gap for pump |
| JP5062033B2 (en) * | 2008-05-21 | 2012-10-31 | 株式会社ジェイテクト | Centrifugal compressor |
-
2013
- 2013-12-10 CN CN201310671980.3A patent/CN103711710B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3771927A (en) * | 1972-03-15 | 1973-11-13 | Purex Corp | Impeller running clearance adjustment device |
| EP1134426A2 (en) * | 2000-03-13 | 2001-09-19 | Ritz Pumpenfabrik GmbH & Co. KG | Centrifugal pump rotor |
| CN201090502Y (en) * | 2007-08-17 | 2008-07-23 | 上海连成（集团）有限公司 | Auxiliary impeller positioning structure for automatic control self-sucking pump without seal |
| CN201437781U (en) * | 2009-06-05 | 2010-04-14 | 佛山市肯富来安德里兹泵有限公司 | Centrifugal pump capable of being convenient to adjust the clearance between front liner plate and impeller |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103711710A (en) | 2014-04-09 |
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| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |