CN204610308U - Aircraft fuel pump the property test platform of centrifugal pump - Google Patents
Aircraft fuel pump the property test platform of centrifugal pump Download PDFInfo
- Publication number
- CN204610308U CN204610308U CN201520200222.8U CN201520200222U CN204610308U CN 204610308 U CN204610308 U CN 204610308U CN 201520200222 U CN201520200222 U CN 201520200222U CN 204610308 U CN204610308 U CN 204610308U
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- centrifugal pump
- pump
- connecting tube
- test platform
- property test
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- Expired - Fee Related
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Abstract
The utility model discloses a kind of aircraft fuel pump the property test platform of centrifugal pump, the vane pump assembly comprise fuel tank, being connected respectively with fuel tank successively, oil are filtered, gearbox, by trial product: be wherein connected with BF-13 low pressure road by connecting tube by trial product, first connecting tube is provided with an inlet adjusting valve, and the second connecting tube is provided with an outlet regulating valve.The utility model mainly uses aircraft fuel pump (centrifugal pump) to test, import frequency variator is adopted to control variable-frequency motor, realize the precise hard_drawn tuhes to centrifugal pump by the highi degree of accuracy gearbox of 1:15, gearbox adopts self-loopa oil lubrication system, can carry out work for a long time.Meanwhile, low pressure and mass flow fuel oil test platform provides constant voltage, and the fuel of constant current to centrifugal pump, thus meets the requirement of the various Test item of centrifugal pump.
Description
Technical field
The utility model relate to a kind of aircraft fuel pump the property test platform of centrifugal pump, belong to the hydraulic pressure maintenance field on airliner.
Background technique
The fuel pump of aircraft is widely used in the systems such as aircraft air condition, supercharging, APU auxiliary power unit.Wherein fuel pump is that in airplane fuel accessory, removal rate is higher, is wherein main repairing annex.Ordinary test platform is fairly simple, testing complex, and rotating speed controls to be not easy, and Test item test department is perfect, so a kind of excellent in design of market in urgent need, for the property test platform after the maintenance of aircraft fuel pump (centrifugal pump) annex.
Aircraft fuel pump property test platform for common: be not generally with driving source and speed change gear, can not meet the accurate rotating speed needs of centrifugal fuel pump, can not control with hourly velocity.This causes great inconvenience to maintenance work, and my company determines to carry out registration study to this for this reason, and the rotational speed regulation fundamentally solving fuel oil centrifugal pump is inconvenient, and pressure, flux test are unstable, the problem that testing efficiency is low.
Model utility content
Goal of the invention: in order to solve the deficiencies in the prior art, the utility model provide a kind of aircraft fuel pump the property test platform of centrifugal pump.
Technological scheme: in order to reach foregoing invention object, the technical solution adopted in the utility model is:
A kind of aircraft fuel pump the property test platform of centrifugal pump, comprise fuel tank, the vane pump assembly be connected successively respectively with fuel tank, oil filter, gearbox, by trial product, wherein be connected with BF-13 low pressure road by connecting tube by trial product, first connecting tube is provided with a voltage supply modulating valve, second connecting tube is provided with a large discharge oil return regulating valve, 3rd connecting tube is provided with a small flow oil return regulating valve, wherein BF-13 is existing test stand, its effect is to provide certain pressure and flow, and regulate return pressure and flow, vane pump assembly comprises blade, rotor, Sealing.
Further, be aircraft fuel pump or centrifugal pump by trial product.
Further, gearbox is provided with an explosion-proof variable frequency motor.
Further, a pressure gauge is provided with between described gearbox and fuel tank.
Further, described second connecting tube and the 3rd connecting tube are respectively equipped with the second flexible pipe and the 3rd flexible pipe.
Further, a pressure gauge is provided with between described gearbox and fuel tank.
From the low pressure connecting pipe road of BF-13 to by the import of trial product, connection outlet pipeline is to interface A4 and C1, open gate valve, voltage supply modulating valve keeps pressure and the flow of import, open the oil feed pump of gearbox to gear-box fuel feeding, regulate variable-frequency motor to make its output speed meet by the requirement of trial product, regulated by the outlet pressure of trial product and flow by large discharge oil return regulating valve.
Aircraft fuel pump (centrifugal pump) test stand mainly uses aircraft fuel pump (centrifugal pump) to test.Adopt import frequency variator to control variable-frequency motor, realize the precise hard_drawn tuhes to centrifugal pump by the highi degree of accuracy gearbox of 1:15, gearbox adopts self-loopa oil lubrication system, can carry out work for a long time.Meanwhile, low pressure and mass flow fuel oil test platform provides constant voltage, and the fuel of constant current to centrifugal pump, thus meets the requirement of the various Test item of centrifugal pump.
This test stand is rationally distributed, designs perfect, measures and adopts high-precision metrical instrument and instrument, and parameter measurement is accurate and control overflow is accurate.
Beneficial effect: the aircraft fuel pump that the utility model provides the property test platform of centrifugal pump, have the following advantages:
1) adopt import frequency variator to control variable-frequency motor, realize the precise hard_drawn tuhes to centrifugal pump by the highi degree of accuracy gearbox of 1:15, solve the uppity hang-up of centrifugal pump rotating speed.
2) gearbox adopts self-loopa oil lubrication system, work can be carried out for a long time, concerning centrifugal pump, can simulated aircraft state carry out repeatedly testing under different rotating speeds, pressure, flow for a long time, all measurements adopt high-precision metrical instrument and instrument, and parameter measurement is accurate and control overflow is accurate, has storage print function concurrently, can contrast all products, checking.
3) this test stand is rationally distributed, designs perfect, easy for installation, and test adopts computer control and storage, and efficiency is high.
4) this Test-bed Design fast interface and clip, can install connecting test fast according to different products, shorten the time of carrying out product installation, improves the repair quality of product.
Accompanying drawing explanation
Fig. 1 is structural representation of the present utility model.
Embodiment
Below in conjunction with accompanying drawing, illustrate the utility model further.
As shown in Figure 1 a kind of aircraft fuel pump the property test platform of centrifugal pump, comprise fuel tank 1, the vane pump assembly 2 be connected successively respectively with fuel tank 1, oil filter 3, gearbox 6, by trial product 7: be wherein connected with BF-13 low pressure road by connecting tube by trial product 7, first connecting tube 11 is provided with a voltage supply modulating valve 4a, second connecting tube 12 is provided with a large discharge oil return regulating valve 8a, 3rd connecting tube 13 is provided with a small flow oil return regulating valve 15a, gearbox 6 is provided with an explosion-proof variable frequency motor 5, a pressure gauge 4 is provided with between gearbox 6 and fuel tank 1, described first connecting tube 11 is provided with gate valve 8 and first flexible pipe 9, described second connecting tube 12 and the 3rd connecting tube 13 are respectively equipped with the second flexible pipe 14 and the 3rd flexible pipe 15a.
The present embodiment with by trial product 7 for aircraft fuel pump (centrifugal pump), start this test stand, open vane pump assembly 2, pressure and the flow of import is kept by voltage supply modulating valve 4a, open the vane pump assembly 2 of gearbox 6 to gear-box fuel feeding, explosion-proof adjustment variable-frequency motor 5 makes its output speed meet by the requirement of trial product, regulates by the outlet pressure of trial product and flow by 8a, to survey product performance as follows:
1, aircraft fuel pump (centrifugal pump) slewing gear: power 5.5KW, rotating speed≤9000rpm
2, aircraft fuel pump (centrifugal pump) charge oil pressure: 0.8 ~ 2.55kgf/cm2A
3, aircraft fuel pump (centrifugal pump) outlet pressure: 2.8 ~ 3.2kgf/cm2
4, aircraft fuel pump (centrifugal pump) rate of discharge: 7800L/H.
Can the precise hard_drawn tuhes of accurate control pump by the utility model, to the control of its rotating speed, thus the various Test item requirement of centrifugal pump can be met.
Above-mentioned mode of execution, only for technical conceive of the present utility model and feature are described, its objective is to allow and is familiar with these those skilled in the art and can understands content of the present utility model and implement according to this, can not limit protection domain of the present utility model with this.All equivalents done by the utility model Spirit Essence or modification, all should be encompassed within protection domain of the present utility model.
Claims (6)
1. the property test platform of a Fei Jiranyoubeng centrifugal pump, it is characterized in that: comprise fuel tank (1), distinguish vane pump assembly (2) connected successively with fuel tank (1), oil filters (3), gearbox (6), by trial product (7): be wherein connected with BF-13 low pressure road by connecting tube by trial product (7), first connecting tube (11) is provided with a voltage supply modulating valve (4a), second connecting tube (12) is provided with a large discharge oil return regulating valve (8a), and the 3rd connecting tube (13) is provided with a small flow oil return regulating valve (15a).
2. the property test platform of Fei Jiranyoubeng centrifugal pump as claimed in claim 1, is characterized in that: described is aircraft fuel pump or centrifugal pump by trial product (7).
3. aircraft fuel pump as claimed in claim 1 the property test platform of centrifugal pump, it is characterized in that: described gearbox (6) is provided with an explosion-proof variable frequency motor (5).
4. aircraft fuel pump as claimed in claim 1 the property test platform of centrifugal pump, it is characterized in that: between described gearbox and fuel tank (1), be provided with a pressure gauge (4).
5. aircraft fuel pump as claimed in claim 1 the property test platform of centrifugal pump, it is characterized in that: described first connecting tube (11) is provided with a gate valve (8) and the first flexible pipe (9).
6. aircraft fuel pump as claimed in claim 1 the property test platform of centrifugal pump, it is characterized in that: described second connecting tube and the 3rd connecting tube are respectively equipped with the second flexible pipe and the 3rd flexible pipe.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520200222.8U CN204610308U (en) | 2015-04-03 | 2015-04-03 | Aircraft fuel pump the property test platform of centrifugal pump |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520200222.8U CN204610308U (en) | 2015-04-03 | 2015-04-03 | Aircraft fuel pump the property test platform of centrifugal pump |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204610308U true CN204610308U (en) | 2015-09-02 |
Family
ID=53962877
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520200222.8U Expired - Fee Related CN204610308U (en) | 2015-04-03 | 2015-04-03 | Aircraft fuel pump the property test platform of centrifugal pump |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204610308U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10428816B2 (en) | 2016-10-24 | 2019-10-01 | Hamilton Sundstrand Corporation | Variable speed multi-stage pump |
| CN112197945A (en) * | 2020-08-26 | 2021-01-08 | 中广核核电运营有限公司 | Test method for testing pump output after full test of test pump |
-
2015
- 2015-04-03 CN CN201520200222.8U patent/CN204610308U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10428816B2 (en) | 2016-10-24 | 2019-10-01 | Hamilton Sundstrand Corporation | Variable speed multi-stage pump |
| CN112197945A (en) * | 2020-08-26 | 2021-01-08 | 中广核核电运营有限公司 | Test method for testing pump output after full test of test pump |
| CN112197945B (en) * | 2020-08-26 | 2022-04-22 | 中广核核电运营有限公司 | Test method for testing pump output after full test of test pump |
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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 |
Granted publication date: 20150902 Termination date: 20190403 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |