CN104653446A - Thermal protection test method for fuel pump of airplane - Google Patents
Thermal protection test method for fuel pump of airplane Download PDFInfo
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- CN104653446A CN104653446A CN201310607961.4A CN201310607961A CN104653446A CN 104653446 A CN104653446 A CN 104653446A CN 201310607961 A CN201310607961 A CN 201310607961A CN 104653446 A CN104653446 A CN 104653446A
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- pump
- core
- impeller
- thermal protection
- protection test
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Abstract
The invention belongs to the field of aviation, and relates to a thermal protection test method for a fuel pump of an airplane. The method is characterized in that overall dimension of an impeller of a tested oil pump is improved to enable the impeller to be in a certain interference fit with an inner cavity of a core of the oil pump, so as to simulate the overload work of a motor during the operation process of the oil pump; the oil pump enters the over-temperature state, in order to verify whether a protector is valid in the operation process of the oil pump. Compared with the traditional thermal protection test method of the fuel pump, the method has the advantages that the over-temperature in the working state can be really verified; in addition, the method is simple, convenient to use, suitable or the thermal protection test of any fuel pump, high in generality, and worthy of popularization and application.
Description
Technical field
The invention belongs to aviation field, relate to a kind of Thermal protection test method of aircraft fuel pump.
Background technique
The fuel pump that domestic existing aircraft adopts is arranged in fuel tank, and when fuel pump motor internal breaks down, motor part may produce high temperature, causes negative effect to fuel tank Security.Therefore, motor is provided with the power supply of heat protector at overtemperature state incision power machine.But in actual design, the extremely difficult simulation of oil feed pump motor overtemperature fault, is just positioned in temperature control box by motor usually, under checking off working state during motor overtemperature, whether heat protector normally works.And the temperature rising of temperature control box makes heat pass to inside gradually by the outside of the pump housing; directly generate heat with real work process internal pump core and have obvious difference; there is the comparatively significantly temperature difference in the temperature of incubator and the true temperature of heat protector, thus can not accurately can normally work on request by heat protector.
Summary of the invention
The object of this invention is to provide a kind of simple to operate, can the Thermal protection test method of real simulation fuel pump abnormal operating state.
Technological scheme of the present invention: a kind of Thermal protection test method of aircraft fuel pump, described aircraft fuel pump comprises the pump housing 1 and pump core 2, and wherein pump core 2 also comprises pump in-core chamber 2a, and impeller 2b and motor 2c, comprises following concrete steps:
Step one, process new large impeller 2d, ensure its install after and be in interference fit between pump in-core chamber;
Step 2, pump core 2 to be extracted out from the pump housing 1; Original-pack impeller is pulled down from pump core 2; Large impeller 2d after size adjusting is installed on pump core 2;
Step 3, pump core 2 to be inserted in the pump housing 1, and install screw; Oil fuel feed pump is energized, and tests.
Advantage of the present invention and beneficial effect:
The method of the present invention is by improving tested fuel pump impeller overall sizes; make the interference fit formed between impeller and oil pump pump in-core chamber to a certain degree; carry out the overload work of the motor in simulated oil pump work process; make oil pump overtemperature, to verify whether heat protector is effective in operation of oil pump process.Compared with traditional fuel pump Thermal protection test method, Thermal protection test method given in the present invention can verify the overtemperature of working state really, and method is simple; easy to use; be applicable to the Thermal protection test of any fuel pump, highly versatile, has application value.
Accompanying drawing explanation
Fig. 1 is heat protector catenation principle figure in the present invention;
Fig. 2 is the structural representation of aircraft fuel pump in the present invention;
Fig. 3 is the aircraft fuel pump structural representation after middle period of the present invention wheel adjustment;
Wherein, the 1-pump housing, 1a-relief opening, 1b-pump discharge, 1c-pump intake, 1d-is vented check valve, 1e-pump discharge check valve, 2-pump core, 2a-pump in-core chamber, 2b-impeller, 2c-motor, the large impeller of 2d-, the self-styled valve assembly of 3-, 4-sealing configuration, 5-fuel tank.
Embodiment
Below in conjunction with accompanying drawing, the present invention is described in further detail, refers to Fig. 1 to Fig. 3.
The common overtemperature of oil feed pump is all caused by motor, no matter and which kind of reason motor overtemperature is at work by first---foreign matter clamping stagnation, bearing damage etc., finally all show as motor load excessive, overwork heating cause motor abnormality heat up burn out; Heat protector is a heat-sensitive element, and in order to ensure that oil pump can not cause oil-fired system and to cause danger situation by overtemperature, be usually series on the winding of oil feed pump motor 2c, when motor portion temperature exceedes specified value, fusing is to make oil feed pump quit work in time; The catenation principle figure of heat protector is shown in Fig. 1.
During concrete enforcement, its step is as follows:
Step one, reference install the size of impeller 2b place pump in-core chamber 2a, design and process new large impeller 2d, ensure that it is installed between rear and pump in-core chamber 2a and are in interference fit;
Step 2, dismounting pump core 2 and the screw be connected between the pump housing 1, then pump core 2 is extracted out from the pump housing 1; Original-pack impeller 2b is pulled down from pump core 2, the larger impeller 2d after size adjusting is installed on pump core 2;
Step 3, pump core 2 to be inserted in the pump housing 1, and install screw; Oil fuel feed pump is energized, and at this moment, large impeller 2d is in clamping stagnation state, and can not rotate, motor temperature raises very soon; If heat protector can fuse in time, then illustrate that the heat protector of fuel pump can normally work.
Embodiment:
Carry out Thermal protection test to the fuel pump of certain model, concrete steps are as follows:
The maximum diameter of the impeller 2b of step one, this model fuel pump is 62mm, and the gap between impeller 2b and pump in-core chamber 2a is 0.35mm; On the basis of original impeller 2b, again process new large impeller 2d, its maximum diameter is adjusted to 63.5mm;
Step 2, dismounting pump core 2 and the screw be connected between the pump housing 1, then pump core 2 is extracted out from the pump housing 1; Original-pack impeller 2b is pulled down from pump core 2, the larger impeller 2d after size adjusting is installed on pump core 2; At this moment, interference fit is between large impeller 2d and pump in-core chamber 2a;
Step 3, pump core 2 to be inserted in the pump housing 1, and install screw; Oil fuel feed pump is energized, and large impeller 2d is in clamping stagnation state, and can not rotate, motor temperature raises very soon; Very fast, the heat protector fusing on motor 2c, off-test, proves that the heat protector of this model fuel pump can normally work.
Claims (1)
1. a Thermal protection test method for aircraft fuel pump, described aircraft fuel pump comprises the pump housing (1) and pump core (2), and wherein pump core (2) also comprises pump in-core chamber (2a), and impeller (2b) and motor (2c), is characterized in that, comprise following concrete steps:
Step one, process new large impeller (2d), ensure its install after and be in interference fit between pump in-core chamber;
Step 2, pump core (2) to be extracted out from the pump housing (1); Original-pack impeller is pulled down from pump core (2); Large impeller (2d) after size adjusting is installed on pump core (2);
Step 3, pump core (2) to be inserted in the pump housing (1), and install screw; Oil fuel feed pump is energized, and tests.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310607961.4A CN104653446A (en) | 2013-11-22 | 2013-11-22 | Thermal protection test method for fuel pump of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310607961.4A CN104653446A (en) | 2013-11-22 | 2013-11-22 | Thermal protection test method for fuel pump of airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104653446A true CN104653446A (en) | 2015-05-27 |
Family
ID=53244966
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310607961.4A Pending CN104653446A (en) | 2013-11-22 | 2013-11-22 | Thermal protection test method for fuel pump of airplane |
Country Status (1)
| Country | Link |
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| CN (1) | CN104653446A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114750976A (en) * | 2022-06-15 | 2022-07-15 | 成都凯天电子股份有限公司 | Ground performance test system and method for self-adaptive oil supply system of helicopter |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0629037A1 (en) * | 1993-06-08 | 1994-12-14 | POMPES SALMSON Société Anonyme à directoire dite: | Power supply control process and device for an electric asynchronous motor |
| US6801031B1 (en) * | 1998-09-04 | 2004-10-05 | Wilo Gmbh | Method and apparatus for current measurement for electronically-controlled pump |
| CN2893251Y (en) * | 2006-03-17 | 2007-04-25 | 瑞立集团有限公司 | Electric oil fuel pump |
| CN102073010A (en) * | 2009-11-19 | 2011-05-25 | 许晓华 | Motor stalling mechanism |
| CN102900569A (en) * | 2012-10-10 | 2013-01-30 | 南京工业大学 | Fuel pump |
| CN102953881A (en) * | 2012-11-22 | 2013-03-06 | 无锡惠山泵业有限公司 | Fuel pump |
| CN103334934A (en) * | 2013-07-10 | 2013-10-02 | 上海霍雷加新材料科技有限公司 | Electric petrol-feed pump with self-protection function |
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2013
- 2013-11-22 CN CN201310607961.4A patent/CN104653446A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0629037A1 (en) * | 1993-06-08 | 1994-12-14 | POMPES SALMSON Société Anonyme à directoire dite: | Power supply control process and device for an electric asynchronous motor |
| US6801031B1 (en) * | 1998-09-04 | 2004-10-05 | Wilo Gmbh | Method and apparatus for current measurement for electronically-controlled pump |
| CN2893251Y (en) * | 2006-03-17 | 2007-04-25 | 瑞立集团有限公司 | Electric oil fuel pump |
| CN102073010A (en) * | 2009-11-19 | 2011-05-25 | 许晓华 | Motor stalling mechanism |
| CN102900569A (en) * | 2012-10-10 | 2013-01-30 | 南京工业大学 | Fuel pump |
| CN102953881A (en) * | 2012-11-22 | 2013-03-06 | 无锡惠山泵业有限公司 | Fuel pump |
| CN103334934A (en) * | 2013-07-10 | 2013-10-02 | 上海霍雷加新材料科技有限公司 | Electric petrol-feed pump with self-protection function |
Non-Patent Citations (1)
| Title |
|---|
| 黄超醒: "电机过热保护", <<家电科技>> * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114750976A (en) * | 2022-06-15 | 2022-07-15 | 成都凯天电子股份有限公司 | Ground performance test system and method for self-adaptive oil supply system of helicopter |
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Application publication date: 20150527 |
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| RJ01 | Rejection of invention patent application after publication |