CN205203423U - Refrigerating system suitable for aircraft fuel oil system icing tests - Google Patents
Refrigerating system suitable for aircraft fuel oil system icing tests Download PDFInfo
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- CN205203423U CN205203423U CN201521037617.7U CN201521037617U CN205203423U CN 205203423 U CN205203423 U CN 205203423U CN 201521037617 U CN201521037617 U CN 201521037617U CN 205203423 U CN205203423 U CN 205203423U
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Abstract
The utility model relates to a refrigerating system suitable for aircraft fuel oil system icing tests, including environment case unit, cycle control unit and cooling unit, environment case unit is used for placing the testpieces to the ambient temperature who locates the testpieces keeps warm, the cycle control unit is used for the oil -fired circulation in the control test spare, cooling unit be used for with the fuel is cooled down, through the fuel circulation in the experimental oil tank of cycle control unit control, make the fuel cooling carrying out the heat exchange through the fuel of cooling unit in with the system, the fuel circulates to the environment incasement and carries out the constant temperature test. The utility model discloses an ambient temperature when refrigerating system can imitate the aircraft and aloft flies, through the utility model discloses a refrigerating system can probe the aircraft fuel oil system refrigeration process under the condition aloft, has advantages such as simple structure, refrigeration effect are good, easy realization.
Description
Technical field
The utility model belongs to aircraft fuel system test field, particularly relates to a kind of refrigeration system being applicable to aircraft fuel system icing tests.
Background technology
Aircraft, when high-altitude flight, freezes because low temperature environment causes the moisture in fuel oil to separate out, easily causes blocking fuel passage, and then affect engine work.The process that during in order to simulate aircraft high-altitude flight, combustion water content in oil freezes, checking fuel line low-temperature working ability, probes into fuel oil system and to freeze mechanism, need a kind of refrigeration system being applicable to aircraft fuel system icing tests.
Utility model content
The purpose of this utility model is to provide a kind of refrigeration system being applicable to aircraft fuel system icing tests, solves the problem of cooling test system of freezing without aircraft fuel system at present.
For achieving the above object, the technical solution adopted in the utility model is: a kind of refrigeration system being applicable to aircraft fuel system icing tests, comprise environmental cabinet unit, cycle control unit and refrigeration unit, described environmental cabinet unit for placing test article, and is incubated the ambient temperature residing for test article; Described cycle control unit is used for the circulation of the fuel oil in Control experiment part; Described refrigeration unit is used for described fuel oil to lower the temperature.
Further, described environmental cabinet unit comprises environment casing and test fuel tank, and described test fuel tank is placed in described environment casing, is connected with cycle control unit and refrigeration unit by pipeline, and described environment casing is incubated test fuel tank.
Further, described cycle control unit comprises the first pilot piping, the second pilot piping and the 3rd pilot piping, described first pilot piping comprises the first oil feed pump, first-class gauge and the first electromagnetic valve, and described first oil feed pump, first-class gauge are connected by pipeline with the first electromagnetic valve; Described second pilot piping comprises the second oil feed pump, second gauge and the second electromagnetic valve, and described second oil feed pump, second gauge are connected by pipeline with the second electromagnetic valve; Described 3rd pilot piping comprises the first tubing pump, the 3rd flow counter and the 3rd electromagnetic valve, and described first tubing pump, the 3rd flow counter are connected by pipeline with the 3rd electromagnetic valve; Described first pilot piping, the second pilot piping, the 3rd pilot piping is in parallel and be provided with the first import and the first outlet, and described first import is connected with test fuel tank, and described first exports and be connected with refrigeration unit.
Further, described refrigeration unit comprises the first refrigeration pipe and the second refrigeration pipe, and described first refrigeration pipe comprises the 4th electromagnetic valve and single-stage compression unit, and described 4th electromagnetic valve is connected by pipe pipeline with single-stage compression unit; Described second refrigeration pipe comprises the 5th electromagnetic valve and overlapping compressor set, and described 5th electromagnetic valve is connected by pipe pipeline with overlapping compressor set; Described first refrigeration pipe and the second refrigeration pipe are in parallel and be provided with the second import and the second outlet, and described second import export with first of cycle control unit and is connected, and described second exports and test fuel tank and be connected.
Further, the first refrigeration pipe 0 cooling extent is normal temperature extremely subzero 20 DEG C, and the second refrigeration pipe cooling extent is subzero 20 DEG C to subzero 40 DEG C.
A kind of refrigeration system being applicable to aircraft fuel system icing tests of the present utility model, by the fuel flow communication in cycle control unit controls test fuel tank, fuel oil is lowered the temperature intrasystem fuel oil being carried out interchange of heat by refrigeration unit, fuel oil is circulated in environmental cabinet and is incubated.Refrigeration system of the present utility model can imitate the ambient temperature of aircraft when high-altitude flight, the process of refrigerastion of aircraft fuel system under high altitude conditions can be probed into by system of the present utility model, have that structure is simple, good refrigeration effect, be easy to the advantages such as realization.
Accompanying drawing explanation
Accompanying drawing to be herein merged in specification sheets and to form the part of this specification sheets, shows and meets embodiment of the present utility model, and is used from specification sheets one and explains principle of the present utility model.
Fig. 1 is the composition schematic diagram being applicable to the refrigeration system of aircraft fuel system icing tests according to the utility model one embodiment.
1 environmental cabinet unit, 2 cycle control unit, 3 refrigeration units;
101 environment casings, 102 test fuel tanks;
210 first pilot piping, 211 first oil pumps, 212 first-class gauge, 213 first electromagnetic valves;
220 second pilot piping, 221 second oil pumps, 222 second gauge, 223 second electromagnetic valves;
230 the 3rd pilot piping, 231 first tubing pumps, 232 the 3rd flow counter, 233 the 3rd electromagnetic valves;
310 first refrigeration pipes, 311 the 4th electromagnetic valves, 312 single-stage compression units;
320 second refrigeration pipes, 321 the 5th electromagnetic valves, 322 overlapping compressor set.
Detailed description of the invention
The object implemented for making the utility model, technical scheme and advantage clearly, below in conjunction with the accompanying drawing in the utility model embodiment, are further described in more detail the technical scheme in the utility model embodiment.In the accompanying drawings, same or similar label represents same or similar element or has element that is identical or similar functions from start to finish.Described embodiment is the utility model part embodiment, instead of whole embodiments.Be exemplary type below by the embodiment be described with reference to the drawings, be intended to for explaining the utility model, and can not be interpreted as restriction of the present utility model.Based on the embodiment in the utility model, those of ordinary skill in the art are not making the every other embodiment obtained under creation type work prerequisite, all belong to the scope of the utility model protection.Below in conjunction with accompanying drawing, embodiment of the present utility model is described in detail.
In description of the present utility model, it will be appreciated that, term " " center ", " longitudinal direction ", " transverse direction ", " front ", " afterwards ", " left side ", " right side ", " vertically ", " level ", " top ", " end ", " interior ", orientation or the position relationship of the instruction such as " outward " are based on orientation shown in the drawings or position relationship, only the utility model and simplified characterization for convenience of description, instead of indicate or imply that the device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore the restriction to the utility model protection domain can not be interpreted as.
Be illustrated in figure 1 a kind of refrigeration system being applicable to aircraft fuel system icing tests of the present utility model, comprise environmental cabinet unit 1, cycle control unit 2 and refrigeration unit 3, described environmental cabinet unit 1 for placing test article, and is incubated the ambient temperature residing for test article; Described cycle control unit 2 is for the circulation of the fuel oil in Control experiment part; Described refrigeration unit 3 is for lowering the temperature described fuel oil.
It is to be noted, described environmental cabinet unit 1 comprises environment casing 101 and test fuel tank 102, described test fuel tank 102 is placed in described environment casing 101, is connected with cycle control unit 2 and refrigeration unit 3 by pipeline, and described environment casing 101 is incubated test fuel tank 102.
It is to be noted, described cycle control unit 2 comprises the first pilot piping 210, second pilot piping 220 and the 3rd pilot piping 230, described first pilot piping 210 comprises the first oil feed pump 211, first-class gauge 212 and the first electromagnetic valve 213, and described first oil feed pump 211, first-class gauge 212 are connected by pipeline with the first electromagnetic valve 213; Described second pilot piping 220 comprises the second oil feed pump 221, second gauge 222 and the second electromagnetic valve 223, and described second oil feed pump 221, second gauge 222 are connected by pipeline with the second electromagnetic valve 223; Described 3rd pilot piping 230 comprises the first tubing pump 231, the 3rd flow counter 232 and the 3rd electromagnetic valve 233, and described first tubing pump 231, the 3rd flow counter 232 are connected by pipeline with the 3rd electromagnetic valve 233; Described first pilot piping 210, second pilot piping 220, the 3rd pilot piping 230 are in parallel and be provided with the first import 240 and the first outlet 250, and described first import 240 is connected with test fuel tank 120, and described first exports 250 is connected with refrigeration unit 3.
It is to be noted, described refrigeration unit 3 comprises the first refrigeration pipe 310 and the second refrigeration pipe 320, described first refrigeration pipe 310 comprises the 4th electromagnetic valve 311 and single-stage compression unit 312, and described 4th electromagnetic valve 311 is connected by pipe pipeline with single-stage compression unit 312; Described second refrigeration pipe 320 comprises the 5th electromagnetic valve 321 and overlapping compressor set 322, and described 5th electromagnetic valve 321 is connected by pipe pipeline with overlapping compressor set 322; Described first refrigeration pipe 310 and the second refrigeration pipe 320 are in parallel and be provided with the second import 330 and the second outlet 340, and described second import 330 export 250 with first of cycle control unit 2 and is connected, described second export 340 with test fuel tank 120 and be connected.
It is pointed out that the first refrigeration pipe 310 cooling extent is normal temperature extremely subzero 20 DEG C, the second refrigeration pipe 320 cooling extent is subzero 20 DEG C to subzero 40 DEG C.
Concrete, applying a kind of working process being applicable to the refrigeration system of aircraft fuel system icing tests of the present utility model is: refrigeration system of the present utility model carries out four-stage altogether:
(1) fuel oil is down to-2 DEG C from normal temperature, and is incubated;
(2) fuel oil is down to-11 DEG C from-2 DEG C, and is incubated;
(3) fuel oil is down to-20 DEG C from-11 DEG C, and is incubated;
(4) fuel oil is down to-40 DEG C from-20 DEG C, and is incubated.
1, open the first oil pump 231, the 3rd electromagnetic valve 233, the 4th electromagnetic valve 311, make the fuel oil in test fuel tank 102 stir circulation;
2, open single-stage compression unit 312, by forced heat-exchanging, the fuel oil in pipeline is cooled to-2 DEG C from normal temperature (room temperature);
3, the first tubing pump 231, the 3rd electromagnetic valve 233, single-stage compression unit 312 is closed, open the first oil pump 211, second oil pump 221, open the first electromagnetic valve 213, second electromagnetic valve 223 according to the flow (flow shown with reference to first-class gauge 212 and second gauge 222 regulates) of regulation, carry out-2 DEG C of stage isothermal experiments of fuel oil;
4, close the first oil pump 211, second oil pump 221, first electromagnetic valve 213, second electromagnetic valve 223, open the first tubing pump 231, the 3rd electromagnetic valve 233, single-stage compression unit 312, by forced heat-exchanging, fuel oil is dropped to-11 DEG C;
5, close the first tubing pump 231, the 3rd electromagnetic valve 233, single-stage compression unit 312, open the first oil pump 211, second oil pump 221, open the first electromagnetic valve 213, second electromagnetic valve 223 according to the flow of regulation, carry out-11 DEG C of stage isothermal experiments;
6, close the first oil pump 211, second oil pump 221, first electromagnetic valve 213, second electromagnetic valve 223, open the first tubing pump 231, the 3rd electromagnetic valve 233, single-stage compression unit 312, by forced heat-exchanging, fuel oil is dropped to-20 DEG C;
7, close the first tubing pump 231, the 3rd electromagnetic valve 233, single-stage compression unit 312, open the first oil pump 211, second oil pump 221, open the first electromagnetic valve 213, second electromagnetic valve 223 according to the flow according to regulation, carry out-20 DEG C of stage isothermal experiments;
8, the 4th electromagnetic valve 311, first oil pump 211, second oil pump 221, first electromagnetic valve 213, second electromagnetic valve 223 is closed, open the first tubing pump 231, the 4th electromagnetic valve 233, the 5th electromagnetic valve 321 and overlapping compressor set 322, fuel oil is cooled to-40 DEG C by forced heat-exchanging;
9, close the first tubing pump 231, the 3rd electromagnetic valve 233, overlapping compressor set 322, open the first oil pump 211, second oil pump 221, open the first electromagnetic valve 213, second electromagnetic valve 223 according to the flow of regulation, carry out-40 DEG C of stage isothermal experiments.
A kind of refrigeration system being applicable to aircraft fuel system icing tests of the present utility model, can carry out cooling and the insulation of multiple different phase as required, meet test requirements document, have the advantages such as structure is simple, handled easily to the fuel oil in test fuel tank 102.
The above; be only optimum detailed description of the invention of the present utility model; but protection domain of the present utility model is not limited thereto; anyly be familiar with those skilled in the art in the technical scope that the utility model discloses; the change that can expect easily or replacement, all should be encompassed within protection domain of the present utility model.Therefore, protection domain of the present utility model should be as the criterion with the protection domain of described claim.
Claims (5)
1. be applicable to a refrigeration system for aircraft fuel system icing tests, it is characterized in that, comprise environmental cabinet unit (1), cycle control unit (2) and refrigeration unit (3),
Described environmental cabinet unit (1) for placing test article, and is incubated the ambient temperature residing for test article;
Described cycle control unit (2) is for the circulation of the fuel oil in Control experiment part;
Described refrigeration unit (3) is for lowering the temperature described fuel oil.
2. a kind of refrigeration system being applicable to aircraft fuel system icing tests according to claim 1, it is characterized in that, described environmental cabinet unit (1) comprises environment casing (101) and test fuel tank (102), described test fuel tank (102) is placed in described environment casing (101), be connected with cycle control unit (2) and refrigeration unit (3) by pipeline, described environment casing (101) is incubated test fuel tank (102).
3. a kind of refrigeration system being applicable to aircraft fuel system icing tests according to claim 1, it is characterized in that, described cycle control unit (2) comprises the first pilot piping (210), the second pilot piping (220) and the 3rd pilot piping (230)
Described first pilot piping (210) comprises the first oil feed pump (211), first-class gauge (212) and the first electromagnetic valve (213), and described first oil feed pump (211), first-class gauge (212) are connected by pipeline with the first electromagnetic valve (213);
Described second pilot piping (220) comprises the second oil feed pump (221), second gauge (222) and the second electromagnetic valve (223), and described second oil feed pump (221), second gauge (222) are connected by pipeline with the second electromagnetic valve (223);
Described 3rd pilot piping (230) comprises the first tubing pump (231), the 3rd flow counter (232) and the 3rd electromagnetic valve (233), and described first tubing pump (231), the 3rd flow counter (232) are connected by pipeline with the 3rd electromagnetic valve (233);
Described first pilot piping (210), the second pilot piping (220), the 3rd pilot piping (230) are in parallel and be provided with the first import (240) and first and export (250), described first import (240) is connected with test fuel tank (120), and described first outlet (250) is connected with refrigeration unit (3).
4. a kind of refrigeration system being applicable to aircraft fuel system icing tests according to claim 1, is characterized in that, described refrigeration unit (3) comprises the first refrigeration pipe (310) and the second refrigeration pipe (320),
Described first refrigeration pipe (310) comprises the 4th electromagnetic valve (311) and single-stage compression unit (312), and described 4th electromagnetic valve (311) is connected by pipe pipeline with single-stage compression unit (312);
Described second refrigeration pipe (320) comprises the 5th electromagnetic valve (321) and overlapping compressor set (322), and described 5th electromagnetic valve (321) is connected by pipe pipeline with overlapping compressor set (322);
Described first refrigeration pipe (310) and the second refrigeration pipe (320) are in parallel and be provided with the second import (330) and second and export (340), described second import (330) exports (250) with first of cycle control unit (2) and is connected, and described second outlet (340) is connected with test fuel tank (120).
5. a kind of refrigeration system being applicable to aircraft fuel system icing tests according to claim 4, it is characterized in that, first refrigeration pipe (310) cooling extent is normal temperature extremely subzero 20 DEG C, and the second refrigeration pipe (320) cooling extent is subzero 20 DEG C to subzero 40 DEG C.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521037617.7U CN205203423U (en) | 2015-12-13 | 2015-12-13 | Refrigerating system suitable for aircraft fuel oil system icing tests |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521037617.7U CN205203423U (en) | 2015-12-13 | 2015-12-13 | Refrigerating system suitable for aircraft fuel oil system icing tests |
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| Publication Number | Publication Date |
|---|---|
| CN205203423U true CN205203423U (en) | 2016-05-04 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201521037617.7U Active CN205203423U (en) | 2015-12-13 | 2015-12-13 | Refrigerating system suitable for aircraft fuel oil system icing tests |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106081156A (en) * | 2016-05-31 | 2016-11-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft fuel system icing tests assembly |
| CN109808916A (en) * | 2019-02-28 | 2019-05-28 | 南京航空航天大学 | A kind of fuel oil water distribution and pipeline icing measurement integration experimental rig and method |
| CN113358688A (en) * | 2021-06-02 | 2021-09-07 | 中国商用飞机有限责任公司 | Icing environment simulation system and test method thereof |
| CN114705435A (en) * | 2022-06-06 | 2022-07-05 | 中国飞机强度研究所 | Device and method for testing icing and water swallowing of aircraft engine in climate laboratory |
-
2015
- 2015-12-13 CN CN201521037617.7U patent/CN205203423U/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106081156A (en) * | 2016-05-31 | 2016-11-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft fuel system icing tests assembly |
| CN106081156B (en) * | 2016-05-31 | 2019-03-22 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft fuel system icing tests assembly |
| CN109808916A (en) * | 2019-02-28 | 2019-05-28 | 南京航空航天大学 | A kind of fuel oil water distribution and pipeline icing measurement integration experimental rig and method |
| CN113358688A (en) * | 2021-06-02 | 2021-09-07 | 中国商用飞机有限责任公司 | Icing environment simulation system and test method thereof |
| CN114705435A (en) * | 2022-06-06 | 2022-07-05 | 中国飞机强度研究所 | Device and method for testing icing and water swallowing of aircraft engine in climate laboratory |
| CN114705435B (en) * | 2022-06-06 | 2022-09-20 | 中国飞机强度研究所 | Device and method for testing icing and water swallowing of aircraft engine in climate laboratory |
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