CN203572657U - Parameter measuring device of internal fuel oil pipeline system of aero-engine - Google Patents
Parameter measuring device of internal fuel oil pipeline system of aero-engine Download PDFInfo
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- CN203572657U CN203572657U CN201320680858.8U CN201320680858U CN203572657U CN 203572657 U CN203572657 U CN 203572657U CN 201320680858 U CN201320680858 U CN 201320680858U CN 203572657 U CN203572657 U CN 203572657U
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Abstract
The utility model discloses a parameter measuring device of an internal fuel oil pipeline system of an aero-engine. The measuring device comprises a base plate; two groups of first measuring pipelines, two groups of second measuring pipelines, and two groups of third measuring pipelines are arranged on the base plate; the two groups of first measuring pipelines are both provided with a temperature measuring element, a flow measuring element, and a pressure measuring element; the two groups of second measuring pipelines are both provided with a pressure measuring element; and the two groups of third measuring pipelines are both provided with a pressure measuring element and a flow measuring element. The parameter measuring device can measure the parameters of every part in the internal fuel oil pipeline system of an aero-engine in real time, moreover, the measuring elements are integrated on the same part, thus the disassembly is convenient, and the measure result is accurate.
Description
Technical field
The utility model relates to aero engine technology field, especially, relates to the parameter measuring apparatus of the inner fuel passage system of a kind of aeromotor.
Background technology
Aeromotor, in development process, need to be used model machine to test on engine testsand, tests out the performance parameter of each annex in engine interior fuel passage system.On the exerciser of each annex test Dou Shige annex manufacturer of the inner fuel system of aeromotor, carry out now, provide the fuel oil of convenient pressure, flow, temperature to annex, whether the performance parameter that checks annex is qualified, and the pilot system of each annex is set up separately.
Due in the development process of aeromotor, to in engine run process, to inner fuel passage system, carry out comprehensively measuring and monitoring, to reflect the real-time change of the fuel flow of inner fuel passage system in commissioning process, pressure P, temperature T, obtain developing the needed supplemental characteristic of each annex.And in prior art, engine is in the process of test run, generally only measure the real-time change of the fuel inlet of inner fuel passage system and the pressure of fuel outlet, flow, temperature, other annex does not all have to measure, the canonical parameter data that Jun Shiyi annex producer provides are foundation, owing to generally all there is error in canonical parameter data and real time data, therefore use canonical parameter data for foundation, unfavorable for the development of inner each annex of fuel passage system.And, when fuel inlet and fuel outlet are measured, because fuel inlet and fuel outlet are all duct surveys outside, measuring sensor arbitrarily can be arranged, measuring sensor is from the distance of engine unified standard not; Simultaneously, the connection caliber of inner fuel passage system is smaller, as larger from the distance of measured parts in measuring sensor, and the pipeline that connects measuring sensor and measured parts will elongate, cause the fuel pressure loss in pipe larger, can bring error to measurement result.
Utility model content
The utility model object is to provide the parameter measuring apparatus of the inner fuel passage system of a kind of aeromotor, to solve in prior art, can not carry out the technical matters of measuring in real time to the parameter of each annex of aeromotor inside fuel passage system.
For achieving the above object, according to an aspect of the present utility model, the parameter measuring apparatus that the inner fuel passage system of a kind of aeromotor is provided, comprising: base plate, is provided with two group first and measures pipeline, two group of second measurement pipeline and two group of the 3rd measurement pipeline on base plate; Measure on pipeline for two group first and be provided with temperature-measuring element, flow measuring element and pressure measuring element; Measure on pipeline for two group second and be provided with pressure measuring element; Measure on pipeline for two group the 3rd and be provided with pressure measuring element and flow measuring element; Wherein one group of first measurement pipeline is connected between the fuel inlet and total solenoid valve valve of the inner fuel passage system of aeromotor; Other one group of first measurement pipeline is connected between the combustion oil cooler and fuel oil oil-collecting house steward of the inner fuel passage system of aeromotor; Wherein one group of second measurement pipeline is connected between the electrodynamic pump and combustion oil cooler of the inner fuel passage system of aeromotor; Other one group of second measurement pipeline is connected between the return flow oil filter and return flow solenoid valve valve of the inner fuel passage system of aeromotor; Wherein one group of the 3rd measurement pipeline is connected between the fuel oil oil-collecting house steward and return flow oil filter of the inner fuel passage system of aeromotor; Other one group of the 3rd measurement pipeline is connected between the return flow solenoid valve valve and fuel outlet of the inner fuel passage system of aeromotor.
Further, base plate is framed structure, comprises underframe and panel, and covering on underframe of panel part, measures pipeline, two group of second measurement pipeline and two group of the 3rd measurement pipeline for two group first and be all arranged on panel.
Further, temperature-measuring element is temperature sensor.
Further, flow measuring element is turbulence measurement meter.
Further, pressure measuring element comprises pressure unit seat and the pressure unit being connected with pressure unit seat, pressure unit seat is separately positioned on two group first and measures on pipeline, two group of second measurement pipeline and two group of the 3rd measurement pipeline, and pressure unit is fixed on underframe.
Further, the quantity of pressure unit is more than the quantity of pressure unit seat.
The utlity model has following beneficial effect:
The utility model can be measured in real time to the parameter of each annex in the fuel passage system of aeromotor inside, and each measuring sensor is integrated on base plate, easy accessibility; During measurement, base plate is placed on engine below, and each measuring sensor is consistent with the distance of tested annex, and measurement result is accurate.
Except object described above, feature and advantage, the utility model also has other object, feature and advantage.Below with reference to figure, the utility model is described in further detail.
Accompanying drawing explanation
The accompanying drawing that forms the application's a part is used to provide further understanding of the present utility model, and schematic description and description of the present utility model is used for explaining the utility model, does not form improper restriction of the present utility model.In the accompanying drawings:
Fig. 1 is the structural representation of the parameter measuring apparatus preferred embodiment of the inner fuel passage system of the utility model aeromotor; And
Fig. 2 is the test philosophy figure of the parameter measuring apparatus preferred embodiment of the inner fuel passage system of the utility model aeromotor.
Description of reference numerals:
11, first measure pipeline; 12, second measure pipeline; 13, the 3rd measure pipeline; 17, temperature sensor; 18, turbulence measurement meter; 19, pressure unit seat; 20, pressure unit; 31, underframe; 32, panel.
Embodiment
Below in conjunction with accompanying drawing, embodiment of the present utility model is elaborated, but the multitude of different ways that the utility model can be defined by the claims and cover is implemented.
Refer to Fig. 1 and Fig. 2, preferred embodiment of the present utility model provides the parameter measuring apparatus of the inner fuel passage system of a kind of aeromotor, comprise: base plate, is provided with two group first and measures pipeline 11, two group of second measurement pipeline 12 and two group of the 3rd measurement pipeline 13 on base plate.Measure on pipeline 11 for two group first and be provided with temperature-measuring element, flow measuring element and pressure measuring element; Measure on pipeline 12 for two group second and be provided with pressure measuring element; Measure on pipeline 13 for two group the 3rd and be provided with temperature-measuring element, flow measuring element and pressure measuring element.
Annex in the inner fuel passage system of aeromotor mainly contains solenoid valve valve (total solenoid valve valve and return flow solenoid valve valve), electrodynamic pump, combustion oil cooler, fuel oil oil-collecting house steward, fuel oil direct projection device and return flow oil filter.Fuel oil, from fuel inlet enters into inner fuel passage system, is divided into two-way through total solenoid valve valve: a road is directly back to fuel outlet through return flow solenoid valve valve; Another road enters fuel oil oil-collecting house steward after electrodynamic pump pressurization, combustion oil cooler are cooling, and the working connection of a part of fuel oil by fuel oil oil-collecting house steward inputs to fuel oil direct projection device and offer engine chamber and do work; Another part fuel oil is delivered to after return flow oil filtration filter by fuel oil oil-collecting house steward's auxiliary oil circuit, then is back to fuel outlet by return flow solenoid valve valve.
Engine assembly on its Test Rig after, when aeromotor inside fuel passage system is measured, directly base plate is placed on to engine below, wherein one group of first measurement pipeline 11 is connected between the fuel inlet and total solenoid valve valve of the inner fuel passage system of aeromotor, by temperature-measuring element, flow measuring element and the pressure measuring element measured on pipeline, measures fuel oil oil-feed general pressure, temperature and the flow parameter before total solenoid valve valve; Other one group of first measurement pipeline 11 is connected between the combustion oil cooler and fuel oil oil-collecting house steward of the inner fuel passage system of aeromotor, by temperature-measuring element, flow measuring element and the pressure measuring element measured on pipeline, measures pressure, temperature and the flow parameter through the cooled fuel oil of combustion oil cooler; Wherein one group of second measurement pipeline 12 is connected between the electrodynamic pump and combustion oil cooler of the inner fuel passage system of aeromotor, measures the oil pressure parameter of the fuel oil after electrodynamic pump pressurizes by the pressure measuring element on measurement pipeline; Other one group of second measurement pipeline 12 is connected between the return flow oil filter and return flow solenoid valve valve of the inner fuel passage system of aeromotor, measures the oil pressure parameter of the fuel oil after return flow oil filtration filter by the pressure measuring element on measurement pipeline; Wherein one group of the 3rd measurement pipeline 13 is connected between the fuel oil oil-collecting house steward and return flow oil filter of the inner fuel passage system of aeromotor; By flow measuring element and the pressure measuring element measured on pipeline, measure oil pressure and the flow parameter through the fuel oil of fuel oil oil-collecting house steward auxiliary oil circuit oil return; Other one group of the 3rd measurement pipeline 13 is connected between the return flow solenoid valve valve and fuel outlet of the inner fuel passage system of aeromotor, measures oil pressure and the flow parameter of the fuel oil after return flow solenoid valve valve by the flow measuring element on measurement pipeline and pressure measuring element.The utility model can be measured in real time to the parameter of each annex in the fuel passage system of aeromotor inside, and each measuring sensor is integrated on same parts, easy accessibility; During measurement, measuring sensor is little and consistent with the distance of tested annex, and measurement result is accurate.
Preferably, for alleviating the weight of measurement mechanism, be convenient to the use of measurement mechanism; Base plate is framed structure, comprises underframe 31 and panel 32, and covering on underframe 31 of panel 32 parts, measures pipeline 11, two group of second measurement pipeline 12 and two group of the 3rd measurement pipeline 13 for two group first and be all arranged on panel 32.Simultaneously, measure for convenience the connection of pipeline, reduce the profile of measurement mechanism, preferably, article two, first measure pipeline 11, two second measure pipeline 12 with two article the 3rd to measure pipeline 13 be that a component is two groups by every three measurement pipelines, it is sheathed successively that the measurement pipeline of every group is " U " font, the compact layout and structure of the measurement pipeline on panel 32 like this, the profile of contract measurement device that can be larger.
Preferably, the accuracy of measuring for improving measurement mechanism, the structure of simplified measurement device; Temperature-measuring element is temperature sensor 17; Flow measuring element is turbulence measurement meter 18; Pressure measuring element comprises pressure unit seat 19 and the pressure unit 20 being connected with pressure unit seat 19, pressure unit seat 19 is separately positioned on two group first and measures on pipeline 11, two group of second measurement pipeline 12 and two group of the 3rd measurement pipeline 13, and pressure unit 20 is fixed on underframe 31.In the concrete process of implementing, the quantity of pressure unit 20 can be more than the quantity of pressure unit seat 19, and such design can facilitate other measuring system to connect.
As can be seen from the above description, the utility model the above embodiments have realized following technique effect:
On base plate, integrated six test pipelines, can measure in real time the parameter of each annex in the fuel passage system of aeromotor inside, and the structural design of test pipeline are compact, are convenient to dismounting and use; During measurement, measuring sensor is little and consistent with the distance of tested annex, and measurement result is accurate.
The foregoing is only preferred embodiment of the present utility model, be not limited to the utility model; For a person skilled in the art, the utility model can have various modifications and variations.All within spirit of the present utility model and principle, any modification of doing, be equal to replacement, improvement etc., within all should being included in protection domain of the present utility model.
Claims (6)
1. a parameter measuring apparatus for the inner fuel passage system of aeromotor, is characterized in that, comprising:
Base plate, is provided with two group first and measures pipeline (11), two group of second measurement pipeline (12) and two group of the 3rd measurement pipeline (13) on described base plate;
Described in two groups, on the first measurement pipeline (11), be provided with temperature-measuring element, flow measuring element and pressure measuring element; Described in two groups, on the second measurement pipeline (12), be provided with pressure measuring element; Described in two groups, on the 3rd measurement pipeline (13), be provided with pressure measuring element and flow measuring element;
Wherein described in one group, the first measurement pipeline (11) is connected between the fuel inlet and total solenoid valve valve of the inner fuel passage system of described aeromotor; Described in other one group, the first measurement pipeline (11) is connected between the combustion oil cooler and fuel oil oil-collecting house steward of the inner fuel passage system of described aeromotor;
Wherein described in one group, the second measurement pipeline (12) is connected between the electrodynamic pump and combustion oil cooler of the inner fuel passage system of described aeromotor; Described in other one group, the second measurement pipeline (12) is connected between the return flow oil filter and return flow solenoid valve valve of the inner fuel passage system of described aeromotor;
Wherein described in one group, the 3rd measurement pipeline (13) is connected between the fuel oil oil-collecting house steward and return flow oil filter of the inner fuel passage system of described aeromotor; Described in other one group, the 3rd measurement pipeline (13) is connected between the return flow solenoid valve valve and fuel outlet of the inner fuel passage system of described aeromotor.
2. the parameter measuring apparatus of the inner fuel passage system of aeromotor according to claim 1, is characterized in that:
Described base plate is framed structure, comprise underframe (31) and panel (32), described panel (32) is local, and to cover described underframe (31) upper, and described in two groups, first measures described in pipeline (11), two groups second and measure pipeline (12) and the 3rd measure pipeline (13) and be all arranged on described panel (32) described in two groups.
3. the parameter measuring apparatus of the inner fuel passage system of aeromotor according to claim 2, is characterized in that:
Described temperature-measuring element is temperature sensor (17).
4. the parameter measuring apparatus of the inner fuel passage system of aeromotor according to claim 2, is characterized in that:
Described flow measuring element is turbulence measurement meter (18).
5. the parameter measuring apparatus of the inner fuel passage system of aeromotor according to claim 2, is characterized in that:
Described pressure measuring element comprises pressure unit seat (19) and the pressure unit (20) being connected with described pressure unit seat (19), described pressure unit seat (19) first is measured described in pipeline (11), two groups second and is measured described in pipeline (12) and two groups the 3rd to measure pipeline (13) upper described in being separately positioned on two groups, and described pressure unit (20) is fixed on described underframe (31).
6. the parameter measuring apparatus of the inner fuel passage system of aeromotor according to claim 5, is characterized in that:
The quantity of described pressure unit (20) is more than the quantity of described pressure unit seat (19).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320680858.8U CN203572657U (en) | 2013-10-30 | 2013-10-30 | Parameter measuring device of internal fuel oil pipeline system of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320680858.8U CN203572657U (en) | 2013-10-30 | 2013-10-30 | Parameter measuring device of internal fuel oil pipeline system of aero-engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203572657U true CN203572657U (en) | 2014-04-30 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320680858.8U Expired - Fee Related CN203572657U (en) | 2013-10-30 | 2013-10-30 | Parameter measuring device of internal fuel oil pipeline system of aero-engine |
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| CN (1) | CN203572657U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104330262A (en) * | 2014-10-23 | 2015-02-04 | 哈尔滨东安发动机（集团）有限公司 | Aero-engine fuel and lubricating oil system test device |
| CN114852354A (en) * | 2022-04-18 | 2022-08-05 | 中国航发沈阳发动机研究所 | Fuel oil system |
-
2013
- 2013-10-30 CN CN201320680858.8U patent/CN203572657U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104330262A (en) * | 2014-10-23 | 2015-02-04 | 哈尔滨东安发动机（集团）有限公司 | Aero-engine fuel and lubricating oil system test device |
| CN104330262B (en) * | 2014-10-23 | 2016-09-28 | 哈尔滨东安发动机（集团）有限公司 | Aero-engine combustion oil system assay device |
| CN114852354A (en) * | 2022-04-18 | 2022-08-05 | 中国航发沈阳发动机研究所 | Fuel oil system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 412002 Dong Jiaduan, Zhuzhou, Hunan Patentee after: China Hangfa South Industrial Co. Ltd. Address before: 412002 Dong Jiaduan, Zhuzhou, Hunan Patentee before: China Southern Airlines Industry (Group) Co., Ltd. |
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| 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: 20140430 Termination date: 20201030 |