CN109357884A - A kind of head air inlet solid fuel ramjet thrust-measuring device - Google Patents
A kind of head air inlet solid fuel ramjet thrust-measuring device Download PDFInfo
- Publication number
- CN109357884A CN109357884A CN201811240843.3A CN201811240843A CN109357884A CN 109357884 A CN109357884 A CN 109357884A CN 201811240843 A CN201811240843 A CN 201811240843A CN 109357884 A CN109357884 A CN 109357884A
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- China
- Prior art keywords
- current limliting
- venturi
- air inlet
- fixing piece
- solid fuel
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Measuring Fluid Pressure (AREA)
- Testing Of Engines (AREA)
Abstract
The invention discloses a kind of head air inlet solid fuel ramjet thrust-measuring devices, including 90 ° of elbows, sensor top plate, current limliting venturi fixing piece, four sensor stands and several pressure sensors；The current limliting venturi fixing piece is cylindrical body, a current limliting venturi is provided with from one end to the other end along center axis thereof, the current limliting venturi includes the first cylindrical channel being sequentially communicated, gradually expanded form channel and the second cylindrical channel, 90 ° of elbows are connected with the first cylindrical channel of current limliting venturi, four sensor stands are symmetrical about the end face center of current limliting venturi fixing piece, one end is connected by the end face of screw thread and current limliting venturi fixing piece, the other end passes through sensor top plate and is fixed by nut, end face of the sensor top plate far from current limliting venturi fixing piece is arranged in several pressure sensors.The present invention solves the problems, such as that air inlet solid fuel ramjet axial thrust in head is difficult to measure, and so that lateral air inlet is become head air inlet to realize the measurement of thrust using 90 ° of elbows.
Description
Technical field
The invention belongs to solid fuel ramjet test measurement technologies, and in particular to a kind of head air inlet solid fuel
Punching engine thrust-measuring device.
Background technique
Solid fuel ramjet is a kind of novel power device, mainly by air intake duct, combustion chamber, afterburning chamber and jet pipe
Composition, have many advantages, such as structure it is simple, than leaping high, flameholding, convenient for storage and use.In solid fuel ramjet
In design studies, experimental study is indispensable research means.By test, necessary ginseng can be provided for theory analysis
Number, proof theory are analyzed as a result, excavating the problem of can not finding in theoretical calculation simultaneously.Connecting leg test in ground is research engine
The most economical effective means of Combustor Flows combustion process.
Ground connecting leg pilot system mainly includes intake simulation system, engine test system and test parameters measurement system
System.Intake simulation system is used to simulate studied state of flight, provides air total temperature, stagnation pressure and air stream under the state
Amount.Engine test system is used to study in-engine combustion flows performance, obtains engine chamber, afterburning chamber and tail
The working condition of jet pipe.Test parameters measuring system by pressure, temperature and thrust measurement sensor obtain afterburning chamber pressure,
Thrust caused by temperature and engine.
Thrust is that solid fuel ramjet provides the power for playing arrow movement, is the main performance parameter of punching engine
One of.Thrust measurement sensor is mounted between the bullet portion of test engine and testing stand, can be carried out calibration in situ, to survey
The axial force that amount test engine generates during the work time.
For the solid fuel ramjet of head air inlet, pressure sensor can not be mounted on the bullet of engine
Portion leads to not directly measure axial thrust caused by solid fuel ramjet, general to be obtained by other parameters calculating
?.
Summary of the invention
The purpose of the present invention is to provide a kind of thrust-measuring devices of head air inlet solid fuel ramjet, solve
Air inlet solid fuel ramjet axial thrust in head is difficult to the problem of measuring, and using 90 ° of elbows becomes lateral air inlet
Head air inlet is to realize the measurement of thrust.
The technical solution for realizing the aim of the invention is as follows: a kind of head air inlet solid fuel ramjet thrust measurement
Device, including 90 ° of elbows, sensor top plate, current limliting venturi fixing piece, four sensor stands and several pressure sensors；Institute
Stating current limliting venturi fixing piece is cylindrical body, is provided with a current limliting venturi, the current limliting from one end to the other end along center axis thereof
Venturi includes the first cylindrical channel being sequentially communicated, gradually expanded form channel and the second cylindrical channel, 90 ° of elbows and current limliting venturi
The first cylindrical channel be connected, four sensor stands are symmetrical about the end face center of current limliting venturi fixing piece, one
End is connected by the end face of screw thread and current limliting venturi fixing piece, and the other end passes through sensor top plate and fixed by nut, several
End face of the sensor top plate far from current limliting venturi fixing piece is arranged in pressure sensor.
Compared with prior art, the present invention its remarkable advantage is: (1) present invention can change the air inlet side of engine
Lateral air inlet is converted to head air inlet by formula.
(2) axial force that test engine generates during the work time can be measured, test parameters analysis is provided effective
With reference to making up head air inlet solid fuel ramjet thrust and be difficult to the deficiency measured.
Detailed description of the invention
Fig. 1 is the schematic diagram of air inlet solid fuel ramjet thrust-measuring device in head of the present invention.
Fig. 2 is the sensor top plate schematic diagram of air inlet solid fuel ramjet thrust-measuring device in head of the present invention.
Fig. 3 is that the current limliting venturi fixing piece of air inlet solid fuel ramjet thrust-measuring device in head of the present invention is illustrated
Figure.
Fig. 4 is the sensor stand schematic diagram of air inlet solid fuel ramjet thrust-measuring device in head of the present invention.
Specific embodiment
Present invention is further described in detail with reference to the accompanying drawing.
In conjunction with Fig. 1 to Fig. 4, a kind of head air inlet solid fuel ramjet thrust-measuring device, including 90 ° of elbows 1,
Sensor top plate 2,3, four sensor stands 4 of current limliting venturi fixing piece and several pressure sensors 5.The current limliting venturi is fixed
Part 3 is cylindrical body, is provided with a current limliting venturi from one end to the other end along center axis thereof, and the current limliting venturi includes successively phase
Logical the first cylindrical channel, gradually expanded form channel and the second cylindrical channel, wherein the diameter of the first cylindrical channel is less than
The diameter of two cylindrical channels, the diameter of the first cylindrical channel are greater than the small end face diameter of gradually expanded form channel diameter, the second circle
The diameter of cylindrical passageway is greater than the big end face diameter of gradually expanded form channel diameter, and 90 ° of elbows 1 pass through screw thread and the first of current limliting venturi
Cylindrical channel is connected, and four sensor stands 4 are symmetrical about the end face center of current limliting venturi fixing piece 3, and one end is logical
The end face for crossing screw thread and current limliting venturi fixing piece 3 is connected, and the other end passes through sensor top plate 2 and fixed by nut, if dry-pressing
End face of the sensor top plate 2 far from current limliting venturi fixing piece 3 is arranged in force snesor 5.
90 ° of elbows 1 are by the first cylindrical channel connecting place of screw thread and current limliting venturi using smooth transition.
The axial length of first cylindrical channel of the current limliting venturi, the axial length of the second cylindrical channel are respectively less than
The axial length in gradually expanded form channel, the axial length in gradually expanded form channel are 3/5ths of 3 length of current limliting venturi fixing piece.
The expansion ratio in the gradually expanded form channel is 5 ° -10 °.
90 ° of elbows 1, sensor top plate 2, current limliting venturi fixing piece 3, sensor stand 4 are all made of 45 steel, ensure that
Intensity, to meet the requirement of thrust measurement.
In conjunction with Fig. 2, the sensor top plate 2 is circle, four symmetrical through-holes of annular spread thereon, is convenient for and sensor
Bracket 4 is connected, transmitting thrust.
The sensor stand 4 is stock, and one end is equipped with external screw thread, for connecting current limliting venturi fixing piece 3.
In use, air inlet solid fuel ramjet in head is connect with the second cylindrical channel, junction is using flat
It slips over and crosses.After solid fuel ramjet igniting is started to work, high-temperature fuel gas expands acceleration in engine chamber, then passes through
It is discharged after crossing afterburning chamber full combustion by jet pipe high speed, generates thrust, thrust is passed by current limliting venturi fixing piece 3, sensor stand 4
Onto sensor top plate 2, obtained through the measurement of several pressure sensors 5.
Claims (8)
1. a kind of head air inlet solid fuel ramjet thrust-measuring device, it is characterised in that: including 90 ° of elbows (1), pass
Sensor top plate (2), current limliting venturi fixing piece (3), four sensor stands (4) and several pressure sensors (5)；The restriction throat
Road fixing piece (3) is cylindrical body, is provided with a current limliting venturi, the current limliting venturi packet from one end to the other end along center axis thereof
Include the first cylindrical channel being sequentially communicated, gradually expanded form channel and the second cylindrical channel, 90 ° of elbows (1) and current limliting venturi
First cylindrical channel is connected, and four sensor stands (4) are symmetrical about the end face center of current limliting venturi fixing piece (3),
One end is connected by the end face of screw thread and current limliting venturi fixing piece (3), and the other end passes through sensor top plate (2) and passes through nut
Fixed, several pressure sensor (5) settings are in the end face of sensor top plate (2) far from current limliting venturi fixing piece (3).
2. air inlet solid fuel ramjet thrust-measuring device in head according to claim 1, it is characterised in that: institute
State diameter of the diameter less than the second cylindrical channel of the first cylindrical channel of current limliting venturi, the diameter of the first cylindrical channel
The end face diameter small greater than gradually expanded form channel diameter, the diameter of the second cylindrical channel are greater than the big end face of gradually expanded form channel diameter
Diameter.
3. the head air inlet solid fuel ramjet thrust-measuring device according to claim, it is characterised in that: institute
The first cylindrical channel connecting place of 90 ° of elbows (1) and current limliting venturi is stated using smooth transition.
4. air inlet solid fuel ramjet thrust-measuring device in head according to claim 1, it is characterised in that: institute
The axial length of the axial length, the second cylindrical channel of stating the first cylindrical channel of current limliting venturi is respectively less than gradually expanded form channel
Axial length, the axial length in gradually expanded form channel is 3/5ths of current limliting venturi fixing piece (3) length.
5. air inlet solid fuel ramjet thrust-measuring device in head according to claim 1, it is characterised in that: institute
The expansion ratio for stating gradually expanded form channel is 5 ° -10 °.
6. air inlet solid fuel ramjet thrust-measuring device in head according to claim 1, it is characterised in that: institute
State 90 ° of elbows (1), sensor top plate (2), current limliting venturi fixing piece (3), sensor stand (4) are all made of 45 steel.
7. air inlet solid fuel ramjet thrust-measuring device in head according to claim 1, it is characterised in that: institute
Sensor top plate (2) are stated as circle, four symmetrical through-holes of annular spread pass thereon convenient for being connected with sensor stand (4)
Recursion power.
8. air inlet solid fuel ramjet thrust-measuring device in head according to claim 1, it is characterised in that: institute
Stating sensor stand (4) is stock, and one end is equipped with external screw thread, for connecting current limliting venturi fixing piece (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811240843.3A CN109357884B (en) | 2018-10-23 | 2018-10-23 | Thrust measuring device for head air inlet solid fuel ramjet |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811240843.3A CN109357884B (en) | 2018-10-23 | 2018-10-23 | Thrust measuring device for head air inlet solid fuel ramjet |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109357884A true CN109357884A (en) | 2019-02-19 |
| CN109357884B CN109357884B (en) | 2020-06-05 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811240843.3A Active CN109357884B (en) | 2018-10-23 | 2018-10-23 | Thrust measuring device for head air inlet solid fuel ramjet |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112254973A (en) * | 2020-12-21 | 2021-01-22 | 中国航发上海商用航空发动机制造有限责任公司 | High-pressure compressor test piece mechanism |
| CN112627982A (en) * | 2020-12-15 | 2021-04-09 | 中国人民解放军国防科技大学 | Air secondary inflow port capable of accurately measuring thrust and flow and RBCC engine |
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| CN105422401A (en) * | 2015-12-08 | 2016-03-23 | 南京航空航天大学 | Jet flow thrust vector device based on plasma flow control |
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|---|---|---|---|---|
| CN112627982A (en) * | 2020-12-15 | 2021-04-09 | 中国人民解放军国防科技大学 | Air secondary inflow port capable of accurately measuring thrust and flow and RBCC engine |
| CN112627982B (en) * | 2020-12-15 | 2021-12-07 | 中国人民解放军国防科技大学 | Air secondary inflow port capable of accurately measuring thrust and flow and RBCC engine |
| CN112254973A (en) * | 2020-12-21 | 2021-01-22 | 中国航发上海商用航空发动机制造有限责任公司 | High-pressure compressor test piece mechanism |
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| Publication number | Publication date |
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| CN109357884B (en) | 2020-06-05 |
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