CN104390716A - Solid engine inflatable temperature measuring system - Google Patents
Solid engine inflatable temperature measuring system Download PDFInfo
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- CN104390716A CN104390716A CN201410657428.3A CN201410657428A CN104390716A CN 104390716 A CN104390716 A CN 104390716A CN 201410657428 A CN201410657428 A CN 201410657428A CN 104390716 A CN104390716 A CN 104390716A
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- engine
- transparency window
- pressure
- temperature measuring
- measuring device
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Abstract
The invention relates to a solid engine inflatable temperature measuring system. The system consists of an engine, a gas supply system and a testing system, wherein the engine is fixedly arranged on an experiment table; the gas supply system and the testing system are positioned on the outer side of the engine; a nitrogen gas cylinder is connected with a pressure reducing valve, a hand valve, an electromagnetic valve and a one-way valve through a pipeline and a gas inlet; a pressure intensity sensor is matched with a pressure measuring hole; a thermocouple is matched with a temperature measuring hole; the pressure intensity sensor and the thermocouple are connected with a computer respectively; a non-contact temperature measuring device is fixedly arranged on one side of a transparent window, and an acqusition head is opposite to the transparent window; the non-contact temperature measuring device is connected with the computer. By filling high-pressure gas, the sectional area of an outlet of a transparent window pedestal is reduced, so that blockage is formed at the outlet and stable gas is produced to protect the quartz glass of a transparent window, and sufficient light transmittance on the cross sectional area is also guaranteed; meanwhile, the temperature of a combustion chamber of the engine is measured in a contact mode and a non-contact mode, and synchronous accurate measurement of the same gas temperature by the two different methods is realized.
Description
Technical field
The present invention relates to solid propellant rocket technical field of measurement and test, specifically, relate to a kind of solid engines inflatable temp measuring system.
Background technology
Solid Rocket Motor combustion chamber temperature is engine structure design, burn-out proof designs and the important indicator parameter of propellant combustion study mechanism.The important parameter characterizing Field Characteristics and rocket engine performance is not only in propellant combustion flame temperature and distribution, more predicts the physical and chemical process of propellant combustion and sets up rational mathematics physics model and provide design guidance.
At present, the application of installation utilizing thermopair to carry out thermometric to rocket engine is comparatively simple and easy, only need weld temperature-measuring base in engine surface, is threaded connection and is fixed on the engine by thermopair, make thermocouple probe arrive combustion chamber and contacts fuel gas, obtain the working temperature of firing chamber.But the limitation utilizing this device to carry out thermometric is that general thermopair can only measure the temperature of less than 2300 DEG C, be difficult to the high temperature measurement carrying out engine, and thermopair easily fuses.
The temperature range utilizing non-contact temperature measuring device to record increases, and has good application prospect in the high temperature test field of solid propellant rocket, and such as infrared thermometer temperature-measuring range is-50 DEG C-+3000 DEG C.Utilize the rocket engine temperature measuring equipment that eyes with non-contact method carries out, conventional method welds a clear glass window in engine surface, makes the light wave of firing chamber through glass, collected by non-contact temperature measuring instrument, thus record the temperature of rocket engine combustion gas.
But the shortcoming of temperature measuring equipment is, the high-temperature fuel gas produced during engine operation directly can touch glass surface, to glass generation damage to a certain degree; Engine combustion products easily covers the collection that transparent glass surface hinders light wave, makes the temperature recorded not be the true temperature of combustion gas, but the temperature of window attachment.
Summary of the invention
In order to avoid the deficiency that prior art exists, the present invention proposes a kind of solid engines inflatable temp measuring system, by being filled with high pressure nitrogen protection transparency window, adopt the temperature of contact and non-contact measurement engine chamber simultaneously, realize the synchronous Measurement accuracy of two kinds of distinct methods to same fuel gas temperature; For engine working process analysis and research provide data foundation.
The technical solution adopted for the present invention to solve the technical problems is: comprise engine, air supply system, test macro, is characterized in, described engine comprises front head, firing chamber, air intake opening, transparency window pressure spiral shell, transparency window base, grate, nozzle block, jet pipe, rear head, thermometer hole, pressure tap, described firing chamber is columnar structured, burner ends respectively with front head, rear head connects, and grate is positioned at rear end, firing chamber and rear head interference fit, and jet pipe and rear head are clearance fit, and are compressed by nozzle block, and thermometer hole and pressure tap are positioned on sidewall of combustion chamber, thermometer hole, pressure tap axis and firing chamber axes normal, sidewall of combustion chamber is provided with transparency window, described transparency window base is step cavity cylindrical structure, lumen shaft is to being step through hole, internal chamber wall there is one section of screw thread, transparency window base side wall front portion has the circular hole of multiple symmetry to communicate with inner chamber, described transparency window pressure spiral shell is T-shaped structure, intermediate shaft is to there being through hole, transparency window pressure spiral shell sidewall there is screw thread, place quartz glass between transparency window pressure spiral shell and transparency window base, and compressed by screw thread, transparent form sidewall has air intake opening, engine is fixed on experiment table,
Described air supply system is positioned at the outside of engine, and nitrogen cylinder is connected by pipeline and air intake opening with reduction valve, hand valve, solenoid valve, retaining valve, adopts and be threaded between loading line;
Described test macro is positioned at the outside of engine, and pressure transducer and pressure tap are connected, and thermopair and thermometer hole are connected, and pressure transducer, thermopair, solenoid valve are connected with computing machine respectively; Non-contact temperature measuring device is fixed on transparency window side, and non-contact temperature measuring device collection head is relative with transparent window, and non-contact temperature measuring device is connected with computing machine.
Transparency window is pressed spiral shell and is added sealing filler ring between transparency window base and quartz glass.
Beneficial effect
The solid engines inflatable temp measuring system that the present invention proposes; by being filled with high pressure gas to transparency window pan frontward end; make to form one deck blanket gas between transparency window quartz glass and engine chamber; effectively prevent products of combustion covers on transparency silica glass, improves the light wave collecting efficiency of temperature measuring equipment.Meanwhile, gases at high pressure hinder high temperature gas flow and directly touch Quartz glass surfaces, effectively prevent transparency silica glass to be subject to the damage of high-temperature gas.
Solid engines inflatable temp measuring system of the present invention, coordinated with the pressure tap on firing chamber by pressure transducer, thermopair coordinates with the thermometer hole on firing chamber, and the output signal of pressure transducer, thermopair is connected to computer data acquisition system respectively; Non-contact temperature measuring device is fixed on transparency window side, and non-contact temperature measuring device collection head is relative with transparent window, and non-contact temperature measuring device is connected with computer data acquisition system.
The present invention, by being filled with gases at high pressure, reduces the discharge area of transparency window base simultaneously, exit both can have been made to form Yong Sai, produced stable gas shield transparency window quartz glass, ensure that again cross-sectional area has enough light transmission capacities; Adopt the temperature of contact and non-contact measurement engine chamber simultaneously, realize the synchronous Measurement accuracy of two kinds of distinct methods to same fuel gas temperature.
The actual pressure of firing chamber and temperature during energy simulated engine of the present invention work; By being processed into the geomery identical with test engine, the actual pressure in the energy simulated engine course of work and temperature, the experimental data of acquisition more accurately and reliably.
Accompanying drawing explanation
Below in conjunction with drawings and embodiments, a kind of solid engines inflatable of the present invention temp measuring system is described in further detail.
Fig. 1 is solid engines inflatable temp measuring system schematic diagram of the present invention.
Fig. 2 is engine structure schematic diagram of the present invention.
Fig. 3 is engine structure vertical view of the present invention.
Fig. 4 is transparency window base cut-open view of the present invention.
Fig. 5 is transparency window base vertical view of the present invention.
Fig. 6 is transparency window of the present invention pressure spiral shell cut-open view.
Fig. 7 is transparency window of the present invention pressure spiral shell vertical view.
Fig. 8 is the experimental data curve figure that the present invention utilizes non-contact temperature measuring device to survey.
In figure:
1. front head 2. firing chamber 3. air intake opening 4. transparency window pressure spiral shell 5. transparency window base 6. grate 7. jet pipe 8. nozzle block 9. rear head 10. thermometer hole 11. pressure tap 12. propellant
Embodiment
The present embodiment is a kind of solid engines inflatable temp measuring system; Comprise engine, air supply system, test macro, air supply system and test macro are arranged on the outside of engine, and engine is bolted on experiment table.
Consult Fig. 1 ~ Fig. 7, engine presses spiral shell 4, transparency window base 5, grate 6, nozzle block 8, jet pipe 7, rear head 9, thermometer hole 10, pressure tap 11 and propellant 12 to form by front head 1, firing chamber 2, air intake opening 3, transparency window; Firing chamber 2 is columnar structured, and two ends, firing chamber 2 are threaded connection with front head 1, rear head 9 respectively, and grate 6 is arranged on rear end in firing chamber 2, and propellant 12 is placed on before grate 6; Grate 6 and rear head 9 are interference fit, jet pipe 7 and rear head 9 are clearance fit, and are compressed by nozzle block 8, and thermometer hole 10 and pressure tap 11 are arranged on the sidewall of firing chamber 2, thermometer hole 10, pressure tap 11 axis and firing chamber 2 axes normal, firing chamber 2 sidewall is provided with transparency window.Transparency window base 5 is step cavity cylindrical structure, and lumen shaft, to being step through hole, internal chamber wall has one section of screw thread; Transparency window base side wall front portion has the circular hole of multiple symmetry to communicate with inner chamber, and the anterior symmetrical circular hole of the present embodiment transparency window base 5 sidewall is 2 to 8.Transparency window pressure spiral shell 4 is T-shaped structure, intermediate shaft, to there being through hole, transparency window pressure spiral shell 4 sidewall has screw thread, places quartz glass between transparency window pressure spiral shell 4 and transparency window base 5, and compressed by screw thread, transparency window is pressed spiral shell 4 and is added sealing filler ring between transparency window base 5 and quartz glass.Transparent form sidewall there is air intake opening 3.
The nitrogen cylinder of air supply system is connected by pipeline and air intake opening 3 with reduction valve, hand valve, solenoid valve, retaining valve, adopts and be threaded between loading line with each valve.
In test macro, pressure transducer and pressure tap 11 are connected, and thermopair and thermometer hole 10 are connected, and the output signal of pressure transducer, thermopair is connected to computer data acquisition system respectively; Non-contact temperature measuring device is fixed on transparency window side, and non-contact temperature measuring device collection head is relative with transparent window, and non-contact temperature measuring device is connected with computer data acquisition system.By being filled with gases at high pressure, reducing the discharge area of transparency window base 5 simultaneously, exit both can have been made to form Yong Sai, produced stable gas shield transparency window quartz glass, ensure that again cross-sectional area has enough light transmission capacities.
Fig. 8 is the one group of experimental data curve utilizing non-contact temperature measuring device to implement test in the present embodiment.The medial temperature of measured engine reaches 3500K, and adopts general contact temperature-measuring device to be difficult to realize.
When testing rocket chamber's temperature, full sized inflatable thermometric engine is processed in design first as requested; And carry out igniting experiments according to actual condition, utilize thermopair and non-contact temperature measuring device to test combustion chamber high temperature; The experimental data that ultimate analysis gathers, for engine working process analysis and research provide data foundation.
Concrete steps are as follows:
(1) assembly connection engine system; The front head of engine is mounted by means of bolts on experiment table, firing chamber and front head are tightened; Put into propellant to firing chamber, transparency silica glass is placed on transparency window base and transparency window is pressed between spiral shell, and compressed by screw thread; Thermopair, pressure transducer are connected with engine respectively, propellant end face in set-point firearm to firing chamber, and grate and rear head are compressed, and rear head and firing chamber are tightened, and put into jet pipe, tighten jet pipe base;
(2) air supply system is connected; Nitrogen cylinder is connected by the air intake opening on pipeline and transparency window base with reduction valve, hand valve, solenoid valve, retaining valve, adopts between loading line and be threaded;
(3) connecting test system; Pressure transducer and pressure tap are connected, thermopair and thermometer hole are connected, and pressure transducer, thermopair, solenoid valve are connected with computing machine respectively; Non-contact temperature measuring device is fixed on transparency window side, and non-contact temperature measuring device collection head is relative with transparent window, and non-contact temperature measuring device is connected with computing machine; Regulate test macro, make test macro reach best test effect;
(4) open high-pressure nitrogen bottle, the switching time of Controlling solenoid valve, igniting sequential is set, first pass into nitrogen and light a fire again; Whether the sealing of pretest inspection engine is intact, and is fixed on testing table by engine, prevents from offseting during test;
(5) engine ignition is carried out; Cut-in point firearm carries out engine ignition experiment, and records the time t that powder charge takes fire
1; Observe powder charge combustion process, treat powder column all burnt record time t now
2; Utilize the pressure transducer in the test macro recording engine course of work, thermopair, the data of non-contact temperature measuring device, for engine performance analysis provides foundation;
(6) engine stop work, preserves experimental data, closes proving installation, record experimental phenomena; Dismounting experimental provision, cleaning engine used in order to next time.
Claims (2)
1. a solid engines inflatable temp measuring system, comprise engine, air supply system, test macro, it is characterized in that: described engine comprises front head, firing chamber, air intake opening, transparency window pressure spiral shell, transparency window base, grate, nozzle block, jet pipe, rear head, thermometer hole, pressure tap, described firing chamber is columnar structured, burner ends respectively with front head, rear head connects, grate is positioned at rear end, firing chamber and rear head interference fit, jet pipe and rear head are clearance fit, and compressed by nozzle block, thermometer hole and pressure tap are positioned on sidewall of combustion chamber, thermometer hole, pressure tap axis and firing chamber axes normal, sidewall of combustion chamber is provided with transparency window, described transparency window base is step cavity cylindrical structure, lumen shaft is to being step through hole, internal chamber wall there is one section of screw thread, transparency window base side wall front portion has the circular hole of multiple symmetry to communicate with inner chamber, described transparency window pressure spiral shell is T-shaped structure, and intermediate shaft, to there being through hole, transparency window pressure spiral shell sidewall is had screw thread, places quartz glass, and compressed by screw thread, transparent form sidewall has air intake opening between transparency window pressure spiral shell and transparency window base, engine is fixed on experiment table,
Described air supply system is positioned at the outside of engine, and nitrogen cylinder is connected by pipeline and air intake opening with reduction valve, hand valve, solenoid valve, retaining valve, adopts and be threaded between loading line;
Described test macro is positioned at the outside of engine, and pressure transducer and pressure tap are connected, and thermopair and thermometer hole are connected, and pressure transducer, thermopair, solenoid valve are connected with computing machine respectively; Non-contact temperature measuring device is fixed on transparency window side, and non-contact temperature measuring device collection head is relative with transparent window, and non-contact temperature measuring device is connected with computing machine.
2. solid engines inflatable temp measuring system according to claim 1, is characterized in that: transparency window pressure spiral shell and add sealing filler ring between transparency window base and quartz glass.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201410657428.3A CN104390716B (en) | 2014-11-18 | 2014-11-18 | A kind of solid engines inflatable temp measuring system |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410657428.3A CN104390716B (en) | 2014-11-18 | 2014-11-18 | A kind of solid engines inflatable temp measuring system |
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| CN104390716A true CN104390716A (en) | 2015-03-04 |
| CN104390716B CN104390716B (en) | 2017-04-05 |
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| CN201410657428.3A Expired - Fee Related CN104390716B (en) | 2014-11-18 | 2014-11-18 | A kind of solid engines inflatable temp measuring system |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111502859A (en) * | 2020-04-29 | 2020-08-07 | 西北工业大学 | Initiating explosive-free gas-solid hybrid rocket engine |
| CN113899552A (en) * | 2021-09-26 | 2022-01-07 | 西安航天动力试验技术研究所 | Operating gas supply system for jet pipe of secondary combustion ramjet engine |
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| US6370946B1 (en) * | 2000-05-02 | 2002-04-16 | Southwest Research Institute | High temperature diesel deposit tester |
| CN101650358A (en) * | 2009-09-17 | 2010-02-17 | 西安近代化学研究所 | Gunpowder combustion property test device under pressure reduction condition |
| CN102032987A (en) * | 2010-12-14 | 2011-04-27 | 西北工业大学 | Experiment device for researching jet atomizing characteristic of jet nozzle |
| CN103308662A (en) * | 2013-06-07 | 2013-09-18 | 北京理工大学 | High-temperature and high-pressure single-drop evaporating and burning device |
| CN203502228U (en) * | 2013-10-31 | 2014-03-26 | 哈尔滨汽轮机厂有限责任公司 | Gas-turbine combustion chamber pressurization visualization combustion testing apparatus |
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2014
- 2014-11-18 CN CN201410657428.3A patent/CN104390716B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6370946B1 (en) * | 2000-05-02 | 2002-04-16 | Southwest Research Institute | High temperature diesel deposit tester |
| CN101650358A (en) * | 2009-09-17 | 2010-02-17 | 西安近代化学研究所 | Gunpowder combustion property test device under pressure reduction condition |
| CN102032987A (en) * | 2010-12-14 | 2011-04-27 | 西北工业大学 | Experiment device for researching jet atomizing characteristic of jet nozzle |
| CN103308662A (en) * | 2013-06-07 | 2013-09-18 | 北京理工大学 | High-temperature and high-pressure single-drop evaporating and burning device |
| CN203502228U (en) * | 2013-10-31 | 2014-03-26 | 哈尔滨汽轮机厂有限责任公司 | Gas-turbine combustion chamber pressurization visualization combustion testing apparatus |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111502859A (en) * | 2020-04-29 | 2020-08-07 | 西北工业大学 | Initiating explosive-free gas-solid hybrid rocket engine |
| CN111502859B (en) * | 2020-04-29 | 2023-03-31 | 西北工业大学 | Initiating explosive-free gas-solid hybrid rocket engine |
| CN113899552A (en) * | 2021-09-26 | 2022-01-07 | 西安航天动力试验技术研究所 | Operating gas supply system for jet pipe of secondary combustion ramjet engine |
| CN113899552B (en) * | 2021-09-26 | 2023-07-04 | 西安航天动力试验技术研究所 | Jet pipe actuating gas supply system of sub-combustion ramjet engine |
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| CN104390716B (en) | 2017-04-05 |
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