CN107271132A - A kind of method that jet engine high-temperature fuel gas is simulated based on single detonation driven clean gas - Google Patents
A kind of method that jet engine high-temperature fuel gas is simulated based on single detonation driven clean gas Download PDFInfo
- Publication number
- CN107271132A CN107271132A CN201710338584.7A CN201710338584A CN107271132A CN 107271132 A CN107271132 A CN 107271132A CN 201710338584 A CN201710338584 A CN 201710338584A CN 107271132 A CN107271132 A CN 107271132A
- Authority
- CN
- China
- Prior art keywords
- gas
- detonation
- section
- fuel
- pressure
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
Abstract
The invention discloses a kind of method that jet engine high-temperature fuel gas is simulated based on single detonation driven clean gas, including analysis fuel and oxidizer composition and temperature and pressure, selection cleaning non-toxic gas, determine mol ratio between cleaning non-toxic gas, be divided into fuel and oxidant premix respectively be filled with bomb, two class gases again and meanwhile be filled with detonation section, step of being lighted a fire etc. using ignitron.The present invention passes through single detonation mode detonation clean gas, generate and true jet engine Gas Components and the completely the same high temperature of thermodynamic state, high velocity air, so as to simulate stagnation temperature jet fuel and state of oxidant burning in the range of 2200K~2800K, gas oil ratio 0.8~1.2, the comprehensive development in laboratory and jet pipe performance and the experimental ability relevant with Nozzle Flow and level are further improved.
Description
Technical field
It is more particularly to a kind of based on single detonation driven cleaning gas the invention belongs to high-temperature aerodynamics technical field
The method that body simulates jet engine high-temperature fuel gas.
Background technology
It is conventional means directly to carry out jet pipe and back court flow Characteristics Experimental Study with jet engine, and maximum is excellent
Point is can to use 1:1 model and reflect real flow regime.But, there is also following problem：1) toxic gas pair
Test personnel are healthy to have very big hidden danger；2) testing equipment and workpiece need to generally be cooled down because the time is longer, it is cold
But the accuracy increase difficulty of heat-flow measurement is caused afterwards；3) it is easy to burn out in test testing equipment and measurement if not cooling down
Instrument, so that it is difficult to ensure that the repeatability of experiment；4) the too high thermal characteristic parameter to heat flow transducer of temperature changes larger, influence
The accuracy of measurement；5) generally testing expenses are high and the cycle is long.And sprayed with simulation high-temperature fuel gas experimental rig research engines tail
Pipe performance and its spray characteristics are, it is necessary to satisfactory in the entrance generation thermodynamic parameter and component and experimental period of jet pipe
High-temperature fuel gas.Generally can be using following several schemes：1) air hydrogenation oxygenating combustion scheme, advantage is that experimental period is long,
But either the combustion gas component produced adds substantial amounts of vapor (being commonly called as dusty gas), or temperature is not high or mixes uneven
Combustion gas quality is caused to be not reaching to requirement；2) shock tube heating air protocol can produce the pure air of very high temperature, but real
It is difficult uniformly to mix and fully burnt with fuel again to test the time extremely short；3) electric arc heated or accumulation of energy heat protocol, electro-arc heater
Nitrogen oxides and a small amount of impurity can be produced；The cobble bed accumulation of energy heater starting time is long, and can produce more granule foreign,
Engine inlet flow conditions can not be met.
Detonation driven scheme：Normal temperature air and fuel are sufficiently mixed in advance according to actual ratio, then with the side of detonation
Formula, which is fully burnt, to be produced thermodynamic parameter and component and meets desired experiment combustion gas.In order to produce high-temperature fuel gas stream, how is U.S.'s health
Your aeronautical laboratory proposes that the shock tunnel utilized produces high-temperature fuel gas stream.The principle of this method is from nineteen sixty-five Coates etc.
People[1]The detonation of proposition and the thought for being aided with the gas-powered high enthalpy shock tunnel of hydrogen, using combustion mixture as experimental gas,
High-pressure helium is used as driving gas.It can cause air-flow shape because Taylor ripples after detonation phenomena, detonation wave can occur for experimental gas
State is very uneven, it is difficult to utilize.If eliminating Taylor ripples, it is necessary to which the pressure of helium is high, therefore this method is only applicable
In the relatively low state of air-flow stagnation pressure, but pressure it is relatively low when, helium driving is difficult directly starting detonation.In addition the helium velocity of sound is relatively low,
It is difficult to suture operation at high operating temperatures, therefore the application of the test method is very limited, and is carried since the sixties in last century
After going out, the experimental method together with detonation driven shock tunnel subsequently has no relevant report again.The end of the eighties in last century and 2000
At the beginning of age, Yu Hongru proposes reverse detonation driven and set up respectively unloads quick-fried section[2-3]It is aided with double detonation driven shock waves with forward direction detonation
Wind-tunnel[4]Thought, the high enthalpy shock tunnel of detonation driven is retrieved extensive attention in the world.Driven based on double detonations
Dynamic theory, starts Chinese Academy of Sciences's mechanics reason for 2007 and proposes and developed double detonations and the side of single detonation generation high-temperature fuel gas
Method[5], this method obtained principle checking.
The content of the invention
The purpose of the present invention is：Offer is a kind of to simulate jet engine high-temperature fuel gas based on single detonation driven clean gas
Method, solving the current toxic gas existed of directly being tested with jet engine development jet pipe and back court flow behavior influences body
The problems such as make it that the heat-flow measurement degree of accuracy is not high, costly, the cycle is long after body health, testing equipment and workpiece cooling, realization makes
The stagnation temperature state that jet fuel and oxidant burn in the range of 2200K~2800K is simulated with clean gas.
The solution of the present invention is：A kind of side that jet engine high-temperature fuel gas is simulated based on single detonation driven clean gas
Method, comprises the following steps：
A. according to the molecular formula of jet fuel and oxidant is modeled, obtain being modeled jet fuel and
The atomic component that oxidant contains respectively；
B. selection contains a variety of cleanings for being modeled atomic composition contained by jet fuel and oxidant without poison gas
Body；
C. according to mass conservation law and energy equation f (a, b, c, d, combustion gas stagnation temperature T, stagnation pressure P, single detonation mode)=Δ
Hf(wherein a, b, c, d are the mol ratio of gas with various respectively), selects a variety of particular types for cleaning non-toxic gas and mutual
Mol ratio；By being modeled the temperature and pressure of jet engine combustion product, it is determined that being filled with first in detonation device detonation section
Beginning pressure；
D. a variety of cleaning non-toxic gas are divided into fuel and the class of oxidant two, premixed respectively in two bombs,
Each gas in each class gas is equal to the principle of intrinsic standoff ratio according to mol ratio, and individually phase is mixed successively under normal temperature condition
Answer in type bomb, fuel-based and oxidation category gas can not be blended mutually；
E. detonation device is divided into three sections, one section is to unload quick-fried section, and length is 2~4 meters；One section be detonation section, length 15~
30 meters；Also one section is jet pipe and vacuum chamber, 8~10 meters of length；Unload quick-fried section and detonation section between, detonation section with nozzle entry it
Between separated and fastened diaphragm with diaphragm respectively with flange；Diaphragm fastening after, by unload quick-fried section, detonation section and nozzle exit vacuum
Chamber is evacuated, and evacuating valve is closed afterwards, only opens the pressure transmitter valve of measurement detonation section the blowing pressure；
F. according to the amount for being modeled jet fuel and oxidant, pre- mixed fuel and oxidant gas will be distinguished
Body is filled with detonation section simultaneously, needs to carry out the demarcation of oxidant and fuel charge flow before being filled with, so as to two class gases according to
Predetermined ratio uniform mixing again in detonation section, the blowing pressure is the initial pressure that is determined in the step C；
G. after the completion of the gas inflated of detonation section, the pressure inverting of the blowing pressure in all charging valves and measurement pipe is closed
Device valve；The high-speed data acquistion system of measurement dynamic pressure is opened before igniting, close to nozzle entry in detonation section during experiment
Place is completed using ignitron igniting, ignition point, and total test period is no more than 100 milliseconds；
H. detonation section tube wall is provided with pressure sensor, process of the test with pressure in high speed data actuation measurement detonation section
Distribution, so as to calculate detonation wave velocity of wave, and further calculates the stagnation temperature and stagnation pressure of high-temperature fuel gas in detonation section.
Further, in the step D, each gas is all that the principle for being equal to intrinsic standoff ratio according to mol ratio is independently filled
Gas, is charged under normal temperature condition after partial pressure value set in advance, is re-filled with second of gas, all gas is charged successively, and protect
It is uniform to be sufficiently mixed to hold the regular hour.
Further, in the step F, the oxidant and fuel gas of detonation section are filled with simultaneously under normal temperature condition.
Further, in the step H, in detonation section tube wall perforate, install and surveyed using piezoresistive pressure sensor
Gaseous-pressure is measured, detonation wave velocity of wave is measured using piezoelectric pressure indicator.
The present invention is according to mass conservation law and energy equation f (a, b, c, d, combustion gas stagnation temperature T, stagnation pressure P, single detonation mode)
=Δ Hf, on the basis of existing detonation driven technology, a variety of cleaning non-toxic gas of selection, and mixed, then pass through
Single detonation mode carries out detonation, produces and actual engine Gas Components and the completely the same high temperature of thermodynamic state, high velocity air,
So as to simulate the condition of high temperature of the stagnation temperature in the range of 2200K~2800K after jet fuel and oxidant burning, further
Improve the comprehensive development in laboratory and jet pipe performance and the experimental ability relevant with Nozzle Flow and level.
Brief description of the drawings
Fig. 1 is the inventive method flow chart；
Fig. 2 is the single detonation driven principle schematic of the present invention；
Fig. 3 be ethene and air experimental state debugging result in the embodiment of the present invention 1 (To=2800K, Po=4.8bar,
Gas oil ratio Φ=1).
Embodiment
Embodiment 1：Referring to Fig. 1 to Fig. 3, using JF-14 high-temperature fuel gas shock tunnels, cleaning is used as using hydrogen and air
During gas, Gas Components are modeled for ethene and air, and oil gas ratio is 0.8~1.2；One kind is based on single detonation driven cleaning gas
The method that body simulates jet engine high-temperature fuel gas, comprises the following steps：
A. according to the molecular formula of jet fuel and oxidant is modeled, obtain being modeled jet fuel and
The atomic component that oxidant contains respectively；
B. selection contains a variety of cleanings for being modeled atomic composition contained by jet fuel and oxidant without poison gas
Body；
C. according to mass conservation law and energy equation f (a, b, c, d, combustion gas stagnation temperature T, stagnation pressure P, single detonation mode)=Δ
Hf(wherein a, b, c, d are the mol ratio of gas with various respectively), selects a variety of particular types for cleaning non-toxic gas and mutual
Mol ratio；By being modeled the temperature and pressure of jet engine combustion product, it is determined that being filled with first in detonation device detonation section
Beginning pressure；
D. a variety of cleaning non-toxic gas are divided into fuel and the class of oxidant two, premixed respectively in two bombs,
Each gas in each class gas is equal to the principle of intrinsic standoff ratio according to mol ratio, and individually phase is mixed successively under normal temperature condition
Answer in type bomb, fuel-based and oxidation category gas can not be blended mutually；Each gas is all to be equal to divide according to mol ratio
The principle independent inflatable of pressure ratio, is charged under normal temperature condition after partial pressure value set in advance, is re-filled with second of gas, fills successively
Complete all gas, and kept for the regular hour uniform to be sufficiently mixed；
E. detonation device is divided into three sections, one section is to unload quick-fried section, and length is 2~4 meters；One section be detonation section, length 15~
30 meters；Also one section is jet pipe and vacuum chamber, 8~10 meters of length；Unload quick-fried section and detonation section between, detonation section with nozzle entry it
Between separated and fastened diaphragm with diaphragm respectively with flange；Diaphragm fastening after, by unload quick-fried section, detonation section and nozzle exit vacuum
Chamber is evacuated, and evacuating valve is closed afterwards, only opens the pressure transmitter valve of measurement detonation section the blowing pressure；
F. according to the amount for being modeled jet fuel and oxidant, pre- mixed fuel and oxidant gas will be distinguished
Body is filled with detonation section simultaneously, needs to carry out the demarcation of oxidant and fuel charge flow before being filled with, so as to two class gases according to
Predetermined ratio uniform mixing again in detonation section, the blowing pressure is the initial pressure that is determined in the step C；
G. after the completion of the gas inflated of detonation section, the pressure inverting of the blowing pressure in all charging valves and measurement pipe is closed
Device valve；The high-speed data acquistion system of measurement dynamic pressure is opened before igniting, close to nozzle entry in detonation section during experiment
Place is completed using ignitron igniting, ignition point, and total test period is no more than 100 milliseconds；
H. detonation section tube wall is provided with pressure sensor, process of the test with pressure in high speed data actuation measurement detonation section
Distribution, so as to calculate detonation wave velocity of wave, and further calculates the stagnation temperature and stagnation pressure of high-temperature fuel gas in detonation section.
Claims (4)
1. a kind of method that jet engine high-temperature fuel gas is simulated based on single detonation driven clean gas, it is characterised in that including
The following steps：
A. according to the molecular formula for being modeled jet fuel and oxidant, obtain being modeled jet fuel and oxidation
The atomic component that agent contains respectively；
B. selection contains a variety of cleaning non-toxic gas for being modeled atomic composition contained by jet fuel and oxidant；
C. according to mass conservation law and energy equation f (a, b, c, d, combustion gas stagnation temperature T, stagnation pressure P, single detonation mode)=Δ Hf(its
Middle a, b, c, d are the mol ratio of gas with various respectively), select the particular type and mutual mole of a variety of cleaning non-toxic gas
Than；By being modeled the temperature and pressure of jet engine combustion product, it is determined that being filled with the initial pressure in detonation device detonation section；
D. a variety of cleaning non-toxic gas are divided into fuel and the class of oxidant two, premixed respectively in two bombs, it is each
Each gas in class gas is equal to the principle of intrinsic standoff ratio according to mol ratio, and individually respective class is mixed successively under normal temperature condition
In type bomb, fuel-based and oxidation category gas can not be blended mutually；
E. detonation device is divided into three sections, one section is to unload quick-fried section, and length is 2~4 meters；One section is detonation section, 15~30 meters of length；
Also one section is jet pipe and vacuum chamber, 8~10 meters of length；Unload between quick-fried section and detonation section, divide between detonation section and nozzle entry
Do not separated and fastened diaphragm with diaphragm with flange；After diaphragm fastening, quick-fried section will be unloaded, detonation section and the vacuum chamber of nozzle exit take out
Into vacuum, evacuating valve is closed afterwards, only opens the pressure transmitter valve of measurement detonation section the blowing pressure；
F. it is same by pre- mixed fuel and oxidant gas is distinguished according to the amount for being modeled jet fuel and oxidant
When be filled with detonation section, need to carry out the demarcation of oxidant and fuel charge flow before being filled with, so that two class gases are according to predetermined
Ratio uniform mixing again in detonation section, the blowing pressure is the initial pressure that is determined in the step C；
G. after the completion of the gas inflated of detonation section, the pressure transmitter valve of the blowing pressure in all charging valves and measurement pipe is closed
Door；The high-speed data acquistion system of measurement dynamic pressure is opened before igniting, is adopted during experiment in detonation section at nozzle entry
Lighted a fire with ignitron, ignition point is completed, total test period is no more than 100 milliseconds；
H. detonation section tube wall is provided with pressure sensor, process of the test with pressure point in high speed data actuation measurement detonation section
Cloth, so as to calculate detonation wave velocity of wave, and further calculates the stagnation temperature and stagnation pressure of high-temperature fuel gas in detonation section.
2. a kind of side that jet engine high-temperature fuel gas is simulated based on single detonation driven clean gas as claimed in claim 1
Method, it is characterised in that in the step D, each gas is all the principle independent inflatable for being equal to intrinsic standoff ratio according to mol ratio, is filled
To after partial pressure value set in advance, second of gas is re-filled with, all gas are charged successively, and kept for the regular hour to fill
Divide well mixed.
3. a kind of side that jet engine high-temperature fuel gas is simulated based on single detonation driven clean gas as claimed in claim 1
Method, it is characterised in that in the step F, is filled with the oxidant and fuel gas of detonation section under normal temperature condition.
4. a kind of side that jet engine high-temperature fuel gas is simulated based on single detonation driven clean gas as claimed in claim 1
Method, it is characterised in that in the step H, measures gaseous-pressure using piezoresistive pressure sensor in detonation section, uses piezoelectricity
Formula pressure sensor measures detonation wave velocity of wave.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710338584.7A CN107271132A (en) | 2017-05-12 | 2017-05-12 | A kind of method that jet engine high-temperature fuel gas is simulated based on single detonation driven clean gas |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710338584.7A CN107271132A (en) | 2017-05-12 | 2017-05-12 | A kind of method that jet engine high-temperature fuel gas is simulated based on single detonation driven clean gas |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107271132A true CN107271132A (en) | 2017-10-20 |
Family
ID=60063982
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710338584.7A Pending CN107271132A (en) | 2017-05-12 | 2017-05-12 | A kind of method that jet engine high-temperature fuel gas is simulated based on single detonation driven clean gas |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107271132A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110160792A (en) * | 2018-11-15 | 2019-08-23 | 北京机电工程研究所 | A kind of dynamical system dynamic simulation test method |
| CN110749445A (en) * | 2019-10-31 | 2020-02-04 | 中国科学院力学研究所 | Ramjet direct-connected test device utilizing detonation driving technology |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH06213763A (en) * | 1993-01-14 | 1994-08-05 | Kunio Terao | Shock wave pipe employing detonation driven piston |
| CN2723978Y (en) * | 2004-05-18 | 2005-09-07 | 中国科学院力学研究所 | Igniter for explosive driving shock wave tunnel |
| CN203178060U (en) * | 2013-01-14 | 2013-09-04 | 中国人民解放军总参谋部工程兵科研三所 | Hypersonic aircraft ground simulation test dedicated shock wave tunnel |
| CN106525439A (en) * | 2016-11-28 | 2017-03-22 | 西安航天动力测控技术研究所 | Complete detonation, explosion transmission and explosion initiation structure for large-size high-energy solid rocket engine |
-
2017
- 2017-05-12 CN CN201710338584.7A patent/CN107271132A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH06213763A (en) * | 1993-01-14 | 1994-08-05 | Kunio Terao | Shock wave pipe employing detonation driven piston |
| CN2723978Y (en) * | 2004-05-18 | 2005-09-07 | 中国科学院力学研究所 | Igniter for explosive driving shock wave tunnel |
| CN203178060U (en) * | 2013-01-14 | 2013-09-04 | 中国人民解放军总参谋部工程兵科研三所 | Hypersonic aircraft ground simulation test dedicated shock wave tunnel |
| CN106525439A (en) * | 2016-11-28 | 2017-03-22 | 西安航天动力测控技术研究所 | Complete detonation, explosion transmission and explosion initiation structure for large-size high-energy solid rocket engine |
Non-Patent Citations (2)
| Title |
|---|
| 陈宏 等: "利用爆轰产生高温燃气的方法", 《高超声速专题研讨会暨第五届全国高超声速科学技术会议论文集》 * |
| 黄永辉: "正向爆轰驱动高焓激波管性能研究", 《中国科学院力学研究所机构知识库》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110160792A (en) * | 2018-11-15 | 2019-08-23 | 北京机电工程研究所 | A kind of dynamical system dynamic simulation test method |
| CN110749445A (en) * | 2019-10-31 | 2020-02-04 | 中国科学院力学研究所 | Ramjet direct-connected test device utilizing detonation driving technology |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107024355A (en) | A kind of method that jet engine high-temperature fuel gas is simulated based on double detonation driven clean gas | |
| Rasheed et al. | Experimental investigations of the performance of a multitube pulse detonation turbine system | |
| CN111157248B (en) | Ramjet based on ground direct connection test and combustion chamber performance evaluation method thereof | |
| Peng et al. | The effect of cavity on ethylene-air continuous rotating detonation in the annular combustor | |
| Stout et al. | Demonstrated low loss and low equivalence ratio operation of a rotating detonation engine for power generation | |
| CN107271132A (en) | A kind of method that jet engine high-temperature fuel gas is simulated based on single detonation driven clean gas | |
| Baratta et al. | Demonstrated low pressure loss inlet and low equivalence ratio operation of a rotating detonation engine (RDE) for power generation | |
| Weixin et al. | Experimental research of air-throttling ignition for a scramjet at Ma 6.5 | |
| Litke et al. | Assessment of the Performance of a Pulsejet and Comparison with a Pulsed-Detonation Engine | |
| Glaser et al. | Performance of an axial flow turbine driven by multiple pulse detonation combustors | |
| Nalim et al. | Air-standard aerothermodynamic analysis of gas turbine engines with wave rotor combustion | |
| Michalski et al. | Experimental investigation of ignition stability in a cyclic constant-volume combustion chamber featuring relevant conditions for air-breathing propulsion | |
| CN103968907B (en) | A kind of above-critical state and the close flow measuring apparatus of gaseous hydrocarbon fuel and method | |
| Munday et al. | The design and validation of a pulse detonation engine facility with and without axial turbine integration | |
| Azevedo et al. | Experimental investigation of high regression rate paraffin for solid fuel ramjet propulsion | |
| CN111024359B (en) | Short-time gas injection flow measuring method | |
| Lisanti et al. | Improving the performance of an active valve resonant pulse combustor | |
| RU2586792C1 (en) | Method of determining coefficient of gas flow through nozzle assembly of turbine bypass gas turbine engine | |
| Salminen et al. | Experimental demonstration of a novel deflagration-based pressure gain combustion technology | |
| Anderson et al. | Performance trends for a product scale pulse detonation engine | |
| Snyder et al. | Pressure Gain Combustor Component Viability Assessment Based on Initial Testing | |
| Tangirala et al. | Performance of a pulse detonation combustor-based hybrid engine | |
| Sterling et al. | Enhanced combustion pulsejet engines for Mach 0 to 3 applications | |
| Foelsche et al. | Experiments on a RBCC ejector scramjet with integrated, staged secondary fuel injection | |
| Cullon et al. | Calibration of Lewis hypersonic tunnel facility at Mach 5, 6, and 7 |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20171020 |