CN103604135A - Automatic ignition and temperature control method for aviation kerosene and gas generator - Google Patents
Automatic ignition and temperature control method for aviation kerosene and gas generator Download PDFInfo
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- CN103604135A CN103604135A CN201310548016.1A CN201310548016A CN103604135A CN 103604135 A CN103604135 A CN 103604135A CN 201310548016 A CN201310548016 A CN 201310548016A CN 103604135 A CN103604135 A CN 103604135A
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Abstract
The invention provides an automatic ignition and temperature control method for an aviation kerosene and gas generator, and relates to an ignition and temperature control method for a combustor. A function implementing method has characteristics of automatic ignition of a combustor in a blowing experiment for a hypersonic aircraft and characteristics of automatic high-precision temperature control. Adoption of expert control mainly comprises that an intelligent technology of an expert is used to guide engineering control, and the engineering control is required to reach an expert control level. Because a combustion process is complicated, and multi-parameter and multi-loop coordination control is related, the knowledge of the combustion expert is summarized in a knowledge base, and after field data are reasoned by the expert, corresponding expert decisions or control outputs are obtained. The control method has high reliability and stability, meets the requirement of a user on a modern management test, and can be used for a thermal environment simulation test of a hypersonic aircraft structure; the testing time and the testing cost are saved; and the economic benefit is high.
Description
The application is dividing an application of No. 201110098384.1, Chinese patent application.
Technical field
The present invention relates to a kind of aviation kerosine ignition of gas generator and automatic temperature control function implementation method.Belong to computer controlled automatic and intelligent control method design field.
Background technology
A kind of gas generator mainly utilizes aviation kerosine burning to produce high-temperature fuel gas stream, can be for hot environment simulation field.
Aviation kerosine ignition process is very complicated, requires the time coordination of fuel feeding and sparking to put in place very much, otherwise is being easy to a little not, and if loss of ignition fuel cut-off not in time probably causes that " fall combustion " jeopardizes the safety of fuel system.On the other hand, aviation kerosine burning is a complexity and dangerous process, is complicated non-linear rule between its outlet temperature and entry of combustion chamber air themperature, air/fuel mass flow ratio and combustion chamber inner tissue combustion case.For different combustion chambers, import and export temperature rise demands, its inlet air temperature, air/fuel mass flow ratio are also different, and control law is difficult to Design and implementation automatically.Once there is overshoot or temperature change fast, likely damage combustion chamber and rear end high-temperature pipe.
For this reason, often there is ignition problem in China's existing aviation kerosine combustion gas generation equipment at present, and be mostly to follow according to outlet gas-flow temperature requirements manual adjustments fuel flow, can not realize automatically-controlled continuous, can not accurately control oil/gas ratio, adversely effecting temp control accuracy again.
Summary of the invention
The present invention is a kind of aviation kerosine ignition of gas generator and temperature automatic control scheme and control method, its objective is realization " one-touch " igniting and combustor exit gas-flow temperature automatically-controlled continuous function.
Wherein, " one-touch " ignition function is mainly by setting certain fired state, and gas supply flow and temperature, fuel pump charge oil pressure while lighting a fire, can guarantee ignition success rate so to greatest extent.Simultaneously, by computer measurement and control programmed acquisition, to ignition switch, start after action, after timing 15s, open oil feed line magnetic valve and start fuel feeding, whether observe combustion chamber lights a fire successfully and keeps turning off igniting oil circuit magnetic valve and ignition power after 30s, if loss of ignition, cut off for solenoid relight step after 180s.
Rely on the distributed measurement and control system of design, the knowledge of burning expert repetition test is converted to control algolithm and optimized.The multiloop double closed-loop control system of design based on expertise reasoning.Ignition temperature desired value, control deviation, combustor inlet temperature, combustion chamber charge flow rate, fuel flow etc. are carried out to reasoning according to the inference rule consisting of expertise and optimized algorithm, and then realize the control to target high temperature.Take combustion high temperature as target, by expert reasoning, make combustor inlet gas temperature degree, the cooperation that cooperatively interacts of fuel flow loop, thus realize the control to high temperature.
Effect of the present invention: the TT&C system of this environmental-test facility, completed the hardware and software management system design based on collecting and distributing type, facilitated testing crew to carry out automatically combustion chamber ignition process, and its temperature parameter is controlled, and obtained good effect, realized higher parameter control accuracy.
Accompanying drawing explanation
Fig. 1 is automatic control ignition mode flow chart according to an embodiment of the invention.
Fig. 2 is temperature control principle drawing according to an embodiment of the invention.
Fig. 3 is burning experts database structure chart according to an embodiment of the invention.
The specific embodiment
Shown in Fig. 1 is automatic control ignition mode flow chart according to an embodiment of the invention.This flow process comprises:
Start step (101), mainly comprise the initialization of data,
Carry out the judgement (112) whether lower limit is reported to the police, if fuel delivery has reached lower limit, terminating operation enters and exits step, otherwise enters oil filter warning (113) judgement, if oil filter is reported to the police, terminating operation enters and exits step.If all without two warnings, start oil pump and carry out (102) step, by inquiry experts database, obtain initial fuel supply flow rate (103) step.Inquiry fuel feeding experts database (104), regulates subsidiary combustion chamber fuel flow (105) and main combustion chamber fuel flow (106) for igniting flow.Start igniting (107), comprise and set timer (as set 45s) and open subsidiary combustion chamber, main combustion chamber ignition switch.Entering igniting judgement (108), if subsidiary combustion chamber, main combustion chamber monitor temperature all raise fast, representing to light a fire successfully, can close ignition switch.If loss of ignition, closes ignition switch, closes all fuel cocks, keep air mass flow constant, after delay scheduled time (as 180s), repeat igniting (107) and (108) two steps of igniting judgement above, until light a fire successfully.In ignition process, intake air temperature should be lower than 220 ℃.Subsequently, operation enters step (109), increases in proportion subsidiary combustion chamber, main combustion chamber fuel flow to smooth combustion flow.Then, operation enters determining step (110) and judges that actual flow is whether in error range, if continuing test, "Yes" enters step (111), if "No", operates and enter step (109), continue to regulate large subsidiary combustion chamber, main combustion chamber fuel flow to smooth combustion flow.Finally entering (114) finishes.
Fig. 2 is temperature control flow figure according to an embodiment of the invention.Rely on the distributed measurement and control system of design, the knowledge of burning expert repetition test is converted to control algolithm and optimized.The multiloop double closed-loop control system of design based on expertise reasoning.Combustion high temperature temperature is target, by expert reasoning, makes interior ring combustor inlet gas temperature degree, the cooperation that cooperatively interacts of fuel flow loop, thus realize the control to high temperature.This temperature control flow comprises:
Start (201).Enter input temp and set (202), after temperature setting is reserved, inquiry temperature/flow/fuel flow (204), inquiry expert knowledge library (203) carries out reasoning by combustion high temperature desired value, control deviation, combustor inlet temperature, combustion chamber charge flow rate, fuel flow etc. according to the inference rule consisting of expertise (203) and optimized algorithm.Then, temperature is controlled and is carried out temperature control signals regulation output (205), by power regulating eqiupment (206), regulates electric heater (207); By error in judgement (208), if in error range; Enter and continue test procedure (216), otherwise get back to temperature control signals regulation output step (205).Simultaneously, flow control signal regulation output (209) is carried out in flow-control, by control valve (210), regulated, by error in judgement (211), if in error range, enter and continue test procedure (216), otherwise get back to flow control signal regulation output step (209).Simultaneously, fuel flow is controlled and is carried out flow control signal regulation output (212), by frequency converter (213), regulate pump group motor (214), by error in judgement (215), if in error range, enter and continue test procedure (216), otherwise get back to fuel flow control signal regulation output step (212).
Fig. 3 has shown burning experts database structure chart according to an embodiment of the invention.Expert knowledge library (301) comprises judgement statement (302), judgement statement 2 (303), judgement statement 3 (304), judgement statement 4 (305), empirical equation (306), and particular content comprises:
Judgement statement 1 (302): if the required temperature of the current high-temp combustion of combustor inlet temperature < sets the temperature value inquiring, by temperature signal, export (205) to power regulating eqiupment (206), the temperature of controlling electric heater (207) makes combustor inlet temperature be stabilized to desired value.
Rule 2: if combustion test air condition needs change, regulate air flow control loop to desired value, regulate fuel flow control loop simultaneously, make fuel flow follow air mass flow and change and change.Object is to make gas generator outlet temperature be stabilized in reduced levels to reduce the thermic load of oil consumption, minimizing outlet temperature section, keeps the stable of combustion chambers burn simultaneously.
Rule 3: if high temperature control is shaped with deviation, illustrate that high-temperature control deviation is larger, region shown in scope division in different high temperature deviations, by expertise formula, according to current environment calculation of parameter, gone out the desired value of fuel flow, by fuel flow control signal (212) output frequency converter (213) and pump group motor (214), control fuel flow to desired value.
Rule 4: if error is larger, illustrate that fuel flow currency and expertise value are substantially approaching, but high temperature deviation is still larger, fuel flow control loop to be controlled by measurement and control program, the desired value that fuel flow is calculated is the basic accurate control of finely tuning to realize ignition temperature.
According to one embodiment of present invention, empirical equation (306) is:
W
ffor total fuel flow, W
aintake air flow Kg/s, T
* 3outlet temperature, T
* 2inlet temperature, C
ffuel oil hot melt, T
ffuel oil temperature, Hu fuel value, C
p2entrance specific heat, C
p3outlet specific heat, η
etemperature combustion efficiency.
When fuel flow reaches the set-point W of above formula
fafter, after smooth combustion 15s, the difference fine setting fuel delivery according to stable section temperature value and target temperature value, if difference is less than 10 ℃, keeps fuel delivery constant; If stable section temperature value is higher than target temperature value, every 10s reduces total fuel delivery 0.5g/s, until stable section temperature value and target temperature value difference are less than 10 ℃, if stable section temperature value is lower than target temperature value, every 10s increases total fuel delivery 0.5g/s, until stable section temperature value and target temperature value difference are less than 10 ℃, if after repeatedly regulating, total fuel delivery reach according to above formula calculate fuel delivery 120% time, while reaching target temperature not yet, total fuel flow is adjusted to W
f, W
fin this step adjustment process, the fuel flow value that stable section temperature is corresponding with the state of the absolute value minimum of target temperature difference.
Claims (3)
1. an aviation kerosine gas generator temperature autocontrol method, is characterized in that comprising:
Temperature Setting step (202),
Temperature/flow/fuel flow query steps (204),
Expert knowledge library query steps, carries out reasoning by combustion high temperature desired value, control deviation, combustor inlet temperature, combustion chamber charge flow rate, fuel flow etc. according to the inference rule consisting of expertise (203) and optimized algorithm,
Temperature control signals regulation output step (205).
2. according to the method for claim 1, further comprise:
By power regulating eqiupment (206), regulate electric heater (207);
Judgement temperature error (208), if in error range, enters and continues test procedure (216), otherwise get back to temperature control signals regulation output step (205).
3. according to the method for claim 2, further comprise:
Air flow rate control signal regulation output step (209),
By control valve (210), regulated the step of air flow rate,
The step (211) of judgement air flow rate error, if in error range, enters and continues test procedure (216), otherwise get back to air flow rate control signal regulation output step (209),
Fuel flow control signal regulation output step (212),
By frequency converter (213), regulated the step (214) of pump group motor,
The step (215) of the error of judgement fuel flow, if in error range, enters and continues test procedure (216), otherwise get back to fuel flow control signal regulation output step (212).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310548016.1A CN103604135B (en) | 2011-04-19 | 2011-04-19 | A kind of aviation kerosine ignition of gas generator and temperature automatic control method |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110098384 CN102330996B (en) | 2011-04-19 | 2011-04-19 | Ignition and temperature automatic control method for aviation kerosene gas generator |
| CN201310548016.1A CN103604135B (en) | 2011-04-19 | 2011-04-19 | A kind of aviation kerosine ignition of gas generator and temperature automatic control method |
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| Application Number | Title | Priority Date | Filing Date |
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| CN 201110098384 Division CN102330996B (en) | 2011-04-19 | 2011-04-19 | Ignition and temperature automatic control method for aviation kerosene gas generator |
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| CN103604135A true CN103604135A (en) | 2014-02-26 |
| CN103604135B CN103604135B (en) | 2016-03-02 |
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| CN 201110098384 Expired - Fee Related CN102330996B (en) | 2011-04-19 | 2011-04-19 | Ignition and temperature automatic control method for aviation kerosene gas generator |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105928004A (en) * | 2016-06-16 | 2016-09-07 | 河北工程大学 | Fuel oil flow control method and system of high-temperature combustor |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105274321B (en) * | 2015-10-29 | 2017-09-01 | 重庆派斯克刀具制造股份有限公司 | The temprature control method of high-frequency heating |
| CN105910131A (en) * | 2016-06-16 | 2016-08-31 | 河北工程大学 | Fuel gas temperature control method and system of high-temperature combustion system |
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| CN105928004A (en) * | 2016-06-16 | 2016-09-07 | 河北工程大学 | Fuel oil flow control method and system of high-temperature combustor |
| CN105928004B (en) * | 2016-06-16 | 2018-04-06 | 河北工程大学 | The fuel flow control method and its system of a kind of high-temperature burner |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102330996B (en) | 2013-11-06 |
| CN102330996A (en) | 2012-01-25 |
| CN103604135B (en) | 2016-03-02 |
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