CN112832910A - Method for identifying air flameout and secondary starting success of turbofan engine - Google Patents
Method for identifying air flameout and secondary starting success of turbofan engine Download PDFInfo
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- CN112832910A CN112832910A CN202011214742.6A CN202011214742A CN112832910A CN 112832910 A CN112832910 A CN 112832910A CN 202011214742 A CN202011214742 A CN 202011214742A CN 112832910 A CN112832910 A CN 112832910A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
- F02C7/262—Restarting after flame-out
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- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Ignition Installations For Internal Combustion Engines (AREA)
- Combined Controls Of Internal Combustion Engines (AREA)
Abstract
The invention discloses a method for identifying air flameout and secondary starting success of a turbofan engine, which comprises the following steps: the method comprises the following steps: judging whether the engine stalls according to the engine stalling criterion, if so, entering the next step, and if not, judging again; step two: judging whether the total pressure behind the high-pressure compressor fails to report faults or not, if so, entering the next step, and otherwise, skipping to the sixth step; step three: judging whether the height H is in the flight envelope, if so, entering the next step, and otherwise, jumping to the sixth step; step four: starting the engine for the second time, starting electric ignition and oil supply of the precombustion chamber, and synchronously working for 30 s; step five: and judging whether the engine is started for the second time successfully, if so, returning to the step one, and otherwise, sending a request recovery instruction to the unmanned aerial vehicle. The invention can automatically process the problem of air flameout, ensure that the engine can quickly identify the phenomenon of air flameout, reliably and quickly start in air for the second time, and improve the flight safety.
Description
Technical Field
The invention relates to a method for quickly and reliably identifying air flameout and secondary starting success of a turbofan engine, and belongs to the technical field of starting control of turbofan engines.
Background
The air stopping of the engine caused by flameout of the main combustion chamber of the aircraft engine is a serious fault of the aircraft engine, and if the engine is not processed in time or is not processed properly, the accident of machine damage and human death can be caused. Engineers around the world are therefore working to improve the air stall determination and the secondary start capability of engines.
When the turbofan engine is flamed out, the rotating speed of the engine is sharply reduced, and the rotating speed change rate is far greater than the rotating speed change rate under the adjusting working condition, so whether the engine is flamed out or not is generally determined by measuring the rotating speed transient value and the rotating speed change rate. Fig. 1 shows the maximum rpm drop values of a gas generator and the normal deceleration of a certain engine at different operating points at shutdown. The minimum difference between the maximum rate of gas generator speed drop produced in these two cases is 5% per second, which is sufficient to determine the engine misfire detection margin.
After the engine is stopped, the reliability of the engine in the air is improved by generally adopting methods of using the height for plane dive to obtain higher gauge speed so as to achieve higher stable rotation speed for engine starting, using an auxiliary power device and the like. For example, an F-15 aircraft is equipped with two engines of the F100 type, which use a digital electronic control system DEEC, while a gas turbine starter is used to assist the main engine for air starting.
For the existing engine flameout criterion, flameout characteristics and variable working condition characteristics of the engine under various rotating speeds need to be obtained through a large number of tests, and the rotating speed change rate of flameout and variable working conditions under the working conditions needs to be obtained through interpolation in the judging process, so that the judging mode is complex. In addition, the traditional air secondary starting mode of the engine is to ignite by increasing the starting rotating speed under the condition that the engine is completely stopped, the starting process is complex, and the starting time is long.
Disclosure of Invention
The invention provides a method for identifying air flameout and successful secondary starting of a turbofan engine, which can automatically process the problem of air flameout, ensure that the engine can quickly identify the phenomenon of air flameout, reliably and quickly start the turbofan engine for the second time in the air and improve the flight safety.
A method for identifying air flameout and secondary starting success of a turbofan engine comprises the following steps:
the method comprises the following steps: judging whether the engine stalls according to the engine stalling criterion, if so, entering the next step, and if not, returning to the judgment again;
step two: judging whether the total pressure behind the high-pressure compressor fails to report faults or not, if so, entering the next step, and otherwise, skipping to the sixth step;
step three: judging whether the altitude is in the flight envelope, if so, entering the next step, and otherwise, jumping to the sixth step;
step four: starting the engine for the second time, starting electric ignition and oil supply of the precombustion chamber, and synchronously working for 30 s;
step five: judging whether the engine is started for the second time successfully according to a second starting success criterion, if so, returning to the step one, and if not, entering the next step;
step six: and sending a request recovery instruction to the unmanned aerial vehicle.
Further, the engine stall criterion in the first step is as follows: there are 3 successive points dnh/dt ≦ -C (r/min/s) in which C is present1＜C＜C2Or nh is less than 55% nh max, the engine is considered to be flamed out;
wherein: nh is the engine high pressure rotor speed, unit: revolutions per minute (r/min); nh max is the highest design rotating speed of the high-pressure rotor of the engine; dnh/dt is the rate of increase in the engine high pressure rotor speed in units: revolutions per minute per second (r/min/s).
Further, the criterion of success of the second start in the fifth step is as follows: the existence of continuous 3 points dnh/dt is more than or equal to C3r/min/s，C1The speed control rule is selected for three continuous periods after the conditions are met, and the secondary starting is considered to be successful.
Further, C in the engine stall criterion1And C2Is respectively C1≈2.5％nh max，C2≈10％nh max。
Further, engine stall judgment is started after the engine enters steady-state control for the first time.
Further, the steady state control means that the device continuously works for 10 control cycles under the action of a rotating speed control rule.
Further, the highest design rotating speed of the high-pressure rotor of the engine is 53600 revolutions per minute (r/min).
Advantageous effects
The invention can accurately identify the flameout and the successful re-ignition of the engine within millisecond-level time, and carry out secondary starting, thereby ensuring the safety of the engine in air flight; compared with the prior art, the method can judge flameout only by the rotating speed change rate or the rotating speed transient value, has simple and reliable calculation process, is quick and accurate, has very low false alarm rate and false alarm rate, and is suitable for engines working in various height ranges.
Drawings
FIG. 1 is a graph of rate of decrease of engine stall versus normal reduced speed;
FIG. 2 is a flow chart of the engine stall determination of the present invention;
FIG. 3 is a flow chart of the engine restart of the present invention.
Detailed Description
The invention provides a method for identifying air flameout and secondary starting success of a turbofan engine, wherein the engine flameout criterion in the method is as follows: the engine flameout and variable working condition test data are obtained through statistical analysis and are distinguished from the conditions of sensor faults, engine variable working conditions and the like, the change rate of the engine rotating speed is unified to be a specified threshold value when the engine is flamed out in a use safety, and the minimum value is not lower than-C1(r/min/s)，C1Approximately equals to 2.5 percent nh max, and the rotating speed change rate of the engine in flameout is lower than-C under different heights and different working conditions2(r/min/s)，C 210% nh max, so to increase the accuracy of determining misfire, theThe engine stall criterion is specified as follows: if there are 3 consecutive points dnh/dt. ltoreq. -C (r/min/s), where C1＜C＜C2Or nh < 55% nh max, the engine is deemed to be stalled. And (3) starting to judge the flameout of the engine after the engine enters steady-state control for the first time (continuously working for 10 control cycles under the action of a rotating speed control rule).
As shown in fig. 2, the engine stall determination process is: firstly, judging whether 3 continuous points dnh/dt are less than or equal to-C (r/min/s), if so, judging that the engine stalls, otherwise, judging whether nh is less than 55% nh max, if so, judging that the engine stalls, and if not, restarting the judgment process.
Secondary starting of engine
And (3) starting to judge the flameout of the engine after the engine enters steady-state control for the first time (continuously working for 10 control cycles under the action of a rotating speed control rule).
And if the flying height of the engine is in the flying envelope after the engine is flamed out, performing secondary starting, sending an engine flameout secondary starting instruction to the upper computer, switching on the electric ignition device to work, simultaneously starting the electromagnetic valve of the starting oil path of the pre-combustion chamber, and supplying oil to the pre-combustion chamber to realize secondary starting of the engine.
Criterion of success of secondary starting: the existence of continuous 3 points dnh/dt is more than or equal to C3r/min/s，C1The speed control rule is selected for three continuous periods after the conditions are met, and the secondary starting is considered to be successful.
The judgment that the engine meets the criterion of 'secondary starting success' within 30s after the engine is shut down is not carried out, and
a request to reclaim command is sent to the drone.
As shown in fig. 3, the flow of the engine secondary start is as follows:
the method comprises the following steps: judging whether the engine stalls according to the engine stalling criterion, if so, entering the next step, and if not, returning to the judgment again;
step two: judging whether Pt3 (total pressure after the high-pressure compressor) fails to report faults or not, if so, entering the next step, and if not, jumping to the sixth step;
step three: judging whether the height H is in the flight envelope, if so, entering the next step, and otherwise, jumping to the sixth step;
step four: starting the engine for the second time, starting electric ignition and oil supply of the precombustion chamber, and synchronously working for 30 s;
step five: judging whether the engine is started for the second time successfully according to a second starting success criterion, if so, returning to the step one, and if not, entering the next step;
step six: and sending a request recovery instruction to the unmanned aerial vehicle.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (7)
1. A method for identifying air flameout and secondary starting success of a turbofan engine is characterized by comprising the following steps:
the method comprises the following steps: judging whether the engine stalls according to the engine stalling criterion, if so, entering the next step, and if not, returning to the judgment again;
step two: judging whether the total pressure behind the high-pressure compressor fails to report faults or not, if so, entering the next step, and otherwise, skipping to the sixth step;
step three: judging whether the height H is in the flight envelope, if so, entering the next step, and otherwise, jumping to the sixth step;
step four: starting the engine for the second time, starting electric ignition and oil supply of the precombustion chamber, and synchronously working for 30 s;
step five: judging whether the engine is started for the second time successfully according to a second starting success criterion, if so, returning to the step one, and if not, entering the next step;
step six: and sending a request recovery instruction to the unmanned aerial vehicle.
2. Root of herbaceous plantThe method for identifying the success of air-stall and secondary start of a turbofan engine as recited in claim 1, wherein the engine stall criterion in the first step is as follows: there are 3 successive points dnh/dt ≦ -C (r/min/s) in which C is present1＜C＜C2Or nh is less than 55% nh max, the engine is considered to be flamed out;
wherein: nh is the engine high pressure rotor speed, unit: rotating every minute; nh max is the highest design rotating speed of the high-pressure rotor of the engine; dnh/dt is the rate of increase in the engine high pressure rotor speed in units: revolutions per minute per second.
3. The turbofan engine flameout and secondary start success identification method of claim 1 wherein the secondary start success criterion in step five is: the existence of continuous 3 points dnh/dt is more than or equal to C3r/min/s，C1The speed control rule is selected for three continuous periods after the conditions are met, and the secondary starting is considered to be successful.
4. The turbofan engine air stall and after-start success identification method of claim 1 wherein C is the engine stall criterion1And C2Is respectively C1≈2.5％nh max，C2≈10％nh max。
5. The turbofan engine air stall and secondary start success identification method of claim 4 wherein engine stall determination is initiated after the engine first enters steady state control.
6. The method for recognizing the success of the air extinction and the secondary start of the turbofan engine according to claim 5, wherein the steady state control means continuous operation for 10 control cycles under the action of a rotation speed control law.
7. The method for identifying the success of an airborne misfire and a secondary start in a turbofan engine of claim 2 wherein the maximum design engine high pressure rotor speed is 53600 revolutions per minute.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114893300A (en) * | 2022-04-14 | 2022-08-12 | 北京动力机械研究所 | Small turbofan engine reference pressure parameter fault judgment method and redundancy control method |
| CN117432529A (en) * | 2023-12-20 | 2024-01-23 | 保定市玄云涡喷动力设备研发有限公司 | Control method and system for high-altitude quick start of aircraft and aircraft |
Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3805517A (en) * | 1970-08-11 | 1974-04-23 | Secr Defence | Control system for gas turbine engines |
| US4454754A (en) * | 1982-05-26 | 1984-06-19 | Chandler Evans, Inc. | Engine failure detector |
| US5581995A (en) * | 1995-03-14 | 1996-12-10 | United Technologies Corporation | Method and apparatus for detecting burner blowout |
| JP2001295669A (en) * | 2000-04-17 | 2001-10-26 | Ishikawajima Harima Heavy Ind Co Ltd | Method and apparatus for controlling jet engine |
| EP2110516A2 (en) * | 2008-04-18 | 2009-10-21 | Honeywell International Inc. | Gas turbine engine rotor lock prevention system and corresponding method |
| US20100107591A1 (en) * | 2008-11-06 | 2010-05-06 | Honeywell International Inc. | Turbomachine flameout confirmation |
| CN102072063A (en) * | 2011-01-04 | 2011-05-25 | 北京航空航天大学 | Encounter-starting airstart system of aircraft engine |
| CN103630363A (en) * | 2013-12-12 | 2014-03-12 | 北京动力机械研究所 | Simulation test method for high altitude ignition ability of turbine engine |
| CN106043715A (en) * | 2016-05-27 | 2016-10-26 | 襄阳宏伟航空器有限责任公司 | In-flight auto-ignition control method of engine of unmanned aerial vehicle |
| CN110736625A (en) * | 2019-10-08 | 2020-01-31 | 中国航发沈阳发动机研究所 | method for identifying main combustion chamber flameout of double-rotor gas turbine engine |
| CN111255570A (en) * | 2018-12-03 | 2020-06-09 | 劳斯莱斯有限公司 | Method and apparatus for controlling at least a portion of a start or re-ignition process of a gas turbine engine |
| CN111527285A (en) * | 2017-12-13 | 2020-08-11 | 赛峰飞机发动机公司 | Method for detecting ignition of a turbine engine |
-
2020
- 2020-11-04 CN CN202011214742.6A patent/CN112832910A/en active Pending
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3805517A (en) * | 1970-08-11 | 1974-04-23 | Secr Defence | Control system for gas turbine engines |
| US4454754A (en) * | 1982-05-26 | 1984-06-19 | Chandler Evans, Inc. | Engine failure detector |
| US5581995A (en) * | 1995-03-14 | 1996-12-10 | United Technologies Corporation | Method and apparatus for detecting burner blowout |
| JP2001295669A (en) * | 2000-04-17 | 2001-10-26 | Ishikawajima Harima Heavy Ind Co Ltd | Method and apparatus for controlling jet engine |
| EP2110516A2 (en) * | 2008-04-18 | 2009-10-21 | Honeywell International Inc. | Gas turbine engine rotor lock prevention system and corresponding method |
| US20100107591A1 (en) * | 2008-11-06 | 2010-05-06 | Honeywell International Inc. | Turbomachine flameout confirmation |
| CN102072063A (en) * | 2011-01-04 | 2011-05-25 | 北京航空航天大学 | Encounter-starting airstart system of aircraft engine |
| CN103630363A (en) * | 2013-12-12 | 2014-03-12 | 北京动力机械研究所 | Simulation test method for high altitude ignition ability of turbine engine |
| CN106043715A (en) * | 2016-05-27 | 2016-10-26 | 襄阳宏伟航空器有限责任公司 | In-flight auto-ignition control method of engine of unmanned aerial vehicle |
| CN111527285A (en) * | 2017-12-13 | 2020-08-11 | 赛峰飞机发动机公司 | Method for detecting ignition of a turbine engine |
| CN111255570A (en) * | 2018-12-03 | 2020-06-09 | 劳斯莱斯有限公司 | Method and apparatus for controlling at least a portion of a start or re-ignition process of a gas turbine engine |
| CN110736625A (en) * | 2019-10-08 | 2020-01-31 | 中国航发沈阳发动机研究所 | method for identifying main combustion chamber flameout of double-rotor gas turbine engine |
Non-Patent Citations (2)
| Title |
|---|
| 廖文波: "RB211-535E4发动机地面低功率喘振熄火故障分析", 《中国民航飞行学院学报》 * |
| 马同玲等: "基于.NET 的小型涡扇发动机故障判读系统设计与实现", 《航空发动机》 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114893300A (en) * | 2022-04-14 | 2022-08-12 | 北京动力机械研究所 | Small turbofan engine reference pressure parameter fault judgment method and redundancy control method |
| CN114893300B (en) * | 2022-04-14 | 2023-10-13 | 北京动力机械研究所 | Parameter control pressure parameter judging method and redundancy control method for small turbofan engine |
| CN117432529A (en) * | 2023-12-20 | 2024-01-23 | 保定市玄云涡喷动力设备研发有限公司 | Control method and system for high-altitude quick start of aircraft and aircraft |
| CN117432529B (en) * | 2023-12-20 | 2024-05-24 | 保定市玄云涡喷动力设备研发有限公司 | Control method and system for high-altitude quick start of aircraft and aircraft |
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