CN113719359A - Protection method and system for preventing overrotation and breakage of turbine of aviation turboshaft engine - Google Patents
Protection method and system for preventing overrotation and breakage of turbine of aviation turboshaft engine Download PDFInfo
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- CN113719359A CN113719359A CN202111141204.3A CN202111141204A CN113719359A CN 113719359 A CN113719359 A CN 113719359A CN 202111141204 A CN202111141204 A CN 202111141204A CN 113719359 A CN113719359 A CN 113719359A
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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
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/48—Control of fuel supply conjointly with another control of the plant
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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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Abstract
The invention discloses a protection method and a system for preventing overrotation fracture of a turbine of an aviation turboshaft engine, and the protection method for preventing overrotation fracture of the turbine of the aviation turboshaft engine comprises the following steps: analyzing the parameter change trend when the power turbine shaft of the engine is broken or the related connection fails; determining the characteristics of the significant test data according to the parameter variation trend; determining a fault condition according to the significant test data characteristics; detecting whether a fault condition reaches a threshold; and when the fault condition reaches a set threshold value, taking protective measures and indicating fault information. The invention obtains the obvious test data characteristic by analyzing the parameter change trend of the breakage of the power turbine shaft or the related connection failure, provides a protection method of high rotating speed and low torque, takes the rotating speed and the torque or the torque reduction slope of the gas generator as judgment conditions, and protects the engine from emergency automatic stop when the fault conditions are met, thereby preventing the destructive over-rotation of the power turbine, having rapid response and improving the test safety.
Description
Technical Field
The invention belongs to the technical field of control of aero-engines, and particularly relates to a protection method and a protection system for preventing over-rotation and breakage of a turbine of an aero-turboshaft engine.
Background
For an aviation turboshaft engine with a turbine part in a bearing common-cavity structure, a rotating speed measuring mechanism is not arranged behind a power turbine, if the power turbine shaft is broken or related connection fails, the rotating speed of the power turbine is increased rapidly, but the actual rotating speed cannot be detected. Because the rotating speed of the power turbine displayed by the engine control system is reduced, at the moment, the control system continues to increase fuel supply, the engine state is not reduced and is reversely increased, so that the rotating speed of the power turbine is sharply increased, and the risk that the engine is seriously damaged due to the over-rotation and breakage of the turbine exists.
The existing protection methods for the ground bench test rotating speed, temperature and torque of the aviation turboshaft engine are all high-value set protection, and no emergency automatic protection method aiming at the condition that the actual rotating speed of the power turboshaft cannot be detected when the power turboshaft is broken or the related connection fails is adopted, and the method is manually judged and reacted or the rotating speed n of a gas generator of the engine is adoptedgThe gas temperature can trigger the protection to stop when reaching the protection set value, has the risk that inefficiency, damage are big, even the processing time of a few seconds delays, and the damage to the engine is all very big, has the cracked risk of engine wheel dish overrotation. At present, the prior art does not simultaneously rotate the gasifier at ngThe rising and the torque rapid descending or the torque descending slope are used as fault conditions for judging the over-rotation of the aviation turboshaft engine, so that a protection method for preventing the over-rotation and the breakage of the turbine of the aviation turboshaft engine is urgently needed.
Disclosure of Invention
Aiming at the problems, the invention discloses a protection method for preventing the turbine of an aviation turboshaft engine from over-rotating and cracking, which comprises the following steps:
analyzing the parameter change trend when the power turbine shaft of the engine is broken or the related connection fails;
determining the characteristic of the significant test data according to the parameter variation trend;
determining a fault condition according to the significant test data characteristics;
detecting whether the fault condition reaches a threshold value;
and when the fault condition reaches a set threshold value, taking protective measures and indicating fault information.
Further, the parameter variation trend is specifically as follows:
power turbine speed n measured by engine control systemp controlDescending;
power turbine rotating speed n measured by ground rack testing systemp ground platformDescending;
actual power turbine speed npragmaRapidly ascending;
the torque measurement drops sharply to 0;
the fuel flow of the engine control system rises;
speed n of engine gas generatorgRising;
actual power turbine speed npragmaAnd rises sharply.
Still further, the significant test data is characterized by a gasifier speed ngRise and sharp drop in torque.
Still further, the fault condition includes:
speed n of gas generatorgGreater than the first set value and for a duration greater than the fourth set value;
the torque is smaller than the second set value or the torque descending slope is larger than the third set value and the duration is larger than the fourth set value.
Further, the protective measures are automatic engine shut-down control and ground rack fuel cut-off.
A protection system for preventing overrotation cracking of an aircraft turboshaft engine turbine, comprising:
the analysis unit is used for analyzing the parameter variation trend when the power turbine shaft of the engine is broken or the related connection fails;
the determining unit is used for determining the significant test data characteristics according to the parameter variation trend;
the determining unit is used for determining a fault condition according to the significant test data characteristics;
a detection unit for detecting whether the fault condition reaches a threshold value;
and the protection unit is used for taking protective measures and indicating fault information when the fault condition reaches a set threshold value.
Further, the parameter variation trend is specifically as follows:
power turbine speed n measured by engine control systemp controlDescending;
power turbine rotating speed n measured by ground rack testing systemp ground platformDescending;
actual power turbine speed npragmaRapidly ascending;
the torque measurement drops sharply to 0;
the fuel flow of the engine control system rises;
speed n of engine gas generatorgRising;
actual power turbine speed npragmaAnd rises sharply.
Still further, the significant test data is characterized by a gasifier speed ngRise and sharp drop in torque.
Still further, the fault condition includes:
speed n of gas generatorgGreater than the first set value and for a duration greater than the fourth set value;
the torque is smaller than the second set value or the torque descending slope is larger than the third set value and the duration is larger than the fourth set value.
Further, the protective measures are automatic engine shut-down control and ground rack fuel cut-off.
Compared with the prior art, the invention has the beneficial effects that: by analyzing the parameter change trend when the power turbine shaft is broken or the related connection fails, the obvious test data characteristics are obtained, and a protection method with a high-rotating-speed low-torque protection function is provided to automatically protect the engineThe emergency stop protection prevents the destructive over-rotation of the power turbine, has quick response, improves the test safety, and reduces the damage of the engine. By adding special detecting unit, the rotating speed n of the gas generator is detectedgAnd the torque or the torque reduction slope, and the power turbine shaft breakage or the related connection failure can be confirmed only when the fault condition is met, so that the protection measures and the fault indication information are taken immediately, the accuracy of judging whether the power turbine shaft breakage or the related connection failure occurs is effectively improved, and the protection measures are taken in time.
Additional features and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. The objectives and other advantages of the invention will be realized and attained by the structure particularly pointed out in the written description and claims hereof as well as the appended drawings.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and those skilled in the art can also obtain other drawings according to the drawings without creative efforts.
FIG. 1 illustrates a ground bench test schematic diagram of an aircraft turboshaft engine according to an embodiment of the present invention;
FIG. 2 illustrates an aircraft turboshaft engine ground bench test control schematic in accordance with an embodiment of the present invention;
FIG. 3 shows a flowchart of a protection method for preventing over-rotation rupture of a turbine of an aviation turboshaft engine according to an embodiment of the invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The ground rack of the present invention comprises: a power absorption and measurement system (i.e., a hydraulic dynamometer), a connecting shaft, a handling system (including a load bar and a control box), a ground bench test system, an electrical control system, a fuel system, an engine control system, etc.
FIG. 1 shows a ground bench test schematic diagram of an aircraft turboshaft engine according to an embodiment of the present invention. As shown in fig. 1, the engine control system is electrically connected with the electrical control system and the ground bench test system, and the engine control system is connected with the engine; the electrical control system is electrically connected with the engine control system, the ground rack test system, the control system, the power absorption and measurement system and the fuel system; the control system is electrically connected with the power absorption and measurement system, the electrical control system and the engine control system; the ground bench test system is electrically connected with the electrical control system, the power absorption and measurement system and the engine control system; the fuel system is electrically connected with the electrical control system and the ground rack test system, and the fuel system is connected with the engine body and supplies fuel for the engine.
The ground bench test principle of the aviation turboshaft engine is as follows: the torque and the rotating speed output by the engine are transmitted to the power absorption and measurement system through the connecting shaft, and the torque, the rotating speed and the absorbed power of the engine are measured. The operating system controls the engine state. The ground bench test system monitors, measures and records various state parameters of the engine and the ground bench equipment, and has the functions of high rotating speed value protection setting and signal output. The electric control system starts and controls the ground rack equipment, and sends related control signals to the engine control system, so that the important working parameters of the engine can be alarmed or protected and indicated. The fuel system provides fuel to the engine that meets pressure and temperature requirements.
The power absorption and measurement system measures the torque and speed of the engine and converts it into output power using the following equation:
FIG. 2 illustrates a ground bench test control schematic diagram of an aircraft turboshaft engine according to an embodiment of the present invention. As shown in fig. 2, a load lever (CLP) is electrically connected with an engine electronic controller and a power absorption and measurement system, and the load lever is used for giving a load demand signal and an engine control system demand regulation signal; the engine electronic controller is electrically connected with the engine and used for controlling the state of the engine; the power absorption and measurement system is connected with the engine and used for adjusting the load of the engine; engine power turbine speed npAnd feeding back to an electronic engine controller. The typical control mode of the ground bench test of the aviation turboshaft engine is the rotating speed n of the power turbinepThe control modes, namely: the engine control system and the power absorption and measurement system act together to control the rotating speed n of the power turbinepIs a constant target value. The engine control system controls the fuel quantity of the engine, the power absorption and measurement system controls the load, and the engine control system calculates the power turbine rotating speed n caused by the load changepVarying, adjusting fuel flow to engine to maintain power turbine speed npIs constant.
FIG. 3 shows a flowchart of a protection method for preventing over-rotation rupture of a turbine of an aviation turboshaft engine according to an embodiment of the invention. As shown in fig. 3, the protection method for preventing the turbine over-rotation rupture of the aviation turboshaft engine provided by the invention comprises the following steps:
analyzing the parameter change trend when the power turbine shaft of the engine is broken or the related connection fails;
determining the characteristic of the significant test data according to the parameter variation trend;
determining a fault condition according to the significant test data characteristics and fully considering the safety and reliability;
establishing a special detection unit for detecting whether the fault condition reaches a threshold value;
and when the fault condition reaches a set threshold value, taking automatic protection measures and indicating fault information.
Wherein a failure of a connection refers to a failure of a connection of a component associated with torque transmission having a mechanical connection to a power turbine shaft. Exemplarily, the connection between the power turbine disk shaft and the power turbine shaft is loosened due to the failure of the connection screw/the abrasion of the spline, the circular arc end teeth at the tail end of the power turbine disk shaft are damaged, or the power turbine disk shaft is broken. Failure refers to loosening or breaking.
If the power turbine shaft is broken or the relevant connection fails, the actual rotating speed of the power turbine cannot be detected, the power turbine loses load immediately, and at the moment, the torque of the engine rapidly drops. According to the calculation formula of the output power of the engine, under the condition of constant power, the torque rapidly drops, and the rotating speed n of the power turbinepThe actual speed rises sharply, but both the engine control system and the ground bench test system display the power turbine speed npDecrease, failing to trigger the power turbine speed npOver-rotation protection, with gas generator speed ngAnd gas temperature protection is not triggered immediately. If the stop is controlled by human judgment and reaction, there is a risk of delay in processing time. The engine control system receives the detected power turbine speed npThe speed reduction signal continues to increase the fuel supply, the engine state does not decrease and reversely rises, and the speed n of the power turbine is caused topRising sharply, there is a safety risk of the turbine over-rotating cracking seriously damaging the engine. The engine parameter variation tendency is specifically shown in table 1. Analyzing the characteristic of the obvious test data when the power turbine shaft is broken or the related connection fails to be the rotating speed n of the gas generatorgRise and sharp drop in torque.
TABLE 1 trend of parameter changes at fault
According to the obvious test data characteristics when the fault occurs, the protection method for determining the ground rack comprises the following steps: protection of high rotating speed and low torque. The ground bench electrical control system increases the rotating speed of the engine gas generator and the torque detection unit of the hydraulic dynamometer, and takes the situation that signal interference possibly occurs to generate misjudgment into consideration, edits a judgment program, and sets guarantee conditions:
a. speed n of gas generatorgGreater than the first set value and for a duration greater than the fourth set value;
b. the torque is smaller than a second set value or the torque descending slope is larger than a third set value and the duration is larger than a fourth set value;
and when the guarantee condition is met, protective measures are taken, the electric control system can display fault information on the upper computer while the vehicle is protected to stop, and the fault information is used for judging and subsequently analyzing the fault reason by an operator.
Wherein, preferably, the first set value is 93.3% of the rated rotation speed of the gas generator; the second set value is 50N · m; the third set value is 890 N.m/s; the fourth setting is 74 ms.
When a or b is detected to meet the requirement, protective measures cannot be taken, only when a and b meet the requirement at the same time, the fault condition is met, the ground bench electrical control system immediately takes the protective measures and sends out an emergency stop signal, the signal is simultaneously output in two paths, one path is sent to the engine control system, the stop valve cuts off fuel oil of the engine, and the engine is controlled to stop immediately; and the other path of the power turbine shaft is sent to a ground rack fuel system, a fuel valve immediately cuts off the supply of ground rack fuel, the emergency stop of the engine is automatically and reliably controlled when the power turbine shaft is broken or the related connection fails, the reliable automatic stop is ensured, and meanwhile, fault information is displayed on an upper computer of an electrical control system and is used for judging and subsequently analyzing the fault reason by an operator. The protection measures adopt a double-protection mode, and the problem that the reliable and automatic stop of the engine cannot be guaranteed due to failure of a single protection measure is effectively avoided. The protection method for preventing the turbine of the aviation turboshaft engine from over-rotating and breaking is applied to a ground bench test of a certain turboshaft engine, emergency stop protection measures are quick in response, the time from the moment when a fault occurs to the moment when the torque quickly drops to reach a guarantee condition to trigger the engine to be stopped in a protection mode is 0.12s, the engine is protected, and the engine is prevented from being seriously damaged. Through setting two guarantee conditions of a and b, and only when satisfying the requirement simultaneously, just can confirm that power turbine shaft breaks or relevant connection failure takes place, and then takes protective measures immediately, protects engine automatic emergency stop, prevents power turbine destructive overrun, improves the accuracy of judging whether power turbine shaft breaks or relevant connection failure takes place, and the response is rapid, improves experimental safety.
Based on the protection method for preventing the overrotation fracture of the turbine of the aviation turboshaft engine, the invention provides a protection system for preventing the overrotation fracture of the turbine of the aviation turboshaft engine, which comprises the following steps:
the analysis unit is used for analyzing the parameter variation trend when the power turbine shaft of the engine is broken or the related connection fails;
the determining unit is used for determining the significant test data characteristics according to the parameter variation trend;
the determining unit is used for determining a fault condition according to the significant test data characteristics;
a detection unit for detecting whether the fault condition reaches a threshold value;
and the protection unit is used for taking protective measures and indicating fault information when the fault condition reaches a set threshold value.
The parameter variation trend is specifically as follows:
power turbine speed n measured by engine control systemp controlDescending;
power turbine rotating speed n measured by ground rack testing systemp ground platformDescending;
actual power turbine speed npragmaRapidly ascending;
the torque measurement drops sharply to 0;
the fuel flow of the engine control system rises;
speed n of engine gas generatorgRising;
actual power turbine speed npragmaAnd rises sharply.
The significant test data is characterized by a gasifier speed ngRise and sharp drop in torque.
The fault conditions include:
speed n of gas generatorgGreater than the first set value and for a duration greater than the fourth set value;
the torque is smaller than the second set value or the torque descending slope is larger than the third set value and the duration is larger than the fourth set value.
The protection measures are automatic control of engine stop and cutting off of fuel supply of a ground stand.
Although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (10)
1. A protection method for preventing overrotation and breakage of a turbine of an aviation turboshaft engine is characterized by comprising the following steps:
analyzing the parameter change trend when the power turbine shaft of the engine is broken or the related connection fails;
determining the characteristic of the significant test data according to the parameter variation trend;
determining a fault condition according to the significant test data characteristics;
detecting whether the fault condition reaches a threshold value;
and when the fault condition reaches a set threshold value, taking protective measures and indicating fault information.
2. The protection method for preventing the turbine over-rotation rupture of the aviation turboshaft engine according to claim 1, wherein the parameter variation trend is as follows:
power turbine speed n measured by engine control systemp controlDescending;
power turbine rotating speed n measured by ground rack testing systemp ground platformDescending;
actual power turbine speed npragmaRapidly ascending;
the torque measurement drops sharply to 0;
the fuel flow of the engine control system rises;
speed n of engine gas generatorgRising;
actual power turbine speed npragmaAnd rises sharply.
3. The method of claim 2, wherein the significant test data is characterized by a gasifier speed ngRise and sharp drop in torque.
4. The method of claim 1, wherein the fault condition comprises:
speed n of gas generatorgGreater than the first set value and for a duration greater than the fourth set value;
the torque is smaller than the second set value or the torque descending slope is larger than the third set value and the duration is larger than the fourth set value.
5. The method of claim 1, wherein the protection measure is automatic engine shutdown control and ground skid fuel supply cutoff.
6. A protection system for preventing overrotation fracture of a turbine of an aviation turboshaft engine, comprising:
the analysis unit is used for analyzing the parameter variation trend when the power turbine shaft of the engine is broken or the related connection fails;
the determining unit is used for determining the significant test data characteristics according to the parameter variation trend;
the determining unit is used for determining a fault condition according to the significant test data characteristics;
a detection unit for detecting whether the fault condition reaches a threshold value;
and the protection unit is used for taking protective measures and indicating fault information when the fault condition reaches a set threshold value.
7. The protection system for preventing overrotation rupture of turbine of aircraft turboshaft engine according to claim 6, wherein the trend of variation of parameters is as follows:
power turbine speed n measured by engine control systemp controlDescending;
power turbine rotating speed n measured by ground rack testing systemp ground platformDescending;
actual power turbine speed npragmaRapidly ascending;
the torque measurement drops sharply to 0;
the fuel flow of the engine control system rises;
speed n of engine gas generatorgRising;
actual power turbine speed npragmaAnd rises sharply.
8. The protection system for preventing overrotation rupture of turbine of aircraft turboshaft engine according to claim 7, characterized in that said significant test data is characterized by a gas generator speed ngRise and sharp drop in torque.
9. The protection system for preventing overrotation cracking of an aircraft turboshaft engine turbine according to claim 6, wherein the fault condition includes:
speed n of gas generatorgGreater than the first set value and for a duration greater than the fourth set value;
the torque is smaller than the second set value or the torque descending slope is larger than the third set value and the duration is larger than the fourth set value.
10. The system of claim 6, wherein the protection is automatic engine shutdown control and ground skid fuel cutoff.
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| CN114679006A (en) * | 2022-04-19 | 2022-06-28 | 贵州航天林泉电机有限公司 | Anti-over-rotation aviation direct-current starting motor structure |
| CN117848709A (en) * | 2024-03-08 | 2024-04-09 | 成都晨发泰达航空科技股份有限公司 | Device and method for testing turbine rotor over-rotation of ultra-high revolution aero-engine |
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| CN113719359B (en) | 2022-11-01 |
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