CN102562319B - Performance adjusting method of engine - Google Patents
Performance adjusting method of engine Download PDFInfo
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- CN102562319B CN102562319B CN201210045878.8A CN201210045878A CN102562319B CN 102562319 B CN102562319 B CN 102562319B CN 201210045878 A CN201210045878 A CN 201210045878A CN 102562319 B CN102562319 B CN 102562319B
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Abstract
The invention provides a performance adjusting method of an engine. The performance adjusting method comprises the following steps of: step S01, respectively obtaining the following parameters including an adjusting rule of the angle of a guide vane of a gas compressor, a throat area of a radial diffuser of the gas compressor, a first flow capacity value of a guider of a gas turbine and a second flow capacity value of a primary guider of a power turbine; step S02, starting the engine, and enabling the gas compressor, the radial diffuser of the gas compressor, the guider of the gas turbine and the primary guider of the power turbine to operate respectively according to the parameters; and simultaneously, carrying out performance test on the engine, thus obtaining performance parameters of the engine. The performance adjusting method has the advantages that by adjustment for the guider of the gas turbine, the primary guider of the power turbine, the gas compressor and the radial diffuser of the gas compressor, all parts of the engine can work in a most coordinated manner, so that all the performances and the pneumatic stability of the engine meet the requirements.
Description
Technical field
The present invention relates to engine art, especially, relate to a kind of performance adjusting method of motor.
Background technique
At present, the gas compressor of some turboshaft engines is without gas compressor stator adjustable system.In order to debug the performance of such turboshaft engine, only the negotiability of the nozzle ring of motor is adjusted, the distribution by appropriate change blow down ratio between turbine, thus reach the object of debugging engine performance.
As known from the above, the debugging of engine performance is only adjusted to the negotiability of nozzle ring, its debugging method is single, can not realize the full picture debugging to motor.Meanwhile, adopt said method can not make the performance of motor and aerodynamic stability meet the demands simultaneously.
Summary of the invention
The object of the invention is to provide a kind of performance adjusting method of motor, with solve existing adjustment method means single, can not realize the full picture debugging to motor, and can not make the performance of motor and the technical problem that aerodynamic stability meets the demands simultaneously simultaneously.
For achieving the above object, draw a side according to the present invention, and a kind of performance adjusting method of motor is provided.Gas compressor, gas compressor radial diffuser, gas turbine guider and power turbine one stage diverter are installed on this motor.The method comprises the steps: step S01: obtain respectively following parameter: the first circulation ability value of long-pending value, gas turbine guider and the second circulation ability value of power turbine one stage diverter are drawn by the stator angle adjustment rule of gas compressor, the throat of gas compressor radial diffuser; Step S02: ato unit, and gas compressor, gas compressor radial diffuser, gas turbine guider and power turbine one stage diverter are moved according to parameter respectively; , motor is made a service test meanwhile, thus the performance parameter of acquisition motor.
Further, in step S02, gas compressor regulates stator according to stator angle adjustment rule.
Further, in step S02, gas compressor radial diffuser is drawn long-pending value according to throat and is regulated throat's picture long-pending.
Further, in step S02, gas turbine guider moves according to the first circulation ability value.
Further, in step S02, power turbine one stage diverter moves according to the second circulation ability value.
Further, after step S02, also carry out following steps: step S03: according to performance parameter, stator angle adjustment rule, throat, draw long-pending value, the first circulation ability value and the second circulation ability value and judge whether the performance of motor and aerodynamic stability all meet the demands.
Further, step S01 specifically comprises the steps: step S011: gas compressor is carried out to parts experiment, obtain stator angle adjustment rule; Step S012: gas compressor radial diffuser is carried out to parts and overall test, obtain throat and draw long-pending value; Step S013; Gas turbine guider is carried out to first-class function experiment, obtain the first circulation ability value; Step S014: power turbine one stage diverter is carried out to the experiment of second function, obtain the second circulation ability value.
Further, step S011, step S012, step S013 and step S014 carry out simultaneously or carry out at times.
The present invention has following beneficial effect:
Adopt the performance adjusting method of motor of the present invention, not only can debug the negotiability of gas turbine guider and power turbine one stage diverter, can also debug the stator angle of gas compressor, long-pending value is drawn by the throat of gas compressor radial diffuser.By the debugging to gas turbine guider, power turbine one stage diverter, gas compressor and gas compressor radial diffuser, can be so that each parts of motor cooperate in harmony most, thus the performance of motor and aerodynamic stability are all met the demands.
Except the described object of upper picture, feature and advantage, the present invention also has other object, feature and advantage.Lower picture is with reference to figure, and the present invention is further detailed explanation.
Accompanying drawing explanation
The accompanying drawing that forms the application's a part is used to provide a further understanding of the present invention, and schematic description and description of the present invention is used for explaining the present invention, does not form inappropriate limitation of the present invention.In the accompanying drawings:
Fig. 1 is the schematic flow sheet of performance adjusting method of the motor of the preferred embodiment of the present invention.
Embodiment
Below in conjunction with accompanying drawing, embodiments of the invention are elaborated, but the multitude of different ways that the present invention can be defined by the claims and cover is implemented.
Referring to Fig. 1, the performance adjusting method of motor of the present invention comprises step S01 and step S02.Wherein, gas compressor, gas compressor radial diffuser, gas turbine guider and power turbine one stage diverter are installed on motor.
Step S01: for gas compressor, gas compressor radial diffuser, gas turbine guider and power turbine one stage diverter being installed on motor provides respectively stator angle adjustment rule, throat to draw long-pending value, the first circulation ability value and the second circulation ability value.
Preferably, before gas compressor, gas compressor radial diffuser, gas turbine guider and power turbine one stage diverter are installed on to motor, can adopt following step S011 and to step S014, obtain respectively stator angle adjustment rule, throat and draw long-pending value, the first circulation ability value and second ability value that circulates.
Step S011: gas compressor is carried out to parts experiment, thereby obtain the stator angle adjustment rule of this gas compressor.
Particularly, first on component test stand, by different stators, regulate rule to carry out parts experiment gas compressor, according to different stators, regulate the impact of rule on component capabilities and stall margin, thereby determine the stator angle adjustment rule of this gas compressor.
Step S012: gas compressor radial diffuser is carried out to parts and complete machine experiment, thereby obtain the long-pending value of throat's picture of this gas compressor radial diffuser.
The long-pending different gas compressor radial diffuser of value of ，Xian Jiang throat picture carries out parts and overall test particularly, thereby according to the experimental result of gas compressor radial diffuser, rationally determines long-pending value of throat's picture of gas compressor radial diffuser.Preferably, in the present embodiment, long-pending value is drawn for 2612mm by the throat of gas compressor radial diffuser
2, upper tolerance is+0.5%, lower tolerance is-1.0%.
Step S013: gas turbine guider is carried out to first-class function experiment, thereby obtain the first circulation ability value of this gas turbine guider.
Particularly, first gas turbine guider is carried out to first-class function experiment, and according to the laboratory data of gained, determine the first circulation ability value of gas turbine guider.Preferably, in the present embodiment, the first circulation ability value of gas turbine guider is
Its tolerance is ± 0.5%.
Step S014: power turbine one stage diverter is carried out to the experiment of second function, thereby obtain the second circulation ability value of this power turbine one stage diverter.
Particularly, first power turbine one stage diverter is carried out to the experiment of second function, and according to the laboratory data of gained, determine the second circulation ability value of power turbine one stage diverter.Preferably, in the present embodiment, the second circulation ability value of power turbine one stage diverter is
Its tolerance is ± 0.5%.
The stator angle adjustment rule obtaining by above-mentioned steps S011, step S012, step S013 and step S014, throat are drawn long-pending value, the first circulation ability value and second ability value that circulates and are carried out respectively the Operational Limits as above-mentioned gas compressor, gas compressor radial diffuser, gas turbine guider and power turbine one stage diverter.Then carry out step S02.
Step S02: ato unit, and make the parameter operation according to the rules of gas compressor, gas compressor radial diffuser, gas turbine guider and power turbine one stage diverter; , the complete machine of motor is made a service test meanwhile, thus the performance parameter of acquisition motor.
In step S02, gas compressor, gas compressor radial diffuser, gas turbine guider and power turbine one stage diverter and the motor that are arranged on motor are simultaneously in running order.Particularly: the stator angle adjustment rule that gas compressor obtains according to above-mentioned steps S011 regulates stator angle; Simultaneously, the throat that gas compressor radial diffuser obtains according to above-mentioned steps S012 draws long-pending value value and regulates its throat's picture long-pending, the first circulation ability value that gas turbine guider obtains according to above-mentioned steps S013 carries out work, and the second circulation ability value that power turbine one stage diverter obtains according to above-mentioned steps S014 carries out work.Now, adopt special-purpose equipment to make a service test to the complete machine of motor, thereby can obtain the performance parameter of each parts of motor.
After completing steps S02, in order further to judge that whether the performance of motor and aerodynamic stability all meet the demands, and can also carry out following steps:
Step S03: the first circulation ability value of the long-pending value of throat's picture of the stator angle adjustment rule of the gas compressor that the performance parameter of the motor obtaining according to above-mentioned steps S02 and above-mentioned steps S011 obtain, the gas compressor radial diffuser that above-mentioned steps S012 obtains, the gas turbine guider that above-mentioned steps S013 obtains and the second circulation ability value of power turbine one stage diverter that above-mentioned steps S014 obtains judge whether the performance of motor and aerodynamic stability all meet the demands.
Adopt the performance adjusting method of motor of the present invention, not only can debug the negotiability of gas turbine guider and power turbine one stage diverter, can also debug the stator angle of gas compressor, long-pending value is drawn by the throat of gas compressor radial diffuser.By the debugging to gas turbine guider, power turbine one stage diverter, gas compressor and gas compressor radial diffuser, can be so that each parts of motor cooperate in harmony most, thus the performance of motor and aerodynamic stability are all met the demands.
The foregoing is only the preferred embodiments of the present invention, be not limited to the present invention, for a person skilled in the art, the present invention can have various modifications and variations.Within the spirit and principles in the present invention all, any modification of doing, be equal to replacement, improvement etc., within all should being included in protection scope of the present invention.
Claims (6)
1. a performance adjusting method for motor, is provided with gas compressor, gas compressor radial diffuser, gas turbine guider and power turbine one stage diverter on described motor, it is characterized in that, described method comprises the steps:
Step S01: obtain respectively following parameter: the second circulation ability value of the first circulation ability value of the throat opening area value of the stator angle adjustment rule of described gas compressor, described gas compressor radial diffuser, described gas turbine guider and described power turbine one stage diverter;
Described step S01 specifically comprises the steps:
Step S011: described gas compressor is carried out to parts experiment, obtain described stator angle adjustment rule;
Step S012: described gas compressor radial diffuser is carried out to parts and overall test, obtain described throat opening area value;
Step S013; Described gas turbine guider is carried out to first-class function experiment, obtain described the first circulation ability value;
Step S014: described power turbine one stage diverter is carried out to the experiment of second function, obtain described the second circulation ability value;
Step S02: start described motor, and make described gas compressor, described gas compressor radial diffuser, described gas turbine guider and described power turbine one stage diverter respectively according to described parameter operation; , described motor is made a service test meanwhile, thereby obtain the performance parameter of described motor;
Step S03: judge according to described performance parameter, described stator angle adjustment rule, described throat opening area value, described the first circulation ability value and described the second circulation ability value whether the performance of described motor and aerodynamic stability all meet the demands.
2. the performance adjusting method of motor according to claim 1, is characterized in that, in described step S02, described gas compressor regulates stator according to described stator angle adjustment rule.
3. the performance adjusting method of motor according to claim 1 and 2, is characterized in that, in described step S02, described gas compressor radial diffuser regulates throat opening area according to described throat opening area value.
4. the performance adjusting method of motor according to claim 3, is characterized in that, in described step S02, described gas turbine guider is according to described the first circulation ability value operation.
5. the performance adjusting method of motor according to claim 4, is characterized in that, in described step S02, described power turbine one stage diverter is according to described the second circulation ability value operation.
6. the performance adjusting method of motor according to claim 1, is characterized in that, described step S011, described step S012, described step S013 and described step S014 carry out simultaneously or carry out at times.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201210045878.8A CN102562319B (en) | 2012-02-27 | 2012-02-27 | Performance adjusting method of engine |
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| CN201210045878.8A CN102562319B (en) | 2012-02-27 | 2012-02-27 | Performance adjusting method of engine |
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| CN102562319A CN102562319A (en) | 2012-07-11 |
| CN102562319B true CN102562319B (en) | 2014-02-12 |
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7020595B1 (en) * | 1999-11-26 | 2006-03-28 | General Electric Company | Methods and apparatus for model based diagnostics |
| CN101206685A (en) * | 2006-12-22 | 2008-06-25 | 联合工艺公司 | Gas turbine engine performance data validation |
| CN101512126A (en) * | 2006-06-30 | 2009-08-19 | 万国引擎知识产权有限责任公司 | Turbocharger performance qualification method and apparatus |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4898491B2 (en) * | 2007-02-23 | 2012-03-14 | 三菱重工業株式会社 | Power turbine test equipment |
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2012
- 2012-02-27 CN CN201210045878.8A patent/CN102562319B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7020595B1 (en) * | 1999-11-26 | 2006-03-28 | General Electric Company | Methods and apparatus for model based diagnostics |
| CN101512126A (en) * | 2006-06-30 | 2009-08-19 | 万国引擎知识产权有限责任公司 | Turbocharger performance qualification method and apparatus |
| CN101206685A (en) * | 2006-12-22 | 2008-06-25 | 联合工艺公司 | Gas turbine engine performance data validation |
Non-Patent Citations (1)
| Title |
|---|
| 刘建军等.一种大涵道比涡扇发动机整机性能试验与调试技术.《第三届民用飞机先进制造技术及装备论坛论文汇编》.2011,第3页第2段，第4页3-7段. * |
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