CN102562319A - Performance adjusting method of engine - Google Patents
Performance adjusting method of engine Download PDFInfo
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- CN102562319A CN102562319A CN2012100458788A CN201210045878A CN102562319A CN 102562319 A CN102562319 A CN 102562319A CN 2012100458788 A CN2012100458788 A CN 2012100458788A CN 201210045878 A CN201210045878 A CN 201210045878A CN 102562319 A CN102562319 A CN 102562319A
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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 adjustment method of motor.
Background technique
At present, the gas compressor of some turboshaft engines does not have 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, through the distribution of appropriate change blow down ratio between turbine, thereby reach the purpose of debugging engine performance.
Know that by above the negotiability of nozzle ring is only adjusted in the debugging of engine performance, and its debugging method is single, can not realize full picture debugging motor.Simultaneously, 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 adjustment method of motor; With solve existing adjustment method means single, can not realize 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 realizing above-mentioned purpose, draw a side according to the present invention, and a kind of performance adjustment 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.This method comprises the steps: step S01: obtain following parameter respectively: first circulation ability value of long-pending value, gas turbine guider and the second negotiability 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 make gas compressor, gas compressor radial diffuser, gas turbine guider and power turbine one stage diverter move according to parameter respectively; Simultaneously, motor is made a service test, thus the performance parameter of acquisition motor.
Further, in step S02, gas compressor is regulated stator according to stator angle adjustment rule.
Further, in step S02, the gas compressor radial diffuser is drawn the long-pending adjusting throat that is worth according to throat and is drawn long-pending.
Further, in step S02, the gas turbine guider is according to the first circulation ability value operation.
Further, in step S02, power turbine one stage diverter moves according to the second negotiability value.
Further, behind step S02, also carry out following steps: step S03: draw long-pending value, the first circulation ability value and the second negotiability value according to performance parameter, stator angle adjustment rule, throat 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 the parts experiment, obtain stator angle adjustment rule; Step S012: the gas compressor radial diffuser is carried out parts and overall test, obtain throat and draw long-pending value; Step S013; The gas turbine guider is carried out first-class function experiment, obtain the first circulation ability value; Step S014: power turbine one stage diverter is carried out the experiment of second stream function, obtain the second negotiability 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 adjustment 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, the long-pending value of throat's picture of gas compressor radial diffuser.Through 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 make the performance of motor and aerodynamic stability all meet the demands.
Except the described purpose of last picture, feature and advantage, the present invention also has other purpose, feature and advantage.Following picture will be done further detailed explanation to the present invention with reference to figure.
Description of drawings
The accompanying drawing that constitutes the application's a part is used to provide further understanding of the present invention, and illustrative examples of the present invention and explanation thereof are used to explain the present invention, do not constitute improper qualification of the present invention.In the accompanying drawings:
Fig. 1 is the schematic flow sheet of performance adjustment 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 adjustment 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 the motor.
Step S01: for gas compressor, gas compressor radial diffuser, gas turbine guider and power turbine one stage diverter that is installed on the motor provides stator angle adjustment rule, throat to draw long-pending value, the first circulation ability value and the second negotiability value respectively.
Preferably; Before gas compressor, gas compressor radial diffuser, gas turbine guider and power turbine one stage diverter are installed on motor, can adopt following step S011 and obtain stator angle adjustment rule, throat respectively to step S014 and draw long-pending value, first the circulate ability value and the second negotiability value.
Step S011: gas compressor is carried out the parts experiment, thereby obtain the stator angle adjustment rule of this gas compressor.
Particularly, earlier gas compressor is regulated rule by different stators on the component test platform and carry out the parts experiment, regulate the influence of rule, thereby confirm the stator angle adjustment rule of this gas compressor component capabilities and stall margin according to different stators.
Step S012: the gas compressor radial diffuser is carried out parts and complete machine experiment, thereby long-pending value is drawn by the throat that obtains this gas compressor radial diffuser.
Particularly, earlier the long-pending different gas compressor radial diffuser of value is drawn by throat and carry out parts and overall test, thereby rationally confirm the long-pending value of throat's picture of gas compressor radial diffuser according to the experimental result of gas compressor radial diffuser.Preferably, in the present embodiment, the throat of gas compressor radial diffuser draws long-pending value and is 2612mm
2, last tolerance is+0.5%, following tolerance is-1.0%.
Step S013: the gas turbine guider is carried out first-class function experiment, thereby obtain the first circulation ability value of this gas turbine guider.
Particularly, earlier the gas turbine guider is carried out first-class function experiment, and confirm the first circulation ability value of gas turbine guider according to the laboratory data of gained.Preferably, in the present embodiment, the first circulation ability value of gas turbine guider does
Its tolerance is ± 0.5%.
Step S014: power turbine one stage diverter is carried out the experiment of second stream function, thereby obtain the second negotiability value of this power turbine one stage diverter.
Particularly, earlier power turbine one stage diverter is carried out the experiment of second stream function, and confirm the second negotiability value of power turbine one stage diverter according to the laboratory data of gained.Preferably, in the present embodiment, the second negotiability value of power turbine one stage diverter does
Its tolerance is ± 0.5%.
The stator angle adjustment rule that obtains through above-mentioned steps S011, step S012, step S013 and step S014, throat draw circulate ability value and the second negotiability value of long-pending value, first and come 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 gas compressor, gas compressor radial diffuser, gas turbine guider and power turbine one stage diverter parameter according to the rules move; Simultaneously, the complete machine of motor is made a service test, thereby obtain the performance parameter of motor.
In step S02, gas compressor, gas compressor radial diffuser, gas turbine guider and power turbine one stage diverter and the motor that are installed on the motor are simultaneously in running order.Particularly: gas compressor is regulated the stator angle according to the stator angle adjustment rule that above-mentioned steps S011 is obtained; Simultaneously; It is long-pending that its throat's picture of long-pending value value adjusting is drawn by the throat that the gas compressor radial diffuser is obtained according to above-mentioned steps S012; The gas turbine guider carries out work according to the first circulation ability value that above-mentioned steps S013 is obtained, and power turbine one stage diverter carries out work according to the second negotiability value that above-mentioned steps S014 is obtained.At this moment, adopt specialized apparatus that the complete machine of motor is made a service test, thereby can obtain the performance parameter of each parts of motor.
Behind 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 throat of the performance parameter of the motor that obtains according to above-mentioned steps S02 and the stator angle adjustment rule of the gas compressor that above-mentioned steps S011 obtains, gas compressor radial diffuser that above-mentioned steps S012 obtains draws the circulate second negotiability value of power turbine one stage diverter that ability value and above-mentioned steps S014 obtain of first of gas turbine guider that long-pending value, above-mentioned steps S013 obtain and judges whether the performance of motor and aerodynamic stability all meet the demands.
Adopt the performance adjustment 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, the long-pending value of throat's picture of gas compressor radial diffuser.Through 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 make the performance of motor and aerodynamic stability all meet the demands.
The above is merely the preferred embodiments of the present invention, is not limited to the present invention, and for a person skilled in the art, the present invention can have various changes and variation.All within spirit of the present invention and principle, any modification of being done, be equal to replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (8)
1. the performance adjustment method of a motor is equipped with gas compressor, gas compressor radial diffuser, gas turbine guider and power turbine one stage diverter on the said motor, it is characterized in that said method comprises the steps:
Step S01: obtain following parameter respectively: first circulation ability value of long-pending value, said gas turbine guider and the second negotiability value of said power turbine one stage diverter are drawn by the throat of the stator angle adjustment rule of said gas compressor, said gas compressor radial diffuser;
Step S02: start said motor, and make said gas compressor, said gas compressor radial diffuser, said gas turbine guider and said power turbine one stage diverter respectively according to said parameter operation; Simultaneously, said motor is made a service test, thereby obtain the performance parameter of said motor.
2. the performance adjustment method of motor according to claim 1 is characterized in that, in said step S02, said gas compressor is regulated stator according to said stator angle adjustment rule.
3. the performance adjustment method of motor according to claim 1 and 2 is characterized in that, in said step S02, said gas compressor radial diffuser is drawn the long-pending adjusting throat that is worth according to said throat and drawn long-pending.
4. the performance adjustment method of motor according to claim 3 is characterized in that, in said step S02, said gas turbine guider is according to the said first circulation ability value operation.
5. the performance adjustment method of motor according to claim 4 is characterized in that, in said step S02, said power turbine one stage diverter moves according to the said second negotiability value.
6. the performance adjustment method of motor according to claim 1 is characterized in that, behind said step S02, also carries out following steps:
Step S03: draw long-pending value, the said first circulation ability value and the said second negotiability value according to said performance parameter, said stator angle adjustment rule, said throat and judge whether the performance of said motor and aerodynamic stability all meet the demands.
7. the performance adjustment method of motor according to claim 1 is characterized in that, said step S01 specifically comprises the steps:
Step S011: said gas compressor is carried out the parts experiment, obtain said stator angle adjustment rule;
Step S012: said gas compressor radial diffuser is carried out parts and overall test, obtain said throat and draw long-pending value;
Step S013; Said gas turbine guider is carried out first-class function experiment, obtain the said first circulation ability value;
Step S014: said power turbine one stage diverter is carried out the experiment of second stream function, obtain the said second negotiability value.
8. the performance adjustment method of motor according to claim 7 is characterized in that, said step S011, said step S012, said step S013 and said step S014 carry out simultaneously or carry out at times.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210045878.8A CN102562319B (en) | 2012-02-27 | 2012-02-27 | Performance adjusting method of engine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210045878.8A CN102562319B (en) | 2012-02-27 | 2012-02-27 | Performance adjusting method of engine |
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| CN102562319A true CN102562319A (en) | 2012-07-11 |
| CN102562319B CN102562319B (en) | 2014-02-12 |
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| CN201210045878.8A Active CN102562319B (en) | 2012-02-27 | 2012-02-27 | Performance adjusting method of engine |
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Citations (4)
| 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 |
| US20080236261A1 (en) * | 2007-02-23 | 2008-10-02 | Mitsubishi Heavy Industries, Ltd. | Power turbine test apparatus |
| 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 |
-
2012
- 2012-02-27 CN CN201210045878.8A patent/CN102562319B/en active Active
Patent Citations (4)
| 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 |
| US20080236261A1 (en) * | 2007-02-23 | 2008-10-02 | Mitsubishi Heavy Industries, Ltd. | Power turbine test apparatus |
Non-Patent Citations (1)
| Title |
|---|
| 刘建军等: "《第三届民用飞机先进制造技术及装备论坛论文汇编》", 10 March 2011 * |
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| CN102562319B (en) | 2014-02-12 |
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