CN103670718A - Electric starting control method and device for gas turbine - Google Patents
Electric starting control method and device for gas turbine Download PDFInfo
- Publication number
- CN103670718A CN103670718A CN201310682269.8A CN201310682269A CN103670718A CN 103670718 A CN103670718 A CN 103670718A CN 201310682269 A CN201310682269 A CN 201310682269A CN 103670718 A CN103670718 A CN 103670718A
- Authority
- CN
- China
- Prior art keywords
- starting
- gas turbine
- power supply
- actuating motor
- branch road
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Landscapes
- Control Of Eletrric Generators (AREA)
- Control Of Turbines (AREA)
Abstract
The invention discloses an electric starting control method and device for a gas turbine. The method comprises the following steps: during the primary starting period, a starting motor of the gas turbine is subjected to reduced voltage starting to drive a high pressure turbine rotor of the gas turbine to rotate; during the secondary starting period, an electric generator of the gas turbine is subjected to reduced voltage starting to drive a low pressure turbine rotor to rotate while the starting motor drives the high pressure turbine rotor to rotate; during the third-stage starting period, a power supply of the electric generator is cut off, and the power supply of the electric generator is connected in series with a power supply of the starting motor; during the fourth-stage starting period, a first current-limiting resistor is connected in series onto a power supply circuit branch of a magnet exciting coil of the starting motor, so as to reduce the magnetic flux of the magnet exciting coil and increase the output torque of the starting motor. According to the invention, a starting system of the gas turbine has sufficient power and good torque characteristics, can quickly start the gas turbine to an idling state, can be operated repeatedly within a short period, and is high in reliability.
Description
Technical field
The present invention relates to gas turbine control field, especially, relate to a kind of electric starting controlling method and device of gas turbine.
Background technique
Ground gas turbine can be used as armored vehicle and Small Vessel power, its distributed energy resource system forming as core engine has broad application prospects in fields such as electric power, oil, chemical industry, metallurgy, boats and ships, railway locomotive power, can quick starting and loading without ABAP Adapter in the situation that, be suitable as emergency supply and bear the peak load in electrical network, can ensure quickly electric power netting safe running, reduce casualty loss.
But the feature of gas turbine starting is that idling speed is high, and the starting time is short, requires actuating motor power large, and the oil-gas ratio of starting process will rationally be adjusted, and factors of these impact startings want appropriate coupling, and guarantee gas turbine starts smoothly.In prior art, Study On Start-up Process For Gas Turbines is that a rotor accelerates the process of rotating, and gas turbine its rotor when starting starts remains static.In minimum speed, if do not have external force to drive gas turbine rotor to rotate, the power that only relies on turbine to send, cannot make gas turbine rotor accelerate to rotate.The external force of gas turbine starting is supplied with by actuating motor, when starting, must gas turbine rotor be accelerated to by actuating motor to the minimum speed that can carry out oil spout igniting over gas turbine.Because the idling speed of the starting of gas turbine is high, the quick starting of actuating motor easily causes the output torque of rotor suddenly to increase, and cause that actuating motor, gas turbine and other starting annexes damage, and starting process does not easily steadily cause starting failure.
Summary of the invention
The object of the invention is to provide a kind of electric starting controlling method and device of gas turbine, to solve the actuating motor causing that suddenly increases because of output torque in existing Study On Start-up Process For Gas Turbines, gas turbine and other starting annexes damage and the technical problem of the starting failure that starting process does not steadily cause.
For achieving the above object, the technical solution used in the present invention is as follows:
According to an aspect of the present invention, provide a kind of electric starting controlling method of gas turbine, comprise the following steps:
First order starting period, the actuating motor of gas turbine drives the High Pressure Turbine Rotor rotation of gas turbine through reduced voltage starting;
Second level starting period, when actuating motor drives High Pressure Turbine Rotor rotation, the generator of gas turbine drives the Low Pressure Turbine Rotor rotation of gas turbine through reduced voltage starting;
Third level starting period, cuts off the power supply of generator, and the power supply of generator is connected serially on the power supply of actuating motor, to increase armature voltage and the field current of actuating motor;
Fourth stage starting period, first current-limiting resistance of connecting on the field coil power supply branch road of actuating motor, to reduce the magnetic flux of field coil, improves the output torque of actuating motor, drives the rotating speed of High Pressure Turbine Rotor to be increased to idling mode.
Further, in first order starting period, on the power supply branch road of the armature terminal of actuating motor, be in series with the second current-limiting resistance.
Further, in the starting period of the second level, by the second current-limiting resistance short circuit on the power supply branch road of the armature terminal of actuating motor.
Further, in the starting period of the second level, on the power supply branch road of the armature terminal of generator, be first in series with the 3rd current-limiting resistance, with reduced voltage starting generator, drive Low Pressure Turbine Rotor rotation, and after the scheduled time by the 3rd current-limiting resistance short circuit on the power supply branch road of the armature terminal of generator.
Further, first order starting period, second level starting period, third level starting period and fourth stage starting period send time-oriented sequential control instruction by the starter box of gas turbine and realize.
Further, when the rotating speed that starter box detects High Pressure Turbine Rotor through speed probe reaches set point fire rotating speed, the igniting of starter box drive point firearm.
According to a further aspect in the invention, a kind of electric starting control gear of gas turbine is also provided, comprise actuating motor, generator, the output shaft of actuating motor connects High Pressure Turbine Rotor, the rotating shaft of generator connects Low Pressure Turbine Rotor, actuating motor and generator are all connected with for controlling the starter controller of the working state of actuating motor and generator, and the working state of actuating motor and generator is controlled in the sequential instruction that the starter box of starter controller reception gas turbine sends.
Further, starter controller comprises the first power supply and second source, the first power supply be connected in parallel the armature terminal of actuating motor and the field coil of actuating motor, the power supply branch road of the armature terminal of actuating motor comprises and is provided with the first branch road of the first switch element and the second branch road that series connection is provided with second switch unit and the second current-limiting resistance, the first branch road and the second branch circuit parallel connection; The power supply branch road of the field coil of actuating motor comprises the 3rd branch road that is provided with the 3rd switch element and the 4th branch road that is provided with the first current-limiting resistance, the 3rd branch road and the 4th branch circuit parallel connection;
Second source be connected in parallel the armature terminal of generator and the field coil of generator, the power supply branch road of the armature terminal of generator comprises and is provided with the 5th branch road of the 4th switch element and the 6th branch road that series connection is provided with the 5th switch element and the 3rd current-limiting resistance, the 5th branch road and the 6th branch circuit parallel connection; The power supply branch road of the field coil of generator is provided with the 6th switch element;
Between the first power supply and second source, be provided with the 7th switch element for connect the first power supply and second source;
The first switch element, second switch unit, the 3rd switch element, the 4th switch element, the 5th switch element, the 6th switch element and the 7th switch element are controlled by the sequential instruction of starter box all.
Further, starter box is connected with for regulating the control panel of starter box time-oriented sequential control instruction.
Further, control panel is touch control screen.
The present invention has following beneficial effect:
Electric starting controlling method and the device of gas turbine of the present invention, by adopting the scheme of step starting improve step by step actuating motor output torque and increase output power, wherein, actuating motor drives High Pressure Turbine Rotor to rotate, generator drives Low Pressure Turbine Rotor to rotate as auxiliary actuating motor, make the starting process of gas turbine steady, starting success rate significantly promotes, and by improving step by step output power and output torque, protected preferably actuating motor, gas turbine and other starting annexes, make the starting system of gas turbine there is enough power and good torque characteristics, can reach idling mode by quick starting gas turbine, and at short notice can repeated work, reliability is high.
Except object described above, feature and advantage, the present invention also has other object, feature and advantage.Below with reference to figure, 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 electric starting controlling method steps flow chart schematic diagram of the gas turbine of the preferred embodiment of the present invention;
Fig. 2 is the electrical block diagram of first order starting in the electric starting controlling method of gas turbine of the preferred embodiment of the present invention;
Fig. 3 is the electrical block diagram of second level starting in the electric starting controlling method of gas turbine of the preferred embodiment of the present invention;
Fig. 4 is the electrical block diagram of third level starting and fourth stage starting in the electric starting controlling method of gas turbine of the preferred embodiment of the present invention;
Fig. 5 is the structural representation of electric starting control gear of the gas turbine of the preferred embodiment of the present invention; And
Fig. 6 be actuating motor in the electric starting process of gas turbine of the preferred embodiment of the present invention starting current, rotating speed and time be related to schematic diagram.
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.
The embodiment of the present invention is in the starting process of gas turbine, adopt actuating motor to drive High Pressure Turbine Rotor to rotate, adopt generator to drive Low Pressure Turbine Rotor to rotate, and the mode that adopts step starting improves output power and the output torque of actuating motor, the starting process of gas turbine is divided into level Four starts, with the rotating speed of booster gas turbine progressively, and quick starting gas turbine reaches idling mode.
With reference to Fig. 1, the preferred embodiments of the present invention provide a kind of electric starting controlling method of gas turbine, comprise the following steps:
Step S10, first order starting period, the actuating motor of gas turbine drives the High Pressure Turbine Rotor rotation of gas turbine through reduced voltage starting;
Step S20, second level starting period, when actuating motor drives High Pressure Turbine Rotor rotation, the generator of gas turbine drives the Low Pressure Turbine Rotor rotation of gas turbine through reduced voltage starting;
Step S30, third level starting period, cuts off the power supply of generator, and the power supply of generator is connected serially on the power supply of actuating motor, to increase armature voltage and the field current of actuating motor;
Step S40, fourth stage starting period, first current-limiting resistance of connecting on the field coil power supply branch road of actuating motor, to reduce the magnetic flux of field coil, improves the output torque of actuating motor, drives the rotating speed of High Pressure Turbine Rotor to be increased to idling mode.
In the electric starting controlling method embodiment of gas turbine of the present invention, by adopting the scheme of step starting improve step by step actuating motor output torque and increase output power, wherein, actuating motor drives High Pressure Turbine Rotor to rotate, generator drives Low Pressure Turbine Rotor to rotate as auxiliary actuating motor, make the starting process of gas turbine steady, starting success rate significantly promotes, and by improving step by step output power and output torque, protected preferably actuating motor, gas turbine and other starting annexes, make the starting system of gas turbine there is enough power and good torque characteristics, can reach idling mode by quick starting gas turbine, and at short notice can repeated work, reliability is high.
In the present embodiment, with reference to Fig. 2, in this first order starting period, on the power supply branch road of the armature terminal of actuating motor, be in series with the second current-limiting resistance R1.In the present embodiment, the starter box of gas turbine sends sequential instruction control contactor K2 and connects, and by the power supply branch road of the armature terminal of the second current-limiting resistance R1 access actuating motor, makes to be loaded on the armature terminal of actuating motor after power supply 1 step-down; Starter box sends sequential instruction control contactor K3 and connects, and makes power supply 1 connect field coil and applies field current.Like this, actuating motor drives High Pressure Turbine Rotor slowly to start rotation, to eliminate the gap between actuating motor and High Pressure Turbine Rotor gear.First order starting period is the reduced voltage starting stage.
With reference to Fig. 3, in the starting period of the second level, first by the second current-limiting resistance R1 short circuit on the power supply branch road of the armature terminal of actuating motor, in the present embodiment, starter box sends sequential instruction control contactor K1 and connects the second current-limiting resistance R1 short circuit, improve and be added in the starting voltage on actuating motor, increase starting current, increase the spin intensity of actuating motor.Simultaneously, starter box sends sequential instruction control contactor K5 and K6 connects, power supply 2 adds little value armature voltage through the 3rd current-limiting resistance R3 to generator, power supply 2 applies field current through contactor K6 to field coil, make generator slow start, to eliminate, connect the gear backlash of alternator shaft and Low Pressure Turbine Rotor and drive Low Pressure Turbine Rotor rotation, after the scheduled time, starter box sends sequential instruction control contactor K4 and connects starting resistance short circuit, generator changes the armature supply for large value, to increase the spin intensity of Low Pressure Turbine Rotor.Second level starting period is starting period in parallel, at this moment power supply 1 and power supply 2 parallel operations and drive respectively actuating motor and generator rotates.After second level starting period finishes, starter box is cancelled the sequential instruction to contactor K4, K5, K6, and generator quits work.
With reference to Fig. 4, in third level starting period, generator no longer participates in the starting of gas turbine.For further booster gas turbine rotor rotation, starter box sends sequential instruction control contactor K7 and connects, by two groups of starting power supplies, be power supply 1 and power supply 2, after series connection, be added on actuating motor to improve actuating motor armature voltage, increase field current, continue to increase the rotating speed of actuating motor.The starting of boosting is also named in third level starting.
In fourth stage starting period, starter box cancellation is added in the sequential instruction on contactor K3, the first current-limiting resistance R2 connects in the field circuit of actuating motor, the field current of supplying with to actuating motor diminishes, because now power supply 1 and power supply 2 are still in series operation state, so the armature supply of actuating motor, by corresponding increase, can improve the moment of torsion of actuating motor, further improves the rotating speed of High Pressure Turbine Rotor.Because at this moment actuating motor rotating speed is higher, in Cen Φ, Cen value is very large, and magnetic flux reduces after △ Φ, the increasing amount that causes (U-Cen Φ) in Tm=Cm Φ (U-Cen Φ)/R is greater than to the decrease of Φ, so starting torque further increases, this is fourth stage starting period.
In the present embodiment, first order starting period, second level starting period, third level starting period and fourth stage starting period send time-oriented sequential control instruction by the starter box of gas turbine and realize.The present invention adopts the principle of controlling based on the time to multistage starting, wherein, and during the operation of first order starting period, second level starting period, third level starting period and fourth stage starting period
Between the sequential instruction of sending by starter box control.Preferably, when the rotating speed that starter box detects High Pressure Turbine Rotor through speed probe reaches set point fire rotating speed, the igniting of starter box drive point firearm, successfully to start gas turbine.Fig. 6 be actuating motor in the electric starting process of gas turbine in the present embodiment starting current, rotating speed and time be related to schematic diagram, wherein, 1 grade of corresponding first order starting period, 2 grades of corresponding second level starting periods, 3 grades of corresponding third level starting periods, 4 grades of corresponding fourth stage starting periods, t represents the time, n represents the rotating speed of actuating motor, and I represents the starting current of actuating motor.By test run, test, the method for starting-controlling of the embodiment of the present invention, can effectively improve the starting performance of gas turbine, and starting process is steady, and starting success rate has a distinct increment.
According to a further aspect in the invention, also provide a kind of electric starting control gear of gas turbine, comprised actuating motor, generator, the output shaft of actuating motor connects High Pressure Turbine Rotor, and the rotating shaft of generator connects Low Pressure Turbine Rotor.With reference to Fig. 5, actuating motor and generator are all connected with for controlling the starter controller of the working state of actuating motor and generator, and the working state of actuating motor and generator is controlled in the sequential instruction that the starter box of starter controller reception gas turbine sends.
In the present embodiment, with reference to Fig. 2 to Fig. 4, starter controller comprises the first power supply and second source, i.e. power supply 1 and power supply 2.Wherein, power supply 1 be connected in parallel the armature terminal of actuating motor and the field coil of actuating motor, the power supply branch road of the armature terminal of actuating motor comprises and is provided with the first branch road of the first switch element (the present embodiment is contactor K1) and the second branch road that series connection is provided with second switch unit (the present embodiment is contactor K2) and the second current-limiting resistance R1, the first branch road and the second branch circuit parallel connection; The power supply branch road of the field coil of actuating motor comprises the 3rd branch road that is provided with the 3rd switch element (the present embodiment is contactor K3) and the 4th branch road that is provided with the first current-limiting resistance R2, the 3rd branch road and the 4th branch circuit parallel connection; Power supply 2 be connected in parallel the armature terminal of generator and the field coil of generator, the power supply branch road of the armature terminal of generator comprises and is provided with the 5th branch road of the 4th switch element (the present embodiment is contactor K4) and the 6th branch road that series connection is provided with the 5th switch element (the present embodiment is contactor K5) and the 3rd current-limiting resistance R3, the 5th branch road and the 6th branch circuit parallel connection; The power supply branch road of the field coil of generator is provided with the 6th switch element (the present embodiment is contactor K6); Between power supply 1 and power supply 2, be provided with the 7th switch element (the present embodiment is contactor K7) for series-connection power supplies 1 and power supply 2; Contactor K1-K7 is controlled by the sequential instruction of starter box all.Preferably, in other embodiments, switch element also can be selected relay.In the present embodiment, the working procedure of starter controller, as described in embodiment of the method, also comprises first order starting period, second level starting period, third level starting period and fourth stage starting period.
Preferably, starter box is connected with for regulating the control panel of starter box time-oriented sequential control instruction, and this control panel is touch control screen.Operator can regulate the sequential instruction that starter box storage is set to control the working time of first order starting period, second level starting period, third level starting period and fourth stage starting period through touch control screen.
Adopt the starting system of gas turbine of the starting arrangement of the embodiment of the present invention to there is enough power and good torque characteristics, can reach idling mode by quick starting gas turbine, and at short notice can repeated work, reliability is high.
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 (10)
1. an electric starting controlling method for gas turbine, is characterized in that, comprises the following steps:
First order starting period, the actuating motor of described gas turbine drives the High Pressure Turbine Rotor rotation of described gas turbine through reduced voltage starting;
Second level starting period, when described actuating motor drives described High Pressure Turbine Rotor rotation, the generator of described gas turbine drives the Low Pressure Turbine Rotor rotation of described gas turbine through reduced voltage starting;
Third level starting period, cuts off the power supply of described generator, and the power supply of described generator is connected serially on the power supply of described actuating motor, to increase armature voltage and the field current of described actuating motor;
Fourth stage starting period, first current-limiting resistance of connecting on the field coil power supply branch road of described actuating motor, to reduce the magnetic flux of described field coil, improve the output torque of described actuating motor, drive the rotating speed of described High Pressure Turbine Rotor to be increased to idling mode.
2. the electric starting controlling method of gas turbine according to claim 1, is characterized in that,
In described first order starting period, on the power supply branch road of the armature terminal of described actuating motor, be in series with the second current-limiting resistance.
3. the electric starting controlling method of gas turbine according to claim 2, is characterized in that,
In the starting period of the described second level, by described the second current-limiting resistance short circuit on the power supply branch road of the armature terminal of described actuating motor.
4. the electric starting controlling method of gas turbine according to claim 3, is characterized in that,
In the starting period of the described second level, on the power supply branch road of the armature terminal of described generator, be first in series with the 3rd current-limiting resistance, with generator described in reduced voltage starting, drive the rotation of described Low Pressure Turbine Rotor, and after the scheduled time by described the 3rd current-limiting resistance short circuit on the power supply branch road of the armature terminal of described generator.
5. according to the electric starting controlling method of the gas turbine described in claim 1 to 4 any one, it is characterized in that,
Described first order starting period, second level starting period, third level starting period and fourth stage starting period send time-oriented sequential control instruction by the starter box of described gas turbine and realize.
6. the electric starting controlling method of gas turbine according to claim 5, is characterized in that,
When the rotating speed that described starter box detects described High Pressure Turbine Rotor through speed probe reaches set point fire rotating speed, described starter box drive point firearm igniting.
7. an electric starting control gear for gas turbine, comprises actuating motor, generator, and the output shaft of described actuating motor connects High Pressure Turbine Rotor, and the rotating shaft of described generator connects Low Pressure Turbine Rotor, it is characterized in that,
Described actuating motor and described generator are all connected with for controlling the starter controller of the working state of described actuating motor and described generator, and described starter controller receives the working state that described actuating motor and described generator are controlled in sequential instruction that the starter box of described gas turbine sends.
8. the electric starting control gear of gas turbine according to claim 7, is characterized in that,
Described starter controller comprises the first power supply and second source, described the first power supply be connected in parallel the armature terminal of described actuating motor and the field coil of described actuating motor, the power supply branch road of the armature terminal of described actuating motor comprises and is provided with the first branch road of the first switch element and the second branch road that series connection is provided with second switch unit and the second current-limiting resistance, described the first branch road and described the second branch circuit parallel connection; The power supply branch road of the field coil of described actuating motor comprises the 3rd branch road that is provided with the 3rd switch element and the 4th branch road that is provided with the first current-limiting resistance, described the 3rd branch road and described the 4th branch circuit parallel connection;
Described second source be connected in parallel the armature terminal of described generator and the field coil of described generator, the power supply branch road of the armature terminal of described generator comprises and is provided with the 5th branch road of the 4th switch element and the 6th branch road that series connection is provided with the 5th switch element and the 3rd current-limiting resistance, described the 5th branch road and described the 6th branch circuit parallel connection; The power supply branch road of the field coil of described generator is provided with the 6th switch element;
Between described the first power supply and described second source, be provided with the 7th switch element for connect described the first power supply and described second source;
Described the first switch element, second switch unit, the 3rd switch element, the 4th switch element, the 5th switch element, the 6th switch element and the 7th switch element are controlled by the sequential instruction of described starter box all.
9. the electric starting control gear of gas turbine according to claim 7, is characterized in that,
Described starter box is connected with for regulating the control panel of described starter box time-oriented sequential control instruction.
10. the electric starting control gear of gas turbine according to claim 9, is characterized in that,
Described control panel is touch control screen.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310682269.8A CN103670718B (en) | 2013-12-12 | 2013-12-12 | The electric starting controlling method of gas turbine and device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310682269.8A CN103670718B (en) | 2013-12-12 | 2013-12-12 | The electric starting controlling method of gas turbine and device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103670718A true CN103670718A (en) | 2014-03-26 |
| CN103670718B CN103670718B (en) | 2015-10-21 |
Family
ID=50309343
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310682269.8A Active CN103670718B (en) | 2013-12-12 | 2013-12-12 | The electric starting controlling method of gas turbine and device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103670718B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107515340A (en) * | 2017-09-04 | 2017-12-26 | 中国航发南方工业有限公司 | The detection means and detection method of starter box |
| CN112130073A (en) * | 2020-09-30 | 2020-12-25 | 北京动力机械研究所 | High-speed generator starting power generation performance test system for closed cycle power generation system |
| CN112763226A (en) * | 2020-12-24 | 2021-05-07 | 襄阳航顺航空科技有限公司 | Detection system and method for engine gas turbine starter |
| CN113323732A (en) * | 2021-06-01 | 2021-08-31 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for measuring turbine work in starting process of aeroengine with running |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB710857A (en) * | 1950-11-01 | 1954-06-23 | Rolls Royce | Improvements in or relating to gas-turbine engines having means to facilitate starting |
| CN1653262A (en) * | 2002-05-10 | 2005-08-10 | 西门子西屋电力公司 | Methods for starting a combustion turbine and combustion turbine generator configured to implement same methods |
| CN101153559A (en) * | 2006-09-27 | 2008-04-02 | 通用电气公司 | Gas turbine engine assembly and method of assembling same |
| US20110101693A1 (en) * | 2009-11-04 | 2011-05-05 | Kawasaki Jukogyo Kabushiki Kaisha | Aircraft starter generator |
| CN202811082U (en) * | 2012-08-09 | 2013-03-20 | 中国南方航空工业(集团)有限公司 | Starting control device of engine |
-
2013
- 2013-12-12 CN CN201310682269.8A patent/CN103670718B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB710857A (en) * | 1950-11-01 | 1954-06-23 | Rolls Royce | Improvements in or relating to gas-turbine engines having means to facilitate starting |
| CN1653262A (en) * | 2002-05-10 | 2005-08-10 | 西门子西屋电力公司 | Methods for starting a combustion turbine and combustion turbine generator configured to implement same methods |
| CN101153559A (en) * | 2006-09-27 | 2008-04-02 | 通用电气公司 | Gas turbine engine assembly and method of assembling same |
| US20110101693A1 (en) * | 2009-11-04 | 2011-05-05 | Kawasaki Jukogyo Kabushiki Kaisha | Aircraft starter generator |
| CN202811082U (en) * | 2012-08-09 | 2013-03-20 | 中国南方航空工业(集团)有限公司 | Starting control device of engine |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107515340A (en) * | 2017-09-04 | 2017-12-26 | 中国航发南方工业有限公司 | The detection means and detection method of starter box |
| CN107515340B (en) * | 2017-09-04 | 2020-01-10 | 中国航发南方工业有限公司 | Detection device and detection method for starting box |
| CN112130073A (en) * | 2020-09-30 | 2020-12-25 | 北京动力机械研究所 | High-speed generator starting power generation performance test system for closed cycle power generation system |
| CN112130073B (en) * | 2020-09-30 | 2023-08-15 | 北京动力机械研究所 | High-speed generator starting power generation performance test system for closed cycle power generation system |
| CN112763226A (en) * | 2020-12-24 | 2021-05-07 | 襄阳航顺航空科技有限公司 | Detection system and method for engine gas turbine starter |
| CN113323732A (en) * | 2021-06-01 | 2021-08-31 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for measuring turbine work in starting process of aeroengine with running |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103670718B (en) | 2015-10-21 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8427116B2 (en) | Starting/generating system with multi-functional circuit breaker | |
| DE102009005242B4 (en) | Electric motor for fuel pump with improved shutdown characteristics | |
| CN102474214B (en) | Method of controlling a variable speed constant frequency generator | |
| CN103670718B (en) | The electric starting controlling method of gas turbine and device | |
| US20190017443A1 (en) | Rapidly available electric power from a turbine-generator system having an auxiliary power source | |
| CN202931247U (en) | Automobile AC generator voltage regulator | |
| US9573539B2 (en) | Electric system architecture for more-electric engine accessories | |
| US20150311843A1 (en) | Method of loadshedding for a variable speed, constant frequency generator | |
| CN103036485A (en) | Permanent magnet direct current motor start impact current suppression device and suppression method thereof | |
| CN104763546A (en) | High and low voltage combined start control method for vehicle | |
| CN110936849B (en) | High-voltage power supply system and method of hybrid power system and vehicle | |
| DE102015203757A1 (en) | Control device for a rotating electrical machine and motor control system, which is equipped with a rotating electrical machine to be controlled by the control device | |
| CN104579063A (en) | Delay control circuit for generator set and control method | |
| US9628008B1 (en) | Method and generator control unit for configuring an output from a generator | |
| US9909502B2 (en) | Battery current regulation | |
| CN203580673U (en) | Novel hydraulic fixed-frequency vehicle-mounted frequency conversion alternating-current electricity self-generating system | |
| CN104989534A (en) | Method for starting vehicle engine through combination of high pressure and low pressure | |
| EP2611994B1 (en) | Method for stopping a turboset | |
| CN109274300B (en) | Starting and excitation system and method for gas turbine generator set | |
| RU2319277C1 (en) | Dc electric energy autonomous supply | |
| EP0406340A1 (en) | Battery-charging device. | |
| CN204553043U (en) | Bielectron switch starting machine | |
| CN114039453B (en) | Gas turbine generator set started by alternating current exciter of brushless generator and starting method thereof | |
| RU2422977C1 (en) | Method of ac motor soft start | |
| JP2007189772A (en) | Drive control system of motor generator for vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 412002 Dong Jiaduan, Zhuzhou, Hunan Patentee after: China Hangfa South Industrial Co. Ltd. Address before: 412002 Dong Jiaduan, Zhuzhou, Hunan Patentee before: China Southern Airlines Industry (Group) Co., Ltd. |
|
| CP01 | Change in the name or title of a patent holder |