CN101737170B - Aeroengine generating system - Google Patents

Aeroengine generating system Download PDF

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Publication number
CN101737170B
CN101737170B CN2009102635304A CN200910263530A CN101737170B CN 101737170 B CN101737170 B CN 101737170B CN 2009102635304 A CN2009102635304 A CN 2009102635304A CN 200910263530 A CN200910263530 A CN 200910263530A CN 101737170 B CN101737170 B CN 101737170B
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aeroengine
controller
control
generation
bus
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CN101737170A (en
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郑宏
徐红兵
李凯
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University of Electronic Science and Technology of China
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University of Electronic Science and Technology of China
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Abstract

The invention discloses an aeroengine generating system. An aeroengine generating set comprises an electric motor/exciter which is coaxially connected with a generator and an aircraft in the aeroengine power generating set; an aeroengine generating control system comprises a main controller, a starting excitation controller and a fuel adjusting controller which form a distributed bus control network in a mode of a bus; each controller is an independent node on the bus; and the main controller is a main node, and the fuel adjusting controller and the starting excitation controller are slave nodes. Each control part is designed in a modularizing mode and controlled in a distributed mode, so that the individual and general safe, economic, stable and reliable operation is realized in the aeroengine generating system, and the aeroengine generating set has the advantages of fast starting, smooth transition, high control precision, simple operation, strong adaptability and high reliability. Compared with a centralized control system in the prior art, each controller has the control function, and a universal standard device can be adopted, so that the aeroengine generating system is easy to expand and the maintenance cost is greatly reduced.

Description

A kind of aeroengine generation system
Technical field
The present invention relates to a kind of power generation system, specifically, relate to a kind of with the aeroengine generation system of aeroengine as generator drive power.
Background technique
The aeroengine generation system is with the electricity generating device of aeroengine (abbreviation plane) through a kind of efficient, the energy-saving and environmental protection that are applicable to terrestrial power generation after a series of transformations, comprise aeroengine generation unit and aeroengine generation control system, wherein, it is object with the aeroengine generation unit that the aeroengine generation control system is one, relate to all multidisciplinary complex control systems such as control, computer, communication, power, electric power, being one of key technology of aeroengine generation, also is its important constituent element.
Hydraulic mechanical type control, analog electronic control, digital control stage have been experienced in the development of aeroengine generation control technique.Functions such as early stage plane control system adopts the hydraulic mechanical type speed regulator, and is aided with pneumatic temperature control, and the starting fluid restriction is stable and manual, program control; All the other protections such as hypervelocity, overtemperature all have independent device to realize.
The continuous development of Digital Electronic Technique, the control of aeroengine generation enter the digital and electronic control epoch.At present, the digital and electronic control system develops to standardization, seriation and modular direction, can realize whole controls and management to aeroengine generation unit and oil system etc.
There are many shortcomings in the Centralized Control System of aeroengine generation employing at present, and three major defects are wherein arranged: one, reliability reduces.Full powers limit digital electronic controllers (FADEC) in the control system are except will realizing major functions such as all signals collecting, processing, control computing, control signal output; also to realize condition monitoring, faut detection, safety protection function; this makes that the software among the FADEC is huge and complicated; the computer load is heavy; cause real-time to reduce; in a single day computer breaks down, and whole system all can not be worked.Two, be unfavorable for the expansion of control system.Three, be unfavorable for safeguarding.Therefore for Centralized Control System, even adopt more advanced microprocessor, more jumbo program storage, its performance can not be greatly improved yet.
Summary of the invention
The objective of the invention is to overcome the deficiencies in the prior art, the aeroengine generation system that provide a kind of reliability height, easily expands and safeguard.
To achieve the above object of the invention, aeroengine generation of the present invention system comprises aeroengine generation unit and aeroengine generation control system, it is characterized in that:
The aeroengine generation unit also comprises an electronic/exciter, with coaxial connection of generator, plane in the aeroengine generation unit; The aeroengine generation control system comprises master controller, starting excitation controller and fuel adjusting controller, forms a distributed bus control network with the form of bus, and each controller all is an isolated node on the bus; Master controller is a host node, and fuel adjusting controller, starting excitation controller are from node;
(1), during the aeroengine generation startup of unit, master controller sends starting command to the starting excitation controller by bus, the electronic/exciter of starting excitation controller control moves as motor, drives the aeroengine generation startup of unit separately; (2), master controller is gathered the plane rotating speed, when rotating speed is raised to fire speed, master controller sends valve opening according to predefined starting curve by bus and instructs to the fuel adjusting controller, the fuel control valve of fuel adjusting controller control aeroengine generation unit is sent into fuel to plane according to predefined starting curve, the igniting of main controller controls plane, plane is according to predefined starting curve raising speed, and electronic/exciter and plane do work jointly and drive aeroengine generation unit raising speed; (3), master controller is gathered the plane rotating speed, when rotating speed is raised to when withdrawing from electronic working speed, master controller sends electronic exiting command to the starting excitation controller by bus, electronic/the exciter of starting excitation controller control withdraws from electronic work, makes plane drive aeroengine generation unit raising speed separately by fuel adjusting controller control fuel control valve fully; (4), master controller is gathered the plane rotating speed, when rotating speed is raised to balancing speed, master controller sends the excitation order to the starting excitation controller by bus, electronic/the exciter of starting excitation controller control moves as exciter, the output field current is to the exciting winding of generator, make generator boost to voltage rating, the aeroengine generation unit carries out normal generator operation; When (5), the aeroengine generation unit normally moves, master controller is gathered the Operational Limits of aeroengine generation unit, calculate fuel flow rate according to control algorithm, sending valve opening by bus then instructs to the fuel adjusting controller, the fuel of fuel adjusting controller control fuel control valve output corresponding discharge makes the operation of aeroengine generation set steady.
The object of the present invention is achieved like this:
Aeroengine generation of the present invention system comprises aeroengine generation unit and plane launch control system, and wherein, the aeroengine generation control system adopts the distributed bus control technique, with the core of master controller as control system, constitutes distributed bus control network.Master controller is a distributed bus control network host node, and fuel adjusting controller, starting excitation controller are from node, communicate with bus form each other.Each control section is modular design like this, distributed control, realize individual and overall safe, economical, reliable and stable operation in the aeroengine generation system, make that the aeroengine generation startup of unit is fast, transition is steady, control accuracy is high, simple to operate, adaptive capacity by force, good reliability.
Centralized Control System with respect to prior art, the distributed bus control system (DCS) that the present invention adopts makes the aeroengine generation system improve a lot from aspects such as controlling method, control structure, control survey executive components, and its systematic function, reliability etc. also have very big change.The advantage of DCS comprises minimizing control system weight, especially cable weight; Owing to adopt general module and standard interface, reduced lead time and design cost; Sensor and actuator are compatible to strengthen; Improve the control system reliability greatly; Because each controller all has the control function, can adopt universal standard device, thereby easily expansion greatly reduces maintenance cost.
Description of drawings
Fig. 1 is the structured flowchart of a kind of embodiment of aeroengine generation of the present invention system;
Fig. 2 is an invention aeroengine generation shown in Figure 1 system control flow chart.
Embodiment
For understanding the present invention better, the present invention is made a more detailed description below in conjunction with the drawings and specific embodiments.In the following description, when perhaps the detailed description of existing prior art can desalinate subject content of the present invention, these were described in here and will be left in the basket.
Fig. 1 is the structured flowchart of a kind of embodiment of aeroengine generation of the present invention system
In the present embodiment, as shown in Figure 1, the aeroengine generation system comprises aeroengine generation unit I and two parts of aeroengine generation control system II.
Aeroengine generation unit I comprises plane 101, generator 102, electronic/exciter 103 and fuel control valve 104, electronic/exciter 103 and generator 102,101 coaxial connections of plane.Plane 101 formations mainly contain gas compressor C, firing chamber B and power turbine T.The structure and the working principle of plane 101 belong to prior art, do not repeat them here.Also have a speed reducer between generator 102 and plane 101, the tachogenerator 105 on speed reducer is as a rotating speed Check point of 201 pairs of planes 101 of master controller.The B ingress, firing chamber of plane 101 links to each other with fuel control valve 104 by fuel channel 106, required fuel quantity during by the unit I of system starting of fuel control valve 104 control aeroengine generation and operation.
Aeroengine generation control system II comprises master controller 201, starting excitation controller 202 and fuel adjusting controller 203, forms a distributed bus control network with the form of bus, and each controller all is an isolated node on the bus 204.In the present embodiment, as shown in Figure 1, aeroengine generation control system II also comprises microcomputer protecting device 205 and monitoring management computer 206.Adopt the master-slave communication mode on the bus, master controller 201 is a host node, and starting excitation controller 202, fuel adjusting controller 203, microcomputer protecting device 205 are from node.Meanwhile; monitoring management computer 206 is carried out the real time data exchange by bus 204 and starting excitation controller 202, fuel adjusting controller 203, microcomputer protecting device 205; monitoring management computer 206 is reflected to main interface with the various status parameters of aeroengine generation unit I operation, is convenient to the real-time monitoring of operator to the aeroengine generation system.
Respectively the each several part among the aeroengine generation control system II is illustrated in more detail below.
1, master controller
Master controller 201 is the core controller of aeroengine generation control system II, is the host node on the distributed bus control network, and main controlling object is a plane 101.Master controller 201 links to each other with Check point on being installed in plane 101, each Check point mainly contains the tachogenerator 105 that is installed on the speed reducer, the exhaust gas temperature sensor thermocouple 107 of plane power turbine T tail end, in addition, controlling object also comprises the igniter that is installed in the entry of combustion chamber place.
Master controller 201 inner employing modular designs are made up of IO Interface Module, communication module and master control nucleus module.The IO Interface Module is used to gather the various status parameters of aeroengine generation unit I operation; Communication module by bus 204 realize with start excitation controller 202, fuel adjusting controller 203, microcomputer protecting device 205 and with the communicating by letter of monitoring management computer 206.The master control nucleus module is gathered each status parameter of aeroengine generation unit I operation by the IO Interface Module, calculate output according to control algorithm, carry out real-time Communication for Power by other nodes among communication module and the aeroengine generation control system II, the operation of control aeroengine generation unit I.
2, starting excitation controller
Starting excitation controller 202 be on the distributed bus control network one from node, form by start trigger and automatic magnetic exciting two-part.When realizing the starting of electronic/exciter 103, after starting excitation controller 202 receives the activating signal of autonomous controller 101, detect the synchronizing signal of three-phase electricity, calculate and trigger the angle, the output trigger impulse is realized the operation of electronic/exciter 103 as motor to thyristor.When aeroengine generation unit II generator operation, the electronic/exciter 103 of starting excitation controller 202 controls is as the exciter operation, and the output field current makes generator 102 boost to voltage rating to the exciting winding of generator 102.
3, fuel adjusting controller
Fuel adjusting controller 203 be on the distributed bus control network one from node, control and operand are the fuel control valves 104 of the required fuel flow rate of control aeroengine generation unit I.Fuel adjusting controller 203 is according to the valve opening instruction that comes autonomous controller 101, moves to given position by controlling the valve rod that its driving circuit of servo valve comes fuel metering modulating valve 104.The position information of the displacement transducer of fuel control valve 104 feedback valve rod is to fuel adjusting controller 203, does poorly with given valve opening again, and difference is controlled electric current by driving circuit of servo valve output after doing control algorithm, forms a closed control circuit.
4, microcomputer protecting device
Microcomputer protecting device 205 is that on the distributed bus control network one is from node; microcomputer protecting device 205 links to each other with generator 102, has the function of generator stator ground protection, generator longitudinal protection, composite voltage overcurrent protection, overvoltage protection, field loss protection, reverse-power protection, the differentiation of PT broken string.Its output normally-closed contact Access Control major loop when protective signal occurring, disconnects the control major loop, shows the protection reason simultaneously, and sends the data to master controller 201.Under the kinds of protect measure, when generator occurs unusual or electrical network when breaking down, microcomputer protecting device can be made various protections actions timely, thereby has guaranteed generator set and staff's safety.
5, monitoring management computer
Monitoring management computer 206 is nodes on the distributed bus control network, carries out real-time exchanges data with all controls, protective gear on the bus 204, and reflects the running state of aeroengine generation unit I by main interface.Monitoring and control management software on the monitoring management computer 206 comprises operation monitoring software, input/output test software and parameter modification downloaded software.Operation monitoring software is realized the real-time demonstration to the unit operation parameter, the fault inquiry of warning, the record of historical data and the selection of the method for operation; Input/output test software is used to detect the manual control of various states and realization part driving arrangement when aeroengine generation unit I shuts down; The parameter modification downloaded software realizes modification, preservation and the download to startup of unit curve, alarm parameters, Operational Limits etc.Monitoring and control management software provides friendly man-machine interface, and the running state of the monitoring aeroengine generation unit I that operator can be intuitively real-time also provides great convenience for operator in the operation of aeroengine generation unit I.
Fig. 2 is an invention aeroengine generation shown in Figure 1 system control flow chart
As shown in Figure 2, in the present embodiment, the control of invention aeroengine generation system may further comprise the steps:
1, starting is prepared
At first; operator send a startup of unit instruction by monitoring management computer 206; master controller 201 on the bus 204 will be done starting and prepare after receiving starting order; send the starting warning order on bus 204; starting excitation controller 202; fuel adjusting controller 203 and microcomputer protecting device 205 are checked various status informations after receiving the starting warning order; whether the valve event of fuel adjusting controller 203 verification fuel control valves 104 and initial zero-bit be correct simultaneously; the condition that whether meets starting, each control gear feeds back to various status informations on the master controller 201 by bus 204 at last.
2, unit hot exposure
Master controller 201 checks whether starting conditions satisfies, if do not satisfy, then return the starting preparatory stage, when starting conditions all satisfies, starting aeroengine generation unit I, master controller 201 sends starting command to starting excitation controller 202 by bus 204, and the electronic/exciter 103 of starting excitation controller 202 controls drives aeroengine generation unit I starting separately as the motor operation.Simultaneously, master controller 201 is gathered plane 101 rotating speeds by tachogenerator 105, when rotating speed is raised to fire speed, be 8% of rated speed～9% o'clock in the present embodiment, master controller 201 sends valve opening according to predefined starting curve by bus 204 and instructs to fuel adjusting controller 203, the fuel control valve `104 of fuel adjusting controller 203 control aeroengine generation unit I sends into fuel to plane 101 according to predefined starting curve, igniter 108 igniting at master controller 201 control planes 101 entry of combustion chamber places, realize the hot exposure of aeroengine generation unit I, plane 101 is according to predefined starting curve raising speed, and electronic/exciter 103 drives aeroengine generation unit I raising speed with plane 101 common actings.
3, set speed adjustment
Master controller 201 is gathered plane 101 rotating speeds, when being raised to, rotating speed withdraws from electronic working speed, in this enforcement, be 44% of rated speed～46% o'clock, master controller 201 sends electronic exiting command to starting excitation controller 202 by bus 204, electronic/the exciter 103 of starting excitation controller 202 controls withdraws from electronic work, makes plane 101 drive aeroengine generation unit I raising speed separately by fuel adjusting controller 203 control fuel control valves 104 fully.
4, unit generation operation
Master controller 201 is gathered plane 101 rotating speeds; if do not receive halt command this moment; then work as rotating speed and be raised to balancing speed; in the present embodiment; when the rated speed 93.8%; master controller 201 sends the excitation order to starting excitation controller 202 by bus 204; electronic/the exciter 103 of starting excitation controller 202 controls moves as exciter; the output field current is to the exciting winding of generator 102; make generator 102 boost to voltage rating, aeroengine generation unit I carries out normal generator operation.When aeroengine generation unit I normally moves, the Operational Limits that master controller 201 is gathered aeroengine generation unit I, calculate fuel flow rate according to control algorithm, sending valve opening by bus 204 then instructs to fuel adjusting controller 203, the fuel of fuel adjusting controller 203 control fuel control valves 104 output corresponding discharges makes aeroengine generation unit I stable operation.
Simultaneously; when aeroengine generation unit I enters the generator operation state; master controller 201 sends order on bus 204; microcomputer protecting device 205 comes into operation; since the output normally-closed contact Access Control major loop of microcomputer protecting device 205, when protective signal occurring, automatic disconnection control major loop; automatic diagnosis simultaneously goes out to protect reason, and sends the data to monitoring management computer 206.
5, the unit deceleration is shut down
If aeroengine generation unit I receives halt command in the set speed adjustment stage, then master controller 201 control aeroengine generation unit I decelerations are shut down.
6, the unit off-load is shut down
If aeroengine generation unit I receives halt command in the unit generation operation phase, then master controller 201 control aeroengine generation unit I decelerations are shut down, and then, slow down and shut down.
When aeroengine generation unit I need shut down, can divide dual mode to carry out according to the operating mode of current unit: off-load be shut down and is slowed down and shuts down.When master controller provides halt command, need to make corresponding shutdown operation according to the residing state of current unit.If current unit is in generate electricity by way of merging two or more grid systems, then unit is implemented earlier off-load and is shut down after receiving halt command, the shutdown of slowing down again after removal of load progressively.If current unit is in the non-stage of being incorporated into the power networks, the operation of then directly slowing down and shutting down.In the process of deceleration or off-load, master controller 201 has provided the instruction of speed-raising again as if unit, and then unit keeps rotating speed after a period of time earlier, carries out speed governing once more, and makes set steady move according to corresponding control strategies.
Aeroengine generation unit I from starting, raising speed is in the middle of running, monitoring management computer 206 is in the state of real-time monitoring, has shown on the visual interface that each monitoring point comprises the feedback displacement information of rotating speed, power, temperature, pressure and fuel control valve; Record correlation time that has shown unit operation comprises cold machine time, warm-up period, surplus commentaries on classics time, starts important time parameters such as setup time, starting time and dead time; Show Realtime Alerts and preserved historical Alert data; Record reflection real-time curve also saves historical data; Whole monitoring system is intuitively visual, provides very big convenience to the user.The aeroengine generation control system adopts the distributed bus control technique, and each several part adopts modular design, realizes that the aeroengine generation unit plays the automatic control in machine, the running.
Aeroengine generation of the present invention system has the following advantages:
1, in this invention in the plane control system in conjunction with having utilized the distributed bus control technique; controller in the system and protective gear are realized distributed control with a control of the form composition network of bus; the starting reliably of aeroengine generation unit safety, raising speed and generator operation have been realized; can be used for being incorporated into the power networks and generate electricity and the islet operation generating, the use field is wide.
2, the flexible control of this plane system, realized following function: when generating electricity by way of merging two or more grid systems, the safety of unit cuts out, and can not cause the big fluctuation of electrical network; Lonely net generating in two kinds of situation, during the unit generating, can holding frequency stable, occur also can not causing when fluctuating by a relatively large margin unit to stop at load; If many units are simultaneously online, can keep the stable of electrical network, the incision of single unit cuts out can not influence the stable of whole electrical network.
3, aeroengine generation control system modularization is divided into several subsystems with whole system and realizes, makes more stability and high efficiency of control system, system have and changes convenient, advantages such as assembling is flexible, communication facility, applicable dissimilar control requirement.
4, the human-computer interaction interface of hommization, the perfect adaptation of each digital display meter and easy-operating control knob on the operating table is for operator provide great intuitive and convenience.Powerful database backstage can inquire the nearly historical data of some months, for analyzing also providing a great convenience property in the backstage of set state.
Although above the illustrative embodiment of the present invention is described; but should be understood that; the invention is not restricted to the scope of embodiment; to those skilled in the art; as long as various variations appended claim limit and the spirit and scope of the present invention determined in; these variations are conspicuous, and all utilize innovation and creation that the present invention conceives all at the row of protection.

Claims (4)

1. an aeroengine generation system comprises aeroengine generation unit and aeroengine generation control system, it is characterized in that:
The aeroengine generation unit comprises an electronic/exciter, with coaxial connection of generator, plane in the aeroengine generation unit; The aeroengine generation control system comprises master controller, starting excitation controller and fuel adjusting controller, forms a distributed bus control network with the form of bus, and each controller all is an isolated node on the bus; Master controller is a host node, and fuel adjusting controller, starting excitation controller are from node;
(1), during the aeroengine generation startup of unit, master controller sends starting command to the starting excitation controller by bus, the electronic/exciter of starting excitation controller control moves as motor, drives the aeroengine generation startup of unit separately; (2), master controller is gathered the plane rotating speed, when rotating speed is raised to fire speed, master controller sends valve opening according to predefined starting curve by bus and instructs to the fuel adjusting controller, the fuel control valve of fuel adjusting controller control aeroengine generation unit is sent into fuel to plane according to predefined starting curve, the igniting of main controller controls plane, plane is according to predefined starting curve raising speed, and electronic/exciter and plane do work jointly and drive aeroengine generation unit raising speed; (3), master controller is gathered the plane rotating speed, when rotating speed is raised to when withdrawing from electronic working speed, master controller sends electronic exiting command to the starting excitation controller by bus, electronic/the exciter of starting excitation controller control withdraws from electronic work, makes plane drive aeroengine generation unit raising speed separately by fuel adjusting controller control fuel control valve fully; (4), master controller is gathered the plane rotating speed, when rotating speed is raised to balancing speed, master controller sends the excitation order to the starting excitation controller by bus, electronic/the exciter of starting excitation controller control moves as exciter, the output field current is to the exciting winding of generator, make generator boost to voltage rating, the aeroengine generation unit carries out normal generator operation; When (5), the aeroengine generation unit normally moves, master controller is gathered the Operational Limits of aeroengine generation unit, calculate fuel flow rate according to control algorithm, sending valve opening by bus then instructs to the fuel adjusting controller, the fuel of fuel adjusting controller control fuel control valve output corresponding discharge makes the operation of aeroengine generation set steady.
2. aeroengine generation according to claim 1 system is characterized in that described aeroengine generation control system also comprises microcomputer protecting device and monitoring management computer;
Microcomputer protecting device is that on the distributed bus control network one is from node, microcomputer protecting device links to each other with generator, function with generator stator ground protection, generator longitudinal protection, composite voltage overcurrent protection, overvoltage protection, field loss protection, reverse-power protection, the differentiation of PT broken string, its output normally-closed contact Access Control major loop, when protective signal occurring, disconnect the control major loop, show the protection reason simultaneously, and send the data to master controller;
Monitoring management computer is a node on the distributed bus control network, carries out real-time exchanges data with all controls, protective gear on the bus, and reflects the running state of aeroengine generation unit by main interface.
3. aeroengine generation according to claim 2 system is characterized in that monitoring and control management software comprises operation monitoring software, input/output test software and parameter modification downloaded software on the described monitoring management computer; Operation monitoring software is realized the real-time demonstration to the unit operation parameter, the fault inquiry of warning, the record of historical data and the selection of the method for operation; Input/output test software is used to detect the manual control of various states and realization part driving arrangement when the aeroengine generation compressor emergency shutdown; The parameter modification downloaded software realizes modification, preservation and the download to startup of unit curve, alarm parameters, Operational Limits.
4. aeroengine generation according to claim 1 system is characterized in that described fire speed is 8%～9% of a rated speed, and described to withdraw from electronic working speed be 44%～46% of rated speed, and described balancing speed is a rated speed 93.8%.
CN2009102635304A 2009-12-23 2009-12-23 Aeroengine generating system Expired - Fee Related CN101737170B (en)

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CN107916998A (en) * 2017-12-18 2018-04-17 石小亮 A kind of micro turbine engine dcs
CN109765881A (en) * 2019-01-18 2019-05-17 南京航空航天大学 A kind of verifying system of aeroengine control system and control algolithm

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