GB2170325A - Device for automatic testing of gas turbine automatic control system - Google Patents
Device for automatic testing of gas turbine automatic control system Download PDFInfo
- Publication number
- GB2170325A GB2170325A GB8501789A GB8501789A GB2170325A GB 2170325 A GB2170325 A GB 2170325A GB 8501789 A GB8501789 A GB 8501789A GB 8501789 A GB8501789 A GB 8501789A GB 2170325 A GB2170325 A GB 2170325A
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06G—ANALOGUE COMPUTERS
- G06G7/00—Devices in which the computing operation is performed by varying electric or magnetic quantities
- G06G7/48—Analogue computers for specific processes, systems or devices, e.g. simulators
- G06G7/64—Analogue computers for specific processes, systems or devices, e.g. simulators for non-electric machines, e.g. turbine
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/83—Testing, e.g. methods, components or tools therefor
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Computer Hardware Design (AREA)
- Physics & Mathematics (AREA)
- Theoretical Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Mathematical Physics (AREA)
- General Physics & Mathematics (AREA)
- Control Of Turbines (AREA)
- Testing And Monitoring For Control Systems (AREA)
Abstract
A simulator for automatic simulation of the real processes of starting, operating and stopping of the gas turbine in conjunction with the actuating elements (9,9') but without rotating the shafts of the turbines (16, 16'), without supplying fuel and initiating the ignition is operationally connected with outputs (18,33,34) of the automatic control system (7), where generated are starting signals for the starting motor (5) of the gas turbine, control signals for the ignition unit (4) and a test signal confirming the reception by the automatic control system (7), of the signal indicating the detection of the flame in combustion chambers (2). The device is also connected to those inputs (25,25', 36, 37, 38, 43, 44, 44') of the automatic control system (7), which are coupled with a behind-the-compressor air pressure transducer (12), rotational speed transducers (15, 15') of the shafts of the turbines (16, 16'), position transducers (8,8') of the actuating elements (9,9') of the fuel control unit (1), exhaust gas temperature transducers (13), detectors (14) of the flame in the combustion chambers (2), and a position transducer (10) of the actuator (11), of the guide assembly (3). <IMAGE>
Description
SPECIFICATION
Device for automatic testing of gas turbine automatic control system
This invention relates to gas turbines and is more particularly concerned with devices for automatic testing of a gas turbine automatic control system.
The present invention can be used for bench tests, for post-adjustment tests, or uncovering complex malfunctions both of the gas turbine and its control system. The invention can also be used for pre-start testing of gas turbines or for tests after removal from long storage.
In modern practice automatic control systems are tested for full serviceability together with actuating mechanisms and devices either in the process of starting of a gas turbine or as a result of thorough and lengthy inspections. Such techniques, however, are not without errors resulting in failure of control system components and, in addition, are as a rule labour-intensive. The time required for such tests runs into hours and even days.
Known in the art is a marine gas turbine simulator which simulates basic parameters of a gas turbine to represent its static and dynamic parameters. This simulating device has no connection with the real gas turbine and its control system and cannot, therefore, be used for automatic testing of the automatic control system of a gas turbine.
Known in the art is a calibrator for adjustment of control system components, manufactured by General Electric under the name
Speedtronic. The calibrator is connected to the control system and operates with a set of sources of various signals controlled manually in static conditions and a contact board. Using straps, many combinations can be connected on the board so that signal sources are electrically coupled with inputs of various adjustment circuits. Signals can be manually regulated in order to effect step-by-step adjustment of the control system components.
This calibrator has no arrangements for automatic operation which is the only way for fast and reliable comprehensive testing of the functioning of the control system in combination with the actuating elements of the gas turbine.
Testing with this calibrator involves many switchings of the board. It is a labour-intensive operation fraught with errors which can result in damaging analog and logical cards of the control system and calibrator.
We know of no other device for automatic testing of a control system for gas turbines.
It is an object of the present invention to provide a novel device for automatic testing of a gas turbine automatic control system.
One more object of the present invention is to provide a device for automatic testing of an automatic control system together with actuating elements.
Another object of the invention is to reduce the number of unfinished starts of a gas turbine.
Still another object of the invention is to make the life of the gas turbine longer.
And, finally, it is an object of the present invention to make the gas turbine more reliable in operation.
This is achieved in that, according to the invention, a device for automatic testing of a gas turbine automatic control system is a simulator device for automatic simulation of the real processes of start, operation and shutdown of a gas turbine in conjunction with actuating elements but without rotation of the turbine shafts, without fuel supply or ignition, and said simulator device is operationally connected with outputs of the automatic control system, at which available are the signals for starting the starting motor of the gas turbine, control signals for the ignition unit and a test signal confirming the reception of the signal generated by the detector of the flame in the combustion chambers, and also connected to those inputs of the gas turbine automatic control system, to which connected are a transducer of the air pressure behind the axial-flow air compressor, turbine shaft rotational speed transducers, position transducers of actuators of the fuel control unit, exhaust gas temperature transducers, detectors of the flame in the combustion chambers, and a position transducer of the actuating element of the guide assembly.
The use of the simulator device according to the invention permits substantial reduction of the number of unfinished starts of the gas turbine, since comprehensive testing of all unit, devices, actuating elements and the automatic control system of the gas turbine performed in advance uncovers malfunctions which could have been the reason of an unsuccessful turbine start. Fewer number of unfinished starts makes the life of "hot" units of a gas turbine, such as discs, turbine blades and vanes, combustion chambers and others, considerably longer. Much fuel, electric power and oil is saved. More complex faults can be spotted faster since any stage of the turbine operation can be run as many times as it is required for a particular purpose. Testing becomes much safer.
It is advisable that the simulator device should comprise, connected to the automatic control system outputs at which the starting signals for the starting engine are formed, a unit for detecting control commands for the starting motor, a unit for calculating the rotational speed of turbine shafts, the input thereof being connected to an output of the unit for detecting control commands for the starting motor, a unit for forming a signal simulating the signal of the behind-the-air-com pressor air pressure transducer, the input thereof being connected to an output of the turbine shaft rotational speed calculating unit and the output thereof being connected to that input of the automatic control system, to which the behind-the air-compressor air pressure transducer is connected, and a unit forming signals simulating the signals of the turbine shaft rotational speed transducers, whose inputs are connected to outputs of the turbine shaft rotational speed calculating unit and whose outputs are connected to those inputs of the automatic control system, to which respective turbine shaft rotational speed transducers are connected.
The simulator device may comprise a unit for conversion of signals of position transducers of the actuating elements of the fuel control unit, whose inputs are connected to the position transducers of the actuating elements of the fuel control unit, a fuel consumption calculating unit whose inputs are connected to outputs of the unit for conversion of signals of the position transducers of the actuating elements of the fuel control unit and whose output is connected to another input of the turbine shaft rotational speed calculating unit, a unit for forming signals simulating the signals of the exhaust gas temperature transducers, whose one input is connected to the output of the fuel consumption calculating unit, whose another input is connected to the output of the turbine shaft rotational speed calculating unit, and whose outputs are connected to those inputs of the automatic control system, to which the exhaust gas temperature transducers are connected.
In addition, the simulator device comprises a unit for detecting the control command for the ignition unit, whose one input is connected to that output of the automatic control system, at which the ignition unit control signal is generated, while another input is connected to that output of said automatic control system, at which the test signal confirming the reception of the signal indicating the detection of the flame in the combustion chambers is generated, a unit generating signals simulating the signals of the detectors of the flame in the combustion chambers, whose one input is connected to the output of the fuel consumtion calculating unit, whose another input is connected to the output of the unit for detection of control commands for the ignition unit, and whose outputs are connected to those inputs of the automatic control system, to which the detacters of the flame in the combustion chambers are connected.
It is advisable that the simulator device should comprise a unit for conversion of the signal of the position transducer of the actuating element of the guide assembly, whose input is connected to the position transducer of the actuating element of the guide assembly and whose output is connected to one more input of the unit for calculating the rotational speed of turbine shafts.
If the fuel control unit comprises two actuating elements and a transducer of fuel pressure between said elements, it is advisable that the simulator device should comprise a unit for generating a signal simulating the signal of the transducer of the fuel pressure between the actuating elements of the fuel control unit, whose inputs are connected to outputs of the unit for conversion of signals of the position transducers of the actuating elements of the fuel control unit and whose output is connected to that input of the automatic control system, to which the transducer of the fuel pressure between the actuating elements of the fuel control unit is coupled.
The invention will now be described in greater detail with reference to a specific embodiment thereof, with reference to the accompanying drawing illustrating a block diagram of a device for automatic testing of a gas turbine automatic control system, according to the invention.
A device for automatic testing of an automatic control system for a gas turbine having at least two turbines, a high-pressure turbine and a low-pressure turbine, is shown in the drawing. The block diagram illustrates a gas turbine comprising a fuel control unit 1 connected with a combustion chamber 2, a guide assembly 3, an ignition unit 4 and a starting motor 5 connected to an axial-fiow air compressor 6.The gas turbine is also equipped with an automatic control system comprising at least one position transducer 8,8' of actuating elements 9,9' of the fuel control unit 1, at least one position transducer 10 of an actuating element 11 of the guide assembly 3, a transducer 12 of the air pressure measured behind the axial-flow compressor 6, at least one exhaust gas temperature transducer 13, at least one detector 14 of the flame in the combustion chambers 2, and at least one shaft rotational speed transducer 15, 15' of the turbines 16 and 16'. The drawing schematically shows a gas turbine having two turbines-a high pressure turbine 16 and a low pressure turbine 16'.
According to the invention, the device is a simulator for automatic simulation of those parameters which could have been formed by respective transducers in real conditions at any operational stage of so that the gas turbine in conjunction with the control system and actuating elements 9,9' and 11 could function exactly as they do in real processes of starting, operating and stopping but without rotating the shafts of the turbines 16 and 16', without supplying the fuel, initiating the ignition, without rotating the starting motor 5 and the air compressor 6.
The simulator comprises a unit 17 for detection of control commands for the starting motor 5, whose inputs are connected to -those outputs 18 of the control system 7, at which starting signals for the motor 5 are formed, a unit 19 for calculating the rotational
speed of shafts of the turbines 16 and 16', whose one input is connected to an output 20 of the unit 17, a former 21 of a signal simu
lating the- signal of the transducer 12, and a former 22 of signals simulating signals of the transducers -15 and 15'. The input of the for
mer 21 is connected to an output 23 of the
unit 19, while the output thereof is connected to that input 24 of the control system 7,
which is connected to the transducer 12.In
puts of the former 22 are connected to the
outputs 23 and 23' of the unit 19, while the outputs thereof are connected to those inputs
25 and 25' of the control system 7, which are
connected to respective transducers 15 and 1-5'.
The position transducers 8-and 8' of the
actuating elements 9 and 9' are connected to
a unit 26 for conversion of the signal of the transducers 8 and 8'. Outputs 27 and 27' of
the unit 26 are connected to the input of a
unit 28 for calculating the fuel consumption.
An output 29 of the unit 28 is connected to
another input of the unit 19 for calculating the
rotational speed of turbine shafts and to an
input of a unit 30 for generating signals simu
lating the signals of the transducers 13.
Another input of the unit 30 is connected to
the output 23 of the unit 19.
Outputs of the unit 30 are connected to
those inputs 31 of the control system 7,
which are connected to the transducers 13.
The simulator also comprises a unit 32 for
detecting control commands for the ignition
unit 4, whose one input is connected to an
output 33 of the control system 7, where the
control command for the ignition unit 4 is formed. Another input- of the unit 32 is con
nected to an output 34 of the control system
7, where a control signal confirming the re
ception of-the signals simulating the signals of the detectors 14 of the flame in the combustion chambers 2 by the control system 7 is formed.
The output 29 of the fuel consumption cal
culating unit 28 is connected to one input of a
unit 35 generating signals simulating the sig
nals indicating detection of the flame in the combustion chambers 2, while the other input
of the unit 35 is connected to an output 36
of the unit 32.
Outputs of the unit 35 are connected to
inputs 37 of the control system 7, which are
connected to the detectors 14 of the flame in the combustion chambers 2.
The transducer 10 of the actuator 11 of the
guide assembly 3, which is connected to an input 38 of the control system 7, is coupled to the input of a unit 39 for conversion of the
signal of the transducer 10. An output 40 of the unit 39 is connected to one more input of the unit 19 for calculating the rotational speed of the shafts of the turbines.
The drawing shows an embodiment of a fuel control unit featuring two actuating elements 9 and 9' between which is a fuel pressure transducer 41. In this case, the simulator should be equipped with a unit 42 for generating a signal simulating the signal of the fuel pressure transducer 41.
Inputs of the unit 42 are connected to the outputs 27, 27' of the unit 26, while the output thereof is connected to an input 43 of the control system 7, which is connected to the output of the transducer 41.
Outputs of the transducers 8 and 8' of the actuating elements 9 and 9' are connected to inputs 44 and 44' of the control system 7.
The drawing shows an embodiment of the device according to the invention, wherein the unit 17 is an AND logical circuit which generates a signal at the output 20 thereof only when all necessary signals for switching on the starting engine 5 are available at all inputs of said AND circuit.
The units 39 and 26 can be built around converters which convert the signals of the transducers 10, 8 and 8' into a DC voltage. If the transducers are linear differential transformers, the converters 39 and 26 should be AC voltage detectors.
The fuel consumption calculating unit 28 is a circuit, built around diodes, for example, for selecting the minimal input signals of the actuating elements 9 and 9' of the fuel control unit 1. The signal at the output 29 of the unit 28 is proportional to the simulated fuel consumption figure which is dictated, for example, by the degree to which the actuating elements 9 and 9' of the fuel control unit 1 are opened.
The turbine shaft rotational speed calculating unit 19 is formatted for a two-shaft gas turbine featuring a low pressure turbine 16' and a high pressure turbine 16. In consequence, the rotational speed calculating unit 19 has two channels for calculating the rotational speed of turbine shafts. The first channel is for calculation of the rotational speed of the shaft of the high pressure turbine is an analog adder supplemented by a functional amplifier so that an analog functional adding circuit 45 is formed, whose non-inverting input is connected to the output 20 of the unit 17, the signal at said output 20 controlling the rotational speed of the shaft of the high-pressure turbine 16 and the axial-flow air compressor 6, when operation from the starting engine 5 is simulated.
Another non-inverting input of the circuit 45 is connected to the output 29 of the unit 28 for calculating the simulated fuel consumption.
The inverting input of the circuit 45 is connected to the output 40 of the conversion unit 39 which simulates redistribution of power between the gas turbines 1 6 and 16'. The output of the circuit 45 is connected to the input of an integrating unit 46 which simulates the inertia of the turbine 16.
The second channel of the calculating unit 19 is also an analog functional adding circuit 47 whose one input is connected to the output 29 of the fuel consumption calculating unit 28, another input is connected to the output 40 of-the unit 39- for conversion of signals of the transducer 10 of the actuating element 11 of the guide assembly 3, while the output of the circuit 47 is connected- to the input of an integrating unit 48 which simulates the inertia of the LP turbine 16'.
As in the described embodiment of a gas turbine the axial-flow air compressor 6 is rigidly connected with the HP turbine 16, the input of the signal former 21 simulating the signal of the pressure transducer 12 is connected to the output 23 of the unit 19, at which a signal is formed proportional to the rotational speed of the shaft of the turbine 16 and, consequently, the axial-flow compressor 6.
The signal former 21 is a functional converter which is connected to the input 24 of the control system 7 and. whose output signal simulates the signal of the transducer 12 of the air pressure behind the axial-flow air compressor 6.
The unit 32 for detection of control commands for the ignition unit 4 can be an OR circuit whose one input is connected to the output 33 of the control system 7, while the other input is connected to the output 34 of the control system 7. The output signal of the unit- 32 is generated when a signal comes to at least one of the inputs thereof.
The unit 35 for generating signals simulating detection of the flame in the combustion chambers 2 comprises a threshold device 49 and an AND logical circuit 50. One input of the AND logical circuit 50 is connected to the output 36 of the unit 32, while the other input is connected to the output of the threshold device 49 whose input is connected to the output 29 of the unit 28.
The former 22 of signals simulating the signals of the transducers 15 and IS' of- the rotational speed of the HP turbine -16 and the
LP turbine 16' can be functional voltage-frequency converters 51 and 51' whose inputs are connected to respective outputs 23 and 23' of the unit 19.
The unit 42 for generating a signal simulating the signal of the transducer 41 can be an analog functional adding circuit whose non-inverting input is connected to the output 27 of the unit 26, while the inverting input-thereof is connected to the output 27' of the unit 26.
The-output signal of the unit 42 simulates the signal of the transducer 41, which is the function of the signals of position transducers 8 and 8' of the actuating elements 9 and 9 of the fuel control unit 1.
The unit 30 for generating signals simulating the signals of the transducers 13 can be an analog functional adding circuit whose invert
ing input is connected to the output 23' of the
unit 19, - while the non-inverting input thereof
is connected to the output 29 of the unit 28.
Output signals of the unit 30, which simulate the signals of the exhaust gas temperature
transducers 13 are the function of the simu
lated fuel consumption and the rotational
speed of the shaft of the LP turbine 16'.
A device for automatic testing of a- gas-tur- bine automatic.contro.l system according to
the invention operates as follows.
After the device is-hooked up to respective
-inputs and outputs of the control system 7,
the fuel supply is shut down before the fuel control unit 1 and the power is cut diff the
starting motor 5.
A "start" command is fed to the control
system 7. If relevant control commands for
the starting motor 5 are available at the out
puts - 18 of the control system 7, the AND
logical circuit of the unit 17 generates, at the
output 20, a signal to be applied to the non
inverting input of the circuit. 45 of the channel
for calculating the rotational speed of the shaft
-of the HP turbine 16 of the -unit 19. -At the
output of the circuit 45 the signal changes by
a jump to a quantity defining the rotational
-speed of the shaft of the high pressure turbine 16 and the axial-flow air compressor 6, simu
lating operation from the starting motor 5 The signal jump -is supplied from the output of
the circuit 45 to the input of the integrating
unit 46 -where it is integrated. A control- signal
is generated at the output 23 of the unit 19 to - simulate the acceleration characteristic which the time-dependent rotational speed of
the.system comprising the starting motor 5,
the axial-flow air compressor 6 and the high
pressure turbine 16.The signal is delivered
from the output -23 of the unit 19 to the input
of the voltage-frequency converter 51 of the
unit .22 and to the input of the functional con
verter of th-e former 21 of the signal simulat
ing the signal of the transducer 12 of the air
pressure behind the axial-flow air compressor:
6. The signal is- further supplied from the out
put of the voltage-frequency functional conver
ter 51 to the input 25 of the control system
7.and simulates, in accordance with a preset principle, -the signal of the rotational speed
transducer 15 of the high pressure turbine 16.
From the output of the former 21 the signal is
applied to the input 24 of the control system
7 and simulates the signal of the transducer 12 - of the air pressure behind the axial-flow air
compressor 6 in accordance with a preset
principle.
The actuating elements 9 and 9' of the fuel
control unit 1 perform the command of the
control system 7 and open to an ignition rat
ing. The position transducers 8 and 8' of the
actuating elements 9 and -9' generate signals
to respective inputs of the unit 26 where they
are converted into DC voltage signals propor
tional-to the position of the actuating elements.
9 and 9'. These signals are supplied from the
outputs 27 and 27' of the unit 26 to the
inputs of the circuit selecting the minimal
quantity of said signals of the fuel consump
tion calculating unit 28. A signal proportional
to the quantity of the simulated fuel consump
tion is generated at the output 29 of the unit
28 and delivered to the input of the threshold
device 49 of the unit 35 generating signals
simulting the signals -of the flame detectors 14
in the combustion chambers 2. The threshold
device 49 produces the enable signal to the
AND logical circuit 50 if the position of the
actuating elements 9 and 9' corresponds to
the minimal ignition threshold value.Simultane
ously, the control system 7 generates, at the
output 33, a control command for the ignition
unit 4, which is applied to the input of the OR
logical circuit of the unit 32 for detection of
the control commands for the ignition unit 4.
The logical signal is supplied from the output
36 of the unit 32 to another input of the AND logical circuit 50. Only when both signals are
available at the inputs of the- AND logical cir
cuit 50, signals simulating the signals of the
flame detectors 14 are produced at the Out- puts of the unit 35 and delivered to the inputs
37 of the control system 7. When the signals
arrive to the inputs 37, the control system 7
generates, at the output 34, a test signal
which confirms the reception, by the control
system 7, of the signals simulating the signals
of the flame detectors 14. This signal is fed
to another input of the OR logical circuit of
the unit 32 and maintains this logical signal at
the output 36 of the unit 32 at subsequent
stages of operation.
The control system 7 opens, according to a
preset principle, the actuating elements 9 and
9' of the fuel control unit 1. The signals of the
transducers 8 and 8' increase respectively, as
do the DC voltage signals at the outputs 27
and 27' of the unit 26 and the signal at the
output 29 of the unit 28, which is supplied to
the non-inverting input of the circuit 45 of the
unit 19.
The signal at the output 45 grows, is inte
grated by the unit 46 and induces the growth
of other simulating signals at the outputs of
the former 21 and the functional converter 51
of the unit 22. In addition, the increasing sig nazi taken from the output 29 of the fuel con
sumption calculating unit 28 is fed to the in
put of the analog functional circuit 47 of the
unit 19 for calculating the rotational speed of the shafts of the turbines 16 and 16', which
organizes the channel for calculation of the
rotational speed of the shaft of the low pres
sure turbine 16'.The output signal of the an
alog functional circuit 47 is integrated by the
integrating unit 48, supplied to the input of the functional voltage-frequency converter 51'
of the unit 22 and induces the increase of the
simulated signal of the rotational speed of the
shaft of the low pressure turbine 16', which is delivered to the input 25' of the control system 7. The increasing signal taken from the output 29 of the unit 28 is supplied to the non-inverting input of the analog functional adding circuit of the unit 30 and induces the increase of output signals which are applied to the inputs 31 of the control system 7 and simulate the signals of the exhaust gas temperature transducers 13.A signal proportional to the rotational speed of the low pressure turbine 16' is supplied to the inverting input of the analog functional circuit of the unit 30 from the output 23' of the unit 19 and thus simulates the process of transformation of the thermal energy of the combustion products into the energy of rotation of the shaft of the turbine 16'.
As soon as the shaft of the high pressure turbine 16 reaches the simulated rotational speed set by the control system 7, this control system 7 begins to close the actuating element 11 of the guide assembly 3. The signal taken from the position transducer 10 of the actuator 11 of the guide assembly 3 and fed to the input of the unit 39 starts growing.
The DC voltage signal at the output 40 of the unit 39 increases proportionally and is supplied simultaneously to the inverting input of the circuit 45 and to the second non-inverting input of the circuit 47 of the unit 19 for calculating the rotational speed of the shafts of the turbines 16 and 16' thus simulating heat redistribution between the turbines 16 and 16'.
Since the signal fed from the output 40 of the unit 39 is applied to the inverting input of the circuit 45, its increase reduces the growth of the simulated rotational speed of the shaft of the high pressure turbine 16 until it is stabilized at a specific level assigned by the control system 7. Simultaneously, since the signal fed from the output 40 of the unit 39 is supplied to the non-inverting input of the analog circuit 47 of the unit 19, the circuit enables the increase of the rotational speed of the shaft of the low pressure turbine 161.
In the embodiment where the fuel control unit 1 is provided with two actuating elements 9 and 9' and the transducer 41 to measure the fuel pressure between them, the signal of said transducer 41 is simulated by the unit 42. When the control system 7 opens the actuator 9, the signal of the position transducer 8 of the actuating element 9 is converted into the DC voltage by the unit 26 and supplied from the output 27 to the non-inverting input of the analog functional circuit of the unit 42. The signal simulating the signal of the transducer 41 grows in accordance with the known principle at the output of the unit 42 and is then supplied to the input 43 of the control system 7.
When the command of the control system 7 opens the actuating element 9', the signal of the transducer 8' converted into the DC voltage is supplied from the output 27' to the inverting input of the functional adding circuit of the- unit 42. The signal simulating the signal of the transducer 41 decreases at the output of the unit 42 in accordance with the known principle.
It can be pointed out in conclusion that a device for automatic testing of a gas turbine automatic control system simulates the signals of the transducers 12, 13, 14, 15 and 41, which are required for the processes of start and operation of the gas turbine without fuel supply, rotation of the shafts and without the ignition. The process of simulation permits tests of the control system and the actuating elements (9,9', 11) of the gas turbine, their feedbacks and feedforwards. Any malfuntion in the control system 7 or in actuators of the gas turbine interrupts the simulated process as it does in the real -starting and operating of the gas turbine. This permits on covering malfunctions without realling starting the gas turbine, thus reducing the number of unfinished starts and, consequently, prologing the life of the turbine and reducing the power consumption. The testing process is automatic and, therefore, the testing time is substantially cut down as is the time for identifying faults in the control system and the gas turbine.
Claims (7)
1. A. device for automatic testing of a gas turbine automatic control system, which is, a simulator for automatic simulation of the real processes of starting, operating and stopping the gas turbine in conjunction with actuating elements but without rotating the shafts of the turbines, without supplying the fuel and initiating the ignition process, said simulator being operationally connected with those outputs of the automatic control system, where generated are signals::for starting the starting motor-of the gas turbine, control signals for an ignition unit and a test signal which confirms the reception of the flame detection signal in combustion chambers by the automatic control system, and also connected to those inputs of the automatic control system of the gas turbine, which are connected to a behind-the-compressor air pressure transducer, a turbine shaft rotational speed transducer, fuel control unit actuator position transducers, exhaust gas temperature transducers, and position transducers of the actuator of a guide assembly of the gas turbine.
2. A device as claimed in claim 1, wherein the simulator comprises, connected to the outputs of the automatic control system, at which the starting motor starting signals are generated, a unit for detection of control commands for the starting motor, a unit for calculating the rotational speed of turbine shafts, whose input is- connected to an output of the -unit for detection of control commands for the starting motor, a former of a signal simulating the signal of a transducer of an air pressure
behind an axial-flow air compressor, whose in
put is connected to an output of the unit for
calculating the rotational speed of the turbine
shafts and the output thereof is connected to
the input of the automatic control system,
which- is coupled to the behind-the-compressor
air pressure transducer, and a former of sig
nals simulating the signals of the turbine shaft
rotational speed transducers, whose input are
connected to outputs of the turbine shaft rotational speed calculating unit and whose out
puts are connected to those inputs of the
automatic control system, which are coupled
to respective turbine shaft rotational speed
transducers.
3.. A device as claimed in claim 2, wherein the simulator comprises a unit for cdnversion- of signals of the position transducers of the
actuators of the fuel control unit, whose in
puts are connected to the position transducers
of the actuatdrs of the fuel control system, a
fuel consumption calculting unit, whose inputs
are connected to outputs of the unit for con
version of signals of the position transducers
of the actuators of the fuel control unit, while
the output thereof is connected to another in
put of the turbine shaft rotational speed calcu
lating unit, a unit generating signals simulating
the signals of the exhaust gas- temperature
transducers, whose one input is connected to
the output of the fuel consumption calculating
unit, another input is connected to the output
of the unit for calculating the -rotational speed
of turbine shafts, while the outputs-thereof are
connected to those inputs of the automatic
control system, which are coupled to the ex
haust gas temperature transducers.
4. A device as claimed in claim 3, wherein
the simulator comprises a unit for detection of
a control command for the ignition unit,
whose one input is connected to that output
of the automatic control system, where the
control signal for the ignition unit is generated,
and whose another input is connected to that
output of the automatic control system, where
a test signal confirming the reception, by said
control system, of the flame detection signals
is generated, a unit for forming signals simu
lating the signals of detectors of the flame in
combustion chambers, whose- one input is
connected to the output of the -fuel consump
tion calculation unit, another input is con
nected to an output of the unit for detection
of control commands for the ignition unit,
while the outputs thereof are connected to
those inputs of the automatic control system,
which are coupled with the detectors of the
flame in the combustion chambers.
5. A device as claimed in any- of the
claims 2, 3 and 4, wherein the simulator com
prises a unit for conversion of the signal of
the position transducer of the actuator of the - guide assembly, whose input is connected to
the position transducer of the actuator of the
guide assembly, while the output thereof is connected to one more input of the unit for calculating the rotational speed of the shafts of the turbines.
6. A device as claimed in claim 3, wherein the simulator comprises a unit for generating a
signal simulating the signal of the transducer
of the fuel pressure between the actuators of
the fuel control unit, whose inputs are con
nected to the outputs of the unit for conver
sion of the signals of the position transducers
of the actuators of the fuel control unit, while the output is connected to that input of the automatic control system, which is coupled with the transducer of the fuel pressure between the actuators of the fuel control unit.
7. A device for automatic testing of a gas turbine automatic control system substantially
as set forth in any one of the preceding
claims and as described herein above with ref
erence to the accompanying drawings.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB8501789A GB2170325B (en) | 1985-01-24 | 1985-01-24 | Device for automatic testing of gas turbine automatic control system |
| DE19853504409 DE3504409A1 (en) | 1985-01-24 | 1985-02-08 | SYSTEM FOR CONTROLLING AND TESTING AN AUTOMATIC CONTROL FOR GAS TURBINE SYSTEMS |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB8501789A GB2170325B (en) | 1985-01-24 | 1985-01-24 | Device for automatic testing of gas turbine automatic control system |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| GB8501789D0 GB8501789D0 (en) | 1985-02-27 |
| GB2170325A true GB2170325A (en) | 1986-07-30 |
| GB2170325B GB2170325B (en) | 1989-07-05 |
Family
ID=10573345
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB8501789A Expired GB2170325B (en) | 1985-01-24 | 1985-01-24 | Device for automatic testing of gas turbine automatic control system |
Country Status (2)
| Country | Link |
|---|---|
| DE (1) | DE3504409A1 (en) |
| GB (1) | GB2170325B (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1659287A3 (en) * | 2004-11-17 | 2009-02-18 | NORDEX ENERGY GmbH | Device and procedure for the functional test of a wind energy plant |
| WO2011150941A1 (en) * | 2010-06-04 | 2011-12-08 | Vestas Wind Systems A/S | Device and method for testing a wind power plant component |
| CN108931380A (en) * | 2017-05-27 | 2018-12-04 | 清华大学 | The turbo blade test macro of gas source driving |
| CN108931359A (en) * | 2017-05-27 | 2018-12-04 | 清华大学 | The turbo blade test macro of compressor driving |
| CN109885023A (en) * | 2019-02-21 | 2019-06-14 | 杭州汽轮动力集团有限公司 | A kind of gas turbine control system semi-physical simulation test system |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2451299C1 (en) * | 2010-10-07 | 2012-05-20 | Российская Федерация, От Имени Которой Выступает Министерство Промышленности И Торговли Российской Федерации | Device for on-line diagnostic of electric propulsion system of ship |
| CN112901598B (en) * | 2021-01-29 | 2022-08-26 | 上海电气燃气轮机有限公司 | Gas turbine hydraulic actuating mechanism testing method, electronic terminal and storage medium |
-
1985
- 1985-01-24 GB GB8501789A patent/GB2170325B/en not_active Expired
- 1985-02-08 DE DE19853504409 patent/DE3504409A1/en not_active Withdrawn
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1659287A3 (en) * | 2004-11-17 | 2009-02-18 | NORDEX ENERGY GmbH | Device and procedure for the functional test of a wind energy plant |
| WO2011150941A1 (en) * | 2010-06-04 | 2011-12-08 | Vestas Wind Systems A/S | Device and method for testing a wind power plant component |
| CN108931380A (en) * | 2017-05-27 | 2018-12-04 | 清华大学 | The turbo blade test macro of gas source driving |
| CN108931359A (en) * | 2017-05-27 | 2018-12-04 | 清华大学 | The turbo blade test macro of compressor driving |
| CN108931359B (en) * | 2017-05-27 | 2019-10-18 | 清华大学 | The turbo blade test macro of compressor driving |
| CN109885023A (en) * | 2019-02-21 | 2019-06-14 | 杭州汽轮动力集团有限公司 | A kind of gas turbine control system semi-physical simulation test system |
Also Published As
| Publication number | Publication date |
|---|---|
| GB2170325B (en) | 1989-07-05 |
| GB8501789D0 (en) | 1985-02-27 |
| DE3504409A1 (en) | 1986-08-14 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PCNP | Patent ceased through non-payment of renewal fee |