Gas turbine engine and starter generator for gas turbine engine. Startup systems with turbostarters
The invention relates to starter-generators of gas turbine engines. The technical result is to create a starter generator, in which the short-circuit rotary induction coil is not required when starting, as well as in increasing the reliability of the machine. The generator starter contains the main electrical machine containing a stator and a rotor with a rotor induction coil and damping rods forming the cell, and an excitation unit containing a stator induction coil and a rotor with rotary windings connected to the rotor induction coil of the main electric machine through a rotating rectifier. During the first stage of the launch phase, the main electrical machine is translated into mode but synchronous engine By applying alternating current to its stator windings, while the start time is created only with damping rods. During the second stage of the launch phase, the main electrical machine is transferred to the synchronous motor mode by means of supplying AC into its stator windings with simultaneous power supply to its rotary induction coil with a constant current through the excitation unit, while the command to the transition from the first stage to the second stage of the start phase is fed, When the rotation speed of the shaft reaches a predetermined value. 3N. and 6 zp F-li, 6 yl.
Figures for the Patent of the Russian Federation 2528950
Technicia
The present invention relates to starters-generators of gas turbine engines.
Prior art
In particular, the field of application of the invention are generator starters for aviation traction gas turbine engines or for auxiliary gas turbine power plants or AUXILIARY POWER UNIT) installed on aircraft. However, the invention can also be applied for other types of gas turbine engines, for example, for industrial turbines.
Such a starter generator or S / G (Starter / Generator) usually contains the main electrical machine that forms the main electrical generator that works in synchronous mode after starting and igniting the corresponding gas turbine engine. The main electrical machine contains a rotary induction coil and stator windings, which in the synchronous generator mode provide a variable electrical energy into the onboard network of the aircraft through the power supply on which the linear contactor is installed. The alternating voltage issued by the main generator is adjusted using the generator or GCU control unit (Generator Control Unit), which feeds the stator induction coil of the excitation block, the rotary windings of which are connected to the rotor induction coil of the main electric machine through a rotating rectifier. The electrical energy required to power the induction coil of the excitation unit can be obtained from an auxiliary electrical generator, such as a synchronous generator with permanent magnets, Or you can select from the onboard electrical network of the aircraft.
The rotors of the main electrical machine, the excitation unit and, possibly, the auxiliary generator is installed on a common shaft mechanically associated with a gas turbine engine shaft, and form a two- or three-fold starter-generator working without brushes (or Brushless).
To ensure the start of the gas turbine engine, as is known, the main electrical machine in synchronous mode electric engine, providing power to its stator windings by alternating voltage from the power line through a linear contactor or providing power to a rotary induction coil through an excitation unit. Since the initial generator shaft is fixed, it is necessary to submit an alternating voltage via GCU to a stator induction coil of the excitation block to obtain an alternating voltage on its rotary windings, which after straightening the rotor induction coil of the main electrical machine.
To enable the required variable voltage in order to obtain the moment necessary for starting, the GCU must be designed with parameters far exceeding the parameters necessary to power the constant current unit in the generator mode.
To solve this problem in the GB 2443032 document, it was proposed to change the excitation unit for its operation in the mode of a rotating transformer to obtain the excitation current of the rotor induction coil of the main electrical machine when it runs on start-up in synchronous mode. This change, as well as the need to pass the increased power through the stator of the excitation unit at a launch at low speed, predetermine the disadvantage of this solution due to the increase in mass and overall dimensions.
It was also proposed to ensure the launch of the main electrical machine in the asynchronous engine mode, and not in the synchronous engine mode. In this regard, you can specify documents US 5055700, US 6844707 and EP 2025926. According to the document US 5055700, when you start, the stator windings of the main electrical machine are powered by alternating voltage through the start contactor using the inverter circuit controlled with a constant voltage ratio to the frequency. The rotor of the main electrical machine is equipped with damping rods, which form a "cellular cell", allowing the rotor to rotate, while the rotor induction coil of the main machine periodically closes the spice with a special switch to avoid harmful voltage jumps. According to the document US 6844707, when you start, the stator windings of the main electrical machine are powered by alternating voltage through the start contactor using the inverter circuit controlled by voltage and frequency. The rotor induction coil of the main machine is closed by spice with an initially closed special switch. The circuit of the rotary induction coil helps to bring the rotor to rotate together with damping rods associated with the rotor induction coil and partially forming the "white cell". The opening of the short circuit switch is controlled by a current obtained from the rotary windings of the excitation block by the start of the generator starter into the electrical generator mode. The EP 2025926 document also describes the operation of the main electric machine in the asynchronous engine mode during start-up, while the start time is provided by the transfer of the rotor induction coil into the closed circuit with a sequential connection with the resistor by means of a switch with the possible participation of damping rods.
Since work in asynchronous mode deteriorates compared to work in synchronous mode, these solutions are not suitable for the case of S / G generators related to gas turbine engines, requiring at the start of increased power, in particular, in the case of traction aviation gas turbine engines.
In addition, these well-known solutions require the use of a controlled switch, parallel or sequentially connected to the rotor induction coil of the main electrical machine, which is a factor that significantly affects reliability.
In addition, it has long been known to ensure the launch in asynchronous mode of synchronous electrical engines equipped with induction coils or rods forming a cellular cell. The start-up phase until the synchronic speed is achieved only in asynchronous mode. In this regard, you can specify Documents US 3354368 and GB 175084.
Object and essence of the invention
The present invention is intended to offer an starter-generator generator of a gas turbine engine that does not have the aforementioned deficiencies, and in this regard, one of the objects of the invention is a starter generator containing:
The main electrical machine, made with the possibility of operation in the mode of a synchronous electrical generator after starting a gas turbine engine and with the possibility of operation in the electric motor mode during the gas turbine engine start phase, while the main electric machine contains a stator with stator windings and a rotor with a rotor induction coil and damping The rods forming the cell being connected to each other with their ends,
The excitation unit containing a stator induction coil and a rotor with rotary windings connected to the rotor induction coil of the main electrical machine through a rotating rectifier, and the rotors of the main electric machine and the excitation unit are installed on the total shaft designed for a mechanical connection with a gas turbine engine shaft,
The generator control unit connected to the stator induction coil of the excitation unit for feeding direct current on the stator induction coil of the excitation block, when the main electric machine works in the mode of the electrical generator, and
The starter control unit connected to the stator windings of the main electrical machine through the start contactor to supply AC to the stator windings of the main electrical machine when it works in the mode of the electric motor;
according to the invention:
The starter control unit contains the first launch control circuit in an asynchronous engine mode, the second launch control circuit in a synchronous motor mode, an AC mode for supplying AC to the stator winding of the main electrical machine through the start contactor, the engine mode switch to control the inverter through the first or second scheme. - start-up regulator and motor mode switch control system to ensure the start of the start phase in the asynchronous motor mode and to go from the asynchronous motor mode to the synchronous mode mode during the launch phase when the shaft rotation speed exceeds a predetermined threshold, and
The cell formed by damping rods is configured to independently provide launch in the asynchronous engine mode without the essential participation of the rotor induction coil of the main electrical machine in creating the start of the launch.
This design is particularly preferable in the case of generators related to aviation gas turbine engines, while the transition to an asynchronous engine is set at a velocity velocity, over which operation in the asynchronous engine mode can no longer guarantee the start of the start sufficient for such gas turbine engines. The invention is noteworthy in that the design of damping rods contributes to working in the mode of an asynchronous engine and does not require closing a rotary induction coil when starting.
Preferably, damping rods are distributed essentially evenly in the angular direction, while the angular pitch r between the two adjacent damping rods is designed in such a way as to 0.8pm According to the distinctive feature of the generator starter, it contains an angular position sensor connected to the second launch regulator scheme to transmit information about the angular position of the rotor of the main electrical machine. Preferably, each start-up regulator circuit is connected to sensors outstanding data characterizing the current values \u200b\u200bin the stator windings of the main electrical machine, and each start-up scheme contains a computing unit to evaluate the resulting real moment of launch on the basis of data that characterize the current strength values \u200b\u200bin stator windings , and to form an inverter control signals in order to automatically adjust the real moment of launch by the specified moment value recorded in the memory. In addition, the start control unit can be connected to the sensor that issues the speed of the shaft rotation speed, and may contain a circuit for transmitting to the first and second launch regulator circuit of a specified moment value based on the change in the profile of the start of the launch of the starting torque, depending on the speed Rotation shaft. The object of the invention is also a gas turbine engine equipped with the above-described generator. Another object of the invention is the method of managing a gas turbine engine generator starter during a phase of the launch of a gas turbine engine, while the starter generator contains: the main electrical machine containing a stator stator winding and a rotor with a rotor induction coil and damping rods forming a spheric cell and connected electrically with each other with its ends, and an excitation unit containing a stator induction coil and a rotor with rotary windings connected to the rotor induction coil of the main electric machine through a rotating rectifier, while the rotors of the main electric machine and the excitation unit are installed on the total shaft; according to the invention: During the first stage of the launch phase, the initial gas turbine engine does not work, the main electrical machine is transferred to the asynchronous engine mode by means of supplying AC to the stator windings of the main electrical machine, while using damping rods create a torque of almost without the participation of a rotary induction coil of an electric machine in creating a rotary induction launch moment During the next, the second stage of the launch phase, the main electrical machine is transferred to a synchronous motor mode by means of supplying AC into stator windings of the main electric machine with simultaneous power supply of the rotor induction coil of the main electrical machine with a constant current by supplying DC to the stator induction coil of the excitation block, and The command on the transition from the first stage to the second stage of the start phase is supplied when the rotational speed of the shaft reaches a predetermined value. Preferably, the main electrical machine, the rotor of which contains damping rods is essentially uniformly distributed in the angular direction with such an angular pitch R between the two adjacent damping rods, at which 0.8pm During the start phase, it is preferable to the starter generator in such a way that it automatically adjust the moment created by the main electrical machine, according to a predetermined specified value, depending on the rotation speed of the shaft. Brief description of the drawings The present invention will be more apparent from the following description represented as a non-limiting example, with reference to the accompanying drawings, in which: figure 1 is a simplified scheme of aviation gas turbine engine; fIG. 2 is a schematic type of an embodiment of an starter generator in accordance with the present invention; FIG. figure 3 is a schematic view of the radial section of an embodiment of the rotor of the main electrical machine in the generator starter shown in FIG. 2; 4 is a schematic view from the end of the rotor shown in figure 3; fIG. 5 is a schematic view of a radial section of another embodiment of the rotor of the main electrical machine in the generator starter shown in FIG. 2; fIG. 6 is a diagram of an embodiment of the starter-generator start-up adjustment unit shown in FIG. 2. Detailed description of embodiments Description of the invention is presented as part of its use for the starter-generator generator of the aviation traction gas turbine engine, an example of which is very schematically shown in FIG. However, the invention can be used for starter-generator starters of other gas turbine engines, in particular for helicopter turbines, industrial turbines or auxiliary power (APU) turbines. The gas turbine engine shown in FIG. 1 contains a combustion chamber 1, while the gases emerging from the chamber 1 lead to a rotation of a high-pressure turbine 2 (DR) and a low-pressure turbine (ND). Turbine 2 is associated with a VD compressor 4, feeding the combustion chamber with compressed air, while the turbine 3 is connected to another shaft with a fan 5 at the engine input. The transmission box 6 or the unit of the aggregates is connected by a mechanical power collection device 7 with a turbine shaft and contains a set of gears to bring different devices to rotate, in particular pumps and at least one electrical generator-generator (referred to hereinafter. S / G) . FIG. 2 is schematically shown by three-stage S / G 10, namely comprising the main electrical machine 20, an excitation unit 30 and auxiliary generator 40, the rotors of which are installed on a total shaft 12, mechanically connected to the shaft of the aviation gas turbine engine shown in FIG. The main electrical machine 20 contains a rotary induction coil 22 on the rotor and on the stator - stator windings 24a, 24b, 24c, which can be connected by the star. The excitation unit 30 contains on the stator induction coil 34 and on the rotor rotary windings 32a, 32b, 32c, which can be connected by the star. Variables generated on the rotor of the excitation unit 30 are straightened by the rotating rectifier 36, such as a rotating diode bridge, to power the rotor induction coil of the main electrical machine. Auxiliary generator 40 is, for example, a synchronous generator with permanent magnets with a rotor 42, on which constant magnets are installed, and with stator windings 44a, 44B, 44C, which can be connected by the star. In the generator mode, after starting and igniting the gas turbine engine, the main electric machine 20 forms an electric synchronous generator, which gives it an electrical three-phase voltage to the stator (in this example) through the power line 26, on which a linear switch 28 is installed. The power line 26 supplies an electrical voltage into the onboard Network (not shown) aircraft. The voltage regulation provides a generator or GCU 50 control unit, which controls the DC feed to the induction coil 34 of the excitation unit for automatic regulation of the U REF voltage at the control point on the line 26 for a given value. To do this, the GCU 50 block receives information that characterizes the instant value of the U REF voltage. The electrical energy required to power the excitation unit 30 comes from the auxiliary generator 40, while the GCU 50 unit receives and rectifies the alternating voltage supplied to the stator of the auxiliary generator 40. In option, the GCU 50 unit can occur from the on-board electrical network of the aircraft. Such a S / G operation in the generator mode is well known. In the starter mode, the main electric machine 20 forms an electric motor that creates the moment necessary to bring the gas turbine engine to rotate. During the launch phase, stator windings 24a, 24b, 24C of the main electric machine are variable from the start control unit 60 containing the inverter connected to the windings 24a, 24b, 24c through line 62 to which the startup contactor 64 is connected. At the first stage of the start phase, the initial gas turbine engine does not work, and the electric machine 20 operates in the asynchronous engine mode, using damping rods associated with the rotor induction coil 22 of the main electrical machine 20. As you know, when working in a synchronous generator mode, these damping rods must provide The mechanical strength of the rotor, increase the coefficient of the sinusoidal form with simultaneous ensuring the uniformity of the magnetic field in the workspace, reduce the effects of poorly distributed three-phase loads and damping vibrations during transition loads. According to the distinctive feature of the invention, damping rods are primarily executed in order to facilitate the creation of an increased launch moment. As shown in FIGS. 3 and 4, damping rods 222 are preferably distributed in the angular direction substantially evenly and are connected electrically with each other with its ends, forming a "white cell". In the presented example, the rotor of the main electrical machine is made with protruding poles 224, on which the rotary windings 226 of the induction coil 22 are located. The rods 222 are parallel to the axis of the rotor near the end of the poles 224, while the axis of the rods 222 are on the same cylindrical surface. On one of its axial ends, the rods 222 are connected by the crown of 228 (figure 4). At its other axial ends, the rods are just connected in a similar crown. In this case, substantially uniform angular distribution of rods 222 should be understood as the location in which the corner pitch r between the two rods corresponds to the ratio of 0.8pm In addition to optimizing work in asynchronous mode, the advantage of a substantially uniform distribution of damping rods is that it allows you to avoid large oscillations of the moment, which usually appear as a result of uneven distribution. However, substantially uniform distribution of rods requires a relative decrease in distance between poles 224 at their ends, which must be less than step R. As a result, leakage appears between the poles, but it is relatively limited and almost does not affect the operation of the main electric machine 20 in synchronous mode. In the example shown in FIG. 3, the poles 224 are made in an amount of 6, and the number of rods is 21 with alternation of 3 rods and 4 rods per pole. It should be noted that the angular arrangement of the rods does not have to be symmetrical relative to the axis passing through the center of the poles. You can envisage another location, for example, to perform a rotor with four protruding poles and with a number of rods equal to 18, alternating 4 rods and 5 rods per pole, as shown in FIG. 6. Of course, another number of rods can be envisaged, in contrast to the examples presented, in particular, depending on the application provided. To obtain an elevated moment in the asynchronous engine mode using the cell 220, the cell's electrical resistance must be minimized. Indeed, if the electrical resistance of the cell formed by the rods 222 and the crosses 228 is too high, it may be impossible to induce the sufficient current in the rods in order to achieve the desired torque level with the inverect voltage inverter inverter inverter. In addition, too high resistance leads to great losses due to the effect of Joule, which affect performance and lead to overheating. In this connection, preferably damping rods 222 and the ends of the wints 228 are performed from a material that is a good conductor of electricity, such as copper, and they have a cross section exceeding the value for rods that only perform the damping function. In addition, it is preferable to perform a rod 228 with a rectangular cross section, and not with a round, with an equal area, to minimize the effect on the cross section of the magnetic flux. It should be noted that the start-up moment in the mode of asynchronous motor is obtained completely using a cell 220 without the participation of rotary windings that are not closed. When the value of the rotation speed of the shaft 12 reaches the threshold value at which the main electrical machine operating in the asynchronous engine mode can no longer guarantee the receipt of the desired torque, the command to switch the asynchronous motor mode to the synchronous motor mode to implement the second and last phase of the start phase. The excitation unit rotates, and GCU 50 gives a constant current to the induction coil 34 of the excitation unit, to feed the induction coil 22 through the rotating rectifier 36. At the same time, an alternating current is supplied to the stator winding 24a, 24b, 24C of the main electrical machine using a block 60 Run control, while providing the optimal orientation of the stator stream with respect to the position of the rotor. Classically, when the moment produced by a gas turbine engine becomes sufficient and can be done without S / G, the start contactor 64 is blurred and the GCU 50 gives the command to the closure of the linear contactor 28, when the S / G speed and, therefore, its frequency is sufficient. Startup Inverter 602, driven by voltage and frequency using an inverter control circuit 604, issues a voltage that feeds the stator windings of the main electrical machine. The electrical energy required to generate the required voltage inverter 602 and for the operation of various components of the starter control unit 60, comes through the power line (not shown) from the on-board network of the aircraft feedable using APU or ground generator set. Depending on the position of the motor mode switch 606, the inverter control circuit 604 is connected to the input with the launch control circuit 608 in asynchronous mode or with a start-up regulator circuit 610 in synchronous mode. Scheme 614 contains inputs connected to current sensors 620a, 620b, 620c connected to the wires 62 wires for issuing data in circuits 608 and 610, characterizing the power of phase currents in the stator windings of the main electrical machine. Scheme 616 contains an input connected to the sensor 14 (FIG. 2) installed on the shaft 12 of the starter generator S / G to issue in circuits 608 and 610 information about the rotation speed of the shaft 12. Scheme 618 contains input, also connected to the sensor 14 for Issuing information about the angular position of the shaft 12 in the information circuit 610, that is, the information characterizing the angular position of the rotor of the main electrical machine 20. The sensor 14 is, for example, a well-known sensor of the angular position, which allows you to highlight information about the position and information about the speed from the sensor signals. From the angular position sensor, you can refuse if this provision can be calculated based on the measurement of electrical values \u200b\u200bdepending on it. The start control unit 60 works as follows. In response to the Start Run command, the control unit 600 gives a command to the closure of the contactor 64 and the transition of the motor mode switch 606 to the start-up regulator connection position in asynchronous mode with the inverter control circuit 604. As schematically shown in FIG. 6, Table 612 contains the data characterizing the specified value of the start of the launch of C, depending on the rotation speed N shaft S / G. In this case, the required moment value is essentially constant from the very beginning of the launch phase and decreases at the end of this phase. The digital control unit 600 receives from the circuit 616 information about the rotation speed N and reads in Table 612 specified CS moment value for its transfer to the scheme 608. In addition, the scheme 608 contains a computing unit for calculating, in particular, the values \u200b\u200bcharacterizing the real moment created by The main electrical machine, and for transmission to the voltage and frequency control circuit 604 of the specified voltage and frequency values, in particular, in order to automatically adjust the value of the real moment on the specified CS value depending on the speed. To do this, on the basis of the values \u200b\u200bof the Phase current strength values \u200b\u200bin stator windings, you can calculate the torque IQ and the flow current of the electrical machine using a known method. The IQ current, which characterizes the real moment is automatically adjustable by a given value corresponding to the specified CS moment. The idle current is a rotary stream characteristic and can be automatically adjusted to its maximum value before saturation. With an increase in speed, the maximum moment that can produce a machine operating in the asynchronous engine mode decreases from a certain speed. In this case, there is a rotation speed N 1, starting from which the machine cannot produce the required moment. This value N 1 depends on the characteristics of the machine. When N 1 is achieved, the digital control unit 600 gives a command to reorient the engine mode switch 606 to connect the launch control circuit 610 in synchronous mode with the inverter control circuit 604 and gives the command to the GCU 50 to supply the DC to the rotor winding of the excitation block 30. As in the previous case, the digital control unit 600 reads Table 612 for issuing a specified CS torque value in a circuit 610, depending on the speed. Just like the scheme 608, the launch control circuit in synchronous mode contains means to calculate the real moment. Scheme 610 displays the specified voltage and frequency controls in the inverter circuit 604 to automatically regulate the real moment at a given CS value depending on the speed, while simultaneously providing the optimal position of the stator stream with respect to the angular position of the rotor. For this, as in the previous case, calculate the currents of IQ and ID. The IQ current is automatically adjusted by a specified value corresponding to the specified CS moment. The stream current can be automatically adjusted by zero value. From the side of the excitation unit, the stator enters the current in which the level of the inducing flow is maximum at the level of the main electrical machine, in order to maximize the stator current of the main electrical machine at a given time produced. When the speed increases, the induction coil of the excitation unit is reduced to reduce the stream in the main electric machine and to avoid excessive increase in the electromotive force in relation to the power voltage of the inverter 602. The control unit 600 gives the command to open the startup 64, when the speed of rotation reaches a predetermined value. 1. Starter-gas turbine engine generator containing: the main electrical machine (20), made with the possibility of operation in the mode of a synchronous electrical generator after starting a gas turbine engine and with the possibility of operation in the mode of the electric motor during the phase of the launch of the gas turbine engine, and the main electric machine contains a stator with stator windings (24a, 24b, 24c) and the rotor with a rotor induction coil (22) and damping rods (222), forming the cell, being electrically connected to each other by their ends, Excitation block (30) containing a stator induction coil (34) and a rotor with rotary windings (32A, 32B, 32C) connected to the rotor induction coil of the main electric machine through a rotating rectifier (36), while the rotors of the main electric machine and the excitation unit Installed on a common shaft (12) intended for mechanical connection with a gas turbine engine shaft, the generator control unit (50), connected to the stator induction coil of the excitation unit for feeding the DC to the stator induction coil of the excitation block, when the main electric machine operates in a synchronous electrical generator mode, and a starter control unit (60), connected to stator windings of the main electrical machine through the trigger contactor (64) to supply AC to the stator winding of the main electrical machine, when it works in the electric motor mode; characterized in that: starter control unit (60) contains a first launch control circuit (608) in an asynchronous engine mode, a second scheme-regulator (610) of start-up in a synchronous engine mode, inverter (602) to supply AC to the stator windings of the main electrical machine via the start contactor (64), motor mode switch (606) to control the inverter (602) through the first or second launch control circuit, and the switch control circuit (606) of the motor mode and the start contactor (64), and the control unit (600) receiving information about the rotation speed of the shaft (12) configured to: lock the contactor (64) of the launch in response to the start command; the start of the launch of the gas turbine motor of the main eclectic machine (20) operating in the asynchronous motor mode using the regulator circuit (608) to start in asynchronous mode; continuing to start using the main electrical machine (20) operating in the synchronous motor mode using the regulator circuit (610) to start in synchronous mode, and the transition from the asynchronous motor mode to the synchronous motor mode is performed when the rotation speed of the shaft exceeds a predetermined threshold; and opening the contactor (64) of the launch after the start and ignition of the gas turbine engine with the ability to ensure the functioning of the main electrical machine (20) in the mode of an electrical synchronous generator; the cell formed by damping rods (222) is configured to be launched in an asynchronous engine mode without the participation of a rotary induction coil of the main electrical machine in creating a start time, in a short circuit mode. 2. The starter generator according to claim 1, characterized in that the damping rods (222) are distributed essentially evenly in the angular direction, while the angular pitch r between the two adjacent damping rods is designed in such a way as to 0.8pm 3. Starter generator according to claim 1, characterized in that it contains an angular position sensor (14) connected to the second regulator (610) launch regulator to transmit information about the angular position of the rotor of the main electrical machine. 4. Starter generator according to claim 1, characterized in that each chart-regulator (608, 610) is connected to the sensors (620a, 620b, 620c), outstanding data characterizing the values \u200b\u200bof the current force in the stator windings of the main electrical machine, and Each start-up regulator contains a computing unit to estimate the resulting real moment of startup based on data characterizing the current value values \u200b\u200bin stator windings, and to generate the inverter control signals (602) in order to automatically regulate the real moment of launch by recorded in the memory of the specified point value. 5. Starter generator according to claim 4, characterized in that the start control unit (60) is connected to the sensor (14) that issues information about the rotation speed of the shaft, and contains a chain for transmission to the first and second regulatory circuits (608, 610 ) Start a specified moment value based on the change in the memory of the start of the launch in advance, depending on the speed of the shaft rotation. 6. Gas turbine engine equipped with a generator starter according to any one of claims 1 to 5. 7. A method for managing a gas turbine engine generator starter during a gas turbine engine start phase, while the starter generator contains: the main electrical machine containing the stator with stator windings and the rotor with a rotor induction coil and damping rods (222) forming the cell and connected electrically with each other with its ends, and an excitation unit (30) containing a stator induction coil and a rotor with rotary windings connected to the rotor induction coil of the main electrical machine through a rotating rectifier (36), while the rotors of the main electric machine and the excitation unit are installed on general shaft (12), mechanically associated with a gas turbine engine shaft; characterized in that: Initially, the gas turbine engine does not work, the main electrical machine (20) is transferred to the asynchronous motor mode by supplying AC to the stator windings of the main electrical machine, and with the help of damping rods (222) create a moment of launch without the participation of a rotary induction coil of an electrical machine in creating a rotary induction launch by short circuit; The main electrical machine (20) is then translated into the synchronous motor mode by means of an AC into stator windings of the main electric machine with simultaneous power supply of the rotor induction coil of the main electrical machine with a direct current by supplying DC to the stator induction coil of the excitation block (30), and excitation, and the command on the transition from the first stage to the second stage of the start phase is supplied when the rotation speed of the shaft reaches a predetermined value, after which, as soon as the gas turbine engine is launched and set fire, the main electric machine (20) works in the electrical synchronous generator mode, and the alternating flow is stopped Current on the stator windings of the main electric machine. 8. The method according to claim 7, characterized in that the main electrical machine is used in which damping rods are essentially evenly distributed in the angular direction with such an angular pitch R between the two adjacent damping rods, at which 0.8pm 9. The method according to any one of claims 7 or 8, characterized in that during the startup phase, the starter generator controls in such a way that it automatically adjust the moment created by the main electrical machine, according to a predetermined specified value, depending on the rotational speed of the shaft. The launch of aviation gas turbine engines can be performed as follows: Pneumatic, turbostarter and electrical start-up methods were most common. On modern aircraft with gas turbine engines, more than 30 000 n gas turbine systems are used with turbocharger starters running on the fuel engine of the aircraft, and with turbostars of a limited reserve of the working fluid (air, powder, liquid). The turbocharger starter (TKS) is a relatively small gas turbine engine with limited performance (up to 90-100 s) at a starter mode and with a capacity of 50 to 200 kW. For the first time in the world, TKS to launch aviation GTD were manufactured in the Soviet Union in the early 50s. TKS is started from an electric starter. After going to the operating mode, TKS spins the rotor of the engine of the engine due to excessive power, the unlocked turbine turbine. The main elements of the TCS are the gas generator, the power turbine and gearbox. The torque from the turbostaster to the shaft of the engine of the engine is transmitted: The electric starter designed to launch a turbostarter is connected to the turbostaster shaft through the friction clutch and the coupling of the free move. The advantage of the turbostarter compared to other launch systems is: comparatively small energy consumption for launch of the starter itself, and therefore large autonomy of the system; the possibility of obtaining a significant power with small dimensions of the starter, which provides an accelerated engine launch; the lack of a special working fluid, as TKS works on the same fuel as the main engine. However, the use of turbostars complicates the production and operation of the CTA, increases the overall start time, since the startup of the turbostarter is added by the start of the GTD. Running systems with electrical starters differ: ease of device and control; reliability in work; provide multiple launch repetition; Run operations are easily automated. However, the area of \u200b\u200befficient use of electrical start-up systems is now limited to an 18 kW output power, and in some cases 40 kW, since the data of these systems is characterized by a significant increase in their mass with an increase in their power. Therefore, for engines with a large load, electrical start-up systems are less suitable than running systems with turbostarters. It should be noted that most aircraft have an electrical start-up system on board. On light aircraft and helicopters, these systems are used to start the main GTD, and on medium and heavy - to start GTD auxiliary power plants, which in turn launch the main GTD of the aircraft. Electrical starters and generator starters are used to start GTD on aircraft: To start gas turbine engines with large * n) gi (power), systems with turbostarters apply. The latter are small-sized high-breed gas turbine engines. Tourbostarters are usually centrifugal compressors that provide one or two-stage turbines, and differ from each other by the type and form of combustion chambers, the method of transmitting torque to the motor of the engine of the engine, sizes and technical characteristics. The transmission of torque from the turbostaster to the engine can be carried out either using various couplings (including hydraulic) or by gas communication between the two turbines. In the latter case, one of the turbines is installed on starter Rotor, and the other should be related to the engine of the started engine when the engine starts starter that does not have a kinematic connection with the engine starter, the starter turbocharger works the main part of the time on stopped mode (except for acceleration time), and the turbine installed on the engine running, works With a continuously increasing speed of rotation, providing a smooth promotion of the engine's rotor, the gas flow rate remains constant through the starting turbine, and the torque when increasing the rotational speed decreases (curve 1 in Fig. 15.6) in turbostarters having a kinematic connection with the engine rotor (hydromefluor) The torque when changing the rotational speed remains constant (curve 2 in Fig. 15.6), which is provided by the turbostaster regulator fuel pump. The advantages of launching systems with gas turbine starters should be given the possibility of obtaining a large power, multiple autonomous starters, which is explained by small electricity flow and start-up fuel. Odiako for the reliability of work These launch systems are usually inferior to electric. Complicated and technical maintenance. This variety of units l is due to the complexity of launching systems in a chain The entire startup system essentially includes two systems: system starting a turbostarter and outputing it to the operating speed mode and the main engine start system. The automatic control system of the engine start process controls the aggregates of many systems: fuel, oil, electric, pneumatic, etc. Automatic regulation is carried out by frequency of rotation. Since the processes of launching a turbostarter and the main engine are performed in series, then a common start cycle continues at least 2 minutes. The launch of the engine turbostarter is carried out in the following sequence (Fig. 15.7) when you press the start button 14 from the onboard set, the maximum speed relay 13 goes to the electric starter 1 and simultaneously to the starting coil and the Candles of 12 turbostarter 2 electric starter comes to work, starts to rotate the turbostar rotor 2 , consequently, the fuel pump controller (TNR) is the latter through the open valve 11 supplies fuel from the tank 15 to the injectors of the starting block, where it is set down, resulting in a launcher of the flame. As the frequency of rotation of the turbostar rotor increases, and therefore, I increase the fuel pressure of the fuel, as a result of which the main (working) nozzle comes into operation. From this point on, the turbine begins to work, and the further scrolling of the starter rotor is continuing for some time together with the electric starter and the turbine when the specified frequency is reached. Rotation. Rotor turbostarter relay Makhsl- figure 157 Startup System Startup with Turbostarter the email turns of the IZ turns off the electric starter and the ignition system 12 Further scrolling of the turbostarter rotor before "Output to operating mode is carried out by a turbine. Hydromefta 3 at a certain speed frequency gradually addly, ensures the clutch of the rotor of the turbostarter and the rotor of the main engine with the engine rotor is rigidly connected to the tachogenerator 6 voltage of which is proportional to the rotor speed of the GTD rotor The further engine starting process is automatically rushed at the power of the tachogenerator and the relay box 7 taegender as the hour increases the rotation of the Rotor GTD increases the voltage created by them and when the groom has reached, the specified values \u200b\u200bare triggered by certain relays in the 7-way box. Running on the 'first stage of the scroll of the rotor GTD turns on the ignition system 8 "and the fuel starting system 9 is created in the combustion chambers of the Tames of Tames somewhat later, the Ezpus automatic machine starts to feed the fuel to the working nozzles, dosing it in terms of air pressure on the turbine compressor The main engine enters the batter, and the further process of scrolling the rotor is made in conjunction with the turbo starter. At this stage, the engine launch already disappears in the work of the starting system. Therefore, the relay of the box 7 when the motor rotor rotation is reached rotating the engine rotor turns off the fuel powder system, go then with some interval, and the ignition system is turned off later in order to provide the "necessary time to train the candles, which creates more favorable conditions for the subsequent launch when the turbine is increasingly Up to this value, at which there is a need for a turbostar, the latter is turned off. In this case, a command for the closing of the valve // \u200b\u200bGoplkev "V Sosa-regulator is served from the relay" Boxes 7 ", a further increase in the rotor rotation frequency engines H output of its small gas mode is provided at the expense of its own turbuush. Depending on the required power and conditions of application, various starters are used, three types were obtained with the greatest distribution: electric, gas turbine and air. Electrostar (EST).The electrostarter is an electric direct current engine powered by batteries or from a gas turbine auxiliary installation with an electric generator. The electric starter rotor through the gear transmission is connected when started with the engine rotor. In the electric starter, with a constant supply voltage, as N increases, the torque is significantly reduced due to the reduction of current. The current strength, and, consequently, the torque with increasing N can be enhanced by increasing the supply voltage. To do this, use the battery switching batteries from the parallel scheme to serial: at the beginning of the start, the electric starter is powering the voltage of 24 V, and then 48 V. As a result, there is no excessive current at the beginning of the start and increases the starter power at elevated N. The 24/48 power supply system in several complicates the power equipment and leads to a faster discharge of batteries, but allows you to speed up the launch. In addition to the electric starters, electrical generators starters have found wide application, which on startups work as starters, and on the main modes, as the generators driven from the engines. This allows you to have one electrical unit instead of two and reduce the mass of the system. Electrostarter, or starter-generator, consists of two main nodes: a fixed stator and rotating rotor-anchor. The capabilities of electrical devices are greatly expanded, if a special energy enterprise is used as a power source instead of batteries (auxiliary power plant), consisting of an electric generator rotating a small gas turbine engine. The advantages of this method are the unlimited possibility of repeated launches and a decrease in the number of batteries; This in many cases justifies its shortcomings of the power supply system and the longer start of the engine due to the need for pre-output to the operating power of the energy enterprise. The rotors of the electric starter and the engine are connected through the gear transmission serving to match the speed of rotation. To connect rotors when started and disconnected after turning off the starter power, this gear includes a clutch mechanism (or centrifugal) ratchet clutch or an overtaking roller coupling. The coupling hours takes place after turning off the electric starter when its rotational speed begins to decrease, the speed of rotation of the engine rotor continues to increase. Gas turbine starters provide autonomy of the start-up system, do not require powerful batteries, do not limit the possible value of the pad and the number of successive launches. The disadvantage of such a system is its rise in price, an increase in the start time due to the need to pre-launch and output to the starter mode, the need to use on each engine of its complex and expensive starter with all its systems. Air turbostarter.The main element of the air starter is an air turbine, powered by compressed air from the auxiliary power plant (VSU) or (in a multi-engine power, installation) of the exhaust engine. ASU may be ground (airfield) or on-board if autonomy is required. In a multi-engine power plant, one side of the aircraft serves all engines on which only air turbines are installed. The blades of the impeller are made in one integer with the disk. The turbine housing is combined in one unit with an air supply valve equipped with a constant pressure regulator, which allows you to maintain the required pressure of the incoming air, regardless of the pressure in the highway. Turbocompressor starter.The turbocharger starter is a small gas turbine engine that spins the main engine rotor; It is usually located in the coke (in the sock) of the main engine. Since the turbocharger starter works briefly, only during the launch, then the requirements are not presented to its economy. It must be compact, easy, simple, cheap and enjoy a quick and reliable one's own launch. Accordingly, the requirements of the turbocharger starter Fig. 20.7. Schemes of gas turbine starters: The gas turbine engine of the Armed Forces is usually fully implemented with a compressor selection. Fig. 20.9. Scheme of gas turbine auxiliary power plant with compressed air selection behind a compressor: 1-case drives with aggregates; 2-
centrifugal compressor: 3 - air extraction nozzle with damper; 4-
the combustion chamber; 5-turbine. Terms and Definitions. Starting system GTD (PS) (NDP - the system of launching a GTD) - a set of devices intended for forced promotion of the GTD rotor at startup. PS with direct compressed air supply. Book is the start-up system with directly supplying air) (PSNP) - the GTD launcher in which the compressor turbine operating when it starts due to the supply of compressed air to the turbine blades. Starting PU) (NDP - starter) - a device intended for the forced promotion of the GTD rotor during the startup process. Elektostarter E.ST)
-
The electric motor used as a trigger of the GTD. Starter generator (NDP - Starter Generator) - an electrical generator used as a starting device when starting GTD. Turbocompressor Starter (GKS) - GTD used as a starting device when starting the main GTD. Turbocompressor starter
- energy Supplies GGCE) - GTD used as a starting device when starting the main GTD, as well as as a source of energy to feed onboard systems of LA. Air turbostarter GVTS) (NDP - air turbine) - turbine operating on the compressed air and used as a starting device to start GTD.CLAIM
perform with simple elements and low cycle parameters. The launch of the turbocharger starter is made by the electric starter feeding from batteries. Since the frequency of rotation of the rotor of the turbocharger starter is high (30000-80000 rpm), the gearbox is always enabled to its design. Two turbocharger starter schemes are shown in Fig. 20.7:
but-cible with hydromefta; b -with a free turbine; / -Centrifugal compressor; 2-
combustion chamber; 3-turbine; 4
-Rucer; 5
-Gidromefta; b.- an extensive roller of the starter; 7-
free turbine; 5-turbine compressor
