Gas turbine engine, starting method thereof, starting system and medium

Abstract

The invention relates to a gas turbine engine, a starting method and system of the gas turbine engine and a medium. The starting method comprises the steps that S1, a high-pressure rotor of the gas turbine engine is driven by an air turbine starter to rotate, the rotating speed of the high-pressure rotor is subjected to closed-loop control according to the air inlet pressure of the air turbine starter to reach the set rotating speed, and whether the engine rotor has the thermal bending effect or not is judged according to a vibration signal of the high-pressure rotor of the engine; and S2, if it is judged that the hot bending effect exists in the step S1, closed-loop control is conducted on the rotating speed of the high-pressure rotor according to the air inlet pressure of the air turbine starter, and the rotating speed is maintained to the set rotating speed till whether the engine rotor has the hot bending effect or not is judged according to the vibration signal of the high-pressure rotor of the engine.

Description

Technical Field

[0001] The present invention relates to the field of gas turbine engines, and in particular to a starting method, a starting system, and a computer-readable medium for a gas turbine engine. Background Art

[0002] The starting process of a gas turbine engine, such as an aircraft engine, is a very complex process, which is mainly completed by the cooperation of the starting system, the fuel control system and the ignition system. The starting system mainly includes an air turbine starter and a starting air valve, and its main function is to drive the engine to the speed required for starting and provide the required compressed air for the combustion chamber. The fuel control system is mainly composed of an electronic controller EEC, a fuel pump, a hydraulic mechanical device HMU and various sensors and actuating accessories. Its main function is to provide the combustion chamber with the fuel required for starting and control the engine to achieve the required operating state and performance. The ignition system is mainly composed of an ignition exciter, an ignition cable and an ignition nozzle. Its main function is to ignite the fuel in the combustion chamber during the engine starting process to provide power for the engine to continue to operate.

[0003] The existing gas turbine engine starting process adopts an open-loop control method, and the starting process is as follows: the air turbine starter works to drive the engine high-pressure rotor to operate; when the engine speed reaches the ignition speed, the ignition system works to ignite the combustion chamber; when the engine speed reaches the fuel supply speed, the fuel control system supplies fuel to the combustion chamber; when the fuel in the combustion chamber is ignited, the ignition system stops working; when the engine speed reaches the disengagement speed, the air turbine starter stops working, and the air turbine starter is disengaged from the engine high-pressure rotor; when the engine speed reaches the idle speed, the engine enters the speed closed-loop control mode, and the engine completes starting.

[0004] However, gas turbine engines have a rotor thermal bending effect. During the cooling process after the engine is stopped, due to convection heat transfer, the lower part of the shaft cools faster than the upper part, causing the rotor to thermally bend. At this time, if the engine executes a start command, the engine starting process will cause excessive vibration. In severe cases, it will cause eccentric wear of the compressor blades and locking of the bearings, causing serious damage to the engine.

[0006] Therefore, in order to solve the problem of thermal bending effect when the gas turbine engine is restarted in hot state, the art needs a gas turbine engine starting method, so as to effectively eliminate the thermal bending effect of the rotor when the engine is started in hot state and ensure reliable and smooth starting of the engine. Summary of the invention

[0007] An object of the present invention is to provide a method for starting a gas turbine engine.

[0008] An object of the present invention is to provide a starting system for a gas turbine engine.

[0009] An object of the present invention is to provide a gas turbine engine.

[0010] An object of the present invention is to provide a computer readable medium.

[0011] A method for starting a gas turbine engine according to a first aspect of the present invention comprises:

[0012] S1. The high-pressure rotor of the gas turbine engine is driven to rotate by the air turbine starter, the speed of the high-pressure rotor is closed-loop controlled to a set speed according to the intake pressure of the air turbine starter, and the engine rotor is judged whether there is a thermal bending effect according to the vibration signal of the high-pressure rotor of the engine;

[0013] S2. If it is determined in S1 that there is a thermal bending effect, the speed of the high-pressure rotor is closed-loop controlled to maintain the set speed according to the intake pressure of the air turbine starter until it is determined according to the vibration signal of the high-pressure rotor of the engine that there is no thermal bending effect on the engine rotor;

[0014] S3. If it is determined by S1 or S2 that the engine rotor has no thermal bending effect, the engine is switched from the closed-loop control of S1 or S2 to open-loop control, and the engine speed is increased to the ignition speed, the fuel supply speed, the disengagement speed, and the idling speed in sequence;

[0015] S4. After the engine speed reaches the slow speed of S3, the engine speed control is switched from the open-loop control of S3 to the closed-loop control, and the closed-loop control is performed according to the fuel injection of the gas turbine engine.

[0016] In one or more embodiments, in S1 and S2, the step of performing closed-loop control of the rotation speed of the high-pressure rotor according to the intake pressure of the air turbine starter includes:

[0017] According to the difference between the target speed of the high-pressure rotor of the engine and the speed feedback value of the high-pressure rotor of the engine, the target value of the air supply pressure of the air turbine starter is obtained through the control algorithm;

[0018] Using the difference between the air supply pressure target value of the air turbine starter and the air intake pressure feedback value of the air turbine starter, a starting air valve control instruction is obtained through a control algorithm;

[0020] The starting air valve receives the control command and controls the intake pressure of the air turbine starter through the valve opening; at the same time, the gas pressure sensor feeds back the intake pressure of the air turbine starter to the controller, forming a closed-loop control of the intake pressure of the air turbine starter;

[0021] The air turbine starter converts the energy of the intake pressure into mechanical energy, driving the engine's high-pressure rotor to rotate. At the same time, the engine's high-pressure rotor speed sensor feeds back the engine's high-pressure rotor speed to the controller, forming a closed-loop control of the engine speed.

[0022] In one or more embodiments, the control algorithm includes PID, PD, and PI algorithms.

[0023] In one or more embodiments, the set rotation speed is less than a critical rotation speed corresponding to a thermal bending failure.

[0024] According to a second aspect of the present invention, a computer readable medium has a computer program thereon, and the program is executed by a processor to implement the steps of the startup method as described in the first aspect.

[0025] According to the third aspect of the present invention, a starting system for a gas turbine engine includes a starting air valve, a gas pressure sensor, an air turbine starter, a controller and an air duct. Air first passes through the starting air valve and then enters the air turbine starter through the air duct. The starting air valve is electrically connected to the controller. The gas pressure sensor is arranged on the starting air valve, or the air turbine starter, or the air duct to sense the airflow through the starting air valve. The controller includes: a memory for storing instructions executable by a processor; and a processor for executing the instructions to implement the starting method as described in any one of claims 1 to 4.

[0026] In one or more embodiments, the starting system further includes a display module for displaying whether the engine rotor has a thermal bending effect as determined by the processor.

[0027] In one or more embodiments, the controller of the starting system is integrated into a full authority digital engine controller.

[0028] A gas turbine engine according to a fourth aspect of the present invention comprises an engine rotor and a starting system according to the third aspect.

[0029] In one or more embodiments, the gas turbine engine also includes a fuel system and an ignition system, wherein: when the engine speed rises to the ignition speed, the ignition system ignites; when the engine speed rises to the fuel supply speed, the fuel system supplies fuel to the combustion chamber, and when the fuel in the combustion chamber is ignited, the ignition system stops working, and the fuel system continues to supply fuel to the combustion chamber.

[0031] The beneficial effects of the present invention include, but are not limited to, closed-loop control of the engine speed by the inlet pressure of the starter during the starting process, that is, closed-loop control of the output torque and power of the starter by the inlet pressure of the starter, and then closed-loop control of the engine speed. Compared with the scheme of directly controlling the starter speed and directly controlling the opening of the air valve, the closed-loop control of the inlet pressure of the starter of the present application combined with the closed-loop control of the engine speed is more accurate and can adapt to various different external starting environments, such as adapting to various different aircraft auxiliary power units (APU), ground air sources or cross-bleed air supply conditions, and can accurately realize the control of the engine speed during the starting process, thereby effectively avoiding the influence of the thermal bending effect on the engine when the engine is started in the hot state, and ensuring reliable and smooth starting of the engine. And, further, by switching the closed-loop control and open-loop control strategies of the engine rotor speed at different starting stages, the efficiency of engine starting is also improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] The above and other features, properties and advantages of the present invention will become more apparent through the following description in conjunction with the accompanying drawings and embodiments, in which:

[0033] Figure 1 It is a schematic block diagram of the structure of a gas turbine engine according to an embodiment of the present application.

[0034] Figure 2 It is a schematic structural diagram of a starting system of a gas turbine engine according to an embodiment of the present application.

[0035] Figure 3 It is a flow chart of a method for starting a gas turbine engine according to an embodiment of the present application.

[0036] Figure 4 is based on Figure 3 A timing diagram of the flow diagram.

[0037] Figure 5 It is a schematic diagram of closed-loop control of a gas turbine engine according to an embodiment of the present application.

[0038] Figure 6 It is a schematic block diagram of the structure of a controller of a starting system of a gas turbine engine according to an embodiment of the present application.

[0039] Reference numerals:

[0040] 1000-Gas Turbine Engine

[0041] 100-Starting system

[0042] 200-Engine rotor

[0043] 300-Fuel system

[0044] 400-Ignition system

[0045] 1-Starting air valve

[0046] 2-Gas pressure sensor

[0047] 3-Air Turbine Starter

[0048] 4-Controller

[0049] 41-Memory

[0050] 42-Processor

[0051] 43-Display module

[0052] 5- Air duct. DETAILED DESCRIPTION

[0053] The present invention is further described below in conjunction with specific embodiments and drawings. More details are elaborated in the following description to facilitate a full understanding of the present invention. However, the present invention can obviously be implemented in a variety of other ways different from the description herein. Those skilled in the art can make similar generalizations and deductions based on actual application situations without violating the connotation of the present invention. Therefore, the protection scope of the present invention should not be limited by the content of this specific embodiment.

[0054] At the same time, the present application uses specific words to describe the embodiments of the present application, such as "one embodiment", "an embodiment", and / or "some embodiments" to refer to a certain feature, structure or characteristic related to at least one embodiment of the present application. Therefore, it should be emphasized and noted that "one embodiment" or "an embodiment" mentioned twice or more in different locations in this specification does not necessarily refer to the same embodiment. In addition, certain features, structures or characteristics in one or more embodiments of the present application can be appropriately combined.

[0055] It should be noted that in the following embodiments, the gas turbine engine described in the following embodiments takes an aircraft and its turbofan engine as an example, but is not limited to this. For example, ships and their gas turbine engines can also be applied to the starting method described in the following embodiments.

[0056] Unless otherwise specified, the rotor described below refers to the high pressure rotor. The engine refers to the gas turbine engine.

[0057] refer to Figure 1 As shown, the gas turbine engine 1000 includes a starting system 100 , an engine rotor 200 , a fuel system 300 , and an ignition system 400 .

[0058] The fuel system 300 may include an electronic controller, a fuel pump, a fuel filter, a hydraulic mechanical device HMU, actuating accessories and engine sensors, etc. The EEC receives signals from various engine sensors to control the operation of the starting air valve, the ignition actuator, the hydraulic mechanical device HMU and the actuating accessories; the fuel pump provides the fuel system with high-pressure fuel of the required flow and pressure, and is driven by the engine's high-pressure rotor; the fuel filter filters the fuel pressurized by the fuel pump to provide clean fuel for the hydraulic mechanical device and the actuating accessories; the hydraulic mechanical device HMU is mainly composed of various servo valves, which are used to control the fuel flow in the combustion chamber and the actuating accessories; the actuating accessories include the engine variable geometry control actuator and various bleed and bleed valves, which mainly control the engine's variable geometry mechanism and the bleed and bleed functions.

[0059] The ignition system 400 may include an ignition actuator, an ignition cable and an ignition nozzle. The ignition actuator receives an ignition instruction from an electronic controller and controls the ignition nozzle to ignite the engine combustion chamber.

[0060] refer to Figure 2 As shown, a starting system 100 for a gas turbine engine includes a starting air valve 1 , a gas pressure sensor 2 , an air turbine starter 3 (ATS), a controller 4 , and an air duct 5 .

[0061] When the gas turbine engine is started, the air supply from the aircraft auxiliary power unit (APU), ground air source or cross-bleed air first enters the starting air valve 1, and then enters the air turbine starter 3 through the air duct 5. The air turbine starter 3 converts the internal energy of the gas into mechanical energy to drive the high-pressure rotor of the gas turbine engine to rotate. For example, the high-pressure rotor can be driven to rotate through the accessory gearbox (Accessory Gearbox, AGB) of the gas turbine engine.

[0062] The starting air valve 1 is electrically connected to the controller 4, for example, it can be electrically connected by wire or wirelessly. The starting air valve 1 receives instructions from the electronic controller 4 to control the air supply of the air turbine starter 3. The starting air valve 1 can include components such as a solenoid valve, a control valve, a butterfly valve and an air flow channel, and a manual override device. The manual override device is directly connected to the disc plate rotating shaft of the starting air valve, and is used to manually control the opening of the disc plate and can lock the position.

[0063] like Figure 1As shown, the gas pressure sensor 2 uses a conduit to draw out the gas between the air turbine starter 3 and the starting air valve 1 and then measures the pressure. The gas pressure sensor 2 is integrated in the starting air valve 1, or the air turbine starter 3, or is set in the air conduit 5. The sensing object of the gas pressure sensor 2 can be the total pressure of the gas or the static pressure of the gas. Figure 1 As shown, the gas pressure sensor 2 adopts A\B dual-channel data transmission, which has good reliability. The data transmission of the controller 4 can also be an A / B dual-channel structure. The controller 4 controls the actuation of the starting air valve 1 according to the state of the engine and the starting instruction, adjusts the air supply of the air turbine starter 3, and monitors the state of the starting system 100 at the same time.

[0064] The controllers of the starting system, fuel system, ignition system and engine rotor described above may be integrated into a Full Authority Digital Engine Control (FADEC), so that the system has a high degree of integration.

[0065] refer to Figure 3 , Figure 4 As shown, the method for starting a gas turbine engine includes:

[0066] S1. The high-pressure rotor of the gas turbine engine is driven to rotate by the air turbine starter. The vibration signal of the high-pressure rotor of the engine is used to determine whether the engine rotor has a thermal bending effect. The speed of the high-pressure rotor is closed-loop controlled to a set speed according to the intake pressure of the air turbine starter.

[0067] The thermal bending effect is a type of rotor imbalance. The method of using vibration signals to determine whether there is a thermal bending effect can be through the rotor vibration through-frequency and base frequency replication changes. For example, as the rotor runs at the critical speed for an increasing amount of time, the fundamental frequency and through-frequency amplitudes of the rotor vibration both decrease, and the fundamental frequency amplitude decreases first quickly and then slowly, while the through-frequency amplitude decreases first slowly and then quickly. The critical speed here refers to the speed that causes excessive vibration during the start-up of the thermal engine, which can be obtained through preliminary engine tests. For example, the critical speed is 3000r / min through testing. It should be noted that the critical speed here is different from the concepts of "first-order critical speed" and "second-order critical speed" usually used in rotors. The critical speed here refers to the speed at which the thermal bending effect will cause excessive vibration and cause thermal bending failure.

[0068] Specifically, the high-pressure rotor of the gas turbine engine is driven to rotate by the air turbine starter. The method for judging whether the engine rotor has a thermal bending effect based on the vibration signal of the engine's high-pressure rotor can be to increase the speed of the high-pressure rotor to a critical speed. If, as the rotor runs at the critical speed for an increasing amount of time, both the fundamental frequency and the through-frequency amplitude of the rotor vibration decrease, and the fundamental frequency amplitude decreases first quickly and then slowly, while the through-frequency amplitude decreases first slowly and then quickly, then it can be determined that thermal bending exists, and the speed is then reduced to a set speed that is less than the critical speed. Generally speaking, the set speed also needs to avoid the "first-order critical speed" and "second-order critical speed" of the rotor to avoid excessive vibration.

[0069] S2. If it is determined in S1 that there is a thermal bending effect, the speed of the high-pressure rotor is closed-loop controlled according to the intake pressure of the air turbine starter and maintained at the set speed until the high-pressure rotor of the engine is

[0071] The vibration signal of the rotor determines that there is no thermal bending effect on the engine rotor;

[0072] The beneficial effect of performing closed-loop control of the rotation speed of the high-pressure rotor to a set rotation speed according to the intake pressure of the air turbine starter is that the engine rotor can be gradually heated evenly to eliminate the thermal bending effect. After the rotation speed of the high-pressure rotor is maintained at the set rotation speed according to the intake pressure of the air turbine starter for a period of time through closed-loop control, the method of judging whether the engine rotor has a thermal bending effect according to the vibration signal of the high-pressure rotor of the engine in S1 can be repeated to judge whether the thermal bending effect still exists. If so, the closed-loop control is continued to maintain the rotation speed of the high-pressure rotor at the set rotation speed.

[0073] S3. If it is determined through S1 or S2 that the engine rotor has no thermal bending effect, the engine is switched from the closed-loop control of S1 or S2 to open-loop control, and the engine speed increases in sequence to the ignition speed, the fuel supply speed, the disengagement speed, and the idling speed.

[0074] The above-mentioned thermal bending effect is absent, that is, through the judgment method introduced above, the speed of the high-pressure rotor is obtained to the critical speed. If, as the running time of the rotor at the critical speed increases, the amplitudes of the fundamental frequency and the through-frequency of the rotor vibration do not decrease, and the amplitude of the fundamental frequency decreases first quickly and then slowly, while the amplitude of the through-frequency decreases first slowly and then quickly, then it can be determined that there is no thermal bending effect.

[0075] like Figure 4 As shown, when it is determined that the thermal bending effect of the engine rotor is eliminated, the engine speed control can be switched from the closed-loop control of S1 and S2 to the open-loop control, and the electronic controller 4 controls the starting air valve 1 to be fully opened, so that the air turbine starter 3 provides greater output power and output torque, and the engine speed increases.

[0076] When the engine speed rises to the ignition speed, the electronic controller 4 controls the ignition system 400 to operate and ignite the engine combustion chamber.

[0077] When the engine speed rises to the fuel supply speed, the electronic controller 4 controls the hydraulic mechanical device HMU to supply fuel to the combustion chamber. When the fuel in the combustion chamber is ignited, the ignition system 400 stops working, and the fuel system 300 continues to supply fuel to the combustion chamber. At this time, the engine is driven by the energy of the air turbine starter 3 and the fuel combustion.

[0078] When the engine speed rises to the disengagement speed of the air turbine starter 3, the electronic controller 4 controls the starting air valve 1 to cut off the air supply to the air turbine starter 3, and the air turbine starter 3 is disengaged from the engine high-pressure rotor. The engine is completely driven by the energy of the combustion chamber fuel combustion.

[0079] S4. After the engine speed reaches the slow speed of S3, the engine speed control is controlled by the S3

[0080] The open-loop control is switched to the closed-loop control, which is performed according to the fuel injection of the gas turbine engine.

[0081] When the engine speed rises to the slow speed, the electronic controller 4 switches the engine control mode from the previous open-loop control to the speed closed-loop control, and the engine starts. However, unlike the closed-loop control of S1 and S2, the closed-loop control at this time is performed according to the fuel injection amount.

[0082] The above-mentioned ignition speed, fuel supply speed, and disconnection speed, as the name implies, are the speeds at which ignition and fuel supply are performed, while the disconnection speed refers to the speed at which the starter and the high-pressure rotor are disconnected, and the idling speed refers to the minimum speed at which the engine can maintain stable operation. The ignition speed, fuel supply speed, disconnection speed, and idling speed can all be obtained through engine testing and engine technical manuals.

[0083] refer to Figure 5 As shown, in the above S1 and S2, the step of performing closed-loop control of the rotation speed of the high-pressure rotor according to the intake pressure of the air turbine starter includes:

[0084] According to the difference between the target speed of the high-pressure rotor of the engine and the speed feedback value of the high-pressure rotor of the engine, the target value of the air supply pressure of the air turbine starter is obtained through the control algorithm;

[0085] Using the difference between the air supply pressure target value of the air turbine starter and the air intake pressure feedback value of the air turbine starter, a starting air valve control instruction is obtained through a control algorithm;

[0086] The starting air valve receives the control command and controls the intake pressure of the air turbine starter through the valve opening; at the same time, the gas pressure sensor feeds back the intake pressure of the air turbine starter to the controller, forming a closed-loop control of the intake pressure of the air turbine starter;

[0087] The air turbine starter converts the energy of the intake pressure into mechanical energy, driving the engine's high-pressure rotor to rotate. At the same time, the engine's high-pressure rotor speed sensor feeds back the engine's high-pressure rotor speed to the controller, forming a closed-loop control of the engine speed.

[0088] In some embodiments, the above control algorithm is a common closed-loop control algorithm, such as PID, PD, and PI algorithms.

[0089] Although the above method is illustrated and described as a series of actions for simplicity of explanation, it should be understood and appreciated that these steps are not limited by the order of the actions, because according to one or more embodiments, some actions may occur in a different order and / or concurrently with other actions from those illustrated and described herein or not illustrated and described herein but understandable to those skilled in the art.

[0090] According to another aspect of the present invention, a computer-readable medium is also provided.

[0092] The computer-readable medium provided by the present disclosure has computer instructions thereon. When the computer instructions are executed by a processor, the program can be executed by the processor to implement the steps executed by the program in the gas turbine engine starting method described in the above embodiment.

[0093] refer to Figure 6 As shown, in some embodiments, the controller 4 corresponding to the starting system 100 includes: a memory 41 for storing instructions executable by a processor; a processor 42 for executing the instructions to implement the steps executed by the program in the starting method of the gas turbine engine as described in the above embodiments.

[0094] In addition, the starting system 100 may also include a display module 43 for displaying the judgment result of the processor 42 on whether the engine rotor has a thermal bending effect, so as to provide the gas turbine engine operator, generally the pilot, with real-time knowledge of the corresponding situation of the thermal bending effect of the start-up, and help the pilot to understand the current engine start-up stage. The display module 43 may have a variety of presentation forms, for example, in an airplane, the display module 43 may be a dashboard or a display screen, or even a head-up display (HUD) on the pilot's helmet.

[0095] It can be understood that the processor 42 in the previous embodiment is a combination of one or more of a system on a chip (SOC), a microcontroller, a microprocessor (e.g., a single-chip microcomputer), a reduced instruction set computer (RISC), an application-specific integrated circuit (ASIC), an application-specific instruction integrated processor (ASIP), a central processing unit (CPU), a graphics processing unit (GPU), a physical processing unit (PPU), a microcontroller unit, a digital signal processor (DSP), a field programmable gate array (FPGA), an advanced RISC machine (ARM), a programmable logic device (PLD), any circuit or processor capable of performing one or more functions, etc.

[0096] In summary, the beneficial effects of the gas turbine engine and its starting method, starting system and computer-readable medium introduced in the above embodiments include but are not limited to closed-loop control of the engine speed through the inlet pressure of the starter during the starting process, that is, closed-loop control of the output torque and power of the starter through the inlet pressure of the starter, thereby closed-loop controlling the engine speed. Compared with the scheme of directly controlling the starter speed and directly controlling the opening of the air valve, the closed-loop control of the inlet pressure of the starter in the present application is combined with the closed-loop control of the engine speed, and its control is more precise and can adapt to various different starting external environments, such as various different aircraft auxiliary power units, ground air sources or cross-bleed air supply conditions, and can accurately realize the control of the engine speed during the starting process, thereby effectively avoiding the engine hot engine state.

[0098] The influence of thermal bending effect on the engine during the state start is reduced to ensure reliable and smooth engine start. Furthermore, the efficiency of engine start is also improved by switching the closed-loop control and open-loop control strategies for the engine rotor speed at different start stages.

[0099] The steps of the method described in conjunction with the embodiments disclosed herein may be embodied directly in hardware, in a software module executed by a processor, or in a combination of the two. The software module may reside in a RAM memory, a flash memory, a ROM memory, an EPROM memory, an EEPROM memory, a register, a hard disk, a removable disk, a CD-ROM, or any other form of storage medium known in the art. An exemplary storage medium is coupled to a processor so that the processor can read and write information from / to the storage medium. In an alternative, a storage medium may be integrated into a processor. The processor and the storage medium may reside in an ASIC. The ASIC may reside in a user terminal. In an alternative, the processor and the storage medium may reside in a user terminal as discrete components.

[0100] In one or more exemplary embodiments, the functions described may be implemented in hardware, software, firmware, or any combination thereof. If implemented as a computer program product in software, each function may be stored on or transmitted by a computer-readable medium as one or more instructions or codes. Computer-readable media include both computer storage media and communication media, including any medium that facilitates the transfer of a computer program from one place to another. Storage media may be any available medium that can be accessed by a computer. As an example and not limitation, such a computer-readable medium may include RAM, ROM, EEPROM, CD-ROM or other optical disk storage, disk storage or other magnetic storage device, or any other medium that can be used to carry or store the desired program code in the form of an instruction or data structure and can be accessed by a computer. Any connection is also properly referred to as a computer-readable medium. For example, if the software is transmitted from a website, server, or other remote source using a coaxial cable, fiber optic cable, twisted pair, digital subscriber line (DSL), or wireless technologies such as infrared, radio, and microwaves, the coaxial cable, fiber optic cable, twisted pair, DSL, or wireless technologies such as infrared, radio, and microwaves are included in the definition of the medium. Disk and disc as used herein include compact disc (CD), laser disc, optical disc, digital versatile disc (DVD), floppy disk and Blu-ray disc, wherein disk often reproduces data magnetically, while disc reproduces data optically with lasers. Combinations of the above should also be included within the scope of computer-readable media.

[0102] Although the present invention is disclosed as above with preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications without departing from the spirit and scope of the present invention. Therefore, any modification, equivalent change and modification made to the above embodiments according to the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope defined by the claims of the present invention.

Claims

1. A method for starting a gas turbine engine, characterized in that: include: S1. The high-pressure rotor of the gas turbine engine is driven to rotate by the air turbine starter, the speed of the high-pressure rotor is closed-loop controlled to a set speed according to the intake pressure of the air turbine starter, and the engine rotor is judged whether there is a thermal bending effect according to the vibration signal of the high-pressure rotor of the engine; S2. If it is determined in S1 that there is a thermal bending effect, the speed of the high-pressure rotor is closed-loop controlled to maintain the set speed according to the intake pressure of the air turbine starter until it is determined according to the vibration signal of the high-pressure rotor of the engine that there is no thermal bending effect on the engine rotor; S3. If it is determined by S1 or S2 that the engine rotor has no thermal bending effect, the engine is switched from the closed-loop control of S1 or S2 to open-loop control, and the engine speed is increased to the ignition speed, the fuel supply speed, the disengagement speed, and the idling speed in sequence; S4. After the engine speed reaches the slow speed of S3, the engine speed control is switched from the open-loop control of S3 to the closed-loop control, and the closed-loop control is performed according to the fuel injection of the gas turbine engine.

2. The starting method according to claim 1, characterized in that: In S1 and S2, the step of performing closed-loop control on the rotation speed of the high-pressure rotor according to the intake pressure of the air turbine starter comprises: According to the difference between the target speed of the high-pressure rotor of the engine and the speed feedback value of the high-pressure rotor of the engine, the target value of the air supply pressure of the air turbine starter is obtained through the control algorithm; Using the difference between the air supply pressure target value of the air turbine starter and the air intake pressure feedback value of the air turbine starter, a starting air valve control instruction is obtained through a control algorithm; The starting air valve receives the control command and controls the intake pressure of the air turbine starter through the valve opening; at the same time, the gas pressure sensor feeds back the intake pressure of the air turbine starter to the controller, forming a closed-loop control of the intake pressure of the air turbine starter; The air turbine starter converts the energy of the intake pressure into mechanical energy, driving the engine's high-pressure rotor to rotate. At the same time, the engine's high-pressure rotor speed sensor feeds back the engine's high-pressure rotor speed to the controller, forming a closed-loop control of the engine speed.

3. The starting method according to claim 2, characterized in that: The control algorithms include PID, PD and PI algorithms.

4. The starting method according to claim 1, characterized in that: The set rotation speed is less than the critical rotation speed corresponding to the thermal bending fault.

5. A computer readable medium having a computer program thereon, characterized in that The program is executed by a processor to implement the steps of the starting method as described in any one of claims 1 to 4.

6. A gas turbine engine starting system (100), characterized in that: The invention comprises a starting air valve (1), a gas pressure sensor (2), an air turbine starter (3), a controller (4) and an air conduit (5), wherein air first passes through the starting air valve (1) and then enters the air turbine starter (3) through the air conduit (5), the starting air valve (1) is electrically connected to the controller (4), and the gas pressure sensor (2) is arranged on the starting air valve (1), or the air turbine starter (3), or the air conduit (5) to sense the air flow passing through the starting air valve (1); wherein the controller (4) comprises: A memory (41) for storing instructions executable by a processor; A processor (42) is used to execute the instructions to implement the starting method according to any one of claims 1 to 4.

7. The starting system (100) according to claim 6, characterized in that It also includes a display module (43) for displaying whether the engine rotor has a thermal bending effect as determined by the processor (42).

8. The starting system (100) according to claim 6, characterized in that The controller (4) of the starting system (100) is integrated into a Full Authority Digital Engine Control (FADEC).

9. A gas turbine engine (1000), characterized in that: It comprises an engine rotor (200) and a starting system (100) as claimed in any one of claims 6 to 8.

10. The gas turbine engine (1000) according to claim 9, characterized in that It also includes a fuel system (300) and an ignition system (400), wherein: When the engine speed increases to the ignition speed, the ignition system (400) ignites; When the engine speed rises to the fuel supply speed, the fuel system (300) supplies fuel to the combustion chamber. When the fuel in the combustion chamber is ignited, the ignition system (400) stops working, and the fuel system (300) continues to supply fuel to the combustion chamber.

Images