Starting system, starting method and computer readable medium of gas turbine engine

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, starting mode input of the gas turbine engine is received; s2, if the starting mode received in the S1 is heat engine starting, the opening degree of a starting air valve is adjustable, and a controller conducts closed-loop control according to the actual value, sensed by a gas pressure sensor, of the air inlet pressure of the air turbine starter and the required value of the air inlet pressure; if the starting mode received in the S1 is non-heat engine starting, the opening degree of the starting air valve is fully open or fully closed, and the controller directly instructs the starting air valve to execute fully open or fully closed for open-loop control.

Description

Technical Field

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

[0002] The starting system of a gas turbine engine, such as an aircraft engine, mainly includes an air turbine starter, a starting air valve, and an air duct. When starting the engine, compressed air provided by a ground air source vehicle, an auxiliary power unit (APU), or an engine cross bleed is generally required to drive the air turbine starter to rotate, and the air turbine starter drives the engine to rotate through the accessory gearbox (AGB). When the engine speed reaches the disengagement speed, the starting air valve closes and cuts off the air supply to the air turbine starter, and the air turbine starter is disengaged from the accessory gearbox.

[0003] In an existing solution, the starting air valve of the starting system is controlled by a switch (with only two states: fully open and fully closed). In this way, the intake pressure of the air turbine starter cannot be adjusted and is completely determined by the air supply pressure of the aircraft auxiliary power unit APU, the ground air source or the cross-bleed air. The output power and output torque of the starter are difficult to adjust.

[0004] During the cooling process of aircraft engines after parking, due to convection heat transfer, the lower part of the shaft cools faster than the upper part, causing thermal bending of the rotor. If the engine executes the start command at this time, the vibration of the engine start process will exceed the standard. In severe cases, it will cause eccentric wear of the compressor blades and locking of the bearings, causing serious damage to the engine. One solution is to eliminate the thermal bending effect by running slowly after normal start when the resonant speed caused by thermal bending is higher than the engine slow speed. However, when the resonant speed is lower than the engine slow speed, this solution cannot eliminate the thermal bending effect.

[0005] Therefore, in order to address the problem of thermal bending effect when a gas turbine engine is restarted in a hot state, the art needs a gas turbine engine starting method that can achieve precise control of the speed of the air turbine starter, thereby effectively eliminating the thermal bending effect of the rotor when the engine is started in a hot state. Summary of the invention

[0006] An object of the present invention is to provide a starting system for a gas turbine engine.

[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 gas turbine engine.

[0009] An object of the present invention is to provide a computer readable medium.

[0010] A starting system for a gas turbine engine according to a first aspect of the present invention comprises: a starting air valve, a gas pressure sensor, an air turbine starter, a controller and an air duct, wherein 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, and the gas pressure sensor is arranged on the starting air valve, the air turbine starter or the air duct to sense the air flow through the starting air valve; wherein the controller comprises: a memory for storing data executable by a processor Instructions; a processor, used to execute the instructions to implement the following steps: S1. Receive a starting mode input of the gas turbine engine; S2. If the starting mode received by S1 is a thermal engine start, the opening of the starting air valve is adjustable, and the processor performs closed-loop control according to the actual value of the intake pressure of the air turbine starter sensed by the gas pressure sensor and the required value of the intake pressure; if the starting mode received by S1 is a non-thermal engine start, the opening of the starting air valve is fully open or fully closed, and the processor directly instructs the starting air valve to perform open-loop control to be fully open or fully closed.

[0011] In one or more embodiments, the starting air valve includes a solenoid valve, a control valve, an actuator cylinder, and a butterfly valve, wherein the solenoid valve is electrically connected to the controller to receive a control signal from the controller to adjust the action of the control valve, the control valve adjusts the gas pressure in the control chamber of the actuator cylinder to move the actuator cylinder, and the movement of the actuator cylinder drives the butterfly plate of the butterfly valve to rotate, so that the opening of the starting air valve is adjustable.

[0012] In one or more embodiments, the starting air valve also includes a manual override device and a butterfly valve opening visual device, wherein the manual override device is connected to the rotating shaft of the butterfly plate of the butterfly valve, and the opening of the butterfly plate can be manually controlled and locked; the butterfly valve opening visual device is directly connected to the rotating shaft of the butterfly plate of the butterfly valve, and rotates with the rotation of the butterfly plate, so that the opening of the butterfly valve can be visually observed.

[0013] In one or more embodiments, the controller is integrated into a full authority digital engine controller.

[0014] In one or more embodiments, the gas pressure sensor is integrated on a starting air valve or an air turbine starter, or is disposed on the air duct.

[0015] In one or more embodiments, the control algorithm of the closed-loop control includes a PID, PI or PD algorithm.

[0016] A gas turbine engine according to a second aspect of the present invention comprises: a starting system as described in the first aspect and a rotor, wherein the starting system can drive the rotor to rotate.

[0017] According to a third aspect of the present invention, a starting method for a gas turbine engine adopts a starting system, including a starting air valve, a gas pressure sensor, an air turbine starter, a controller and an air duct, wherein 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, and the gas pressure sensor is arranged on the starting air valve, or the air turbine starter, or the air duct, for sensing the airflow passing through the starting air valve; the starting method comprises: S1. receiving a starting mode input of a gas turbine engine; S2. if the starting mode received by S1 is a thermal engine start, the opening of the starting air valve is adjustable, and the controller performs closed-loop control according to the actual value of the intake pressure of the air turbine starter sensed by the gas pressure sensor and the required value of the intake pressure; if the starting mode received by S1 is a non-thermal engine start, the opening of the starting air valve is fully open or fully closed, and the controller directly instructs the starting air valve to perform open-loop control by fully opening or fully closing.

[0018] In one or more embodiments, the starting mode is a hot engine start and there is a thermal bending effect on the engine rotor.

[0019] According to a fourth 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 third aspect.

[0020] The beneficial effects of the present invention include but are not limited to, by implementing different control strategies for the starting system in the cases of hot engine starting and non-hot engine starting, in the case of non-hot engine starting, the starting air valve open-loop control is fully opened to reduce pressure loss and improve the output power of the air turbine starter; and in the case of hot engine starting, the inlet pressure is closed-loop controlled to control the output torque and power of the starter, and then the engine speed is closed-loop controlled. Compared with the scheme of directly controlling the starter speed and directly controlling the air valve opening, the scheme introduced in the above embodiment can more accurately control the output torque and power of the starter, and can adapt to various different starting external environments, such as adapting to various different aircraft auxiliary power units (APUs), ground air sources or cross-bleed air supply conditions, and can accurately realize the control of the engine speed during the hot engine starting process. When the resonant speed is lower than the engine idling speed, the scheme of the embodiment introduced above can accurately and stably maintain the engine speed at the time of starting at a resonant speed lower than the resonant speed caused by thermal bending to eliminate thermal bending, and then complete the starting. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] 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:

[0022] Figure 1 It is a structural schematic diagram of a starting system according to an embodiment of the present application.

[0023] Figure 2 It is a schematic structural diagram of a starting air valve of a starting system of an embodiment of the present application.

[0024] Figure 3A as well as Figure 3B It is a control principle schematic diagram and a flow chart of a method for starting a gas turbine engine according to an embodiment of the present application.

[0025] Figure 4 It is a schematic block diagram of the structure of a controller of a starting system according to an embodiment of the present application.

[0026] Reference numerals:

[0027] 100-Starting system

[0028] 1-Starting air valve

[0029] 11-Solenoid valve

[0030] 12-Control valve

[0031] 13-Actuator

[0032] 14-Butterfly valve

[0033] 15-Manual override device

[0034] 16-Butterfly valve opening visual device

[0035] 2-Gas pressure sensor

[0036] 3-Air Turbine Starter

[0037] 4-Controller

[0038] 41-Memory

[0039] 42-Processor

[0040] 43-Display module

[0041] 5- Air duct. DETAILED DESCRIPTION

[0042] 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.

[0043] 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.

[0044] 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.

[0045] Unless otherwise specified, the rotor described below refers to the high pressure rotor. The engine refers to the gas turbine engine.

[0046] refer to Figures 1 to 3A , Figure 3B 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 .

[0047] 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.

[0048] 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 to the air turbine starter 3 .

[0049] refer to Figure 2As shown, in some embodiments, the starting air valve 1 may include a solenoid valve 11, a control valve 12, an actuator 13, and a butterfly valve 14, wherein the solenoid valve 11 is electrically connected to the controller 4 to receive a control signal from the controller 4 to adjust the action of the control valve 12, the control valve 12 adjusts the gas pressure in the control chamber of the actuator 13 to move the actuator 13, and the movement of the actuator 13 drives the butterfly plate of the butterfly valve 14 to rotate, so that the opening of the starting air valve 1 is adjustable. The beneficial effect of this is that the opening of the starting air valve 1 is easy to control.

[0050] Continue to refer Figure 2 As shown, preferably, the starting air valve 1 may also include a manual override device 15 and a butterfly valve opening visual device 16, wherein the manual override device 15 is connected to the rotating shaft of the butterfly plate of the butterfly valve 14, and the opening of the butterfly plate can be manually controlled and locked; the butterfly valve opening visual device 16 is directly connected to the rotating shaft of the butterfly plate of the butterfly valve 14, and rotates with the rotation of the butterfly plate, so that the opening of the butterfly valve 14 can be visually observed. The beneficial effect of this is that by providing the manual override device 15 and the butterfly valve opening visual device 16, during the starting process, the starting system not only has an electronic control method, but the operator also retains the option of manually controlling the starting system, so that in the event of a controller failure, the normal shutdown of the starting system is guaranteed, and the safety of the system is guaranteed.

[0051] like Figure 1 As shown, the gas pressure sensor 2 uses a conduit to lead 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. However, it should be noted that the position where the gas pressure sensor 2 is integrated in the starting air valve 1 or the air turbine starter 3 should be a position that can accurately measure the intake pressure of the air turbine starter 3, for example, it cannot be located at a position close to the rear side of the butterfly plate of the starting air valve 1, etc., which cannot accurately measure the intake pressure of the air turbine starter 3.

[0052] The electrical connection between the controller 4 and the gas pressure sensor 2 and the starting air valve 1 can be single-channel, dual-channel or triple-channel, etc., and is not limited to this as long as the signal can be transmitted reliably. The controller 4 can receive the air turbine starter intake pressure signal sensed by the gas pressure sensor 2, control the opening of the starting air valve 1 through the control algorithm, and realize closed-loop control of the air turbine starter intake pressure.

[0053] refer to Figure 1 as well as Figure 3A , Figure 3B , Figure 4As shown, the controller 4 includes: a memory 41, which is used to store instructions executable by a processor; a processor 42, which is used to execute the instructions to implement the following steps:

[0054] S1. Receiving a start mode input of a gas turbine engine;

[0055] S2. If the starting mode received by S1 is a thermal engine start, the opening of the starting air valve 1 is adjustable, and the processor 42 performs closed-loop control according to the actual value of the intake pressure of the air turbine starter 3 sensed by the gas pressure sensor 2 and the required value of the intake pressure;

[0056] If the starting mode received by S1 is non-thermal engine starting, the opening of the starting air valve 1 is fully open or fully closed, and the processor 42 directly instructs the starting air valve 1 to execute full opening or full closing for open-loop control.

[0057] The meaning of the above "hot engine start" and "non-hot engine start" is whether there is a thermal bending effect when the engine starts. "Hot engine start" means that there is a thermal bending effect at the beginning of the start, and "non-hot engine start" means that there is no thermal bending effect at the beginning of the start. The reason why it is defined as a "hot engine start" is that the engine has not been fully cooled down after the last stop when starting, so the engine is still hot, which is called a "hot engine start". The judgment of whether the engine is specifically in "hot engine start" or "non-hot engine start" mode can be obtained through engine test calibration. For example, the time for the engine thermal bending to disappear corresponding to different temperature, pressure and other data is the cooling time. If the time elapsed after the last stop is greater than the cooling time, the starting mode is a non-hot engine start, and if it is below the cooling time, it is a hot engine start.

[0058] like Figure 3A , Figure 3B As shown, corresponding to the thermal engine start, the opening of the starting air valve 1 is adjustable. The adjustable opening here means that it can be adjusted to any position between the fully open position and the fully closed position of the starting air valve 1. In the starting mode of non-thermal engine start, the opening of the starting air valve 1 is only in two positions, fully open or fully closed. At this time, the opening of the starting air valve 1 is non-adjustable because there are only two possible positions, fully open or fully closed.

[0059] Continue to refer Figure 3A , Figure 3BAs shown, the specific steps of closed-loop control based on the actual value of the intake pressure of the air turbine starter 3 sensed by the gas pressure sensor 2 and the required value of the intake pressure can be: the controller 4 calculates the intake pressure requirement of the air turbine starter 3 according to the engine vibration, speed, temperature and pressure signals according to the adjustment plan, and obtains the control instruction of the starting air valve 1 through the control algorithm; the starting air valve 1 receives the control instruction to control the opening of the starting air valve 1, thereby controlling the intake pressure of the air turbine starter 3; the gas pressure sensor 1 feeds back the intake pressure of the air turbine starter 3 to the controller 4, forming a closed-loop control of the intake pressure of the air turbine starter 3. The above control algorithm can be PID, PI or PD algorithm, which is more common and easy to implement. For the starting mode corresponding to non-thermal engine starting, the open-loop control is that the controller 4 directly gives the starting air valve 1 opening / closing instruction, and the starting air valve 1 performs a full opening or full closing action after receiving the instruction.

[0060] The controller 4 of the starting system 100 described above may be integrated into a full authority digital engine controller (FADEC), so that the control system of the gas turbine engine has a high degree of integration.

[0061] 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.

[0062] As described above, the present invention also provides a method for starting a gas turbine engine, comprising:

[0063] S1. Receiving a start mode input of a gas turbine engine;

[0064] S2. If the starting mode received by S1 is a thermal engine start, the opening of the starting air valve 1 is adjustable, and the controller 4 performs closed-loop control according to the actual value of the intake pressure of the air turbine starter 3 sensed by the gas pressure sensor 2 and the required value of the intake pressure;

[0065] If the starting mode received by S1 is non-thermal engine starting, the opening of the starting air valve 1 is fully open or fully closed, and the controller 4 directly instructs the starting air valve 1 to perform open-loop control by fully opening or fully closing.

[0066] According to another aspect of the present invention, a computer-readable medium is also provided.

[0067] 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.

[0068] In addition, the starting system 100 may also include a display module 43 for displaying the starting mode currently corresponding to the processor 42, so that the gas turbine engine operator, generally the pilot, can know the status of the starting process and the time judgment in real time. For example, when the display is a hot engine starting mode, the starting process time is generally longer, while the non-hot engine starting mode is generally shorter. The display module 43 can have a variety of forms. For example, in an airplane, the display module 43 can be a dashboard or a display screen, or even a head-up display (HUD) on the pilot's helmet.

[0069] 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.

[0070] The beneficial effect of the starting method described in the above embodiment is that, by implementing different control strategies for the starting system in the case of hot engine starting and non-hot engine starting, in the case of non-hot engine starting, the starting air valve open-loop control is fully opened to reduce pressure loss and improve the output power of the air turbine starter; and in the case of hot engine starting, the inlet pressure is closed-loop controlled to control the output torque and power of the starter, and then the engine speed is closed-loop controlled. Compared with the scheme of directly controlling the starter speed and directly controlling the air valve opening, the scheme described in the above embodiment can more accurately control the output torque and power of the starter, and can adapt to various different starting external environments, such as adapting to various different aircraft auxiliary power units (APUs), ground air sources or cross-bleed air supply conditions, and can accurately realize the control of the engine speed during the hot engine starting process. When the resonant speed is lower than the engine idling speed, the scheme of the embodiment described above can accurately and stably maintain the engine speed at the time of starting at a resonant speed lower than the resonant speed caused by thermal bending to eliminate thermal bending, and then complete the starting process, so that the starting process is smooth and reliable.

[0071] 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.

[0072] 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.

[0073] 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 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; The processor (42) is used to execute the instructions to implement the following steps: S1. Receiving a start mode input of a gas turbine engine; S2. If the starting mode received by S1 is a thermal engine start, the opening of the starting air valve (1) is adjustable, and the processor (42) performs closed-loop control according to the actual value of the intake pressure of the air turbine starter (3) sensed by the gas pressure sensor (2) and the required value of the intake pressure; If the starting mode received by S1 is non-thermal engine starting, the opening of the starting air valve (1) is fully open or fully closed, and the processor (42) directly instructs the starting air valve (1) to execute full opening or full closing for open-loop control.

2. The starting system (100) according to claim 1, characterized in that: The starting air valve (1) comprises a solenoid valve (11), a control valve (12), an actuator (13), and a butterfly valve (14), wherein the solenoid valve (11) is electrically connected to the controller (4) to receive a control signal from the controller (4) to adjust the action of the control valve (12); the control valve (12) adjusts the gas pressure in the control chamber of the actuator (13) to move the actuator (13); the movement of the actuator (13) drives the butterfly plate of the butterfly valve (14) to rotate, so that the opening of the starting air valve (1) is adjustable.

3. The starting system (100) according to claim 2, characterized in that: The starting air valve (1) further comprises a manual override device (15) and a butterfly valve opening visual device (16), wherein the manual override device (15) is connected to the rotating shaft of the butterfly plate of the butterfly valve (14), and the opening of the butterfly plate can be manually controlled and locked; the butterfly valve opening visual device (16) is directly connected to the rotating shaft of the butterfly plate of the butterfly valve (14), and rotates with the rotation of the butterfly plate, so that the opening of the butterfly valve (14) can be visually observed.

4. The starting system (100) according to claim 1, characterized in that: The controller (4) is integrated into a Full Authority Digital Engine Control (FADEC).

5. The starting system (100) according to claim 1, characterized in that: The gas pressure sensor (2) is integrated on the starting air valve (1) or the air turbine starter (3), or is arranged on the air duct (5).

6. The starting system (100) according to claim 1, characterized in that: In S2, the control algorithm of the closed-loop control includes a PID, PI or PD algorithm.

7. A gas turbine engine, characterized in that: It comprises a starting system (100) as described in any one of claims 1 to 6 and a rotor, wherein the starting system is capable of driving the rotor to rotate.

8. A method for starting a gas turbine engine, characterized in that: A starting system (100) is used, comprising a starting air valve (1), a gas pressure sensor (2), an air turbine starter (3), a controller (4) and an air conduit (5); 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); 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); the starting method comprises: S1. Receiving a start mode input of a gas turbine engine; S2. If the starting mode received by S1 is a thermal engine start, the opening of the starting air valve (1) is adjustable, and the controller (4) performs closed-loop control according to the actual value of the intake pressure of the air turbine starter (3) sensed by the gas pressure sensor (2) and the required value of the intake pressure; If the starting mode received by S1 is non-thermal engine starting, the opening of the starting air valve (1) is fully open or fully closed, and the controller (4) directly instructs the starting air valve (1) to execute full opening or full closing to perform open-loop control.

9. The starting method according to claim 8, characterized in that: The starting mode is a thermal engine start and there is a thermal bending effect on the engine rotor.

10. 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 startup method as claimed in claim 8 or 9.

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