Air turbine starter with gunpowder starting function and large aircraft

Abstract

The invention discloses an air turbine starter with a gunpowder starting function and a large aircraft, comprising a turbine unit, a guide cavity, an air bleed pipe, a transmission shaft, a transmission mechanism and a gunpowder starting device. The air bleed pipe is provided with a first interface for connecting to a high-pressure gas source device, a second interface for connecting to the gunpowder starting device, a third interface for connecting to the guide cavity and a partition for switching the third interface to be connected to the first interface or to the second interface. The gunpowder starting device is used to quickly drive the turbine blades of the turbine unit to rotate, thereby driving the large aircraft power device to rotate through the transmission shaft, so that the large aircraft can take off within a few minutes without affecting the large aircraft power device, and can achieve repeated gunpowder starting by replacing the gunpowder starting device, which can meet the emergency take-off requirements of large aircraft in emergency conditions and has great promotion value.

Description

Technical Field

[0001] The present invention relates to the technical field of aeroengines, and in particular to an air turbine starter with a gunpowder starting function. In addition, the present invention also relates to a large aircraft comprising the air turbine starter with a gunpowder starting function. Background Art

[0002] The power systems of large aircraft are all started by air turbine starters. Air turbine starters require a high-pressure air source to work. The working principle of air turbine starters for large aircraft is: high-pressure air is introduced into the turbine unit of the air turbine starter through a dedicated high-pressure air source. The air passes through the turbine blades and rotates at high speed to generate power, thereby driving the transmission device, and then driving the power system of the large aircraft to rotate.

[0003] At present, the methods of providing high-pressure air sources for air turbine starters of large aircraft usually adopt two methods: providing high-pressure air sources on the airport ground and manufacturing high-pressure air sources with the auxiliary power unit of the aircraft. For large aircraft with multiple power units, these two starting methods require dozens of minutes of preparation to start all the power systems of the large aircraft. The take-off preparation time is too long, which greatly affects the execution of emergency tasks. If it is necessary to take off multiple aircraft at the same time, the take-off requirements cannot be met. In addition, in the case of no airport ground guarantee and the aircraft's own auxiliary power unit cannot be used, the power system of the large aircraft lacks a backup starting plan.

[0004] Gunpowder is also partially used in today's aviation power starting field. It is generally used in the micro-turbojet engine of missiles. The basic principle is to place gunpowder in the combustion chamber and use gunpowder to generate high-temperature and high-pressure gas. The gas impacts the turbine blades of the micro-turbojet engine to drive the rotor to rotate, thereby completing the engine ignition and starting process. Since the missile itself does not need to be reused, the gunpowder starter only needs to be used once, so the gunpowder can be placed in the combustion chamber when assembling the turbojet engine. If a large aircraft adopts this structure, the gunpowder starter cannot be reused, and there is a problem of being unable to start again after stopping in the middle of the journey. In addition, the high-temperature and high-pressure gas generated by the explosion of gunpowder directly blows the turbine blades of the large aircraft power device, which will cause damage to the turbine blades of the large aircraft power device, affecting the service life and even the stability of the flight. Summary of the invention

[0005] The present invention provides an air turbine starter with a gunpowder starting function to solve the technical problems that the existing air turbine starter of large aircraft takes too long to start the power device of large aircraft, greatly affecting the execution of emergency tasks, and lacks a backup starting solution.

[0006] According to one aspect of the present invention, there is provided an air turbine starter with a gunpowder starting function, comprising a turbine unit, a guide cavity for introducing high-pressure air into the turbine unit, an air bleed pipe for introducing high-pressure air into the guide cavity, a transmission shaft for driving a power system of an aircraft, a transmission mechanism for connecting the turbine unit and the transmission shaft, and a gunpowder starting device for use in an emergency state to generate high-temperature and high-pressure gas, wherein the air bleed pipe is provided with a first interface for connecting to a high-pressure gas source device, a second interface for connecting to the gunpowder starting device, a third interface for connecting to the guide cavity, and a partition for switching the third interface to be connected to the first interface or to the second interface.

[0007] Furthermore, a stop ring adapted to the partition and a hinge seat for hingedly connecting the partition are arranged on the inner circumferential wall of the air duct, the stop ring is arranged between the first interface and the second interface, and the hinge seat is arranged between the stop ring and the second interface.

[0008] Furthermore, a first sealing arc adapted to the inner diameter of the stop ring and a second sealing arc adapted to the inner diameter of the second interface are arranged on the partition.

[0009] Furthermore, the hinge seat is arranged at the bottom end of the inner circumferential wall of the air duct, and the center of gravity of the partition is offset toward the first sealing arc.

[0010] Furthermore, the gunpowder starting device includes a placement tube connected to the second interface, a bottom plug forming a receiving cavity with the placement tube, a gunpowder column arranged in the receiving cavity, and a firing pin arranged on the bottom plug for igniting the gunpowder column.

[0011] Furthermore, the firing pin is arranged at the center position of the bottom plug.

[0012] Furthermore, the bottom end of the placing cylinder is provided with a first clamping ring extending radially outwardly thereof, and the top end of the bottom plug is provided with a second clamping ring extending radially outwardly thereof, the first clamping ring and the second clamping ring are connected by a clamp, the clamp comprises a first clamp, a second clamp and a lock, the first end of the first clamp is hinged to the first end of the second clamp, the inner walls of the first clamp and the second clamp are respectively provided with grooves, the grooves are adapted to the first clamp and the second clamp, a first fastening frame is provided on the second end of the first clamp, a second fastening frame is provided on the second end of the second clamp, a U-shaped groove is provided on the first fastening frame and the second fastening frame respectively, the lock comprises a connecting rod adapted to the U-shaped groove and a locking head arranged on the first end of the connecting rod, and the second end of the connecting rod is hinged to the second fastening frame through a hinge shaft.

[0013] Furthermore, the gunpowder column includes an outer metal shell adapted to the inner diameter of the placement tube, a primer layer arranged at the bottom end of the outer metal shell, and a solid gunpowder layer filled in the outer metal shell.

[0014] Furthermore, a stopper is arranged on the outer side wall of the bottom end of the outer metal shell, and a slot adapted to the stopper is arranged on the placement tube.

[0015] According to another aspect of the present invention, there is also provided a large aircraft characterized in that it has the above-mentioned air turbine starter with a gunpowder starting function.

[0016] The present invention has the following beneficial effects:

[0017] The air turbine starter with gunpowder starting function of the present invention, when started in a conventional manner, the partition blocks the second interface, the third interface is connected to the first interface, the high-pressure air provided by the high-pressure air source device is axially introduced into the turbine unit through the first interface, the third interface, and the guide cavity, the high-pressure air drives the turbine blades of the turbine unit to rotate at a high speed to generate power, the turbine blades drive the transmission mechanism to drive the transmission shaft, thereby driving the rotation of the power system of the aircraft; when started in an emergency state, the partition blocks the first interface, the third interface is connected to the second interface, the high-temperature and high-pressure gas generated by the ignition of the gunpowder starting device is axially introduced into the turbine unit through the second interface, the third interface, and the guide cavity, which can quickly drive the turbine blades of the turbine unit to rotate, thereby driving the large aircraft power device to rotate through the transmission shaft, and enabling the large aircraft to take off within a few minutes, the guide cavity guides the high-temperature and high-pressure gas to blow the radially installed The turbine blades of the air turbine starter are uniformly stressed, and the loss of the turbine blades of the air turbine starter can be reduced. The turbine of the air turbine starter has high efficiency and long service life. In addition, since the high-temperature and high-pressure gas generated by the combustion of the gunpowder starting device impacts the turbine blades of the air turbine starter, it will not affect the turbine blades of the power unit of the large aircraft, and the service life and flight stability of the power unit of the large aircraft can be guaranteed. The air bleed pipe is a three-way pipe structure, and the gunpowder starting device is arranged on the air bleed pipe. The second interface is used to introduce the high-temperature and high-pressure gas generated by the combustion of the gunpowder starting device into the guide cavity. Repeated gunpowder starting can be achieved by replacing the gunpowder starting device, which can meet the emergency take-off requirements of large aircraft in emergency situations. It can provide a third starting backup for the power unit of large aircraft when there is no airport ground guarantee and the auxiliary power unit of the aircraft cannot be used, and has great promotion value.

[0018] In addition to the above-described objects, features and advantages, the present invention has other objects, features and advantages. The present invention will be further described in detail with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The drawings constituting a part of this application are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings:

[0020] Figure 1 1 is a schematic structural diagram of an air turbine starter with a gunpowder starting function according to a preferred embodiment of the present invention;

[0021] Figure 2 is a schematic structural diagram of an air duct according to a preferred embodiment of the present invention;

[0022] Figure 3 is a schematic diagram of the structure of the first interface and the third interface of a preferred embodiment of the present invention;

[0023] Figure 4 is a schematic structural diagram of the second interface and the third interface in a preferred embodiment of the present invention being connected;

[0024] Figure 5 is a schematic structural diagram of a partition in a preferred embodiment of the present invention;

[0025] Figure 6 It is a structural schematic diagram of a gunpowder starting device according to a preferred embodiment of the present invention;

[0026] Figure 7 It is a structural schematic diagram of the connection between the placement cylinder and the bottom plug in a preferred embodiment of the present invention;

[0027] Figure 8 is a schematic structural diagram of a clamp according to a preferred embodiment of the present invention;

[0028] Fig. 9 It is a cross-sectional view of the connection between the placement cylinder and the bottom plug in a preferred embodiment of the present invention.

[0029] Legend:

[0030] 1. air duct; 11. first interface; 12. second interface; 13. third interface; 14. partition; 141. first sealing arc; 142. second sealing arc; 15. stop ring; 16. hinge seat; 2. flow guide chamber; 3. turbine unit; 4. transmission mechanism; 5. transmission shaft; 6. gunpowder starting device; 61. placement tube; 611. first clamp ring; 62. bottom plug; 621. second clamp ring; 63. gunpowder column; 631. outer metal shell; 632. primer layer; 633. solid gunpowder layer; 634. stopper; 64. firing pin; 65. clamp; 651. first clamp; 652. second clamp; 653. groove; 654. first fastening frame; 655. second fastening frame; 656. U-shaped groove; 657. hinge shaft; 658. connecting rod; 659. lock. DETAILED DESCRIPTION

[0031] The embodiments of the present invention are described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below.

[0032] Please also read Figures 1 to 9 The air turbine starter with a gunpowder starting function of this embodiment includes a turbine unit 3, a guide cavity 2 for introducing high-pressure air into the turbine unit 3, an air bleed pipe 1 for introducing high-pressure air into the guide cavity 2, a transmission shaft 5 for driving a power system of an aircraft, a transmission mechanism 4 for connecting the turbine unit 3 and the transmission shaft 5, and a gunpowder starting device 6 for generating high-temperature and high-pressure gas in an emergency state. The air bleed pipe 1 is provided with a first interface 11 for connecting a high-pressure gas source device, a second interface 12 for connecting the gunpowder starting device 6, a third interface 13 for connecting to the guide cavity 2, and a partition 14 for switching the third interface 13 to be connected to the first interface 11 or to be connected to the second interface 12.

[0033] The air turbine starter with gunpowder starting function of this embodiment, when started in a conventional manner, the partition 14 blocks the second interface 12, the third interface 13 is connected to the first interface 11, and the high-pressure air provided by the high-pressure gas source device is axially introduced into the turbine unit 3 through the first interface 11, the third interface 13, and the guide chamber 2. The high-pressure air drives the turbine blades of the turbine unit 3 to rotate at a high speed to generate power, and the turbine blades drive the transmission mechanism 4 to drive the transmission shaft 5, thereby driving the rotation of the power system of the aircraft; when starting in an emergency state, the partition 14 blocks the first interface 11, the third interface 13 is connected to the second interface 12, and the high-temperature and high-pressure gas generated by the ignition of the gunpowder starting device 6 is axially introduced into the turbine unit 3 through the second interface 12, the third interface 13, and the guide chamber 2, which can quickly drive the turbine blades of the turbine unit 3 to rotate, thereby driving the large aircraft power device to rotate through the transmission shaft 5, and enabling the large aircraft to take off within a few minutes. The guide chamber 2 guides the high-temperature and high-pressure gas. The high-pressure gas blows the radially installed turbine blades evenly along the axial direction, and each turbine blade bears the force evenly, which can reduce the loss of the turbine blades of the air turbine starter. The turbine of the air turbine starter has high efficiency and long service life. In addition, since the high-temperature and high-pressure gas generated by the combustion of the gunpowder starting device 6 impacts the turbine blades of the air turbine starter, it will not affect the turbine blades of the large aircraft power unit, which can ensure the service life and flight stability of the large aircraft power unit. The air bleed pipe 1 is a three-way pipe structure, and the gunpowder starting device 6 is arranged on the air bleed pipe 1. The second interface 12 is used to introduce the high-temperature and high-pressure gas generated by the combustion of the gunpowder starting device 6 into the guide cavity 2. Repeated gunpowder starting can be achieved by replacing the gunpowder starting device 6, which can meet the emergency take-off requirements of large aircraft in emergency conditions, and can provide a third starting backup for the large aircraft power unit when there is no airport ground guarantee and the aircraft's own auxiliary power unit cannot be used, which has great promotion value.

[0034] like Figure 2 As shown, in this embodiment, a stop ring 15 adapted to the partition 14 and an articulated seat 16 for articulating the partition 14 are arranged on the inner circumferential wall of the air duct 1, the stop ring 15 is arranged between the first interface 11 and the second interface 12, and the articulated seat 16 is arranged between the stop ring 15 and the second interface 12; the partition 14 includes a metal plate and a bar handle arranged on the metal plate and extending outward along the radial direction of the metal plate, the bar handle is articulated with the articulated seat 16 through a pin shaft, and the first interface 11 and the second interface 12 can be switched by flipping the partition 14. Optionally, the partition 14 is driven by a driving mechanism to achieve flipping, and the driving mechanism is a gear rack mechanism driven by an oil cylinder, an air cylinder or a motor, and the driving mechanism is arranged on the side of the partition 14 away from the second interface 12 to avoid being damaged by high-temperature and high-pressure gas.

[0035] like Figure 5 As shown, in this embodiment, a first sealing arc 141 adapted to the inner diameter of the stop ring 15 and a second sealing arc 142 adapted to the inner diameter of the second interface 12 are arranged on the partition 14. The first sealing arc 141 can reduce the gap between the stop ring 15 and the partition 14, thereby preventing the high-temperature and high-pressure gas generated by the combustion of the gunpowder starting device 6 from leaking from the first interface 11; the second sealing arc 142 can reduce the gap between the partition 14 and the second interface 12, and can prevent the high-pressure air from leaking from the second interface 12.

[0036] like Figure 5As shown, in this embodiment, the hinge seat 16 is arranged at the bottom end of the inner circumferential wall of the air duct 1, and the center of gravity of the partition 14 is offset to the first sealing arc 141. When the gunpowder starting device 6 is started, the partition 14 is impacted by the high-temperature and high-pressure gas and abuts against the stop ring 15. Since the center of gravity of the partition 14 is offset to the first sealing arc 141, even after the high-temperature and high-pressure gas generated in the late combustion of the gunpowder starting device 6 is reduced, the partition 14 can be ensured to abut against the stop ring 15, so as to avoid the partition 14 from falling due to gravity and blocking the second interface 12. The second interface 12 is always connected with the third interface 13, so as to ensure that the high-temperature and high-pressure gas can It smoothly enters the guide cavity 2; during normal starting, the high-pressure air introduced from the first interface 11 impacts the partition 14, and the partition 14 falls to cover the second interface 12. It has a simple structure and is easy to install. The action of the partition 14 blocking the first interface 11 is completed by the impact of the high-temperature and high-pressure gas generated by the combustion of the gunpowder starting device 6. When normal starting is required, after the first interface 11 is connected to the high-pressure gas source, the partition 14 automatically falls back to its position under the impact of the high-pressure gas source to complete the blocking of the second interface 12. No additional power is required to drive the partition 14 to switch the blocking position, which can not only reduce the manufacturing cost, but also reduce the overall weight of the air turbine starter. Optionally, when the partition 14 abuts against the stop ring 15, the center line of the partition 14 is arranged in the vertical direction. Optionally, when the partition 14 abuts against the stop ring 15, the center line of the partition 14 tilts toward the stop ring 15, so that the partition 14 abuts against the stop ring 15 due to gravity. On the one hand, the flipping angle of the partition 14 can be greater than 90° by increasing the distance between the hinge seat 16 and the stop ring 15; on the other hand, the radial plane of the stop ring 15 can be tilted so that the distance from the upper end of the stop ring 15 to the vertical plane is greater than the distance from the lower end of the stop ring 15 to the vertical plane, which can also make the flipping angle of the partition 14 greater than 90°.

[0037] like Figure 2 As shown, in this embodiment, the gunpowder starting device 6 includes a placement tube 61 connected to the second interface 12, a bottom plug 62 forming a receiving cavity with the placement tube 61, a gunpowder column 63 arranged in the receiving cavity, and a striker 64 arranged on the bottom plug 62 for igniting the gunpowder column 63; the bottom plug 62 is disc-shaped and detachably connected to the outer port of the placement tube 61, which can block the outer port of the placement tube 61 and form a receiving cavity, and the bottom plug 62 withstands the recoil of the gunpowder column 63 deflagration while preventing the high-temperature and high-pressure gas generated by the combustion of the gunpowder column 63 from leaking out. Optionally, the abutting surfaces of the placement tube 61 and the bottom plug 62 are respectively provided with skirts extending radially outward. On the one hand, the skirts can increase the abutting area between the placement tube 61 and the bottom plug 62, thereby extending the sealing surface between the placement tube 61 and the bottom plug 62 along the radial direction of the placement tube 61, thereby ensuring the sealing effect.

[0038] like Figure 6As shown, in this embodiment, the firing pin 64 is remotely controlled by the control system, and the firing pin 64 is remotely controlled by the control system to strike and ignite the gunpowder column 63, thereby releasing high-temperature and high-pressure gas. The firing pin 64 is arranged at the center of the bottom plug 62, which can make the gunpowder column 63 burn fully and instantly.

[0039] like Figure 7 , Figure 8 and Fig. 9 As shown, in this embodiment, a first clamping ring 611 extending radially outward is arranged at the bottom end of the placement cylinder 61, and a second clamping ring 621 extending radially outward is arranged at the top end of the bottom plug 62. The first clamping ring 611 and the second clamping ring 621 are connected by a clamp 65. The clamp 65 includes a first clamp 651, a second clamp 652 and a lock. The first end of the first clamp 651 is hinged to the first end of the second clamp 652. The inner walls of the first clamp 651 and the second clamp 652 are respectively provided with grooves 653, and the grooves 653 are adapted to the first clamp 611 and the second clamp 621. A first fastening frame 654 is arranged on the second end of the first clamp 651, and a second fastening frame 655 is arranged on the second end of the second clamp 652. The first fastening frame 654 and the second fastening frame 655 are respectively provided with U-shaped grooves 656, and the lock includes a U-shaped groove 656. 56 is adapted to the connecting rod 658 and the lock head 659 arranged on the first end of the connecting rod 658, and the second end of the connecting rod 658 is hinged to the second fastening frame 655 through the hinge shaft 657; when assembling, the lock head 659 is pushed forward to make the connecting rod 658 rotate around the hinge shaft 657, and when the connecting rod 658 is fully pushed into the U-shaped groove 656 on the first fastening frame 654, the lock head 659 cooperates with the first fastening frame 654 to achieve limiting, and the first clamping ring 611 on the placement tube 61 and the second clamping ring 621 on the bottom plug 62 are clamped through the groove 653; when disassembling, the lock head 659 is pushed backward, and the lock head 659 is separated from the first fastening frame 654 to remove the clamp 65; it has a simple structure, is easy to disassemble and assemble, and is firmly connected. Compared with the connection through bolts or threads, it can further save the time for disassembling and assembling the gunpowder starting device 6, thereby reducing the preparation time for take-off in an emergency state.

[0040] like Figure 2 and Figure 6 As shown, in this embodiment, the gunpowder column 63 includes an outer metal shell 631 adapted to the inner diameter of the placement tube 61, a primer layer 632 arranged at the bottom of the outer metal shell 631, and a solid gunpowder layer 633 filled in the outer metal shell 631. The solid gunpowder layer 633 is ignited by the striker 64 hitting the primer layer 632 to release high-temperature and high-pressure combustion gas.

[0041] like Figure 6As shown, in this embodiment, a stop 634 is arranged on the outer wall of the bottom end of the outer metal shell 631, and a groove adapted to the stop 634 is arranged on the placing tube 61; the stop 634 on the outer metal shell 631 cooperates with the groove on the placing tube 61 to limit the axial position of the gunpowder column 63 in the placing tube 61, which can prevent the gunpowder column 63 from moving in the placing tube 61 and ensure that the firing pin 64 can smoothly ignite the primer layer 632.

[0042] A large aircraft is characterized in that the above-mentioned air turbine starter with gunpowder starting function is itself equipped with a gunpowder starting device 6, which can use the high-temperature and high-pressure gas generated by the gunpowder starting device 6 to drive the turbine unit 3 in an emergency state, so that the outer starter works, which can solve the problem that the air turbine starter of the current large aircraft power unit cannot independently complete the starting work and the starting time of the large aircraft power unit is too long; because the gunpowder starting device 6 is arranged on the air bleed pipe 1, it does not affect the use of conventional high-pressure gas source starting, and can achieve repeated starting in an emergency state by replacing the gunpowder starting device 6. It can provide a third starting backup for the large aircraft power unit when there is no airport ground guarantee and the aircraft's own auxiliary power unit cannot be used, which has great promotion value.

[0043] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. An air turbine starter with a gunpowder starting function, characterized in that: The invention comprises a turbine unit (3), a flow guide cavity (2) for introducing high-pressure air into the turbine unit (3), an air bleed pipe (1) for introducing high-pressure air into the flow guide cavity (2), a transmission shaft (5) for driving a power system of an aircraft, a transmission mechanism (4) for connecting the turbine unit (3) and the transmission shaft (5), and a gunpowder starting device (6) for generating high-temperature and high-pressure gas in an emergency state, wherein the air bleed pipe (1) is provided with a first interface (11) for connecting to a high-pressure gas source device, a second interface (12) for connecting to the gunpowder starting device (6), and a second interface (13) for connecting to the air bleed pipe (1). The invention relates to a third interface (13) of the flow cavity (2) and a partition (14) for switching the third interface (13) to communicate with the first interface (11) or the second interface (12). The gunpowder starting device (6) comprises a placement tube (61) in communication with the second interface (12), a bottom plug (62) forming a receiving cavity with the placement tube (61), a gunpowder column (63) arranged in the receiving cavity, and a striker (64) arranged on the bottom plug (62) for igniting the gunpowder column (63). The bottom end of the placement tube (61) is provided with a first clamping ring (64) extending radially outwards thereof. 611), a second clamping ring (621) extending radially outward is arranged at the top end of the bottom plug (62), the first clamping ring (611) and the second clamping ring (621) are connected via a clamp (65), the clamp (65) comprises a first clamp (651), a second clamp (652) and a lock, the first end of the first clamp (651) is hinged to the first end of the second clamp (652), the inner walls of the first clamp (651) and the second clamp (652) are respectively provided with grooves (653), the grooves (653) and the first clamp (611) and the second clamp (652) are respectively provided with grooves (653), and the grooves (653) and the first clamp (611) and the second clamp (652) are respectively provided with grooves (653). A second clamping ring (621) is adapted, a first fastening frame (654) is arranged on the second end of the first clamping hoop (651), a second fastening frame (655) is arranged on the second end of the second clamping hoop (652), the first fastening frame (654) and the second fastening frame (655) are respectively provided with a U-shaped groove (656), the locking comprises a connecting rod (658) adapted to the U-shaped groove (656) and a locking head (659) arranged on the first end of the connecting rod (658), and the second end of the connecting rod (658) is hinged to the second fastening frame (655) through a hinge shaft (657).

2. The air turbine starter with gunpowder starting function according to claim 1, characterized in that: A stop ring (15) adapted to the partition (14) and a hinge seat (16) for hingedly connecting the partition (14) are arranged on the inner circumferential wall of the air duct (1), the stop ring (15) being arranged between the first interface (11) and the second interface (12), and the hinge seat (16) being arranged between the stop ring (15) and the second interface (12).

3. The air turbine starter with gunpowder starting function according to claim 2, characterized in that: The partition plate (14) is provided with a first sealing arc (141) adapted to the inner diameter of the stop ring (15) and a second sealing arc (142) adapted to the inner diameter of the second interface (12).

4. The air turbine starter with gunpowder starting function according to claim 3, characterized in that: The hinge seat (16) is arranged at the bottom end of the inner circumferential wall of the air duct (1), and the center of gravity of the partition plate (14) is offset toward the first sealing arc (141).

5. The air turbine starter with a powder starting function according to any one of claims 1 to 4, characterized in that: The striker (64) is arranged at the center of the bottom plug (62).

6. The air turbine starter with a gunpowder starting function according to any one of claims 1 to 4, characterized in that: The gunpowder column (63) comprises an outer metal shell (631) adapted to the inner diameter of the placement tube (61), a primer layer (632) arranged at the bottom end of the outer metal shell (631), and a solid gunpowder layer (633) filled in the outer metal shell (631).

7. The air turbine starter with gunpowder starting function according to claim 6, characterized in that: A stopper (634) is arranged on the outer side wall of the bottom end of the outer metal shell (631), and a slot adapted to the stopper (634) is arranged on the placement tube (61).

8. A large aircraft, characterized in that: An air turbine starter with a powder starting function comprising any one of claims 1 to 7.

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