A turboshaft engine gas storage system and method

Abstract

The present application relates to a kind of turbo-shaft engine gas storage system and method, belong to turbo-shaft engine field, including engine body, air storage structure, controller, still including bleed air valve seat, bleed air pipe, air collector, the bleed air valve seat is located on the compressor casing of engine body, the bleed air valve seat is close to the diffuser outlet of engine body, one end of the bleed air pipe is located on bleed air valve seat, the other end of the bleed air pipe is communicated with air collector, the air collector is communicated with air storage structure, the air storage structure is communicated with the air inlet of engine body, air pipe is equipped on the air collector.The high-pressure gas in the engine body and atmospheric air are collected by the air collector, and are pressurized and stored by air storage structure, not only realize self-circulation system, but also improve engine starting difficulty and make up take-off power, reduce the dependence on ground device auxiliary.

Description

TECHNICAL FIELD

[0001] The present application belongs to the field of turboshaft engines, and particularly relates to a turboshaft engine gas storage system and method. BACKGROUND

[0002] With the increase of altitude, the air is thinner, the atmospheric temperature and atmospheric pressure are lower, and the starting success rate of the aviation turboshaft engine gradually decreases. At the same time, the power output by the gas generator at a lower speed is smaller, which makes the aviation turboshaft engine have starting difficulties and insufficient power on the plateau.

[0003] The main reasons for the starting difficulties and insufficient power of the aviation turboshaft engine are reflected in the starting suspension and the insufficient power for taking off from the ground. There are three main reasons for the starting suspension. First, the on-board battery power decreases rapidly during the starting process, the starting machine belt speed is low, second, the starting machine is disconnected at a low speed, and third, the turbine belt power is insufficient. In view of the three reasons, the existing countermeasures mainly include equipping with a ground power supply vehicle and optimizing the starting law. For the aviation engine started by the starting machine belt, in order to ensure smooth starting, the airport needs to be equipped with a ground power supply vehicle to provide stable power, so as to increase the belt speed and provide more starting power for the engine. Optimizing the starting law is to optimize the fuel supply law, the starting machine belt speed and time, etc. through a large number of ground and plateau starting test data, to obtain a starting law suitable for the plateau. In the actual application process, the aviation turboshaft engine needs to coordinate the airport staff to prepare the ground power supply vehicle in advance before starting, which prolongs the take-off time of the aircraft and increases the workload of the airport. For the temporary stopover airport without ground power supply vehicle, it may lead to the aircraft unable to perform flight tasks. The defect of optimizing the starting law is that the engine may be limited by hardware, and no matter how the starting law is optimized, it is difficult to improve the plateau starting success rate, and the time cost and material cost of changing the hardware are too high.

[0004] The insufficient power for taking off from the ground is mainly due to the power attenuation of the turboshaft engine on the plateau due to the thin air. At the same speed of the gas generator, all the power output is small, which may lead to the failure to take off normally. In view of this problem, the existing countermeasures mainly have three ways. First, replacing the engine with a higher power level, second, reducing the weight of the aircraft, and third, the helicopter can take off from the ground by sliding. However, replacing the engine with a higher power level has high cost and long cycle, and if the engine is not replaced, the weight of the aircraft needs to be reduced, which also reduces the load capacity and economy of the aircraft. Although the helicopter can take off by sliding, it puts forward higher requirements for the length of the airport runway, which goes against the convenience of the helicopter landing and taking off.

[0005] In order to solve the above problems, the application establishes a self-circulation system capable of storing high-pressure gas generated by the engine to improve the starting difficulty and make up for the insufficient take-off power, reduces the dependence on ground device assistance, and solves the problems of helicopter starting difficulty and insufficient take-off power on the plateau. SUMMARY

[0006] In order to solve the above problems, the application provides a turboshaft engine gas storage system, which comprises an engine body, an air storage structure, a controller, an air bleed valve seat, an air bleed pipe and an air collector, the air bleed valve seat is arranged on the compressor casing of the engine body, the air bleed valve seat is close to the diffuser outlet of the engine body, one end of the air bleed pipe is arranged on the air bleed valve seat, the other end of the air bleed pipe is communicated with the air collector, the air collector is communicated with the air storage structure, the air storage structure is communicated with the air inlet of the engine body, the air pipe is arranged on the air collector, and the air storage structure, the air collector and the air bleed valve seat are electrically connected with the controller.

[0007] Further, the air storage structure comprises a pressure pump, a storage device, a flow valve, an air inlet pipe and a gas conveying pipe, the storage device is communicated with the air collector through the air inlet pipe, the pressure pump is arranged on the air inlet pipe, the gas conveying pipe is arranged on the storage device, one end of the gas conveying pipe away from the air storage device is connected with the air inlet of the engine body, the part of the gas conveying pipe close to the air inlet is arranged in a slanting manner, the flow valve is arranged on the gas conveying pipe, and the pressure pump and the storage device are electrically connected with the controller.

[0008] Further, the gas conveying pipe comprises a communication pipe, a circular arc pipe and a gas guide pipe in sequence along the vertical direction, the communication pipe is communicated with the circular arc pipe, a plurality of gas guide pipes are uniformly arranged on the side of the circular arc pipe away from the communication pipe, the communication pipe is communicated with the storage device, the circular arc pipe is sleeved on the casing of the compressor, one end of the gas guide pipe away from the circular arc pipe penetrates through the casing and is communicated with the air inlet of the engine body, and the flow valve is arranged on the communication pipe.

[0009] Further, a second mass flow meter is arranged at the position between the flow valve and the circular arc pipe.

[0010] A turboshaft engine gas storage method, comprising the following steps:

[0011] During the starting on the plateau, the air electronic instruction is sent to the air storage structure, the air storage structure is opened, and the high-pressure air in the air storage structure enters the engine body after being corrected;

[0012] When the pressure in the air storage structure is lower than the preset pressure, the pressure signal is sent to the controller, the controller receives the pressure signal, sends the air collection signal to the air collector and the air bleed valve seat, and sends the pressurization and storage signal to the air storage structure;

[0013] When the diffuser bleed air preset condition is met, the high-pressure air after the diffuser outlet is collected by opening the bleed air valve seat, filtered by the air collector, and then delivered to the air storage structure for storage.

[0014] When the ambient atmospheric bleed air preset condition is met, the air collector and air pipe are used to collect external air, which is filtered by the air collector and then delivered to the air storage structure for pressurization and storage.

[0015] During the engine body starting process, high-pressure air is continuously introduced, and after successful starting, the air storage structure is closed.

[0016] Further, when the high-pressure air pressure after the diffuser outlet is less than the set pressure of the air storage structure, start the pressure pump for secondary pressurization.

[0017] Further, during highland starting, send an avionics command to the flow valve, open the flow valve, and push the engine state to take-off power. The high-pressure air mixes with the air sucked by the engine body and enters the compressor, is compressed into high-pressure air by the centrifugal impeller in the compressor, and then enters the combustion chamber after being expanded by the diffuser.

[0018] Further, the diffuser bleed air preset condition includes:

[0019] The engine body working state is greater than or equal to the in-flight idle state;

[0020] Tt45 < T45 max -△T45;

[0021] The pilot has not manually closed the high-pressure gas production;

[0022] The storage device is not full of gas;

[0023] Wherein, Tt45 is the turbine inlet temperature; T45 max is the turbine inlet temperature limit; △T45 is the turbine inlet temperature increment.

[0024] Further, the ambient atmospheric bleed air preset condition includes:

[0025] During the engine body starting process;

[0026] During the engine body climbing process;

[0027] One engine fails and works alone;

[0028] The pilot manually closes the high-pressure gas production;

[0029] Tt45 ≥ T45 max -△T45;

[0030] The storage device is not full of gas;

[0031] Wherein, Tt45 is turbine inlet temperature; T45 max is turbine inlet limit temperature; △T45 is turbine inlet temperature increment.

[0032] Further, the correction formula is as follows:

[0033]

[0034] Wherein, Wa H is engine body intake air flow;

[0035] Wf H is engine body initial fuel flow;

[0036] Wa 额定 is engine body rated intake air flow;

[0037] Wf H-修正 is corrected fuel flow after high-pressure air is introduced.

[0038] Compared with the prior art, the present application has the beneficial effects that:

[0039] 1) The present application collects high-pressure gas and atmospheric air in the engine body through the air collector, and pressurizes and stores the air through the air storage structure, which not only realizes a self-circulation system, but also improves engine starting difficulty and makes up for take-off power, reducing the dependence on ground device assistance.

[0040] 2) The present application stores high-pressure gas generated by the engine, which makes up for the shortcomings of high-altitude air thinness and narrow engine flameout boundary.

[0041] 3) The present application improves the engine highland starting success rate and take-off power through self-circulation, reduces the dependence on ground device assistance, expands the helicopter highland use environment, and can cope with different complex topography.

[0042] 4) The present application promotes ram effect through the pressure difference between the high-pressure air introduced into the intake duct and the atmospheric air after the engine body tail nozzle, which is more conducive to engine starting.

[0043] Other features and advantages of the present application will be set forth in the following description, and in part will become apparent to those skilled in the art from the description, or can be learned by practice of the present application. The objects and other advantages of the present application can be achieved and obtained by the structure as indicated in the specification, claims and drawings. BRIEF DESCRIPTION OF DRAWINGS

[0044] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed in the embodiments or prior art description. Obviously, the drawings described below are only some embodiments of the present application, and for those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative labor.

[0045] Figure 1 A system diagram according to an embodiment of the present application is shown;

[0046] Figure 2 A connection diagram of the air supply pipe and the engine body is shown;

[0047] Figure 3 A perspective view of Figure 2 is shown;

[0048] Figure 4 A sectional view of A-A in Figure 2 is shown;

[0049] Figure 5 A partial enlarged view of B in Figure 4 is shown.

[0050] Reference signs: 1, engine body; 11, speed reducer; 12, compressor; 121, air inlet channel; 122, first mass flow meter; 123, diffuser; 124, centrifugal impeller; 125, impeller cover; 13, casing; 14, combustion chamber; 15, turbine; 16, tail nozzle; 2, bleed air valve seat; 21, bleed air pipe; 3, air collector; 31, air pipe; 4, controller; 5, storage device; 51, air inlet pipe; 52, pressure pump; 53, air supply pipe; 531, communication pipe; 532, flow valve; 533, second mass flow meter; 54, circular arc pipe; 55, air guide pipe. DETAILED DESCRIPTION

[0051] In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the following will combine the drawings in the embodiments of the present application to make a clear and complete description of the technical solutions in the embodiments of the present application. Obviously, the described embodiments are some of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative labor fall within the protection scope of the present application.

[0052] Figure 1 A device diagram according to an embodiment of the present application is shown. As Figure 1As shown, a turboshaft engine air storage system includes an engine body 1, an air storage structure, a controller 4, and further includes a bleed valve seat 2, a bleed pipe 21, and an air collector 3, the bleed valve seat 2 is arranged on a compressor 12 casing 13 of the engine body 1, the bleed valve seat 2 is close to an outlet of a diffuser 123 of the engine body 1, one end of the bleed pipe 21 is arranged on the bleed valve seat 2, the other end of the bleed pipe 21 is communicated with the air collector 3, the air collector 3 is communicated with the air storage structure, the air storage structure is communicated with an air inlet 121 of the engine body 1, the air collector 3 is provided with an air pipe 31, and the air storage structure, the air collector 3 and the bleed valve seat 2 are electrically connected with the controller 4.

[0053] The turboshaft engine air storage system realizes the storage of high-pressure gas and atmospheric air by the air collector 3, the air pipe 31, the bleed valve seat 2 and the air storage structure, thereby improving the engine starting difficulty and making up the take-off power, reducing the dependence on ground device assistance, and solving the problems of helicopter starting difficulty and insufficient take-off power on the plateau.

[0054] Specifically, the bleed valve seat 2 plays a role of connecting the casing 13 and the bleed pipe 21, and is close to the outlet of the diffuser 123 of the engine body 1, so that high-pressure air after working by the compressor 12 can be led out, thereby providing air conditions for realizing self-circulation.

[0055] Specifically, the bleed pipe 21 plays a role of conveying high-pressure air.

[0056] Specifically, the air collector 3 can collect high-pressure air and atmospheric air, and filter impurities in the air to prevent engine failure.

[0057] Specifically, the diffuser 123 has the functions of diffusing, rectifying and reducing speed, the pressure at the outlet of the diffuser 123 is higher, and the airflow is more stable, so the bleed valve seat is arranged at the outlet of the diffuser 123.

[0058] Specifically, the bleed valve seat 2 is always open.

[0059] Specifically, the storage device 5 and the controller 4 are prior art, and thus will not be described here.

[0060] Figure 2 A connection diagram of the gas pipe 53 and the engine body 1 is shown. Figure 2As shown, in some embodiments, the air storage structure includes a pressure pump 52, a storage device 5, a flow valve 532, an intake pipe 51, and an air delivery pipe 53. The storage device 5 is connected to the air collector 3 via the intake pipe 51. The intake pipe 51 is equipped with a pressure pump 52, and the storage device 5 is equipped with an air delivery pipe 53. One end of the air delivery pipe 53 away from the air storage device 5 is connected to the intake duct 121 of the engine body 1. The portion of the air delivery pipe 53 near the intake duct 121 is obliquely arranged, and the air delivery pipe 53 is equipped with a flow valve 532. The pressure pump 52, the storage device 51, the air delivery pipe 52, the air storage device 51, the air delivery pipe 53, the air storage device 52, the air storage device 53 ... All storage devices 5 are connected to the control system; the pressure pump 52 is used to pressurize air below the preset pressure value and deliver the pressurized air to the storage device 5; the storage device 5 provides storage conditions and temperature regulation function for high-pressure air; the intake pipe 51 is used to transmit the collected air; the air delivery pipe 53 is used to transmit high-pressure air to the intake duct 121 of the engine body 1; the flow valve 532 is used to control the flow rate of high-pressure air entering the intake duct 121; the part of the air delivery pipe 53 near the intake duct 121 is set at an angle to ensure that the high-pressure air can enter the intake duct 121 at a uniform speed without disturbing the airflow.

[0061] Specifically, the storage device 5 can adjust the temperature of the high-pressure gas to 13-18°C to meet the starting requirements of the engine.

[0062] In some embodiments, a first mass flow meter 122 is provided in the air intake duct 121; the first mass flow meter 122 can monitor in a timely manner whether the flow rate of atmospheric air meets the preset requirements.

[0063] Figure 3 It shows Figure 2 A three-dimensional image. For example... Figure 3 As shown, in some embodiments, the air supply pipe 53 includes, in vertical order, a connecting pipe 531, an arc pipe 54, and an air guide pipe 55. The connecting pipe 531 is connected to the arc pipe 54. A plurality of air guide pipes 55 are evenly distributed on the side of the arc pipe 54 away from the connecting pipe 531. The connecting pipe 531 is connected to the storage device 5. The arc pipe 54 is sleeved on the casing 13 of the compressor 12. The end of the air guide pipe 55 away from the arc pipe 54 passes through the casing 13 and connects to the engine body. The intake duct 121 of 1 is connected, and the flow valve 532 is installed on the connecting pipe 531; the connecting pipe 531 is the main delivery pipe; the arc pipe 54 and the air guide pipe 55 both serve to transmit high-pressure gas, and the air guide pipe 55 can deliver high-pressure gas to the intake duct 121 at a uniform speed; the arc pipe 54 is arc-shaped and can accommodate multiple air guide pipes 55, providing installation conditions for the air guide pipes 55; several air guide pipes 55 can ensure that high-pressure air can enter the intake duct 121 at a uniform speed, avoiding intake distortion.

[0064] In some embodiments, eight air guide pipes 55 are evenly distributed on the arc tube 54; the eight air guide pipes 55 can ensure that high-pressure air can enter the air intake duct 121 at a uniform speed, avoiding air intake distortion.

[0065] Figure 5 It shows Figure 4 A magnified view of part B, such as Figure 5 As shown, in some embodiments, the portion of the air duct 55 near the air intake 121 is arranged at a clockwise angle; the angled arrangement of the portion of the air duct 55 near the air intake 121 enables the pressure difference between the high-pressure gas entering the air intake 121 and the atmosphere behind the tail nozzle 16 of the engine body 1 to promote the ram effect, which is more conducive to engine starting.

[0066] In some embodiments, a second mass flow meter 533 is provided at the position of the connecting pipe 531 between the flow valve 532 and the arc pipe 54; the second mass flow meter 533 can monitor in a timely manner whether the flow rate of the high-pressure gas meets the preset requirements.

[0067] In some embodiments, the engine body 1 includes a reducer 11, a compressor 12, a combustion chamber 14, a turbine 15, and a tailpipe 16 arranged sequentially in the transverse direction. The arc-shaped tube 54 is sleeved on the compressor casing 13. The ends of the plurality of air guide pipes 55 away from the arc-shaped tube 54 pass through the casing 13 and the impeller cover 125 in sequence and communicate with the intake duct 121 of the compressor 12. The air guide pipes 55 are arranged in a clockwise direction at the part of the impeller cover 125. The casing 13 is provided with an air intake valve seat 2 at the outlet of the diffuser 123 of the compressor 12. Because the diffuser 123 has the functions of diffusion, rectification and speed reduction, the pressure at the outlet of the diffuser 123 is higher and the airflow is more stable. Therefore, the air intake valve seat is connected to the outlet of the diffuser 123. The casing 13 and the impeller cover 125 provide the installation conditions for the air guide pipes 55.

[0068] Specifically, compressor 12 is a centrifugal compressor 12.

[0069] The gas storage method for turboshaft engines includes the following steps:

[0070] When starting at high altitude, avionics commands are sent to the air storage structure to activate it. The high-pressure air in the air storage structure is then modified and enters the engine body 1.

[0071] When the pressure inside the air storage structure is lower than the preset pressure, a pressure signal is sent to the controller 4. The controller 4 receives the pressure signal and sends an air collection signal to the air collector 3, the air bleed valve seat 2, and a pressurization and storage signal to the air storage structure.

[0072] When the preset condition of the bleed air of the diffuser 123 is met, the bleed air valve seat 2 is opened to collect the high-pressure air after the diffuser 123, the high-pressure air is filtered by the air collector 3 and then is delivered to the air storage structure for storage;

[0073] When the preset condition of the ambient air bleed is met, the air collector 3 and the air pipe 31 are used to collect the ambient air, the ambient air is filtered by the air collector 3 and then is delivered to the air storage structure for pressurization and storage;

[0074] The high-pressure air is continuously delivered during the starting process of the engine body 1, and the air storage structure is closed after the starting is successful.

[0075] In some embodiments, when the pressure of the high-pressure air after the diffuser 123 outlet is less than the pressure set in the air storage structure, the pressure pump 52 is started for secondary pressurization.

[0076] Specifically, the air storage structure is electrically connected with the controller 4, so that the air storage structure can timely transmit the pressure of the high-pressure air to the controller 4, the controller 4 receives the information and judges whether the pressure is less than the pressure set in the air storage structure, and if yes, the pressure pump 52 is started for secondary pressurization.

[0077] Specifically, the storage device 5 is provided with a pressure sensor, which is a conventional setting in the prior art, and thus will not be described here.

[0078] In some embodiments, the engine body 1 is electrically connected with the controller 4, so that the diffuser 123 can timely transmit the pressure of the high-pressure air to the controller 4, the controller 4 receives the information and judges whether the pressure is less than the pressure set in the air storage structure, and if yes, the pressure pump 52 is started for secondary pressurization.

[0079] Specifically, the diffuser 123 outlet is provided with a pressure sensor, which is a conventional setting in the prior art, and thus will not be described here.

[0080] In some embodiments, when the engine is started on the plateau, an avionics command is sent to the flow valve 532, the flow valve 532 is opened, and the engine state is pushed to the take-off power, the high-pressure air and the air sucked by the engine body 1 are mixed and then enter the compressor 12, the high-pressure air is compressed into high-pressure air by the centrifugal impeller 124 in the compressor 12 at a high speed, and then enters the combustion chamber 14 after being expanded by the diffuser 123.

[0081] In some embodiments, before the bleed air, an influence analysis test of the bleed air flow on the turbine 15 inlet temperature T45 is carried out. When the bleed air valve seat 2 is fully opened in the maximum continuous state of the engine body 1, the increment AT45 of the turbine 15 inlet temperature before and after the opening is measured.

[0082] Specifically, the influence analysis test of the bleed air flow on the turbine 15 inlet temperature T45 is the prior art, and thus will not be described here.

[0083] In some embodiments, the diffuser 123 bleed air preset conditions include:

[0084] Engine body 1 operating state ≥ in the air idle;

[0085] Tt45 < T45 max -△T45

[0086] Pilot does not manually close the high pressure gas production;

[0087] Storage device 5 is not full of gas;

[0088] Wherein, Tt45 is the turbine 15 inlet temperature; T45 max is the turbine 15 inlet limit temperature; △T45 is the increment of turbine 15 inlet temperature.

[0089] In some embodiments, the ambient atmospheric bleed air preset conditions include:

[0090] Engine body 1 starting process;

[0091] Engine body 1 climb process;

[0092] One engine failure, rely on a single engine work;

[0093] Pilot manually closes the high pressure gas production;

[0094] Tt45 ≥ T45 max -△T45

[0095] Storage device 5 is not full of gas;

[0096] Wherein, Tt45 is the turbine 15 inlet temperature; T45 max is the turbine 15 inlet limit temperature; △T45 is the increment of turbine 15 inlet temperature.

[0097] Further, the correction formula is as follows:

[0098]

[0099] Wherein, Wa H is the engine body 1 inlet air flow 121;

[0100] Wf H is the initial fuel flow of engine body 1;

[0101] Wa 额定 is the rated engine body 1 inlet air flow 121;

[0102] Wf H-修正 is the corrected fuel flow after the high pressure air is passed.

[0103] In some embodiments, the engine body 1 receives the air flow discharged from the air storage structure, and the calculation formula is as follows:

[0104] Wa s = Wa 额定 -Wa H

[0105] Wherein, Wa 额定 is the rated air flow of the intake port 121 of the engine body 1;

[0106] Wa H is the air flow of the intake port 121 of the engine body 1.

[0107] The working principle of the turbo-shaft engine air storage system is as follows:

[0108] The high-pressure gas of the engine body 1 and the atmospheric air are pressurized and stored, which not only realizes self-circulation, but also improves the engine starting difficulty and makes up for the take-off power. When the pressure in the storage device 5 is lower than the preset pressure, the controller 4 sends a signal to the air collector 3 to collect air, sends a pressurization signal to the pressure pump 52, and sends a storage signal to the storage device 5. Since the bleed valve seat 2 is always open, the air collector 3 can collect the high-pressure gas compressed by the compressor 12 through the bleed valve seat 2 and the bleed pipe 21. If the high-pressure gas is lower than the preset pressure, the controller 4 sends a pressurization signal to the pressure pump 52, and the pressurized high-pressure air is delivered to the storage device 5 through the air inlet pipe 51. The air collector 3 collects high-pressure gas at the same time. When the engine body 1 needs high-pressure air, the pilot sends a power instruction from the helicopter control panel to the flow valve 532, which is opened, and the high-pressure air in the storage device 5 enters the circular arc pipe 54 and the bleed pipe 55 in sequence through the communication pipe 531. Since the circular arc pipe 54 is provided with a plurality of bleed pipes 55, the high-pressure air can enter the intake port 121 at a uniform speed, and the pressure difference between the high-pressure air uniformly entering the intake port 121 and the tail nozzle 16 of the engine body 1 promotes the ram effect, which is more conducive to engine starting. The high-pressure air compressed by the compressor 12 can enter the air collector 3 again through the bleed valve, and then enter the storage device 5 after being compressed by the pressure pump 52 for storage, forming a self-circulation.

[0109] Although the present application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that the technical solutions recorded in the foregoing embodiments can be modified, or some technical features can be replaced by equivalent ones. These modifications or replacements do not change the essence of the corresponding technical solutions, and do not deviate from the spirit and scope of the technical solutions of the embodiments of the present application.

Claims

1. A turboshaft engine air storage system, comprising an engine body (1), an air storage structure, and a controller (4), characterized in that, It also includes a bleed air valve seat (2), a bleed air pipe (21), and an air collector (3). The bleed air valve seat (2) is located on the compressor (12) casing (13) of the engine body (1). The bleed air valve seat (2) is close to the diffuser (123) outlet of the engine body (1). One end of the bleed air pipe (21) is located on the bleed air valve seat (2), and the other end of the bleed air pipe (21) is connected to the air collector (3). The air collector (3) is connected to the air storage structure. The air storage structure is connected to the air intake (121) of the engine body (1). The air collector (3) is equipped with an air pipe (31). The air storage structure, the air collector (3), and the bleed air valve seat (2) are all electrically connected to the controller (4). The system is used to solve the problems of difficult start-up and insufficient power of turboshaft engines by integrating self-circulating air storage and replenishment in high-altitude environments. It includes the following steps: When starting at high altitude, avionics commands are sent to the air storage structure to open the air storage structure. The high-pressure air in the air storage structure is then corrected and enters the engine body (1). When the pressure inside the air storage structure is lower than the preset pressure, a pressure signal is sent to the controller (4). The controller (4) receives the pressure signal and sends the air collection signal to the air collector (3), the air intake valve seat (2), and the pressurization and storage signal to the air storage structure. When the pre-set conditions for bleed air from the diffuser (123) are met, the bleed air valve seat (2) is opened to collect the high-pressure air after the outlet of the diffuser (123), which is then filtered by the air collector (3) and sent to the air storage structure for storage. When the ambient atmospheric intake conditions are met, the outside air is collected by the air collector (3) and the air pipe (31), filtered by the air collector (3), and then transported to the air storage structure for pressurization and storage. High-pressure air is continuously supplied during the engine body (1) startup process, and the air storage structure is closed after successful startup.

2. The turboshaft engine gas storage system according to claim 1, characterized in that, The air storage structure includes a pressure pump (52), a storage device (5), a flow valve (532), an intake pipe (51), and an air delivery pipe (53). The storage device (5) is connected to the air collector (3) through the intake pipe (51). The intake pipe (51) is equipped with a pressure pump (52). The storage device (5) is equipped with an air delivery pipe (53). The end of the air delivery pipe (53) away from the storage device (5) is connected to the intake duct (121) of the engine body (1). The part of the air delivery pipe (53) near the intake duct (121) is set at an angle. The air delivery pipe (53) is equipped with a flow valve (532). The pressure pump (52) and the storage device (5) are both connected to the control circuit.

3. The turboshaft engine gas storage system according to claim 2, characterized in that, The gas supply pipe (53) includes, in sequence along the vertical direction, a connecting pipe (531), an arc pipe (54), and a guide pipe (55). The connecting pipe (531) is connected to the arc pipe (54). Several guide pipes (55) are evenly distributed on the side of the arc pipe (54) away from the connecting pipe (531). The connecting pipe (531) is connected to the storage device (5). The arc pipe (54) is sleeved on the casing (13) of the compressor (12). The end of the guide pipe (55) away from the arc pipe (54) passes through the casing (13) and is connected to the air intake (121) of the engine body (1). The flow valve (532) is located on the connecting pipe (531).

4. A turboshaft engine gas storage system according to claim 3, characterized in that, The connecting pipe (531) is equipped with a second mass flow meter (533) located between the flow valve (532) and the arc pipe (54).

5. A turboshaft engine gas storage system according to claim 1, characterized in that, When the high-pressure air pressure after the outlet of the diffuser (123) is less than the pressure set by the air storage structure, the pressure pump (52) is started to pressurize the air for a second time.

6. A turboshaft engine gas storage system according to claim 1, characterized in that, When starting at high altitude, an avionics command is sent to the flow valve (532) to open the flow valve (532) and push the engine status up to takeoff power. The high-pressure air mixes with the air drawn in by the engine body (1) and enters the compressor (12). The centrifugal impeller (124) in the compressor (12) rotates at high speed and is compressed into high-pressure air. Then it is diffused by the diffuser (123) and enters the combustion chamber (14).

7. A turboshaft engine gas storage system according to claim 1, characterized in that, The pre-set conditions for bleed air from the diffuser (123) include: Engine body (1) working state ≥ idle in the air; Tt45<T45 max — △T45; The pilot did not manually shut off the high-pressure gas generator; Storage device (5) is not full of gas; Where Tt45 is the turbine (15) inlet temperature; T45 max ΔT45 is the inlet temperature limit of turbine (15); ΔT45 is the increment of the inlet temperature of turbine (15).

8. A turboshaft engine gas storage system according to claim 1, characterized in that, The ambient atmospheric venting preset conditions include: During the engine start-up process (1); During the engine body (1) climbing process; If one engine fails, the aircraft relies on the remaining engine to function independently. The pilot manually shut off the high-pressure gas generation system; Tt45≥T45 max - △T45 Storage device (5) is not full of gas; Where Tt45 is the turbine (15) inlet temperature; T45 max ΔT45 is the inlet temperature limit of turbine (15); ΔT45 is the increment of the inlet temperature of turbine (15).

9. A turboshaft engine gas storage system according to claim 1, characterized in that, The correction formula is as follows: in, The airflow rate of the intake duct (121) of the engine body (1); The initial fuel flow rate of the engine body (1); The rated airflow of the engine body (1) intake manifold (121) is provided; This is the corrected fuel flow rate after high-pressure air is introduced.

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