Air intake structure, power system and aircraft

Abstract

This invention relates to the field of aerospace technology and discloses an air intake structure, a power system, and an aircraft. The air intake structure includes a first air duct, a second air duct, and a switching component. The first air duct extends along a first direction, with one end connected to a third air intake of the combustion chamber and the other end connected to a first air supply device. The second air duct extends along the first direction, with one end also connected to the third air intake of the combustion chamber and the other end connected to a second air supply device. The third air intake is connected to two channels of the combustion chamber, which are connected to the combustion chamber cavity. The switching component can switch the air duct connected to the third air intake, or control both the first and second air ducts to be connected to the third air intake, thereby ensuring the stability of the core flow field, such as the central recirculation zone of the combustion chamber, eliminating the risk of flameout caused by flow field distortion, and greatly improving the reliability of the power system under emergency conditions.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, specifically to an air intake structure. Furthermore, this invention also relates to a power system incorporating this air intake structure. Additionally, this invention relates to an aircraft incorporating this power system. Background Technology

[0002] Existing aircraft secondary propulsion systems typically consist of an auxiliary power unit (APU) and an emergency power unit (EPU). To reduce system complexity, a combined APU and EPU integrated auxiliary power unit has been proposed. Furthermore, the super-combined auxiliary power unit forms a dual-mode combustor by sharing a combustion chamber and turbine, enabling the APU to also perform emergency functions, thereby further reducing system size and weight.

[0003] The dual-mode combustor needs to accommodate both APU mode (using compressor bleed air) and EPU mode (using onboard high-pressure gas tanks for gas supply). Since APU intake air is typically introduced via an axial diffuser, while EPU intake air requires an additional interface in the combustor head casing, increasing the number of intake ports and leading to a complex structural layout that struggles to meet the requirements of extreme compactness. Furthermore, the different airflow entry paths in the two modes result in opposite airflow directions within the two combustor channels. During mode switching, the intense airflow collisions and flow field reconstruction can easily cause severe flow field distortion, disrupting combustion stability and potentially inducing combustor flameout, significantly impacting power reliability under emergency conditions. Summary of the Invention

[0004] This invention provides an air intake structure, a power system, and an aircraft to solve the aforementioned technical problems.

[0005] In a first aspect, the present invention provides an air intake structure, including a first air passage, a second air passage, and a switching component. The first air passage extends along a first direction, and its port is connected to a third air intake of the combustion chamber, and its other end is connected to a first air supply device. The second air passage extends along the first direction, and its port is also connected to the third air intake of the combustion chamber, and its other end is connected to a second air supply device. The third air intake is connected to two channels of the combustion chamber, and the two channels are connected to the combustion chamber of the combustion chamber. The switching component can switch the air passage connected to the third air intake, or control both the first air passage and the second air passage to be connected to the third air intake.

[0006] Beneficial effects: Since both the first and second air intakes ultimately enter the combustion chamber through the same third air intake, the airflow dynamic vector entering the combustion chamber tends to be consistent regardless of the mode. This ensures that during mode switching, the airflow in the two channels no longer experiences violent collisions with opposing flow directions, but rather a smooth flow ratio replacement. This guarantees the stability of the core flow field, such as the central recirculation zone of the combustion chamber, eliminates the risk of flameout caused by flow field distortion, and greatly improves the reliability of the power system under emergency conditions.

[0007] Optionally, the air intake structure further includes an air intake chamber, with an installation part inside the air intake chamber. The air intake chamber is connected to the third air intake of the combustion chamber. The switching component is disposed on the installation part and configured to block one of the first air intake communicating with the first air passage and the second air intake communicating with the second air passage and the second air intake.

[0008] Beneficial effects: Therefore, ensuring that the airflow dynamics entering the combustion chamber tend to be consistent completely avoids the problem of opposite airflow directions caused by different intake paths in the prior art, effectively suppressing the flow field distortion that may occur during mode switching and the resulting combustion instability or flameout risk.

[0009] Optionally, the first air passage and the second air passage are located on both sides of the air intake chamber along the first direction; the switching component includes a pin rod, which passes through the mounting portion along the first direction and is slidable relative to the mounting portion. A first sealing ring and a second sealing ring are formed at both ends of the pin rod, the first sealing ring being used to block the first air intake, and the second sealing ring being used to block the second air intake. Along the first direction, when the first sealing ring blocks the corresponding first air intake, the second sealing ring is spaced apart from the second air intake; when the second sealing ring blocks the second air intake, the first sealing ring is spaced apart from the first air intake.

[0010] Beneficial effects: This application achieves switching control through gas pressure difference, which simplifies the structure, increases the system integration, and effectively reduces the risk of mode switching failure and auxiliary power device failure due to abnormal actuator or signal transmission.

[0011] Optionally, the second gas supply device includes an onboard gas storage tank; the pin rod is provided with a spring structure, the spring structure abuts against the mounting part and the second sealing ring, and when the second sealing ring blocks the second air inlet, the spring structure is in a compressed or uncompressed state.

[0012] Beneficial effects: As the gas pressure generated on the compressor side gradually increases and reaches a preset pressure threshold, the combined force of the pressure exerted by the gas on the first sealing ring and the elastic restoring force provided by the spring structure is greater than the pressure on the second sealing ring. As a result, the pin will be forced to move along the first direction toward the second air passage, causing the first sealing ring to gradually release its blocking state on the first air inlet. This allows some of the compressed air on the compressor side to enter the intake chamber through the first air passage and further into the combustion chamber.

[0013] Optionally, a first sealing structure is formed at the port of the first air inlet facing the first sealing ring, and when the first sealing ring blocks the first air inlet, the periphery of the first sealing ring is configured to abut against the first sealing structure.

[0014] Beneficial effects: Enhance the sealing performance between the first sealing ring and the first air inlet.

[0015] Optionally, the first air passage portion extends into the air intake chamber, and this portion abuts against the corresponding inner wall surface of the air intake chamber to form a first stepped structure. The first stepped structure constitutes the first sealing structure. Along the first direction, the first sealing ring includes a first ring portion and a second ring portion coaxially arranged. The diameter of the first ring portion is smaller than that of the second ring portion. The circumferential direction of the first ring portion and the surface of the second ring portion facing the first air intake form a first annular groove. When the first sealing ring blocks the first air intake, the stepped structure of the first annular groove is correspondingly inserted.

[0016] Beneficial effects: Enhance the sealing performance between the first sealing ring and the first air inlet.

[0017] Optionally, a second sealing structure is formed at the port of the second air inlet facing the second sealing ring, and when the second sealing ring blocks the second air inlet, the periphery of the second sealing ring abuts against the second sealing structure.

[0018] Beneficial effects: Enhance the sealing performance between the second sealing ring and the second air inlet.

[0019] Optionally, the second air passage extends into the air intake chamber, and this portion abuts against the corresponding inner wall surface of the air intake chamber to form a second stepped structure. The second stepped structure constitutes the second sealing structure. Along the first direction, the second sealing ring includes a third ring portion and a fourth ring portion. The diameter of the third ring portion is smaller than that of the fourth ring portion. The circumferential direction of the third ring portion and the surface of the fourth ring portion facing the second air intake form a second annular groove. When the second sealing ring blocks the second air intake, the second annular groove is correspondingly inserted into the second stepped structure.

[0020] Beneficial effects: Enhance the sealing performance between the second sealing ring and the second air inlet.

[0021] Secondly, the present invention also provides a power system, including the intake structure and combustion chamber as described above.

[0022] Thirdly, the present invention also provides an aircraft including the power system described above. Attached Figure Description

[0023] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0024] Figure 1 This is a partial structural diagram of the air intake structure provided in the power system of an embodiment of the present invention; Figure 2 This is a schematic cross-sectional view of the air intake structure according to an embodiment of the present invention; Figure 3 This is a schematic diagram of the air intake structure according to an embodiment of the present invention; Figure 4 This is a schematic diagram of the first air intake in an embodiment of the present invention; Figure 5 This is a schematic diagram of the second air intake in an embodiment of the present invention; Figure 6 This is a schematic diagram of the first and second air passages sharing the same air intake according to an embodiment of the present invention.

[0025] Explanation of reference numerals in the attached figures: 100. First air passage; 110. First air inlet; 120. First sealing structure; 130. Second sealing structure; 200. Second air passage; 210. Second air intake; 300. Combustion chamber; 310. Third air intake; 320. Two air channels; 400. Switching assembly; 410. Pin rod; 420. First sealing ring; 421. First ring portion; 422. Second ring portion; 423. First ring groove; 430. Second sealing ring; 431. Third ring portion; 432. Fourth ring portion; 433. Second ring groove; 440. Spring structure; 500. Intake chamber; 510. Mounting part; 511. Support column; 520. Protruding structure; 600. Combustion chamber casing; 610. Outer casing; 611. Volute; 612. Volute intake seat; 613. Volute intake port; 614. Baffle; 615. Nozzle mounting seat; 616. Fuel nozzle; 620. Inner casing; 700, Flame Tube; 800, Axial diffuser; 900. Export guide components. Detailed Implementation

[0026] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0027] refer to Figure 1 , Figure 2 and Figure 3 The air intake structure of this embodiment includes a first air duct 100, a second air duct 200, and a switching component 400. Both the first air duct 100 and the second air duct 200 extend along a first direction (X direction). One end of the first air duct 100 is connected to the third air intake 310 of the combustion chamber 300, and the other end is connected to a first air supply device (such as a compressor). The second air duct 200 is also connected to the same third air intake 310, and the other end is connected to a second air supply device (such as an onboard high-pressure air tank). The third air intake 310 is connected to two channels 320. Simultaneously, the two channels 320 are connected to the combustion chamber of the combustion chamber 300 to guide air into the combustion chamber. Therefore, by converging the air supply from the APU mode (first air duct 100) and the EPU mode (second air duct 200) into the same set of third air intakes 310, the number of openings on the combustion chamber 300 is directly reduced, significantly improving the system's structural compactness compared to related technical solutions.

[0028] The switching component 400 is configured to switch the target airway and the third air inlet 310 to have a first state (APU mode) in which the first airway 100 is connected to the third air inlet 310, and a second state (EPU mode) in which the second airway 200 is connected to the third air inlet 310. It can also control a transition state in which the first airway 100 and the second airway 200 are simultaneously connected to the third air inlet 310.

[0029] Therefore, in this embodiment, since both the first air duct 100 and the second air duct 200 ultimately enter the two channels 320 of the combustion chamber 300 through the same third air inlet 310, the airflow dynamic vector entering the combustion chamber 300 tends to be consistent regardless of the mode. This ensures that at the moment of mode switching, the airflow in the two channels 320 no longer experiences violent collisions with opposite flow directions, but rather a smooth flow ratio replacement. This guarantees the stability of the core flow field, such as the central recirculation zone of the combustion chamber 300, eliminates the risk of flameout caused by flow field distortion, and greatly improves the reliability of the power system under emergency conditions.

[0030] In one embodiment, the air intake structure further includes an air intake chamber 500, and a mounting portion 510 is disposed inside the air intake chamber 500. (Reference) Figure 3 Along a second direction (e.g., the Y direction), the intake chamber 500 is located on the side of the third intake port 310 opposite to the combustion chamber 300 and is physically connected to the third intake port 310. The first air passage 100 and the second air passage 200 are respectively connected to the intake chamber 500, wherein the first air passage 100 is connected to the intake chamber 500 through the first air intake port 110, and the second air passage 200 is connected to the intake chamber 500 through the second air intake port 210. By setting the intake chamber 500 as a shared intermediate air collection space, the APU mode corresponding to the first air passage 100 and the EPU mode corresponding to the second air passage 200 can both supply air to the combustion chamber 300 through the same third air intake port 310.

[0031] refer to Figure 2 , Figure 4 , Figure 5 as well as Figure 6 When the switching component 400 is controlled to connect the first air passage 100 and / or the second air passage 200 with the intake chamber 500, air from the first air supply device and / or the second air supply device first enters and converges in the intake chamber 500, and then uniformly enters the combustion chamber 300 through the third air intake port 310. This ensures that the airflow dynamic vector entering the combustion chamber 300 tends to be consistent, completely avoiding the problem of opposite airflow directions due to different intake paths, and effectively suppressing the flow field distortion that may occur during mode switching and the resulting combustion instability or flameout risk.

[0032] Meanwhile, during the operation of the combustion chamber 300, a relative negative pressure zone is formed at the two channels 320 and the third air inlet 310. Under the action of this pressure gradient, the air in the intake chamber 500 can smoothly enter the combustion chamber of the combustion chamber 300 through the third air inlet 310 and the two channels 320 to participate in combustion. The switching component 400 is disposed on the mounting part 510 and achieves switching and control between different intake modes by selectively blocking the first air inlet 110 or the second air inlet 210.

[0033] In one embodiment, reference Figure 2 as well as Figure 3 The mounting portion 510 may include a support column 511, the two ends of which extend along a second direction perpendicular to the first direction and are fixedly connected to the inner wall surface of the air intake chamber 500, thereby forming a stable mounting area inside the air intake chamber 500 for supporting and guiding the switching assembly 400 to move along the first direction. It should be understood that the mounting portion 510 may also employ other suitable structural forms to achieve the above-mentioned mounting and guiding functions, and this document does not limit such implementation.

[0034] Furthermore, the first air passage 100 and the second air passage 200 are respectively arranged on both sides of the axial direction of the air intake chamber 500, so that the first air passage 100 and the second air passage 200 can supply air to the air intake chamber 500 from opposite sides, so as to match the physical position distribution of the first air supply device (e.g., compressor) and the second air supply device (e.g., airborne high-pressure air tank), and reduce the pressure loss along the path by shortening the air passage length.

[0035] Further, refer to Figure 3 The switching assembly 400 includes a pin 410, which passes through the mounting portion 510 and the support column 511 along a first direction and is configured to reciprocate between the first air inlet 110 and the second air inlet 210 relative to the support column 511. The pin 410 has a first sealing ring 420 and a second sealing ring 430 at its axial ends, respectively, used to seal the first air inlet 110 or the second air inlet 210 under different operating conditions.

[0036] It is understandable that after the airflow from the first air passage 100 and the second air passage 200 enters the intake chamber 500, it will preferentially act on the corresponding first sealing ring 420 or second sealing ring 430, thereby avoiding direct collision between the two airflows within the intake chamber 500. Based on this, an axial pressure difference can be formed between the first sealing ring 420 and the second sealing ring 430 at both ends of the pin rod 410. Under the action of this pressure difference, the pin rod 410 is driven to move along the first direction, thereby achieving automatic sealing of the corresponding air inlet. Compared with related technologies that require external actuation mechanisms, signal transmission devices, and additional control logic programs to complete the switching, this embodiment achieves switching control through gas pressure difference, resulting in a simpler structure, higher system integration, and effectively reducing the risk of mode switching failure or auxiliary power device malfunction due to abnormal actuation mechanisms or signal transmission.

[0037] Specifically, such as Figure 3The cross-section of the second-direction air intake structure is shown, in which the outer peripheral surfaces of the first sealing ring 420 and the second sealing ring 430 abut against the inner wall of the air intake chamber 500 for a tight fit. When the pin rod 410 moves under the action of axial pressure difference, the corresponding sealing ring moves toward the corresponding air intake, and its end face can abut against the corresponding end face of the air intake, thereby achieving physical cutoff of the corresponding air passage.

[0038] Furthermore, the air intake chamber 500 has a protruding structure 520 on the side facing the third air intake 310 along the second direction. The inner wall of the protruding structure 520 is spaced apart from the corresponding outer periphery of the sealing ring, forming a circumferential interval region. The third air intake 310 can be formed on the inner wall of the protruding structure 520. Thus, air from the first air passage 100 and the second air passage 200 can smoothly enter the third air intake 310 through the interval region. On the one hand, in the first and second states, this embodiment can ensure a reliable seal on the non-working air passage through the corresponding sealing ring, which can prevent the high-pressure gas output from the high-pressure gas tank (second gas supply device) from flowing back into the compressor (first gas supply device) in the second state, thereby preventing the loss of available gas volume and compressor reversal. On the other hand, in the transition state corresponding to the mode switching, the two airflows will not scour or interfere with each other, but will smoothly converge and enter the combustion chamber 300, effectively avoiding flow field distortion and ensuring the stability of flow and combustion in the combustion chamber 300.

[0039] Furthermore, the axial length of the pin 410 satisfies the following: when the first sealing ring 420 blocks the first air inlet 110, the second sealing ring 430 is spaced apart from the second air inlet 210; when the second sealing ring 430 blocks the second air inlet 210, the first sealing ring 420 is spaced apart from the first air inlet 110. In other words, along the first direction, the length of the pin 410 is less than the distance between the first air inlet 110 and the second air inlet 210, and its axial travel ensures that the first sealing ring 420 and the second sealing ring 430 respectively abut against the corresponding air inlets, thereby preventing both ends of the pin 410 from being simultaneously located in the first sealing position and the second sealing position. The first sealing position is the axial position of the corresponding end of the pin 410 when the first sealing ring 420 blocks the first air inlet 110, and the second sealing position is the axial position of the corresponding end of the pin 410 when the second sealing ring 430 blocks the second air inlet 210.

[0040] Therefore, this embodiment achieves three air intake states during movement by reasonably setting the length and stroke of the pin rod 410: when the pin rod 410 is in the first blocking position, it corresponds to the first state; when the pin rod 410 is in the second blocking position, it corresponds to the second state; and when the pin rod 410 is between the first blocking position and the second blocking position, it corresponds to the transition state.

[0041] Typically, the compressor and turbine are arranged coaxially. Therefore, in EPU mode, the compressor continues to idle along the shaft and compress the air entering it. If the compressed air generated on the compressor side cannot enter the combustion chamber 300 through the intake passage for consumption, the gas pressure on the compressor outlet side will continuously increase, easily inducing compressor surge, thus adversely affecting the overall operational stability and reliability of the machine.

[0042] Based on the above issues, refer to Figure 3 In one embodiment, a spring structure 440 is provided on the pin 410, and the spring structure 440 abuts against the mounting portion 510 and the second sealing ring 430. When the second sealing ring 430 blocks the second air inlet 210, the spring structure 440 is in a compressed or uncompressed state, such that when in the second state, the spring structure 440 is in a compressed state.

[0043] Therefore, when the system is in the second state and the compressor continues to compress air, if the gas pressure generated on the compressor side gradually increases and reaches the preset pressure threshold, the combined force formed by the pressure of the gas acting on the first sealing ring 420 and the elastic restoring force provided by the spring structure 440 is greater than the pressure on the second sealing ring 430. Then the pin rod 410 will be forced to move along the first direction toward the second air passage 200, so that the first sealing ring 420 gradually gets out of the blocking state of the first air inlet 110, thereby allowing part of the compressed air on the compressor side to enter the intake chamber 500 through the first air passage 100 and further enter the combustion chamber 300.

[0044] Therefore, this embodiment can promptly release the compressed air generated on the compressor side when the pressure is too high, thereby reducing the air pressure in the first air passage 100 and effectively avoiding compressor surge caused by gas accumulation. It can be seen that by providing a spring structure 440 on the pin 410, this embodiment allows the gas generated by the compressor in the second state to release pressure even when the pressure is insufficient to move the pin 410 alone, thanks to the elasticity of the spring. This further improves the operational stability and safety of the system in EPU mode.

[0045] Therefore, it can be clearly understood that the working principle of the switching component 400 in this embodiment is as follows: under different gas supply modes, the switching component 400 automatically adjusts its axial position under the combined action of the gas pressure difference and the elastic force of the spring structure 440, thereby achieving selective conduction of the first air passage 100 and the second air passage 200.

[0046] Combination Figure 4In APU mode, the second air supply device does not supply air, and the corresponding sides of the second air passage 200 and intake chamber 500 are in a low-pressure state. At this time, the spring structure 440 can be in a naturally expanded or compressed state, and the second sealing ring 430 is driven to press and seal the second air inlet 210, thereby cutting off the second air passage 200. Air from the first air supply device enters the intake chamber 500 through the first air passage 100, and finally enters the combustion chamber 300 through the third air inlet 310, forming the first state.

[0047] Combination Figure 5 When the system switches to EPU mode, the second air supply device begins to supply high-pressure air to the second air passage 200, and the gas pressure in the second air passage 200 gradually increases. The high-pressure gas acts on the second sealing ring 430, and after overcoming the elasticity of the spring structure 440 and the gas pressure on the first air passage 100 side, it pushes the pin rod 410 to move in the first direction, causing the first sealing ring 420 to gradually tighten and seal the first air inlet 110, thereby cutting off the first air passage 100. At this time, the combustion chamber 300 is only supplied with air by the second air passage 200, forming a single-channel working state, which can reliably prevent the gas in the high-pressure gas tank from flowing back into the compressor, avoiding compressor reversal or damage.

[0048] Combination Figure 6 During mode switching or when system operating conditions change, if the sum of the gas pressure on the first air passage 100 side and the elastic force of the spring structure 440 reaches a relatively balanced state with the gas pressure on the second air passage 200 side, and the pin 410 is located between the first and second positions, that is, the first sealing ring 420 and the second sealing ring 430 maintain a distance from their respective air inlets, then the first air passage 100 and the second air passage 200 are simultaneously connected to the intake chamber 500, forming a transition state. In this state, the two gas streams enter the intake chamber 500 together and converge before entering the combustion chamber 300 through the third air inlet 310. This not only alleviates the surge problem that the compressor may generate under EPU mode, but also makes full use of the air output by the compressor, extending the service life of the onboard high-pressure air tank.

[0049] In one embodiment, a first sealing structure 120 is formed at the port of the first air inlet 110 facing the first sealing ring 420. When the first sealing ring 420 blocks the first air inlet 110, the periphery of the first sealing ring 420 is configured to abut against the first sealing structure 120, thereby enhancing the sealing between the first sealing ring 420 and the first air inlet 110.

[0050] refer to Figure 3The first air passage 100 can partially extend into the air intake chamber 500, and this portion abuts against the corresponding inner wall surface of the air intake chamber 500 to form a first stepped structure. This first stepped structure can form the aforementioned first sealing structure 120. Specifically, along the first direction, the first sealing ring 420 includes a first ring portion 421 and a second ring portion 422 coaxially arranged. The outer diameter of the first ring portion 421 is smaller than that of the second ring portion 422, so that the circumferential direction of the first ring portion 421 and the surface of the second ring portion 422 facing the first air intake 110 form a first annular groove 423. This first annular groove 423 is adapted to the first stepped structure, such as... Figure 3 As shown, in the first state, the stepped structure of the first annular groove 423 is inserted into the first opening, that is, the first ring portion 421 is inserted into the first opening and abuts against the inner wall of the first opening, and the corresponding surface of the second ring portion 422 abuts against the end face of the first opening, thereby enhancing the sealing between the first sealing ring 420 and the first air inlet 110.

[0051] In one embodiment, a second sealing structure 130 is formed at the port of the second air inlet 210 facing the second sealing ring 430. When the second sealing ring 430 blocks the second air inlet 210, the periphery of the second sealing ring 430 is configured to abut against the second sealing structure 130, thereby enhancing the sealing between the second sealing ring 430 and the second air inlet 210.

[0052] refer to Figure 3 The second air passage 200 can partially extend into the air intake chamber 500, and this portion abuts against the corresponding inner wall surface of the air intake chamber 500 to form a second stepped structure. This second stepped structure can form the aforementioned second sealing structure 130. Specifically, along the first direction, the second sealing ring 430 includes a third ring portion 431 and a fourth ring portion 432 coaxially arranged. The outer diameter of the third ring portion 431 is smaller than that of the fourth ring portion 432, so that the circumferential direction of the third ring portion 431 and the surface of the fourth ring portion 432 facing the second air intake port 210 form a second annular groove 433. This second annular groove 433 is adapted to the second stepped structure, such as... Figure 3 As shown, in the second state, the second annular groove 433 is inserted into the stepped structure, that is, the third ring portion 431 is inserted into the second opening and its outer peripheral surface abuts against the inner wall of the second opening, and the corresponding surface of the fourth ring portion 432 abuts against the end face of the second opening, thereby enhancing the sealing between the second sealing ring 430 and the second air inlet 210.

[0053] Secondly, this embodiment also provides a power system, which includes the intake structure and combustion chamber 300 as described above, and further includes combustion chamber casing 600, flame tube 700, fuel nozzle 616, axial diffuser 800 and outlet guide assembly.

[0054] The combustion chamber casing 600 includes an outer casing 610 and an inner casing 620 that are nested and connected to each other. The flame tube 700 is disposed between the outer casing 610 and the inner casing 620 and is arranged correspondingly to the fuel nozzle 616 to form a combustion chamber 300 inside it. The outlet guide assembly is disposed at the tail of the flame tube 700 and is located at the communication position between the flame tube 700 and the inner casing 620. It is used to guide the exhaust gas after combustion into the inner casing 620 and further discharge it.

[0055] The air intake structure is located between the outer casing 610 and the flame tube 700, and is used to supply the combustion chamber 300 with the air required for combustion. Specifically, the outer casing 610 is provided with a volute air intake seat 612, a volute air intake hole 613, a volute 611, a baffle 614, and a nozzle mounting seat 615, and the fuel nozzle 616 is mounted on the nozzle mounting seat 615. The baffle 614 is located inside the volute 611 and between the volute 611 and the flame tube 700, forming an air intake channel between the baffle 614 and the volute 611. In this embodiment, the second air passage 200 communicates with the air intake channel; the volute air intake hole 613 communicates with the air intake channel and is used to guide gas into the volute 611 structure. The second air supply device communicates with the air intake channel through the volute air intake seat 612.

[0056] Furthermore, the first air passage 100 is connected to the compressor via an axial diffuser 800, allowing compressed air output from the compressor to enter the first air passage 100 via the axial diffuser 800 and further enter the intake structure. The internal space of the flame tube 700 constitutes the combustion chamber 300. Under different air supply modes, air from the first air passage 100 or the second air passage 200 is introduced into the combustion chamber 300 within the flame tube 700 via the intake structure and mixes with the fuel injected by the fuel nozzle 616 for combustion.

[0057] It should be noted that in this embodiment, the intake chamber 500, intake channel, second air passage 200, and first air passage 100 are all formed in the volute 611 and are all annular in structure. Correspondingly, the first sealing ring and the second sealing ring are also annular and are used to seal the first opening and the second opening. In this structural configuration, the support columns 511 can be configured as multiple and evenly distributed along the circumference. Correspondingly, the pin rods 410 can also be configured as multiple to provide stable support for the annular first sealing ring and the second sealing ring, thereby ensuring the structural stability and sealing reliability of the switching assembly 400 during operation.

[0058] Thirdly, this application also includes an aircraft comprising the power system described above.

[0059] Although embodiments of the invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the invention, and such modifications and variations all fall within the scope defined by the appended claims.

Claims

1. An air intake structure characterized by, The application relates to an air inlet structure of a gas turbine engine. The air inlet structure comprises: a first air passage (100) extending along a first direction, and having a port communicating with a third air inlet (310) of a combustion chamber (300) and the other end communicating with a first air supply device; a second air passage (200) extending along the first direction, and having a port also communicating with the third air inlet (310) of the combustion chamber (300) and the other end communicating with a second air supply device, the third air inlet (310) communicating with a two-way passage (320) of the combustion chamber (300), and the two-way passage (320) communicating with a combustion cavity of the combustion chamber (300); 2. The air intake structure of claim 1, wherein a switching assembly (400) capable of switching the air passage communicating with the third air inlet (310) or controlling the first air passage (100) and the second air passage (200) to communicate with the third air inlet (310) respectively. The air inlet structure further comprises: an air inlet cavity (500) internally provided with a mounting portion (510), the air inlet cavity (500) communicating with the third air inlet (310) of the combustion chamber (300), and the switching assembly (400) being arranged on the mounting portion (510) and being configured to block one of a first air inlet (110) of the first air passage (100) and a second air inlet (210) of the second air passage (200) communicating with the air inlet cavity (500).

3. The air inlet structure according to claim 2, wherein: the first air passage (100) and the second air passage (200) are respectively located on two sides of the air inlet cavity (500) along the first direction; the switching assembly (400) comprises a latch rod (410) extending along the first direction, the latch rod (410) penetrating through the mounting portion (510) and being capable of sliding relative to the mounting portion (510), and two ends of the latch rod (410) are respectively formed with a first blocking ring (420) and a second blocking ring (430), the first blocking ring (420) being used for blocking the first air inlet (110), and the second blocking ring (430) being used for blocking the second air inlet (210), along the first direction, when the first blocking ring (420) blocks the first air inlet (110), the second blocking ring (430) is arranged to be spaced from the second air inlet (210), and when the second blocking ring (430) blocks the second air inlet (210), the first blocking ring (420) is arranged to be spaced from the first air inlet (110).

4. The air inlet structure according to claim 3, wherein: the second air supply device comprises an on-board gas tank; the latch rod (410) is provided with a spring structure (440), the spring structure (440) abutting between the mounting portion (510) and the second blocking ring (430), and when the second blocking ring (430) blocks the second air inlet (210), the spring structure (440) is in a compressed or natural state.

5. The air inlet structure according to claim 3, wherein: A first sealing structure (120) is formed at the port of the first air inlet (110) facing the first sealing ring (420). When the first sealing ring (420) blocks the first air inlet (110), the periphery of the first sealing ring (420) is configured to abut against the first sealing structure (120).

6. The intake structure according to claim 5, characterized in that, The first air passage (100) extends into the air intake chamber (500), and the portion abuts against the corresponding inner wall surface of the air intake chamber (500) to form a first stepped structure, the first stepped structure constituting the first sealing structure (120). Along the first direction, the first sealing ring (420) includes a first ring portion (421) and a second ring portion (422) coaxially arranged. The first ring portion (421) is formed on the surface of the second ring portion (422) facing the first air inlet (110). The diameter of the first ring portion (421) is smaller than that of the second ring portion (422). The circumferential direction of the first ring portion (421) and the surface of the second ring portion (422) facing the first air inlet (110) form a first annular groove (423). When the first sealing ring (420) blocks the first air inlet (110), the stepped structure of the first ring groove (423) is inserted accordingly.

7. The intake structure according to claim 3, characterized in that, A second sealing structure (130) is formed at the port of the second air inlet (210) facing the second sealing ring (430). When the second sealing ring (430) blocks the second air inlet (210), the periphery of the second sealing ring (430) abuts against the second sealing structure (130).

8. The intake structure according to claim 7, characterized in that, The second air passage (200) extends into the air intake chamber (500), and the portion abuts against the corresponding inner wall of the air intake chamber (500) to form a second stepped structure, which constitutes the second sealing structure (130). Along the first direction, the second sealing ring (430) includes a third ring portion (431) and a fourth ring portion (432), wherein the diameter of the third ring portion (431) is smaller than that of the fourth ring portion (432), the third ring portion (431) is formed on the surface of the fourth ring portion (432) facing the second air inlet (210), and the circumferential direction of the third ring portion (431) and the surface of the fourth ring portion (432) facing the second air inlet (210) form a second annular groove (433). When the second sealing ring (430) blocks the second air inlet (210), the second ring groove (433) is inserted into the second stepped structure.

9. A power system characterized by, Includes the intake structure and combustion chamber (300) as described in any one of claims 1-8.

10. An aircraft, characterized in that Includes the power system as described in claim 9.

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