Air intake system for an aeroengine

Abstract

The present disclosure provides an air intake system for an aero-engine, comprising an outer casing, an inner casing, a center body and a support plate array. The inner casing is coaxially arranged in the outer casing. The center body is configured as a rotary body structure and is arranged in the inner casing. An annular area between the outer casing, the inner casing and the center body forms an air intake passage. The support plate array comprises at least one support plate arranged at an inlet position of the air intake passage. The support plate extends along a radial direction of the air intake passage and is arranged between the outer casing and the inner casing. The support plate has a first flow channel therein, which is in communication with an external high-temperature gas source. By arranging the support plate, the flow channel in the support plate is formed in communication with the external high-temperature gas source, thereby realizing the integration of force bearing and ice prevention. No additional independent ice prevention pipeline is arranged, thereby saving space and reducing the weight of the system.

Description

Technical Field

[0001] This disclosure relates to the field of aero-engine technology, and more particularly to an air intake system for an aero-engine. Background Technology

[0002] When aircraft engine air intakes operate in low-temperature, high-humidity environments, supercooled water droplets impact their inner walls and release latent heat, leading to icing. Icing alters the aerodynamic shape of the air intake, reducing intake efficiency and engine performance. In severe cases, ice may detach and be sucked into the core engine, causing mechanical damage. Therefore, effective anti-icing and de-icing capabilities are crucial for ensuring flight safety.

[0003] The relevant anti-icing technologies mainly include three categories: liquid anti-icing, mechanical de-icing, and thermal anti-icing. Liquid anti-icing systems require loading and pumping anti-icing fluid, increasing the aircraft's additional weight. Furthermore, the amount of fluid loaded limits the duration of continuous protection, resulting in limited effectiveness under severe or prolonged icing conditions, and there is a risk of fluid leakage. Mechanical de-icing systems physically remove ice, but repeated operation can lead to structural fatigue, and they are ineffective at removing firmly attached ice, potentially introducing vibration and noise problems. Thermal anti-icing technology typically draws air from the compressor and uses high-temperature air for heating, resulting in higher structural reliability.

[0004] However, traditional thermal anti-icing systems often employ parallel heating methods with independent piping for each heating zone. This method results in hot air being directly discharged after only one heat exchange along the heated wall, leading to underutilization of thermal energy and a higher overall bleed air volume requirement. The additional independent piping also increases the system's complexity and overall weight. Increased bleed air volume not only negatively impacts engine performance but may also cause insufficient system response and adjustment due to thermal inertia. Summary of the Invention

[0005] To address at least one of the aforementioned and other technical problems in the related art, this disclosure provides an air intake system for an aircraft engine, comprising an outer casing, an inner casing, a central body, and a support plate array. The inner casing is coaxially disposed within the outer casing. The central body is configured as a rotating structure and is disposed within the inner casing; an annular region between the outer casing, the inner casing, and the central body forms an air intake duct. The support plate array includes at least one support plate disposed at the inlet position of the air intake duct, extending radially along the air intake duct and disposed between the outer casing and the inner casing; the support plate has a first flow channel communicating with an external high-temperature air source.

[0006] According to an embodiment of this disclosure, the support plate has a partition extending radially along the air intake passage to divide the first flow passage into a first segment near the leading edge and a second segment near the trailing edge. The first segment is configured to guide the flow of high-temperature gas in a first direction, and the second segment is configured to guide the flow of high-temperature gas in a second direction opposite to the first direction.

[0007] According to an embodiment of this disclosure, a second flow channel extending along the profile of the central body is formed between the inner and outer wall surfaces of the central body. The inlet end of the second flow channel is connected to the outlet end of the first section, and the outlet end of the second flow channel is connected to the inlet end of the second section.

[0008] According to an embodiment of this disclosure, along the mainstream direction of the intake duct, the intake end of the second flow channel is located upstream of the outlet end of the second flow channel.

[0009] According to embodiments of this disclosure, in a meridional section including the intake duct axis, the profile of the central body has a hump apex, which is the point on the central body profile furthest from the intake duct axis in radial distance. Along the main flow direction of the intake duct, the profile of the central body includes an upstream segment located upstream of the hump apex and a downstream segment located downstream of the hump apex, wherein the average curvature of the upstream segment is configured to be greater than the average curvature of the downstream segment.

[0010] According to embodiments of this disclosure, the average curvature of the upstream segment is configured as follows: And / or, the average curvature of the downstream segment is configured as follows: .

[0011] According to embodiments of this disclosure, a sand-discharging volute is also included, disposed in the outer casing and surrounding the outer side of the central body.

[0012] According to an embodiment of this disclosure, an outer shell is disposed between the central body and the sand-discharging volute. The outer shell is configured as a hollow structure with a sandwich layer, the sandwich layer defining a third flow channel extending along the extension direction of the outer shell. The end of the outer shell near the support plate forms the air inlet end of the third flow channel, and the end of the outer shell away from the support plate is provided with an air outlet. The air inlet end of the third flow channel communicates with the air outlet end of the second section, and the air outlet of the third flow channel communicates with the air inlet channel.

[0013] According to embodiments of this disclosure, the system further includes an ejector line and an ejector device. The ejector line is connected to the outlet of the sand discharge volute. The ejector device is connected to the ejector line and is used to introduce high-pressure gas into the ejector line to generate a suction effect.

[0014] According to embodiments of this disclosure, a separation lip is further included, disposed on the inner wall of the air intake duct downstream of the central body. The separation lip forms a throat channel that gradually narrows along the mainstream direction of the air intake duct to deflect at least a portion of the foreign matter separated by the central body to the sand discharge volute.

[0015] According to an embodiment of the present disclosure, the separation lip is configured as a hollow structure with a sandwich, the sandwich defining a fourth flow channel extending along the profile of the separation lip, the fourth flow channel being in communication with an external high-temperature gas source.

[0016] According to the illustrative embodiments of the present disclosure, an air intake system for an aircraft engine integrates a load-bearing structure and an anti-icing flow channel by installing a support plate with a built-in first flow channel at the air intake inlet between the outer and inner casings and connecting the first flow channel to an external high-temperature air source. This design eliminates the need for separate anti-icing piping within the air intake, saving space and reducing system weight, while providing an efficient path for the direct delivery of high-temperature media to the most icing-prone air intake area. Attached Figure Description

[0017] The above and other objects, features and advantages of this disclosure will become clearer from the following description of embodiments with reference to the accompanying drawings, in which:

[0018] Figure 1 A partial cross-sectional view of an intake system according to an embodiment of the present disclosure is shown schematically;

[0019] Figure 2 A schematic diagram of the air intake system flow path according to an embodiment of the present disclosure is shown.

[0020] Figure 3 A schematic cross-sectional view of the first flow channel in an embodiment of this disclosure is shown;

[0021] Figure 4 A schematic cross-sectional view of the heart body is shown in an embodiment of this disclosure;

[0022] Figure 5 A schematic cross-sectional view of the housing according to an embodiment of the present disclosure is shown;

[0023] Figure 6 A schematic cross-sectional view of the ejector conduit and ejector device according to an embodiment of the present disclosure is shown;

[0024] Figure 7 A schematic cross-sectional view of the separated lip according to an embodiment of the present disclosure is shown;

[0025] Figure 8 A schematic cross-sectional view of a radial air intake duct according to an embodiment of the present disclosure is shown;

[0026] Figure 9 The schematic diagram illustrates the anti-icing and de-icing process of the intake system according to an embodiment of the present disclosure.

[0027] The meanings of the reference numerals in the attached figure are as follows:

[0028] 1. Inner casing, 2. Outer casing, 3. Central body, 4. Support plate array

[0029] 41. First paragraph; 42. Second paragraph; 31. Upstream paragraph; 32. Downstream paragraph.

[0030] 5. Sand discharge volute, 6. Outer shell, 7. Separation lip, 8. Ejector pipe, 9. Ejector device, 10. Radial air intake channel. Detailed Implementation

[0031] To make the objectives, technical solutions, and advantages of this disclosure clearer, the following detailed description is provided in conjunction with specific embodiments and the accompanying drawings.

[0032] The terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit this disclosure. The terms “comprising,” “including,” etc., as used herein indicate the presence of features, steps, operations, and / or components, but do not exclude the presence or addition of one or more other features, steps, operations, or components.

[0033] All terms used herein, including technical and scientific terms, have the meanings commonly understood by those skilled in the art, unless otherwise defined. It should be noted that the terms used herein are to be interpreted in a manner consistent with the context of this specification, and not in an idealized or overly rigid way.

[0034] When using expressions such as "at least one of A, B, and C," the meaning should generally be interpreted according to the understanding of someone skilled in the art. For example, "a system having at least one of A, B, and C" should include, but is not limited to, systems having A alone, having B alone, having C alone, having A and B, having A and C, having B and C, and / or having A, B, and C. Similarly, when using expressions such as "at least one of A, B, or C," the meaning should generally be interpreted according to the understanding of someone skilled in the art. For example, "a system having at least one of A, B, or C" should include, but is not limited to, systems having A alone, having B alone, having C alone, having A and B, having A and C, having B and C, and / or having A, B, and C.

[0035] In a typical scheme using compressor bleed air for thermal anti-icing, high-temperature gas is transported through pipelines independent of the main intake structure. These pipelines are usually connected in parallel to multiple areas requiring heating, such as the separation lip 7 or specific interlayers of the central body 3. After flowing through the heat exchange cavities in these areas, the high-temperature gas is directly discharged into the main flow or purge channel, completing a single heat exchange. In this method, each stream of high-temperature gas only heats a single local area it flows through, and the heat energy it carries is discharged after one heat exchange, without further utilization. For the support plate in the intake area, this component is usually designed as a purely load-bearing structure, without integrated fluid channels. When anti-icing is required in this area, additional heating elements attached to the surface or independent surrounding pipelines are often needed, which not only increases the complexity and installation difficulty of the structure, but also introduces additional aerodynamic drag and potential reliability risks. From the perspective of overall system efficiency, parallel heating and independent piping modes require a significant amount of air to be drawn from the engine compressor to ensure heating for multiple dispersed areas. This increase in air volume will negatively impact the engine's work capacity. Furthermore, the multiple independent pipes and connecting structures cumulatively increase the system's total weight and the space it occupies.

[0036] Figure 1 A partial cross-sectional view of an intake system according to an embodiment of the present disclosure is schematically shown. Figure 2 A schematic diagram of the air intake system flow path according to an embodiment of the present disclosure is shown.

[0037] This disclosure provides an air intake system for an aircraft engine, such as Figure 1 and Figure 2 As shown, the system includes an outer casing 2, an inner casing 1, a central body 3, and a support plate array 4. The inner casing 1 is coaxially disposed within the outer casing 2. The central body 3 is configured as a rotating structure and is disposed within the inner casing 1. An annular region between the outer casing 2, the inner casing 1, and the central body 3 forms an air intake duct. The support plate array 4 includes at least one support plate, arranged at the inlet position of the air intake duct. The support plate extends radially along the air intake duct and is disposed between the outer casing 2 and the inner casing 1. The support plate has a first flow channel that communicates with an external high-temperature air source.

[0038] In some illustrative embodiments of this disclosure, the intake system includes an outer casing 2 and an inner casing 1 arranged coaxially. A central body 3, a rotating structure, is mounted on the inner casing 1. The outer casing 2, inner casing 1, and central body 3 together form an annular intake duct for guiding airflow towards the engine core. At the intake duct inlet, at least one radially extending support plate is provided, connecting the outer casing 2 and inner casing 1, serving a supporting and rectifying function. The support plate's interior is constructed with a hollow cavity, forming a first flow channel. The first flow channel has an intake port, which is connected via a pipeline to the engine compressor stage bleed port or other high-temperature gas sources, allowing high-temperature gas to enter the support plate's interior.

[0039] In some illustrative embodiments of this disclosure, a high-temperature gas source refers to a gas source capable of providing a hot gas flow or heat medium with a temperature significantly higher than the freezing temperature of supercooled water droplets. Its characteristic is that the temperature of the provided medium is sufficient to maintain the wall temperature above the freezing point even after heat exchange with the inlet duct wall. This gas source typically originates from the interstage bleed air of an aircraft engine compressor, where the gas has a higher temperature due to compression. Since the fundamental function of this gas source in this invention is to raise the wall temperature through convective heat transfer with the duct wall to achieve anti-icing, it can functionally be called a heat exchange gas source. Other sources in aircraft or engine systems that can provide gaseous heat media that meet the temperature and flow requirements can be considered equivalent heat exchange gas sources, as long as they can achieve the same purpose of transferring heat to a designated area for exchange. Furthermore, the transported high-temperature gas can also be called a heat exchange gas.

[0040] In some illustrative embodiments of this disclosure, the outer casing 2 and the inner casing 1 form an annular channel. The central body 3 needs to be securely mounted and positioned inside the outer casing 2 to resist the aerodynamic pressure generated by high-speed airflow, vibrations from engine operation, and other possible external loads. The support plate extends radially and its two ends are rigidly connected to the inner wall of the outer casing 2 and the outer wall of the inner casing 1, respectively, for example, by welding, bolting, or integral molding.

[0041] In this implementation, the support plate creates several circumferentially distributed rigid connection points between the outer casing 2 and the inner casing 1, connecting the two casings into a unified, deformation-resistant frame structure. The radial support of the support plate effectively prevents the inner casing 1 from radially shifting or oscillating under airflow, ensuring that the annular intake channel formed by the outer casing 2, inner casing 1, and central body 3 maintains its designed concentricity and geometry, thereby maintaining the expected intake efficiency and airflow stability.

[0042] In some illustrative embodiments of this disclosure, multiple support plates can be configured and evenly distributed circumferentially to provide more balanced structural support and airflow guidance. The direction of the first flow channel inside the support plate can be straight, or it can be designed as a broken line or curve according to the internal space of the support plate and the heat exchange requirements, as long as it can realize the flow of high-temperature gas and heat transfer. The connection method of the high-temperature gas source can be a rigid pipeline connection or a connection form with a certain degree of flexibility to adapt to the thermal expansion and contraction of the structure.

[0043] In this implementation, the support plate, acting as a composite of a load-bearing structure and a fluid channel, has an internal first flow channel that allows externally introduced high-temperature gas to be directly delivered to the air intake. As the high-temperature gas flows through the first flow channel, it transfers heat to the solid structure of the support plate, particularly the leading edge, through convective heat transfer with the channel wall. This maintains the support plate wall temperature above the freezing point of water droplets, effectively preventing supercooled water droplets from icing upon impact on the support plate surface. Integrating the fluid channel within the support plate avoids the need for separate anti-icing piping within the air intake, reducing the number of system parts, lowering overall weight, simplifying assembly, and improving structural compactness. This design provides the structural basis for implementing efficient and integrated anti-icing measures at the air intake location.

[0044] Figure 3 A schematic cross-sectional view of the first flow channel in an embodiment of the present disclosure is shown.

[0045] According to embodiments of this disclosure, such as Figure 3 As shown, the support plate has a baffle extending radially along the intake passage to divide the first flow passage into a first section 41 near the leading edge and a second section 42 near the trailing edge. The first section 41 is configured to guide the flow of high-temperature gas in a first direction, and the second section 42 is configured to guide the flow of high-temperature gas in a second direction opposite to the first direction.

[0046] In some illustrative embodiments of this disclosure, a partition is provided inside the support plate. The partition extends radially along the support plate, and its two side edges are respectively connected to the upper and lower walls constituting the cavity of the support plate, thereby dividing a continuous internal cavity into two spatially isolated parallel flow channels. One flow channel is near the leading edge of the support plate and is defined as the first segment 41; the other flow channel is near the trailing edge of the support plate and is defined as the second segment 42. To achieve specific heat distribution, high-temperature gas is guided to flow in from one end of the first segment 41 and flows through the entire first segment 41 in a first direction (e.g., from the root wall to the tip wall or vice versa), completing the heating of the leading edge region. Thereafter, the airflow changes direction through an external connecting pipe or a pre-set deflection chamber inside the support plate, enters the inlet of the second segment 42, and flows through the second segment 42 in a second direction opposite to the first direction, thereby heating the trailing edge region.

[0047] In this implementation, by configuring the first section 41 to preferentially flow through the leading edge region, it is ensured that anti-icing heat can be concentrated and efficiently transported to the windward leading edge, which has the highest risk of icing, thus achieving enhanced heating of the critical area. Subsequently, the airflow turns back and flows through the second section 42 to supplement the heating of the trailing edge region. At the same time, the arrangement of the first section 41 and the second section 42 extends the flow path and heat exchange time of the high-temperature gas inside the support plate, improving the thermal energy utilization rate of the single gas working fluid within the support plate. From a structural perspective, a single baffle realizes the function of a dual flow channel, avoiding the complexity of setting up two independent piping systems for heating the leading and trailing edges separately, and improving the compactness and lightweight of the overall support plate structure.

[0048] Figure 4 A cross-sectional view of the heart body in an embodiment of this disclosure is shown schematically.

[0049] According to embodiments of this disclosure, such as Figure 2 and Figure 4 As shown, a second flow channel extending along the profile of the central body 3 is formed between the inner and outer wall surfaces of the central body 3. The air inlet of the second flow channel is connected to the air outlet of the first section 41, and the air outlet of the second flow channel is connected to the air inlet of the second section 42.

[0050] In some illustrative embodiments of this disclosure, the central body 3 is a double-walled structure with an inner wall surface and an outer wall surface. A certain gap exists between the inner and outer wall surfaces, extending continuously along the aerodynamic profile of the central body 3, thereby forming a second flow channel inside the central body 3 that matches its external shape. This second flow channel has an inlet end A2 and an outlet end B1. The inlet end A2 is connected to the outlet end A1 of the first section 41 within the support plate via a pipe or internal channel. Correspondingly, the outlet end B1 of the second flow channel is connected to the inlet end B2 of the second section 42 within the support plate via a pipe or internal channel, thus forming a continuous fluid loop.

[0051] In this implementation, the second flow channel extends along the profile of the central body 3, allowing high-temperature gas to flow close to the complex aerodynamic surface of the central body 3. By connecting the inlet A2 of the second flow channel to the outlet A1 of the first section 41, and connecting the outlet B1 of the second flow channel to the inlet B2 of the second section 42, a series, directional hot gas flow path is established between the support plate and the central body 3. This design allows the gas flowing out from the first section 41 of the support plate, which has undergone preliminary heat exchange and has been cooled, to be introduced into the second flow channel of the central body 3 for continued flow. As the gas flows through the second flow channel, it exchanges heat with the wall of the central body 3, thereby heating the surface of the central body 3 to achieve anti-icing. Subsequently, the gas that has completed this heat exchange is discharged from the second flow channel and guided back to the second section 42 of the support plate for subsequent heating circulation or discharge. This series connection method enables a single high-temperature gas working medium to sequentially heat multiple key parts such as the front edge of the support plate, the central body 3, and the rear edge of the support plate. It transfers and utilizes heat energy between different components, improving the overall thermal efficiency. At the same time, it avoids the increased system complexity and weight caused by setting up independent parallel gas supply pipelines for each component.

[0052] According to embodiments of this disclosure, such as Figure 4 As shown, along the main flow direction of the intake duct, the intake end A2 of the second flow channel is located upstream of the outlet end B1 of the second flow channel.

[0053] In some illustrative embodiments of this disclosure, when viewed along the mainstream airflow within the intake duct (i.e., the direction from the inlet to the engine core), the intake end of the second flow channel, used to receive high-temperature gas from the first section 41 of the support plate, is spatially positioned upstream of the outlet end of the second flow channel used to discharge gas to the second section 42 of the support plate. Thus, the overall flow direction of the high-temperature gas within the second flow channel is from the upstream region to the downstream region of the mainstream airflow, consistent with the mainstream direction.

[0054] In this implementation, the inlet of the second flow channel is positioned upstream of the outlet, ensuring that the flow direction of the high-temperature gas within the channel aligns with the mainstream direction of the cold air outside the inlet. As the high-temperature gas flows in from the upstream end and moves downstream along the mainstream direction, its temperature gradually decreases due to continuous heat exchange with the wall. Simultaneously, the anti-icing heat load may vary across different regions of the central body 3 wall along the mainstream direction, with the upstream region typically having a higher anti-icing requirement. The flow direction aligning with the mainstream direction allows the higher-temperature gas to preferentially contact and heat the upstream wall, while the lower-temperature gas flows to the downstream region with a relatively lower heat load. This achieves a better match between heat supply and anti-icing requirements, contributing to improved uniformity of wall temperature distribution and heat exchange efficiency. Furthermore, this unidirectional arrangement reduces additional flow resistance and pressure loss that may result from sharp changes in airflow direction or reverse flow, helping to maintain a stable and smooth flow field within the entire anti-icing gas loop, thereby reducing the pressure required from the induced draft gas source.

[0055] According to embodiments of this disclosure, such as Figure 4 As shown, within the meridional section including the intake duct axis, the profile of the central body 3 has a hump apex, which is the point where the radial distance of the central body 3 profile from the intake duct axis is the greatest. Along the main flow direction of the intake duct, the profile of the central body 3 includes an upstream segment 31 located upstream of the hump apex and a downstream segment 32 located downstream of the hump apex. The average curvature of the upstream segment 31 is configured to be greater than the average curvature of the downstream segment 32.

[0056] In some illustrative embodiments of this disclosure, the aerodynamic shape of the central body 3 is defined by its profile. Viewed in a meridional section including the intake axis, this profile appears as a smooth, outwardly convex curve. A special point on this curve, called the hump apex, is the location on the entire profile with the greatest radial distance from the intake axis, i.e., the point where the profile is most convex. Using the hump apex as a boundary, along the main flow direction of the intake (upstream airflow direction), the profile is divided into two parts: the portion between the hump apex and the intake inlet is called the upstream segment 31, and the portion between the hump apex and the engine direction is called the downstream segment 32. The average curvature of the upstream segment 31 is configured to be greater than the average curvature of the downstream segment 32.

[0057] In this implementation, the greater curvature of the upstream section 31 causes the airflow to experience a more abrupt change in direction as it flows through this region. According to the principle of inertial separation, solid particles or supercooled water droplets carried in the air, due to their larger mass and stronger inertia, tend to deviate from the streamline and be thrown outwards when following the abrupt deflection of the airflow, thus achieving initial separation of impurities from the mainstream air. Secondly, placing the region with greater curvature in the upstream section 31, and designing the curvature inflection point (hump apex) as the point farthest from the axis on the profile, means that this apex region is where the airflow velocity and static pressure change significantly, and it is also where the impact intensity of supercooled water droplets may be high, thus being a critical area with a prominent risk of icing.

[0058] The downstream section 32 employs a smaller average curvature, resulting in a smoother expansion or turning of the airflow in this region. This helps reduce the risk of airflow separation, promotes pressure recovery, and reduces total pressure loss, thereby optimizing the overall performance of the intake. Therefore, this asymmetric curvature distribution coordinates the requirements of enhancing foreign object separation capability (through the large curvature upstream) and ensuring good aerodynamic efficiency (through the small curvature downstream). At this point, the upstream section 31 at and near the apex of the hump is the area that requires focused protection.

[0059] According to embodiments of this disclosure, the average curvature of the upstream segment 31 is configured as follows: And / or, the average curvature of the downstream segment 32 is configured as follows: .

[0060] In a specific embodiment of this disclosure, the profile of the central body 3 is a non-axisymmetric, integral, through-space surface. The curvature of the upstream segment is... to Between, its mean curvature is The standard deviation of the curvature variation is 7.34. The upstream section maintains a relatively large average curvature overall, with drastic local variations in curvature. The point of maximum curvature ( It generates extremely strong streamline curvature at specific local locations, thereby applying maximum centrifugal acceleration to foreign objects carried in the airflow, ensuring that even small particles can obtain sufficient inertial separation force.

[0061] Meanwhile, the curvature of the downstream section is to Between, its mean curvature is The standard deviation of the curvature variation is 6.74. Its average curvature is smaller than that of the upstream section, and the curvature variation is relatively gentler (with a slightly lower standard deviation). Downstream of the flow channel where the main foreign matter separation has been completed, the relatively gentle average profile curvature guides the clean airflow to make smoother flow changes or expansions. This effectively suppresses airflow separation and vortex generation, thereby minimizing flow losses and ensuring the total pressure recovery performance of the intake duct.

[0062] In summary, the curvature configuration of the upstream and downstream sections involves a larger and more drastically varied curvature distribution in the upstream section to enhance the centrifugal effect and improve foreign matter separation efficiency. The downstream section, while ensuring necessary aerodynamic functions, employs a relatively gentle curvature distribution to optimize airflow quality and reduce total pressure loss. Experiments have shown that the total pressure recovery coefficient reaches 99%, and the fine sand separation efficiency reaches 84.71%.

[0063] According to embodiments of this disclosure, such as Figure 1 and Figure 2 As shown, it also includes a sand discharge volute 5, which is disposed on the outer casing 2 and surrounds the outside of the central body 3.

[0064] In some illustrative embodiments of this disclosure, the intake system further includes a sand venting housing 5. The sand venting housing 5 is mounted inside the outer casing 2 and arranged radially around the central body 3.

[0065] In some illustrative embodiments of this disclosure, the sand-discharging volute 5 is a spiral or involute shell structure with a gradually changing cross-section, one end of which begins in the region near the downstream of the hump of the central body 3.

[0066] In this implementation, when air flows over the surface of the central body 3 with its highly curved upstream section 31, the larger water droplets or sand particles it carries are thrown outwards by inertia. A sand-removing volute 5 surrounds the central body 3, forming a cavity for collecting these separated solid particles and liquid water droplets. The spiral design utilizes the airflow's own energy to guide and transport impurities accumulated near the wall, causing them to move along the volute channel and then be discharged outside the intake system. This process continuously removes impurities from the mainstream airflow, effectively preventing the separated foreign matter from accumulating in the intake duct, being re-intaken into the mainstream, or entering the engine core, thus protecting critical components such as compressor blades from corrosion and damage. Simultaneously, maintaining a clean flow path helps ensure stable aerodynamic performance of the intake system during long-term operation and prevents blockage by foreign matter.

[0067] Figure 5 A schematic cross-sectional view of the housing according to an embodiment of the present disclosure is shown.

[0068] According to embodiments of this disclosure, such as Figure 5 As shown, the outer shell 6 is disposed between the central body 3 and the sand-discharging volute 5. The outer shell 6 is configured as a hollow structure with a sandwich layer, and the sandwich layer of the outer shell 6 defines a third flow channel extending along the extension direction of the outer shell 6. The end of the outer shell 6 near the support plate forms the air inlet end of the third flow channel, and the end of the outer shell 6 away from the support plate is provided with an air outlet. The air inlet end of the third flow channel is connected to the air outlet end of the second section 42, and the air outlet of the third flow channel is connected to the air inlet channel.

[0069] In some illustrative embodiments of this disclosure, the intake system further includes an outer casing 6. The outer casing 6 is disposed within an annular space between the radially outer side of the central body 3 and the radially inner side of the sand-discharging volute 5. The outer casing 6 itself is constructed as a double-walled hollow structure with an inner wall and an outer wall, the interlayer gap between the inner and outer walls forming a continuous third flow channel extending circumferentially and axially along the outer casing 6. At the end of the outer casing 6 near the intake duct inlet and the support plate array 4, its interlayer structure forms the intake end of the third flow channel. An air outlet is provided at the end of the outer casing 6 away from the support plate array 4.

[0070] In this implementation, the air inlet of the third flow channel is connected to the air outlet of the second section 42 inside the support plate, and the air outlet of the third flow channel is connected to the mainstream airflow path of the air inlet. The gas flowing out from the second section 42 of the support plate, whose temperature has been further reduced after heat exchange with the leading edge and the central body 3, is introduced into the third flow channel of the outer shell 6. When the gas flows through the third flow channel, it exchanges heat with the wall surface of the outer shell 6, thereby heating the annular structural area located between the central body 3 and the sand discharge volute 5 and preventing ice formation on the surface of this area. Finally, the gas that has completed this heat exchange is released back into the mainstream airflow path of the air inlet from the air outlet. This design achieves a third effective utilization of high-temperature gas, using the heat energy of a single gas source to heat the leading edge of the support plate, the central body 3, and the outer shell 6 in sequence, and the anti-icing requirements of these three parts decrease sequentially, thereby greatly improving the cascade efficiency of heat energy utilization and overall economy. Meanwhile, by constructing the outer casing 6 itself as a heat exchange channel, the necessity of adding independent heating pipes is again avoided, maintaining the high integration and compact structure of the intake system after the introduction of efficient anti-icing function. The gas is eventually discharged back to the mainstream, which also minimizes the loss of working fluid flow caused by anti-icing induced gas.

[0071] In some illustrative embodiments of this disclosure, the outer casing 2 extends structurally along the main flow direction of the intake duct and is divided into two independent parts at a specific axial position. One part of the outer casing 2 extends outward, and the outer wall of the sand discharge volute 5 is connected and fixed to the inner wall of this part of the outer casing 2, thereby supporting and positioning the sand discharge volute 5 within the intake duct. The other part of the outer casing 2 is located between the central body 3 and the aforementioned outwardly extending part, forming an annular support structure. The outer casing 6 is connected and fixed to this annular support structure, such that the outer casing 6 is suspended within the annular space between the central body 3 and the sand discharge volute 5. The central body 3 is connected and fixed to the corresponding structure of the inner casing 1 via its mounting edge.

[0072] The above-mentioned connection and fixing methods include, but are not limited to, bolt connection, welding or riveting, as long as the structural integrity, relative positional accuracy and sealing requirements between components can be ensured in the engine operating environment.

[0073] In this implementation, the split design of the outer casing 2 provides independent and stable mounting bases for the two functional components, the sand venting volute 5 and the outer casing 6. This modular mounting method allows the sand venting volute 5 and the outer casing 6 to be manufactured and assembled separately, and finally integrated into a whole through the two parts of the outer casing 2, simplifying the manufacturing and assembly process. The central body 3 is mounted and fixed through the inner casing 1, establishing the reference axis of the entire intake system's aerodynamic core.

[0074] Figure 6 A schematic cross-sectional view of the ejector conduit and ejector device according to an embodiment of the present disclosure is shown.

[0075] According to embodiments of this disclosure, such as Figure 7 As shown, it also includes ejector line 8 and ejector line 9. Ejector line 8 is connected to the outlet of sand discharge volute 5. Ejector line 9 is connected to ejector line 8 and is used to introduce high-pressure gas into ejector line 8 to generate a suction effect.

[0076] In some illustrative embodiments of this disclosure, the air intake system further includes an ejector line 8 and an ejector line 9. One end of the ejector line 8 is connected to the outlet of the sand discharge volute 5. The ejector line 9 is connected to the ejector line 8 and is used to introduce high-pressure gas into the ejector line 8.

[0077] In this implementation, ejector line 9 introduces high-pressure gas into ejector line 8. The high-pressure gas forms a high-speed jet within ejector line 8, and according to Bernoulli's principle, this high-speed airflow causes a local decrease in static pressure. This low-pressure area is directly connected to the outlet of the sand discharge volute 5 via a pipe, thereby generating a directional suction effect within the sand discharge volute 5. This suction effect forces foreign particles and liquid water contained within the cavities of the sand discharge volute 5 into ejector line 8, where they are carried by the high-speed airflow and ultimately discharged outside the engine or to a designated collection area. This active ejection and discharge mechanism ensures continuous and reliable removal of foreign matter, preventing the separated foreign matter from depositing within the sand discharge volute 5 or re-mixing into the clean mainstream, thus guaranteeing the long-term effective operation of the inertial separation system and the unobstructed flow of the intake passage.

[0078] Figure 7 A schematic cross-sectional view of the separated lip according to an embodiment of the present disclosure is shown.

[0079] According to embodiments of this disclosure, such as Figure 7As shown, it also includes a separation lip 7, which is located on the inner wall of the air intake duct downstream of the central body 3. The separation lip 7 forms a throat channel that gradually narrows along the mainstream direction of the air intake duct, so as to bounce at least part of the foreign matter separated by the central body 3 back to the sand discharge volute 5.

[0080] In some illustrative embodiments of this disclosure, the intake system further includes a separation lip 7. The separation lip 7 is disposed on the inner wall of the intake duct downstream of the central body 3. The inner surface profile of the separation lip 7 is configured to gradually converge inward along the mainstream direction of the intake duct, thereby forming a throat channel with a gradually narrowing flow cross-section within the intake duct, i.e., a channel for foreign objects to enter the sand discharge volute 5.

[0081] In this implementation, when larger foreign particles attempt to follow the airflow change direction, the curvature of their trajectory is less than the curvature of the airflow streamline. This causes some particles to fail to flow closely against the inner wall and instead collide with the surface of the separation lip 7. After the collision, the particle's direction of motion changes, and it is rebounded towards the annular area outside the intake duct. This area is connected to or adjacent to the inlet or collection space of the upstream sand discharge volute 5 in the flow direction, allowing the rebounded particles to enter the receiving cavity of the sand discharge volute 5, thus enhancing the overall system's ability to capture foreign objects.

[0082] According to embodiments of this disclosure, such as Figure 2 and Figure 7 As shown, the separation lip 7 is configured as a hollow structure with a sandwich layer. The sandwich layer of the separation lip 7 defines a fourth flow channel extending along the profile of the separation lip 7. The fourth flow channel is connected to an external high-temperature gas source.

[0083] In some illustrative embodiments of this disclosure, the separation lip 7 is configured as a double-walled hollow structure with an inner wall and an outer wall. The gap between the inner and outer walls forms a fourth flow channel that extends continuously along the aerodynamic profile of the separation lip 7. The fourth flow channel is provided with an air inlet, which is connected to an external high-temperature air source via a pipeline.

[0084] In this implementation, the fourth flow channel provides integrated anti-icing capability for the separation lip 7. High-temperature gas is introduced from an external gas source and flows through the fourth flow channel extending along the lip profile. As the gas flows within the flow channel, it undergoes convective heat transfer through the flow channel wall in contact with it, efficiently transferring heat to the separation lip 7 to prevent icing. Since the separation lip 7 itself is a pneumatic component that guides airflow and achieves foreign object repulsion through its specific geometry, surface icing will directly alter its profile, block the throat channel, and severely impair its separation function. Therefore, the direct heating method of the built-in fourth flow channel can effectively prevent this functional component from failing due to icing, ensuring the reliable operation of the entire multi-stage foreign object separation system in icing environments.

[0085] Figure 8A schematic cross-sectional view of a radial air intake according to an embodiment of the present disclosure is shown.

[0086] In some illustrative embodiments of this disclosure, such as Figure 8 As shown, the intake system includes a radial intake passage 10. One end of this passage is connected to the external atmospheric environment of the gas turbine, and the other end is connected to the inlet area of ​​the particle separator. Its function is to draw external air into the particle separator. The structure of this passage is designed to guide and transform the initial radial airflow into an axial flow that is approximately around the central axis, thereby achieving axial intake.

[0087] In such an implementation, the central space at the inlet of the gas turbine typically requires the placement of a central body 3 support structure or other components. By employing a radial intake channel 10 and converting the airflow to axial direction at the inlet section, the high-speed radial airflow can be prevented from directly scouring or interfering with these components located in the radial central region, providing them with the necessary spatial layout and aerodynamic protection.

[0088] Secondly, when an aircraft or gas turbine is running, the external airflow relative to the engine is primarily axial. Simple axial or radial air intake can easily cause foreign objects (such as sand, dust, and water droplets) carried in the air to be directly propelled along a straight line of inertia into the particle separator or deeper components. Axial air intake, however, forces the air to undergo a directional change from radial to axial, roughly parallel to the engine axis, before entering the core area of ​​the separator. During this change, larger foreign particles, due to their greater inertia, are less likely to keep up with the rapid change in airflow direction, thus being initially separated at the inlet stage and tending to be thrown towards the outer wall. This creates more favorable initial conditions for subsequent, more refined inertial separation within the particle separator, overall reducing the risk of large foreign particles directly entering and damaging internal components.

[0089] In some illustrative embodiments of this disclosure, the intake system is equipped with icing detectors and temperature sensors in areas prone to icing within the intake duct, such as the leading edge of the support plate, the upstream wall of the hump of the central body 3, the outer shell, and the separation lip 7. These sensors continuously monitor the physical state of their respective areas and transmit signals characterizing the icing risk or wall temperature to the control unit in real time. The control unit is the core processing component of the system, internally configured with temperature thresholds determined based on the icing temperature of supercooled water droplets and a safety margin, and capable of integrating the direct physical signals from the icing detectors for comprehensive judgment.

[0090] Figure 9 The schematic diagram illustrates the anti-icing and de-icing process of the intake system according to an embodiment of the present disclosure.

[0091] In some illustrative embodiments of this disclosure, such as Figure 9As shown, the workflow is as follows: When the control unit receives a temperature sensor signal from a certain area simultaneously or individually, indicating that the wall temperature is close to or below the anti-icing threshold, or when the icing detector detects ice formation, it determines that the area needs anti-icing and de-icing operations. Subsequently, the control unit generates and issues a control command to drive the high-temperature air valve of the corresponding pipeline to open. The high-temperature air valve acts as an actuator, and its opening allows high-temperature gas from the compressor interstage bleed air to enter the flow channel network integrated inside the intake duct structure through two preset inlets: the intake support plate and the separation lip 7.

[0092] The high-temperature gas then flows through the path formed by the first flow channel inside the support plate, the second flow channel inside the central body 3, the third flow channel inside the outer shell 6, and the fourth flow channel inside the separation lip 7. As the gas flows through these channels, heat is transferred to the corresponding wall surface of the intake duct through convective heat transfer with the solid walls, raising its surface temperature. This heating process continues until the sensor located in that area indicates that the wall temperature has stabilized above the safe threshold. At this point, the control unit determines that the anti-icing requirement has been eliminated and then issues a command to close the corresponding high-temperature air valve, interrupting the heating of that area, thus ending a single anti-icing cycle.

[0093] This workflow achieves fully automated control from state perception and intelligent judgment to precise action. Its core advantage lies in changing the traditional continuous or timed heating mode commonly used in thermal anti-icing systems, transforming it into on-demand heating based on actual physical conditions. This closed-loop control strategy based on real-time monitoring effectively avoids energy waste, activating heating only when there is a clear risk of icing, minimizing the consumption of high-temperature gas drawn from the engine compressor, thereby ensuring flight safety while improving the overall performance and economy of the engine.

[0094] It should also be noted that the directional terms mentioned in the embodiments, such as "up," "down," "front," "back," "left," and "right," are only for reference to the directions in the accompanying drawings and are not intended to limit the scope of protection of this disclosure. Throughout the drawings, the same elements are identified by the same or similar reference numerals. Conventional structures or constructions will be omitted where they may cause confusion in understanding this disclosure.

[0095] The embodiments of this disclosure have been described above. However, these embodiments are for illustrative purposes only and are not intended to limit the scope of this disclosure. Although various embodiments have been described above, this does not mean that the measures in the various embodiments cannot be used advantageously in combination. The scope of this disclosure is defined by the appended claims and their equivalents. Various substitutions and modifications can be made by those skilled in the art without departing from the scope of this disclosure, and all such substitutions and modifications should fall within the scope of this disclosure.

Claims

1. An air intake system for an aircraft engine, characterized in that, include: Outer casing; The inner casing is coaxially disposed within the outer casing; The central body is configured as a rotating structure and is disposed in the inner casing, and the annular area between the outer casing, the inner casing and the central body forms an air intake; The support plate array includes at least one support plate arranged at the inlet position of the air intake duct. The support plate extends radially along the air intake duct and is disposed between the outer casing and the inner casing. The support plate has a first flow channel that is connected to an external high-temperature air source.

2. The intake system according to claim 1, characterized in that, The support plate has a partition that extends radially along the air intake to divide the first flow channel into a first section near the leading edge and a second section near the trailing edge. The first segment is configured to guide the flow of high-temperature gas along a first direction, and the second segment is configured to guide the flow of high-temperature gas along a second direction opposite to the first direction.

3. The intake system according to claim 2, characterized in that, A second flow channel extending along the profile of the central body is formed between the inner and outer wall surfaces of the central body. The air inlet of the second flow channel is connected to the air outlet of the first section, and the air outlet of the second flow channel is connected to the air inlet of the second section.

4. The intake system according to claim 3, characterized in that, Along the main flow direction of the air intake, the air intake end of the second flow channel is located upstream of the air outlet end of the second flow channel.

5. The intake system according to claim 3, characterized in that, Within a meridional section including the intake duct axis, the profile of the central body has a hump apex, which is the point on the central body profile that is furthest from the intake duct axis in the radial direction. Along the main direction of the air intake, the profile of the central body includes an upstream segment located upstream of the apex of the hump and a downstream segment located downstream of the apex of the hump, wherein the average curvature of the upstream segment is configured to be greater than the average curvature of the downstream segment.

6. The intake system according to claim 5, characterized in that, The average curvature of the upstream segment is configured as follows: ; And / or, the average curvature of the downstream segment is configured as follows: .

7. The intake system according to claim 3, characterized in that, Also includes: The sand-discharging volute is located on the outer casing and surrounds the outside of the central body.

8. The intake system according to claim 7, characterized in that, Also includes: An outer shell is disposed between the central body and the sand discharge volute. The outer shell is configured as a hollow structure with a sandwich layer, and the sandwich layer of the outer shell defines a third flow channel extending along the extension direction of the outer shell. The end of the outer casing near the support plate forms the air inlet of the third flow channel, and the end of the outer casing away from the support plate is provided with an air outlet. The air inlet of the third flow channel is connected to the air outlet of the second section, and the air outlet of the third flow channel is connected to the air inlet.

9. The intake system according to claim 7 or 8, characterized in that, Also includes: The ejector pipe is connected to the outlet of the sand discharge volute. An ejector device, connected to the ejector line, is used to introduce high-pressure gas into the ejector line to generate a suction effect.

10. The intake system according to claim 7 or 8, characterized in that, Also includes: A separation lip is located on the inner wall of the air intake duct on the downstream side of the central body; The separation lip forms a throat channel that gradually narrows along the mainstream direction of the air intake, so as to bounce at least a portion of the foreign matter separated by the central body back to the sand discharge volute.

11. The intake system according to claim 10, characterized in that, The separation lip is configured as a hollow structure with a sandwich, the sandwich defining a fourth flow channel extending along the profile of the separation lip, the fourth flow channel being connected to an external high-temperature gas source.

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