Inlet guide vane for a compressor

Abstract

The invention provides an inlet guide vane for a gas compressor. The inlet guide vane is installed on a stator casing of the gas compressor with a gas collection cavity. Comprising a first mounting part and a guide vane body. And the first mounting part is connected with the stator casing. The guide vane body is connected to the first mounting part, a heat exchange cavity communicating with the gas collection cavity is formed in the guide vane body, and a plurality of exhaust holes communicating with the external environment are formed in the suction surface side of the guide vane body so that heat exchange gas in the gas collection cavity can be exhausted through the heat exchange cavity. At least two filling assemblies are arranged in the heat exchange cavity, each filling assembly comprises at least one filling column, and each filling column is inclined relative to the radial direction of the stator casing and extends from one side of the heat exchange cavity to the other side of the heat exchange cavity in the thickness direction of the guide blades. The packed columns are inclined relative to the radial direction of the stator casing, the flowing path and the flowing state of heat exchange gas are changed, airflow disturbance and turbulent flow mixing is enhanced, the heat exchange area is increased, and the heat exchange efficiency is improved.

Description

Technical Field

[0001] This disclosure relates to the field of gas turbine engine technology, and more particularly to an inlet guide vane for a compressor. Background Technology

[0002] When aero-engines operate in high-humidity, low-temperature environments, the guide vanes at the compressor inlet are at risk of icing. Accumulated ice can alter the aerodynamic profile of the blades, inducing flow separation and stall. Detached ice debris can also damage downstream rotor blades. Therefore, effective anti-icing measures are crucial for ensuring engine safety and performance. Currently, hot gas bleed air anti-icing technology is widely used. This involves introducing heat-exchanging gas from the rear stage of the compressor into the internal cavity of the blades, heating the blade walls to prevent icing.

[0003] Existing technologies typically design the interior of blades as a smooth, hollow cavity structure. When heat-exchanging gas flows through the cavity, the contact area between the gas and the cavity wall is primarily determined by the cavity's geometric surface area, which is limited. This results in insufficient convective heat transfer intensity between the gas and the metal wall, leading to low heat transfer efficiency and preventing the blade's outer surface temperature rise from achieving the desired anti-icing effect. To increase the wall temperature, it is often necessary to increase the bleed air volume, but this results in a loss of core engine power and a reduction in overall engine efficiency. Summary of the Invention

[0004] To address at least one of the aforementioned and other technical problems in the related art, this disclosure provides an inlet guide vane for a compressor, installed in the stator casing of a compressor having a gas collecting chamber. It includes a first mounting portion and a guide vane body. The first mounting portion is connected to the stator casing. The guide vane body is connected to the first mounting portion. The interior of the guide vane body has a heat exchange chamber communicating with the gas collecting chamber. The suction side of the guide vane body has multiple exhaust holes communicating with the external environment, allowing the heat exchange gas in the gas collecting chamber to be discharged through the heat exchange chamber. At least two filling assemblies are provided within the heat exchange chamber. Each filling assembly includes at least one filling column, and each filling column is inclined relative to the radial direction of the stator casing and extends from one side of the heat exchange chamber to the other side in the thickness direction of the guide vane.

[0005] According to embodiments of this disclosure, each filling component includes at least two filling pillars, each filling pillar intersecting with at least one other filling pillar.

[0006] According to an embodiment of the present disclosure, the extension direction of each filling column is at 45 degrees to the plane defined by the radial direction and the axial direction of the stator casing, the plane defined by the radial direction and the circumferential direction of the stator casing, and the plane defined by the axial direction and the circumferential direction of the stator casing.

[0007] According to embodiments of this disclosure, a plurality of exhaust holes are arranged in at least one row in the chordal direction on the suction surface side, and the exhaust holes in the same row are spaced apart along the spanwise direction of the guide vane.

[0008] According to an embodiment of this disclosure, the angle between the axial direction of the exhaust port and the tangent direction of the exhaust port at its position on the suction side is greater than or equal to 30° and less than or equal to 45°, and the angle between the exhaust port and the axial direction of the stator casing is less than or equal to 30°.

[0009] According to embodiments of this disclosure, the diameter of the vent hole is greater than or equal to 1 mm and less than or equal to 3 mm; and / or, the ratio of the distance between two adjacent vent holes along the spanwise direction to the diameter of the vent hole is greater than or equal to 3 and less than or equal to 6.

[0010] According to embodiments of this disclosure, the gas collecting chamber is configured to at least partially surround a first mounting portion, on which an air inlet channel is provided. The air inlet channel includes a first channel, a second channel, and a seal. The first channel is configured to extend radially along the stator casing and connect the two ends of the gas collecting chamber surrounding the first mounting portion. The second channel is configured to extend axially along the stator casing and connect the first channel to a heat exchange chamber. The seal is disposed at the connection point between the first channel and the gas collecting chamber.

[0011] According to embodiments of this disclosure, the seal is configured to extend toward the outer side of the outer casing in a direction away from the blade body, and to form a clamping portion that fits tightly against the outer side of the outer casing. The anti-icing structure also includes a fastening assembly fitted onto the first mounting portion, the fastening assembly including a first pressure plate disposed on the side of the seal away from the outer casing and configured to clamp the clamping portion.

[0012] According to embodiments of this disclosure, the fastening assembly further includes a third pressure plate. The third pressure plate abuts directly or indirectly against the side of the first pressure plate away from the outer casing and is configured to have an inwardly projecting protrusion. The first mounting portion has a recess opposite the protrusion, and the protrusion and recess cooperate to secure the first mounting portion to the outer casing.

[0013] According to embodiments of this disclosure, the fastening assembly further includes a second pressure plate located between the first and third pressure plates. The anti-icing structure also includes an adjustment member disposed between the first and second pressure plates, the adjustment member being configured to connect to the first mounting portion and be rotatable about the axis of the first mounting portion to adjust the mounting angle of the guide vane body.

[0014] According to the illustrative embodiments of this disclosure, the guide vanes, by setting the filling column in the heat exchange cavity to be inclined radially relative to the stator casing, change the flow path and flow state of the heat exchange gas, enhance airflow disturbance and turbulent mixing, thereby improving the convective heat transfer efficiency between the gas and the solid. Simultaneously, the increased heat transfer area further improves the heat transfer efficiency. Attached Figure Description

[0015] The above and other objects, features, and advantages of this disclosure will become clearer from the following description of embodiments of the present disclosure with reference to the accompanying drawings, in which:

[0016] Figure 1 This is a perspective view of the stator casing and guide vanes according to an embodiment of the present disclosure;

[0017] Figure 2 This is a partial cross-sectional view of the stator casing and guide vanes according to an embodiment of the present disclosure;

[0018] Figure 3 A cross-sectional view of the connection between the guide vane and the stator casing in one embodiment of this disclosure;

[0019] Figure 4 This is a cross-sectional view of the guide vane body according to an embodiment of the present disclosure;

[0020] Figure 5 This is a cross-sectional view of the guide vane body from another direction, according to an embodiment of this disclosure.

[0021] Figure 6 This is a partial view of the guide vane body according to an embodiment of the present disclosure;

[0022] Figure 7 Another partial cross-sectional view of the guide vanes and stator casing of an embodiment of this disclosure.

[0023] In the accompanying drawings, the meanings of the reference numerals are as follows:

[0024] 1. First mounting section; 11. Recess; 2. Stator housing; 3. Gas collecting chamber.

[0025] 4. Intake passage; 41. First passage; 42. Second passage; 43. Seals.

[0026] 5. Guide vane body; 51. Filling assembly; 511. Filling column; 52. Exhaust port.

[0027] 6. Adjusting component; 7. Fastening assembly; 71. First pressure plate; 72. Second pressure plate; 73. Third pressure plate; 731. Protrusion; X: Radial direction of the stator housing; Y: Axial direction of the stator housing; Z: Circumferential direction of the stator housing. Detailed Implementation

[0028] 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.

[0029] 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 the stated features, steps, operations, and / or components, but do not exclude the presence or addition of one or more other features, steps, operations, or components.

[0030] 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.

[0031] 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.

[0032] Figure 1 This is a perspective view of the stator casing 2 and guide vanes according to an embodiment of the present disclosure. Figure 2 This is a partial cross-sectional view of the stator casing 2 and guide vanes according to an embodiment of this disclosure. Figure 3 This is a cross-sectional view of the guide vane connected to the stator casing 2 in one embodiment of the present disclosure.

[0033] like Figure 1 and Figure 2 As shown, the guide vanes involved in this embodiment are installed in the inlet section of the aero-engine compressor. The guide vanes are installed in the stator casing 2. Specifically, the first mounting part 1 passes through the mounting hole on the stator casing 2 and is fixed relative to the stator casing 2.

[0034] To facilitate the description of the orientation and relative relationships of the various structures in this embodiment, the following directions are defined: the direction parallel to the engine main shaft and pointing downstream of the airflow is the axial direction of the stator casing 2 (Y direction in the figure). The direction perpendicular to the engine main shaft and radiating outward along the casing radius is the radial direction of the stator casing 2 (X direction in the figure); and also the direction perpendicular to the plane formed by the axial (Y) and radial (X) directions. In the cylindrical coordinate system of the engine, this direction, i.e., the circumferential direction around the main shaft axis, is the circumferential direction of the stator casing 2. In this disclosure, for ease of description, the tangential direction of the circumference at the location of the guide vanes is defined as the circumferential direction of the stator casing 2 (Z direction in the figure). The spanwise direction of the guide vanes is the direction from the blade root connected to the casing to the blade tip away from the casing; the chordal direction of the guide vanes is the straight line direction from the leading edge to the trailing edge of any given cross-section of the blade. The thickness direction of the guide vanes is the direction within the same cross-section of the blade, perpendicular to both the chordal and spanwise directions at its location.

[0035] It is important to note that, because guide vanes are typically mounted on the stator casing with a certain installation angle (i.e., the angle between the blade chord and the engine axis), and the blade profile itself may have three-dimensional torsion, their local chord, spanwise, and thickness directions usually do not coincide with the axial (Y), radial (X), and Z) directions of the stator casing 2. For example, the blade's thickness direction is generally not parallel to the global Z direction; the blade's spanwise direction may also deviate from the purely radial (X) direction. Only when the guide vane is in a specific zero installation angle and in an ideal state without torsion can its local coordinate directions be aligned with the global coordinate directions.

[0036] In an engine, the core function of the guide vanes located in the first stage of the compressor is to regulate the direction of the intake airflow. By driving the guide vanes to rotate around the axis of the first mounting part 1 through an external actuation mechanism, the installation angle of the vanes can be changed. This change in installation angle causes the vanes to apply a tangential velocity component to the airflow from upstream, i.e., to pre-swirl the airflow. By adjusting the angle of attack of the airflow as it enters the first-stage rotor blades through pre-swirl, the airflow can impact the rotor blades at a more optimal aerodynamic angle.

[0037] To address at least one of the aforementioned and other technical problems in the related art, this disclosure provides an inlet guide vane for a compressor, installed in the stator casing 2 of a compressor having a gas collecting chamber 3. It includes a first mounting portion 1 and a guide vane body 5. The first mounting portion 1 is connected to the stator casing 2. The guide vane body 5 is connected to the first mounting portion 1. The interior of the guide vane body 5 has a heat exchange chamber communicating with the gas collecting chamber 3. The suction side of the guide vane body 5 is provided with multiple exhaust holes 52 communicating with the external environment, so that the heat exchange gas in the gas collecting chamber 3 can be discharged through the heat exchange chamber. At least two filling assemblies 51 are provided in the heat exchange chamber. Each filling assembly 51 includes at least one filling column 511. Each filling column 511 is configured to be inclined relative to the radial direction X of the stator casing 2 and extends from one side of the heat exchange chamber to the other side in the thickness direction of the guide vane.

[0038] In some illustrative embodiments of this disclosure, the inlet guide vane is connected and fixed to the stator casing 2 via its first mounting portion 1. The guide vane body 5 has a hollow heat exchange chamber inside, which is connected to the air collection chamber 3 on the stator casing 2 via an air intake channel 4 opened in the first mounting portion 1.

[0039] In some illustrative embodiments of this disclosure, at least two filling assemblies 51 are provided inside the heat exchange chamber. Each filling assembly 51 includes at least one filling column 511, which is configured to be inclined relative to the radial direction X of the stator casing 2 and extend along the thickness direction of the guide vane, so that it penetrates from one inner wall of the heat exchange chamber (e.g., the inner wall near the pressure surface) to the other inner wall (e.g., the inner wall near the suction surface).

[0040] In this implementation, high-temperature anti-icing gas drawn from the compressor's downstream stage enters the heat exchange chamber via the gas collecting chamber 3 and the inlet channel 4. The presence of a packing column 511 within the heat exchange chamber increases the total contact heat transfer area between the heat exchange gas and the metal wall. Simultaneously, the inclined arrangement of the packing column 511 disturbs and diverts the airflow, enhancing the gas turbulence and thus increasing the intensity of convective heat transfer between the gas and the solid surface. Heat is conducted from the heat exchange gas through the packing column 511 and the chamber wall to the entire guide vane body 5, causing a uniform increase in surface temperature and preventing icing.

[0041] Furthermore, the inclined filling column 511 guides the gas along a longer spiral or tortuous path, extending its residence time within the cavity and ensuring sufficient heat transfer. Finally, the cooled gas is discharged through multiple exhaust ports 52 located on the blade suction surface and merges into the compressor mainstream. This structure enhances the utilization efficiency of the anti-icing gas by strengthening the internal heat exchange process.

[0042] In some illustrative embodiments of this disclosure, at least two filling components 51 are arranged in a two-dimensional array inside the heat exchange cavity in a plane formed by the radial direction X and the axial direction Y of the stator casing 2. Each filling component 51 is assigned to a specific unit region, and multiple unit regions are arranged in a regular interval in the radial and axial directions to form a cover within the space of the heat exchange cavity.

[0043] In other illustrative embodiments of this disclosure, the array arrangement of the filling components 51 can be a uniform matrix, or a non-uniform or gradient distribution. For example, based on the differences in anti-icing heat load in different areas of the blade surface, a higher density array of filling components 51 can be arranged in areas with higher heat exchange requirements, such as near the leading edge of the blade or at a specific radial height; while in areas with relatively low heat exchange requirements or strict restrictions on flow resistance, the array spacing can be appropriately increased. The shape of the unit region of the filling component 51 can be a cuboid, a cube, or other polyhedron capable of spatial tessellation.

[0044] In this implementation, the filling components 51 are arranged in an array along the radial and axial directions, firstly dividing the entire heat exchange cavity into multiple continuous and regularly distributed heat exchange sub-units in space. This ensures that when the heat exchange gas flows through the heat exchange cavity, it can systematically and uniformly exchange heat with the area corresponding to the wall of the entire guide vane body 5, avoiding local heat accumulation or insufficient heat. Each filling component 51 serves as a local heat exchange enhancement unit, and the airflow flowing through the unit is disturbed by the internal filling column 511 structure, thereby enhancing local convective heat transfer.

[0045] Multiple such units are connected in series along the flow path, causing the heat exchange gas to be repeatedly disturbed and continuously in contact with the surface of the heat exchange column as it passes through the entire array, thereby improving heat exchange efficiency. At the same time, the arrayed layout also helps to guide the airflow to form a more uniform and stable flow field within the heat exchange cavity, reducing the formation of low-speed zones or dead zones, making heat transfer more efficient.

[0046] According to the illustrative embodiments of the present disclosure, each filling assembly 51 includes at least two filling posts 511, each filling post 511 intersecting with at least one other filling post 511.

[0047] In some illustrative embodiments of this disclosure, the intersection of each filling column 511 with at least one other filling column 511 refers to the physical contact and connection of the filling columns 511 at a certain spatial point or along a certain length during spatial extension, forming a spatial grid structure with nodes. The intersection angle between the filling columns 511 can be fixed, such as a 90-degree perpendicular intersection, or other angles. The intersection point can be located in the middle section of the filling column 511 or at the end of the filling column 511. All the filling columns 511 are interconnected to form a continuous, integrated, and geometrically defined overall skeleton structure.

[0048] In other illustrative embodiments of this disclosure, two filler pillars 511 simply intersect at one point, or one filler pillar 511 intersects with multiple filler pillars 511 at multiple different locations, forming a multi-node connection. The connection at the intersection point can be that the filler pillars 511 directly merge and intersect, forming a rigid node without relative motion. The mesh formed by the intersection is an extension of a two-dimensional planar mesh in three-dimensional space, or a three-dimensional mesh structure.

[0049] In this implementation, the interlocking filler columns 511 first form a spatial grid skeleton with continuous internal support in the mechanical structure. This skeleton divides the unit space inside the heat exchange cavity into a large number of smaller interconnected pores, and distributes the load to the entire filler assembly 51 through the interlocking nodes, and finally to the inner wall of the guide vane body 5, thereby enhancing the overall structural rigidity of the filler assembly 51 and its resistance to airflow impact or vibration.

[0050] Secondly, the intersecting structure provides more contact surfaces, with each intersection node itself forming part of the heat exchange surface, thereby increasing the total effective contact heat exchange area between the filling component 51 and the heat exchange gas. Simultaneously, the intersecting filling columns 511 divide and disturb the airflow channel. When the heat exchange gas flows through the porous medium formed by the intersecting filling columns 511, the airflow is divided, redirected, and flows around the surface of the filling columns 511, resulting in a tortuous and variable flow path. This significantly enhances the turbulence within the gas and the relative velocity between the gas and the solid surface, thus strengthening the convective heat transfer process. The intersections, acting as local flow barriers, further disturb the airflow, disrupting any potential thermal boundary layer and promoting heat exchange. Therefore, by intersecting the filling columns 511 to form a spatial grid, the physical stability of the structure is improved, and the heat exchange area and enhanced flow disturbance are increased. These two factors synergistically improve the overall heat transfer efficiency and uniformity within the heat exchange cavity, from the heat exchange gas to the filling component 51 and then to the wall of the guide vane body 5.

[0051] In some illustrative embodiments of this disclosure, the cross-sectional shape of the filler rod is circular, and its diameter d is set to be greater than or equal to 0.3 mm and less than or equal to 0.5 mm. In the filler rod segments defined by the intersection nodes, the ratio of the segment length L between two adjacent nodes to the rod diameter d is 4. This filler structure, including the filler rods with the above-mentioned specific dimensions and proportions and the grid formed therein, is preferably formed by additive manufacturing technology. Specifically, the filler rods and the guide vane body 5 are integrally formed by metal 3D printing technology, thereby ensuring the geometric accuracy and integrity of the complex internal structure.

[0052] In other illustrative embodiments of this disclosure, the cross-sectional diameter of the filler rod can be selected from specific values ​​such as 0.3 mm, 0.4 mm, or 0.5 mm. The ratio of the rod segment length L between two adjacent nodes to the rod diameter d can be fine-tuned within a range of 3.5 to 4.5 according to the optimization objectives of flow resistance and heat transfer intensity. The manufacturing process is not limited to a specific type of metal 3D printing; any additive manufacturing technology that can achieve high-precision, one-piece molding of complex internal flow channels is applicable.

[0053] In this implementation, the ratio of rod length L to diameter d between nodes is 4, defining a dense and uniform mesh structure. Within a given space, the filling rods can have multiple intersecting nodes, which serve as structural support points, additional heat transfer surfaces, and sources of flow disturbance. This ratio allows the mesh to have high porosity to reduce flow resistance while also possessing a large unit heat transfer area and high structural stiffness.

[0054] Furthermore, the use of additive manufacturing technology for integral molding ensures the precise determination of the size, position, and cross-joint connection of the filling rod, while also ensuring a strong connection between the filling structure and the cavity wall, which is beneficial for heat conduction.

[0055] In other illustrative embodiments of this disclosure, the filling structure takes various forms. For example, the filling structure can be an open-cell foam metal structure with a continuous, interconnected, and randomly or regularly distributed pore network, providing extremely high specific surface area and strong airflow turbulence. It can also be a periodic lattice structure, such as a three-dimensional truss, gyroscope, or diamond lattice unit arranged periodically in space, combining excellent specific surface area, structural stiffness, and controllable porosity. It can also be a corrugated plate / fin array structure, arranging a series of parallel corrugated thin plates or fins along a specific direction to form multiple tortuous flow channels, increasing the heat transfer area and guiding airflow. Furthermore, biomimetic honeycomb structures, hierarchical porous structures, etc., are also acceptable, as long as they meet the requirements of manufacturability and enhanced heat transfer.

[0056] According to the illustrative embodiment of the present disclosure, the extension direction of each filling post 511 is at 45 degrees to the plane defined by the radial direction X of the stator housing 2 and the axial direction Y of the stator housing 2, the plane defined by the radial direction X of the stator housing 2 and the circumferential direction Z of the guide vane, and the plane defined by the axial direction Y of the stator housing and the circumferential direction Z of the guide vane.

[0057] In some illustrative embodiments of this disclosure, the spatial unit of the filling component 51 is a virtual cubic region inside the heat exchange cavity. Among the eight vertices of the cubic unit, there are four spatial body diagonals, each connecting a pair of spatially opposite vertices. Within this unit, a plurality of filling pillars 511 are provided, corresponding to the number of body diagonals. The central axis of each filling pillar 511 extends precisely along the direction of one of the body diagonals and from one vertex of the cubic unit to the opposite vertex.

[0058] Therefore, within a cubic unit corresponding to a filling component 51, up to four filling columns 511 extending along different body diagonal directions can be accommodated. These columns intersect at the geometric center of the cube, forming a spatially converging core node. When multiple such filling components 51 are arranged in radial and axial arrays, adjacent cubic units share the vertices of their interfaces. The filling columns 511 within adjacent units extend from one vertex to the other, which then serves as the starting point for another filling column 511, thus connecting the filling columns 511 of different filling components 51 end-to-end. This allows the filling columns 511 of multiple arrayed units to form a continuous support and heat transfer network.

[0059] In other illustrative embodiments of this disclosure, the shape of the spatial unit corresponding to each filling component 51 is not limited to a cube, but can also be a cuboid or other parallelepiped, with its body diagonal defined accordingly as a spatial line segment connecting opposite vertices of the parallelepiped. The number of filling columns 511 can be configured according to heat exchange requirements, for example, two or three filling columns 511 can be arranged only along a portion of the body diagonal direction. The cross-sectional shape of the filling column 511 remains consistent along its entire length, or varies depending on its position within the unit. The connection method between the filling columns 511 of different filling components 51 can be that the filling column 511 entities are directly connected as one piece at a shared vertex (e.g., integrally formed by additive manufacturing), or the ends of the separately manufactured filling columns 511 can be mechanically fixed by connection nodes set at the vertices.

[0060] In this implementation, the single filling column 511 has a longer length within a finite unit space, resulting in a larger column surface area, which maximizes the contact heat transfer area between the filling material and the heat transfer gas within a given unit volume.

[0061] Furthermore, the diagonal orientation of the filling column 511 ensures that it has significant components along the three coordinate axes of the stator casing 2: radial (X), axial (Y), and circumferential (Z). This multidirectional nature allows a single filling column 511 to effectively disturb and impede airflow components from multiple directions simultaneously, forcing the airflow to deflect and mix in three dimensions. This disrupts the laminar boundary layer and promotes intense three-dimensional turbulence, thereby significantly enhancing the convective heat transfer intensity.

[0062] In embodiments where infill columns 511 are arranged along all diagonal directions, multiple infill columns 511 converge at the center of the unit to form a symmetrical and stable spatial truss core, thereby improving the load-bearing and deformation resistance of the infill assembly 51.

[0063] Furthermore, by connecting the filling columns 511 end-to-end at the shared vertices of different filling components 51, the reinforced structure inside the entire heat exchange cavity is no longer an isolated unit, but is integrated into a continuous, seamlessly connected, overall mesh skeleton in three-dimensional space. This enhances the overall rigidity and vibration stability of the internal structure.

[0064] According to the illustrative embodiment of the present disclosure, a plurality of exhaust holes 52 are arranged in at least one row in the chordal direction on the suction surface side, and the exhaust holes 52 in the same row are arranged at intervals along the spanwise direction of the guide blade.

[0065] In some illustrative embodiments of this disclosure, a plurality of exhaust ports 52 for discharging heat exchange gases are provided on the suction side of the guide vanes. In the chordal direction of the guide vanes, the exhaust ports 52 are organized into at least one continuous row. Each row contains a plurality of independent exhaust ports 52, which are arranged at equal intervals along the spanwise direction of the guide vanes. Each row of exhaust ports 52 forms a linear array extending in the spanwise direction. The direction of extension of the row is generally parallel to the chordal direction.

[0066] Specifically, "the extension direction of the exhaust holes 52 is roughly parallel to the chord direction" means that the geometric lines formed by the arrangement of the exhaust holes 52 on the suction surface of the blade generally align with the chord direction of the blade at that local location. Furthermore, the outer surface of the actual guide vane is a curved surface with a certain degree of distortion in three-dimensional space, and the local chord direction at different spanwise positions may differ. Simultaneously, the machining and arrangement of the exhaust holes 52 must comprehensively consider the influence of manufacturing tolerances, surface curvature, and the final aerodynamic optimization goals. Therefore, "roughly parallel" refers to an angular deviation between the two caused by the three-dimensional shape and machining of the guide vane, as well as a certain degree of startup optimization, and this angular deviation is acceptable in actual use.

[0067] In other illustrative embodiments of this disclosure, the exhaust holes 52 are arranged in multiple rows, with the rows of exhaust holes 52 parallel to each other and spaced apart along the chord direction. The spanwise spacing of the exhaust holes 52 can be uniform or non-uniform. For example, in the mid-section region of the blade where the risk of icing may be higher, a smaller spanwise spacing is used to arrange more densely packed exhaust holes 52; in the root and tip regions of the blade, a relatively larger spacing is used. The diameter of the exhaust holes 52 within the same row can be the same or can be varied according to the aerodynamic or heat transfer requirements of their spanwise location.

[0068] In this implementation, the chordally arranged rows create a continuous, spanwise extending line of high-temperature gas discharge on the blade surface. When these gases are discharged into the main flow, at the chordally located position of the rows, the multiple fine jets discharged spanwise can interact and more easily coalesce on the blade surface. This helps to form a more uniform, coherent, and stable gas film on the suction surface of the blade. The gas film can, to some extent, separate the blade surface from the airflow of the external environment, thereby further improving the anti-icing effect.

[0069] According to the illustrative embodiment of the present disclosure, the angle ββ between the axial direction of the exhaust port 52 and the tangent direction of the exhaust port 52 at its position on the suction surface side is greater than or equal to 30° and less than or equal to 45°, and the angle αα between the exhaust port 52 and the axial direction Y of the stator casing is less than or equal to 30°.

[0070] In some illustrative embodiments of this disclosure, the angle between the axial direction of the exhaust hole 52 and the local tangential direction of the blade suction surface at the opening point is greater than or equal to 30 degrees and less than or equal to 45 degrees.

[0071] In some other illustrative embodiments of this disclosure, the angle between the axial direction of the exhaust port 52 and the local tangential direction of the blade suction surface at the opening point is including but not limited to 30°, 35°, 40° and 45°.

[0072] In this implementation, the angle is configured so that the heat-exchange gas exiting the orifice has a sufficiently large normal velocity component pointing outwards from the blade surface. This normal component allows the airflow to overcome the resistance of the mainstream boundary layer after leaving the orifice and propel itself outwards for an effective distance, thereby forming a gas film or high-temperature air layer of the required thickness and with a wider coverage on the blade surface downstream of the orifice, preventing icing on the guide blade surface. If the angle is too small, the jet may have difficulty detaching from the wall, causing the hot air to be entrained prematurely, resulting in poor coverage; if the angle is too large, the jet may penetrate the mainstream too deeply, causing severe mixing losses and weakening the protection of the wall.

[0073] In some illustrative embodiments of this disclosure, the angle α between the axial direction of the exhaust port 52 and the axial direction Y of the stator casing is less than or equal to 30°.

[0074] In some other illustrative embodiments of this disclosure, the angle α between the axial direction of the exhaust port 52 and the axial direction Y of the stator casing includes, but is not limited to, 0°, 5°, 10°, 15°, 20°, 25° and 30°.

[0075] In this implementation, the velocity direction of the heat-exchange gas ejected from the exhaust port 52 is relatively close to the ideal average flow direction of the mainstream gas at the compressor inlet (i.e., the axial direction of the stator casing 2). When the exhaust jet direction is close to the mainstream flow direction, the difference in the lateral velocity components between their velocity vectors is significantly reduced. This directly reduces the strong shearing action and momentum exchange caused by the significant difference in velocity direction and magnitude between the exhaust jet and the high-speed mainstream during mixing. This, in turn, leads to aerodynamic mixing losses, generates additional flow resistance, and may induce unstable flow. Reducing negative interference with the mainstream flow field is beneficial for maintaining the aerodynamic efficiency and stability of the compressor.

[0076] According to the illustrative embodiments of the present disclosure, the diameter of the exhaust hole 52 is greater than or equal to 1 mm and less than or equal to 3 mm; and / or, the ratio of the spacing between two adjacent exhaust holes 52 along the spanwise direction to the diameter of the exhaust hole 52 is greater than or equal to 3 and less than or equal to 6.

[0077] In some illustrative embodiments of this disclosure, the exhaust hole 52 opened on the suction surface has a diameter of greater than or equal to 1 mm and less than or equal to 3 mm.

[0078] In other illustrative embodiments of this disclosure, specific aperture values ​​include, but are not limited to, 1 mm, 1.5 mm, 2 mm, 2.5 mm, and 3 mm.

[0079] In this implementation, orifices with a diameter of 1 to 3 millimeters can generate sufficiently fine gas jets. These fine jets have a large surface area-to-volume ratio, which facilitates rapid heat exchange between the jet and the air near the blade surface and makes it easier for them to adhere to the wall and form a continuous gas film. Too small an orifice diameter may lead to manufacturing difficulties, easy clogging, and limited flow rate per orifice; too large an orifice diameter will result in an excessively coarse jet, making it difficult to form a uniform thin gas film and exacerbating penetration and disturbance to the mainstream flow field. Therefore, this orifice diameter range optimizes the heat and mass transfer characteristics of the jet while ensuring manufacturability and sufficient flow capacity.

[0080] In some illustrative embodiments of this disclosure, the ratio of the straight-line distance between the centers of two adjacent exhaust holes 52 along the spanwise direction of the guide vane (from the root to the top) to the diameter of the exhaust hole 52 is set in the range of 3 to 6.

[0081] In some other illustrative embodiments of this disclosure, the ratio of the straight-line distance between the centers of two adjacent exhaust holes 52 along the guide vane to the diameter of the exhaust hole 52 is, but is not limited to, 3, 3.5, 4, 4.5, 5, 5.5 and 6.

[0082] In this implementation, the ratio of the straight-line distance between the centers of two adjacent exhaust holes 52 along the spanwise direction of the guide vane to the diameter of the exhaust hole 52 ensures that the two adjacent exhaust jets, after being discharged and diffused along the spanwise direction, can effectively converge and overlap on the blade surface, thereby constructing a continuous high-temperature gas coverage layer in the spanwise direction and eliminating anti-icing blind spots. If this ratio is too small (i.e., the hole spacing is too small), although the coverage continuity is better, it may cause premature mutual interference and merging between jets, weakening the wall adhesion and coverage ability of each independent jet, and may also affect the local structural strength of the blade due to excessively dense openings; if this ratio is too large (i.e., the hole spacing is too large), it is difficult for the jets to be effectively connected, leaving gap areas on the blade surface that are not directly covered by high-temperature gas, resulting in uneven anti-icing effect. Therefore, a ratio range of 3 to 6 can achieve uniform anti-icing effect, effective jet action, and reliable structural strength.

[0083] According to the guide vanes provided in the illustrative embodiment of this disclosure, the gas collecting chamber 3 is configured to at least partially surround the first mounting portion 1, on which an air intake channel 4 is provided. The air intake channel 4 includes a first channel 41, a second channel 42, and a seal 43. The first channel 41 is configured to extend in the radial direction X of the stator casing 2 and connect the two ends of the gas collecting chamber 3 surrounding the first mounting portion 1. The second channel 42 is configured to extend in the axial direction Y of the stator casing and connect the first channel 41 to the heat exchange chamber. The seal 43 is disposed at the connection between the first channel 41 and the gas collecting chamber 3.

[0084] In some illustrative embodiments of this disclosure, the gas collecting cavity 3 is configured as a partial annular cavity or similar structure within the stator housing 2, surrounding the first mounting portion 1, thereby at least partially surrounding the first mounting portion 1. The first channel 41 extends in the same direction as the radial direction X of the stator housing 2, and its two ends communicate with both sides of the gas collecting cavity 3 surrounding the first mounting portion 1. The second channel 42 extends in the same direction as the axial direction Y of the stator housing, with one end communicating with the first channel 41 and the other end leading to the heat exchange chamber inside the guide vane body. A seal 43 is provided at the interface between the first channel 41 and the gas collecting cavity 3 to fill any assembly gaps that may exist between the first mounting portion 1 and the stator housing 2, ensuring that the heat exchange gas flowing from the gas collecting cavity 3 into the first channel 41 does not leak from this point to the external environment or other areas of the engine.

[0085] In this embodiment, the first channel 41 connects both sides of the gas collecting chamber 3 radially, ensuring that the gas pressure within the gas collecting chamber 3 acts evenly on both sides of the first mounting portion 1 regardless of the blade's rotation angle, and guaranteeing that gas can always enter through this channel. The second channel 42 guides the gas axially from the radial first channel 41 to the heat exchange chamber inside the blade, completing the reversal of the airflow direction and final delivery. The seal 43 prevents high-pressure heat exchange gas from leaking through the dynamic gap between the gas collecting chamber 3 and the rotating first mounting portion 1.

[0086] According to the illustrative embodiment of the present disclosure, the seal 43 is configured to extend away from the blade body to the outside of the outer casing and form a pressing portion that fits tightly against the outside of the outer casing. The anti-icing structure also includes a fastening assembly 7 sleeved on the first mounting portion 1, the fastening assembly 7 including a first pressure plate 71 disposed on the side of the seal 43 away from the outer casing and configured to press the pressing portion.

[0087] In some illustrative embodiments of this disclosure, the main body of the seal 43 is mounted at the interface between the first mounting portion 1 and the stator casing 2. The seal 43 is designed to have an extension extending away from the guide vane body (typically pointing outwards towards the engine or maintenance side). This extension extends to the outer surface of the outer casing and is formed at its end into a radially enlarged clamping portion. The clamping portion has a contact surface adapted to the shape of the outer surface of the outer casing, allowing the clamping portion to adhere tightly to this outer surface. The anti-icing structure also includes a fastening assembly 7 fitted onto the first mounting portion 1. The fastening assembly 7 includes a first pressure plate 71 located on the side of the clamping portion of the seal 43 extension away from the outer casing. The first pressure plate 71 is configured to apply an axial clamping force directly or indirectly to the clamping portion, thereby firmly pressing the clamping portion against the outer surface of the outer casing.

[0088] In other illustrative embodiments of this disclosure, the extension of the seal 43 may be a resilient cylindrical or sleeve-like structure. The clamping part may be a flange, annular flange, or a block with a flat clamping surface integrally formed with the extension. The first clamping plate 71 may be a separate annular gasket or a component integrated with other fastening parts.

[0089] In this embodiment, the seal 43 extends outward from the casing and forms a pressed portion. Combined with the axial pressing action of the first pressure plate 71, a controllable and stable sealing force is first established at the sealing interface. The pressing force provided by the first pressure plate 71 forces the pressed portion of the seal 43 to fit tightly against the outer surface of the casing. This contact surface constitutes the main sealing line or sealing surface that prevents high-pressure heat exchange gas in the gas collecting chamber 3 from leaking axially along the first mounting portion 1. This allows the magnitude and uniformity of the sealing force to be effectively controlled and adjusted by the fastening assembly 7, ensuring the reliability of the seal.

[0090] According to the guide vane provided in the illustrative embodiment of this disclosure, the fastening assembly 7 further includes a second pressure plate 73. The second pressure plate 73 abuts directly or indirectly against the side of the first pressure plate 71 away from the outer casing and is configured to have an inwardly projecting protrusion 731. The first mounting portion 1 has a recess 11 opposite to the protrusion 731, and the protrusion 731 cooperates with the recess 11 to secure the first mounting portion 1 to the outer casing.

[0091] In some illustrative embodiments of this disclosure, the fastening assembly 7 further includes a second pressure plate 73. The second pressure plate 73 has an inwardly protruding protrusion 731 that extends radially inward toward the axis of the first mounting portion 1. Correspondingly, a recess 11, such as a groove, a partial recess, or a hole, is machined on the outer cylindrical surface or end face of the first mounting portion 1, corresponding in position and matching in shape to the protrusion 731 of the second pressure plate 73. When the fastening assembly 7 is assembled and a preload is applied, the protrusion 731 of the second pressure plate 73 is inserted into or engaged in the recess 11 of the first mounting portion 1, forming a fitting engagement.

[0092] In this embodiment, the second pressure plate 73 is mechanically interlocked with the recess 11 on the first mounting portion 1 by its protrusion 731, thereby providing a defined circumferential positioning and reliable axial retention.

[0093] According to the illustrative embodiment of the present disclosure, the guide vane, the fastening assembly 7 further includes a second pressure plate 72 located between the first pressure plate 71 and the second pressure plate 73. The anti-icing structure also includes an adjustment member 6 disposed between the first pressure plate 71 and the second pressure plate 72, the adjustment member 6 being configured to connect to the first mounting portion 1 and be rotatable about the axis of the first mounting portion 1 to adjust the mounting angle of the guide vane body 5.

[0094] In some illustrative embodiments of this disclosure, the fastening assembly 7 further includes a second pressure plate 72 between the first pressure plate 71 and the second pressure plate 73. The second pressure plate 72 is sleeved on the first mounting portion 1, located between and adjacent to the first pressure plate 71 and the second pressure plate 73. The anti-icing structure also includes an adjusting member 6 disposed between the first pressure plate 71 and the second pressure plate 72. The adjusting member 6 is connected to the first mounting portion 1 and is rotatable about the axis of the first mounting portion 1. When the adjusting member 6 rotates, through its interaction with the first pressure plate 71, the second pressure plate 72, or related structures on the first mounting portion 1, it can drive the guide vane body 5 to rotate about its own axis, thereby changing the mounting angle of the guide vane body 5 (i.e., the angle between the blade chord and the engine axial reference).

[0095] In this embodiment, the introduction of the second pressure plate 72 adds an intermediate component to the axial clamping force transmission path. Its main function is to isolate and transmit the forces from the second pressure plate 73 and the adjusting member 6 to a certain extent from the first pressure plate 71 and the seal 43. When the adjusting member 6 is operated to rotate and change the mounting angle of the guide vane body 5, the axial position of the adjusting member 6 may change slightly, or it may generate uneven forces on adjacent components. The second pressure plate 72 can absorb or buffer this dynamic action related to adjustment, preventing it from being directly and completely transmitted to the first pressure plate 71, thereby helping to maintain the stability of the sealing pressure applied by the first pressure plate 71 to the sealing member 43, and avoiding seal failure due to adjusting the blade angle.

[0096] In some illustrative embodiments of this disclosure, the adjusting member 6 is an annular or sleeve-shaped component surrounding the first mounting portion 1. It is connected to the first mounting portion 1 via a threaded connection; that is, the outer cylindrical surface of the first mounting portion 1 is machined with external threads, and the inner hole of the adjusting member 6 is machined with matching internal threads. By screwing the adjusting member 6, it can be axially displaced along the axis of the first mounting portion 1. This axial displacement is transmitted through the second pressure plate 72, and then converted into a pushing or pulling action on the rocker arm or drive mechanism connected to the guide vane body 5, ultimately causing the guide vane body 5 to rotate around its axis, thereby adjusting the mounting angle.

[0097] In other illustrative embodiments of this disclosure, the adjusting member 6 is connected to the first mounting part 1 via a spline or keyway, allowing it to slide along the axis but not rotate relative to it. The adjusting member 6 is provided with a fixing nut that mates with it; rotating the nut drives the adjusting member 6 to move axially.

[0098] 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.

[0099] 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 inlet guide vane for a compressor, installed in the stator casing of a compressor having a gas collecting chamber, characterized in that, include: The first mounting part is connected to the stator casing; The guide vane body is connected to the first mounting part. The interior of the guide vane body has a heat exchange chamber that communicates with the gas collection chamber. The suction side of the guide vane body is provided with multiple exhaust holes that communicate with the external environment so that the heat exchange gas in the gas collection chamber can be discharged through the heat exchange chamber. The heat exchange cavity is provided with at least two filling assemblies, each of which includes at least one filling column. Each filling column is configured to be inclined relative to the radial direction of the stator casing and extend from one side of the heat exchange cavity to the other side in the thickness direction of the guide vanes.

2. The guide vane according to claim 1, characterized in that, Each of the filling components includes at least two filling columns, and each of the filling columns intersects with at least one other filling column.

3. The guide vane according to claim 2, characterized in that, The extension direction of each of the filling columns is at 45 degrees to the planes defined by the radial and axial directions of the stator casing, the planes defined by the radial and circumferential directions of the stator casing, and the planes defined by the axial and circumferential directions of the stator casing.

4. The guide vane according to any one of claims 1 to 3, characterized in that, The plurality of exhaust holes are arranged in at least one row in the chordal direction on the suction surface side, and the exhaust holes in the same row are arranged at intervals along the spanwise direction of the guide vane.

5. The guide vane according to claim 4, characterized in that, The angle between the axial direction of the exhaust port and the tangent direction of the exhaust port at the position of the exhaust port on the suction surface side is greater than or equal to 30° and less than or equal to 45°, and the angle between the exhaust port and the axial direction of the stator casing is less than or equal to 30°.

6. The guide vane according to claim 5, characterized in that, The diameter of the exhaust port is greater than or equal to 1 mm and less than or equal to 3 mm; and / or, the ratio of the distance between two adjacent exhaust ports along the spanwise direction to the diameter of the exhaust port is greater than or equal to 3 and less than or equal to 6.

7. The guide vane according to claim 1, characterized in that, The air collection chamber is configured to at least partially surround the first mounting portion, and the first mounting portion is provided with an air intake channel, the air intake channel comprising: The first channel is configured to extend radially along the stator casing and connect the two ends of the gas collection chamber surrounding the first mounting portion. The second channel is configured to extend along the axial direction of the stator casing and communicate with the first channel and the heat exchange chamber. A sealing element is provided at the junction of the first channel and the gas collection chamber.

8. The guide vane according to claim 7, characterized in that, The seal is configured to extend outward from the outer casing in a direction away from the blade body and to form a pressing portion that fits tightly against the outer casing. The guide vane also includes a fastening assembly sleeved on the first mounting portion. The fastening assembly includes a first pressure plate disposed on the side of the seal away from the outer casing and configured to press the pressure portion.

9. The guide vane according to claim 8, characterized in that, The fastening assembly also includes: The third press plate abuts directly or indirectly against the side of the first press plate away from the outer casing and is configured to have an inwardly protruding protrusion. The first mounting portion has a recess opposite to the protrusion, and the protrusion and the recess cooperate to fix the first mounting portion to the outer casing.

10. The guide vane according to claim 9, characterized in that, The fastening assembly further includes a second pressure plate located between the first pressure plate and the third pressure plate; The guide vane also includes an adjustment member disposed between the first pressure plate and the second pressure plate. The adjustment member is configured to be connected to the first mounting portion and can rotate about the axis of the first mounting portion to adjust the mounting angle of the guide vane body.

Images