Treatment casing for ultrahigh-load transonic-speed serial rotor and gas compressor

Abstract

The invention provides a treatment casing for an ultrahigh-load transonic-speed serial rotor and a gas compressor, and relates to the technical field of pneumatic design of gas compressors. The serial rotor comprises a front-row rotor and a rear-row rotor which are sequentially arranged in the axial direction. The treatment casing comprises a casing body and a plurality of casing channels. The casing body is arranged outside the serial rotor in a surrounding mode. The multiple casing channels are arranged on the outer wall face of the casing body at intervals in the circumferential direction of the casing body, and each casing channel comprises a suction section, a connecting section and a spraying section. The suction section extends outwards from the outer wall face of the casing body and is suitable for sucking high-pressure air flow at the tail edge of a rear row rotor, the connecting section extends in the axial direction, and one end of the connecting section is connected with the suction section. The injection section extends from the other end of the connecting section to the axis of the casing body and is suitable for spraying the high-pressure airflow from the suction section to the front edge of the rear row rotor, and the included angle between the airflow sprayed out of the injection section and the inner wall face of the casing body is larger than 55 degrees and smaller than 70 degrees.

Description

Technical Field

[0001] This invention relates to the field of compressor aerodynamic design technology, and more specifically, to a processing casing and compressor for ultra-high load transonic tandem rotors. Background Technology

[0002] The compressor is one of the core components of an aero-engine. Its main function is to continuously perform work on the intake air through a series of rotors and stator blades, increasing the air pressure and temperature, laying the foundation for efficient combustion and turbine expansion in the subsequent combustion chamber. High-thrust aero-engines generally adopt a multi-stage axial-flow structure. Its performance directly determines the engine's pressure ratio, efficiency, and overall thrust level. The internal flow of the compressor is a complex three-dimensional, unsteady, viscous turbulent flow, facing a series of severe aerodynamic challenges such as boundary layer separation, shock wave / boundary layer interference, secondary flow losses, and corner stall. With the continuous improvement of engine performance requirements (high thrust-to-weight ratio, low fuel consumption), compressor design is developing towards higher stage loads, higher pressure ratios, and wider stable operating ranges, making its internal flow control and stability issues particularly critical and prominent.

[0003] Tandem rotor compressors, as an advanced ultra-high load (load factor generally greater than 0.43) compressor design technology, utilize two rotor blade rows (front and rear rotors) connected in series on the same shaft. This aims to achieve the pressure rise typically achievable with traditional multi-stage rotors within a single stage, effectively reducing engine weight and component count, and improving thrust-to-weight ratio. However, when applied in transonic conditions (tip relative Mach number 1.2-1.6), the leakage flow at the front rotor tip generates strong unsteady interference with the shock wave. Furthermore, the leakage flow and wake of the front rotor significantly affect the flow field characteristics of the rear rotor. When the leakage flow impacts the leading edge of the rear rotor in a periodic pulsating manner, it induces boundary layer separation, leading to a sharp drop in flow instability margin and severely limiting engine performance. How to broaden the stable operating range of tandem rotors through aerodynamic design and active control strategies has become a key factor restricting the engineering application of this technology.

[0004] In aerodynamic design, casing treatment technology is representative, but traditional circumferential slots and axial slot structures struggle to balance margin and peak efficiency; the margin enhancement often comes at the cost of peak efficiency loss. Active control (e.g., jet propulsion) can achieve directional flow control, but requires an external high-pressure air source and a complex control system, increasing engine weight and airworthiness risks. Among related technologies, self-circulating casing treatment can improve compressor stall margin. It typically involves bleed air from the rear or rear stages after the rotor, using high-speed jets to suppress tip blockage. However, its application is primarily in low-load or single-rotor scenarios, and coupled design for ultra-high-load transonic conditions is lacking. Therefore, providing a casing treatment that can balance peak efficiency, margin, and system complexity under ultra-high-load transonic conditions has become a pressing technical problem. Summary of the Invention

[0005] In view of this, the present invention provides a processing casing for ultra-high load transonic tandem rotors, which guides the high-pressure airflow at the trailing edge of the captured rear rotor to the leading edge for injection, forming a closed-loop passive flow control, and by optimizing the injection angle, improves the surge margin of the tandem rotor under ultra-high load and transonic conditions, while minimizing peak efficiency loss.

[0006] To achieve the above objectives, the present invention provides a processing casing for an ultra-high load transonic tandem rotor. The tandem rotor includes a front row of rotors and a rear row of rotors arranged sequentially along the axial direction. The processing casing includes: a casing body surrounding the outside of the tandem rotors; and a plurality of casing channels spaced apart along the circumferential direction of the casing body on the outer wall surface of the casing body. Each casing channel includes: a suction section extending outward from the outer wall surface of the casing body, adapted to suction high-pressure airflow at the trailing edge of the rear row of rotors; a connecting section extending along the axial direction, one end of the connecting section being connected to the suction section; and a jetting section extending from the other end of the connecting section toward the axis of the casing body, adapted to jettison the high-pressure airflow from the suction section toward the leading edge of the rear row of rotors. The angle between the airflow ejected from the jetting section and the inner wall surface of the casing body ranges from 55° to 70°.

[0007] According to an embodiment of the present invention, the suction section and the connecting section together define a reference plane, and the angle between the extension direction of the suction section and the reference plane is in the range of 40° to 60°.

[0008] According to an embodiment of the present invention, the length of the connecting segment is L, the distance between the connecting segment and the casing body is H, and 0.25≤L / H≤0.4.

[0009] According to an embodiment of the present invention, the above-mentioned injection section is constructed as an arc-shaped pipe section, and the ratio of the radius of curvature R of the arc-shaped pipe section to the spacing H is in the range of 0.06-0.08.

[0010] According to an embodiment of the present invention, the length of the connecting segment is equal to the chord length of the blades of the rear rotor.

[0011] According to an embodiment of the present invention, the distance between the connecting section and the casing body is less than half the chord length of the blades of the rear rotor.

[0012] According to an embodiment of the present invention, both the injection port of the above-mentioned injection section and the suction port of the above-mentioned suction section are constructed as rectangles with chamfers.

[0013] According to an embodiment of the present invention, the connecting segment is constructed as a tube with a circular cross-section.

[0014] According to an embodiment of the present invention, the number of the aforementioned casing channels is 3-6.

[0015] The present invention also provides a compressor comprising a processing casing for ultra-high load transonic tandem rotors as described in any of the above embodiments, wherein the processing casing forms an inlet and an outlet at its two ends in the axial direction; inlet guide vanes are arranged at the inlet, and front and rear rotors are arranged at intervals in the axial direction, wherein the inlet guide vanes are adapted to adjust the impact angle when the airflow contacts the front rotor, wherein the casing channel of the processing casing is adapted to draw in the high-pressure airflow at the trailing edge of the rear rotor and spray it to the leading edge of the rear rotor.

[0016] The processing casing for ultra-high load transonic tandem rotors provided by this invention, through the inclusion of a suction section, a connecting section, and a jet section, captures the high-pressure airflow near the trailing edge of the rear rotor and directionally injects it into the low-pressure region near the leading edge of the rear rotor. This effectively improves the deteriorated flow field in the blade tip region of the rear rotor, alleviates channel blockage, and the jet stream directly fills the boundary layer separation initiation point, preemptively offsetting the interference flow field from the front rotor and providing energy enhancement to the mainstream. Simultaneously, this design alters the local Mach number distribution before the shock wave, shifting the shock wave position downwards and thus weakening the adverse effects of premature adverse pressure gradients on the boundary layer. The entire cycle is driven by the pressure difference between the high and low pressure regions of the rear rotor itself, requiring no external energy input. By further optimizing the jet angle, it ensures that the jet stream cuts into the low-energy region at the leading edge of the rear rotor with the optimal trajectory, significantly suppressing flow separation induced by the wake of the front rotor and shock wave interference. This improves the surge margin of the tandem rotor under ultra-high load, transonic conditions, while minimizing peak efficiency loss. Attached Figure Description

[0017] Figure 1This is a three-dimensional structural diagram of the processing casing for ultra-high load transonic tandem rotors provided in an embodiment of the present invention, showing the tandem rotors;

[0018] Figure 2 This is a three-dimensional structural diagram of the processing casing for ultra-high load transonic tandem rotors provided in an embodiment of the present invention, from another perspective.

[0019] Figure 3 This is a plan view of the processing casing for ultra-high load transonic tandem rotors provided in an embodiment of the present invention;

[0020] Figure 4 This is a planar schematic diagram of the processing casing for ultra-high load transonic tandem rotors provided in an embodiment of the present invention from another perspective;

[0021] Figure 5 This is a meridional view of the compressor provided in an embodiment of the present invention.

[0022] In the accompanying drawings, the meanings of the reference numerals are as follows:

[0023] 1. Casing body;

[0024] 2. Casing passage;

[0025] 21. Suction section;

[0026] 22. Connecting segment;

[0027] 23. Injection section;

[0028] 3. Front rotor;

[0029] 4. Rear rotor;

[0030] 5. Imported guide vanes. Detailed Implementation

[0031] Hereinafter, embodiments of the present invention will be described with reference to the accompanying drawings. However, it should be understood that these descriptions are exemplary only and are not intended to limit the scope of the invention. In the following detailed description, numerous specific details are set forth to provide a thorough understanding of the embodiments of the invention for ease of explanation. However, it will be apparent that one or more embodiments may be practiced without these specific details. Furthermore, descriptions of well-known structures and techniques are omitted in the following description to avoid unnecessarily obscuring the concept of the invention.

[0032] The terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the invention. 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.

[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", they should generally be interpreted in accordance with the meaning that is commonly understood by those skilled in the art (e.g., "a system having at least one of A, B and C" should include, but is not limited to, a system having A alone, a system having B alone, a system having C alone, a system having A and B, a system having A and C, a system having B and C, and / or a system having A, B and C, etc.).

[0035] Figure 1 This is a three-dimensional structural diagram of the processing casing for ultra-high load transonic tandem rotors provided in an embodiment of the present invention, showing the tandem rotors. Figure 2 This is a three-dimensional structural diagram of the processing casing for ultra-high load transonic tandem rotors provided in an embodiment of the present invention, from another perspective. Figure 3 This is a plan view of the processing casing for ultra-high load transonic tandem rotors provided in an embodiment of the present invention.

[0036] Embodiments of the present invention provide a processing casing for ultra-high load transonic tandem rotors, such as Figures 1 to 3 As shown, the tandem rotors include a front row of rotors 3 and a rear row of rotors 4 arranged sequentially along the axial direction. The processing casing includes a casing body 1 and multiple casing channels 2. The casing body 1 is arranged around the outside of the tandem rotors. The multiple casing channels 2 are spaced apart along the circumferential direction of the casing body 1 on the outer wall surface of the casing body 1. Each casing channel 2 includes a suction section 21, a connecting section 22, and a jetting section 23. The suction section 21 extends outward from the outer wall surface of the casing body 1 and is used to suction the high-pressure airflow at the trailing edge of the rear row of rotors 4. The connecting section 22 extends axially and is connected at one end to the suction section 21. The jetting section 23 extends from the other end of the connecting section 22 toward the axis of the casing body 1 and is used to spray the high-pressure airflow from the suction section 21 toward the leading edge of the rear row of rotors 4. The angle between the airflow ejected from the jetting section 23 and the inner wall surface of the casing body 1 ranges from 55° to 70°.

[0037] In this embodiment, the casing body 1 is constructed as a generally cylindrical shell, with the front rotor 3 and the rear rotor 4 arranged sequentially inside the casing body 1 along its axial direction. The hubs of the casing body 1 and the front / rear rotors 3 and 4 define a generally annular channel for airflow to flow into and impact the front / rear rotors 3 and 4. By providing a suction section 21, a connecting section 22, and a jet section 23, the high-pressure airflow near the trailing edge of the rear rotor 4 is captured and directionally injected into the low-pressure region near the leading edge of the rear rotor 4. This captures the deteriorated flow field at the blade tip of the rear rotor 4, improves the low-speed region at the trailing edge, alleviates the channel blockage, and the jet directly fills the boundary layer separation initiation point, preemptively offsetting the interference flow field transmitted from the front rotor 3 to the rear rotor 4, thus enhancing the energy of the mainstream flow. It can also change the local Mach number distribution before the shock wave, causing the shock wave position to move downstream and weakening the adverse effects of the premature adverse pressure gradient on the boundary layer. The entire cycle is driven entirely by the pressure difference between the high-pressure zone and the low-pressure zone of the rear rotor 4 itself, without the need for external energy input.

[0038] By further setting the angle between the airflow ejected from the injection section 23 and the inner wall of the casing body 1 to be greater than 55° and less than 70°, that is... Figure 3 The angle α shown allows the jet flow to penetrate more effectively and act on the low-energy flow region at the leading edge of the rear rotor blades 4. This ensures that when the jet flow cuts into the mainstream, it is neither too small, resulting in insufficient penetration and only limited shearing action on the boundary layer near the wall, nor too large, making it difficult to exchange energy with the rotor blades. At this optimized angle, the jet flow can reach the suction surface at the leading edge of the rear rotor 4 with the best trajectory, significantly enhancing the flow stability in this region and effectively suppressing flow separation induced by the wake and shock wave interference of the front rotor 3. This further improves the aerodynamic performance and stability margin of the tandem rotors under ultra-high load and transonic conditions.

[0039] It should be noted that the included angle α includes the endpoint values ​​of 55° and 70°.

[0040] For example, in Figure 2 The diagram shows a spatial rectangular coordinate system for reference, where the "z" direction is the axial direction of the casing body 1 or the tandem rotor, the "r" direction is the vertical direction or the radial direction parallel to the vertical direction, and the "θ" direction is the circumferential direction. Figure 3 The view of the processing casing as seen along the θ direction is shown.

[0041] Figure 4 This is a planar schematic diagram of the processing casing for ultra-high load transonic tandem rotors provided in an embodiment of the present invention from another perspective.

[0042] In one exemplary embodiment, such as Figure 3 and Figure 4 As shown, the suction section 21 and the connecting section 22 together define a reference plane, and the angle between the extension direction of the suction section 21 and the reference plane ranges from 40° to 60°.

[0043] In this implementation, the reference plane is a virtual plane that changes with the positions of the suction section 21 and the connecting section 22, but the reference plane always passes through the axis of the casing body 1. Figure 4 As shown, the angle between the extension direction of the suction section 21 and the reference plane is β. By tilting the suction section 21 relative to the reference plane, it is better matched with the flow direction of the airflow, reducing the flow loss when the airflow enters the suction section 21, making the flow of the airflow in the connecting section 22 more stable and with less loss. This ensures that the high-pressure airflow maintains high kinetic energy and concentration when it is ejected from the injection section 23. Furthermore, limiting the angle range of β to 40° to 60° allows the high-pressure airflow at the trailing edge of the rear rotor 4 to smoothly enter the casing channel 2. If β is less than 40°, the angle between the suction port of the suction section 21 and the mainstream direction of the wake is too large, which can easily cause impact loss and affect the suction efficiency. If β is greater than 60°, the suction port can easily intrude into the mainstream channel, causing additional flow resistance.

[0044] It should be noted that the included angle β includes the endpoint values ​​of 40° and 60°.

[0045] In one exemplary embodiment, such as Figure 3 As shown, the length of the connecting section 22 is L, the distance between the connecting section 22 and the casing body 1 is H, and 0.25≤L / H≤0.4.

[0046] In this implementation, the distance H between the connecting section 22 and the casing body 1 can also be called the height of the casing channel 2. By limiting the ratio of L to H to between 0.25 and 0.4, the airflow inside the casing channel 2 can be optimized, effectively controlling flow loss while ensuring sufficient flow capacity. If the ratio is less than 0.25, the connecting section 22 may be too short, failing to guide more airflow into the casing channel 2. Furthermore, after the high-pressure airflow turns from the suction section 21, it needs to enter the injection section 23 for a second turn before it has fully developed, which can easily lead to the formation of violent secondary flows and separation vortices in the connecting section 22, increasing flow loss and weakening the energy of the final ejected airflow. If the ratio is greater than 0.4, the connecting section 22 may be too long, not only increasing the overall radial dimension and weight of the casing, violating the lightweight design requirements of aero-engines, but also increasing the total pressure loss due to wall friction due to excessive flow channel length. It may also cause excessive dissipation of airflow before reaching the injection section 23, reducing the response speed and penetration capability of the ejection.

[0047] According to embodiments of this disclosure, such as Figure 3As shown, the injection section 23 is constructed as an arc-shaped pipe section, and the ratio of the radius of curvature R of the arc-shaped pipe section to the spacing H ranges from 0.06 to 0.08.

[0048] In this implementation, the injection section 23 is preferably constructed as a Coanda nozzle structure. While the included angle α is limited to 55°-70°, the ratio of R to H is further limited to 0.06 to 0.08. This facilitates smooth airflow turning and avoids local losses such as airflow separation and vortex generation caused by sharp bends or right-angle turns. This ensures that the injection airflow remains concentrated, high-speed, and high-energy, which can enhance the wall adhesion effect and enable the injection airflow to accurately ram the low-speed interference zone at the leading edge of the rear rotor 4. This avoids insufficient ramming force when α is greater than 70°, which cannot block the transmission of leakage flow, and a sharp increase in mixing losses when α is less than 55°.

[0049] Furthermore, if the ratio is less than 0.06, the curvature of the arc-shaped pipe section is too abrupt, which may cause the airflow to experience excessive centrifugal force when turning, leading to a sharp increase in the pressure gradient between the inner and outer sides of the flow channel, causing airflow separation, increasing flow losses, and making the ejected airflow unstable and divergent. If the ratio is greater than 0.08, the arc-shaped pipe section is too gentle, which may make it difficult to achieve the previously limited injection angle of 55°-70°, and will also unnecessarily increase the radial and circumferential dimensions of the casing channel 2, adversely affecting the structural compactness. At the same time, an excessively long flow channel will also increase surface friction losses.

[0050] In one exemplary embodiment, the length of the connecting segment 22 is equal to the chord length of the blades of the rear rotor 4.

[0051] In this implementation, by limiting the length of the connecting section 22 to match the chord length (or axial chord length) of the rear rotor 4, the jet airflow can be better matched in phase with the main periodic flow disturbances encountered at the leading edge of the rear rotor 4, improving the quality of the airflow flowing into the rear rotor. Furthermore, since the chord length is a key geometric parameter characterizing the aerodynamic load of the blades and the flow development space, making the length of the connecting section 22 equal to it ensures that the delivered airflow effectively covers the critical area on the suction surface of the rear rotor where flow separation is most likely to occur, achieving more precise energy injection.

[0052] In one exemplary embodiment, the distance between the connecting segment 22 and the casing body 1 is less than half the chord length of the blades of the rear rotor 4.

[0053] This implementation improves the aerodynamic dimensional compatibility between the casing channel 2 and the flow field at the tip of the rear rotor 4 blades, avoiding a disconnect between structural dimensions and flow field requirements. If the spacing H exceeds half the chord length, it will lead to volume redundancy in the entire casing channel 2, resulting in increased mass and space occupation. It will also cause the airflow to remain in the casing channel 2 for too long, easily generating secondary eddies or flow lag, interfering with self-circulation efficiency.

[0054] In one exemplary embodiment, both the injection port of the injection section 23 and the suction port of the suction section 21 are configured as rectangles with chamfers.

[0055] In this implementation, the injection and suction ports are designed as chamfered rectangular ports, which improves the adaptability to the flow field range at the blade tips of the casing body 1 and the rear rotor 4, ensuring effective coverage area for suction and injection. Specifically, the rectangular suction port can more efficiently capture the non-axisymmetric flow field structure related to the sweep direction of the rear rotor 4 blades; the rectangular injection port can generate a fan-shaped jet that better matches the shape of the blade leading edge, achieving better circumferential coverage and aerodynamic coupling. The chamfered design ensures a smooth transition of airflow when entering and exiting the casing channel 2, avoiding additional energy dissipation caused by flow separation, and ensuring high flow efficiency throughout the entire process from suction to injection.

[0056] Furthermore, the chamfered rectangular structure avoids stress concentration, extending the service life of parts under harsh vibration environments. Simultaneously, this shape is ideally suited for one-piece molding using processes such as precision casting or additive manufacturing, ensuring dimensional accuracy while facilitating demolding and powder removal, thus exhibiting excellent manufacturability.

[0057] According to an embodiment of this disclosure, the connecting segment 22 is configured as a tube with a circular cross-section.

[0058] In this implementation, the inner wall of the circular cross-section tube is relatively smooth and has no dead corners, which can effectively reduce airflow resistance and avoid flow field disturbance. The circular tube structure achieves the required strength and rigidity with a lighter weight, which meets the strict lightweight design requirements of aero-engine components, while improving the structural integrity of the entire casing channel 2, and also has good manufacturing convenience and consistency.

[0059] In one exemplary embodiment, the number of casing channels 2 is 3-6.

[0060] In this implementation, limiting the number of casing channels 2 to 3-6 balances stability margin and peak efficiency, minimizing peak efficiency loss while ensuring sufficient return flow. Fewer than 3 channels result in insufficient flow field coverage density and localized aerodynamic dead zones. For example, the flow field between the leading and trailing edges of the fourth blade of the rear rotor cannot be effectively counteracted or drawn in, failing to address the stability bottleneck of the tandem rotor. More than 6 channels significantly increase structural redundancy; the larger airflow return flow generates additional flow resistance and entropy production, reducing the peak efficiency of the tandem rotor.

[0061] Figure 5 This is a meridional view of the compressor provided in an embodiment of the present invention.

[0062] An exemplary embodiment of the present invention also provides a compressor, such as Figure 5 As shown, the device includes a processing casing for ultra-high load transonic tandem rotors as described in any of the above embodiments, an inlet guide vane 5, and front rotors 3 and rear rotors 4 spaced apart along the axial direction. The processing casing has an inlet and an outlet at its two ends in the axial direction, respectively. The inlet guide vane 5 is arranged at the inlet and is adapted to adjust the impact angle when the airflow is released from the front rotor 3. The casing channel 2 of the processing casing is adapted to draw in the high-pressure airflow from the trailing edge of the rear rotor 4 and spray it onto the leading edge of the rear rotor 4.

[0063] In this implementation, the treatment casing effectively delays the onset of compressor surge and stall by suppressing flow separation at the rear rotor blade tips and preemptively counteracting interference, enabling the compressor to operate stably over a wider flow range. The improved flow field directly reduces flow losses, while the energy-boosting effect of the jet flow on the mainstream helps increase the compressor's pressure ratio. Furthermore, when changes in operating conditions lead to increased load on the rear rotor and a deteriorating flow field, the suction-jet action of the treatment casing automatically intensifies, acting as a "negative feedback" regulation that improves compressor performance under off-design conditions. This achieves flow control effects comparable to active control systems without significantly increasing the compressor's axial length and structural complexity.

[0064] Those skilled in the art will understand that the features described in the various embodiments of the present invention can be combined and / or combined in various ways, even if such combinations or combinations are not explicitly described in the present invention. In particular, the features described in the various embodiments of the present invention can be combined and / or combined in various ways without departing from the spirit and teachings of the present invention. All such combinations and / or combinations fall within the scope of the present invention.

[0065] The embodiments of the present invention have been described above. However, these embodiments are merely illustrative and not intended to limit the scope of the invention. Although various embodiments have been described above, this does not mean that the measures in the various embodiments cannot be used advantageously in combination. Various substitutions and modifications can be made by those skilled in the art without departing from the scope of the invention, and all such substitutions and modifications should fall within the scope of the invention.

Claims

1. A process casing for a super-high-load transonic tandem rotor, the tandem rotor comprising a front row of rotors and a rear row of rotors arranged in series in an axial direction, characterized in that, The processing casing comprises: a casing body, which is arranged outside the tandem rotor in a surrounding manner; a plurality of casing channels, which are arranged on the outer wall surface of the casing body in a circumferential direction of the casing body, each of the casing channels comprising: a suction section, which extends outward from the outer wall surface of the casing body and is adapted to suck high-pressure airflow at the trailing edge of the rear row of rotors; a connecting section, which extends in the axial direction, one end of the connecting section being connected to the suction section; a jetting section, which extends from the other end of the connecting section toward the axis of the casing body and is adapted to jet the high-pressure airflow from the suction section toward the leading edge of the rear row of rotors, the jetting section jetting airflow at an included angle with the inner wall surface of the casing body ranging from 55° to 70°.

2. The process chamber for ultra-high load cross-sonic cascade rotor according to claim 1, characterized in that, The suction section and the connecting section jointly define a reference plane, and the extension direction of the suction section has an included angle with the reference plane ranging from 40° to 60°.

3. The process chamber for ultra-high load cross-sonic cascade rotor according to claim 2, characterized in that, The length of the connecting section is L, the spacing between the connecting section and the casing body is H, and 0.25≤L / H≤0.

4.

4. The process chamber for ultra-high load cross-sonic cascade rotor according to claim 3, characterized in that, The jetting section is configured as an arc-shaped tube section, and the ratio of the curvature radius R of the arc-shaped tube section to the spacing H ranges from 0.06 to 0.

08.

5. The process chamber for ultra-high load cross-sonic cascade rotor according to claim 3, characterized in that, The length of the connecting section is equal to the chord length of the blade of the rear row of rotors.

6. The process chamber for ultra-high load cross-sonic cascade rotor according to claim 3, characterized in that, The spacing between the connecting section and the casing body is less than half of the chord length of the blade of the rear row of rotors.

7. The process chamber for super-high-load cross-sonic cascade rotor according to claim 1, characterized in that, The jetting port of the jetting section and the suction port of the suction section are each configured as a rectangular shape with a chamfer.

8. The process chamber for ultra-high load cross-sonic cascade rotor according to claim 7, characterized in that, The connecting section is configured as a tube body with a circular cross section.

9. The handling cabinet for super-high-load cross-sonic tandem rotor according to any one of claims 1 to 8, characterized in that, The number of the casing channels ranges from 3 to 6.

10. A compressor characterized by, The processing casing comprises: The processing casing for the ultra-high-load transonic tandem rotor according to any one of claims 1-9, two ends of the processing casing in the axial direction forming an inlet and an outlet, respectively; an inlet guide vane arranged at the inlet; a front row of rotors and a rear row of rotors arranged in a spaced manner in the axial direction, the inlet guide vane being adapted to adjust the impact angle of airflow when the airflow contacts the front row of rotors, wherein the casing channel of the processing casing is adapted to suck high-pressure airflow at the trailing edge of the rear row of rotors and jet to the leading edge of the rear row of rotors.

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