Load compressor configuration

Abstract

The present invention discloses a load compressor configuration, comprising: a rotor assembly, and a first bearing casing and an air intake casing relatively spaced apart and installed on the outer circles at both ends of the rotor assembly. The power input end of the rotor assembly is supported on the first bearing casing through a front bearing, and the power output end of the rotor assembly is supported on the air intake casing through a rear bearing to form an independent rotor support structure. The power input end of the rotor assembly can also be detachably connected to the upstream power input system, and the power output end of the rotor assembly can also be detachably connected to the downstream power output system to ensure the input and output of the load compressor power. The present invention can form an independent rotor system, ensure an independent unit design, and then can be quickly adapted to auxiliary power units of different models and powers, with a wide range of adaptability; the rotor assembly has a short fulcrum span and strong rigidity, ensuring that the rotor system has sufficient critical speed margin.

Description

Technical Field

[0001] The present invention relates to the field of aviation engine auxiliary power devices, in particular to a load compressor configuration. Background Art

[0002] As a typical aviation turbine power unit, the auxiliary power unit's main function is to start the main engine to provide high-pressure gas and electrical power for the aircraft. Figure 1 As shown, they are not designed as independent component units, but together with the core engine constitute the main body of the power unit. Its main structural features are:

[0003] The load compressor does not have an independent rotor support system. The load compressor rotating impeller and the core engine rotating impeller are connected to form a whole through end teeth. The front bearing is supported on the first bearing casing of the load compressor, and the rear bearing is supported on the core engine turbine section. The single rotor is connected in series with multiple centrifugal impellers and multiple turbines through end teeth.

[0004] During the assembly of the auxiliary power unit, the load compressor components and the core engine components are assembled in a staggered manner according to a certain process sequence to complete the assembly of the entire auxiliary power unit. When adjusting important parameters such as blade tip clearance and flushness, the coordination and matching between the two must be considered;

[0005] At the radial diffuser outlet, facing the exhaust direction, a circular or D-shaped bleed air passage is arranged along the circumferential gradient to form a bleed air volute. The flange mounting edge of the bleed air volute is then connected to the intake casing by a bolt structure. This volute layout design is inefficient and loads the compressor components with a large outer diameter, resulting in excessive weight of the compressor components.

[0006] The single-layer centrifugal impeller outer cover is structurally connected to the load-bearing casing through outlet bolts.

[0007] Existing load compressor components do not adopt a unit body design and cannot be designed, manufactured, assembled, transported and sold as independent products; existing load compressor components do not have an independent rotor system, and their rotating impellers and core machine impellers together constitute the rotor system. The rotor span is large and the rigidity is weak, which makes it easy for the rotor to have insufficient stable working margin; the existing load compressor bleed air volute 110 is arranged at the radial diffuser outlet, facing the exhaust direction, with a circular (or D-shaped) bleed air channel that gradually changes along the circumference to form an bleed air volute. This volute design has a large outer diameter, resulting in a relatively large total weight of the volute or the load compressor. Summary of the Invention

[0008] The present invention provides a load compressor configuration to solve the technical problems of low adaptability of existing load compressor components, inability to be produced, assembled, transported and sold as independent component units or products, large radial deflection of the rotor during operation and poor stability.

[0009] The technical solution adopted in the present invention is as follows:

[0010] A load compressor configuration includes: a rotor assembly, and a first bearing casing and an air intake casing relatively spaced apart and mounted on the outer circles at both ends of the rotor assembly; the power input end of the rotor assembly is supported on the first bearing casing via a front bearing, and the power output end of the rotor assembly is supported on the air intake casing via a rear bearing to form an independent rotor support structure; the power input end of the rotor assembly is also detachably connected to an upstream power input system, and the power output end of the rotor assembly is also detachably connected to a downstream power output system to ensure the input and output of power of the load compressor.

[0011] Furthermore, the rotor assembly includes an axially arranged centrifugal impeller, a front shaft neck and a rear shaft neck respectively arranged at both ends of the centrifugal impeller, and a pull rod assembly; the front shaft neck is installed on the outer circle of the power input end of the centrifugal impeller, and is centrally connected to the centrifugal impeller through a first end tooth structure and transmits torque, and the front bearing is interference mounted on the outer circle of the front shaft neck; the rear shaft neck is installed on the outer circle of the power output end of the centrifugal impeller, and is centrally connected to the centrifugal impeller through a second end tooth structure and transmits torque, and the rear bearing is interference mounted on the outer circle of the rear shaft neck; after the pull rod assembly passes through the front shaft neck, centrifugal impeller and rear bearing in sequence along the axis, the three are axially tightened to form a whole.

[0012] Furthermore, the load compressor configuration also includes a radial diffuser in an annular shape and mounted on the exhaust end of the centrifugal impeller; the outer end of the first bearing casing is connected to the radial diffuser, and the first bearing casing, the radial diffuser, the centrifugal impeller and the front journal are surrounded to form an air cavity connected to the exhaust end of the radial diffuser.

[0013] Furthermore, the load compressor configuration also includes a grate sealing ring disk that is arranged in an annular shape and fixed to the front end wall of the centrifugal impeller; the first bearing casing is sealed with the grate sealing ring disk and the centrifugal impeller respectively to separate the air cavity into a high-pressure cavity, a closed air cavity and a low-pressure cavity that are arranged in sequence from the outside to the inside.

[0014] Furthermore, the first bearing casing includes a casing front wall body mounted on the outer circle of the front bearing, and an inner sealing gear ring and an outer sealing gear ring connected to the inner wall surface of the casing front wall body and in a ring shape; an impeller grate is also provided on the outer circle of the power input end of the centrifugal impeller; the outer sealing gear ring and the grate sealing ring disk cooperate to form a first seal, and the inner sealing gear ring and the impeller grate form a second seal, thereby forming a closed air cavity between the first bearing casing, the centrifugal impeller and the grate sealing ring disk, and a connecting hole connecting the closed air cavity is also opened on the wall surface of the casing front wall body.

[0015] Furthermore, the centrifugal impeller and the rear journal are mounted on the air intake casing through the rear bearing, and the air intake casing and the outer peripheral surface of the rear journal are sealed by a grate structure; an internal air duct for gas to enter is also provided in the air intake casing, and the exhaust end of the air intake casing is close to the intake end of the centrifugal impeller, so as to form a smooth air flow channel between the air intake casing and the centrifugal impeller.

[0016] Furthermore, the load compressor configuration also includes an annular air intake volute installed outside the centrifugal impeller; the air intake volute is located between the radial diffuser and the intake casing, and the intake end of the air intake volute is connected to the first bearing casing; the air intake volute and the intake casing are integrally formed.

[0017] Furthermore, the inlet cross-section of the induced air volute is annular with a support plate; the inlet annular cross-section of the induced air volute is connected to the exhaust end of the radial diffuser, and the exhaust cross-section of the induced air volute is an inner volute setting that extends inwardly toward the centrifugal impeller side.

[0018] Furthermore, the load compressor configuration also includes an impeller cover that is annular and is arranged outside the centrifugal impeller, and the impeller cover is connected to the air induction volute; the inner air duct of the intake casing, the air duct between the impeller cover and the centrifugal impeller, and the inner air duct of the radial diffuser are connected to form an air flow channel.

[0019] Furthermore, the impeller outer cover includes an inner ring cover and an outer ring cover which are arranged in an inner and outer fitting manner and are both annular; the inner ring cover is trumpet-shaped, is arranged outside the centrifugal impeller, and extends along the extension direction of the centrifugal impeller; the outer ring cover is a cylindrical or conical annular cover shell, the first end of the outer ring cover is fixedly connected to the exhaust end of the inner ring cover along the circumferential direction, and the second end of the outer ring cover is fixedly connected to the outer wall surface of the air induced volute along the circumferential direction.

[0020] The present invention has the following beneficial effects:

[0021] The present invention provides a new auxiliary power unit load compressor configuration. The rotor assembly adopts a simply supported structure, that is, the front fulcrum of the rotor assembly is rotatably supported on the first bearing casing via the front bearing, and the rear fulcrum is rotatably supported on the intake casing via the rear bearing, thereby forming an independent rotor system, ensuring an independent unit design, and thus enabling independent research and development, production, assembly, testing, status debugging, transportation and sales. It can be quickly adapted to auxiliary power units of different models and powers, has a wide range of adaptability, and significantly improves research and development efficiency and production efficiency, reducing preparation costs. However, the comparative solution does not have these characteristics. It must be assembled with a unique matching core engine, has low adaptability, and cannot be produced, assembled, transported and sold as an independent component unit or product.

[0022] On the other hand, the present invention's solution can form an independent rotor support structure with two bearing fulcrums, namely the front and rear bearings. The rotor assembly's fulcrum span is short and rigid. By providing elastic plates between the bearings and the assembled casing, the support stiffness can be freely adjusted, ensuring that the rotor system has sufficient critical speed margin, is less susceptible to resonance damage during operation, and ensures sufficient rotor operational stability. In contrast, the comparative solution lacks an independent rotor system and only has a single bearing fulcrum, which must be connected to the core engine rotor to form the rotor system. This structure has a long fulcrum span, resulting in large radial deflection during rotor operation and poor stability.

[0023] In addition to the above-described objects, features and advantages, the present invention has other objects, features and advantages. The present invention will be further described in detail below with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] The accompanying drawings, which constitute part of this application, are intended to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are intended to explain the present invention and do not constitute an undue limitation of the present invention. In the accompanying drawings:

[0025] Figure 1 It is a structural diagram of existing load compressor components;

[0026] Figure 2 This is a schematic diagram of the main structure of a load compressor configuration according to a preferred embodiment of the present invention;

[0027] Figure 3 yes Figure 2 Schematic diagram of the main structure of the middle rotor assembly.

[0028] Legend

[0029] 10. Rotor assembly; 11. Centrifugal impeller; 12. Front journal; 13. Rear journal; 14. Tie rod assembly; 20. First bearing casing; 21. Casing front wall; 210. Connecting hole; 22. Inner sealing gear ring; 23. Outer sealing gear ring; 30. Intake casing; 40. Front bearing; 50. Rear bearing; 60. First end gear structure; 70. Second end gear structure; 80. Radial diffuser; 90. Grate sealing ring disk; 110. Induction volute; 120. Impeller cover; 121. Inner ring cover; 122. Outer ring cover; 131. Slender shaft; 132. Grate ring; 133. Impeller; 134. Exhaust volute; 135. Second bearing casing; 136. Hyperbolic arc impeller cover. DETAILED DESCRIPTION

[0030] The embodiments of the present invention are described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below.

[0031] Reference Figure 2 A preferred embodiment of the present invention provides a load compressor configuration, comprising: a rotor assembly 10, and a first bearing casing 20 and an air intake casing 30 that are relatively spaced apart and mounted on the outer circles of both ends of the rotor assembly 10. The power input end of the rotor assembly 10 is supported on the first bearing casing 20 via a front bearing 40, and the power output end of the rotor assembly 10 is supported on the air intake casing 30 via a rear bearing 50, to form an independent rotor support structure. The power input end of the rotor assembly 10 can also be detachably connected to an upstream power input system, and the power output end of the rotor assembly 10 can also be detachably connected to a downstream power output system to ensure the input and output of power for the load compressor.

[0032] The present invention provides a new auxiliary power unit load compressor configuration, in which the rotor assembly 10 adopts a simply supported structure, i.e., the front fulcrum of the rotor assembly 10 is rotatably supported on the first bearing casing 20 via the front bearing 40, and the rear fulcrum is rotatably supported on the intake casing 30 via the rear bearing 50, thereby forming an independent rotor system, ensuring an independent unit design, and thus enabling independent research and development, production, assembly, testing, status debugging, transportation, and sales. It can be quickly adapted to auxiliary power units of different models and powers, has a wide range of adaptability, significantly improves research and development efficiency and production efficiency, and reduces production costs. However, the comparative solution does not have these characteristics. It must be assembled with a unique matching core engine, has low adaptability, and cannot be produced, assembled, transported, and sold as an independent component unit or product.

[0033] On the other hand, the present invention's solution can form an independent rotor support structure with two bearing pivots, namely the front bearing 40 and the rear bearing 50. The rotor assembly 10 has a short pivot span and strong rigidity. By providing elastic plates between the bearings and the assembled casing, the support stiffness can be freely adjusted, ensuring that the rotor system has sufficient critical speed margin, is less likely to experience resonance damage during operation, and ensures sufficient rotor operational stability. In contrast, the comparative solution lacks an independent rotor system and only has a single bearing pivot, which must be connected to the core engine rotor to form the rotor system. This structure has a long pivot span, resulting in large radial deflection during rotor operation and poor stability.

[0034] Alternatively, as Figure 2 and Figure 3 As shown, the rotor assembly 10 includes an axially arranged centrifugal impeller 11, a front journal 12 and a rear journal 13 respectively arranged at both ends of the centrifugal impeller 11, and a pull rod assembly 14. The front journal 12 is mounted on the outer circle of the power input end of the centrifugal impeller 11, and is centrally connected and transmits torque to the centrifugal impeller 11 through the first end tooth structure 60, and the front bearing 40 is interference mounted on the outer circle of the front journal 12. The rear journal 13 is mounted on the outer circle of the power output end of the centrifugal impeller 11, and is centrally connected and transmits torque to the centrifugal impeller 11 through the second end tooth structure 70, and the rear bearing 50 is interference mounted on the outer circle of the rear journal 13. After the pull rod assembly 14 passes through the front journal 12, the centrifugal impeller 11 and the rear bearing 50 in sequence along the axis, the three are tightened axially to form a whole. In this optional solution, as Figure 3 As shown, the rotor assembly 10 is mainly composed of parts such as the front shaft neck 12, the centrifugal impeller 11, the rear shaft neck 13 and the tie rod assembly 14. The front bearing 40 is interference mounted on the front shaft neck 12, and the rear bearing 50 is interference mounted on the rear shaft neck 13. The front shaft neck 12, the centrifugal impeller 11 and the rear shaft neck 13 are centered and torque is transmitted through the end tooth structure. The tie rod assembly 14 applies axial preload from the inside to form a whole. At the same time, a spline structure is designed at the center position of the hole of the front shaft neck 12 and the rear shaft neck 13 to ensure the input and output of power of the load compressor components.

[0035] The present invention adopts an independent rotor system with two bearing supports (attached Figure 3 The front bearing 40 and the rear bearing 50) of the rotor fulcrum have a very small span; Figure 3 The front journal 12, centrifugal impeller 11 and rear journal 13 transmit torque through the end teeth, and the tie rod assembly 14 is pre-tightened from the axis. This structure has strong rotor rigidity and good rotor system stability. The comparative scheme does not have an independent rotor system, but only has one bearing fulcrum (attached Figure 1 The rotor system must be connected to the core rotor. This structure has a long support span, large radial deflection during rotor operation, and poor stability. Figure 1The middle impeller 133 and the grate ring 132 are connected as a whole through the slender shaft 131. The entire rotor shaft system has a small diameter, poor rigidity, is prone to radial deformation, and has poor stability of the rotor system.

[0036] Alternatively, as Figure 2 As shown, the load compressor configuration also includes an annular radial diffuser 80 mounted on the exhaust end of the centrifugal impeller 11. The outer end of the first bearing casing 20 is connected to the radial diffuser 80, and the first bearing casing 20, radial diffuser 80, centrifugal impeller 11, and front journal 12 enclose an air cavity that communicates with the exhaust end of the radial diffuser 80.

[0037] Furthermore, if Figure 2 and Figure 3 As shown, the load compressor configuration also includes an annularly arranged grate sealing ring disk 90 fixed to the front end wall of the centrifugal impeller 11. The first bearing casing 20 is sealedly connected to the grate sealing ring disk 90 and the centrifugal impeller 11, respectively, to separate the air cavity into a high-pressure chamber, a closed air chamber, and a low-pressure chamber, arranged in order from the outside to the inside.

[0038] In this option, if Figure 2 As shown, the first bearing casing 20 includes a casing front wall 21 mounted on the outer circumference of the front bearing 40, and an annular inner and outer sealing rings 22 and 23 connected to the inner surface of the casing front wall 21. Impeller grates are also provided on the outer circumference of the power input end of the centrifugal impeller 11. The outer sealing ring 23 cooperates with the grate sealing ring 90 to form a primary seal, while the inner sealing ring 22 cooperates with the impeller grate to form a secondary seal, thereby forming a closed air cavity between the first bearing casing 20, the centrifugal impeller 11, and the grate sealing ring 90. Furthermore, a connecting hole 210 is provided on the surface of the casing front wall 21 to connect to the closed air cavity. In this optional solution, a venting system is designed at the back of the centrifugal impeller 11. Through two sealing grate structures, namely the first seal between the outer sealing gear ring 23 and the grate sealing ring disk 90, and the second seal between the inner sealing gear ring 22 and the impeller grate, a closed air cavity for venting is formed. During the operation of the load compressor, the gas in the high-pressure cavity passes through the first seal, decelerates, and releases pressure before entering the closed air cavity. During use, the high-pressure gas in the closed air cavity is vented and adjusted as needed to ensure that the entire rotor system operates under an appropriate axial force state, reduce the bearing load, and increase the service life of the bearing. In contrast, Figure 1 As shown, there is no independent air bleed system, and the axial force of the rotor system cannot be effectively adjusted. The bearing can only rely on the bearing to independently withstand the large axial force, which makes it difficult to ensure a sufficient bearing service life.

[0039] Alternatively, as Figure 2As shown, the centrifugal impeller 11 and rear journal 13 are mounted on the intake casing 30 via a rear bearing 50. A grate structure seals the intake casing 30 against the outer circumference of the rear journal 13. An internal air duct is provided within the intake casing 30 for air to enter, with the exhaust end of the intake casing 30 positioned adjacent to the intake end of the centrifugal impeller 11, creating a smooth air flow path between the intake casing 30 and the centrifugal impeller 11.

[0040] In this option, if Figure 2 As shown, the load compressor configuration also includes an annular bleed air volute 110 mounted outside the centrifugal impeller 11. The bleed air volute 110 is located between the radial diffuser 80 and the intake casing 30, with the intake end of the bleed air volute 110 connected to the first bearing casing 20. The bleed air volute 110 and the intake casing 30 are integrally formed. In this optional solution, the integrated design of the bleed air volute 110 and the intake casing 30 increases the integration of parts, reduces the number of parts, improves assembly and disassembly processability, and reduces the total weight of the load compressor components.

[0041] Further, if Figure 2 As shown, the inlet cross-section of the bleed volute 110 is annular with a support plate. The inlet annular cross-section of the bleed volute 110 is connected to the exhaust end of the radial diffuser 80, and the exhaust cross-section of the bleed volute 110 is an inner volute setting that extends inward toward the centrifugal impeller 11. In this optional solution, the design of the bleed volute 110 has obvious advantages and characteristics: the special-shaped cross-section design can significantly reduce the aerodynamic loss of the bleed volute 110, and the special-shaped cross-section can enhance its structural strength and bearing capacity; the exhaust cross-section of the bleed volute 110 adopts an inner volute design, which greatly reduces the maximum outer diameter of the volute, greatly reduces the weight of the bleed volute 110, and fully and effectively utilizes the internal and external structural space, improves the internal structural design efficiency of the compressor, and makes the overall structural design simple and compact; the bleed volute 110 is designed to be integrated with the air inlet casing 30, which can further reduce the structural overlap interface and reduce the weight of the loaded compressor. In contrast, Figure 1 As shown, its structural features are: conventional circular cross-section design, conventional outward-expanding exhaust cross-section design, facing the diffuser exhaust channel; exhaust volute 134 and second bearing casing 135 are integrated into one design. These structural features result in the entire load compressor component having a large outer diameter, a relatively large weight, and poor load-bearing capacity.

[0042] Alternatively, as Figure 2 As shown, the load compressor configuration further includes an annular impeller shroud 120 disposed outside the centrifugal impeller 11. The impeller shroud 120 is connected to the bleed volute 110. The inner air duct of the intake casing 30, the air duct between the impeller shroud 120 and the centrifugal impeller 11, and the inner air duct of the radial diffuser 80 are connected to form an air flow channel.

[0043] In this option, if Figure 2 As shown, the impeller cover 120 includes an inner ring cover 121 and an outer ring cover 122, which are arranged in an inner and outer manner and are both annular. The inner ring cover 121 is trumpet-shaped, and is arranged outside the centrifugal impeller 11, and extends along the extension direction of the centrifugal impeller 11. The outer ring cover 122 is a cylindrical or conical annular cover. The first end of the outer ring cover 122 is fixedly connected to the exhaust end of the inner ring cover 121 along the circumferential direction, and the second end of the outer ring cover 122 is fixedly connected to the outer wall surface of the bleed volute 110 along the circumferential direction. In this optional solution, the load compressor impeller cover 120 adopts a double-layer folding structure design. The structural elastic deformation of the transition zone between the inner ring cover 121 and the outer ring cover 122 can absorb impact energy, and the double-layer wall thickness can also ensure that the compressor casing has sufficient impact resistance. When the wheel disc and blades fly out at high speed, the double-layer impeller cover 120 can achieve effective covering to ensure the containment capacity of the load compressor casing. In contrast, the comparative solution, such as Figure 1 As shown, the hyperbolic arc impeller cover design is adopted (attached Figure 1 136), which relies on the deformation energy absorption capability of the hyperbolic arc to improve the containment capacity of the loaded compressor casing.

[0044] The patent of this invention has been designed and verified on the KD130 load compressor components. The results show that it can effectively reduce the weight of the load compressor components, has good connection strength, and can realize the various technical advantages of the technical solution.

[0045] The foregoing description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Those skilled in the art will readily appreciate that various modifications and variations of the present invention are possible. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention are intended to be within the scope of protection of the present invention.

Claims

1. A load compressor configuration, characterized in that: include: A rotor assembly (10), and a first bearing casing (20) and an air intake casing (30) which are relatively spaced and mounted on the outer circles of both ends of the rotor assembly (10); The power input end of the rotor assembly (10) is supported on the first bearing casing (20) through a front bearing (40), and the power output end of the rotor assembly (10) is supported on the air intake casing (30) through a rear bearing (50) to form an independent rotor support structure; The power input end of the rotor assembly (10) can be detachably connected to an upstream power input system, and the power output end of the rotor assembly (10) can be detachably connected to a downstream power output system to ensure the input and output of the load compressor power; The rotor assembly (10) comprises a centrifugal impeller (11) arranged in the axial direction, a front journal (12) and a rear journal (13) respectively arranged at two ends of the centrifugal impeller (11), and a pull rod assembly (14); The load compressor configuration further includes a grate sealing ring disk (90) which is arranged in an annular shape and fixed to the front end wall surface of the centrifugal impeller (11); The first bearing casing (20) comprises a casing front wall body (21) mounted on the outer circle of the front bearing (40), and an inner sealing gear ring (22) and an outer sealing gear ring (23) connected to the inner wall surface of the casing front wall body (21) and in an annular shape; an impeller grate is also provided on the outer circle of the power input end of the centrifugal impeller (11); the outer sealing gear ring (23) cooperates with the grate sealing ring disk (90) to form a first seal, and the inner sealing gear ring (22) cooperates with the impeller grate to form a second seal, thereby forming a closed air cavity between the first bearing casing (20), the centrifugal impeller (11) and the grate sealing ring disk (90), and a connecting hole (210) communicating with the closed air cavity is also opened on the wall surface of the casing front wall body (21).

2. The load compressor configuration according to claim 1, characterized in that: The front journal (12) is mounted on the outer circle of the power input end of the centrifugal impeller (11), and is centrally connected to the centrifugal impeller (11) through the first end tooth structure (60) and transmits torque. The front bearing (40) is interference-mounted on the outer circle of the front journal (12); The rear journal (13) is mounted on the outer circle of the power output end of the centrifugal impeller (11), and is centrally connected to the centrifugal impeller (11) through the second end tooth structure (70) and transmits torque. The rear bearing (50) is interference-mounted on the outer circle of the rear journal (13); After the pull rod assembly (14) is sequentially passed through the front journal (12), the centrifugal impeller (11) and the rear bearing (50) along the axis, the three are tightened along the axial direction to form a whole.

3. The load compressor configuration according to claim 2, characterized in that: The load compressor configuration further includes a radial diffuser (80) in an annular shape and mounted on the exhaust end of the centrifugal impeller (11); The outer end of the first bearing casing (20) is connected to the radial diffuser (80), and the first bearing casing (20), the radial diffuser (80), the centrifugal impeller (11) and the front journal (12) are surrounded to form an air cavity connected to the exhaust end of the radial diffuser (80).

4. The load compressor configuration according to claim 3, characterized in that: The first bearing casing (20) is sealedly connected to the grate sealing ring disc (90) and the centrifugal impeller (11) respectively, so as to separate the air cavity into a high-pressure cavity, a closed air cavity and a low-pressure cavity which are sequentially arranged from the outside to the inside.

5. The load compressor configuration according to claim 3, characterized in that: The centrifugal impeller (11) and the rear journal (13) are mounted on the air intake casing (30) via a rear bearing (50), and the air intake casing (30) and the outer peripheral surface of the rear journal (13) are sealed by a grate structure. An internal air passage for gas to enter is also provided in the air intake casing (30), and the exhaust end of the air intake casing (30) is close to the intake end of the centrifugal impeller (11), so that a smooth air flow channel is formed between the air intake casing (30) and the centrifugal impeller (11).

6. The load compressor configuration according to claim 5, characterized in that: The load compressor configuration further includes an annular air induced volute (110) installed outside the centrifugal impeller (11); The bleed air volute (110) is located between the radial diffuser (80) and the air intake casing (30), and the air intake end of the bleed air volute (110) is connected to the first bearing casing (20); The air bleed volute (110) and the air intake casing (30) are integrally formed.

7. The load compressor configuration according to claim 6, characterized in that: The inlet cross section of the air bleed volute (110) is annular with a support plate; The inlet annular section of the induced air volute (110) is connected to the exhaust end of the radial diffuser (80), and the exhaust section of the induced air volute (110) is an inner volute type arrangement extending inwardly toward the centrifugal impeller (11).

8. The load compressor configuration according to claim 6, characterized in that: The load compressor configuration further includes an impeller outer cover (120) in an annular shape and arranged outside the centrifugal impeller (11), and the impeller outer cover (120) is connected to the air volute (110); The inner air passage of the air intake casing (30), the air passage between the impeller outer cover (120) and the centrifugal impeller (11), and the inner air passage of the radial diffuser (80) are connected to form an air flow channel.

9. The load compressor configuration according to claim 8, characterized in that: The impeller outer cover (120) comprises an inner ring cover (121) and an outer ring cover (122) which are arranged in an inner and outer manner and are both annular; The inner ring cover (121) is trumpet-shaped, is arranged outside the centrifugal impeller (11), and extends along the extension direction of the centrifugal impeller (11); The outer ring cover (122) is a cylindrical or conical annular cover. The first end of the outer ring cover (122) is fixedly connected to the exhaust end of the inner ring cover (121) along the circumferential direction, and the second end of the outer ring cover (122) is fixedly connected to the outer wall surface of the air volute (110) along the circumferential direction.

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