Rigid rotor compressor design method, rigid rotor and compressor

Abstract

The embodiment of the invention discloses a rigid rotor compressor design method, a rigid rotor and a compressor. By shortening the length of a rigid rotor main shaft and the length of a dry gas seal shaft section and arranging a shaft shoulder table, the positioning mode of a rigid rotor balance disc is changed, the supporting span of the rigid rotor is shortened, and the weight of the rigid rotor is reduced; the total length of the compressor is shortened according to the shortening condition of the main shaft length of the rigid rotor and the length of the dry gas seal shaft section, the design effectively reduces the scraping abrasion risk between the rotor and a seal, a bearing and other small-gap stator parts caused by amplitude increase when the rotor passes through a first-order critical rotating speed response area, and the service life of related parts is prolonged. Meanwhile, due to the fact that the length of the compressor rotor is shortened, the weight is reduced, on the basis of being influenced by the weight of the rotor, the disturbing force value and the static equivalent load are reduced on year-on-year basis, the pneumatic torque of a driver is reduced on year-on-year basis, and the equipment foundation design and driver design requirements are lowered.

Description

Technical Field

[0001] The embodiments of the present application relate to the field of turbine machinery technology, and in particular to a rigid rotor compressor design method, a rigid rotor, and a compressor. Background Art

[0002] Traditional single-shaft centrifugal compressors all use a flexible rotor (flexible rotor) design structure, that is, the operating speed range of the compressor is between the first-order critical speed and the second-order critical speed of the rotor. Since the vibration amplitude of the rotor increases when the unit is running close to the critical speed, it is easy to cause wear and damage to the rotor itself, bearings, seals, etc. When starting up, the unit with a flexible rotor generally adopts the method of quickly passing the critical speed to reduce the above-mentioned wear caused by over-criticality. This solution can be implemented for units driven by a single cylinder. For a device with a driver driving multiple cylinder compressors, it is necessary to avoid the critical speed range of multiple compressors and the critical speed range of the driver itself, which greatly increases the difficulty of quickly passing the critical area of ​​the device during the start-up process and the risk of vibration scratches.

[0003] For units with a small number of compression stages or a small impeller stage spacing, in order to design the first-order critical speed within a reasonable range, it is necessary to artificially lengthen the compressor body structure, which increases the aerodynamic loss of the compressor flow part and affects the unit's operating efficiency; at the same time, it increases the difficulty of processing and manufacturing the compressor host and supporting equipment, and increases the difficulty of project construction planning and operation and maintenance on the user's site. In addition, from the perspective of unit layout, there are unreasonable structural problems, which have a "stupid, big, black and thick" bulky feel, which seriously affects the product's appearance quality and user experience. Summary of the invention

[0004] The present invention aims to solve at least one of the technical problems existing in the prior art or related art.

[0005] To this end, a first aspect of the present invention provides a rigid rotor compressor design method.

[0006] A second aspect of the present invention provides a rigid rotor.

[0007] A third aspect of the present invention provides a compressor.

[0008] In view of this, according to a first aspect of an embodiment of the present application, a rigid rotor compressor design method is proposed, including: by shortening the length of the rigid rotor main shaft, the length of the dry gas seal shaft section and setting a shaft shoulder, changing the positioning method of the rigid rotor balancing disk, shortening the rigid rotor support span, and reducing the rigid rotor weight;

[0009] The overall length of the compressor is shortened according to the shortening of the rigid rotor main shaft length and the dry gas seal shaft section length.

[0010] In a feasible implementation manner, shortening the main shaft length and changing the balancing disc positioning method to shorten the rigid rotor support span and reduce the rigid rotor weight includes:

[0011] Set up a shaft shoulder to change the positioning method of the rigid rotor balancing disc from the shaft sleeve nut positioning to the shaft shoulder positioning;

[0012] The main shaft length and dry gas seal shaft section length of the rigid rotor are shortened, the support span of the rigid rotor is shortened to 42% or more of the original flexible rotor, and the weight of the rigid rotor is reduced to 43% or more of the original flexible rotor.

[0013] In a feasible implementation, it also includes:

[0014] Increase the diameter of the main shaft section and dry gas seal section;

[0015] The weight of the supporting shaft section is reduced by shortening the length and reducing the outer diameter.

[0016] In a feasible implementation, it also includes:

[0017] The compressor casing drive side adopts an integral welded structure and a barrel-type design;

[0018] The non-drive end of the compressor casing adopts an integrally formed forged steel end cover structure;

[0019] The assembly is performed through a fixed ring structure;

[0020] The compressor inlet volute adopts a variable cross-section cavity structure;

[0021] The compressor outlet volute adopts a variable cross-section cavity structure;

[0022] The compressor air outlet adopts a tangential discharge structure.

[0023] In a feasible implementation manner, shortening the overall length of the compressor according to the shortening of the length of the rigid rotor main shaft includes:

[0024] The total length of the compressor is shortened to 41% or more of the length of the original flexible rotor compressor and 40% or more of the weight of the original flexible rotor compressor.

[0025] According to a second aspect of an embodiment of the present application, a rigid rotor is proposed, and the rigid rotor compressor is designed according to the above-mentioned method, including:

[0026] A supporting shaft segment, wherein the number of the supporting shaft segments is two, and one end of the two supporting shaft segments is respectively connected to an external compressor connection port;

[0027] A dry gas sealing shaft segment, wherein the number of the dry gas sealing shaft segments is two, one end of the two dry gas sealing shaft segments is respectively connected to the other end of the supporting shaft segment, and the length of the dry gas sealing shaft segment is less than the dry gas sealing shaft length of the flexible rotor;

[0028] A main shaft section, wherein the front and rear ends of the main shaft are respectively connected to the other end of the dry gas seal shaft section, and the length of the main shaft is less than the main shaft length of the flexible rotor;

[0029] A balancing disc, which is used to offset the axial force of the rigid rotor and is arranged on the main shaft;

[0030] A shaft shoulder, through which both ends of the balancing disc are positioned on the main shaft.

[0031] In a feasible implementation, it also includes:

[0032] An impeller, the impeller is arranged on the main shaft and is used to pressurize the gas, and the balancing disk is arranged on one side of the high-pressure end of the impeller;

[0033] A thrust plate, which is arranged on the main shaft and is used to transmit the axial thrust to the main shaft;

[0034] A spacer sleeve is arranged at the connection between the support shaft section and the external compressor connection port.

[0035] In a feasible implementation manner, the diameters of the main shaft section and the dry gas seal section are larger than the diameters of the flexible rotor main shaft section and the dry gas seal section;

[0036] The diameter of the support shaft segment is smaller than the diameter of the flexible rotor support shaft segment, and the length of the support shaft segment is smaller than the length of the flexible rotor support shaft segment.

[0037] According to a third aspect of an embodiment of the present application, a compressor is provided, which is designed by the rigid rotor compressor method described above, comprising:

[0038] Compressor body;

[0039] A compressor connection port, the compressor connection port being arranged on the compressor body;

[0040] A rigid rotor as described in any one of the above, wherein the rigid rotor is connected to the compressor body through the compressor connection port;

[0041] A casing, the casing is arranged outside the compressor body, and the driving side of the casing is an integrally welded cylindrical structure;

[0042] An end cover, which is arranged on the non-motorized side of the housing and is made of formed forged steel;

[0043] A fixing ring, which is arranged on the end cover and is used to connect the housing and the end cover;

[0044] A partition is arranged inside the casing, and the length of the partition is shortened according to the length of the rigid rotor.

[0045] In a feasible implementation, it also includes:

[0046] An inlet volute chamber, which is arranged inside the casing and is a cavity with a variable cross-section;

[0047] An outlet volute chamber, the outlet volute chamber is arranged inside the casing, the outlet volute chamber is connected to the inlet volute chamber, and the outlet volute chamber is a variable cross-section cavity;

[0048] An air outlet duct is connected to the outlet volute chamber, and the outlet volute chamber adopts a variable cross-section cavity.

[0049] Compared with the prior art, the present invention includes at least the following beneficial effects: Therefore, the rigid rotor compressor designed by the present design method replaces the flexible rotor with a rigid rotor. The rigid rotor structure is more compact and the material is usually a hard material such as metal and ceramic. Its intrinsic hardness and stiffness are relatively high. Therefore, the rigid rotor can withstand higher loads and movement speeds.

[0050] According to the characteristics of the rigid rotor, this design method shortens the main shaft section and dry gas seal section of the rotor, and sets a shaft shoulder. The rigid rotor is positioned through the shaft shoulder, shortening the length of the rigid rotor support shaft section.

[0051] This design effectively reduces the risk of scratching and wear between the rotor and the seal, bearings and other small-gap stator components caused by the increased amplitude when the rotor passes through the first-order critical speed response zone, thereby increasing the service life of related components.

[0052] At the same time, due to the shortening of the compressor rotor length and the reduction of weight, the disturbance force value and static equivalent load affected by the rotor weight are reduced year-on-year, and the aerodynamic torque of the driving machine is reduced year-on-year, which reduces the basic design of the equipment and the design requirements of the driving machine.

[0053] At the same time, due to the reduction in length and weight of the rigid rotor, the total length of the compressor can also be reduced according to the shortened length of the rigid rotor, thereby streamlining the size of the compressor, reducing the unit's footprint, and improving the flexibility of the unit's installation. BRIEF DESCRIPTION OF THE DRAWINGS

[0054] Various other advantages and benefits will become apparent to those of ordinary skill in the art by reading the detailed description of the preferred embodiments below. The accompanying drawings are only for the purpose of illustrating the preferred embodiments and are not to be considered as limiting the present application. Also, the same reference symbols are used throughout the accompanying drawings to represent the same components. In the accompanying drawings:

[0055] Figure 1 A schematic diagram of a speed operating range of a flexible rotor according to an embodiment of the present application;

[0056] Figure 2 A schematic diagram of a speed operating range of a rigid rotor according to an embodiment of the present application;

[0057] Figure 3 A structural block diagram of a rigid rotor according to an embodiment of the present application;

[0058] Figure 4 A structural block diagram of a compressor according to an embodiment of the present application.

[0059] in, Figure 3-4 The corresponding relationship between the reference numerals and the component names is as follows:

[0060] 100, rigid rotor; 200, compressor body; 300, casing; 400, end cover; 500, fixing ring; 600, partition; 700, inlet volute; 800, outlet volute; 900, air outlet;

[0061] 110. Support shaft section; 120. Dry gas seal shaft section; 130. Main shaft section; 140. Balance disk; 150. Impeller. DETAILED DESCRIPTION

[0062] In order to better understand the above-mentioned technical scheme, the technical scheme of the embodiments of the present application is described in detail below through the accompanying drawings and specific embodiments. It should be understood that the embodiments of the present application and the specific features in the embodiments are detailed descriptions of the technical scheme of the embodiments of the present application, rather than limitations on the technical scheme of the present application. In the absence of conflict, the embodiments of the present application and the technical features in the embodiments may be combined with each other.

[0063] like Figure 1-4 As shown, according to the first aspect of the embodiment of the present application, a design method for a rigid rotor 100 compressor is proposed, including: changing the positioning method of the rigid rotor 100 balancing disk 140 by shortening the main shaft length of the rigid rotor 100, the length of the dry gas sealing shaft section 120 and setting a shaft shoulder, shortening the support span of the rigid rotor 100, and reducing the weight of the rigid rotor 100; shortening the total length of the compressor according to the shortening of the main shaft length of the rigid rotor 100 and the length of the dry gas sealing shaft section 120.

[0064] The rigid rotor 100 compressor design method provided in the embodiment of the present application is developed through structural innovation, which effectively solves the problems of scraping and wear of rotor and stator components caused by increased amplitude when the flexible rotor compressor starts / stops beyond the critical speed, the problem of narrow speed regulation range of the unit caused by critical binding and stability limitations, and a series of problems such as the difficulty of processing and manufacturing due to the large size and weight of the unit, the large basic load and space occupation of the plant, and the difficulty in operation and maintenance, thereby improving the stability, pressure bearing capacity, chemical process and environmental applicability of the unit.

[0065] The compressor rotor is mainly composed of an impeller 150, a main shaft, a balancing plate 140, a thrust plate, a spacer and various locking nuts. Existing single-shaft centrifugal compressors all adopt a flexible rotor (flexible rotor) design structure. The compressor speed operating range is as follows: Figure 1 shown.

[0066] According to the flexible rotor speed operating range in the figure, it can be seen that the operating speed of the centrifugal compressor equipped with a flexible rotor is above the first-order critical speed (Nc1 in the figure), that is, the compressor has a first-order critical speed. To ensure that the unit can avoid the first-order critical speed and run as smoothly as possible, the lower limit of the operating speed (Nma in the figure) needs to be within the existing speed range (such as Sa1 in the figure) from the critical speed.

[0067] Therefore, the rigid rotor 100 compressor designed by the present design method replaces the flexible rotor with the rigid rotor 100. The rigid rotor 100 has a more compact structure and is usually made of hard materials such as metal and ceramic. Its intrinsic hardness and stiffness are relatively high. Therefore, the rigid rotor 100 can withstand higher loads and movement speeds.

[0068] According to the characteristics of the rigid rotor 100 , this design method shortens the main shaft section 130 and the dry gas seal section 120 of the rotor, and sets a shaft shoulder to position the rigid rotor 100 through the shaft shoulder, thereby shortening the length of the supporting shaft section 110 of the rigid rotor 100 .

[0069] This design effectively reduces the risk of scratching and wear between the rotor and the seal, bearings and other small-gap stator components caused by the increased amplitude when the rotor passes through the first-order critical speed response zone, thereby increasing the service life of related components.

[0070] At the same time, due to the shortening of the compressor rotor length and the reduction of weight, the disturbance force value and static equivalent load affected by the rotor weight are reduced year-on-year, and the aerodynamic torque of the driving machine is reduced year-on-year, which reduces the basic design of the equipment and the design requirements of the driving machine.

[0071] At the same time, due to the reduction in length and weight of the rigid rotor 100, the total length of the compressor can also be reduced according to the shortened length of the rigid rotor 100, thereby streamlining the size of the compressor, reducing the unit footprint, and improving the flexibility of the unit installation.

[0072] like Figure 1-4 As shown, the method of shortening the main shaft length and changing the positioning method of the balancing disk 140 to shorten the support span of the rigid rotor 100 and reduce the weight of the rigid rotor 100 includes: providing a shaft shoulder, changing the positioning method of the balancing disk 140 of the rigid rotor 100 from shaft sleeve nut positioning to positioning through the shaft shoulder; shortening the main shaft length of the rigid rotor 100 and the length of the dry gas sealing shaft section 120, until the support span of the rigid rotor 100 is shortened to 42% or more of the original flexible rotor, and the weight of the rigid rotor 100 is reduced to 43% or more of the original flexible rotor weight.

[0073] In this technical solution, in the existing flexible rotor compressor, the flexible rotor is positioned by means of a balancing disk 140, a sleeve and a nut. In this design solution, a rigid rotor 100 is used to replace the flexible rotor. Since the rigid rotor 100 has higher hardness and rigidity, the connection method can be replaced by a shaft shoulder connection, thereby further shortening the support span of the rigid rotor 100.

[0074] At the same time, based on attempts and practices, in the present technical solution, the support span of the rigid rotor 100 is shortened to 60% to 42% of the support span of the flexible rotor, and the weight of the rigid rotor 100 is reduced to 60% to 43% of the original flexible rotor weight. If the length of the rigid rotor 100 is reduced too little, the optimization effect will be poor, and if the length of the rigid rotor 100 is reduced too much, the use effect will be affected.

[0075] like Figure 1-4 As shown, it also includes: increasing the diameters of the main shaft segment 130 and the dry gas seal segment 120; and reducing the weight of the support segment 110 by shortening the length and reducing the outer diameter.

[0076] In this technical solution, the stability of the rigid rotor 100 during operation is increased by increasing the diameter of the dry gas sealing shaft section 120, and the weight increased by the increased diameter of the dry gas sealing shaft section 120 of the rigid rotor 100 can be offset by shortening the length and outer diameter of the supporting shaft section 110, while further shortening the length of the rigid rotor 100.

[0077] like Figure 1-4As shown, it also includes: the driving side of the compressor casing 300 adopts an integrally welded structure and a cylindrical design; the non-driving end of the compressor casing 300 adopts an integrally formed forged steel end cover 400 structure; it is assembled and connected through a fixing ring 500 structure; the compressor inlet volute 700 adopts a variable cross-section cavity structure; the compressor outlet volute 800 adopts a variable cross-section cavity structure; the compressor air outlet 900 adopts a tangential discharge structure.

[0078] In this technical solution, the compressor housing 300 driving side adopts an integrally welded structure and a cylindrical design, and the compressor housing 300 non-driving side adopts an integrally formed forged steel cover structure, which is assembled and assembled through a fixed exchange structure. Under this design solution, the total housing 300 structure has the characteristics of good rigidity and high pressure bearing capacity, and the maximum designed pressure bearing capacity is 300 bar. At the same time, the structure has the characteristics of good stability, easy installation, and strong applicability.

[0079] In this technical solution, the compressor inlet volute 700 and outlet volute 800 both adopt a variable cross-section cavity design, and the air outlet duct 900 adopts a tangential discharge structure. This arrangement can reduce the total aerodynamic loss efficiency of the unit. According to calculations, its efficiency loss is reduced to less than 3%.

[0080] like Figure 1-4 As shown, shortening the overall length of the compressor according to the shortening of the main shaft length of the rigid rotor 100 includes: shortening the overall length of the compressor to 60% to 41% or more of the original length of the flexible rotor compressor and 60% to 40% or more of the original weight of the flexible rotor compressor.

[0081] In this technical solution, due to the shortening of the rotor length, the length and weight of the corresponding compressor can also be shortened, and the corresponding compressor partition 600 and casing 300 components are reduced, thereby reducing the design load of the design foundation and the base, and at the same time reducing the demand for installation and maintenance space, reducing the difficulty of civil engineering design and the demand for process land, and complying with the guiding principles of energy conservation and emission reduction in the petrochemical industry.

[0082] like Figure 1-4As shown, according to the second aspect of the embodiment of the present application, a rigid rotor 100 is proposed, which is designed according to any of the rigid rotor 100 compressor methods mentioned above, including: a support shaft segment 110, the number of which is two, and one end of the two support shaft segments 110 is respectively connected to the external compressor connection port; a dry gas sealing shaft segment 120, the number of which is two, and one end of the two dry gas sealing shaft segments 120 is respectively connected to the other end of the support shaft segment 110, and the length of the dry gas sealing shaft segment 120 is less than the dry gas sealing shaft length of the flexible rotor; a main shaft segment 130, the front and rear ends of the main shaft are respectively connected to the other end of the dry gas sealing shaft segment 120, and the length of the main shaft is less than the main shaft length of the flexible rotor; a balancing disk 140, the balancing disk 140 is used to offset the axial force of the rigid rotor 100, and the balancing disk 140 is arranged on the main shaft; a shaft shoulder, and the two ends of the balancing disk 140 are positioned on the main shaft through the shaft shoulder.

[0083] like Figure 1-4 As shown, it also includes: an impeller 150, which is arranged on the main shaft and is used to pressurize the gas, and the balancing plate 140 is arranged on one side of the high-pressure end of the impeller 150; a thrust plate, which is arranged on the main shaft and is used to transmit the axial thrust to the main shaft; and a spacer, which is arranged at the connection between the support shaft section 110 and the external compressor connection port.

[0084] like Figure 1-4 As shown, the diameters of the main shaft section 130 and the dry gas seal section 120 are larger than the diameters of the flexible rotor main shaft section 130 and the dry gas seal section 120 ; the diameter of the support shaft section 110 is smaller than the diameter of the flexible rotor support shaft section 110 , and the length of the support shaft section 110 is smaller than the length of the flexible rotor support shaft section 110 .

[0085] like Figure 1-4As shown, according to the third aspect of the embodiment of the present application, a compressor is proposed, which is designed by the rigid rotor 100 compressor method as described in any one of the above items, including: a compressor body 200; a compressor connection port, the compressor connection port is arranged on the compressor body 200; a rigid rotor 100 as described in any one of the above items, the rigid rotor 100 is connected to the compressor body 200 through the compressor connection port; a casing 300, the casing 300 is arranged on the outside of the compressor body 200, and the driving side of the casing 300 is an integrally welded cylindrical structure; an end cover 400, the end cover 400 is arranged on the non-motorized side of the casing 300, and the end cover 400 is made of formed forged steel; a fixing ring 500, the fixing ring 500 is arranged on the end cover 400, and is used to close the casing 300 and the end cover 400; a partition 600, the partition 600 is arranged inside the casing 300, and the length of the partition 600 is shortened according to the length of the rigid rotor 100.

[0086] like Figure 1-4 As shown, it also includes: an inlet volute chamber 700, which is arranged inside the casing 300, and the inlet volute chamber 700 is a variable cross-section cavity; an outlet volute chamber 800, which is arranged inside the casing 300, and the outlet volute chamber 800 is connected to the inlet volute chamber 700, and the outlet volute chamber 800 is a variable cross-section cavity; an air outlet duct 900, which is connected to the outlet volute chamber 800, and the outlet volute chamber 800 adopts a variable cross-section cavity.

[0087] In this technical solution, the rigid rotor 100 and the compressor are designed by the above design method. The rigidity of the rigid rotor 100 is improved by the design method proposed in this patent. The rigid rotor 100 and the compressor products proposed by the present invention designed by this method are simulated by the lateral vibration analysis software. The results show that the first-order critical speed of the unit (i.e. Figure 1 Nc1) is higher than the maximum continuous speed of the compressor (i.e. Figure 1 Nmc), and has a margin of more than 30% to avoid the influence of the first-order critical response interval on the rotor operation, thereby achieving the stability of the rigid rotor 100, which proves the success of the design and development of the rigid rotor 100.

[0088] This technical solution effectively reduces the risk of scratching and wear between the rotor and the seal, bearings and other small-gap stator parts caused by the increase in amplitude when the rotor passes through the first-order critical speed response zone, thereby increasing the service life of related components. At the same time, due to the shortening of the compressor rotor length and the reduction in weight, the disturbance force value and energy equivalent load on the basis of the influence of the rotor weight are reduced in the same proportion, and the driving torque of the driving machine is also reduced year-on-year, reducing the design requirements of the equipment foundation and the driving machine.

[0089] In the present invention, the terms "first", "second", and "third" are used for descriptive purposes only and should not be understood as indicating or implying relative importance; the term "plurality" refers to two or more, unless otherwise clearly defined. The terms "installed", "connected", "connected", "fixed", etc. should be understood in a broad sense. For example, "connected" can be a fixed connection, a detachable connection, or an integral connection; "connected" can be a direct connection or an indirect connection through an intermediate medium. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0090] In the description of the present invention, it is necessary to understand that the directions or positional relationships indicated by terms such as “upper”, “lower”, “left”, “right”, “front” and “back” are based on the directions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or unit referred to must have a specific direction, be constructed and operated in a specific orientation, and therefore, cannot be understood as a limitation on the present invention.

[0091] In the description of this specification, the description of the terms "one embodiment", "some embodiments", "specific embodiments", etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

[0092] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A method for designing a rigid rotor compressor, characterized in that: include: By shortening the length of the rigid rotor main shaft, the length of the dry gas seal shaft section and setting a shaft shoulder to change the positioning method of the rigid rotor balancing disk, the rigid rotor support span is shortened and the rigid rotor weight is reduced; The overall length of the compressor is shortened according to the shortening of the rigid rotor main shaft length and the dry gas seal shaft section length.

2. The rigid rotor compressor design method according to claim 1, characterized in that: The method of changing the positioning mode of the rigid rotor balancing disc by shortening the rigid rotor main shaft length, the dry gas seal shaft section length and setting a shaft shoulder platform includes: Set up a shaft shoulder to change the positioning method of the rigid rotor balancing disc from the shaft sleeve nut positioning to the shaft shoulder positioning; The main shaft length and dry gas seal shaft section length of the rigid rotor are shortened, the support span of the rigid rotor is shortened to 60% to 42% of the original flexible rotor, and the weight of the rigid rotor is reduced to 60% to 43% of the original flexible rotor.

3. The rigid rotor compressor design method according to claim 1, characterized in that: Also includes: Increase the diameter of the main shaft section and dry gas seal section; The weight of the supporting shaft section is reduced by shortening the length and reducing the outer diameter.

4. The rigid rotor compressor design method according to claim 1, characterized in that: Also includes: The compressor casing drive side adopts an integral welded structure and a barrel-type design; The non-drive end of the compressor casing adopts an integrally formed forged steel end cover structure; The assembly is performed through a fixed ring structure; The compressor inlet volute adopts a variable cross-section cavity structure; The compressor outlet volute adopts a variable cross-section cavity structure; The compressor air outlet adopts a tangential discharge structure.

5. The rigid rotor compressor design method according to claim 2, characterized in that: Shortening the overall length of the compressor based on the shortening of the rigid rotor main shaft length includes: The overall length of the compressor is shortened to 60% to 41% of the length of the original flexible rotor compressor and 60% to 40% of the weight of the original flexible rotor compressor.

6. A rigid rotor, characterized in that: Designing a rigid rotor compressor according to any one of claims 1 to 5, comprising: A supporting shaft segment, wherein the number of the supporting shaft segments is two, and one end of the two supporting shaft segments is respectively connected to an external compressor connection port; A dry gas sealing shaft segment, wherein the number of the dry gas sealing shaft segments is two, one end of the two dry gas sealing shaft segments is respectively connected to the other end of the supporting shaft segment, and the length of the dry gas sealing shaft segment is less than the dry gas sealing shaft length of the flexible rotor; A main shaft section, wherein the front and rear ends of the main shaft are respectively connected to the other end of the dry gas seal shaft section, and the length of the main shaft is less than the main shaft length of the flexible rotor; A balancing disc, which is used to offset the axial force of the rigid rotor and is arranged on the main shaft; A shaft shoulder, through which both ends of the balancing disc are positioned on the main shaft.

7. The rigid rotor according to claim 6, characterized in that Also includes: An impeller, the impeller is arranged on the main shaft and is used to pressurize the gas, and the balancing disk is arranged on one side of the high-pressure end of the impeller; A thrust plate, which is arranged on the main shaft and is used to transmit the axial thrust to the main shaft; A spacer sleeve is arranged at the connection between the support shaft section and the external compressor connection port.

8. The rigid rotor according to claim 1, characterized in that The diameters of the main shaft section and the dry gas seal section are larger than the diameters of the flexible rotor main shaft section and the dry gas seal section; The diameter of the support shaft segment is smaller than the diameter of the flexible rotor support shaft segment, and the length of the support shaft segment is smaller than the length of the flexible rotor support shaft segment.

9. A compressor, characterized in that: Designing a rigid rotor compressor according to any one of claims 1 to 5, comprising: Compressor body; A compressor connection port, the compressor connection port being arranged on the compressor body; The rigid rotor according to any one of claims 6 to 8, wherein the rigid rotor is connected to the compressor body through the compressor connection port; A casing, the casing is arranged outside the compressor body, and the driving side of the casing is an integrally welded cylindrical structure; An end cover, which is arranged on the non-motorized side of the housing and is made of formed forged steel; A fixing ring, which is arranged on the end cover and is used to connect the housing and the end cover; A partition is arranged inside the casing, and the length of the partition is shortened according to the length of the rigid rotor.

10. The compressor according to claim 9, characterized in that Also includes: An inlet volute chamber, which is arranged inside the casing and is a cavity with a variable cross-section; An outlet volute chamber, the outlet volute chamber is arranged inside the casing, the outlet volute chamber is connected to the inlet volute chamber, and the outlet volute chamber is a variable cross-section cavity; An air outlet duct is connected to the outlet volute chamber, and the outlet volute chamber adopts a variable cross-section cavity.

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