Stator assembly with air guide hole and air compressor

Abstract

The stator assembly comprises a half-and-half casing and a plurality of stages of integrated stator lining rings, each integrated stator lining ring comprises a lining and a stator ring, the lining is integrated on the stator ring and arranged at the position, located at the blade tip of a rotor blade, of a half-and-half machine brake, and the stator ring is arranged on the half-and-half machine brake. A reinforcing structure is arranged on the surface of the outer wall of the integrated stator bushing ring; the integrated stator bushing ring insertion groove and the half-and-half casing are provided with air entraining channels which are communicated with each other, and the air entraining channels are used for leading air flow from the integrated stator bushing ring at the hot end to the integrated stator bushing ring at the cold end through the insertion groove and the half-and-half casing so as to coordinate expansion deformation of the stator blades and the half-and-half casing. Compared with a conventional stainless steel casing, the weight is reduced by 30% or above, the blade containing coefficient is increased by 10% or above compared with the conventional casing, non-design point blade tip cold-state gaps caused by casing deformation increase are reduced by 20% or above compared with the conventional casing, and the performance of an aero-engine compressor is effectively improved.

Description

Technical Field

[0001] The invention relates to the technical field of aeroengines, in particular to a stator assembly with air bleed holes and a compressor. Background Art

[0002] The existing half-type axial flow casing is generally made of stainless steel. A graphite coating is sprayed on the casing corresponding to the blade tips of the first-stage blade disk 1 and the second-stage blade disk 4 of the rotor to prevent blade scratching. Figure 1 , Figure 1 The middle arrow indicates the airflow direction in the casing. The first-stage stator ring 2 and the second-stage stator ring 5 are installed on the axial flow casing 3 through T-slots. The existing half-type axial flow casing has the following problems:

[0003] 1. In aircraft engines or test pieces that use a half-axial flow casing structure, the volume of the axial flow casing accounts for a relatively high proportion of the total volume of the whole machine relative to other parts. The overall use of high-density stainless steel materials will result in a heavier machine mass; 2. If the existing casing wants to improve the tolerance of the rotor blade disk when it breaks, it is necessary to replace the material or increase the casing wall thickness to make the whole machine heavier; 3. For an axial flow casing made of titanium alloy, a graphite coating is sprayed only on the casing corresponding to the tip of the rotor blade. Once the casing is severely scraped and rubbed with the rotor disk, which is also made of titanium alloy, titanium fire is easily generated, and the casing and rotor are burned at the same time. 4. When the compressor rotor is in working condition, the impeller blades will be deformed in the axial and radial directions under the influence of aerodynamic force, temperature and centrifugal force at high speed, resulting in a smaller gap between the rotor and stator. The blade tip is easily scraped and rubbed with the casing, resulting in titanium fire. The current practice is to design a larger cold gap to ensure that the rotor and stator do not collide during operation. Summary of the invention

[0004] The present invention provides a stator assembly with air bleed holes and a compressor to solve the technical problem that the blades of the existing compressor rotor impeller undergo radial deformation during high-speed operation, making it easy for the impeller blade tip to scrape against the casing.

[0005] According to one aspect of the present invention, there is provided a stator assembly with air bleed holes, the stator assembly with air bleed holes comprising a half casing and several stages of integrated stator bushing rings, the several stages of the integrated stator bushing rings being mounted on the insertion grooves of the half casing, the integrated stator bushing ring comprising a bushing and stator blades, the stator blades being mounted on the bushing, the bushing being arranged at the tip of the rotor blades on the half casing and forming a gap with the rotor blades, the outer wall surface of the integrated stator bushing ring being provided with a reinforcement structure; the integrated stator bushing ring, the insertion groove and the half casing being provided with bleed channels interconnected with each other, the bleed channels being used to guide the airflow from the integrated stator bushing ring at the hot end through the insertion groove and the half casing to the integrated stator bushing ring at the cold end to enable the stator blades and the half casing to deform in a coordinated manner.

[0006] Furthermore, the integrated stator bushing rings of several levels include at least a first-level integrated stator bushing ring for being close to the cold end of the compressor and a second-level integrated stator bushing ring for being close to the hot end of the compressor, and a first insertion groove and a second insertion groove are provided on the half casing; the first-level integrated stator bushing ring is installed on the first insertion groove, and the second-level integrated stator bushing ring is installed on the second insertion groove; the second-level integrated stator bushing ring is provided with an air inlet hole connected with the second insertion groove in a radial direction, a first air vent is provided on a stop end face of the second-level integrated stator bushing ring close to the first-level integrated stator bushing ring, and a second air vent is provided on a stop end face of the first-level integrated stator bushing ring close to the second-level integrated stator bushing ring, and a third air vent connected with the first air vent and the second air vent is provided on the half casing; an air outlet connected with the first insertion groove is provided on the outer wall of the half casing; the air inlet hole, the first air vent, the third air vent, the second air vent and the air outlet constitute an air bleed channel.

[0007] Furthermore, a plurality of air bleed channels are provided, and the plurality of air bleed channels are evenly spaced along the circumference of the stator assembly.

[0008] Furthermore, the diameters of the air inlet and the air outlet are 1.5 to 8 mm.

[0009] Furthermore, the cross-sections of the first ventilation hole, the third ventilation hole, and the second ventilation hole are waist-shaped.

[0010] Furthermore, a graphite coating is provided on the inner wall of the bushing corresponding to the rotor impeller blade tip.

[0011] Furthermore, the bushing is made of stainless steel, and the casing halves and the rotor impeller are made of titanium alloy.

[0012] Furthermore, the reinforcement structure of the outer wall of the integrated stator liner ring is a reinforcing rib.

[0013] Furthermore, the thickness of the reinforcing rib is 30% to 80% of the height of the insertion groove.

[0014] According to yet another aspect of the present invention, there is provided a compressor, comprising the above-mentioned stator assembly with air bleed holes.

[0015] The present invention has the following beneficial effects:

[0016] 1. In the present invention, the bushing and the stator ring are integrated into one body to achieve the purpose of the integrated lightweight design of the stator assembly. The outer wall surface of the integrated stator bushing ring is provided with a reinforcement structure to improve the strength and containment of the stator assembly, and can contain the fallen blocks or fallen blades at the highest operating speed to avoid large cracks and distortion of the stator assembly. At the same time, the integrated stator bushing ring, the insertion groove and the half casing are provided with interconnected air bleed channels, which are used to guide the airflow from the high-temperature integrated stator bushing ring to the The integrated stator bushing ring with a lower temperature heats the stator blades in the half-casing and the integrated stator bushing ring with a lower temperature, so that the stator blades in the stator assembly are deformed by the heat during operation, and the deformation trend is the same as that of the rotor blades, thereby keeping the gap between the rotor and the stator within a set range, thereby preventing the blades from being deformed by aerodynamics, temperature, centrifugal force, etc. during high-speed operation of the impeller, resulting in some blade tips being easily scraped against the casing and generating titanium fire, thereby allowing a smaller cold gap to be designed to improve the performance of the compressor in the non-working state.

[0017] 2. The weight of the stator assembly with air bleed holes of the present invention is reduced by more than 30% compared with the conventional stainless steel casing, the blade inclusion coefficient is increased by more than 10% compared with the conventional casing, and the cold clearance of the blade tip at the non-design point caused by the increased casing deformation is reduced by more than 20% compared with the conventional casing, effectively improving the performance of the compressor.

[0018] 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. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The drawings constituting a part of this application are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings:

[0020] Figure 1 It is a structural schematic diagram of an existing half-type axial flow casing;

[0021] Figure 2 It is a schematic diagram of the explosion structure of the half-type axial flow casing of the present invention;

[0022] Figure 3 Schematic diagram of the structure of the reinforcing ribs on the bushing Figure 1 ;

[0023] Figure 4 Schematic diagram of the structure of the reinforcing ribs on the bushing Figure 2 ;

[0024] Figure 5 It is a structural schematic diagram of the air bleed channel;

[0025] Figure 6 A schematic cross-sectional view of the air inlet hole on the end face of the stopper;

[0026] Figure 7 is a schematic diagram of the connection structure between the bushing and the insertion groove;

[0027] Figure 8 Illustration of the anti-rotation structure on the half receiver Figure 1 ;

[0028] Fig. 9 Illustration of the anti-rotation structure on the half receiver Figure 2 ;

[0029] Fig.10 Schematic diagram of the anti-rotation structure on the integrated stator bushing Figure 1 ;

[0030] Fig.11 Schematic diagram of the anti-rotation structure on the integrated stator bushing Figure 2 ;

[0031] Fig.12 Top view of the anti-rotation structure on the integrated stator bushing;

[0032] Fig.13 Schematic diagram of the structure of the integrated stator bushing.

[0033] In the figure: 1-first-stage blade disk; 2-first-stage stator ring; 3-axial flow casing; 4-second-stage blade disk; 5-second-stage stator ring; 6-first-stage integrated stator bushing ring; 61-first insertion groove; 62-second ventilation hole; 7-half casing; 71-third ventilation hole; 72-exhaust hole; 8-second-stage integrated stator bushing ring; 81-second insertion groove; 82-inlet hole; 83-first ventilation hole; 9-bushing. DETAILED DESCRIPTION

[0034] 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.

[0035] See also Figures 2 to 13An embodiment of the first aspect of the present invention provides a stator assembly with air bleed holes, the stator assembly with air bleed holes comprises a half casing 7 and several stages of integrated stator bushing rings, the several stages of the integrated stator bushing rings are mounted on the insertion grooves of the half casing 7, the integrated stator bushing ring comprises a bushing 9 and a stator blade 10, the stator blade 10 is mounted on the bushing 9, the bushing 9 is arranged at the tip of the rotor blade on the half casing and forms a gap with the rotor blade, and the outer wall surface of the integrated stator bushing ring is provided with a reinforcement structure; the integrated stator bushing ring, the insertion groove and the half casing 7 are provided with mutually connected air bleed channels, the air bleed channels are used to guide the airflow from the integrated stator bushing ring at the hot end through the insertion groove and the half casing to the integrated stator bushing ring at the cold end to make the stator blades and the half casing 7 deform in a coordinated manner.

[0036] Specifically, the casing halves 7 and rotor impellers of the present invention are made of titanium alloy to meet the requirements of lightweight design. A graphite coating is provided on the inner side of the bushing to prevent titanium fire caused by scraping between the rotor and stator. The number of the integrated stator bushing rings is set according to the requirements, and can be two, three, four or more stages. Several stages of the integrated stator bushing rings are installed on the insertion grooves of the casing halves 7. Preferably, the insertion grooves are T-shaped grooves. Figure 7 , a gap is provided at the connection between the integrated stator bushing ring and the insertion groove. More specifically, a groove is milled at the T-slot of the longitudinal mounting edge of the half casing 7 (see Figure 8 and Fig. 9 ), the groove depth D1 is 4 to 10 mm, and the groove width D2 is 3 to 6 mm; a boss is provided on the mounting edge of the integrated stator bushing ring (see Fig.10 , Fig.11 and Fig.12 ), the boss width d1 is 4 to 10 mm, the height d2 is 2 to 5 mm, and d2 needs to be smaller than D2, so that the integrated stator bushing ring can be installed into the groove on the T-slot through the boss and engage with each other. Furthermore, the first-stage integrated stator bushing ring and the second-stage integrated stator bushing ring are installed in place through the T-slot on the half casing 7. See Fig.13 , integrated stator bushing ring mounting edge outer diameter The diameter clearance with the insertion groove of the half casing 7 must be 0.02 to 0.1 mm, and the inner diameter of the mounting edge of the integrated stator bushing ring The matching with the half casing 7 needs to ensure a diameter clearance of 0.05-0.2mm, and the axial matching distance X1 between the mounting edge of the integrated stator bushing ring and the half casing 7 needs to be 3-10mm. The above-mentioned matching dimensions are guaranteed by the processing design of the matching parts. The clearances of 0.02-0.1mm, 0.05-0.2mm, and 3-10mm are to ensure that the bushing can be successfully installed in the T-slot during the assembly process. Too small a clearance will cause jamming during assembly, and too large a clearance will cause the bushing to shake during use, causing safety hazards.

[0037] The integrated stator bushing ring, the insertion groove and the half casing 7 are provided with interconnected bleed channels in sequence. A plurality of groups of bleed channels are provided on the stator assembly. Preferably, the bleed channels can be provided as 15-30 groups. More preferably, the bleed channels are provided on two adjacent groups of integrated stator bushing rings. The bleed channels are used to direct the airflow from the integrated stator bushing ring at the hot end through the insertion groove and the half casing between two adjacent insertion grooves into the insertion groove on the integrated stator bushing ring at the cold end to heat the first-stage stator blades with lower temperature. Finally, the airflow flows out from the outer wall of the casing to coordinate the expansion and deformation of the stator blades and the half casing 7 to avoid scraping between the blade tips of the rotor impeller and the casing.

[0038] The present invention integrates the bushing 9 and the stator ring into one body to achieve the purpose of an integrated lightweight design of the stator assembly. The outer wall surface of the integrated stator bushing ring is provided with a reinforcement structure for improving the strength and containment of the casing. It can contain fallen blocks or detached blades at the highest operating speed to avoid major cracks and twisting deformation of the casing.

[0039] Furthermore, the integrated stator bushing ring of the present invention includes a bushing and a stator blade, the integrated stator bushing ring is installed on the insertion slot of the half casing, and the bushing is arranged at the tip of the rotor blade on the half casing and forms a gap with the rotor blade. It can be understood that the bushing in the present invention extends to the tip of the rotor blade on the basis of the stator ring in the prior art. Preferably, the bushing is made of stainless steel and is provided with a graphite coating to prevent the rotor blade from scraping and rubbing against the bushing to produce titanium fire.

[0040] Since the smaller the rotor-stator gap is, the better the aerodynamic performance can be achieved during the operation of the compressor, it is necessary to ensure the smallest possible rotor-stator gap while ensuring safety. As the compressor speed increases (centrifugal force increases), the working state of the compressor becomes larger (aerodynamic force increases, temperature rises), and the rotor blades deform (mainly radial elongation) under the action of aerodynamic force, temperature and centrifugal force, resulting in a smaller radial gap between the rotor and stator. A design speed is given when the compressor is designed. The state when working at the design speed is called the design state. When the compressor reaches the design speed, the rotor-stator gap can reach the design gap (generally 0.2-0.3mm). Therefore, during assembly, the radial deformation of the rotor caused by aerodynamic force, temperature and centrifugal force is usually added to the gap in the design state (0.2-0.3mm), which is also the assembly gap as the cold state (stationary state / speed is 0) gap. If the rotor-stator gap is designed to be too small in the cold state, scraping will occur in the working state. The aerodynamic performance of the compressor in the non-design state (other speeds than the design speed) is also very important, so reducing the cold clearance can also improve the performance of the compressor in the non-working state.

[0041] Therefore, the present invention provides interconnected air bleed channels in sequence on the integrated stator liner ring, the insertion groove and the half casing, and the air bleed channels are used to guide the airflow from the integrated stator liner ring with a high temperature to the integrated stator liner ring with a lower temperature, so as to heat the stator blades in the integrated stator liner ring with a lower temperature, so that the stator blades and the half casing expand due to heat, and the expansion trend is the same as that of the rotor, thereby preventing the impeller blades from being deformed by aerodynamics, temperature, centrifugal force, etc. during high-speed operation, resulting in some blade tips being easily scraped against the casing and generating titanium fire, thereby making it possible to design a smaller cold clearance and improve the compressor performance in the non-working state.

[0042] In the embodiments of the present invention, see Figure 5 , Figure 5 The arrow in indicates the flow direction of the high-temperature and high-pressure airflow. The half-casing 7 is provided with an air bleed channel in units of at least two adjacent integrated stator bushing rings, and the stator assembly with air bleed holes is provided with a plurality of integrated stator bushing rings. As described above, in this embodiment, the air bleed channel is provided in units of two adjacent integrated stator bushing rings, and the high-temperature and high-pressure airflow enters the insertion groove from one of the integrated stator bushing rings 6, enters the half-casing between two adjacent insertion grooves from the insertion groove, and then enters the insertion groove of the integrated stator bushing ring 6 with a lower temperature, heats the stator blades with a lower temperature, and finally flows out from the half-casing wall on the insertion groove corresponding to the integrated stator bushing ring of this level. In actual application, the air bleed channel can also be provided in units of three or more integrated stator bushing rings according to actual conditions, and the coordinated deformation of the blades and the casing can be controlled by introducing a reasonable amount of high-temperature and high-pressure airflow through calculation. In this embodiment, the bleed air channel is set based on the two-stage integrated stator liner ring so that the bleed air volume of the provided airflow will not be too large. If only one airflow is used in the entire compressor to heat the blades on the multi-stage integrated stator liner rings at the same time, the bleed air volume will increase accordingly, which may easily lead to a decrease in compressor performance.

[0043] In the embodiments of the present invention, see Figure 5The integrated stator bushing rings of several stages at least include a first-stage integrated stator bushing ring 6 for being close to the cold end of the compressor and a second-stage integrated stator bushing ring 8 for being close to the hot end of the compressor. A first insertion groove 61 and a second insertion groove 81 are provided on the half casing 7; the first-stage integrated stator bushing ring 6 is installed on the first insertion groove 61, and the second-stage integrated stator bushing ring 8 is installed on the second insertion groove 81; the second-stage integrated stator bushing ring 8 is provided with an air inlet 82 connected with the second insertion groove 81 in the radial direction, a first air vent 83 is provided on the stop end face of the second-stage integrated stator bushing ring 8 close to the first-stage integrated stator bushing ring, a second air vent 62 is provided on the stop end face of the first-stage integrated stator bushing ring 6 close to the second-stage integrated stator bushing ring, and a third air vent 71 connected with the first air vent 83 and the second air vent 62 is provided on the half casing; an air outlet 72 connected with the first insertion groove 61 is provided on the outer wall of the half casing 7. The number of the air inlet holes 82 can be the same as or less than the number of the stator blades. The air inlet holes 82 are arranged along the circumference of the stator ring together with the stator blades. Preferably, the air inlet holes 82 are arranged in the middle of the integrated stator bushing ring so that the airflow from the air inlet holes 82 can smoothly enter the insertion groove without being blocked. The number of the air inlet holes 82, the first air vents 83, the third air vents 71, the second air vents 62 and the air outlet holes 72 is the same. By arranging the first air vent 83, the third air vent 71 and the second air vent 62 which are interconnected at the stop end faces of the second stator liner ring, the half casing 7 and the first stator liner ring, the air flow entering the second insertion slot 81 from the air inlet 82 can enter the first insertion slot 61 through the first air vent 83, the third air vent 71 and the second air vent 62, and then the air flow flows out from the air outlet 72, thereby heating the stator blades on the first-stage integrated stator liner ring 6 and the corresponding half casing 7, so that the stator blades and the half casing 7 expand due to the heat, with the same expansion trend as the rotor, and thus a smaller cold gap can be designed to improve the compressor performance in different working conditions.

[0044] In the embodiment of the present invention, the air inlet 82, the first air vent 83, the third air vent 71, the second air vent 62 and the air outlet 72 form an air bleed passage. When in use, the high-temperature and high-pressure airflow in the casing flow passage after work flows from the air inlet 82 on the secondary integrated stator bushing ring 8 into the first insertion groove 61 of the half casing 7, passes through the first air vent 83, the third air vent 71, the second air vent 62 at the stop end face of the secondary integrated stator bushing ring 8, the half casing 7 and the first integrated stator bushing ring 6, and passes through the outer surface of the first integrated stator bushing ring 6 to heat the stator blades on the first integrated stator bushing ring 6 with a lower temperature, so that the stator blades and the half casing 7 are deformed in coordination, and finally flows out from the air outlet 72 on the casing wall of the first insertion groove 61 of the half casing 7.

[0045] In an embodiment of the present invention, the bleed air passages are provided in a plurality, and the plurality of bleed air passages are evenly arranged along the circumferential interval of the stator assembly. Further, the bleed air passages may be provided in 15 to 30 numbers. Multiple groups of bleed air passages are provided on each unit of the integrated stator bushing ring and the half casing, so that the stator blades and the half casing on the axial flow casing can be heated more evenly.

[0046] In the embodiments of the present invention, see Figure 6 , the diameters of the air inlet 82 and the air outlet 72 are 1.5 to 8 mm, and the cross-sections of the first vent 83, the third vent 71, and the second vent 62 are waist-shaped. The air inlet 82 is evenly distributed at 15 to 30 locations on the secondary integrated stator bushing ring 8 in the circumferential direction, and has a diameter of 1.5 to 8 mm; the air outlet 72 is evenly distributed at 15 to 30 locations on the casing wall above the coating of the first-stage integrated stator bushing ring 6 of the half casing 7, and has a diameter of 1.5 to 8 mm. The first vent 83, the third vent 71, and the second vent 62 are located on the stop end faces of the first-stage integrated stator bushing ring 6, the half casing 7, and the second-stage integrated stator bushing ring 8, and have a waist-shaped cross-section, evenly distributed at 15 to 30 locations in the circumferential direction. The cross-sections of the first ventilation hole 83, the third ventilation hole 71 and the second ventilation hole 62 are waist-shaped, the angle α° on both sides of the hole edge is 2°~10°, the hole height X is not greater than 2 / 3 of the height of the mating end face, and the chamfer R is 0.5mm~2mm. The values ​​of the angle on both sides of the hole edge, the hole height X and the chamfer R are obtained through calculation. The airflow rate of the holes in this range is higher, and the stress concentration generated on the casing is smaller.

[0047] In an embodiment of the present invention, a graphite coating is provided on the inner wall of the bushing corresponding to the tip of the rotor impeller. The graphite coating is an abradable coating that can protect the casing and the blades when the rotor and stator are slightly scraped. Without the protection of the coating, the high-speed rotating rotor and the stator may scrape and cause a safety accident.

[0048] In an embodiment of the present invention, the bushing 9 is made of stainless steel, and the casing halves 7 and the rotor impeller are made of titanium alloy.

[0049] In this embodiment, both the half casing and the impeller rotor are made of a lighter titanium alloy material, and the bushing 9 is arranged at the tip of the rotor blade on the half casing, and the bushing 9 is made of stainless steel, so as to avoid the problem that the impeller is easily deformed during high-speed operation, resulting in the blade tip being easily scraped against the casing and causing titanium fire. In addition, a graphite coating is also provided on the bushing 9 of the present invention to further improve the titanium fire resistance.

[0050] In an embodiment of the present invention, the reinforcement structure of the outer wall of the integrated stator bushing ring is a stiffener rib. The present invention sets a stiffener rib structure on the outer wall of the integrated stator bushing ring to improve the rigidity of the half-casing, thereby improving the containment of the half-casing. The containment of the casing on an aircraft engine generally refers to the containment of the casing to the blades, requiring that the casing must have sufficient strength to contain fallen or detached blades at the highest operating speed, and the casing does not suffer from major cracks and verified distortion. The prior art increases the rigidity of the casing by increasing the wall thickness, but the increase in wall thickness increases the weight of the casing. The integrated stator ring bushing ring can be formed by additive manufacturing. By adding a stiffener rib structure to the outer wall surface, the rigidity and containment of the casing can be improved while controlling the weight.

[0051] In an embodiment of the present invention, the thickness of the reinforcing rib is 30% to 80% of the height of the insertion groove. Figure 3 and Figure 4 , the thickness of the reinforcing rib t2 is 30% to 80% of the height of the T-slot t1, and the cross angle θ° of the reinforcing rib is 40° to 90°. Through topological optimization calculation, it is found that the best effect on stiffness improvement is obtained within this range. At the same time, since the integrated stator bushing ring is installed in the insert slot, and the insert slot needs to be used for airflow, the thickness of the reinforcing rib cannot be too high to avoid affecting the airflow; at the same time, the thickness of the reinforcing rib cannot be too low, otherwise it will affect the stiffness of the casing. Therefore, the thickness of the reinforcing rib t2 is 30% to 80% of the height of the T-slot t1, which is the optimal range, which can take into account both airflow and improving the stiffness of the casing.

[0052] According to another aspect of the present invention, a compressor is provided, the compressor comprising the stator assembly with air bleed holes. The engine comprising the stator assembly with air bleed holes can simultaneously meet the requirements of preventing titanium fire caused by scraping between the rotor and stator, containing fragments caused by explosion of the internal rotor, coordinating the deformation of the front and rear stage stators, and light weight.

[0053] The contact impact algorithm of the commercial finite element analysis software ANSY / LSDYNA was used to perform simulation calculation analysis on the existing casing made of stainless steel material and the titanium alloy casing of the present invention. The results are shown in Table 1.

[0054] Table 1 Weight analysis results of steel and titanium alloy receivers

[0055] project Receiver weight Stator ring and bushing weight gross weight Weight reduction percentage Steel Receiver 12.02 0.88 12.89 / Titanium alloy receiver 6.46 1.97 8.44 34.5％

[0056] Through three-dimensional model simulation, the weight of the stator assembly with air bleed holes of the present invention is reduced by more than 30% compared with that of a conventional casing, the blade inclusion coefficient is increased by more than 10% compared with that of a conventional casing, and the cold clearance of the blade tip at non-design points caused by increased casing deformation is reduced by more than 20% compared with that of a conventional casing, thereby effectively improving the performance of the compressor.

[0057] The above description is only a preferred embodiment of the present invention and is 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 stator assembly with air ducting holes, characterized in that: The stator assembly with bleed holes comprises a half casing (7) and several stages of integrated stator bushing rings, wherein the several stages of the integrated stator bushing rings are mounted on the insertion grooves of the half casing (7), wherein the integrated stator bushing ring comprises a bushing (9) and a stator blade (10), wherein the stator blade (10) is mounted on the bushing (9), wherein the bushing (9) is arranged at the tip of the rotor blade on the half casing and forms a gap with the rotor blade, and a reinforcement structure is arranged on the outer wall of the integrated stator bushing ring; the integrated stator bushing ring, the insertion groove and the half casing (7) are provided with bleed channels that are interconnected, wherein the bleed channels are used to guide the airflow from the integrated stator bushing ring at the hot end through the insertion groove and the half casing (7) to the integrated stator bushing ring at the cold end so that the stator blade and the half casing (7) are deformed in a coordinated manner.

2. The stator assembly with air bleed holes according to claim 1, characterized in that: The integrated stator bushing rings of several stages include a first-stage integrated stator bushing ring (6) for use near the cold end of the compressor and a second-stage integrated stator bushing ring (8) for use near the hot end of the compressor. The half casing (7) is provided with a first insertion groove (61) and a second insertion groove (81); the first-stage integrated stator bushing ring (6) is installed on the first insertion groove (61), and the second-stage integrated stator bushing ring (8) is installed on the second insertion groove (81); the second-stage integrated stator bushing ring (8) is provided with an air inlet hole (82) in radial direction and connected with the second insertion groove (81); the second-stage integrated stator bushing ring (8) is close to the first stage. A first vent hole (83) is provided on the stop end face of one side of the integrated stator bushing ring (6); a second vent hole (62) is provided on the stop end face of the first-stage integrated stator bushing ring (6) close to the second-stage integrated stator bushing ring (8); a third vent hole (71) connected to the first vent hole (83) and the second vent hole (62) is provided on the half casing; an outlet hole (72) connected to the first insertion groove (61) is provided on the outer wall of the half casing (7); the air inlet hole (82), the first vent hole (83), the third vent hole (71), the second vent hole (62) and the outlet hole (72) constitute an air bleed passage.

3. The stator assembly with air bleed holes according to claim 2, characterized in that: There are a plurality of air bleed channels, which are evenly spaced along the circumference of the stator assembly.

4. The stator assembly with air bleed holes according to claim 2, characterized in that: The diameters of the air inlet (82) and the air outlet (72) are 1.5 to 8 mm.

5. The stator assembly with air bleed holes according to claim 2, characterized in that: The cross-sections of the first ventilation hole (83), the third ventilation hole (71), and the second ventilation hole (62) are waist-shaped.

6. The stator assembly with air bleed holes according to claim 1, characterized in that: The inner wall of the bushing (9) corresponding to the rotor impeller blade tip is provided with a graphite coating.

7. The stator assembly with air bleed holes according to claim 6, characterized in that: The bushing (9) is made of stainless steel, and the casing halves (7) and the rotor impeller are made of titanium alloy.

8. The stator assembly with air bleed holes according to claim 1, characterized in that: The reinforcement structure on the outer wall of the integrated stator liner ring is a reinforcing rib.

9. The stator assembly with air bleed holes according to claim 8, characterized in that: The thickness of the reinforcing rib is 30% to 80% of the height of the insertion groove, and the crossing angle of the reinforcing rib is 40° to 90°.

10. A compressor, characterized in that: A stator assembly with air bleed holes comprising any one of claims 1-9.

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