DIFFUSER FOR CENTRIFUGAL COMPRESSOR

Abstract: A diffuser of a centrifugal compressor of a type in which a plurality of stator blades (7) are provided outside an impeller (1) thereof,and which converts kinetic energy of fluid from the impeller (1) into pressure energy by operation of the stator blade (7), which diffuser being provided with sub-blades (8) near the inner ends of the stator blades (7), and intermediate blades (9) near outer ends of and between the stator blades (7).

Description: The invention relates to a diffuser of a centrifugal compressor for converting kinetic energy of fluid discharged from the impeller of the compressor with supersonic velocity into pressure energy by means of a plurality of stator blades and sub-blades at the inlet portion of the diffuser. The sub-blades are disposed between the stator blades and near to the inner ends thereof. Only one side surface of the sub-blades faces the stator blades, and the sub-blades are situated at positions intersecting a circle, the center of which corresponds to the center of the impeller. The circle passes through the inner ends of the stator blades. A diffuser of the generic kind is shown in the CH-A-492130. The known diffuser of a centrifugal compressor comprises sub-blades the leading edge of which is arranged upstream the leading edge of the stator blade facing the sub-blade. Thus the air speed is decelerated from supersonic speed to subsonic speed by means of a shock front generated by the sub-blade. The stator blades further decelerate the subsonic air flow. The sub-blades and the stator blades are adjustable in their angle with regard to the air flow from the impeller. Another diffuser is disclosed in JP-57-159 998 in connection with a centrifugal compressor the impeller of which generates an air flow with a velocity exceeding sonic velocity. The diffuser downstream of the impeller comprises stator blades. The spaces between these stator blades form diffuser passages. The design of the compressor is such that high pressure ratio can be obtained through a single stage. When the rotational speed is relatively high and discharge flow rate is also relatively small, a separation flow region could be generated in the negative pressure side of the stator blades, resulting in a surge phenomenon which means that a sufficient rise in pressure could not be obtained. In general, pressure in the direction of air flow passing through the stator blade-provided diffuser rises according to the reduction in the flow rate of the compressor. If it exceeds a certain limit, the same generates a back run, causing the stop of normal compressing function what is called a surging phenomenon which means that the compressor cannot be operated normally. The limit causing the diffuser to generate the back run is varied in accordance with the shape of the stator blade or the like. The generation of the back run is likely to be easily generated by separation of the air flow from the surface of the stator blade or the wall surfaces facing both sides of the stator blade. In general, separation of the air flow from the negative pressure side of the stator blade is a major cause. In this state, if the shock wave has reached the negative pressure side, the boundary layer along the negative pressure side is likely to undergo, due to strong rise in pressure in front of and behind the shock wave, rapid increase in its thickness, partial separation, or large scale of separation depending on circumstances. To prevent this pivotable sub-blades are provided at the inlet portion of the diffuser for the purpose of controlling the fluid passing through the diffuser. Since the diffuser passages formed between the stator blades are drastically enlarged immediately behind the downstream of the sub-blades a problem arises such that pressure loss is generated, and the choking flow is reduced, causing the performance of the diffuser to be deteriorated. In JP 53-119411, it is proposed that a blade-provided diffuser is formed in a double circular blade cascade and the length of the blade in the inner annular blade cascade is arranged to be no more than 0.9 times of the interval of the blades. With this arrangement problem of reduction in choking flow does not arise, but loss is generated due to a strong shear flow generated at the downstream of the blades of the inner circular blade cascade when the speed of the fluid at the inlet portion of the blades which form the inner circular blade cascade exceeds sound velocity. As a result, a problem arises such that the performance of the diffuser is deteriorated. US-3 184 152 further describes a diffuser of a centrifugal compressor comprising stator blades, in the channel between which the supersonic flow is decelerated to subsonic flow by means of extension waves and a shock front. Downstream of the shock front a guide blade can be disposed in each flow channel extending to the peripheral circle defined by the downstream edges of the stator blades. The problem underlying the invention is to design a diffuser such that the above mentioned problems are overcome and that wide operating range and high performance can be obtained. Starting out from the diffuser of the generic kind this problem is solved in that the chord length of the sub-blades is considerably shorter than the corresponding chord of the fixed stator blades, and in that the leading edge of each sub-blade is situated downstream of a line drawn from the leading edge of the respective facing stator blade perpendiculary to this stator blade. As the leading edge of the sub-blade lies downstream of the leading edge of the facing stator blade a shock wave is generated at the front end of the stator blade. The shock wave does not strike or reach the sub-blade and neighboring stator blade since the shock wave is extended substantially perpendicular to the stator blade when the Mach number of the air flow aproximates 1. Since the shock waves are generated when a supersonic flow is decelerated to a subsonic flow, the shock wave does not reach the negative pressure side. Therefore, subsonic flow passes through the region between the sub-blade and the negative pressure side of the stator blade. Thus the operting range can be enlarged by avoiding the occurence of surging phenomenon. Preferably each sub-blade is disposed at a position not intersecting a perpendicular line which is drawn to one of the stator blades at the inner end of said one stator blade which confronts said sub-blade. An adjustment of the sub-blade can be obtained by rotatably supporting each sub-blade by a supporting shaft which is disposed in parallel to the rotational shaft of the impeller. Losses can be further reduced if the distance between the inner end of the sub-blade and said stator blade confronting said sub-blade and the distance between the outer end of said sub-blade and said stator blade is arranged to be different. It is preferred for the inner sub-blades to be made as thin as possible, however, a certain thickness is required for keeping strength. Therefore, the number of the stator blades needs to be selected to secure sufficient cross sectional area of flow. In such a case the performance may be lowered because the flow passage near the outer periphery of the stator blade or the interval of the stator blades is excessively enlarged. For avoiding this intermediate blades are disposed near the outer ends of the stator blades and between those stator blades the length of chord of which intermediate blades is shorter than that of the stator blades. Each intermediate blade extends through the middle point of a perpendicular line drawn from an outer edge of the stator blade to the neighbouring stator blade or to an extension of inside of the neighbouring stator blade. The outer edge of each intermediate blade reaches a circle which passes through an outer edge of said stator blade. The length of the intermediate blade is disposed inside the middle point of the perpendicular line if within 20% of the overall length of the intermediate blade. The whole shape of the intermediate blade is formed in such a manner that, if said intermediate blade is assumed to be rotationally displaced around the center of the rotational shaft of the impeller, said intermediate blade is included in a contour of said stator blade. Since the intermediate blades are extended near the outer periphery of and between the stator blades in such a manner that the intermediate blade extends through the middle point of the perpendicular line from the outer end of the stator blade to the blade surface of the neighbouring blade, the intervals of the stator blades can be made proper value near the outer periphery of the stator blade. As a result of this reduction in the performance can be prevented. Because of adjustment reasons, the intermediate blades can be rotatably supported by supporting shafts which are disposed in parallel to the rotational shaft of the impeller. Preferably the distance between the inner end of the intermediate blade and the stator blade confronting the intermediate blade and the distance between the outer end of the intermediate blade and the stator blade is arranged to be different. With the convenient embodiment of the diffuser according to the invention the inlet-side sub-blade has a height that is smaller than that of the stator blade. Further, a rectifier blade can be disposed downstream of the inlet-side sub-blade, which rectifier blade has a height which is shorter than that of the inlet-side sub-blade. Finally, the outlet-side intermediate blade, which is provided downstream of the rectifier blade, can have a height corresponding or similar to that of the inlet-side sub-blade. The arrangements consisting of an inlet-side sub-blade, a rectifier blade and an outlet-side intermediate blade may be provided in a confronting manner with each other in said diffuser portion. With these arrangements the operating flow rate range of the diffuser can be enlarged without deterioration in performance, so that the operating flow rate range of the centrifugal compressor or air fan can be significantly enlarged. With reference to the drawings embodiments of the invention will be described. Fig. 1 is a sectional view of a diffuser for a centrifugal compressor according to a first embodiment of the invention, Fig. 2 is a cross-sectional view taken along the line II-II in Fig. 1, Figs. 3 to 5 are diagrams respectively illustrating the operation of the diffuser according to the first embodiment, Figs. 6 to 8 are enlarged views respectively illustrating modified portions of the first embodiment, Fig. 9 is a cross-sectional view of a second embodiment of a diffuser for a centrifugal compressor, Fig. 10 is a perspective view of a diffuser portion of the second embodiment shown in Fig. 10, and Figs. 11 to 14 are enlarged views respectively illustrating modified portions of the second embodiment. Fig. 1 shows a centrifugal compressor provided with an impeller 1 comprising blades 1A and a core plate 1B and being driven by a rotational shaft 2 which is connected to a not shown driving means of motor. The centrifugal compressor further comprises a casing 3, a suction pipe 4, a diffuser portion 5, and a scroll casing 6. The diffuser portion 5 comprises a blade-side diffuser casing 5A, a core-side diffuser casing 5B, a plurality of stator blades 7 disposed, as shown in Fig. 2, between the diffuser casings 5A and 5B, and intermediate blades 9 and sub-blades 8 provided for the blade-side diffuser casing 5A or for the core-side diffuser casing 5B in such a manner that the same project into the diffuser flow passage between the stator blades 7. The sub-blades 8 are disposed in such a manner that they intersect a circle 10 making the center of the rotational shaft 2 of the impeller 1 as its center and passing the inner end or edge (front end or edge) of the stator blade 7. When a perpendicular line 11 is drawn from the front end of a stator blade 7b, situated at a side of a center of radius of curvature of a neighbouring stator blade 7a, down to the other stator blade 7a, the sub-blade 8 is disposed not to intersect this perpendicular line 11. The intermediate blades 9 are disposed in such a manner that they pass the middle point of a perpendicular line 12 drawn from the rear end (outer end) of the stator blade 7a to the neighbouring stator blade 7b. The rear end or edge of the intermediate blade 9 reaches a circle 13 which passes through the outer periphery or rear ends or edges of the stator blades 7. The length of the intermediate blade 9 projecting from the middle point of the perpendicular line 12 toward inside is no more than 20% of the overall length of this intermediate blade 9. The whole shape of the intermediate blade 9 is designed such that the blade 9 is included in the stator blade 7 if this intermediate blade 9 is assumed to be rotationally displaced by a certain angle around the center of the rotational shaft 2. Furthermore, the stator blades 7, the sub-blades 8 and the intermediate blades 9 are respectively restricted at their both ends by the confronting casings 5A and 5B in the diffuser portion, the resulted space forming the diffuser portion 5. The kinetic energy of air flow A discharged from the impeller 1 is converted into pressure energy and the air is compressed at the time of its passing through the diffuser portion 5. Since the flow velocity of air flow A introduced into the diffuser portion 5 exceeds sound velocity, shock waves are generated causing the flow velocity to be reduced to subsonic speed. Figs. 3 and 4 show strong shock waves 15a, 15b and 20 which are generated near the front ends of the stator blades 7a and 7b and the sub-blade 8, and which affect the flow, such shock waves being generated in a case where the Mach number of the air flow A approximates 1 (for example 1.1 or less). The angle ϑ (Fig. 3) defined by the air flow A and the stator blade 7a is changed in accordance with the flow rate of air compressed by the compressor. The shock wave 15a generated at the front end of the stator blade 7a does not strike or reach the sub-blade 8 and neighbouring stator blade 7b since the shock wave 15a is extended substantially perpendicular to the stator blade 7a in a case where the Mach number of the air flow A approximates 1. Subsonic flow 17 passes through a region situated between the sub-blade 8 and the negative pressure side 16 of the stator blade 7a and a region in its downstream between a dashed line 18 and the negative pressure side 16. The shock wave 15b generated at the front end of the stator blade 7b confronting the stator blade 7a only reaches the dashed line 18, and it does not reach the negative pressure side 16 of the stator blade 7a. By provision of the subblade 8 in the manner as described above, the shock wave is prevented from reaching the negative pressure side 16, and the operating range can be enlarged by avoiding the occurrence of the surging phenomenon as the separation of the air flow layer from the negative pressure side can be substantially prevented and the limit causing the back run can be shifted to lower flow rate range by preventing the shock wave from reaching the negative pressure side. The larger or higher flow rate limit of the air flow is defined in accordance with the minimum cross-sectional area of the flow passage in the diffuser portion. Therefore, referring to Fig. 3, it is defined by the length of the perpendicular or normal line 11 drawn from the front end of the stator blade 7b to the negative pressure side 16 of the stator blade 7a. In this case, since the sub-blade 8 does not intersect the perpendicular line 11, avoiding the perpendicular line 11 to be shortened, it does not affect the larger flow rate limit. Because of the provision of the sub-blade 8, the smaller or lower flow rate limit can be shifted to smaller flow rate range without any reduction in the larger flow rate limit. The described effect of enlargening the flow rate range by means of the sub-blade 8 is improved without any deterioration in the performance of the diffuser when the sub-blade 8 satisfies the following conditions. The first condition is that the rear end of the sub-blade 8 is situated at an upstream side of the perpendicular line 11. If the sub-blade 8 intersects the perpendicular line 11, the maximum flow rate, as described, decreases and the pressure loss is generated as well due to the rapid enlargement of the cross-sectional area of the flow passage. Since the passage situated at the downstream of the perpendicular line 11 is located between the stator blades 7a and 7b, the width of the passage is rapidly or drastically enlarged by the thickness h of the rear end if the rear end of the sub-blade 8 is situated at a position downstream of the perpendicular line 11. On the other hand, in the region within a distance p between the rear end of the sub-blade 8 and the perpendicular line 11, since the air flow 17 which has been reduced in its velocity to subsonic after passing between the sub-blade 8 and the stator blade 7b and the supersonic flow 19 upstream of the shock wave 15b are brought into contact with each other and mixed each other, large pressure loss is generated. Therefore, the distance p is required to be small enough. The distance p is required or preferred to be 50% or less of the distance m between the front end of the stator blade 7b and the perpendicular line 11. The second condition is that the ratio r/q of the distance r at the outlet between the sub-blade 8 and the stator blade 7a with respect to the distance q at the inlet of the sub-blade 8 and the stator blade 7a is approximated to 1, for example, is 1 to 1.1. If r/q is made outside of this range, the flow will be separated from the surface of the sub-blade 8, causing loss downstream of the sub-blade 8 or stator blade 7a, to be increased. The third condition is that the ratio n/q of the length n of the portion where the sub-blade 8 and the stator blade 7 confronts each other with respect to the distance q between the front end of the stator blade 7a and the surface of the sub-blade 8 is required to be larger than 1 for the purpose of ensuring to make the air flow 17 subsonic. Since the sub-blade 8 does not protrude into the region where the flow is strictly restricted between the stator blades 7a and 7b, the rapid enlargement of the cross-sectional area of the flow passage and reduction in the choking flow rate at the immediately downstream of the sub-blade 8 do not occur. Furthermore, the distance between the outer end of the sub-blade 8 and the perpendicular line 11 is relatively short, and the region in which strong shear flow occurs is thereby short, reducing the pressure loss. Since the rear end of the sub-blade 8 is situated between the front end of the stator blade 7a and the front end of the stator blade 7b, the shock wave does not reach the surface of the stator blade 7a, reducing the risk of the air flow 17 to be separated from the surface of the stator blade 7a. As a result of this, the range of flow rate where the diffuser portion 5 can be normally operated can be enlarged. The sub-blade 8 is, in the viewpoint of aerodynamics, preferable to be made as thin as possible, but it is required to be thick enough to have a reasonable strength structurally. That is, an appropriate length should be selected depending on the thickness (for example, 5 to 10 times of the thickness). In this state, the number of the stator blades needs to be selected to satisfy the above-mentioned relationship between the stator blade 7 and the sub-blade 8. In general, it should be decreased down to 80% or less with respect to the case where no sub-blade 8 is provided. As described above, by decreasing the number of the stator blades 7, the interval between stator blades 7 becomes too large near the outer periphery (outlet side), which may prevent the flow from passing along the surface of the stator blade 7 to result in the reduction of the performance. As shown in Fig. 5 the flow does not pass along the surface of the stator blade 7a, 7b on the negative pressure side 21 near the rear end of the stator blade 7a, causing large separation region 22 to be generated. This generation of the large separation region causes the reduction in the substantial cross-sectional area. As a result of this, the velocity reduction in the diffuser is deteriorated and the kinetic energy is dissipated in the separation region, causing the performance of the diffuser to be deteriorated. Such a type of large separation can be prevented by reducing load (deceleration) on the negative pressure side 16 near the rear end by inserting intermediate blades 9. The amount of deceleration on a negative pressure side 21 near the rear end of the stator blade 7a can be expressed, according to the one-dimensional flow theory, as h·sinβ/f-1 by using the circumferential distance h between a rear end 23 of the stator blade 7a and a rear end 24 of the stator blade 7b, the outlet angle β of the stator blade, and the length f of the perpendicular or normal line drawn from the rear end 23 of the stator blade 7a to its neighboring stator blade 7b. As this value becomes larger, the deceleration load becomes larger. The value h·sinβ/f-1 is determined in accordance with the shape and the number of the stator blades. As the number of the blades become large, it becomes small. Table 1 shows examples. In the case where the intermediate blades 9 are provided, the amount of deceleration near the rear end negative pressure side of the stator blade 7a can be expressed as g·sinβ/e-1 by the same reason as above. A deceleration load when the intermediate blade 9 is provided is also shown on Table 1. Because of the provision of the intermediate blade 9, the deceleration of 23% can be made deceleration of 19% in a case where the number of the stator blades is 17. As a result, the amount of deceleration can be reduced by 20%, causing the occurrence of large separation near the rear end of the negative pressure side to be suppressed. Effect of Intermediate blades The number of stator blades 21 17 17(with intermediate blade) h·sinβ/f-1 0.16 0.23 - g·sinβ/e-1 - - 0.19 Since the intermediate blade 9 serves to prevent the occurrence or generation of the large separation near the rear end of the stator blade 7a, the intermediate blade 9 is arranged in such a manner, for the purpose of ensuring to restrict the flow near the rear end of the stator blade 7, that it intersects the perpendicular line drawn from the rear end 23 of the stator blade 7a to the neighboring stator blade 7b, and that the rear end 25 reaches the circle 13. If the length of the intermediate blade is too long, the area which comes in contact with the flow is increased. Therefore, the length i of the intermediate blade 9 which is situated upstream of the above-described perpendicular line is arranged to be within 20% of the overall length of the intermediate blade 9. Since the flow upstream of the perpendicular line involves relatively small non-uniformity, the intermediate blade 9 is made pass through the middle point of the perpendicular line to equally divide the flow so that the flow at the outlet of the diffuser is made uniform. As a result of this, occurrence of additional loss due to non-uniform flow can be prevented. Since the overall shape of the intermediate blade 9 is formed in such a manner that, if the intermediate blade 9 is virtually or assumed to be rotationally displaced around the center of the rotational shaft 2, it is included within the contour of the stator blade 7, the flow can pass through smoothly, causing occurrence of loss to be reduced. Fig. 7 illustrates an embodiment in which the perpendicular line cannot be drawn from the rear end of the stator blade 7a onto the neighboring stator blade 7b, since the length of the chord of the stator blade 7 is too short. In this case, a perpendicular line 27 is used which is drawn to an extension 26 of the mean thickness line at the front end of the stator blade 7b. This extension line 26 may be formed by a straight line, but a logarithmic spiral passing through the front end of the stator blade 7b and forming an inlet angle ε achieves the same effect. As shown in Fig. 8, the sub-blade 8 is rotatably, by an angular extent δ, supported by a supporting shaft 29 which is disposed in parallel to the rotational shaft 2 of the impeller 1. In large flow rate operation mode, the length of a perpendicular line 28 drawn from the front end of the stator blade 7b to the sub-blade 8 is selected to be greater, while in small flow rate operation mode, the length of the perpendicular line 28 is selected to be smaller. As a result of this, the flow rate range can be further enlarged due to the throttling effect. In this embodiment, the supporting shaft 29 for the sub-blade 8 is manufally rotated. but it may be automatically operated by an appropriate control unit. In the embodiment of Fig. 9, the intermediate blade 9 is rotatably, by an angular extent γ, supported by a supporting shaft 31 disposed in parallel to the rotational shaft 2 of the impeller 1. The sum of the length of a perpendicular line 32 drawn from the front end of the intermediate blade 9 to the neighboring stator blade 7a and the length of a perpendicular line 30 drawn from the rear end of the intermediate blade 9 to the neighboring blade 7b is made greater in a large flow rate mode, while the sum is made smaller in a small flow rate mode. The same effect as that in the embodiment shown in Fig. 8 is intended to be obtained in which the flow rate range is enlarged by the throtting effect. If this embodiment is employed in combination with rotation control of the sub-blade 8, a better effect can be obtained. As shown in Fig. 10 blade arrangements 40 are provided at the blade-side diffuser casing 5A in such a manner that they project into the diffuser flow passage between the stator blades 7. Each blade arrangement 40 comprises, as shown in Figs. 10 and 11, an inlet-side sub-blade 40A having a length of chord and height smaller than those of the stator blade 7; a rectifier blade 40B with the height shorter than that of the inlet-side sub-blade 40A, and outlet-side intermediate blades 40C connected with the rectifier blade 40B and having the same or similar dimensions as those of the inlet-side sub-blade 40A. Since the inlet-side sub-blades 40A of the blade arrangements 40 guide the flow along the stator blades 7, the flow can be made pass along the stator blades 7 even if the flow rate is small or low. Therefore, possibility of occurring the surging phenomenon can be reduced, and the operating range of the impeller 1 can be enlarged. Since the inlet-side sub-blade 40A acts as described above, the height of the sub-blade 40A is preferably arranged to be in the order of 50% of that of the stator blade 7. Since the inlet-side sub-blades 40A are overhung from the blade-side diffuser casing 5A, the protruded height is preferably short for the purpose of securing strength. Therefore, it is made shorter than the height of the stator blade 7. Since the inlet-side sub-blade 40A narrows the flow passage, the inlet-side sub-blade 40A acts as a resistance if the discharging flow rate of the compressor exceeds the designed value. Also from this viewpoint, the height of the sub-blade 40A is preferable to be as short as possible, it being preferable to be within 70% of the height of the stator blade 7. A strong vortex flow 110 is, as shown in Fig. 11, generated at the end and the root portion of the inlet-side sub-blade 40A, i.e. at the downstream end thereof. Energy of the vortex flow is converted into heat energy to cause energy loss. The vortex flow discharged from the downstream end of the root portion, in particular, disturbes the flow in the diffuser 5, causing large loss. The rectifier blades 40B provided downstream of the inlet sub-blades 40A serve to suppress generation of the vortex flow at the root portions of the inlet sub-blades 40A, thereby serving to reduce the loss. Since the rectifier blade 40B is provided for the purpose of preventing generation of vortex flow, the height of the same may be arranged to be shorter than that of the inlet sub-blade 40A. The flow near the outer peripheral between the stator blades 7 is, in general, directed not along nearer the stator blade 7, but along nearer the circumferential direction. Therefore, the outlet-side intermediate blades 40C are provided to guide the flow along the stator blades 7 so that the performance of the diffuser is improved. The height of the outlet-side intermediate blade 40C is preferably in the order of 50% of that of the stator blade 7. On the viewpoint of securing rigidity, it is preferable to be within 70%. As shown in Fig. 12 the rectifier blades 40B are provided not only at a first side or face supporting the blade arrangement 40 but also at a second side or face which confronts the first side. In this case, vortex flows generated at downstream end of the inlet sub-blade 40A as well as at the root of the same can be prevented from generation. Therefore, a further improvement in performance can be achieved. As shown in Fig. 13 the blade arrangement 40 is provided at each of the stator blades 7 in a confronting manner. The height of the blade arrangement 40 is half of that of the blade arrangements 40 shown in Figs. 10 and 12. Compared with Fig. 10 the structure of the embodiment shown in Fig. 14 is simplified, by omitting the outlet-side intermediate blade 40C. In this case, although slight decrease in performance cannot be avoided, the cost of the diffuser can be reduced. According to the structure shown in Fig. 15 the rectifier blade 40B and the outlet intermediate blade 40C are omitted, i.e. there is the inlet-side sub-blade 40A only.

Claims: A diffuser of a centrifugal compressor for converting kinetic energy of fluid discharged from the impeller (1) of the compressor with supersonic velocity into pressure energy by means of a plurality of stator blades (7a, 7b) and sub-blades (8, 40A) at the inlet portion of the diffuser, wherein the sub-blades (8, 40A) are disposed between the stator blades (7a, 7b) and near to the inner ends thereof, only one side surface of the sub-blades (8, 40A) faces the stator blades (7a, 7b), and the sub-blades (8, 40A) are situated at positions intersecting a circle (10), the center of which corresponds to the center of the impeller (1) and which passes through the inner ends of the stator blades (7a, 7b). characterized in that the chord length of the sub-blades (8, 40A) is considerably shorter than the corresponding chord of the fixed stator blades (7), and the leading edge of each sub-blade (8) is situated downstream of a line drawn from the leading edge of the respective facing stator blade (7a) perpendiculary to this stator blade (7a). A diffuser according to claim 1, wherein each sub-blade (8, 40A) is disposed at a position not intersecting a perpendicular line (11) which is drawn to one of said stator blades (7a) at the inner end of said one stator blade (7b) which confronts said sub-blade (8, 40A). A diffuser according to claim 1 or 2, wherein said sub-blade (8) is rotatably supported by a supporting shaft (29) which is disposed in parallel to the rotational shaft (2) of said impeller (1). A diffuser according to one of the claims 1 to 3, wherein the distance between the inner end of said sub-blade (8) and said stator blade (7a) confronting said sub-blade (8) and the distance between the outer end of said sub-blade (8) and said stator blade (7b) is arranged to be different. A diffuser according to one of the claims 1 to 4, characterized by intermediate blades (9, 40C) which are disposed near the outer ends of and between said plurality of stator blades (7, 7a, 7b) the length of chord of which is shorter than that of said stator blade (7, 7a, 7b) each of which extends through the middle point of a perpendicular line (12) drawn from an outer edge of said stator blade (7a) to said neighbouring stator blade (7b) or to an extension of said neighbouring stator blade (7b) the outer edge of which reaches a circle (13) which passes through an outer edge of said stator blade (7, 7a, 7b) the length of each intermediate blade (9, 40C) disposed inside said middle point of said perpendicular line (12) being within 20% of the overall length of said intermediate blade (9, 40C), and the whole shape of each intermediate blade (9, 40C) being formed in such a manner that if said intermediate blade (9, 40C) is assumed to be rotationally displaced around the center of a rotational shaft (2) of said impeller (1), said intermediate blade (9, 40C) is included in a contour of said stator blade (7, 7a, 7b). A diffuser according to claim 5, wherein said intermediate blade (9) is rotatably supported by a supporting shaft (31) which is disposed in parallel to said rotational shaft (2) of said impeller (1). A diffuser according to claim 5 or 6, wherein the distance between the inner end of said intermediate blade (9) and said stator blade (7a) confronting said intermediate blade (9) and the distance (30) between the outer end of said intermediate blade (9) and said stator blade (7b) is arranged to be different. A diffuser according to claim 1 and 5 including or not including one of the claims 2 to 4 or 6 or 7 characterized in that the inlet-side sub-blade (40A) has a height that is smaller than that of said stator blade (7). A diffuser according to claim 8, wherein a rectifier blade (40B) is disposed downstream of said inlet-side sub-blade (40A) and has a height which is shorter than that of said inlet-side sub-blade (40A). A diffuser of a centrifugal compressor according to claim 8 or 9 in that the outlet-side intermediate blade (40C) provided downstream of said rectifier blade (40B) has a height corresponding or similar to that of the inlet-side sub-blade (40A). A diffuser of a centrifugal compressor according to one of the claims 8 to 10, wherein the arrangements (40), each consisting of an inlet-side sub-blade (40A), a rectifier blade (40B) and an outlet-side intermediate blade (40C), are provided in a confronting manner with each other in said diffuser portion.

Inventors: ABE, YOSHIAKI, NAKAGAWA, KOJI, SAKAI, HARUKI, TAKAGI, TAKEO
Applicants: HITACHI, LTD.
Application year: 1988
Main classification: F04D29
IPC codes: F04D29