Compressor housing (versions) and compressor impeller blade

FIELD: mechanical engineering; compressors of gas-turbine engines.

SUBSTANCE: proposed housing of compressor includes axially convex inner surface located around row of impeller blades with radial clearance between surface and blades. Edges at tip of blades add to housing contour, thus reducing losses on ends at blade tips and blocking of flow.

EFFECT: improved reliability in operation.

23 cl, 6 dwg

The present invention generally relates to gas turbine engines, and more particularly to compressors.

Turbofan gas turbine engine includes a fan, which, in turn, should multistage axial compressor, each of these nodes includes a number of spaced around the circumference at intervals relative to each other of the blades of the impeller, which in a typical case work together with the blades of the stator. The impeller blades work with such speeds where there may be air in the range from subsonic to supersonic, which is accompanied by the corresponding shock wave. Under the influence of a shock wave losses pressure and decrease efficiency.

The blades of the fan are the largest of the compressor blades, and their outer radial edges are under the influence of the high relative velocities and are influenced by strong shock waves in the aisles and on the front edge.

The impeller blades surrounds the fixed housing, the inner surface facing radially inward, defines a casing forming a small radial clearance on edges or gap with the blades of the impeller during operation. The compression or pumping in the air flow between the passages for the flow, located between adjacent blades, creates a pressure differential between opposite one relative to the other sides of the suction and discharge of each blade. Under the influence of this pressure differential is a partial flow of compressed air through the gap at the edges of the blades, resulting in reduced efficiency during injection.

In addition, the air flow passing over the edges of the blades, twisted, forming a vortex in the vicinity of the casing body, which leads to considerable losses in efficiency and causes drag a thread lock.

The throughput speed of the impeller of the compressor flow during injection is the ability to provide maximum air flow between adjacent blades. The injection should be carried out with maximum efficiency when there are sufficient with regard to the possibility of loss of speed or throttling. Leakage profile on the edges of the blades cause aerodynamic thread locking in those outer parts of passages for the flow, which are located between adjacent edges, resulting in lower throughput and efficiency during injection.

The presence of shock waves at the edges of the blades exacerbates this problem. With the passage formed at edges of the vortex through the shock wave is the rapid diffusion of air with spots the existing pressure loss and increased aerodynamic thread block.

From SU # 1109065 known compressor casing containing convex in the axial direction of the inner surface located around the number of blades of the impeller with a radial clearance between it and the shoulder blades.

The present invention is the creation of better housing of the compressor in combination with the mating with him by the edges of the blades in order to reduce deterioration of operating characteristics associated with vortex formation at edges and thread lock to improve efficiency at discharge and increase stock on the throttle.

The problem is solved in that a compressor housing having an inner surface, along the axis to cover the number of blades of the impeller from the front to the rear edges of the radial clearance between the tops of the blades and the inner surface and the inner surface includes a convex along the axis of the rear portion to cover the tops of the blades on the rear edges, the front portion of larger diameter located downstream referred to the back, to cover the tops of the blades on the front edges and the front section tapering towards the rear along the axis of the part to cover the openings of the passages between the vanes, and each of the openings passes axis from the side of the compression on the front edge of one of the blades essentially perpendicularly corresponding to the area on the side of the rarefaction of the next adjacent blade, located behind its leading edge.

The inner surface is made along the axis of the convex and tapers for both in front and in back. Housing according to the invention may further comprise a diverging inlet portion coaxially connected with the front part, while the inlet part can be made concave along an axis. In case the number of blades located therein coaxially aligned with him-axis, and the tops of the blades is made to complement the front and rear of the hull to create essentially a uniform gap between them. Moreover, the inner surface further includes an intermediate part located between the front and rear portions and converging between them. Intermediate shell converges to a greater extent than the front and back. The rear part of the case is made along the axis of the arc. The intermediate part of the housing and the front part of the housing can be made along the axis of the straight, and the front part of the case can be made along the axis of the arc. In another aspect of the invention, the front part of the body in its front part is made along the axis of a straight line and in its rear part is made along the axis of the concave, the front part of the body is concave along the axis of the intermediate part of the body is tapered, and the rear part of the case is made of vdol the axis is convex. Moreover, the housing can further comprise an inlet portion, coaxially connected with the front part of the hull extending radially outward ledge. The number of blades located therein coaxially aligned along the axis of the housing, and the top of the blades is made to complement the rear, intermediate and front to create essentially a uniform gap between them. The number of blades located therein coaxially may be aligned along the axis of the housing, and the top of the blades is made to complement the rear, intermediate and front to create essentially a uniform gap between them, and the blades further include an external radius tops, which are made to complement the body to create essentially a uniform gap between them.

The problem is solved also by the fact that the compressor housing has an internal surface, passing along the axis to cover the number of blades of the impeller between their front and rear edges with the appropriate clearances along the radius between the body and the tops of the blades and the inner surface includes a front portion, the diameter of which is larger than the diameter of the rear part, the rear part being convex along the axis, and the front part converges along an axis to cover the openings of passages passing essentially perpendicularly between adjacent blades on their front edges. Inside the I surface further comprises an intermediate part, located between the front and rear portions and converging between them. The front part of the body is concave along the axis of the intermediate part is made conical, and the rear part of the body is convex along the axis.

To resolve the above problems are also created vane of the impeller of the compressor, designed for installation in a radial direction from an outer side relative to the disk impeller inside covering this drive enclosure and containing the discharge side and suction-held with overlapping space from the tail to the top of the blade and along the chord between the front and rear edges and having a twisting between them, with the top of the blades are made concave on the inside radius section from front to rear its edges, at least in its rear along the axis of the back edge to create essentially a uniform gap with convex along the axis of the inner surface of the housing, and the top of the blades converge along the axis from the leading edge to the mouth of the passage with the adjacent blade passing essentially perpendicular to the suction side of the blades on the front edge of the adjacent blade. When this blade further comprises along the axis of the front and intermediate parts, distinguished by its path from its rear, which are located between the front and rear CR what mkami, to complement appropriate along the axis of the front, intermediate and rear part of the inner surface of the shell and in which an intermediate portion of the top of the vanes converging radially inward between the front and rear parts. The contour of the top of the blade changes from convex in the axial direction of the front portion, a tapered intermediate portion and concave in the axial direction of the rear part, to complement the concave in the axial direction of the front part of the housing, a conical intermediate part of the housing and convex in the axial direction of the rear part of the body.

The compressor casing according to the invention, as described above, includes convex in the axial direction of the inner surface located around the number of blades of the impeller with radial clearance between it and the blades. Edges of the blades complement the contour of body, providing a reduction of losses at the edges of the blades and reducing the thread lock.

The present invention is explained by examples of preferred variants of its implementation, together with other objectives and advantages of the present invention, discussed more specifically in the following detailed description, which is conducted with reference to the accompanying drawings, on which:

Figure 1 is represented in side view in axial vertical projection of the number of Lopato the fan, inside the housing is made in accordance with one of the exemplary embodiments of the present invention.

Figure 2 is presented in the form of front radial projection part of the fan and the case depicted in figure 1, is built along the line 2-2.

Figure 3 is represented in top view end-to-end picture of the fan blades, is depicted in figure 2, is built along the line 3-3.

Figure 4 is represented in an enlarged scale an axial side view of the three located on a circle, one after the other of the adjacent fan blades on their edges inside the circle marked with the numeral 4 in the figure 1.

Figure 5 is represented in an enlarged scale an axial side view of the edge of the blade and paired with her body, made in accordance with another embodiment of the present invention.

Figure 6 is represented in side view in axial vertical projection of the number of compressor blades, following the close of the blades of the stator in accordance with another embodiment of the present invention.

The figure 1 shows a portion of the fan 10 turbofan gas turbine engine. The fan 10 assymmetrical relative to the axial center line axis 12.

The fan includes a number of spaced around the circumference at intervals relative to each other profiles 14 is the form of blades of the impeller, shown in figures 1-3. As initially shown in figure 3, each of the profiles 14 comprises in General a concave pressure side 16 and located opposite to her in the circumferential direction in General, the convex suction side 18 passing in the longitudinal or radial direction with overlapping the transverse or radial section located radially inside of the tail 20 and located at a radius outside edge 22.

As shown in figure 1, each profile 14 passes radially outward along the radial axis 24 about which can be determined by changing the radial or cross-sectional profile. In addition, each profile is located at a distance from one another in the axial direction or along the chord of the front and rear edges 26, 28 between which in the axial direction are held on the pressure side and suction.

As shown in figure 3, each radial or cross-section profile has a regular straight chord between the front and rear edges, and passing between them curved in an arc line. Profile curled from the tail to the edge to ensure interoperability with the air 30 passing over it during operation. Chord sections vary along the twisting angle And from the tail to the edge as usual.

The path of the air stream flowing between the profiles, ogranichivaetsya on the outside radius of the annular body 32 of the fan or compressor, and along the radius from the inside - made in one piece pads 34 of each blade, which are tails 20. Conventional dovetail 36 securely connects each blade disk 38 of the impeller, having a reciprocal axial grooves under dovetail to hold the blades on it in the radial direction.

As shown in figure 1, the blades 14 of the fan depicted within the approximate annular body 32. The size and configuration of the blades in a typical case, are defined in such a way as to achieve the desired high throughput flow during injection of a fan, which is expressed in units of mass per second. The fan initially designed to obtain maximum efficiency of compression with an acceptable amount of loss rate (zapuganie) or choking.

The size and configuration of the edges of the blades in a typical case are chosen in such a way as to provide essentially uniform gap, or gap, between the edges and the housing 32, which allows to minimize leakage of air flow through the gap during operation at preventing or reducing unwanted touching the edges of the body. Conventional housing (not shown) is straight in the axial direction or with a cylindrical inner surface, facing toward the edges of the blades, or the conical converging or diverging surface, addressed to the edges.

Due to considerable twisting of the blades is typical for the first stage of fan blades, the edges of the blades are partially circumferentially about the inner surface of the shell and must be bent radially outward to provide the desired uniform gap between the edges and the inside cylindrical or conical body.

The configuration of the adjacent blades in a typical case is developed based on the provision of the passage 40 for flow having a converging-diverging shape in the vicinity of the edges of the blades, as shown in figure 3, so that the deceleration of the flow in the area between the front and rear edges. The internal form of the passage for flow up to tails blades made only divergent. Diffusion occurs in the passage to flow with increasing static pressure with decreasing speed. The vortex at the edge acts as a lock, limiting the increase in static pressure.

Because the blades of the fan having a relatively large size, can test the effect of the flow with high Mach number on their edges, whirlwind 30v at the edge, as shown schematically in figures 3 and 4, can interact with the shock waves. Supersonic flow at edges l is patok can create an oblique shock wave, emitted by the front edges of the blades, and a normal shock wave occurs in the passage between adjacent blades. As indicated above, the pressure loss caused by the vortices at the edges, contribute to further strengthening these effects of the shock wave in the area at the edges, resulting in lower throughput for discharge and deterioration of the efficiency of compression.

In accordance with the present invention, the housing 32 of the fan, shown in figure 1, has a tailored contour of its inner radial surface defining a stationary casing that at least partially made convex in the axial direction, being located around a series of blades 14 of the impeller, is placed coaxially inside the casing, and the edges 22 of the blades complement the contour of the housing, providing essentially uniform gap between the edges and the casing.

As shown in an enlarged scale in the figure. 4, the inner surface of the housing 32, passing in the axial direction, comprises a blade 14 from the front to the rear edges 26, 28 and executed in the axial direction convex at least in its rear portion 32A, covering the edges at the vertex of the blades at their rear edges 28. Since the edges 22 at the top of the blades complement the axial contour of the housing, each such edge is opacki includes a rear portion 22A, which is made concave in the radial direction inside at least in the rear axial portion from the rear edge 28 towards the front edge 26. Thus, facing each other in the radial direction of the rear edges 22 of the blades and the inner surface of the casing complement each other, with the first made concave in the radial direction inside, and the last executed on the radius of the convex inward in the axial direction so as to ensure a uniform gap between them.

The axial contour of the inner surface of the housing, shown in figure 4, represents only one component of a complex three-dimensional (3-D) configuration of the respective passages 40 to flow between adjacent with each other in the circumferential direction of the blades 14. The radial configuration of the blades in cross section from the front to the rear edge is usually determined from the condition of maximum throughput flow during injection and the highest level of efficiency in compression with acceptable margin on spontaneous shutdown. Each passage 40 for a thread includes a conventional inlet zone 40A, as shown in figures 3 and 4. This inlet zone passes from the discharge side of the leading edge of one blade to the suction side just behind the leading edge of the next next adjacent Lopatkin represents a zone which covers a first closed compression wave of rarefaction during operation.

Directly behind the inlet zone 40A is neck 40b passage, which runs from the discharge side of the leading edge of one blade is essentially perpendicular to the corresponding part on the suction side of the next next adjacent vanes behind the leading edge and the inlet zone. The passage for air is made converging from his neck to a narrowing of the 40s, with a minimum flow section and respectively located essentially at the rear region of the mid-chord of the blades, from which the passage for the thread made divergent in the direction towards the outlet portion 40d having a larger flow section, and this narrowing is limited to the area between the suction side near the trailing edge of one blade is essentially perpendicular to the discharge side next next adjacent vanes ahead of its rear edge.

Due to the converging-diverging contour of each passage 40 for the flow is provided by the slow movement of the air stream, which in turn helps increase the air pressure, because the diffusion in the axial direction as the air moves between the fan blades.

The importance of such prepact the positive path, proposed housing 32 may be further appreciated by consideration of figure 5, in which the contours of the body and its complementary blades of the fan are presented in an even more enlarged scale. The dashed line drawn inside the housing 32, shown his usual conical configuration, which combines work with straight tapered edge at the top of the blade shown in phantom line in the form of an axial profile that is characteristic of normal blades of the fan. By performing the rear portion 32A of the inner surface of the housing so that it had in the axial direction of the convex shape in the front, when viewed in the flow direction, the rear edges of the blades may be derived from a local decrease of diffusion into the vortex that is created during the operation of the edge at the top of the scapula.

Reducing diffusion in a whirlwind at the edge, respectively, contributes to the reduction caused by this phenomenon of pressure loss and the concomitant weakening of the wind blocking flow, resulting in increase as bandwidth stream for discharge, and the efficiency of the compression within the relevant limitations associated with specific dimensional characteristics of the fan. The outer diameter of the fan blades at their front and rear edges, and corresponding to them nutrena diameters specified opposite edges of the housing parts can remain exactly the same by its size, as in conventional constructions, but it ensures carried out with the aim of improving the corresponding change in the contour of the inner surface in the axial direction between the specified edges in order to achieve local improvements aerodynamic characteristics.

Convex rear portion 32A of the inner surface of the case can be made a variety of means, including continuously curved or composed of separate conical sections, depending on what is desirable. Further, the rear part of the housing may have a corresponding contour, providing the transition back to a given inner diameter, but with the outer side relative to the edges of the blades.

More specifically, as shown in figures 4 and 5, the inner surface of the housing includes, in addition, also the front portion 32b located in the axial direction in the front, when viewed in the flow direction, relative to the rear portion 32A and covering the edge at the top of the blades at their front edges. The front part 32b of the body has a larger diameter along the axis passing through the center line than the rear portion 32A, and thus, the body is made converging on the area between the two parts.

For example, the inner surface of the housing preferably includes the t also in its composition and the intermediate portion 32C, located in the axial direction in the area between the front and rear parts, respectively, 32b and 32A, which is made converging on the specified area in the rear.

Supplementing the considered contour edge 22 at the top of the blades include a front axial portion 22b and the intermediate, or located in the middle of the chord, part 22s, which are parallel to the corresponding parts of the body. The relevant part of the edge at the top of the blades have a circuit that accurately follows the contour of the corresponding part of the inner surface, the housing covering the blade, in the area between the front and rear edges of the blades, due to what is maintained essentially uniform radial clearance between the edges and the inner surface of the housing. Since the intermediate portion 32C of the case is made converging in the flow direction, and an intermediate portion 22p of the edges at the vertex of the blades are also made converging or inclined inward along the profile in the axial direction in the area between the front and rear parts.

The inner surface of the housing 32 preferably performed so that the circuit it produces improved distribution of static pressure in the axial direction, resulting in a local reduction of the diffusion of the vortex, created at the edge, at the top of the blades, as well as improved aerodynamic characteristics. Additionally, the local reduction of diffusion also contributes to the weakening of the normal shock wave for supersonic applications that, in turn, allows to reduce the degree of diffusion in a whirlwind cross this shock wave. Since the vortex generated at the edge at the top of the blades, are exposed to less sharp gradient of increasing the static pressure behind the shock wave, this tends to further reduce the pressure loss, as well as to decrease or prevent migration of the vortex in the direction of the discharge side of the neighboring blade.

Reduction in force the normal shock wave, and also smaller pressure loss in the whirlwind and the attenuation of blocking flow occurring due to the formation of vortex - all this contributes to the efficiency of the impeller of the compressor with the capacity increase during injection and expansion of the throttling range. In one of the structures is investigated using the method of dimensional analysis, viscous flow at transonic regime of rotation of the impeller at high unit value stream enclosure with circuit made in accordance with the example of the embodiment nastojasih the invention, showed the results indicate a significant increase in the total air flow and the corresponding higher is the efficiency of the impeller at the same speed as when using comparable conical housing of conventional design.

In the example embodiment of the present invention, is shown in figure 4, the forward portion 32b of the housing, located on top of the front edges of the blades has a greater outer diameter when measuring its axis passing through the center line of the fan than the rear portion 32A of the housing, located on top of the rear edges of the blades. The contour of the inner surface of the housing preferably is selected from the conditions ensuring local unfolding of the inlet zone and narrow passages for the flow, while the output or outlet area of the passages for the flow remains the same for this application. It also helps to reduce the effective bending at high speeds of rotation of the fan, providing the increase of the total air flow with a corresponding increase in the efficiency of compression.

Since the outer diameters of the front edges of blades and at their rear edges preferably are selected each time separately for each particular design of the fan, as well as applying a more perfect con is ur front and rear housing parts, accordingly 32b and 32A, preferably it would also, to the intermediate portion 32C of the body was made with a more abrupt transition at its convergence than its front and rear parts, respectively, 32b and 32A, thereby obtaining aerodynamic transition between different local impacts arising in the areas of the front and rear edges of the blades.

As described above, the rear portion 32A of the housing, located on top of the rear edges of the blades, in the preferred embodiment of the present invention is made arcuate convex in the axial direction. In alternative embodiments, the implementation of the present invention convex contour of the rear portion of the chassis may be formed of sequentially arranged in the axial direction of the straight sections, for example, such as may be one or more conical sections, which are located over the area of the rear edges of the blades.

The intermediate portion 32C of the housing preferably is straight in the axial direction in the form of a conical section, with the angle or half-angle of taper which is substantially greater than the corresponding angles of the front and rear parts, respectively, 32b and 32A. Thus, the front and rear part have limited tilt, or convergence and bases of the second share of the slope and convergence have on the intermediate portion 32C of the housing, the relevant section from the middle of the chord to the rear edge at the top of the shoulder blades, around which is located the specified intermediate part.

The front part 32b of the housing preferably is straight in the axial direction where it starts on top of the front edges of the blades, or having an essentially constant radius or inner diameter, or with a slight toe-in and forming a conical section. In addition, the front part of the casing 32b preferably performed with the transition to curved in the axial direction form in connection with its intermediate part 32C of the housing. Thus, the forward portion 32b of the housing is straight in the axial direction within the front of the site, located on top of the front edges of the blades, and preferably is convex within the back of their area in connection with its preferred running straight conical intermediate part 32C. Next is the rear portion 32A of the housing, which, in turn, is convex in the axial direction of the contour, finishing a combined circuit, which has in the axial direction of the entire body as a whole, covering an edge at the top of the blades throughout these edges, starting from the front to the rear edges of the blades.

As indicated above, the axial is Ontur edges 22 at the top of the blades, because they are extended radially outward toward the inner surface of housing 32, complements the contour of the respective parts. Accordingly, the front portion 22b of edges at the vertex of the blades is made with the transition in the side view in the axial direction from straight in shape to convex in the axial direction so as to adjoin to complement their axial contour of the front portion 32b of the body, which is made with the transition from straight to convex in the axial direction. The intermediate portion 22p of edges at the vertex of the blades is made conical in the axial direction in order to complement the taper in the axial direction intermediate portion 32C of the housing. And finally, the rear portion 22A of edges at the vertex of the blades are made concave in the axial direction in order to complement the convex in the axial direction of the rear portion 32A of the housing.

Thus, the axial contour of the inner surface of housing 32 where it covers the edges at the vertex of the blades throughout these edges from the front to the rear edges of the blades varies with the purpose of ensuring a favourable distribution of static pressure in the axial direction in order to reduce the diffusion of the vortices generated at the edges at the top of the blades, as well as to reduce the normal shock wave during operation at supersonic mode, in which opalanie to those benefits, which were previously considered herein above the description.

As shown in figure 1, the inner surface of the housing 32 additionally includes an annular inlet portion 32d that are ahead, when viewed in the flow direction relative to the front portion 32b on the outer side relative to the front edges 26 of the blades. The inlet portion 32d may be made cylindrical, conically diverging or conically converging and is located coaxially to other parts of the body, providing them air flow 30. In figure 4, the inlet portion 32d shown in the preferred radiating in the axial direction design with a smooth pairing it with the front part 32b of the casing that allows you to maximize the flow area in the inlet zone 40A.

In the embodiment of the present invention, is shown in figure 5, the inlet portion 32b has a reduced inner diameter and connected with the front part 32b of the housing, being located coaxially with it, and at the junction of these two parts to each other has the rim in the radial direction to the outside ledge 42, through which the inner surface of the housing, covering the edges at the vertex of the blades located in the annular recess limiting the casing, comprising a flange at the top of the blades. To Lavoe recess, defining a casing that has a typical form, but in the preferred implementation, this can be the inner surface of the axial contour, which is performed in accordance with the present invention, which allows to improve the operating characteristics of the fan.

Shown in figures 1-5 variant implementation of the present invention is characteristic for relatively long blades of the fan, the outer part of which increases the air pressure of the air leaving turbofan engine and creates momentum. However, the present invention can be used also in other types of profiles of compressor blades, for example, that what is presented in schematic form in figure 6 in the form of vanes 14B axial compressor.

Shoulder 14C of the compressor extends radially outwards relative to the reference disk or drum, 38A, and there are one or more impellers axial type and the corresponding speed stator located in the compressor in the usual way. Ahead of a number of compressor blades, when viewed in the flow direction, there is a corresponding series of blades 44 of the stator, which direct the air stream 30 to the compressor blades.

The air flow is directed in the axial direction from the shoulder blade to shoulder blade after a few students who Eney when restricting flow in the radial direction from the outer and the inner side of the respective restraining walls, defining a path of flow. The case is an external such wall, and the drum inner wall, between which are having the appropriate profile blade speed stator and compressor. Stator vanes are separated from the inner wall to ensure proper radial clearance between the vanes and the wall, similar in use to the radial gap at the edges at the top of the compressor blades, namely to allow relative rotational movement.

In this embodiment of the present invention the inner surface of the housing includes adjacent to each other in the front and rear parts, respectively 32A and 32b covering blades 14B of the compressor. The entire inner surface of the housing as a whole is made convex in the axial direction in the present embodiment of the present invention, and made it again to ensure that local reduction of diffusion in the vortices generated at the edges at the top of the blades, and thereby increase the throughput of air flow during injection due to the weakening effect of blocking the flow and reduce pressure loss.

In this embodiment of the present invention the annular inlet portion 32d of the housing is connected with secured and alignment between the front part 32b, located ahead on it, when viewed in the flow direction, and preferably is converging in the flow direction, with either tapered section or convex in axial cross-section, as shown in the example of the preferred alternative implementation of the present invention.

Edges at the vertex of the blades 14 In the compressor have an outline, a complementary and combined with the convex axial contour of the inner surface of the housing in order to ensure the availability of essentially uniform radial clearance between the vanes and the surface. Accordingly, adjacent one to the other of the front and rear parts 22A and 22b of edges at the vertex of the blades are concave in the axial direction in order to complement and harmonize with the axial convex contour covering the inner surface of the housing.

The operating characteristic of the compressor can be improved additionally by performing in the housing spaced around the circumference of the slots or grooves. In common practice ordinary circumstances, these grooves can increase stock to throttling of the impeller, but it usually leads to a concomitant decrease in the efficiency of the impeller.

However, such grooves in combination with the convex contour of the housing, discussed in the above, C is the return above description, to get additional advantage that otherwise get, it would be impossible. For example, in figure 4 is shown located around the circumference of the single groove 46, is made in the front part 32 of the housing that faces its open side edges 22 at the top of the blades, located on the inner side relative to the grove beyond. This groove is made in the case, and a convex outline, complementing a each other, provide the maximum improvement of the working characteristics and stability of operation.

Available in the housing groove has such an impact on workflow, which improves its stability, and also allows you to apply more steep convex contour in the design, which otherwise apply would be impossible. Discontinuities arising from the presence of the grooves 46, allows to achieve a maximum flow area at the inlet zone and the area of narrowing and at the same time to increase the curvature of the convex portion 32A of the housing located at the specified zones in the direction of flow. In the absence of such grooves path of flow through the housing could have otherwise in its place a more concave curvature that could lead to a deterioration of the working characteristics and resistance R of the press.

The corresponding deterioration of the operating characteristics commonly associated with the presence in the body of the grooves, can be avoided by applying a smaller number of grooves, and preferably only a single groove, and by providing a more favorable distribution of the static pressure near the edges at the vertex of the blades when the application of the proposed contour of the hull.

In embodiments implementing the present invention discussed herein above the description, can be obtained increasing the capacity for discharge and increase efficiency As in the embodiment of the present invention, is presented in figure 6, there is only convex in the axial direction of the inner surface of the housing, this option allows for all the advantages discussed herein above description with reference to the first embodiment of implementation of the present invention.

However, various embodiments of the present invention discussed herein above the description of allow with minimal changes in the geometry of the hull and the edge at the top of the blades to achieve a noticeable improvement in the performance of compressor blades and fan without any other changes in the overall size of the speed of the fan or compress the ora. Given the technical conditions for the design of the application having the above circuit blocks and consistently complement the contour of the edges at the vertex of the blades allows a significant improvement in operating characteristics, which otherwise would have been impossible to obtain. These new signs can be used to embed them into existing structures in cases where feasible, thus providing a corresponding improvement in the operating characteristics of the fan and compressor running either subsonic or supersonic mode.

In here, from the above description considered were those embodiments of the present invention, which are considered to be preferred and exemplary, but experts in the art should be obvious that on the basis of the guidelines of the invention can be designed and also other modifications of the present invention, and it is therefore desirable to determine various such modifications which do not go beyond the actual limits of the essence and scope of the invention, the attached claims.

1. A compressor housing having an inner surface, along the axis to cover the number of blades of the impeller from the front to the rear edges of the radial gap is m between the tops of the blades and the inner surface, moreover, the inner surface includes a convex along the axis of the rear portion to cover the tops of the blades on the rear edges, the front portion of larger diameter located downstream referred to the back, to cover the tops of the blades on the front edges and the front section tapering towards the rear along the axis of the part to cover the openings of the passages between the vanes, and each of the openings passes through the axis from the side of the compression on the front edge of one of the blades, which essentially perpendicular to the corresponding area on the side of the rarefaction of the next adjacent blade located behind the front edge.

2. The housing according to claim 1, in which the inner surface is made along the axis of the convex and tapers over at the front, at the rear.

3. The housing according to claim 2, additionally containing a divergent inlet portion coaxially connected with the front part.

4. The housing according to claim 3, in which the inlet part is concave along an axis.

5. The housing according to claim 2, in which the number of blades located therein coaxially aligned with him-axis and the top of the blades is made to complement the front and rear of the hull to create, essentially, a uniform gap between them.

6. Housing of claim 1, wherein the inner surface further includes an intermediate part located between the front and rear portions and converging IU who do them.

7. The housing according to claim 6, in which the intermediate part of the housing converges to a greater extent than the front and the rear.

8. The housing according to claim 7, in which the rear part of the case is made along the axis of the arc.

9. The housing according to claim 7, in which the intermediate part of the body is along the axis line.

10. The housing according to claim 7, in which the front part of the case is made along the axis line.

11. The housing according to claim 7, in which the front part of the case is made along the axis of the arc.

12. The housing according to claim 7, in which the front part of the body in its front part is made along the axis of the straight line and its rear part is made along the axis of the concave.

13. The housing according to claim 7, in which the front part of the body is concave along the axis of the intermediate part of the body is tapered, and the rear part of the case is made along the axis of the convex.

14. The case indicated in paragraph 13 additionally containing an inlet portion, coaxially connected with the front part of the hull extending radially outward ledge.

15. The case indicated in paragraph 13, in which the number of blades located therein coaxially aligned along the axis of the housing and the top of the blades is made to complement the rear, intermediate and front-to create, essentially, a uniform gap between them.

16. The housing according to claim 7, in which the number of blades located therein coaxially aligned along the axis of the housing, and the tops of the blades are made updat the catch back, intermediate and front-to create, essentially, a uniform gap between them.

17. The housing according to claim 1, in which the number of blades located therein coaxially aligned along the axis of the housing, and vanes further include outer radius of the top, which is made complementary to the housing to create, essentially, a uniform gap between them.

18. The compressor housing containing the inner surface along the axis to cover the number of blades of the impeller between their front and rear edges with the appropriate clearances along the radius between the body and the tops of the blades and the inner surface includes a front portion, the diameter of which is larger than the diameter of the rear part, the rear part being convex along the axis, and the front part converges along the axis of the scope of the openings of passages passing essentially perpendicularly between adjacent blades on their front edges.

19. Corps p in which the inner surface further comprises an intermediate part located between the front and rear portions and converging between them.

20. Case in claim 19, in which the front part of the body is concave along the axis of the intermediate part is made conical, and the rear part of the body is convex along the axis.

21. The blade of the impeller of the compressor, designed for installation is it in the radial direction from the outer side relative to the disk impeller inside covering this drive enclosure and containing the discharge side and suction, passing with overlapping space from the tail to the top of the blade and along the chord between the front and rear edges and having a twisting between them, with the top of the blades are made concave on the inside radius section from front to rear its edges, at least in its rear along the axis of the back edge to create, essentially, a uniform gap with convex along the axis of the inner surface of the housing, and the top of the blades converge along the axis from the leading edge to the mouth of the passage with the adjacent blade passing essentially perpendicular to the suction side of the blades on the front edge of the adjacent the scapula.

22. The blade on item 21, further containing the axis of the front and intermediate parts, distinguished by its path from its rear, which are located between the front and rear edges to complement appropriate along the axis of the front, intermediate and rear part of the inner surface of the shell and in which an intermediate portion of the top of the vanes converging radially inward between the front and rear parts.

23. The blade on p.22, in which the contour of the top of the blade changes from convex in the axial direction of the front portion, a tapered intermediate portion and concave in the axial direction of the rear part to complement along the axis of the concave front of the chassis, conic the municipal intermediate shell and convex in the axial direction of the rear part of the body.