Axial compressor

Abstract

The axial compressor has a two-stage guide vane cascade at the discharge-side end of the rotor. The guide vanes of the second stage of the cascade are staggered in the circumferential direction in relation to the guide vanes of the first stage in such a way that vortex streamers created by the guide vanes of the first stage cannot impinge upon the guide vanes of the second stage.

Claims

1. An axial compressor, comprising: a rotor rotatably arranged in a casing, the rotor comprising: a plurality of rotor blade stages; a multistage guide vane cascade arranged in a stationary manner in the casing on a discharge side of a rotor-blade final stage of the rotor and which has axially arranged guide vane rows without axial overlapping; wherein the guide vanes of a preceding guide vane row are at a same arcuate distance to adjacent guide vanes in the circumferential direction of the casing, as guide vanes in an axially following guide vane row and the axially following guide vane row is arranged in each case in a circumferentially staggered manner in relation to the preceding guide vane row in such a way that vortex streamers, which are created by the guide vanes of the preceding row, flow through in each case between adjacent guide vanes of the following guide vane row, wherein an arcuate distance U′.sub.2 from the vortex streamers to a leading edge of a convexly curved side of one guide vane of the following guide vane row is smaller than an arcuate distance U″.sub.2 from the vortex streamers to a leading edge of a concavely curved side of an adjacent guide vane of the following guide vane row in the circumferential direction of the casing and the two distances (U′.sub.2, U″.sub.2) are related to each other according to an order of magnitude of approximately 1:1>U′.sub.2:U″.sub.2>1:2.

2. The axial compressor according to claim 1, wherein the casing is assembled from circumferentially adjoining shell sections, and an inner wall segment, which predetermines the spacing of the guide vanes in the circumferential direction, is arranged in each case between circumferentially adjacent guide vanes of the cascade, wherein on a parting plane between adjacent shell sections of the casing provision is made for a split inner wall segment, of which the parting plane between the segment sections coincides with the parting plane between the shell sections of the casing, wherein the segment sections of the axially series-arranged guide vane rows are dimensioned so that the two guide vane rows have a predetermined stagger in the circumferential direction.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) In the drawing

(2) FIG. 1 shows a schematized axial section of a conventional axial compressor with a discharge-side guide vane cascade which consists of so-called super guide vanes,

(3) FIG. 2 shows a schematized axial section of an axial compressor with a two-stage guide vane cascade arranged on the discharge side of the rotor,

(4) FIG. 3 shows a sectional drawing in detail of a conventional two-stage guide vane cascade, wherein all the vane profiles are shown in relation to a developed view of an inner wall of the compressor casing,

(5) FIG. 4 shows a view according to FIG. 3 of a guide vane cascade according to the invention,

(6) FIG. 5 shows a plan view of an inner wall section of the compressor casing, in a developed view, in the region of the discharge-side guide vane cascade.

DETAILED DESCRIPTION

(7) In FIG. 1, a conventional axial compressor is shown. This, in a known way, has a casing 1 with an inner wall 3 which is essentially rotationally symmetrical to a rotor axis 2. The casing 1 encloses a rotor 4 which is arranged axially between an inlet 5 for a flow medium which is to be compressed and an outlet 5′ which as a rule leads to a combustion chamber.

(8) Rotor blades 6, fixed to the rotor, specifically in rotor blade rows or rotor blade stages which extend in the circumferential direction of the rotor in each case, are arranged on the rotor 4 in a known manner. Stator blades 7, fixed to the casing, specifically in stator blade rows or stages which extend in the circumferential direction of the casing inner wall 3 in each case, are arranged in each case between axially adjacent rotor blade stages.

(9) Provided axially downstream of the rotor blade final stage of the rotor 4 is a single-stage guide vane arrangement or guide vane cascade 8 which comprises so-called super guide vanes 9. These super guide vanes have a distinctly curved profile and are arranged in such a way that they eliminate the intense swirl of the flow medium on the discharge side of the rotor 1 and create a largely axial flow of the medium.

(10) The axial compressor which is shown in FIG. 2 differs from the axial compressor of FIG. 1 essentially only in that the guide vane cascade 8 is a two-stage construction with “normal” guide vanes 10 and 11 which have a profile which is curved to a lesser degree in comparison.

(11) The type of construction of an axial compressor which is shown in FIG. 2 is basically known and is also provided in the case of the invention.

(12) FIGS. 3 and 4 show the differences of the invention compared with previous constructions. In FIG. 3, the relative positions of the guide vanes 10 and 11 of a two-stage conventional guide vane cascade are shown. In particular, it becomes apparent that the leading edges of the front guide vanes 10, in the flow direction, of the front guide vane stage have a distance U.sub.1 in the circumferential direction, whereas the guide vanes 11 of the following guide vane stage have a distance U.sub.2 in this direction which deviates therefrom. This inevitably leads to vortex streamers 13, which are created by the front guide vanes 10, at least partially directly impinging upon the leading edge of a guide vane 11 of the following guide vane stage. As a result, the efficiency of the guide vane cascade and correspondingly also the efficiency of the axial compressor are negatively affected, however.

(13) In the case of the invention, on the other hand, according to FIG. 4, the distances U.sub.1 and U.sub.2 have equal dimensions so that by a corresponding stagger of the guide vanes 11 of the following guide vane stage in the circumferential direction it can be ensured that the vortex streamers 13 pass between circumferentially adjacent guide vanes 11 in each case. The arrangement of the guide vanes 10 and 11 is preferably designed so that the vortex streamers 13 are guided in comparatively closer proximity past the convexly curved sides of the lower guide vanes 11 in the drawing in each case. In this case, the distances U′.sub.2 and U″.sub.2, as U′.sub.2:U″.sub.2,=1:2.

(14) As a result, the effect is therefore achieved of the vortex streamers 13 finding their way into the comparatively fast circumflow of the convex guide vane sides.

(15) In order to achieve the desired stagger in the circumferential direction between the guide vane stage formed by the guide vanes 10 and the guide vane stage formed by the guide vanes 11 during assembly of the axial compressor, a construction according to FIG. 5 is preferably provided.

(16) In a basically known manner, the compressor casing is assembled from shell sections which are placed against each other on a parting plane 14. On the inner side of these shell sections, the guide vanes 10 and 11 are installed in a conventional way, for example by the roots 15 and 16 of the guide vanes 10 and 11, by anchors formed upon them, being inserted in the circumferential direction into a channel which is formed in the inner side of the respective shell section. Arranged in each case between circumferentially adjacent roots 15 or 16 is an inner wall segment 17 or 18 which is dimensioned so that the arcuate dimensions U.sub.1 and U.sub.2 apparent from FIG. 4, which have the same values, exist between the leading edges of the guide vanes 10 and 11. Segmented wall segments, with the segment sections 17′ and 17″ or 18′ and 18″, are provided in each case in the region of the parting plane 14, wherein the respective segment sections 17′ and 17″ or 18′ and 18″ are positioned so that their parting plane coincides with the parting plane 14 of the casing shell sections. With corresponding dimensioning of the segment sections 17′ and 18′ and also 17″ and 18″, the desired stagger in the circumferential direction between the guide vanes 10 and 11 is ensured in this way.

(17) In FIGS. 1 to 5, one or more of the rotor-side rotor blades 6 of the final rotor blade stage are schematically also shown in profile in each case, wherein R refers to the rotational direction of the rotor 4.