Run-up surface for the guide-vane shroud plate and the rotor-blade base plate

Abstract

A guide vane segment 10 for a turbomachine includes a radially inner shroud plate 13 having a shroud plate surface 14 that is adapted to be configured in the turbomachine to face a rotor blade 20 adjacent to the guide vane segment, and thereby essentially extend along an outer conical surface K.sub.1 whose cone axis coincides with the axis of rotation A of a rotor shaft 30. In a radially inner region, a rotor blade 20 for a turbomachine has a base plate 23 having a base plate surface 24 that is adapted to be configured in the turbomachine to face a shroud of a guide vane row 10 adjacent to the rotor blade and thereby essentially extend along an outer conical surface K.sub.2 whose cone axis coincides with the axis of rotation A of a rotor shaft 30.

Claims

1. A guide vane segment for a turbomachine, the guide vane segment comprising: a radially inner shroud plate having an outwardly facing top surface, an inwardly facing bottom surface, and a conical chamfer connecting the top surface and the bottom surface, the conical chamfer forming an inwardly facing shroud plate surface that faces both a rotor shaft and a rotor blade adjacent to the guide vane segment, an imaginary extension of the conical chamfer extending along an outer conical surface with a cone axis coinciding with the rotor shaft at an axis of rotation of the rotor shaft.

2. The guide vane segment as recited in claim 1 wherein the outer conical surface is angled relative to the axis of the rotor shaft by at most 80.

3. The guide vane segment as recited in claim 2 wherein the outer conical surface is angled relative to the axis of the rotor shaft by at most 60.

4. The guide vane segment as recited in claim 3 wherein the outer conical surface is angled relative to the axis of the rotor shaft by at most 50.

5. A rotor blade for a turbomachine, the rotor blade comprising: a base plate in a radially inner region having a projection and an outwardly facing base plate surface, the projection and the outwardly facing base plate surface each adapted to be configured in the turbomachine to face away from a rotor shaft and to face a shroud of a guide vane row adjacent to the rotor blade, the outwardly facing base plate surface being conical in that an imaginary extension of the outwardly facing base plate surface extends along an outer conical surface with a cone axis coinciding with the rotor shaft at an axis of rotation of the rotor shaft.

6. The rotor blade as recited in claim 5 wherein the outer conical surface is angled relative to the axis of the rotor shaft by at most 80.

7. The rotor blade as recited in claim 6 wherein the outer conical surface is angled relative to the axis of the rotor shaft by at most 60.

8. The rotor blade as recited in claim 7 wherein the outer conical surface is angled relative to the axis of the rotor shaft by at most 50.

9. A subassembly for a turbomachine comprising: a guide vane segment for a turbomachine, the guide vane segment including a radially inner shroud plate having a shroud plate surface adapted to be configured in the turbomachine to face a rotor blade as recited in claim 5 adjacent to the guide vane segment and to extend along a guide vane segment outer conical surface with a guide vane segment cone axis coinciding with the axis of rotation of the rotor shaft.

10. The subassembly as recited in claim 9 wherein the guide vane outer conical surface extends along a shroud surface of the guide vane segment, and the outer conical surface extends along a base plate surface of the rotor blade, the guide vane outer conical surface and the outer conical surface having a similar cone angle.

11. A turbomachine comprising: a guide vane segment, the guide vane segment including a radially inner shroud plate having a shroud plate surface adapted to be configured in the turbomachine to face a rotor blade as recited in claim 6 adjacent to the guide vane segment and to extend along a guide vane segment outer conical surface with a guide vane segment cone axis coinciding with the axis of rotation of the rotor shaft.

12. The turbomachine as recited in claim 11 wherein the guide vane segment outer conical surface extends along a shroud surface of the guide vane segment, and the outer conical surface extends along a base plate surface of the rotor blade, the guide vane segment outer conical surface and the outer conical surface having a similar cone angle.

13. A turbomachine comprising: a rotor shaft; a rotor blade attached to the rotor shaft; and a guide vane segment, the guide vane segment comprising a radially inner shroud plate having an outwardly facing top surface, an inwardly facing bottom surface, and a conical chamfer connecting the top surface and the bottom surface, the conical chamfer forming an inwardly facing shroud plate surface that faces the rotor blade, an imaginary extension of the conical chamfer extending along an outer conical surface with a cone axis coinciding with the rotor shaft at an axis of rotation of the rotor shaft; and the rotor blade comprising a base plate in a radially inner region having a projection and an outwardly facing base plate surface, the projection and the outwardly facing base plate surface each adapted to be configured in the turbomachine to face away from the rotor shaft and to face a shroud of a guide vane row adjacent to the rotor blade, the outwardly facing base plate surface being conical in that an imaginary extension of the outwardly facing base plate surface extends along an outer conical surface with a cone axis coinciding with the rotor shaft at the axis of rotation of the rotor shaft.

14. The guide vane segment as recited in claim 13 wherein the outer conical surface is angled relative to the axis of the rotor shaft by at most 80.

15. The guide vane segment as recited in claim 14 wherein the outer conical surface is angled relative to the axis of the rotor shaft by at most 60.

16. The guide vane segment as recited in claim 15 wherein the outer conical surface is angled relative to the axis of the rotor shaft by at most 50.

Description

BRIEF DESCRIPTION OF THE DRAWING

(1) Preferred exemplary embodiments of the present invention will be described in greater detail in the following with reference to the drawing. It is understood that different combinations of individual elements and components are possible other than those explained. Reference numerals for corresponding elements are used throughout the figures and, as the case may be, are not newly specified for each figure.

(2) Schematically shown in:

(3) FIG. 1: is an exemplary guide vane segment according to the present invention in a perspective view;

(4) FIG. 2: is a configuration of an exemplary guide vane segment according to the present invention and of an exemplary rotor blade according to the present invention in a sectional view;

(5) FIG. 3: are portions of the configuration in accordance with FIG. 2, including imaginary conical surfaces for illustration purposes.

DETAILED DESCRIPTION OF AN EMBODIMENT

(6) FIG. 1 shows a guide vane segment 10 in accordance with a specific embodiment of the present invention. Guide vane segment 10 includes an outer shroud plate 12 and an inner shroud plate 13, which each delineate segments of shrouds that are disposed one inside the other and have the same central axis; configured between outer shroud plate 12 and inner shroud plate 13 are a plurality of airfoils 11. Together with other, analogously configured guide vane segments, guide vane segment 10 is adapted to form a guide vane row that extends as a ring about a rotary shaft, respectively machine axis of the turbomachine. The axis of rotation thereof thereby essentially coincides with a central axis of the guide vane row, and airfoils 11 essentially extend radially relative thereto.

(7) On the side thereof facing the central axis, radially inner shroud plate 13 features a fastening element 15 for fastening at least one seal that, in particular, may include at least one sealing ring.

(8) At the front axial side thereof in the representation of FIG. 1, shroud plate 13 has a shroud plate surface 14 that is adapted to be configured in the turbomachine to face a rotor blade that is axially adjacent to guide vane segment 10. Shroud surface 14 is thereby conically chamfered; thus, extends essentially along an (imaginary) outer conical surface about the central axis (and thus about the axis of rotation of the rotor shaft). This is clarified with reference to FIGS. 2 and 3.

(9) FIG. 2 schematically shows a configuration of an exemplary guide vane segment 10 according to the present invention and of an exemplary rotor blade 20 according to the present invention in a sectional view; this configuration may be present, for example, in a turbomachine according to the present invention, in particular in a turbine section of the same.

(10) Rotor blade 20 is coupled to a rotor shaft 30 and adapted to rotate therewith about axis of rotation A thereof. Moreover, this axis of rotation is a central axis of the illustrated configuration, relative to which rotor blades 20 and airfoils 11 of the guide vane segment are essentially radially oriented. Direction R of a designated primary flow is from left to right in the illustration of FIG. 2.

(11) Guide vane segment 10 features a radially inner shroud plate 13, a radially outer shroud plate 12, as well as an airfoil 11 therebetween. A sealing element 16 is mounted on radially inner shroud plate 13, preferably radially displaceably, notably by a spoke-centering suspension. This makes it possible to prevent stresses that result from different, thermally induced radial expansions between sealing element 16, on the one hand, and guide vane segment 10, respectively the guide vane row formed from a plurality of such guide vane segments 10, on the other hand, during operation of the turbomachine.

(12) In a radially inner region, rotor blade 20 has a base plate 23, from which a rotor blade airfoil 21 extends radially outwardly. At the side facing guide vane segment 10 (in the axial direction), the base plate has a projection 26, which, together with inner shroud plate 13 of the guide vane segment, reduces a disadvantageous radial flow.

(13) Inner shroud plate 13 of guide vane segment 10 features a shroud plate surface 14 that faces a base plate surface 24 of base plate 23 of rotor blade 20; both of the mentioned surfaces are essentially thereby configured at the same radial distance from rotor shaft 30. Viewed in designated primary flow direction R, base plate surface 24 is configured on a rear side of base plate 23, and shroud plate surface 14 on a front side of shroud plate 13. Thus, in the event of a breakage of the rotor shaft, base plate surface 24 is able to run up onto shroud plate surface 14, so that the rotor is advantageously braked.

(14) Shroud plate surface 14 and base plate surface 24 are each configured along (imaginary) outer conical surfaces; with reference to a parallel P to axis of rotation A, the magnified circular view shows that shroud plate surface 14 and base plate surface 24 are angled by angle or relative to axis of rotation A; preferably, or are each at most 80, preferably at most 60, more preferably at most 50. It is especially advantageous when and are essentially of equal value; this provides both surfaces with an especially large contact area in the case that they run up against each other; a considerable braking friction action resulting therefrom.

(15) FIG. 3 illustrates the configuration according to FIG. 2 including the (imaginary) conical surfaces: as is readily apparent from the figure, shroud plate surface 14 extends along outer conical surface K.sub.1, which features a cone angle of 2. Analogously, base plate surface 24 extends along outer conical surface K.sub.2 that features a cone angle of 2. In the illustrated example, <; in a modified specific embodiment, these two angles also essentially being able to be of equal value.

(16) A guide vane segment 10 according to the present invention for a turbomachine includes a radially inner shroud plate 13 having a shroud plate surface 14 that is adapted to be configured in the turbomachine to face a rotor blade 20 adjacent to the guide vane segment, and to thereby essentially extend along an outer conical surface K.sub.1, whose cone axis coincides with axis of rotation A of a rotor shaft 30.

(17) In a radially inner region, a rotor blade 20 according to the present invention for a turbomachine has a base plate 23 having a base plate surface 24 that is adapted to be configured in the turbomachine to face a shroud of a guide vane row 10 adjacent to the rotor blade and thereby essentially extend along an outer conical surface K.sub.2 whose cone axis coincides with axis of rotation A of a rotor shaft 30.

REFERENCE NUMERAL LIST

(18) 10 guide vane segment

(19) 11 guide vane airfoil

(20) 12 radially outer shroud plate

(21) 13 radially inner shroud plate

(22) 14 shroud plate surface

(23) 15 fastening element

(24) 16 sealing element

(25) 20 rotor blade

(26) 21 rotor blade airfoil

(27) 23 base plate

(28) 24 base plate surface

(29) 30 rotor shaft

(30) A central axis or axis of rotation

(31) P parallel to A

(32) angle between shroud plate surface and A (or P)

(33) 2 cone angle of K.sub.1

(34) 2 cone angle of K.sub.2

(35) angle between base plate surface and A (or )

(36) K.sub.1, K.sub.2 outer conical surface