ADJUSTABLE GUIDE VANE WITH CONVEXLY SHAPED, RADIALLY INNER STORAGE SECTION FOR A GAS TURBINE, IN PARTICULAR AN AIRCRAFT GAS TURBINE

Abstract

An adjustable guide vane for a compressor, in particular a high-pressure compressor, of a gas turbine, in particular an aircraft gas turbine is described, said vane comprising a radially outer storage section, a radially inner storage section, and a vane section, which extends in the radial direction between the outer storage section and the inner storage section, wherein the outer and the inner storage sections are designed in such a way that the adjustable guide vane can be taken up rotatably about a vane axis in the compressor, and wherein the radially inner storage section is designed like a journal (cone-shaped) and has a casing surface that revolves relative to the vane axis, said surface being of convex shape. In this way, it is provided that the radius of curvature of the convex casing surface is at least double the maximum diameter of the storage section.

Claims

1. An adjustable guide vane for a high-pressure compressor of an aircraft gas turbine, comprising: a radially outer storage section, a radially inner storage section, a vane section, which extends in the radial direction between the outer storage section and the inner storage section, wherein the outer and the inner storage sections are configured and arranged so the adjustable guide vane can be taken up rotatably about a vane axis in the compressor, and wherein the radially inner storage section is configured and arranged as a cone-shaped journal or a plate and has a casing surface that revolves relative to the vane axis, the surface being of convex shape, wherein a radius of curvature of the convex casing surface is at least double the maximum diameter of the radially inner storage section.

2. The adjustable guide vane according to claim 1, wherein the radius of curvature of the convex casing surface is three to ten times the maximum diameter of the storage section.

3. The adjustable guide vane according to claim 1, wherein the convex casing surface is formed by a plurality of casing surface sections, each having a different radius of curvature.

4. The adjustable guide vane according to claim 1, wherein the adjustable guide vane is mounted exclusively over the storage section on its radially inner-lying side relative to the vane section.

5. An aircraft gas turbine, comprising: at least one adjustable high-pressure compressor, wherein the high-pressure compressor has a plurality of adjustable guide vanes arranged next to one another in the peripheral direction according to claim 1.

6. The aircraft gas turbine according to claim 5, wherein the compressor has a radially inner bearing ring with a plurality of cylindrical drill holes that are arranged next to one another in the peripheral direction, wherein an inner storage section with convex casing surface is taken up in each cylindrical drill hole.

7. The aircraft gas turbine according to claim 5, wherein it has a radially outer adjustable ring device that is joined with the radially outer storage sections of the adjustable guide vanes so that all adjustable guide vanes are simultaneously rotatable about their respective vane axis.

Description

BRIEF DESCRIPTION OF THE DRAWINGS FIGURES

[0016] The invention will be described below with reference to the appended figures by way of example and not in any limiting manner.

[0017] FIG. 1 shows in a simplified schematic illustration a diagram of an aircraft gas turbine.

[0018] FIG. 2 shows in a simplified and schematic sectional illustration an adjustable guide vane with its radially inner storage section.

DESCRIPTION OF THE INVENTION

[0019] Schematically and simplified, FIG. 1 shows an aircraft gas turbine 10, which is illustrated as a turbofan engine purely by way of example. The gas turbine 10 comprises a fan 12, which is surrounded by a casing 14, which is simply indicated. In the axial direction AR of the gas turbine 10, a compressor 16 is connected to the fan 12, the compressor being taken up in a simply indicated inner housing 18 and can be designed as a single-stage or a multistage compressor. The combustion chamber 20 is connected to the compressor 16. Hot exhaust gas streaming out from the combustion chamber then flows through the subsequently connected turbine 22, which can be designed as a single-stage or a multistage turbine. In the present example, the turbine 22 comprises a high-pressure turbine 24 and a low-pressure turbine 26. A hollow shaft 28 connects the high-pressure turbine 24 to the compressor 16, in particular a high-pressure compressor 29, so that these are driven or rotated jointly. In the radial direction RR of the turbine, another inner-lying shaft 30 connects the low-pressure turbine 26 to the fan 12 and to a low-pressure compressor 32, so that these are driven or rotated jointly. A thruster 33, which is only indicated here, is connected to the turbine 22.

[0020] In the illustrated example of an aircraft gas turbine 10, a turbine midframe 34 is arranged between the high-pressure turbine 24 and the low-pressure turbine 26, and is arranged also around the shafts 28, 30. In its radially outer region 36, hot exhaust gases from the high-pressure turbine 24 flow through said turbine midframe 34. The hot exhaust gas then reaches an annular space 38 of the low-pressure turbine 26. By way of example, rotating blade cascades 27 are illustrated from compressors 29, 32 and turbines 24, 26. Guide vane cascades 31 that are usually present are illustrated only in the compressor 32 by way of example, for reasons of clarity.

[0021] The description below of an embodiment of an adjustable guide vane particularly refers to the compressor 16, in particular the high-pressure compressor 29.

[0022] In a simplified and schematic sectional illustration, FIG. 2 shows an adjustable guide vane 50. The adjustable guide vane 50 comprises a radially inner storage section 52. Radially toward the outside, a vane section connects to the storage section 52. The vane section in this case extends radially outside up to a radially outer storage section 56, which is indicated here only very simply.

[0023] The outer and inner storage sections 52, 56 are thus embodied here in such a way that the adjustable guide vane 50 is rotatable about a vane axis SA in the compressor. The radially inner storage section 52 is designed like a journal (cone-shaped) and has a casing surface 58 that revolves relative to the vane axis SA, said surface being of convex shape. In this case, the radius of curvature KR of the convex casing surface 58 is at least double the maximum diameter DM of the storage section 52.

[0024] In FIG. 2, two radii of curvature KR of the casing surface 58 are indicated by dot-dash lines that do not intersect in FIG. 2 (on the right). In this way, it can be seen that a central point for a circle, whose radius corresponds to the radius of curvature KR, is found outside FIG. 2, and that the radius of curvature KR is clearly greater than the diameter DM of the storage section 52.

[0025] The selected diagram illustrates also that the radius of curvature KR of the convex casing surface 58 can be three to ten times the maximum diameter DM of the storage section 52.

[0026] Although this is not explicitly shown in FIG. 2, the convex casing surface 58 can also be formed by a plurality of casing surface sections, each of which has a different radius of curvature. In this case, each of the different radii of curvature fulfill the above-mentioned conditions in relation to the diameter DM of the storage section 52.

[0027] In an aircraft gas turbine 10, which is shown in FIG. 1 and which has at least one adjustable compressor, in particular the adjustable high-pressure compressor 29, the compressor 29 can have a plurality of adjustable guide vanes that are arranged next to one another in the peripheral direction, as they have been described above with reference to FIG. 2. For this, the compressor 29 can have a radially inner bearing ring 60 (FIG. 2) with a plurality of cylindrical drill holes 62 that are arranged next to one another in the peripheral direction, whereby an inner storage section 52 with convex casing surface 58 is received in each cylindrical drill hole 62. The diameter of a drill hole 62 in this case essentially corresponds to the maximum diameter DM of the storage section 52, so that, also with respect to the diameter of the drill hole, it is valid that the radius of curvature KR of the casing surface 58 is at least twice as large as the diameter of the drill hole 62.