ROTOR-STATOR COMBINATION FOR AN AXIAL TURBOMACHINE AND AERO ENGINE

Abstract

Disclosed is a rotor-stator combination for an axial turbomachine which comprises a rotor having an impeller and a stator having a diffuser and a casing section. The combination features a one-piece structural design in manufacture and the casing section has at least one radial access which is prepared and designed for installation steps and/or machining steps for rotor sections and/or stator sections which are arranged inside the casing section. Also disclosed is an aero engine comprising such a rotor-stator combination.

Claims

1. A rotor-stator combination for an axial turbomachine, wherein the combination comprises at least one rotor comprising an impeller and at least one stator comprising a diffuser and a casing section, the rotor-stator combination featuring a one-piece structural design in manufacture and the casing section having at least one radial access which is prepared and designed for installation steps and/or machining steps for rotor sections and/or stator sections arranged inside the casing section.

2. The rotor-stator combination of claim 1, wherein the rotor-stator combination is a compressor, or comprises such.

3. The rotor-stator combination of claim 1, wherein the rotor-stator combination is a turbine, or comprises such.

4. The rotor-stator combination of claim 1, wherein the rotor-stator combination further comprises a combustion chamber.

5. The rotor-stator combination of claim 1, wherein the radial access comprises a sealing device.

6. The rotor-stator combination of claim 1, wherein the rotor-stator combination is manufactured from one material.

7. The rotor-stator combination of claim 1, wherein the rotor-stator combination is manufactured from at least two different materials, or features such.

8. The rotor-stator combination of claim 1, wherein impeller blades are manufactured from a first material, or feature such, and at least one casing section is manufactured from a second material, or features such, the first material and the second material being different.

9. The rotor-stator combination of claim 8, wherein impeller blades together with a rotor basic body are manufactured from the first material.

10. The rotor-stator combination of claim 8, wherein diffuser blades are manufactured from the second material or from a third material, or feature such.

11. The rotor-stator combination of claim 9, wherein diffuser blades are manufactured from the second material or from a third material, or feature such.

12. The rotor-stator combination of claim 1, wherein the rotor-stator combination comprises a support structure and/or a retaining device during manufacture.

13. The rotor-stator combination of claim 1, wherein the rotor-stator combination comprises at least one connecting flange for connecting the rotor-stator combination to one or more additional components of the turbomachine.

14. An aero engine, wherein the aero engine comprises the rotor-stator combination of claim 1.

15. The aero engine of claim 14, wherein the rotor-stator combination comprises a high-pressure compressor.

16. The aero engine of claim 14, wherein the rotor-stator combination comprises a high-pressure turbine.

17. A method of manufacturing a rotor-stator combination for an axial turbomachine, wherein the combination comprises at least one rotor comprising an impeller and at least one stator comprising a diffuser and a casing section, and the rotor is manufactured together with the stator in one production step, the rotor-stator combination features a one-piece structural design, and the casing section has at least one radial access which is prepared and designed for installation steps and/or machining steps for rotor sections and/or stator sections arranged inside the casing section.

Description

BRIEF DESCRIPTION OF THE DRAWING

[0047] The present invention is explained by way of example in the following text with reference to the attached drawing in which identical designations refer to the same or similar components. In the schematically simplified drawing:

[0048] FIG. 1 shows a rotor-stator combination according to an embodiment of the invention.

DETAILED DESCRIPTION OF EMBODIMENTS OF THE INVENTION

[0049] The particulars shown herein are by way of example and for purposes of illustrative discussion of the embodiments of the present invention only and are presented in the cause of providing what is believed to be the most useful and readily understood description of the principles and conceptual aspects of the present invention. In this regard, no attempt is made to show details of the present invention in more detail than is necessary for the fundamental understanding of the present invention, the description in combination with the drawing making apparent to those of skill in the art how the several forms of the present invention may be embodied in practice.

[0050] FIG. 1 shows in a longitudinal sectional view a rotor-stator combination 100 according to the invention of an axial turbomachine having a compressor 101, a combustion chamber 103 and a turbine 105.

[0051] The rotor-stator combination 100 comprises a stator 107 and a rotor 109. The stator 107 has a plurality of diffusers 1, which are arranged in series in the axial direction a, having in each case a plurality of diffuser blades 3 which are arranged in a distributed manner over the circumference u, and a casing 5 having individual casing sections 7. The rotor 109 has a plurality of impellers 9, which are arranged in series in the axial direction a, having in each case a plurality of impeller blades 11, which are arranged in a distributed manner over the circumference u, and at least one rotor basic body 13.

[0052] The casing 5, in a plurality of casing sections 7, has numerous radial accesses 15 which are arranged in series in the axial direction a and are designed as radial openings. The radial openings can have different circumferential angles or opening angles over the circumference u. For example, four or more openings with, for example, a circumferential angle of 20 degrees, 30 degrees or another angle can be arranged in each case. The radial accesses 15 can be referred to as openings for the casing interior. The radial accesses 15 are closed off by means of sealing devices 17 which are designed as covers. The sealing devices 17 or covers can additionally have hooks for the closure and/or seals for airtight sealing (not shown in FIG. 1).

[0053] The rotor-stator combination 100 also has a longitudinal axis 19.

List of reference numerals

[0054] a Axial; axial direction

[0055] r Radial; radial direction

[0056] u Circumferential direction

[0057] 100 Rotor-stator combination

[0058] 101 Compressor

[0059] 103 Combustion chamber

[0060] 105 Turbine

[0061] 107 Stator

[0062] 109 Rotor

[0063] 1 Diffuser

[0064] 3 Diffuser blade

[0065] 5 Casing

[0066] 7 Casing section

[0067] 9 Impeller

[0068] 11 Impeller blade

[0069] 13 Rotor basic body

[0070] 15 Radial access

[0071] 17 Sealing device

[0072] 19 Longitudinal