WO2021018333A1

WO2021018333A1 - Module for a turbomachine

Info

Publication number: WO2021018333A1
Application number: PCT/DE2020/000175
Authority: WO
Inventors: Stefan Rauscher; Manfred Feldmann; Peter Iberl
Original assignee: MTU Aero Engines AG
Priority date: 2019-08-01
Filing date: 2020-07-29
Publication date: 2021-02-04
Also published as: DE102019211524A1

Abstract

The invention relates to a module (20) for a turbomachine (1), having two components (21, 22), which each extend peripherally and are segmented, wherein the components (21, 22) have an axial overlap (40) and have a radial offset (41) relative to each other such that they contact each other in a contact area (42), and wherein segment joints (23, 24) of the two components (21, 22) coincide at a rotational position (25), wherein an impact edge (21.1.1) of the first segment (21.1) of the first component (21) together with impact edges (22.1.1, 22.2.1) of the first and second segment (22. 1, 22.2) of the second component (22) forms an angle (35).

Description

MODULE FOR A FLOW MACHINE DESCRIPTION Technical field

The present invention relates to a module for a turbomachine.

State of the art

The turbo engine can be, for example, a jet engine, e.g. B. a turbofan engine. The flow machine is functionally divided into a compressor, combustion chamber and turbine. In the case of the jet engine, for example, the air that is sucked in is compressed by the compressor and burned in the downstream combustion chamber with the added kerosene. The resulting hot gas, a mixture of combustion gas and air, flows through the downstream turbine and is expanded in the process. Both the compressor and the turbine are generally constructed in several stages, each stage having a guide vane ring and a rotor blade ring.

The module in question here has a first and a second component, the components each extending circumferentially and segmented, that is to say being divided into a plurality of segments. Such a segmentation is often used to store hotter components in a cool housing structure, the segment joints then absorbing differential thermal expansion. The components have an axial overlap and such a radial offset that they rest against one another in a contact surface. The first component can be, for example, a guide vane ring, the second component can be, for example, an outer air seal (OAS, Outer Air Seal). This is intended to illustrate the subject matter at hand, but not initially to limit its generality.

CONFIRMATION COPY Presentation of the invention

The present invention is based on the technical problem of specifying a particularly advantageous module for a turbomachine.

This is achieved according to the invention with the module according to claim 1. A segment joint of the first component and a segment joint of the second component are arranged in the same rotational position. In the segment joint of the first component, a first and a second segment of the first component adjoin each other with a joint edge located in the contact surface (at least in a state of thermal expansion), and in the segment joint of the second component a first and second segment of the second component (also each with an abutting edge located in the contact surface). The abutting edge of the first segment of the first component runs in such a way that it forms an angle with the abutting edges of the first and second segments of the second component.

Figuratively speaking, the joint edge of the first segment of the first component crosses the segment joint of the second component, that is to say the joint edges of the first and second segment thereof. The first segment of the first component touches both the first and the second segment of the second component, ie is supported on both segments. As a result, if there is thermal expansion during operation, for example, the abutting edge of the first segment of the first component can be prevented from getting caught on the abutting edge of the circumferentially opposite segment of the second component. Such a blocked thermal expansion could otherwise be critical due to the increased loads. In the case of an orientation of the joint edges not according to the invention, for example, due to the tolerance situation, there could be no exact overlap of the segment joints with minimal thermal expansion and this could only arise at maximum thermal expansion. If the radial positions do not exactly match one another, the described hooking can occur. As an alternative to the present subject matter, such a hooking could also be avoided by arranging the segment joints at different circumferential positions. However, this would mean an additional boundary condition that could require the component to be subdivided into more segments than is necessary for other technical reasons. The segment numbers would have to be adjusted relative to one another, for example, so that a l: n ratio (with n = N> 1) results. In other circumstances, the circumferential misalignment between two segment joints could be so small that there would be a risk of entanglement. In the case of the module according to the invention, on the other hand, two segment joints are deliberately placed in the same circulating position, and the hooking is avoided by the alignment of the joint edges. This increases the freedom of design with regard to the remaining abutting edges or segmentation of the components.

Preferred refinements can be found in the dependent claims and the entire disclosure, although a distinction is not always made between the different claim categories in detail when presenting the features; at any rate, the disclosure is to be read implicitly both with regard to device and corresponding process or use aspects.

The indication "circumferential" and the "circumferential direction", with regard to which, for example, the components are also segmented, relate to a revolution around the longitudinal axis of the module or the turbomachine, around which the rotor blade rings, for example, also rotate during operation. The same applies to the information “axial” and “radial”, as well as the associated directions. The statement "Anyhow in a thermal expansion state" means that the system exists in any case when the module or the turbo machine is in operation, for example when the radially inner component has an increased temperature during operation.

The axial overlap between the components consists of at least one axial section, so, for example, one component can also extend further axially forward than the other (in front of the overlap area) and / or the other component further axially backwards (behind the overlap area ). The radial offset exists in the area of the axial overlap, where one component is arranged radially outside the other component when viewed in a section perpendicular to the axis.

The angle that the joint edge of the first segment of the first component makes with the joint edge of the first and second segment of the second component is based on the axially opening angle between the cutting lines (not the angle oriented in the direction of rotation). In general, the consideration of the joint edges refers to the contact surface and thus the area of the axial overlap; axially in front of or behind it, the segment joints can, for example, also have a different course (e.g. to reduce leakage). In the area of the axial overlap, the abutting edges generally run in a straight line when viewed individually.

The abutting edges of the first and second segments of the first component are preferably parallel to one another; the same applies to the abutting edges of the first and second segments of the second component.

According to a preferred embodiment, the angle enclosed by the abutting edges is at least 60 °, a preferred upper limit is at most 120 °. This also limits the inclination or inclination of the abutting edges, so for example acute-angled corners are avoided, which z. B. can reduce the risk of injury during assembly and revision. Angles of around 90 ° can be particularly preferred. In a preferred embodiment, not only the abutting edge of the first, but also the abutting edge of the second segment of the first component crosses both the abutting edge of the first and the second segment of the second component. In general, however, it would also be sufficient if only the joint edge of the first segment of the first component crosses the other two joint edges, provided that the joint edge that does not cross (of the second segment of the first component) does not "exceed" the joint, taking into account the thermal expansion, so the opposite segment of the other component is not reached. Preferably, however, both joint edges of one component cross the segment joint of the other component, that is to say they touch the first and also the second segment of the first component both segments of the second component, i.e. both its first and its second (which is then very understandably also the other way around).

In general, the inclination between the abutting edges of the first and second components can also be achieved, for example, if the abutting edges are tilted relative to the axial direction in only one of the components. However, both the abutting edges of the first and second segment of the first component and the abutting edges of the first and second segment of the second component are preferably tilted relative to the axial direction, so the inclination is divided to a certain extent (e.g. avoidance of sharp corners). The abutting edges of the first component with the axial direction preferably enclose an edge angle of at least 30 ° and at most 60 ° and / or the abutting edges of the first and second segment of the second component form an edge angle of at least 30 ° and at most with the axial direction 60 ° (the smaller of the two angles included with the axial direction is considered in each case). “Majority” generally means at least two, so there are at least two segments per component. The number will preferably be higher, for example at least 4, 5 or 6 (a possible upper limit can be at most 100, for example). In general, the first and the second plurality can also be of the same size, ie the two components can have the same number of segments. In a preferred embodiment, however, the two differ in their number of segments; the respective number of segments can be determined, for example, according to the structural-mechanical or production-technical boundary conditions of the respective component. Since the number of segments of the components does not need to be coordinated with one another, the total number of segments and thus the number of individual parts to be handled can be reduced. B. can be advantageous in terms of costs.

In a preferred embodiment, the rotary position at which the first and second segment of the first component and also the first and second segment of the second component adjoin one another is the only rotary position at which a segment joint of the first component meets a segment joint of the second component . The remaining segment joints of the first component are therefore closed the remaining segment joints of the second component are each set ver in the direction of rotation. In other words, the remaining segment joints of the first component each overlap with exactly one segment of the second component, and the remaining segment joints of the second component each overlap with exactly one segment of the first component. Per component, the segments are preferably the same size, so they extend over the same angle (which is generally true); the offset of the remaining segment joints then preferably results from different segment numbers (which are in a non-integer ratio). In a preferred embodiment, all segments of the first component are structurally identical to one another and / or all segments of the second component are structurally identical to one another. Correspondingly, there are also abutting edges on the remaining joint edges of the respective component, even if the respective segment joint does not coincide with a segment connection of the other component. The provision of structurally identical segments can, for example, help prevent assembly errors.

Alternatively, in general, of course, only the abutting edges of the first and second segments of the first component could be angled to the abutting edges of the first and second segments of the second component and the remaining segment joints could be aligned parallel to one another.

The first and the second component can each surround a gas duct, for example a hot gas duct, of the turbomachine, in particular the turbofan engine, in a ring shape.

The two components can be axially adjacent and only partially overlap axially, ie the axial overlap area can correspond to only a part, for example 2% -30%, of the axial extent of the first and / or the second component. The overlap area can be completely and continuously in the circumferential direction (without taking segment gaps into account).

In some embodiments, the axial overlap area can also amount to the entire axial extent of the first and / or the second component or more than 80% thereof.

In some embodiments, the first and second components are different housing shells.

As already mentioned, the first component in a preferred embodiment is a guide vane ring and the second component is an outer air seal, in particular with an inlet coating and with a carrier for the inlet coating that surrounds the guide vane ring radially outward and / or partially axially with the Guide vane ring overlaps. An application in the turbine area is generally preferred.

The invention also relates to a turbomachine with a module disclosed here. The turbo machine can in particular be an aircraft engine such. B. a turbofan engine.

Brief description of the drawings

The invention is explained in more detail below with the aid of an exemplary embodiment, the individual features within the framework of the independent claims also being essential to the invention in other combinations and furthermore no distinction is made between the different claim categories.

In detail shows

Figure 1 shows a turbo machine, namely a jacket current engine in one

Axial section; FIG. 2 two components of a turbomachine in a schematic axial view;

Figure 3 shows a section of the arrangement according to Figure 2 in a schematic

Radial view; FIG. 4 shows an axial section through the arrangement according to FIG.

Preferred embodiment of the invention

1 shows a turbomachine 1, specifically a turbofan engine, in an axial section. The flow machine 1 is functionally divided into compressor la, combustion chamber lb and turbine lc. Both the compressor la and the turbine l c are each made up of several stages, each stage is composed of a guide and a subsequent rotor blade ring. During operation, the rotor blade rings rotate around the longitudinal axis 2 of the turbo machine 1. The air that is sucked in is compressed in the compressor la, and then burned in the downstream combustion chamber lb with the kerosene added. The hot gas is expanded in the turbine 1c and thereby drives the rotor blade rings, which rotate about the longitudinal axis 2.

FIG. 2 shows a module 20 which has a first component 21 and a second component 22. The first component 21 can in particular be a guide vane ring, the second component 22 is then an external air seal (OAS). Both components 21, 22 are each segmented, that is to say each divided into several segments 21.1-21.4, 22.1-22.5. As can be seen from Fig. 2, there is a rotary position 25 at which a segment joint 23 of the first component 21 and a segment joint 24 of the second component 22! lie.

Fig. 3 shows a detailed view of this revolving position 25, looking at it radially from the outside. Axial direction 30, parallel to longitudinal axis 2, and direction of rotation 31 are shown for orientation. A first segment 21.1 and a second segment 21.2 of the first component 21, as well as a first segment 22.1 and a second segment 22.2 of the second component 22 (each a Detail). In the following, reference is also made to FIG. 4, which shows an axial section through the arrangement according to FIG. 3 (cf. the section line AA marked in FIG. 3).

The abutting edges 21.1.1, 21.2.1 of the segments 21.1, 21.2 of the first component 21 are angled to the axial direction 30 and form an angle 35 with the abutting edges 22.1.1, 22.2.1 of the segments 22.1, 22.2 of the second component 22. In the present example, this is around 90 °. The abutting edges 21.1.1, 21.2.1, 22.1.1, 22.2.1 cross one another in such a way that each of the segments 21.1, 21.2 of the first component 21 touches both segments 22.1, 22.2 of the second component 22 in every thermal expansion state. Accordingly, as explained in detail in the introduction to the description, a reciprocal hooking can be prevented, that is, a hooking of the segment 21.1 with the segment 22.2 and the segment 22.1 with the segment 21.2.

In the view according to FIG. 3, the axial overlap 40 of the components 21, 22 can also be seen, the section according to FIG. 4 illustrates the radial offset 41. Looking at the two figures together, it can be seen that the first and the second component 21, 22 in the area of the axial overlap 40 have a contact surface 42 aneinan the. The joint edges 21.1.1, 21.2.1, 22.1.1, 22.2.1 which form the respective segment joint 23, 24 are also located in this contact surface 42.

REFERENCE LIST

Turbo machine 1

Compressor la

Combustion chamber lb

Turbine lc

Longitudinal axis 2

Module 20

First component 21

Segments 21.1-21.4 abutting edges 21.1.1, 21.2.1

Second component 22

Segments 22.1-22.5

Butt edges 22.1.1, 22.2.1

Segment joint of the first component 23

Segment joint of the second component 24

Circulation position 25

Axis direction 30

Direction of rotation 31

Angle 35

Axial overlap 40

Radial offset 41

Contact surface 42

Claims

EXPECTATIONS

1. Module (20) for a turbomachine (1), with

a first component (21) which extends circumferentially and is subdivided into a first plurality of segments (21.1-21.4), and

a second component (22), which also extends circumferentially and is subdivided into a second plurality of segments (22.1 -22.5),

wherein the first and the second component (21, 22) have an axial overlap (40) and such a radial offset (41) to one another that they rest against one another in a contact surface (42),

and wherein the first component (21) has a segment joint (23), in which a first and a second segment (21.1, 21.2) of the first component (21) each with a joint edge (21.1.1 located in the contact surface (42)) , 21.2.1) adjoin one another at least in a thermal expansion state, and wherein the second component (22) has a segment joint (24) in which a first and a second segment (22.1, 22.2) of the second component (22) each with an in the abutment edge (22.1.1,

22.2.1) adjoin each other at least in a thermal expansion state,

wherein the segment joint (23) of the first component (21) lies on a rotating position (25) with the segment joint (24) of the second component (22), and the joint edge (21.1.1) of the first segment (21.1) of the first component (21) with the abutting edges (22.1.1, 22.2.1) of the first and second segment (22.1, 22.2) of the second component (22) includes an angle (35).

2. Module (20) according to claim 1, in which the abutting edges (21.1.1, 22.1.1, 22.2.1) of the first and second components (21, 22) form a closed angle (35) with one another at least 60 ° . 3. Module (20) according to claim 1 or 2, in which the angle (35) enclosed by the abutting edges (21.1.1, 22.1.1, 22.2.1) of the first and second components (21, 22) with one another is at most 120 ° is. 4. Module (20) according to any one of the preceding claims, wherein the first

Segment (21.1) of the first component (21) in the contact surface (42) touches the first and the second segment (22.1, 22.2) of the second component (22) and also the second segment (21.2) of the first component (21) in the Contact surface (42) touches the first and second segments (22.1, 22.2) of the second component (22).

5. Module (20) according to one of the preceding claims, in which both the abutting edges (21.1.1, 21.2.1) of the first and second segments (21.1, 21.2) of the first component (21) and the abutting edges (22.1.1 , 22.2.1) of the first and second segments (22.1, 22.2) of the second component (22) each lie at an angle to the axial direction (30).

6. Module (20) according to one of the preceding claims, in which the first and second components (21, 22) differ in their number of segments, that is to say the first and second plurality are different in size.

7. Module (20) according to one of the preceding claims, in which the remaining segment joints of the first component (21) are each offset from the remaining segment joints of the second component (22).

8. Module (20) according to one of the preceding claims, in which all segments (21.1-21.4) of the first component (21) are structurally identical to one another. 9. Module (20) according to one of the preceding claims, in which all segments (22. 1 -22.5) of the second component (22) are structurally identical to one another. 10. Module (20) according to any one of the preceding claims, wherein the first

Component (21) is a guide vane ring.

1 1. module (20) according to any one of the preceding claims, wherein the second component (22) is an outer air seal.

12. Turbo machine (1), in particular aircraft engine, with a module (20) according to one of the preceding claims.