Component system of a turbo engine

Abstract

A component system of a turbine engine including a first component segment and a second component segment configurable in a ring segment shape, so that at least one abutment surface of the first component segment and an abutment surface of the second component segment abut against each other; together, the first component segment and the second component segment including at least three overlapping elements for sealing a gap between the abutment surfaces. In the case of mutually abutting abutment surfaces, each overlapping element overlapping radially with the respective other component segment. At least two of the overlapping elements are configured on the first component segment, while at least one of the overlapping elements is configured on the second component segment. In the case of mutually abutting abutment surfaces, the overlapping element of the second component segment is axially configured between the overlapping elements of the first component segment.

Claims

1. A component system of a turbine engine, the component system comprising: a first component segment; and a second component segment configurable in a ring segment shape about an axis of a rotor of the turbine engine, so that a first abutment surface of the first component segment abuts against a second abutment surface of the second component segment, wherein, together, the first component segment and the second component segment include at least first, second and third overlapping elements for sealing a gap between the first and second abutment surfaces; the first and third overlapping elements being configured as first projections in a circumferential direction with respect to the first abutment surface on the first component segment and overlapping radially the second component segment; the second overlapping element being configured as a second projection in the circumferential direction with respect to the second abutment surface on the second component segment and overlapping radially the first component segment; and, the second overlapping element being axially configured between the first and third overlapping elements; wherein, the first and third overlapping elements each have a radially inward surface overlapping radially the second component segment, wherein the second overlapping element has a radially inward surface overlapping radially the first component segment, and wherein at least one of the three radially inward surfaces is configured at a radially different distance or in a radially different plane relative to the axis than another of the three radially inward surfaces.

2. The component system as recited in claim 1 wherein at least one of the first, second and third overlapping elements is integrally formed on the respective first or second component segment or is metallurgically bonded to the respective first or second component segment.

3. The component system as recited in claim 1 wherein the first and third overlapping elements are configured at mutually opposing outer regions of the first component segment, or the second overlapping element is configured in the axially middle region of the second component segment.

4. The component system as recited in claim 1 wherein the first, second and third overlapping elements jointly seal the gap between the first and second abutment surfaces.

5. The component system as recited in claim 1 wherein at least one of the first, second and third overlapping elements is configured to be hook-shaped or rectangular in cross section, or trough-shaped, or V-shaped, or U-shaped.

6. The component system as recited in claim 1 wherein the first component segment or the second component segment includes at least one overlapping region configured to complement an associated one of the first, second and third overlapping elements of the respective other of the first and second component segments.

7. The component system as recited in claim 1 wherein the second overlapping element has a larger surface area or a greater axial extent than the first and third overlapping elements.

8. The component system as recited in claim 1 wherein the first component segment or the second component segment is configured as a blade ring segment or as a turbine ring segment.

9. The component system as recited in claim 1 wherein at least one of the first and second component segments is manufactured additively.

10. A method for assembling a component system as recited in claim 1 in a turbine engine, comprising: joining the first component segment and the second component segment in a way to allow: the first abutment surface to abut the second abutment surface; the first and third overlapping elements to overlap radially with the second component segment; the second overlapping element to overlap radially with the first component segment; and to be axially configured between the first and third overlapping elements.

11. A turbine engine comprising the component system as recited in claim 1.

12. An aircraft engine comprising the component system as recited in claim 1.

13. The component system as recited in claim 1 wherein the first overlapping element is V-shaped and the third overlapping element is rectangular in cross section.

14. The component system as recited in claim 1 wherein the first projections are separated axially by the first abutment surface.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) Other features of the present invention are derived from the claims, the exemplary embodiments, as well as in light of the drawings. The aforementioned features and feature combinations mentioned in the Specification, as well as the features and feature combinations subsequently mentioned in the exemplary embodiments may be used not only in the particular stated combination, but also in other combinations, without departing from the scope of the present invention. Specifically,

(2) FIG. 1: shows a schematic perspective view of two component segments of a component system according to the present invention in accordance with a first specific embodiment; and

(3) FIG. 2: shows a schematic perspective view of two component segments of the component system according to the present invention in accordance with a second specific embodiment.

(4) FIG. 3 shows schematically of an aircraft engine of the present invention.

(5) FIGS. 4A and 4B show the overlapping element in the form of a U-shaped element and a hook shaped element.

DETAILED DESCRIPTION

(6) FIG. 1 shows a schematic perspective view of a component system 10 in accordance with a first exemplary embodiment of the present invention. Component system 10 includes a plurality of component segments, of which merely one first component segment 12a and a second component segment 12b are shown in a cutaway view. In the present case, component system 10 is configured as a blade ring of an aircraft turbine and includes other component segments which are designed analogously to illustrated component segments 12a, 12b and complement one another to form a ring. For assembly purposes, the component segments are annularly configured about an axis 101 of a rotor of the aircraft engine 100 as shown schematically in FIG. 3, so that, in each case, an abutment surface 14a of first component segment 12a and an abutment surface 14b of the second component segment 12b abut against each other. Abutment surfaces 14a, 14b are provided in each case at the narrow sides of component segments 12a, 12b. In principle, the opposing abutment surfaces of individual components segments 12a, 12b may be designed to be identical to or to complement abutment surfaces 14a, 14b, to ensure a non-interchangeable assembly of all component segments. For the sake of assembly, all of the component segments are circumferentially slid onto each other until the particular abutment surfaces thereof abut against each other, respectively rest against each other.

(7) In order to seal the segments between abutment surfaces 14a, 14b, component segments 12a, 12b have altogether three overlapping elements 16a, 16,b, 16c for each abutment surface pair. In the case of mutually abutting abutment surfaces 14a, 14b, it is discernible that overlapping elements 16a-c overlap radially with the respective other component segment 12a, 12b, so that component segments 12a, 12b are still only circumferentially movable relative to one another, not, however, axially or radially. As illustrated by arrow Ia, overlapping element 16a comes to rest on associated overlapping region 18a, which has a complementary form; as illustrated by arrow Ib, overlapping element 16b comes to rest on associated overlapping region 18b, which has a complementary form; and, as illustrated by arrow Ic, overlapping element 16c comes to rest on associated overlapping region 18c, which has a complementary form. As is also discernible, all of overlapping elements 16a-c are integrally formed with the particular component segment 12a, 12b. This may be achieved very readily and cost-effectively, for example by an additive production of component segments 12a, 12b. It is also readily apparent from FIG. 1 that individual overlapping element 16b is formed in the middle of second component segment 12b and, accordingly, in the assembled state, is configured between the particular outer overlapping elements 16a, 16c of first component segment 12b. It is also apparent that second, oppositely oriented overlapping element 16b has a larger surface area, as well as a greater axial extent than outer overlapping elements 16a, 16c of first component segment 12a, is formed in another, further radially outwardly disposed plane than overlapping elements 16a, 16c, and has a different geometry than overlapping elements 16a, 16c. Moreover, overlapping elements 16a, 16c are formed to be cuboid, respectively rectangular in cross section, while overlapping element 16b is formed to be trough-shaped, respectively virtually V-shaped in cross section. A self-centering is thereby achieved during assembly of component segments 12a, 12b. In the assembled state of component segments 12a, 12b, all three overlapping elements 16a-c provided completely cover the gap between abutment surfaces 14a, 14b. In other words, the sealing of segments is integrated in component segments 12a, 12b in such a way that, depending on the joint, respectively abutment surface pair, at least three overlapping elements 16a-c are made available, of which two overlapping elements 16a, 16c are affixed to the first marginal edge portion (component segment 12a), while other overlapping element 16b is affixed to the second marginal edge portion (component segment 12b), as well as between the two other overlapping elements 16a, 16c, thereby providing an alternating overlapping in the assembled state. From the alternating covering, the advantage is derived that the leakage gap is only determined by the component segments themselves, since they affix themselves to one another and do not need to be affixed by housing receptacles or the like. The tolerance chain for the leakage gap may be reduced in this manner. Moreover, no unattached, respectively separate parts are needed for the sealing. In principle, it may be provided that first component segment 12a and/or second component segment 12b have one or a plurality of further overlapping elements.

(8) FIG. 2 shows a semi-transparent, schematic perspective view of component system 10 in accordance with a second exemplary embodiment of the present invention. Component system 10 likewise includes a plurality of component segments, of which merely one first component segment 12a and a second component segment 12b are shown in a cutaway view. It is discernible that the geometries of component segments 12a, 12b, of first, primarily V-shaped overlapping element 16a, and of second overlapping element 16b deviate from the preceding exemplary embodiment, while overlapping element 16c continues to be cuboid, respectively rectangular in cross section. Moreover, overlapping elements 16a and 16c are not integrally formed, rather metallurgically bonded to component segment 12a, for example by welding, soldering or adhesive bonding. Analogously, second overlapping element 16b may be metallurgically bonded to component segment 12b, for example by welding, soldering or adhesive bonding. In addition, at the radial inner sides thereof, component segments 12a, 12b include sealing elements 20a, 20b, which may be formed as honeycomb seals for turbine blades, for example. However, the basic principle of component system 10 including the alternating covering of overlapping elements 16a-c corresponds to that of the preceding exemplary embodiment, so that assembling, respectively joining component segments 12a, 12b, as illustrated by arrows IIa-c, thereby accomplishes a corresponding overlapping and segment sealing. As a general principle, however, deviating geometries of overlapping elements 16a-c are also conceivable. For example, at least one of overlapping elements 16a-c may be configured to be hook-shaped, (e.g. element 16a, FIG. 4B) thereby allowing component segments 12a, 12b, in response to the sliding together thereof, to lock engagingly in the manner of a clip-type connection and be fixed in relation to one another. Alternatively or additionally, at least one of the overlapping elements may be configured to be U-shaped (e.g. element 16a, FIG. 4B)