Jacket ring assembly for a turbomachine

Abstract

A jacket ring assembly for a turbomachine, the jacket ring assembly including a casing part, a jacket ring segment which is adapted to radially outwardly surround a rotor blade ring and to this end is disposed radially inwardly of the casing part, as considered with respect to a longitudinal axis of the turbomachine, and a segmented ring which is circumferentially divided into segments and by which the jacket ring segment is mounted to the casing part, the segmented ring being axially form-fittingly disposed on a form-fitting element of the casing part, for which purpose each of the respective segments of the segmented ring is radially outwardly assembled with the form-fitting element, and the segmented ring forming a supporting seat on which the jacket ring segment is seated and radially inwardly supported with an axially forward end.

Claims

1. A jacket ring assembly for a turbomachine, comprising: a casing part; a jacket ring segment adapted to radially outwardly surround a rotor blade ring and disposed radially inwardly of the casing part, as considered with respect to a longitudinal axis of the turbomachine; and a segmented ring circumferentially divided into segments, the jacket ring segment mounted to the casing part by the segmented ring, the segmented ring being axially form-fittingly disposed on a form-fitting element of the casing part, so that each of the respective segments of the segmented ring is radially outwardly assemblable with the form-fitting element, the segmented ring forming a supporting seat, the jacket ring segment being seated on the supporting seat and radially inwardly supported with an axially forward end, wherein at least two of the segments of the segmented ring meet circumferentially at a pair of adjacent faces, the pair of the adjacent faces when viewed in an axial direction being angled with respect to the radial direction.

2. The jacket ring assembly as recited in claim 1 wherein the form-fitting element of the casing part is a radially inwardly projecting web disposed in a radially outwardly open receptacle of the segmented ring.

3. The jacket ring assembly as recited in claim 2 wherein when viewed in the axial direction, the web extends at an angle of no more than 30° in the radial direction.

4. The jacket ring assembly as recited in claim 1 further comprising a retaining ring pressing the segments of the segmented ring radially outwardly into engagement on the form-fitting element.

5. The jacket ring assembly as recited in claim 4 wherein the retaining ring is circumferentially closed and is axially pressed into a receptacle in the segmented ring.

6. The jacket ring assembly as recited in claim 5 wherein, when viewed in the axial direction, the retaining ring is axially form-fittingly retained in the receptacle behind a projection.

7. The jacket ring assembly as recited in claim 1 wherein the jacket ring segment is a sheet-metal part or wherein an abradable seal is disposed on the jacket ring segment.

8. The jacket ring assembly as recited in claim 1 wherein at least one segment of the segments has one adjacent face of the pair of adjacent faces and has an opposite face, the one adjacent face and the opposite face being parallel to each other when viewed in the axial direction, the opposite face thus also being angled with respect to the radial direction.

9. The jacket ring assembly as recited in claim 8 wherein a further segment of the segments has opposing faces parallel to each other when viewed in the axial direction.

10. The jacket ring assembly as recited in claim 1 wherein at least one of the adjacent faces is an oblique abutting face which, when viewed in the axial direction, forms an angle α of at least 85° and no more than 110° with a connecting line extending between a point of intersection of the oblique abutting face with an outer periphery of the segmented ring and a point of intersection of an opposite abutting face with an inner periphery of the segmented ring.

11. The jacket ring assembly as recited in claim 10 wherein all segments of the segmented ring are identical in construction.

12. The jacket ring assembly as recited in claim 1 further comprising a sealing insert disposed at a joint where the at least two segments meet.

13. A turbine module having the jacket ring assembly as recited in claim 1 and a rotor blade ring radially outwardly surrounded by the jacket ring segment.

14. The turbine module as recited in claim 13 wherein the jacket ring assembly is part of an axially forward stage of the turbine module.

15. A method for overhauling a turbine module according to claim 13 wherein the jacket ring segment is removed by dismantling the segmented ring from an axially forward end.

16. A turbomachine comprising the jacket ring assembly as recited in claim 1.

17. A jet engine comprising the turbomachine as recited in claim 16.

18. The jacket ring assembly as recited in claim 1 wherein the two segments are different in construction.

19. The jacket ring assembly as recited in claim 9 wherein between the at least one segment and the further segment is a yet further segment with further opposing faces that are not parallel to each other.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) The present invention will now be explained in more detail with reference to an exemplary embodiment. The individual features may also be essential to the invention in other combinations within the scope of the other independent claims, and, as above, no distinction is specifically made between different claim categories.

(2) In the drawings,

(3) FIG. 1 shows an axial cross-sectional view of a turbofan engine;

(4) FIG. 2 shows an axial cross-sectional view of an inventive jacket ring assembly as part of the turbofan engine of FIG. 1;

(5) FIG. 3 shows a portion of a segmented ring of the assembly of FIG. 2 in a cross-sectional view taken perpendicular to the axial direction;

(6) FIG. 4 shows, as an alternative to FIG. 3, a further option for the orientation of the abutting faces of the individual segments.

DETAILED DESCRIPTION

(7) FIG. 1 shows in axial section a turbomachine 1, specifically a turbofan engine. Turbomachine 1 is functionally divided into a compressor 1a, a combustor 1b and a turbine 1c. Both compressor 1a and turbine 1c are made up of a plurality of stages, each stage being composed of a stator vane ring and a subsequent rotor blade ring. During operation, the rotor blade rings rotate about longitudinal axis 2 of turbomachine 1. The intake air is compressed in compressor 1a, and is then mixed and burned with jet fuel in the downstream combustor 1b. The hot gas flows through hot gas duct 3, thereby driving the rotor blade rings that rotate about longitudinal axis 2.

(8) FIG. 2 shows a jacket ring assembly 20 provided as part of a module of turbine 1c. It has a casing part 21 and a jacket ring segment 22 having a seal 23, here an abradable coating in the form of a honeycomb seal, disposed on the radially inner side thereof. Jacket ring segment 22 radially outwardly surrounds rotor blades 24.

(9) In order to mount jacket ring segment 22 on casing part 21, a segmented ring 25 is provided which is circumferentially divided into a plurality of segments (see FIGS. 3 and 4). The individual segments of segmented ring 25 are assembled from radially inside with a form-fitting element 26 of casing part 21. In the present case, form-fitting element 26 is provided as a radially inwardly projecting web of the casing, onto which the segments of segmented ring 25 are slid until the web of the casing comes radially into engagement within a receptacle 25a of segmented ring 25. The segments of the segmented ring are then also axially form-fittingly retained. Segmented ring 25 forms a supporting seat 27 which radially inwardly supports jacket ring segment 22 at its axially forward end. A retaining ring 28 is inserted to retain the segments of segmented ring 25 radially in position. The retaining ring extends uninterruptedly in the circumferential direction and is axially pressed into a receptacle 29 of segmented ring 25. In receptacle 29, the retaining ring is axially form-fittingly retained behind a projection 30.

(10) Form-fitting element 26; i.e., the web of casing part 21, is provided with a bore 31, which is optional and may be used to supply a cooling fluid. Furthermore, the shielding plates 32 disposed radially between casing part 21 and jacket ring segment 22 are also optional; the inventive approach could also be implemented with an insulating material or the like between casing part 21 and jacket ring segment 22.

(11) FIG. 3 shows segmented ring 25 in a cross-sectional view taken perpendicular to longitudinal axis 2 (for the sake of clarity without hatching), and more specifically, a portion of the segmented ring including several segments 35, 36. At their circumferential ends, segments 35, 36 are provided with respective abutting faces 35a, 36a with which they meet. In the case of the assembly shown in FIG. 3, segmented ring 25 is built from two types of segments. On the one hand, there are segments 35 whose abutting faces 35a are parallel to each other in each segment 35. These segments 35 and the complementary segments 36 alternate with one another. Due to the mutually parallel abutting faces 35a, segments 35 can each be slid into their installed positions in an insertion direction 37 after the immediately adjacent segments 36 have been placed in position.

(12) FIG. 4 shows segments 40 which are alternative to those shown in FIG. 3 and which allow the segmented ring 25 to be entirely built from only one type of segment. To this end, an abutting face 40a is oriented obliquely such that it forms an angle α of about 90° with a connecting line 41. The opposite abutting face 40b has a complementary oblique orientation; it forms an obtuse angle at an inner circumferential surface 42 of the segmented ring and an acute angle at outer circumferential surface 43. During insertion, when the immediately circumferentially adjacent segments 40 are already in their installed positions, a corresponding segment 40 can initially be hooked into place with its abutting face 40b. Subsequently, segment 40 is rotated into its installed position.

(13) Regardless of the specific configuration of segments 35, 40, sealing inserts 46 are provided at the respective joints 45.

LIST OF REFERENCE NUMERALS

(14) TABLE-US-00001 turbomachine  1 compressor  1a combustor  1b turbine  1c longitudinal axis  2 hot gas duct  3 jacket ring assembly 20 casing part 21 jacket ring segment 22 seal 23 rotor blade 24 segmented ring 25 receptacle 25a form-fitting element 26 supporting seat 27 retaining ring 28 receptacle 29 projection 30 bore 31 shielding plates 32 segment 35 abutting face 35a segment 36 abutting face 36a segment 40 abutting faces 40a, b connecting line 41 inner circumferential surface 42 outer circumferential surface 43