EP3293369A1 - Cladding element for a mid-turbine housing - Google Patents

Abstract

The invention relates to a cladding element of a hot gas leading channel of a turbine intermediate housing of a gas turbine, in particular aircraft gas turbine, with a first, axially front connection section (12, 112), a second, axially rearward terminal portion (14; 114), a center portion (16; 116) connected to said first terminal portion (12; 112) and said second terminal portion (14; 114) and disposed therebetween in the axial direction (AR), said central portion (16; Has channel facing outer surface (20; 120), and wherein the first connection section (12; 112) can be coupled to axially front components of the turbine intermediate housing or the gas turbine, and the second connection section (14; 114) can be coupled to axially rear components of the turbine intermediate housing or the gas turbine. According to the invention, it is proposed that the central portion (16; 116) has at least one first reinforcing portion (24; 124) projecting away from the channel, extending substantially rectilinearly between an axially forward end (28) and an axially rearward end, at least one of the two the axial end is followed by a second reinforcing portion (26; 126) projecting away from the channel, which is inclined or curved relative to the rectilinear course of the first reinforcing portion (24; 124), the first reinforcing portion (24; 124) and the second reinforcing portion (24; 26; 126) together form a reinforcing element (22; 122), wherein the entire reinforcing element (22; 122) is arranged within the outer surface (20; 120) of the central section (16; 116), in particular such that the reinforcing element (22; 122 ) to the first terminal portion (12; 112) and the second terminal portion (14; 114) has a distance.

Description

The present invention relates to a cladding element of a hot gas duct of a turbine intermediate housing of a gas turbine, in particular an aircraft gas turbine, having a first, axially front connection section, a second, axially rear connection section, a central section which is connected to the first connection section and the second connection section and in the axial direction is arranged between these, wherein the central portion has an outer surface facing away from the channel, and wherein the first connection portion with axially front components of the gas turbine can be coupled and the second connection portion with axially rear components of the gas turbine can be coupled.

Directional details such as "axial" or "axial", "radial" or "radial" and "circumferential" are basically related to the machine axis of the turbine intermediate housing or the gas turbine, unless the context explicitly or implicitly something else results.

The term "turbine intermediate housing" in the context of the present invention comprises housings, which adjoin the housing of a turbine stage in the axial direction of the gas turbine, are preferably arranged between two turbine stages, the gas turbine, depending on the design, may have two or more turbine stages. In particular, the term "turbine housing" thus also includes a so-called "turbine center frame".

The provision of stiffening ribs on components, in particular lining elements, turbine housings or gas turbines is known. In this case, known stiffening ribs generally run in the axial direction or in the circumferential direction. The known stiffening ribs are coupled to edge portions of the respective component, so that the stiffening ribs generally extend in the axial direction or in the circumferential direction along the entire component. Although a high rigidity of the components can be achieved by means of stiffening ribs of this type, high thermally induced stresses are generated on the component as a result of the connection of the stiffening ribs to the edge sections. Furthermore, the material requirement is high in such known stiffening ribs.

It is therefore an object of the invention to provide a cladding element for an annular channel of a turbine intermediate housing, in which a sufficient use of material Rigidity is achieved and thermally induced stresses can be reduced.

To achieve this object, it is proposed that the central portion has at least one in the direction away from the channel protruding first reinforcing portion which extends substantially rectilinearly between an axially front end and an axially rear end, wherein at least one of the two axial ends in a direction adjoining the second reinforcing section which is inclined or curved relative to the rectilinear course of the first reinforcing section, wherein the first reinforcing section and the second reinforcing section together form a reinforcing element, the entire reinforcing element being disposed within the outer surface of the central section, in particular such that the Reinforcing element to the first connection portion and the second connection portion has a distance.

The first reinforcing section, which extends substantially rectilinearly between the axially front end and the axially rear end, thus has a main extension direction with an axial direction component, that is to say a directional component which is oriented in the axial direction of the turbomachine. Preferably, the main extension direction of the first reinforcing section has no or only one circumferential direction component which is smaller than the axial direction component, that is to say a directional component in the circumferential direction of the turbomachine.

The arrangement of two reinforcing portions, which together form the reinforcing member, wherein the second reinforcing portion is formed inclined or curved to the first rectilinear reinforcing portion, enables a material-saving configuration. Furthermore, constraints can be prevented by the distances to the terminal sections, so that high thermally induced voltages can be avoided.

A free end of the first reinforcing portion that is not connected to a second reinforcing portion may be tapered at least in the radial direction such that the first reinforcing portion is substantially continuous with the outer surface of the central portion. The free end of the first reinforcing portion thus forms a kind of seamless or fluid transition between the first reinforcing portion and the outer surface of the central portion.

The second reinforcing section may be substantially symmetrical with respect to the first reinforcing section connected thereto, in particular such that the first reinforcing section and the second reinforcing section form a Y-shaped reinforcing element. In this case, the free ends of the second reinforcing section can in particular be oriented such that they point in the direction of bearing points of the lining element at which the lining element is connected to other structures of the turbine intermediate housing or of the gas turbine. The symmetrical design, in particular in the manner of a Y, is also particularly well suited to optimally distribute acting forces and stresses.

The second reinforcing portion may have two free ends that are tapered at least in the radial direction such that the second reinforcing portion merges substantially continuously into the outer surface of the central portion. Thus, the entire reinforcing element, when formed, for example, by a first reinforcing section and by a second reinforcing section, has three free ends that merge substantially seamlessly or fluently into the outer surface of the central section.

The first reinforcing section can be arranged substantially centrally with respect to the circumferential direction on the central section. In particular, the central region of the central portion is subject to the greatest deformations, in particular bending stresses, by pressure differences between the hot gas flowing in the annular channel and the secondary air system located outside the annular channel. Accordingly, this central region is preferably to reinforce, in order to counteract a radial Ausbuchten or bending of the central portion.

The first connection portion, the second connection portion and the central portion may be curved at least in the circumferential direction. On the one hand, the curvature serves to adapt the lining element with regard to the assembled state of a turbine intermediate housing. As a rule, a plurality of adjacent cladding elements form the cladding of the annular channel, so that it is advantageous if the individual cladding elements already have a corresponding curvature.

The reinforcing element may have in the circumferential direction at a distance to lateral edge portions of the cladding element, which protrude at least in the radial direction of the outer surface of the central portion. Such edge sections usually form the Transition to a circumferentially adjacent component, in particular an adjacent cladding element. If the reinforcing element also has a spacing from these edge sections, in addition to the distance to the first connection section and to the second connection section, the entire reinforcement element is provided only in the region of the (outer) surface of the central section. In this way, the central portion can be reinforced in the desired manner, without thermally induced stresses being transferred to a great extent to the edge portions or the two connection portions.

At each end of the first reinforcing section, a respective second reinforcing section may be arranged. This results in a kind of double Y or a kind of stick figure without a head with spread legs and arms outstretched. In this case, the first reinforcing section is arranged centrally and the two second reinforcing sections each have two arms which extend away from the first reinforcing section.

The entire reinforcing element may be made integral with the central portion of the trim element. This can be achieved, for example, by means of a corresponding casting mold in which the reinforcing element has already been taken into account. Preferably, the cladding element is produced by means of a casting process. Alternatively, however, the component could also be generated entirely or partially by a generative process. For example, the reinforcing element can be applied by laser deposition welding on the outer surface of the central portion.

The invention also relates to a turbine intermediate housing for a gas turbine, in particular aircraft gas turbine, with a hot gas leading annular channel, wherein the annular channel has radially outwardly a plurality of cladding elements described above. In this case, the cladding elements can be arranged adjacent to each other in the circumferential direction. Alternatively, also above-described trim elements and differently configured cladding elements can be used alternately in the circumferential direction.

• Fig. 1 zeigt in einer vereinfachten Perspektivdarstellung ein Verkleidungselement mit Verstärkungselement.
• Fig. 2 zeigt das Verstärkungselement der Fig. 1 in vergrößerter Perspektivdarstellung.
• Fig. 3 zeigt in einer vereinfachten Perspektivdarstellung ein weiteres Verkleidungselement mit einem anderen Verstärkungselement.
• Fig. 4 zeigt das andere Verstärkungselement der Fig. 3 in vergrößerter Perspektivdarstellung.

The invention will be described below by way of example and not limitation with reference to the attached figures.

• Fig. 1 shows in a simplified perspective view of a cladding element with reinforcing element.
• Fig. 2 shows the reinforcing element of Fig. 1 in enlarged perspective view.
• Fig. 3 shows in a simplified perspective view another cladding element with another reinforcing element.
• Fig. 4 shows the other reinforcing element of Fig. 3 in enlarged perspective view.

In Fig. 1 is shown in a simplified and schematic perspective view of a cladding element 10 of a turbine intermediate case, not shown. The present example according to Fig. 1 shows a so-called inner duct panel, so a cladding element, which is designed to limit the hot gas channel of the turbine intermediate housing radially inside. Fig. 1 shows the hot gas duct facing away from the surface of the cladding element, which points in the installed state substantially radially inward to the machine axis of the gas turbine. The cladding element 10 has a first, axially front connection section 12 and a second, axially rear connection section 14. These two connection sections 12, 14 serve to connect the lining element 10 with axially adjoining components of the turbine intermediate housing or an associated gas turbine. Along the axial direction AR, a central section 16 extends between the first connection section 12 and the second connection section 14. In the circumferential direction UR, the central section 16 is delimited by edge sections 18. The central section 16 has an outer surface 20. The outer surface 20 is bounded in particular by the two edge sections 18, which project radially from the outer surface 20, and by the two connecting sections 12, 14.

Thus, the central portion 16 is not greatly deformed by pressure differences between the flowing in the annular channel hot gas and the outside of the annular channel secondary air system, in particular bulged or bent, a reinforcing element 22 is provided. The reinforcing member 22 includes a first reinforcing portion 24 and a second reinforcing portion 26. As shown in FIG Fig. 1 can be seen, the reinforcing element 22 is arranged with respect to the circumferential direction in a central or central region of the cladding element 10 and the central portion 16. In this case, the reinforcing element 22 both at a distance from the first connection portion 12 and a distance from the second connection portion 14. Further, the cladding element 22 is also spaced from the edge portions 18. In other words can also be said that the reinforcing element 22 is disposed completely within the outer surface 20 of the central portion 16. The reinforcing element 22 is thus not in direct contact with the connecting sections 12, 14 or the edge sections 18.

In Fig. 2 the reinforcing element 22 is shown enlarged. The first reinforcing portion 24 extends along the axial direction along the outer surface 20 of the central portion 16. The first reinforcing portion 24 has a free end 28. This free end 28 is tapered at least in the radial direction RR. In other words, the free end 28 of the first reinforcing section 24 has a wedge shape. This enables a seamless transition from the first reinforcing element 24 into the outer surface 20 of the central section 16.

The second reinforcing portion 26 includes two arms 30 a and 30 b disposed inclined to the first reinforcing portion 24. In the present embodiment, the reinforcing element 22 thus has a kind of Y-shape. The second reinforcing section 26 has two free ends 32a, 32b. These free ends 32a, 32b, too, are tapered in the radial direction. As a result, a seamless or flowing transition to the outer surface 20 of the central portion 16 is also made possible. The reinforcing element 22 or its reinforcing sections 24, 26 protrude in the radial direction from the central section 16 or from the outer surface 20. The reinforcing portions 24, 26 form a kind of ribs which reinforce the central portion 16 with respect to bending stresses. All of the reinforcing portions 24, 26 have a respective upper surface 34 and side surfaces 36 inclined or curved from the upper surface to the outer surface 20 of the central portion 16. The surface 34 has at the respective free ends 28, 32a, 32b each have a maximum width B. In this case, the maximum width is provided in particular in the region of the transition from the corresponding reinforcing section 24, 26 to the outer surface 20.

The continuous transition from the outer surface into the reinforcing portions 24, 26 allows easy manufacture of the central portion 16 and the trim element 10 by means of a casting process. Due to the continuous transition in the region of the free ends 28, 32 a, 32 b, the reinforcing element 22 is formed only within the outer surface 22 without direct contact with other, in particular structurally bearing components, such as the connection sections 12, 14 or the edge sections 18.

In Fig. 3 a slightly differently designed cladding element 110 is shown, namely a so-called Outer Duct Panel, so a cladding element, which is designed to limit the hot gas channel of the turbine intermediate housing radially outward. Fig. 3 shows the hot gas duct facing away from the surface of the cladding element, which has in the installed state substantially radially outward to the machine axis of the gas turbine. The trim element 110 likewise comprises a first, axially front connection section 112 and a second, axially rear connection section 114. Also visible are the central section 116 and the edge sections 118. A reinforcing element 122 is arranged in the central section 116. This reinforcing element comprises a first reinforcing section 124 and two second reinforcing sections 126. This reinforcing element 122 is also arranged inside the outer surface 120 of the central section 116. It therefore has a distance to the connection sections 112 and 114 as well as to the edge sections 118.

The reinforcing element 122 is enlarged in FIG Fig. 4 shown. The first reinforcing portion 124 does not have a free end in this embodiment, but is connected to a second reinforcing portion 126 on both sides. The Indian Fig. 4 Axially front (second) reinforcing section 126 has two substantially rectilinear arms 130a and 130b with respective free ends 132a and 132b. The two arms 130a and 130b are inclined relative to the rectilinear first reinforcing section 124.

The in Fig. 4 Axially rear (second) reinforcing section 126 has two curved arms 130c and 130d. These arms 130c and 130d also have free ends 132c and 132d. The above with reference to the Fig. 1 and 2 As regards the tapering configurations of the free ends (wedge shape), the same applies analogously to the free ends 132a, 132b, 132c, 132c. Also, the reinforcing member 122 has an upper surface 134 and inclined or curved side surfaces 136 thereof, which merge into the outer surface 120 of the central portion.

The in the 3 and 4 The differently configured second reinforcing sections 126, one with rectilinear arms 130a, 130b, the other with curved arms 130c, 130d, could also be interchanged. Furthermore, two similar second reinforcement sections 126 could also be connected to the first reinforcement section 124. Finally, it is also conceivable that instead of a second reinforcing portion 26 with rectilinear arms 30a, 30b in the Fig. 1 a second reinforcing section with curved arms ( Fig. 4 ) is trained. With regard to the configuration of the reinforcing element 22, 122 with its reinforcing sections 24, 124, 26, 126, other possibilities not described here may also be considered. It is also conceivable, for example, a combination of curvature and straight course of an arm. In all embodiments, including those which are not shown here, it is advantageous if the free ends of the reinforcing portions are tapered and merge seamlessly into the outer surface of the central portion. Furthermore, further embodiments of a reinforcing element should be provided with a respective distance to the terminal portions and the edge portions of the cladding element.

By means of the cladding element with stiffening element presented here, a sufficient rigidity of the central section or of the cladding element can be achieved with little use of material. Furthermore, the thermally induced stress in the cladding element and in particular in the connecting portions or the edge portions can be kept low because the reinforcing element is not connected directly to these.

LIST OF REFERENCE NUMBERS

• 10, 110 cladding element
• 12, 112 first, axially front terminal portion
• 14, 114 second, axially rear connection section
• 16, 116 central section
• 18, 118 edge section
• 20, 120 outer surface
• 22, 122 reinforcing element
• 24, 124 first reinforcing section
• 26, 126 second reinforcing section
• 28 free end of the first reinforcing section
• 30a 30b, 130a, 130b, 130c, 130d arms of the second reinforcement section
• 32a, 32b, 132a, 132b, 132c, 132d have free ends of the second reinforcing portion
• 34.134 upper surface
• 36, 136 side surface
• B width
• AR axial direction
• RR radial direction
• UR circumferential direction

Claims (10)

Cladding element of a hot gas leading channel of a turbine intermediate housing of a gas turbine, in particular aircraft gas turbine, with
a first, axially front connection section (12, 112),
a second, axially rearward terminal portion (14; 114),
a center portion (16; 116) connected to said first terminal portion (12; 112) and said second terminal portion (14; 114) and disposed therebetween in the axial direction (AR), said central portion (16; Has channel facing outer surface (20; 120), and
wherein the first connection section (12; 112) can be coupled to axially front components of the turbine intermediate housing or of the gas turbine, and the second connection section (14; 114) can be coupled to axially rear components of the turbine intermediate housing or the gas turbine,
characterized in that
the central portion (16; 116) has at least one first reinforcing portion (24; 124) projecting away from the channel, extending substantially rectilinearly between an axially forward end (28) and an axially rearward end, at least one of the two the axial end is followed by a second reinforcing portion (26; 126) projecting away from the channel, which is inclined or curved relative to the rectilinear course of the first reinforcing portion (24; 124), the first reinforcing portion (24; 124) and the second reinforcing portion (24; 26; 126) together form a reinforcing element (22; 122), wherein the entire reinforcing element (22; 122) is arranged within the outer surface (20; 120) of the central section (16; 116), in particular such that the reinforcing element (22; 122 ) to the first terminal portion (12; 112) and the second terminal portion (14; 114) has a distance. Cladding element according to claim 1, characterized in that a free end (28) of the first reinforcing section (24) which is not connected to a second reinforcing section (26), at least in the radial direction (RR) is tapered, such that the first reinforcing section ( 24) merges substantially continuously into the outer surface (20) of the central portion (16). Cladding element according to claim 1 or 2, characterized in that the second reinforcing section (26; 126) relative to the first reinforcing section connected thereto (24; 124) is formed substantially symmetrically, in particular such that the first reinforcing section (24; 124) and the second reinforcing section (26; 126) form a Y-shaped reinforcing element (22; 122). Cladding element according to one of the preceding claims, characterized in that the second reinforcement section (26; 126) has two free ends (32a, 32b; 132a, 132b, 132c, 132d) which are tapered at least in the radial direction (RR), such that the second reinforcing portion (26; 126) merges substantially continuously with the outer surface (20; 120) of the central portion (16; 116). Cladding element according to one of the preceding claims, characterized in that the first reinforcing section (24; 124) is arranged substantially centrally with respect to the circumferential direction (UR) on the central section (16; 116). Cladding element according to one of the preceding claims, characterized in that the first connection section (12; 112), the second connection section (14; 114) and the central section (16; 116) are curved at least in the circumferential direction (UR). Cladding element according to one of the preceding claims, characterized in that the reinforcing element (22; 122) in the circumferential direction (UR) at a distance from lateral edge portions (18; 118) of the cladding element (10; 110), at least in the radial direction (RR) of the outer surface (20; 120) of the central portion (16; 116) protrude. Cladding element according to claim 1, characterized in that at each end of the first reinforcing portion (124), a respective second reinforcing portion (126) is arranged. Cladding element according to one of the preceding claims, characterized in that the entire reinforcing element (22; 122) is made in one piece with the central section (16; 116) of the cladding element (10; 110). Turbine intermediate housing for a gas turbine, in particular an aircraft gas turbine with a hot gas-carrying annular channel, characterized in that the annular channel has a plurality of cladding elements (10, 110) according to one of the preceding claims.

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