EP2464831B1 - Fastening means for a guide blade ring of a turbomachine - Google Patents

Description

The invention relates to a turbomachine, in particular a gas turbine, with a housing and at least one vane ring, the outer shroud is divided by dividing lines into segments.

Such a turbomachine is for example from the DE 198 07 247 C2 known. The vane rings are mounted in the region of their outer shroud with bearing pins on the housing of the turbomachine, wherein the segments of the vane ring are radially freely movable in the region of the outer shroud. Such storage is also referred to as storage centering. The bearing pin absorbs all transmitted from the vane ring on the housing forces, especially in the circumferential direction and axial direction. Another turbomachine is out US2903237 known. The invention has for its object to provide an improved attachment of a vane ring on the housing of the turbomachine, which allows a radial mobility of the vane ring segments while low load on the fasteners.

The object of the invention is solved by the features of claim 1. Further advantageous embodiments of the invention are given in the dependent claims.

According to the invention, a turbomachine of the abovementioned type is provided, wherein the outer shroud of the vane ring is fastened to the housing via a first fastening element for axial force absorption and a second fastening element for circumferential force absorption independent of the first fastening element, and wherein the first and the second fastening element for the segments of the outer Shroud allow a game in the radial direction.

In this way, the Axialkraftaufnahme and the Umfangsskraftaufnahme via separate, independent fasteners. The load on the fasteners is thereby reduced, and the fasteners can be optimally designed for their respective function. Axial force and circumferential force are orthogonal to each other, allowing for independent force absorption while simultaneously applying forces in the radial direction are not received by the fasteners, whereby a clearance in the radial direction for the vane ring is made possible.

According to a preferred embodiment, the fastening element for circumferential force absorption is formed by a substantially annular, radially inwardly projecting housing component, wherein first slots and / or first lugs are provided in the housing component, which project with second lugs or second slots in a radially outwardly projecting, Peripheral force-transmitting component of the outer shroud engage in such a way that the vane ring is fixed in the circumferential direction and the second nose or the second slot has a play in the radial direction. This allows a simple geometry of the peripheral force transmitting components and thus the smallest possible space required. By a symmetrical or asymmetrical arrangement of the lugs and slots in the circumferential direction, the installation position of the vane ring can be determined.

It is possible that the fastening element for Axialkraftaufnahme arranged in the direction of force behind an axial force transmitting component of the outer shroud. This allows the transmission of compressive forces on the fastener.

Preferably, the axial force is transmitted via a plurality of separate contact surfaces between the vane ring and the fastening element for Axialkraftaufnahme. In this way, the friction between the axial force receiving fastener and the vane ring can be reduced.

Preferably, the fastening element for Axialkraftaufnahme is annular and forms a positive connection with the housing. This allows, for example, a rotationally symmetrical embodiment of the fastener for Axialkraftaufnahme.

The positive connection can be formed by a mounting extension on the housing and a groove in the annular fastener for Axialkraftaufnahme.

Preferably, the inner radius of the mounting extension is greater than the outer radius of the outer shroud. This allows a mounting of the turbomachine in the axial direction.

According to a further preferred embodiment, a plurality of fastening elements are provided for axial force transmission, which are arranged in the direction of force in front of an axial force transmitting component of the vane ring. In this way, the axial force is transferred from the vane ring via tensile forces on the fasteners.

Preferably, the fastening elements for axial force transmission are radially elastic elements. This ensures the mobility of the vane ring segments in the radial direction.

The fastening elements for Axialkraftübertragung can be positively secured to the housing and the vane ring.

The preferably positive connection between the fastening element for Axialkraftaufnahme and the housing may be secured by a fuse wire. In this way, unintentional release of the connection between the axial force-receiving fastener and the housing is prevented.

• Figur 1 einen Leitschaufelkranz;
• Figur 2 eine Schnittansicht einer Strömungsmaschine mit zwei Leitschaufeln und einer Laufschaufel;
• Figur 3 eine Schnittansicht einer Strömungsmaschine mit einer radial beweglichen Leitschaufel;
• Figur 4 eine Schnittansicht einer Strömungsmaschine gemäß einer ersten Ausführungsform der Erfindung;
• Figur 5 ein Leitschaufelkranzsegment der Strömungsmaschine gemäß Figur 4; und
• Figur 6 eine Strömungsmaschine gemäß einer zweiten Ausführungsform der Erfindung in einer Schnittansicht.

Further features and advantages of the invention will become apparent from the following description and from the following drawings, to which reference is made. In the schematic drawings show:

• FIG. 1 a vane ring;
• FIG. 2 a sectional view of a turbomachine with two vanes and a blade;
• FIG. 3 a sectional view of a turbomachine with a radially movable vane;
• FIG. 4 a sectional view of a turbomachine according to a first embodiment of the invention;
• FIG. 5 a vane ring segment of the turbomachine according to FIG. 4 ; and
• FIG. 6 a turbomachine according to a second embodiment of the invention in a sectional view.

In the FIGS. 1 to 3 a turbomachine 10 with a vane ring 12 is shown. This has an outer shroud 16, which is divided by parting lines in individual segments 14. As in FIG. 1 and FIG. 3 is indicated by the double-sided arrows, the segments 14 of the outer shroud 16 can move in the radial direction.

FIG. 2 shows a portion of the turbomachine 10 with two vane rings 12 and a blade 18. The two vane rings 12 are connected by a honeycomb carrier 20.

FIG. 3 shows a vane ring 12 between two blades 18. The vane ring. 12 and the associated honeycomb carrier 20 are mounted in a housing 22 of the turbomachine 10, wherein the (in FIG. 3 not shown) attachment for the segments 14 of the outer shroud 16 of the vane ring 12 allows clearance in the radial direction for memory-centered attachment. The outer shroud 16 of the vane ring 12 can move in the radial direction between the radially inwardly and outwardly located positions shown with dashed lines.

With the inner shroud 17 of the vane ring 12, the various vanes are preferably integrally connected.

FIG. 4 shows a first embodiment of the attachment of the vane ring 12 on the housing 22 of the turbomachine 10. A fastening element 24 for circumferential force receiving is a substantially annular, radially inwardly projecting housing member 26 in which a plurality of slots are provided. The vane ring 12 has a radially outwardly projecting component 28 in the region of the outer cover strip 16, which forms lugs which are positively connected to the slots in the housing member 26 and fix the vane ring 12 in the circumferential direction. It is of course also possible that the housing member 26 has lugs which engage in slots in the component 28 of the vane ring 12, or that on both the housing member 26 and the component 28 of the vane ring 12 lugs and slots are provided which mutually engage in order to establish the positive connection.

A force acting on the vane ring 12 in the circumferential direction is transmitted from the component 28 via the interlocking lugs and slots on the housing member 26, which receives the circumferential force and thus fixes the vane ring 12 in the circumferential direction in the housing 22 of the turbomachine 10.

Axially acting forces are not absorbed by the fastener 24 for circumferential force absorption. The circumferential force receiving member 24, taken by itself, permits movement of the vane ring 12 in one or both axial directions.

A fastening element 30 for axial force absorption is arranged in the force direction behind an axial force-transmitting component 32 of the vane ring 12. The direction of the axial force has in the embodiment shown from left to right. In this arrangement, the axial force is transferred from the vane ring 12 via the axial force transmitting member 32 to the fastener 30 for axial force absorption as a compressive force.

The axial force transmitting member 32 has a plurality of separate contact surfaces 34, via which the axial force between the vane ring 12 and the fastening element 30 is transmitted to Axialkraftaufnahme. In FIG. 5 a segment 14 of the shroud 16 of the vane ring 12 is shown, which has a respective contact surface 34 at its ends lying in the circumferential direction. Of course, it is also possible that the contact surface 34 extends over the entire circumference of the vane ring 12.

For the contact surfaces 34, a special surface structure or a special coating, such as armor, be provided to keep the friction between the vane ring 12 and the fastener 30 for Axialkraftaufnahme as low as possible.

The slotted for mounting on the circumference fastener 30 for Axialkraftaufnahme is annular and has a running at its outer radius in the circumferential direction groove with which it is positively connected to a mounting extension 36 which is formed on the housing 22. The inner radius of the mounting extension 36 is greater than the outer radius of the vane ring 12. In this way, the guide vane ring 12 can be inserted during assembly of the turbomachine 10 in the axial direction in the closed housing 22.

When assembling the turbomachine 10, after insertion of the vane ring 12 in housing 22, the annular mounting member slotted for mounting on the circumference 30 is used for axial force on the mounting extension 36 of the housing 22, wherein the mounting extension 36 engages positively in the groove of the fastener 30.

The inner radius of the axial force receiving member 30 is smaller than the outer radius of the diaphragm ring 12. Thus, the vane ring 12 contacts the contact surfaces 34 on the axial force receiving member 30 and the vane ring 12 is fixed in its axial position by the fastener 30.

In the embodiment shown, the axial force transmitting member 32 is in the opposite direction of the axial force on the fastening element 24 for circumferential force absorption. In this way, the axial position of the vane ring 12 by the two fastening elements 24, 30 for Umfangsskraftaufnahme and Axialkraftaufnahme exactly defined, the axial force acting during normal operation of the turbomachine due to their direction is taken only by the fastener 30 for Axialkraftaufnahme.

The two fastening elements 24, 30 for circumferential force absorption and Axialkraftaufhahme together form a guide for the components 28, 32 of the segment 14 of the outer shroud 16 of the vane ring 12, which allows movement of the segment 14 in the radial direction.

The positive connection between the fastening element 30 for Axialkraftaufnahme and the mounting extension 36 of the housing 22 is secured by a fuse wire 38. It is also possible that the fastening element 30 is secured directly to the housing 22 by the safety wire 38 for Axialkraftaufhahme.

A second embodiment of the fastening element 30 for Axialkraftaufhahme is in FIG. 6 shown. The fastening element 30 for Axialkraftaufnahme is arranged in this embodiment in the direction of force in front of an axial force transmitting member 32 of the vane ring 12, whereby tensile forces between the axial force transmitting member 32 and the fastener 30 can be transmitted to Axialkraftaufnahme.

One or more fastening elements 30 are provided for axial force absorption per segment 14 of the outer shroud of the vane ring 12. The fasteners 30 are positively secured to the housing 22 and the vane ring 12. On the housing 22, the positive connection with the fastening element 30 is secured by a locking wire 38. The positive connection between the fastener 30 and the vane ring 12 is secured by a clamp 40, which may be part of the honeycomb support 20 or a separate part.

The fastening elements 30 for Axialkraftaufnahme are radially elastic elements. The attached to the vane ring 12 end of the fastening element 30 for Axialkraftaufnahme can move along a circular path around the attached to the housing 22 end of the fastener 30, wherein at small angles, the movement is approximately linear, takes place in the radial direction.

It is possible that the fastening elements 30 for axial force absorption are completely separate components. Alternatively, a plurality and in particular all fastening elements 30 may be connected to one another at the end fastened to the housing 22, whereby a substantially annular fastening element 30 is formed, with a plurality of radially elastic extensions which are fastened to the guide vane ring 12 at their respective ends.

In this embodiment, regardless of the axial force, a substantially frictionless radial movement of the segments 14 of the vane ring 12 is possible. Since no fasteners 24, 30 are arranged in the direction of force behind the vane ring, a simple assembly in the axial direction is possible.

The radially inwardly projecting housing part 26, which forms the fastening element 24 for circumferential force absorption, and the peripheral force transmitting component 28 of the vane ring 12 is similar in design and function to in FIG. 4 described embodiment.

Claims (4)

1. A turbomachine (10), particularly a gas turbine, with a housing (22) and a guide vane ring (12) whose outer shrouding band (16) is subdivided by separating joints into segments (14), wherein the outer shrouding band (16) is secured to the housing (22) by means of a first fastening element (30) for absorbing axial forces and a second fastening element (24), which is independent of the first fastening element (30), for absorbing circumferential forces, wherein the first and the second fastening element (24, 30) provide a play in the radial direction for the segments (14) of the outer shrouding band (16), wherein the first fastening element (30) for absorbing axial forces has an annular shape and forms a form-fitting connection with the housing (22), wherein the form-fitting connection is formed by a mounting extension (36) on the housing (22) and a groove in the annular fastening element (30), which extends in the circumferential direction, for absorbing axial forces, and wherein the fastening element (30) for absorbing axial forces is arranged, as seen in the direction of force, behind an axial force-transmitting component (32) of the outer shrouding band (16), characterized in that the axial force is transmitted via a plurality of mutually separated contact surfaces (34) between the guide vane ring (12) and the fastening element (30) for absorbing axial forces.
2. The turbomachine (10) according to claim 1, characterized in that the second fastening element (24) for absorbing circumferential forces is formed by an essentially annular, radially inwardly protruding housing component (26), wherein first slots and/or first lugs are provided in the housing component (26) that engage with second lugs and/or second slots in a radially outwardly protruding, circumferential force-transmitting component (28) of the outer shrouding band (16) such that the guide vane ring (12) is fixed in place in the circumferential direction and the second lug or the second slot has a play in the radial direction.
3. The turbomachine (10) according to claim 1, characterized in that the inner radius of the mounting extension (36) is greater than the outer radius of the outer shrouding band (16).
4. The turbomachine (10) according to any one of the preceding claims, characterized in that the form-fitting connection between the fastening element (30) for absorbing axial forces and the housing (22) is secured by a locking wire.

Images