Sealing element of an axial turbomachine
The present invention relates to a sealing element ( 100 ) of an axial turbomachine for the sealing of regions at or in at least two static components of the turbomachine, wherein the components can be moved axially relative to one another. The sealing element ( 100 ) has a first radial region ( 1 ) with a first stiffness or rigidity and a second radial region ( 5 ) with a second stiffness or rigidity, wherein the first stiffness and the second stiffness are different from one another, and the sealing element ( 100 ) is configured as segmented in the peripheral direction of the turbomachine.
1. A sealing element of an axial turbomachine for the sealing of regions at or in at least two static components of the turbomachine against flow media, wherein the components can move axially relative to one another due to thermal expansion,
consisting essentially of:
the sealing element having an inner radius, an outer radius and segmented in a peripheral direction in at least two segments, each segment having an arc length, the arc length having a curvature about a mid-point angle, the sealing element further having a first radial region, lying radially inward at least at inner radius, with a first stiffness or rigidity and a second radial region, lying radially outward at most at outer radius with a second stiffness or rigidity, wherein the first radial region is spiral-shaped with a first distal end curved inwardly thereon, the second radial region comprising a sealing surface and a diagonal transition region between the first radial region and the sealing surface, the diagonal transition region extending in an axial and radial direction offsetting the first radial region axially from the sealing surface, wherein the first stiffness and the second stiffness are different from one another, the first stiffness being greater than the second stiffness and the first radial region is configured and arranged for attachment in a static component of the turbomachine, the sealing surface having a second distal end, the sealing surface and second distal end aligned perpendicular in an axial direction, the sealing surface further configured and arranged to form a seal against a flow media.
2. The sealing element according to claim 1 , wherein the first radial region is configured and arranged for attachment in a groove or at a web in a static component of the turbomachine.
3. The sealing element according to claim 1 , wherein the first radial region is configured and arranged for sealing engagement at a seal support of an inlet lining.
4. The sealing element according to claim 1 , wherein the sealing surface of the sealing element is configured and arranged for sealing engagement at a guide vane suspension on the housing of the turbomachine.
5. The sealing element according to claim 1 , wherein the regions to be sealed are disposed in a high-pressure turbine region and/or in a low-pressure turbine region of the turbomachine.
6. The sealing element according to claim 1 , wherein the regions to be sealed are disposed in the housing of the turbomachine between a high-pressure turbine region and a low-pressure turbine region.
7. The sealing element according to claim 1 , wherein the regions to be sealed are disposed between a combustion chamber on one side and a high-pressure turbine region or high-pressure compressor region on the other side.