초록 ▼

A component support of the turbomachine, in particular an aircraft engine, is described, which includes at least two essentially annular components on the stator side, which are in axial contact with each other and are preferably oriented coaxially to the machine axis, the first component having a p

A component support of the turbomachine, in particular an aircraft engine, is described, which includes at least two essentially annular components on the stator side, which are in axial contact with each other and are preferably oriented coaxially to the machine axis, the first component having a plurality of radial, groove-like recesses, which are laterally overlapped by the second component with its projection-like bearing sections, and an uncontoured support ring surface section being provided between the adjacent bearing sections, a turbomachine also being described.

대표청구항 ▼

1. A component support of a turbomachine, the component support comprising: at least first and second annular components on a stator side of the turbomachine, the first and second annular components in axial contact with each other, the first annular component having a support ring surface, and the

1. A component support of a turbomachine, the component support comprising: at least first and second annular components on a stator side of the turbomachine, the first and second annular components in axial contact with each other, the first annular component having a support ring surface, and the second annular component having a plurality of bearing sections distributed over a circumference, the second annular component being in contact with the support ring surface via the bearing sections distributed over the circumference,the support ring surface having a plurality of radial groove recesses, the recesses have a depth-to-width ratio of 1:5 to 1:20, each bearing section having two side edge areas each overlapping one of the recesses and an uncontoured support ring surface area extending between adjacent bearing sections, the uncontoured support ring surface continuing an original contour of the support ring surface. 2. The component support as recited in claim 1 wherein the recesses have a depth-to-width ratio of 1:10. 3. The component support as recited in claim 1 wherein the recesses have a total width 0.25 times to twice a width of the bearing sections. 4. The component support as recited in claim 1 wherein the recesses each have different transition radii in a transition area to the uncontoured support ring surface regions and to the support ring surface sections accommodating the bearing sections. 5. The component support as recited in claim 4 wherein the transition radii correspond to 0.1 times to 1 times a base radius of the recesses. 6. The component support as recited in claim 1 wherein the recesses each have same transition radii in the transition area to the uncontoured support ring surface regions and to the support ring surface sections accommodating the bearing sections. 7. The component support as recited in claim 6 wherein the transition radii correspond to 0.1 times to 1 times a base radius of the recesses. 8. The component support as recited in claim 1 wherein transition areas from the recesses to the uncontoured support ring surface regions and to the support ring surface sections accommodating the bearing sections are designed as chamfers or edges. 9. The component support as recited in claim 1 wherein a base radius of the recesses is interrupted by a flat spot. 10. The component support as recited in claim 1 wherein the first and second stator-side components are oriented coaxially to each other. 11. The component support as recited in claim 1 wherein the first and second stator-side components are provided with a rotationally symmetrical design. 12. A turbomachine comprising a component support as recited in claim 1. 13. A component support of a turbomachine, the component support comprising: an annular housing on a stator side of the turbomachine;an intermediate turbine housing on the stator side;the annular housing and the intermediate turbine housing being in axial contact with each other, the annular housing having a support ring surface, and the intermediate turbine housing having a plurality of bearing sections distributed over a circumference, the intermediate turbine housing being in contact with the support ring surface via the bearing sections distributed over the circumference, the bearing sections being projections extending radially from the outside of the intermediate turbine housing, the annular housing and the intermediate turbine housing being oriented rotationally symmetrically and coaxially to a machine axis of the turbomachine;the support ring surface having a plurality of radial groove recesses, the recesses have a depth-to-width ratio of 1:5 to 1:20, each bearing section having two side edge areas each overlapping one of the recesses and an uncontoured support ring surface area extending between adjacent bearing sections, the uncontoured support ring surface continuing an original contour of the support ring surface.