Turbomachine with blades having blade tips lowering towards the trailing edge
A turbomachine, particularly an aircraft engine, having a rotor, which is mounted rotatably around its longitudinal axis in a stator, and which has at least one row of rotating blades, which is formed by a plurality of rotating blades, is disclosed, wherein the stator has at least one abradable layer, and wherein each rotating blade has a blade tip that is lowered radially inward, at least in sections, proceeding from a leading edge on the side of the rotating blades in the direction of a trailing edge on the side of the rotating blades, and with a blade tip region that extends downstream from the leading edge runs into the abradable layer during operation of the turbomachine.
1. A turbomachine, comprising:
a rotor, which is mounted rotatably around its longitudinal axis in a stator, and which has at least one row of rotating blades, which is formed by a plurality of rotating blades,
the stator having at least one abradable layer,
each rotating blade of the plurality of rotating blades having blade tips comprising a front blade tip region, at least one middle blade tip region, and a trailing blade tip region that are lowered radially inward in sections from a leading edge of the rotating blade to a trailing edge of the rotating blade,
wherein, during operation, the front blade tip region and the at least one middle blade tip region of each of the rotating blades runs into, and is in contact with, the at least one abradable layer, and the trailing blade tip region is radially distanced from the at least one abradable layer, forming a radial gap, whereby formation of a parasitic gap is prevented,
wherein the front blade tip region extends from the leading edge of the rotating blade to the at least one middle blade tip region in a direction towards the trailing edge of the rotating blade,
wherein the trailing blade tip region extends from the at least one middle blade tip region to the trailing edge of the rotating blade, and
wherein radial dimensions of the front blade region are greater than radial dimensions of the at least one middle blade tip region, and the radial dimensions of the at least one middle blade tip region are greater than radial dimensions of the trailing tip region.
2. The turbomachine according to claim 1 , wherein the trailing blade tip region of each of rotating blades of the plurality of rotating blades terminate downstream radially inward relative to a side wall structure on the stator side.
3. The turbomachine according to claim 2 , wherein the front blade tip region, the at least one middle blade tip region, and the trailing blade tip region of the blade tips comprise linearly adjacent regions with different angular positions relative to one another.
4. The turbomachine according to claim 2 , wherein one of the front blade tip region, the at least one middle blade tip region, and the trailing blade tip region of the blade tips comprise an arc-shaped region.
5. The turbomachine according to claim 2 , wherein the at least one abradable layer is inserted into a peripheral groove on the stator side and is sealed flush with the side wall structure.