초록 ▼

A sealing device is disclosed for maintaining a small positive clearance between the sealing sectors and the turbine blade tips of a turbojet engine. The sealing segments are connected to an internal ring structure and an external ring structure located within the casing of the jet engine. The two r

A sealing device is disclosed for maintaining a small positive clearance between the sealing sectors and the turbine blade tips of a turbojet engine. The sealing segments are connected to an internal ring structure and an external ring structure located within the casing of the jet engine. The two ring structures serve to expand and contract the diameter of the ring formed by the sealing segments in conjunction with the expansion and contraction of the turbine blades for stabilized and transient engine operating modes. The device utilizes ventilating air taken from a stage of the jet engine compressor to cause the radial expansion or contraction of the internal and external rings in direct conjunction with the conditions under which the engine is operating.

대표청구항 ▼

In a turbojet engine having a compressor, an outer casing having a longitudinal axis, and at least one turbine wheel rotatably mounted within the casing, the turbine wheel having a plurality of turbine blades attached thereto, a device for effecting a seal between the turbine blades and the outer ca

In a turbojet engine having a compressor, an outer casing having a longitudinal axis, and at least one turbine wheel rotatably mounted within the casing, the turbine wheel having a plurality of turbine blades attached thereto, a device for effecting a seal between the turbine blades and the outer casing during stabilized and transitory operating modes of the engine, comprising: (a) an annular external ring attached to the outer casing; (b) an internal ring structure having a higher coefficient of thermal expansion than the external ring, attached to the outer casing, the internal ring also having a plurality of longitudinally extending, cantilevered control fingers disposed about its circumference, each control finger having a distal end; (c) a plurality of sealing segments disposed radially outwardly of the tips of the turbine blades, each of the sealing segments having a sealing surface disposed in close proximity to the tips of the turbine blades; (d) first attachment means attaching each of the sealing segments to the internal ring structure; (e) second attachment means attaching each of the sealing segments to the external ring; and, (f) means to direct air from a stage of the compressor onto the external ring and the internal ring structure such that the thermal expansion/contraction of the internal ring structure and the external ring moves the sealing segments radially outwardly/inwardly corresponding to the expansion/contraction of the blade tips due to different operating modes of the engine in order to maintain clearance between the blade tips and the sealing segments, and to prevent excess air leakage between the blade tips and the sealing segments.