Ring seal for a turbine engine

Abstract

Aspects of the invention are directed to a ceramic matrix composite ring seal segment. The ring seal segment according to aspects of the invention includes a relatively simple body that is circumferentially curved. At least a portion of the hot gas path surface of the ring seal segment can be coated with a thermal insulating. material. In one embodiment, each ring seal segment can be operatively connected to a stationary support structure, such as by way of isolation rings. The ring seal segments and / or the isolation rings can be configured so as to restrain the ring seal segments in the axial, radial and / or circumferential directions. The ring seal segments can be attached to the isolation rings so that the support points act opposite the operating pressure loads. Thus, the ring seal segments carry these loads in compression, a strong direction of the CMC fibers.

Description

FIELD OF THE INVENTION[0001]Aspects of the invention relate in general to turbine engines and, more particularly, to ring seals in the turbine section of a turbine engine.BACKGROUND OF THE INVENTION[0002]FIG. 1 shows an example of one known turbine engine 10 having a compressor section 12, a combustor section 14 and a turbine section 16. In the turbine section 16 of a turbine engine, there are alternating rows of stationary airfoils 18 (commonly referred to as vanes) and rotating airfoils 20 (commonly referred to as blades). Each row of blades 20 is formed by a plurality of rotating airfoils 20 attached to a disc 22 provided on a rotor 24. The blades 20 can extend radially outward from the discs 22 and terminate in a region known as the blade tip 26. Each row of vanes 18 is formed by attaching a plurality of vanes 18 to a vane carrier 28. The vanes 18 can extend radially inward from the inner peripheral surface 30 of the vane carrier 28. The vane carrier 28 is attached to an outer c...

AI Technical Summary

Benefits of technology

"The invention is a turbine engine ring seal system that includes a ring seal segment, a forward isolation ring, and an aft isolation ring. The ring seal segment is made of ceramic matrix composite and has a radially inner surface that is concave. The system also includes a thermal insulating material that is recessed from the axial forward and aft ends of the ring seal segment. The forward and aft isolation rings are attached to the stationary support structure and can engage with the ring seal segment. The system helps to improve the sealing performance of the turbine engine and to restrain the movement of the ring seal segment."

Problems solved by technology

Such active cooling systems are usually complicated and costly.

However, there are a number of natural limitations and manufacturing constraints associated with CMC materials.

Such areas are difficult to form in a CMC component using known fabrication techniques.

Further, anisotropic shrinkage during processing can lead to result in de-lamination defects in such areas, which can further reduce the interlaminar tensile strength of the CMC material.

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