时尚汽车_汽车生活移动版

CROSS REFERENCE TO RELATED APPLICATIONS

This application claims priority to and the benefit U.S. Provisional Patent Application No. 61/778,286, filed on Mar. 12, 2013, the disclosure of which is now expressly incorporated herein by reference.

The present invention relates to a blade track assembly for a gas turbine engine, and more particularly to a blade track assembly having low stress attachment configurations.

Turbine blade tracks. sometimes ailed turbine shroud seals are designed to provide a circumferential flow path around a turbine rotor. The inner surface of the blade track is typically positioned as close to the tips of the turbine rotor blades as possible without actually engaging during operation. The clearance between the tip of the blade and the blade track is minimized so as to provide higher operating efficiencies as understood by those skilled in the art. The inner surface of the blade tracks operate at the temperature of the hot exhaust gases flowing therethrough which can be well in excess of 2000° F. In addition to high temperatures, the gas path also operates at elevated pressures relative to ambient conditions. The blade tracks are supported through connections to static structure radially outward and opposite the gas path side of the inner surface. The blade track connections can be placed under high stress due to high thermal and high pressure gradients across the blade track and over time a mechanical failure can occur. Some existing blade track systems have various shortcomings, drawbacks, and disadvantages relative to certain applications. Accordingly, there remains a need for further contributions in this area of technology.

One embodiment of the present invention is a unique turbine blade track configuration and assembly. Other embodiments include unique apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engine power systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the following description and drawings.

The description herein makes reference to the accompanying drawings wherein like reference numerals refer to like parts throughout the several views, and wherein:

FIG. 1 is an elevational view of one embodiment of a blade track, as shown somewhat schematically in a circumferential viewing direction;

FIG. 2 is an elevational view of the blade track illustrated in FIG. 1, as shown somewhat schematically in an axial viewing direction;

FIG. 3 is an elevational view of another embodiment of a blade track, as shown somewhat schematically in an axial viewing direction;

FIG. 4 is an elevational view of another embodiment of a blade track, as shown somewhat schematically in a circumferential viewing direction;

FIG. 5 is an elevational view of another embodiment of a blade track, as shown somewhat schematically in a circumferential viewing direction;

FIG. 6 is an elevational view of one embodiment of a preform structure used in the formation of a blade track, as shown somewhat schematically in a circumferential viewing direction;

FIG. 7 is an elevational view of another embodiment of a preform structure used in the formation of a blade track, as shown somewhat schematically in a circumferential viewing direction;

FIG. 8 is an elevational view of a core used in the formation of the preform structure illustrated in FIG. 6, as shown somewhat schematically in a circumferential viewing direction;

FIG. 9 is an elevational view of a core used in the formation of the preform structure illustrated in FIG. 7, as shown somewhat schematically in a circumferential viewing direction;

FIG. 10 is an elevational view of another embodiment of a preform structure used in the formation of a blade track, as shown somewhat schematically in a circumferential viewing direction;

FIG. 11 is an elevational view of one embodiment of a blade track assembly including the blade track shown in FIG. 1, as shown somewhat schematically in a circumferential viewing direction;

FIG. 12 is an elevational view of the blade track assembly illustrated in FIG. 11, as shown somewhat schematically in an axial viewing direction; and

FIG. 13 is an elevational view of one embodiment of a partially-constructed turbine engine blade track assembly, as shown somewhat schematically in an axial viewing direction.

For the purposes of promoting an understanding of the principles of the invention, reference will now be made to the embodiments illustrated in the drawings and specific language will be used to describe the same. It will nevertheless be understood that no limitation of the scope of the invention is hereby intended. Any alterations and further modifications in the described embodiments, and any further applications of the principles of the invention as described herein are contemplated as would normally occur to one skilled in the art to which the invention relates.