Seal system for cooling fluid flow through a rotor assembly in a gas turbine engine

Abstract

A sealing system for a rotor assembly in a gas turbine engine is disclosed. The sealing system may include a seal formed from a side block and an upper seal that seals a gap between a radially outward extending first rotor supply channel in a rotor assembly terminating at an inlet of an axially extending second rotor supply channel that is in fluid communication with an internal blade cooling system of a turbine blade. The seal may include components that enhance the flow of cooling fluids over conventional configurations. In another embodiment, the sealing system may include an integrated sealing block configured to seal a gap between adjacent turbine blades at an intersection between the first and second rotor supply channels. The integrated sealing block may be formed from a radially inward extending leg and central body.

Description

FIELD OF THE INVENTION[0001]This invention is directed generally to turbine engines, and more particularly to cooling fluid feed systems in turbine engines.BACKGROUND[0002]Typically, gas turbine engines include a compressor for compressing air, a combustor for mixing the compressed air with fuel and igniting the mixture, and a turbine blade assembly for producing power. Combustors often operate at high temperatures that may exceed 2,500 degrees Fahrenheit. Typical turbine combustor configurations expose turbine blade assemblies to these high temperatures. As a result, turbine blades and turbine vanes must be made of materials capable of withstanding such high temperatures. Turbine blades, vanes and other components often contain cooling systems for prolonging the life of these items and reducing the likelihood of failure as a result of excessive temperatures.[0003]Turbine blades are typically supported by a rotor assembly that enables turbine blades to extend radially outward circum...

AI Technical Summary

Benefits of technology

[0004]This invention is directed to a sealing system for a rotor assembly in a gas turbine engine that enhances the flow of cooling fluids from a rotor assembly to turbine blades. The sealing system may include a seal configured to seal a conduit directing cooling fluids from a cooling fluid source into turbine blades attached to the rotor assembly. In one embodiment, the seal may be formed from a side block and an upper seal that seal a gap between a radially outward extending first rotor supply channel in the rotor assembly terminating at an inlet of an axially extending second rotor supply channel that is in fluid communication with an internal blade cooling system of a turbine blade. The seal may include components that enhance the flow of cooling fluids over conventional configurations. In another embodiment, the sealing system may include an integrated sealing block configured to seal the gap between adjacent turbine blades at an intersection between the first and second rotor supply channels. The integrated sealing block may be formed from a radially inward extending leg and a central body.

Problems solved by technology

Turbine blades, vanes and other components often contain cooling systems for prolonging the life of these items and reducing the likelihood of failure as a result of excessive temperatures.

Conventional cooling channels in the rotor assembly often have cooling fluid leaks between radially extending and axially extending cooling channels that direct cooling fluids to turbine vanes.

Additionally, conventional cooling fluid supply configurations often have choke points that cause pressure losses and unduly restrict cooling fluid flow.

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