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

[0006]The upper seal may contact the side block and may include a radially inner surface that is generally flat and flush with an inner surface forming the second rotor supply channel. With the upper seal being flush with the second rotor supply channel, the upper seal is capable of increasing the cooling fluid flow past the seal and into the second rotor channel towards the turbine blades. The upper seal may include one or more teeth on the upper seal extending radially outward from the upper seal and contacting two turbine blades. The teeth may be used to assist in attaching the seal to the turbine blades and to prevent cooling fluid leakage between the turbine blades and the seal. The seal may include an arm extending axially from the upper seal away from the intersection between the upper seal and the side block. One or more of the teeth may extend radially outward from the arm, and in one embodiment, two teeth may extend radially outward from the arm. One or more of the teeth may form an interference fit in a cavity in each of the two turbine blades to reduce leakage.

[0015]Another advantage of this invention is that the seal may include a curved corner between the axially extending leg and the radially extending central body, thereby further reducing cooling air pressure losses.

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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