Segmented component seal

Abstract

A seal for restricting leakage of a fluid from a first chamber, through a gap between two components, to a second chamber, is provided. A slot is formed in each of the two components. The slots face one another and are open to the gap. Each slot contains a longitudinal axis, an upstream surface proximate the first chamber and a downstream surface proximate the second chamber. Disposed in the slots and spanning the gap is a bridging element. The bridging element contains a sectional profile, transverse to the longitudinal slot axis, that includes a flat central portion disposed between two approximately wave shaped end portions. The bridging element spans the gap between the two components with the end portions disposed in the slots, and the central portion disposed in the gap.

Description

BACKGROUND OF THE INVENTION [0001] 1. Field of the Invention [0002] The invention relates to gas turbine engine components in general, and specifically to a seal for preventing leakage of high pressure air or other fluids between segmented components found in such engines. [0003] 2. Description of the Related Art [0004] As illustrated in FIG. 1, a gas turbine engine 10 comprises one or more forward compressor sections 12, a central combustor section 14 and one or more rearward turbine sections 16. The engine 10 operates by compressing ambient air 18 with the compressors 12, adding fuel upstream of the combustor 14 and burning a fuel-air mixture 20 in the combustor 14. High temperature combustion gases 22 are directed axially rearward from the combustor 14, through an annular duct 24 disposed in the turbines 16. The combustion gases 22 interact with one or more turbine rotors 26 disposed in the duct 24. The turbine rotors 26 are coupled to compressor rotors 28 via concentric shafts 3...

AI Technical Summary

Benefits of technology

[0012] In accordance with the present invention, there is provided a seal for restricting leakage of a high-pressure fluid from a first chamber, through a gap between two adjoining components, to a second chamber.

Problems solved by technology

Because stationary components such as vanes, shrouds, supports and the like are subject to extreme temperature gradients, they can develop cracks due to thermal mechanical fatigue (TMF).

Excessive leakage of the compressor air may cause premature oxidation of the components and can increase the engine's fuel burn.

Assembly damage, misaligned slots, slot surface finish and low compressor air pressure may negatively affect the performance of flat bridging elements.

However, the single loop ends of the Grosjean bridging element offer limited contact pressure with the slot and are subject to compression about their minor axis.

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