Turbine blade clearance control system

Details Turbine blade clearance control system Turbine blade clearance control system

1996-08-07

1998-07-14

Kwon, John T.

Rotary kinetic fluid motors or pumps

With passage in blade, vane, shaft or rotary distributor...

F04D 2938

Patent

active

057794367

ABSTRACT:
Past gas turbine engines have been manufactured with a variety of systems which have attempted to compensate for the varying radial clearance or interface between a tip of a turbine blade and a surrounding shroud. Such systems have engineered in large clearances, utilized special tips on blades and provided abradable structures. The present system controls a radial clearance or an interface or spaced distance between a tip of a blade and a stationary shroud. The system includes an introduction of a cool fluid or a hot fluid flow or a combination of cool fluid and hot fluid into a support case cavity. The flow is controlled by modulating a flow control apparatus and controlling the expansion of a nozzle support case and a stationary shroud relative to the position of the tip of the turbine blade. The system improves efficiency, longevity and operation of the gas turbine engine.

REFERENCES:
patent: 3975901 (1976-08-01), Hallinger et al.
patent: 4416111 (1983-11-01), Lenahan et al.
patent: 4541775 (1985-09-01), Hovan
patent: 5154578 (1992-10-01), Miraucourt et al.
patent: 5169287 (1992-12-01), Proctor et al.

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