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US 4,541,775 AGranted
Clearance control in turbine seals
AssigneeUnited Technologies Corporation
InventorEdward J. Hovan
Life of this patent
Estimating the term…
Abstract
A multistage turbine construction in which the cooling flow to the turbine rotor is controlled by cooperating sealing elements carried respectively by the row of vanes and by the rotor with the sealing surface carried by the vanes, the stationary surface being an outwardly sealing surface and the fins cooperating therewith carried by the rotor extending radially inward such that as the turbine rotor cools down during reduced power operation the sealing effect will be increased to reduce the flow of cooling fluid over the rotor surface.
Claims4
In a gas turbine:
- a rotor having at least two disks;
- seal sleeves extending between the disks and supported by flanges on the discs and having sealing elements on their outer periphery;
- one end disk carrying a sealing member having at least one inwardly extending sealing flange;
- a row of vanes adjacent one end disk and at least one other row of vanes between the disks;
- a sealing ring carried by the inner ends of said row of vanes and having an outer sealing surface cooperating with said sealing flange;
- a sleeve extending through the rotor from said sealing member and forming with the sealing member and sealing sleeves a chamber enclosing the inner portions of the rotor disks;
- said sleeve also forming inwardly of the sleeve a pressurized compartment for cooling fluid for the rotor, said cooperating sealing flange and outer sealing surface providing a clearance space for the flow of fluid from the compartment to enter the chamber.
4 more elements
Dependencies are inferred from the claim text.