Rotor shroud assembly
AssigneeROLLS-ROYCE plc
InventorsMichael C. Roberts, John F. Leonard
Life of this patent
Estimating the term…
Abstract
In a gas turbine engine tip clearance between rotor blades and an encircling shroud liner is controlled by moving the shroud liner radially to match the thermal and centrifugal growth of the rotor assembly. The shroud liner segments are suspended between two axially displaced control rings located in a passageway carrying air ducted from the compressor. One control ring responds very quickly to changes in gas temperature corresponding to centrifugal growth and blade thermal growth. The other ring responds very much more slowly and corresponds to the thermal growth of the disc. The shroud liner segments are suspended from the control rings to adopt a position that constitutes the average between the growth positions of the two control rings.
Claims13
A gas turbine engine rotor seal for surrounding a rotor assembly of circumferentially spaced blades, each having a radial tip, comprising:
- a plurality of arcuate shroud liner segments encircling the rotor assembly, each segment being mounted for radial movement and having a radially inner surface spaced from the tips of said blades by a pre-determined clearance,
- a first control ring having a relatively rapid radial response to thermal change,
- a second control ring having a relatively slow radial response to thermal change,
- mounting means including a support member supporting each of the shroud segments, each support member being coupled to the first and second control rings and each of the shroud segments, whereby the radial position of the shroud segments is continuously controlled by the thermal expansion of the first and second control rings in combination.
Dependencies are inferred from the claim text.