Arrangement for internal passive turbine blade tip clearance control in a high pressure turbine
AssigneeRolls-Royce Deutschland Ltd & Co KG
InventorsThomas Wunderlich, Peter Broadhead
Life of this patent
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Abstract
A passive internal control system for rotor blade tip clearance of a high-pressure turbine is based on inner rings that expand in a radial direction under the influence of heat and radially adjust the clearance delimited by liner segments (9) on the casing side. It comprises a radially expandable U-shaped downstream inner ring (10) mounted to inner platforms (7b) of guide vanes (7) on a side where the rotor does not have a static bearing, said ring providing expansion compensation in the axial and peripheral directions and forming a torsion box (8) with struts (13, 14) that absorbs rolling and tilting moments.
Claims8
An arrangement for internal passive turbine blade tip clearance control in a high-pressure turbine in which casing segments located above blade tips of a turbine rotor are supported at front and rear ends of outer platforms thereof by radially movable guide vane segments and concentric inner rings acting upon them whose thermal expansion and contraction behavior matches a load-dependent expansion/contraction of the rotor to provide controlled radial movement of the casing segments to control the blade tip clearance, wherein, an inner platform of each guide vane segment includes front and rear struts forming a U-shaped profile and which are mounted to a U-shaped downstream inner passive ring to form a torsion box which compensates for thermal expansions/contractions in both axial and circumferential directions.
Dependencies are inferred from the claim text.