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US 4,050,843 AGranted
Gas turbine engines
AssigneeRolls-Royce (1971) Limited
InventorsPeter Richard Needham, Kenneth Richard Langley
Life of this patent
Estimating the term…
Abstract
A seal clearance control device for maintaining a radial clearance between turbine blade tips and the surrounding seal ring. The shroud is controlled by a relatively fast response ring and a relatively slow ring the fast ring serving to control the radial growth of the sealing ring and the slow ring serving to control the radial contraction of the seal ring.
Claims15
A gas turbine engine including a rotor having a relatively slow thermal growth response rate disposed adjacent non-rotating structure for operation over a range of speeds and temperatures, comprising:
- an annular sealing ring surrounding a portion of the rotor to define a clearance therewith and being capable of radial expansion and contraction,
- means defining first and second radially inwardly facing surfaces on the ring,
- a first annular control member having a relatively high thermal growth response rate and having means for engaging and supporting at least a portion of the first surface of the ring,
- a second annular control member having a relatively low thermal growth response rate and having means for engaging and supporting at least a portion of said second surface of the ring, the surfaces of the ring and the engagement means on the control members being so juxtaposed that during any rapid increase in the operating temperature of the engine the ring is supported and expanded by the first control member and during any rapid decrease in the engine operating temperature, the ring is supported by the second control member and is constrained to contract at the same rate of contraction as said second control member.
1 more element
Dependencies are inferred from the claim text.