Turbine blade tip clearance system
OwnerAnthony Phippsinventor
Life of this patent
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Abstract
A stage of gas turbine engine turbine blades (22) is surrounded by segments (26) that in turn, are suspended from a flexible casing (24). The inner surface of casing (24) is exposed to compressor flow. On engine thrust being increased, compressor output also increases and rapidly flexes casing (24) radially outwards, thus equally rapidly moving the segments (24) away from the tips of the turbine blades (22).
Claims7
A turbine blade tip clearance system comprising a rigid outer casing and an inner casing having induced flexing capability supported by the outer casing in radially spaced relationship therewith, so as to define an annular space therebetween, and wherein said inner casing supports a ring of arcuate segments within it in fixed radial relationship therewith, such that on placing the whole around a stage of disk mounted turbine blades in coaxial relationship therewith, said segments will lie in radial close spaced relationship with the tips of said turbine blades.
Dependencies are inferred from the claim text.