Cooled shroud support

Rotary kinetic fluid motors or pumps – Bearing – seal – or liner between runner portion and static part – Between blade edge and static part

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Details

4151731, 415175, 415177, 415178, F04D 2918

Patent

active

051674874

ABSTRACT:
A shroud support includes an annular casing and an annular hanger spaced radially inwardly therefrom. The hanger includes a circumferentially extending flow duct therein and a base for radially supporting a shroud positionable radially over a plurality of circumferentially spaced turbine blades. The hanger is cooled by channeling a cooling fluid circumferentially inside the hanger flow duct for providing more uniform circumferential blade tip clearance and for better matching the thermal movement between the shroud and blade tips.

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patent: 4759687 (1988-07-01), Miraucourt et al.
patent: 4863345 (1989-09-01), Thompson et al.
GE Aircraft Engines, "Stage 1 Turbine Shroud Support" from CT7 gas turbine engine, single page excerpt from shop manual, on sale in U.S. for more than one year.

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