| US 7,540,709 B1 | ||
| Box rim cavity for a gas turbine engine | ||
| Todd A. Ebert, West Palm Beach, Fla. (US) | ||
| Assigned to Florida Turbine Technologies, Inc., Jupiter, Fla. (US) | ||
| Filed on Oct. 20, 2005, as Appl. No. 11/255,125. | ||
| Int. Cl. F04D 29/08 (2006.01) | ||
| U.S. Cl. 415—173.7 [415/174.5] | 5 Claims |
| 1. In a gas turbine engine having a rotor rotatable mounted about an axis, a blade carried by said rotor for rotation therewith
and nozzles, a seal between each rotor blade and nozzle for inhibiting ingestion of hot gas from a hot gas flow through the
turbine engine into a turbine wheel space, comprising:
a blade platform extending generally in an axial direction from a blade root;
a blade finger extending generally in a radial direction from the blade platform;
a vane platform extending generally in an axial direction from a vane root;
a vane finger extending generally in a radial direction from the vane platform;
a first restriction formed between the blade platform and the vane finger;
a second restriction formed between the first restriction and the second restriction; and,
the blade platform extends beyond the blade finger and forms a third restriction and a second buffer cavity.
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