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US 8,998,577 B2Granted
Turbine last stage flow path
AssigneeGeneral Electric Company
InventorsRoss James Gustafson, Gunnar Leif Siden
Life of this patent
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Abstract
The present application thus provides a gas turbine engine. The gas turbine engine may include a turbine and a diffuser positioned downstream of the turbine. The turbine may include a number of last stage buckets, a number of last stage nozzles, and a gauging ratio of the last stage nozzles of about 0.95 or more.
Claims19
A gas turbine engine, comprising:
- a turbine, the turbine comprising:
- a plurality of last stage buckets;
- a plurality of last stage nozzles, wherein a gauging of the last stage nozzles increases from a hub side to a tip side of the last stage nozzles;
- and
- a radius ratio of 0.4 to 0.65;
- and
- a diffuser positioned downstream of the turbine.
4 more elements
A gas turbine engine, comprising:
- a last stage of a turbine, the last stage of the turbine comprising:
- a plurality of last stage buckets;
- a plurality of last stage nozzles, wherein a gauging of the last stage nozzles increases from a hub side to a tip side of the last stage nozzles;
- a last stage flow path therethrough;
- and
- a radius ratio of 0.4 to 0.65;
- and
- a diffuser positioned downstream of the last stage of the turbine.
5 more elements
A gas turbine engine, comprising:
- a last stage of a turbine, the last stage of the turbine comprising:
- a plurality of last stage buckets,
- a plurality of last stage nozzles, wherein a gauging of the last stage nozzles increases from a hub side to a tip side of the last stage nozzles,
- a last stage flow path therethrough,
- a radius ratio of 0.4 to 0.65,
- an unguided turning angle of less than twenty degrees(20°), and
- an exit angle ratio of less than one (1),
- wherein the turbine is configured to result in a degree of hub reaction of greater than zero (0);
- and
- a diffuser positioned downstream of the last stage of the turbine.
7 more elements
Dependencies are inferred from the claim text.