Turbine and gas turbine
OwnerTakefumi Hatanakainventor
Life of this patent
Estimating the term…
Abstract
A turbine and gas turbine comprise an annular stator and a turbine rotor rotatably disposed in the stator. The stator includes a tangential inlet to introduce a jet stream of motive gases in a tangential direction, an outlet to exhaust expanded gases, and a plurality of circumferentially spaced and radially extending flow deflectors. The turbine rotor includes an annular jet stream path communicating with the inlet and the outlet, and a plurality of turbine blades circumferentially spaced in close proximity with the annular jet stream path, which accommodates the flow detectors to deflect the jet stream toward the turbine blades.
Claims15
A gas turbine comprising:
- a compressor for introducing compressed air;
- a turbine having an output shaft for driving said compressor;
- and
- a combustor for combusting compressed air and fuel to produce motive gases to drive said turbine;
- said turbine including an inlet to introduce a jet stream of said motive gases in a tangential direction, an outlet for exhausting expanded gases, a stator having at least one flow deflector extending radially inward at a position between said inlet and said outlet, and a turbine rotor rotatably received in said stator, said turbine rotor having an annular jet stream path communicating with said inlet and said outlet to allow said jet stream to run in a circumferential direction, and a plurality of turbine blades formed around a periphery of said turbine rotor in close proximity with said annular jet stream path, and said flow deflector being disposed in said annular jet stream path to deflect said jet stream toward said turbine blades.
A gas turbine comprising:
- a turbine housing having front, intermediate and rear sections;
- a compressor mounted in said intermediate section to produce compressed air;
- a combustor mounted in said rear section for combusting said compressed air and fuel to produce motive gases;
- a turbine located in said intermediate section between said compressor and said combustor and driven by said motive gases;
- and
- an output shaft connected to said turbine;
- said turbine including an inlet to introduce a jet stream of said motive gases in a tangential direction, an outlet for exhausting expanded gases, a stator having at least one flow deflector extending radially inward at a position between said inlet and said outlet, and a turbine rotor rotatably received in said stator, said turbine rotor having an annular jet stream path communicating with said inlet and said outlet to allow said jet stream to run in a circumferential direction, and a plurality of turbine blades formed around a periphery of said turbine rotor in close proximity with said annular jet stream path, and said flow deflector being disposed in said annular jet stream path to deflect said jet stream toward said turbine blades.
Dependencies are inferred from the claim text.