Title:
シュラウド付きタービン・ロータ・ブレード
Document Type and Number:
Japanese Patent JP7034587
Kind Code:
B2
Abstract:
A rotor blade (16) for a gas turbine (10) that is configured for use within a row of samely configured rotor blades (16) attached to and circumferentially spaced about a rotor disc. The rotor blade (16) may further include an airfoil (25) defined between pressure (26) and suction faces (27); and a midspan shroud (75) comprising a pressure wing (76) and a suction wing (77) extending from the airfoil (25). The pressure wing (76) and the suction wing (77) of the midspan shroud (75) may be configured so to cooperatively form an interface (85) between installed neighboring ones of the rotor blades (16) within the row of samely configured rotor blades (16). The interface (85) may include a first one of the pressure wing (76) and the suction wing (77) disposed as an upstream wing (76) and a remaining other one of the pressure wing (76) and the suction wing (77) disposed as a downstream wing (76). The interface (85) may include the upstream wing (76) and the downstream wing (76) configured as a downstream narrowing step (110).
Inventors:
Michael david mcdaford
Application Number:
JP2016241762A
Publication Date:
March 14, 2022
Filing Date:
December 14, 2016
Export Citation:
Assignee:
GENERAL ELECTRIC COMPANY
International Classes:
F01D5/22
Domestic Patent References:
| JP49120901U | ||||
| JP2009007981A | ||||
| JP55064103A | ||||
| JP2014118974A |
Foreign References:
| US4798519 |
Attorney, Agent or Firm:
Hiroshi Ogura
Toshihisa Kurokawa
Takuto Tanaka
Toshihisa Kurokawa
Takuto Tanaka
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