Title:
受動モーフィング構造を備えるタービン翼形部
Document Type and Number:
Japanese Patent JP6374937
Kind Code:
B2
Abstract:
A turbine engine airfoil apparatus, comprising an airfoil (18) defined by a plurality of airfoil sections (36,40,136) arrayed along a stacking axis (34) that extends between a root (20) and a tip (22), wherein at least two of the airfoil sections (36,40,136) spaced apart from each other have differing airfoil section thermal expansion properties. A first section (136) may include a plurality of regions (146,148,150), wherein each of the regions has its particular coefficient of thermal expansivity. Thus, the airfoil (18) may have a static shape at standard atmospheric temperature and a second morphed shape at elevated temperature levels. The airfoil (18) has accordingly a variable camber depending on the fluid temperature. The airfoil is manufactured using an additive manufacturing method such as selevtive laser sintering or direct metal laser melting and the airfoil may be made of a metallic alloy or ceramic powder.
Inventors:
Nicholas Joseph Clay
Narendra Digger Joshi
Samar Giotti Carita
Paul Gerald Maasland
Wayne Allen Spence
Narendra Digger Joshi
Samar Giotti Carita
Paul Gerald Maasland
Wayne Allen Spence
Application Number:
JP2016222018A
Publication Date:
August 15, 2018
Filing Date:
November 15, 2016
Export Citation:
Assignee:
GENERAL ELECTRIC COMPANY
International Classes:
F04D29/38; B22F3/105; B22F3/16; B33Y10/00; B33Y80/00; F01D5/28; F01D9/02; F01D25/00; F02C7/00; F04D29/56
Domestic Patent References:
| JP2015517623A |
Foreign References:
| WO2014105432A1 | ||||
| US4619580 |
Attorney, Agent or Firm:
Arakawa Satoshi
Hirokazu Ogura
Toshihisa Kurokawa
Takuto Tanaka
Hirokazu Ogura
Toshihisa Kurokawa
Takuto Tanaka