Title:
ACCELERATOR INSERT FOR GAS TURBINE ENGINE AIRFOIL
Document Type and Number:
Japanese Patent JP2017150477
Kind Code:
A
Abstract:
PROBLEM TO BE SOLVED: To provide an accelerator insert for use in a gas turbine engine airfoil.SOLUTION: An airfoil 90 for a turbine engine comprises: an outer wall bounding an interior and defining a pressure side and a suction side that extend axially between a leading edge 114 and a trailing edge 116 to define a chord-wise direction, and extend radially between a root and a tip to define a span-wise direction; at least one cooling air channel defined in the interior extending in the span-wise direction; and an accelerator insert 160 located within and filling a portion of the cooling air channel and leaving an unfilled portion of the cooling air channel that defines an airflow passage 180, where the accelerator insert is shaped to provide the airflow passage with a reduced cross-sectional area 170 that accelerates an airflow through the airflow passage.SELECTED DRAWING: Figure 6
Inventors:
BRIGGS ROBERT DAVID
SHAWN MICHAEL PEARSON
ANDREW DAVID KEMP
GULCHARAN SINGH BRAINCH
SHAWN MICHAEL PEARSON
ANDREW DAVID KEMP
GULCHARAN SINGH BRAINCH
Application Number:
JP2017019230A
Publication Date:
August 31, 2017
Filing Date:
February 06, 2017
Export Citation:
Assignee:
GENERAL ELECTRIC CO GE
International Classes:
F01D5/18; F02C7/18
Domestic Patent References:
| JP2011069359A | 2011-04-07 | |||
| JP2005023936A | 2005-01-27 |
Foreign References:
| US20100054915A1 | 2010-03-04 |
Attorney, Agent or Firm:
Arakawa Satoshi
Hirokazu Ogura
Toshihisa Kurokawa
Takuto Tanaka
Hirokazu Ogura
Toshihisa Kurokawa
Takuto Tanaka