Invention Application
- Patent Title: AIRFOIL SHAPE FOR SIXTH STAGE COMPRESSOR ROTOR BLADE
-
Application No.: US15280943Application Date: 2016-09-29
-
Publication No.: US20180087525A1Publication Date: 2018-03-29
- Inventor: Paul G. Deivernois , Sunil Rajagopal
- Applicant: General Electric Company
- Main IPC: F04D29/38
- IPC: F04D29/38 ; F04D29/32 ; F04D29/54 ; F02C3/04

Abstract:
A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
Public/Granted literature
- US10519972B2 Airfoil shape for sixth stage compressor rotor blade Public/Granted day:2019-12-31
Information query