Rotor Assembly For Use In A Turbofan Engine And Method Of Assembling

Abstract: ABSTRACT A rotor assembly (100) for use in a turbofan engine (10) is provided. The rotor assembly (100) includes an annular spool (102) including a blade opening (104) defined therein, and a rotor blade (112) radially insertable through the blade opening (104). The rotor blade (112) includes a rotor blade (112) radially insertable through the blade opening (104). The rotor blade (112) includes a root portion (114) having a dovetail shape, and the root portion (114) is undersized relative to the blade opening (104). At least one secondary dovetail member (118) is positioned within the blade opening (104) and configured to couple the root portion (114) within the blade opening (104) with an interference fit. FIG. 1

Patent Information

Application #

Filing Date

18 November 2016

Publication Number

21/2017

Publication Type

INA

Invention Field

MECHANICAL ENGINEERING

Status

Email

bpo.mail@ge.com

Parent Application

Applicants

GENERAL ELECTRIC COMPANY

1 River Road, Schenectady, New York 12345, United States of America

Inventors

1. KRAY, Nicholas Joseph

GE Aviation, 1 Neumann Way, Cincinnati, OH 45215, USA

2. ANDERSON, Todd Alan

General Electric Company Global Research, 1 Research Circle, Bldg. K1-3A59, Niskayuna, NY 12309, USA

Specification

Claims:As Attached , Description:As Attached