Research/Patents/US 5299914
US 5299914Tier 3 — General Defense

STAGGERED FAN BLADE ASSEMBLY FOR A TURBOFAN ENGINE

Assignee

General Electric

Filed as: GENERAL ELECTRIC COMPANY A CORP. OF NEW YORK

Filed

Sep 11, 1991

Granted

Apr 5, 1994

Location

MIDDLETOWN OH US

Abstract

A turbofan gas turbine engine fan stage having alternating relatively rugged, preferably hollow titanium, blades and staggered relatively less rugged, preferably composite, blades. The blades are staggered such that the leading edges of the rugged titanium blades are positioned forward of the leading edges of the less rugged composite blades. One embodiment provides that all fan blades have trailing edges at the same axial position while another embodiment provides that all fan blades are of the same size and shape.

Source: Google Patents

35 USC §181 Secrecy Order

Imposed

Dec 5, 1991

Rescinded

Jul 20, 1992

Duration

7 months

Inventor

  • 1JAN C. SCHILLING

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Back to patent indexSource: USPTO 35 USC §181 secrecy order records