GAS TURBINE DUCTED FAN ENGINE

• US 3,713,748 A
• Filed: 04/19/1971
• Issued: 01/30/1973
• Est. Priority Date: 04/28/1970
• Status: Expired due to Term

• Current Assignee: Kenneth Richard Langley
• Original Assignee: Kenneth Richard Langley
• Inventors: Langley, Kenneth Richard
• Primary Examiner(s): Husar, C. J.
• Application Number:
  US05/135,343
• Time in Patent Office: 652 Days
• Field of Search: 415/77,79,119 60/226
• US Class Current: 415/77
• CPC Class Codes: F02K 3/06 with front fan

Abstract

A gas turbine engine having a multi-stage fan in which the blade rows are spaced apart by at least one and a half chord widths of the adjacent upstream blade to reduce noise. A flow splitter divides the flow through the fan into radially outer and inner flow passages. The first row of stator blades of the fan is reduced in chord width in the inner passage and an additional stage of blading is disposed in the inner passage only, between the first row of stator blades and the second row of rotor blades.

Claims

1. A gas turbine engine comprising a multi-stage fan mounted in an annular flow duct, the fan including first and second rows of rotor blades, a flow splitter which divides the duct into radially inner and outer flow passages, the rows of rotor blades extending across both passages, first rows of stator blades extending across each passage between the rotor blade rows, the rows of blades in at least the outer flow passage being axially spaced from the adjacent upstream blade row by at least one and a half times the length of the chord of the blades in said upstream row, the radially inner passage additionally including a row of rotor and stator blades disposed between said first row of stator blades and the second row of rotor blades.