Jet engine fan and compressor bearing support

Details Jet engine fan and compressor bearing support Jet engine fan and compressor bearing support

1988-12-16

1990-02-13

Garrett, Robert E.

Rotary kinetic fluid motors or pumps

Shaft bearing combined with or retained by arm or vane in...

602261, F04D 2960

Patent

active

049002210

ABSTRACT:
A bypass turbofan jet engine subassembly. A row of structural fan stators and a row of structural compressor guide vanes have their outer ends attached to the engine outer duct. The structural stator inner ends are attached by an inner support cone to the outer race of the fan rolling element bearing and the structural guide vane inner ends are attached by another inner support cone to the outer race of the compressor rolling element bearing. The fan and compressor outer races are interconnected by a tie bar. The subassembly eliminates the engine fan and compressor frames.

REFERENCES:
patent: 3391540 (1968-07-01), Bauger et al.
patent: 3396905 (1968-08-01), Johnson
patent: 3434288 (1969-03-01), Petrie
patent: 3618323 (1971-11-01), Needham
patent: 3620009 (1971-11-01), Wilde
patent: 4287715 (1981-09-01), Klees
F110-GE-100 Engine Airflow Diagram, 2/85 Drawing Date.
Installation Handbook for Turbojet Engines, FIGS. 17-4, p. 314, (General Electric Company, First Printing 5/1952).
35 Year-Old Foreign Engine.
18 Year-Old Pratt & Whitney Presentation.
Exoskeletal Structures Concept.

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