Aircraft gas turbine engine particle separator

Details Aircraft gas turbine engine particle separator Aircraft gas turbine engine particle separator

1991-06-04

1993-04-13

Bertsch, Richard A.

Power plants

Reaction motor

Interrelated reaction motors

F02K 302

Patent

active

052018016

ABSTRACT:
A front fan gas turbine engine subassembly which acts as a particle separator. The subassembly includes an aft-most row of full-size fan blades, a flow splitter, and a row of stator vanes. The flow splitter separates the fan exit air into a core engine airflow and a surrounding bypass airflow. The stator vanes each have a first portion disposed radially inward of, and longitudinally forward of, the leading edge of the flow splitter. The subassembly, in essence, has moved the leading edge of a conventional flow splitter aft without also moving the forward-most row of stator vanes aft. This means that particles which would strike a conventionally-positioned flow splitter and be reflected radially into the core engine airflow will instead miss the aft-moved leading edge of the flow splitter to radially outwardly bypass the core engine airflow.

REFERENCES:
patent: 3528246 (1970-09-01), Fischer
patent: 3536414 (1970-10-01), Smith, Jr.
patent: 3611724 (1971-10-01), Kutney
patent: 3979903 (1976-09-01), Hull, Jr. et al.
patent: 4055042 (1977-10-01), Colley
patent: 4463552 (1984-08-01), Monhaedt et al.
patent: 4881367 (1989-11-01), Flatman
patent: 4900221 (1990-02-01), Ciokajlo et al.
Final Report, "Energy Efficient Engine, Preliminary Design and Integration Studies" by Advanced Engineering and Technology Programs Department, General Electric Company, Prepared for National Aeronautics and Space Administration, Cleveland, Ohio; Sep. 1978, pp. 153, 155, 158, 159, 161.

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