Gas turbine engine with anti-icing facility

Details Gas turbine engine with anti-icing facility Gas turbine engine with anti-icing facility

1977-05-25

1978-12-19

Casaregola, Louis J.

Power plants

Combustion products used as motive fluid

With safety device

60269, 137 151, 416245R, F02C 704, B04C 1114

Patent

active

041299841

ABSTRACT:
The disclosure of this invention pertains to a gas turbine engine with anti-icing facility. The engine has an axial flow compressor having a rotor hub provided at its upstream end with a nose for dividing the air stream into the compressor. The nose has a pointed conical upstream part of limited angle of divergence where ice formation is minimal. The conical part is followed by a toroidally surfaced concave intermediate part defining a transition from the downstream end of the conical part toward the relatively longer diameter of the hub. The increasing angle of divergence of the intermediate part is progressively more prone to ice formation but is also progressively, more able to throw off the ice by centrifugal force. A convex toroidal part forms a surface blending the intermediate part to the hub.

REFERENCES:
patent: 2540594 (1951-02-01), Price
patent: 3799475 (1974-04-01), Mitchell et al.
patent: 3925979 (1975-12-01), Ziegler

Affiliated with

Also associated with

Rating

Gas turbine engine with anti-icing facility does not yet have a rating. At this time, there are no reviews or comments for this patent.

If you have personal experience with Gas turbine engine with anti-icing facility, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Gas turbine engine with anti-icing facility will most certainly appreciate the feedback.

Rate now

Comments { 0 }

Profile ID: LFUS-PAI-O-2368804