Title: Gas turbine engine with booster stage

Abstract: A gas turbine engine is provided with a booster stage which operates to increase the power and improve the performance of the engine as well as a particle separator provided at the engine inlet. The booster stage may also eliminate the need for additional anti-icing downstream thereof. The booster is driven at near constant speed by the power turbine of the engine and airflow from the booster is matched to the airflow requirements of the engine by a plurality of variable inlet guide vanes in cooperation with variable bleed means in a manner which maintains the minimum temperature increase of the airflow through the booster required to inhibit ice formation downstream of the booster. In addition, the booster operates to improve the centrifuging effect of the inlet separator, thus eliminating the need for a separate blower for extracting extraneous matter from the collection chamber of the separator.

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Inventors: Hull, Jr., Thomas Neil (Marblehead, MA, US)
Warren, Robert Evans (Marblehead, MA, US)

Application Number: 493506
Filing Date: 1974-08-01
Publication_date: 1976-09-14
Assignee: General Electric Company (Lynn, MA)
Primary Class(es): 60/39.092 55/306, 60/39.093, 60/39.23, 415/145
Other Classes:
US Patent Ref:

2672726	Mar, 1954	Wolf et al.	60/226.
2781634	Feb, 1957	Moore	60/226.
2931168	Apr, 1960	Alexander et al.	60/39.
3166989	Jan, 1965	Cowles et al.	60/39.
3302395	Feb, 1967	Robbins	60/39.
3362155	Jan, 1968	Driscoll	60/39.
3433244	Mar, 1969	Gardiner et al.	60/226.
3436910	Apr, 1969	Haworth	60/39.
3444672	May, 1969	Alsobrooks	55/306.
3514952	Jun, 1970	Schumacher et al.	60/226.
3832086	Aug, 1974	Hull et al.	415/121.

Other Refs: 647,632

Dec, 1950	UK

Primary Examiner: Husar, C. J.
Assistant Examiner: Garrett, Robert E.
Attorney: Lawrence; Derek P., Johnson; James W.