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US 2021/0262384 A1Published application
Variable geometry inlet system
AssigneePratt & Whitney Canada Corp.
InventorsMichel LABRECQUE, Vincent COUTURE-GAGNON, Richard ULLYOTT
Life of this patent
Estimating the term…
Abstract
A variable geometry inlet system of an aircraft engine includes an inlet duct. The inlet duct includes at least first and second sections moveable between extended and retracted positions such that the inlet duct defines a variable axial length of an inlet passage for selective flight conditions. The inclusion of acoustic treatment may assist in controlling noise.
Claims6
An aeroengine comprising:
- a compressor section having an axis;
- a combustion section;
- a turbine section;
- and
- a nacelle surrounding at least the compressor section, the nacelle including:
- a main portion in a stationary relationship with the compressor section, the main portion having an annular outer skin and an inner barrel radially spaced apart from each other,
- an inlet cowl having a lip portion with an annular outer skin and an annular inner wall radially spaced apart from each other, the inlet cowl disposed upstream of the main portion with respect to an air flow entering the nacelle through a front opening circumscribed by the lip portion of the inlet cowl, the inlet cowl translatable relative to the main portion of the nacelle between a retracted position in which the annular outer skin of the inlet cowl and the annular outer skin of the main portion of the nacelle are immediately axially adjacent each other and in which the annular inner wall of the inlet cowl and the inner barrel of the main portion are inserted one into the other, and an extended position in which the annular outer skin of the inlet cowl and the annular outer skin of the main portion of the nacelle are positioned axially spaced apart from each other relative to the axis of the compressor section, and in which the annular inner wall of the inlet cowl and the inner barrel of the main portion are inserted one into the other less than the insertion in the retracted position, the annular inner wall of the inlet cowl and the inner barrel of the main portion thereby forming a length-variable inlet duct for directing the air flow toward the compressor section.
4 more elements
A variable geometry inlet system of an aeroengine comprising:
- an inlet duct for directing an air flow from a front opening in the inlet duct to a compressor, the inlet duct having:
- an annular lip circumscribing the front opening, and
- at least first and second sections, the at least first and the second sections movable relative to one another between an extended position and a retracted position, the first and second sections in the extended position defining an axially longer inlet duct than when in the retracted position, the inlet duct extending continuously from the front opening to the compressor in both positions and providing only one inlet path for the air flow from the front opening to the compressor regardless of the inlet duct position, the front opening of the inlet duct having a same diameter in the extended position and the retracted position.
Dependencies are inferred from the claim text.