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US 9,004,850 B2Granted
Twisted variable inlet guide vane
AssigneePratt & Whitney Canada Corp.
InventorsJason Nichols, Hien Duong, Peter Townsend
Life of this patent
Estimating the term…
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AssigneePratt & Whitney Canada Corp.
InventorsJason Nichols, Hien Duong, Peter Townsend
Estimating the term…
A compressor for a gas turbine engine with variable inlet guide vanes each defining an airfoil portion twisted such that at each location of the airfoil portion along the pivot axis, an angle is defined between a respective chord extending between the leading and trailing edges and a same reference plane containing the pivot axis and extending radially with respect to the compressor. The angle, which is measured along a direction of rotation of the rotor, varies from a minimum value near the hub side wall to a maximum value near the shroud side wall. A method of reducing vortex whistle in a radial inlet of a compressor is also provided.
A compressor for a gas turbine engine, the compressor comprising:
An inlet guide vane for a compressor of a gas turbine engine, the vane comprising:
A method of reducing vortex whistle in a radial inlet of a compressor having a shroud side wall surrounding a hub side wall thereof, the method comprising swirling a flow along a trailing edge of each one of a plurality of axial inlet guide vanes extending between the hub side and shroud side walls, wherein swirling the flow along the trailing edge includes generating a swirl having a first angle adjacent the hub side wall and generating a swirl having a second angle larger than the first angle adjacent the shroud side wall.
A method of selecting a twist angle of an inlet guide vane for a compressor, the method comprising:
Dependencies are inferred from the claim text.