초록 ▼

A prop-fan of the type having a high solidity factor (1 or greater) near the root fairing to a lower solidity factor (less than 1) near the tip and operable over a critical Mach No. range is designed for sound suppression by contouring the tip so that its sweep and sweep distribution of the leading

A prop-fan of the type having a high solidity factor (1 or greater) near the root fairing to a lower solidity factor (less than 1) near the tip and operable over a critical Mach No. range is designed for sound suppression by contouring the tip so that its sweep and sweep distribution of the leading and trailing edge bears a judicious relationship with the Mach surface. This feature is obtainable by designing the planform from a prescribed linearized or non-linearized acoustic theory and tailoring in the sweep so that the leading and trailing edges fall behind the Mach surface.

대표청구항 ▼

The method of designing the planform of a prop-fan blade whose airfoil section operates at or above a critical Mach No. for reducing its noise level comprising the steps of calculating the planform to obtain the sweep distribution of the blade for obtaining performance and noise level design objecti

The method of designing the planform of a prop-fan blade whose airfoil section operates at or above a critical Mach No. for reducing its noise level comprising the steps of calculating the planform to obtain the sweep distribution of the blade for obtaining performance and noise level design objectives, calculating the Mach surfaces of the leading and trailing edges of the blade in accordance with linearized or non-linearized aeroacoustical theory, sweeping the tip to an intermediate radial blade station so that the blade sweep distribution is such that the leading and trailing edges fall behind the desired leading and trailing Mach surfaces respectively, repeating the step of calculating the Mach surfaces to ascertain whether or not the leading and trailing edges actually fall behind its leading and trailing Mach surface, and repeating the last two mentioned steps until such time as the leading edge falls behind the leading Mach surface and the trailing edge falls behind the trailing Mach surface.