Patent ID: 9638201
Date: 2017-05-02
CPC Classifications: F02C,F04D,F05D,Y02T,Y10T

Claim:
1. An air bleed system for a jet engine having a low pressure compressor chamber, a low pressure compressor, a low pressure rotor which generates swirling air that impinges on the air bleed system at an angle thereto, an engine core inlet, a fan duct, a combustion chamber and a longitudinal axis, the air bleed system comprising: a stationary bleed case having a forward section, an aft section, and ligaments extending from an inner wall of the forward section to an inner wall of the aft section connecting the forward section and the aft section, wherein the forward section, the aft section and the ligaments together define a series of bleed ports circumferentially disposed around the stationary bleed case and configured to bleed a portion of the swirling air generated by the low pressure rotor from the engine core inlet into the fan duct; a bleed valve connected to the stationary bleed case and configured to open and close the series of bleed ports, the series of bleed ports located between the longitudinal axis and the bleed valve, wherein each bleed port of the series of bleed ports has an angular shape and includes an angled section angled obliquely relative to the longitudinal axis and a radial section extending continuously from the angled section, the angled section further oriented at an oblique angle to a plane defined by the stationary bleed case, wherein the angled section and the radial section are joined at a bend; and wherein each of the ligaments comprises: