Patent ID: 9677472
Date: 2017-06-13
CPC Classifications: F02C,F04D,Y10T

Claim:
1. A compressor case for a gas turbine engine comprising: a boss including a forward lip and an aft wall; at least two bleed air slots defined within the boss between the forward lip and the aft wall, the at least two bleed air slots spaced circumferentially apart, each of the at least two bleed air slots for communicating airflow from a compressor section, wherein each of the at least two bleed air slots includes an inlet defining a substantially teardrop shape and having a first cross-sectional area, an outlet having a second cross-sectional area greater than the first cross-sectional area, and a length between the inlet and the outlet, the length between the inlet and the outlet being greater than a wall thickness of the compressor case; wherein the substantially teardrop shape of each inlet includes a substantially circular center portion disposed about a radial line extending from a longitudinal axis of the gas turbine engine and an elongated portion coplanar with the substantially circular center portion and extending from the substantially circular center portion at an angle relative to a line normal to the radial line.