Abstract: A disclosed gas turbine engine includes a case for a case for a compressor section including a bleed air slot. The bleed air slot includes an inlet having a first area radially inward of an outlet having a second area with the second area being greater than the first area. The bleed air slot further includes a center portion disposed along a radial line extending from an axis of the engine and an elongated portion extending from the opening at an angle relative to a line normal to the radial line.

Abstract: A variable vane assembly comprises an upstream vane stage including an airfoil coupled with an upstream vane stem and an upstream vane arm, configured to drive the upstream vane stem to rotate. The upstream vane stem is supported in an upstream housing boss. A downstream vane stage includes an airfoil coupled with a downstream vane stem and a downstream vane arm, and configured to drive the downstream vane stem to rotate. The downstream vane stem is supported in a downstream housing boss. A first clearance is defined between a radially inner end of the upstream vane arm and a radially outer end of the upstream housing boss. A second clearance is defined between a radially inner end of the downstream vane arm and a radially outer end of the downstream housing boss. A clearance ratio of the second clearance to the first clearance is greater than or equal to 10.

Abstract: A seal is positioned radially outwardly of a compressor blade. The seal has a seal hook facing in a downstream direction. A seal mount has a mount hook for receiving the seal hook in a gap. The hook face in an upstream direction. The seal mount has an upstream portion extending from an upstream end into the gap. The mount hook extends into a web which extends in a downstream direction. A thermal barrier coating on the upstream portion of the seal mount extends to a downstream end. There is a thermal barrier coating on a radially inner surface of the mount hook, and along the web to a downstream coating end. An upstream end of the coating on the inner surface of the hook being formed axially upstream of the downstream end of the coating on the upstream portion.

Abstract: A disclosed gas turbine engine includes a case for a case for a compressor section including a bleed air slot. The bleed air slot includes an inlet having a first area radially inward of an outlet having a second area with the second area being greater than the first area. The bleed air slot further includes a center portion disposed along a radial line extending from an axis of the engine and an elongated portion extending from the opening at an angle relative to a line normal to the radial line.