Patent ID: 9611744
Date: 2017-04-04
CPC Classifications: F01D,F04D,F05D,Y02T

Claim:
1. A multi-stage intercooled compressor for a gas turbine engine, including multiple stages of rotating blades and cooling stator vanes, the cooling stator vane including an outer wall that defines an internal coolant fluid passage and has a length along a centerline from a leading edge to a trailing edge of the outer wall, and an internal flow divider wall disposed within the internal passage and extending along the centerline to divide the internal coolant fluid passage into an inflow pathway and an outflow pathway; wherein the multi-stage intercooled compressor includes an outer casing, wherein the outer wall includes a first outer wall and a second outer wall that are connected at the leading edge, the trailing edge and the distal end of the outer wall, and a base end attached to the outer casing, wherein the cooling vane further includes a coolant input connection and a coolant output connection, each extending through the outer casing to provide fluid communication between the internal coolant fluid passage and a coolant condensation and pumping system, and wherein the internal flow divider wall has a base end attached to the outer casing between the coolant input connection and the coolant output connection, and a distal end, and the internal coolant fluid passage is divided into an inflow pathway disposed between the internal flow divider wall and an interior surface of the first outer wall, and an outflow pathway disposed between the internal flow divider wall and the interior surface of the second outer wall, and wherein the distal end of the internal flow divider wall extends toward the distal end of the outer wall with a passage for a coolant fluid to pass around the distal edge of the internal flow divider wall from the inflow pathway to the outflow pathway.