Patent ID: 9719424
Date: 2017-08-01
CPC Classifications: F01D,F02C,F05D,Y02T,Y10T

Claim:
1. A flow guiding system for an aircraft turbo engine, comprising: an air intake device including an inlet, an outlet and an enclosed passage between the inlet and the outlet, the inlet being connected to a free flowing air stream during operation of the turbo engine to direct a thermal management air stream from the free flowing air stream, the outlet being positioned in a chamber of the turbo engine, a flow guiding device positioned in the chamber spaced apart from the outlet, wherein the flow guiding device comprises a guide surface, the outlet being oriented toward the flow guiding device so that an axis of flow of the thermal management air stream at the outlet is directed toward the guide surface, and the guide surface is oriented such that the axis of flow is deflected by the guide surface toward a target device in the chamber, such that the thermal management air stream impacts the guide surface and is deflected toward the target device, wherein the guide surface is at least one chosen from flat, at least partially flat and at least partially curved.